STUDENT HANDOUT TITLE: AH-64D LONGBOW HELLFIRE MODULAR MISSILE SYSTEM FILE NUMBER:

Transcription

1 UNITED STATES ARMY AVIATION CENTER OF EXCELLENCE FORT RUCKER, ALABAMA 14 June 2011 STUDENT HANDOUT TITLE: AH-64D LONGBOW HELLFIRE MODULAR MISSILE SYSTEM FILE NUMBER: Proponent For This Student Handout Is: COMMANDER, 110 TH AVIATION BRIGADE ATTN: ATZQ-ATB-AD Fort Rucker, Alabama FOREIGN DISCLOSURE STATEMENT: (FD6) This product/publication has been reviewed by the product developers in coordination with the USAACE Foreign Disclosure Authority. This product is releasable to students from foreign countries who have purchased the AH-64D model, but the IETM is not releasable. D-3

2 TERMINAL LEARNING OBJECTIVE: NOTE: Inform the students of the following Terminal Learning Objective requirements. At the completion of this lesson, you (the student) will: ACTION: CONDITIONS: STANDARD: Identify missiles, launcher components, operations, icons, symbology, controls, displays, and safety features of the AH-64D Longbow Hellfire Modular Missile System (LBHMMS). In a classroom environment, given an AH-64D Operator's Manual, Aircrew Training Manual (TC 1-251), a computer with IMI software lesson, and a student handout. Identify the missiles, launcher components, operations, icons, symbology, controls, displays, and safety features of the AH-64D Longbow Hellfire Modular Missile System (LBHMMS) and receive a Go by answering 15 of 20 questions on scoreable unit 3 of criterion referenced test IAW the SEP. D-4

3 A. ENABLING LEARNING OBJECTIVE 1 ACTION: CONDITIONS: Identify the Hellfire SAL and RF missiles. Given a written test without the use of student notes or references. STANDARD: In accordance with TM , TC 1-251, and FM (FM 1-140). 1. Learning Step/Activity 1 Identify the Hellfire SAL and RF Missiles. (a) AGM-114 series Figure 1. Hellfire Air-to-Ground Missile. 1) There are Semi-Active Laser (SAL 1 and SAL 2), and Radio Frequency (RF) models of the Hellfire tactical Air-to-Ground-Missile (AGM) currently in the Army inventory. 2) The missiles are 7 inch diameter, anti-armor munitions with a wingspan of 12.9 inches and, depending on the missile model, weigh 99.2 to 107 lbs with an overall length of 64 to 71 inches. 3) The Hellfire missile is an extremely reliable missile with a Probability of Kill (PK) above 90%. 4) With the new programmable laser codes, dual warheads, and virtually smokeless motors, the Hellfire is among the best AGMs in the world. 5) The guidance section is the main difference between the SAL and RF missiles. D-5

4 (b) Missile types Figure 2. Hellfire Missiles. 1) AGM-114A. The A-model is the original Hellfire missile, which is no longer purchased by the Army. 2) AGM-114C. This missile has an Improved Low Visibility (ILV) capability that allows it to fly lower trajectories than the AGM-114A and contains a minimum-smoke rocket motor (less smoke than the AGM-114A). The missile is 64 inches long and weighs 100 pounds. 3) AGM-114B. This missile is the same as the AGM-114C except it contains a Safe and Arm Device (SAD), which provides electrical and mechanical blockage in the rocket motor firing train, making it approved for U.S. Navy shipboard use. 4) AGM-114F. This missile is the same as the AGM-114C but features dual warheads for improved performance against reactive armor. The missile is 71 inches long and weighs 107 pounds. 5) AGM-114K. One of the newest missiles in the Hellfire family, this missile features dual warheads, electro-optical countermeasure immunity, and a programmable guidance section for trajectory shaping/seeker logic changes. This missile is referred to as the Hellfire II missile. The missile is 64 inches long and weighs 100 pounds. 6) AGM-114L. The RF Hellfire missile uses an active RF signal to detect and track targets. It emits RF energy and homes-in on the reflected RF energy. It is an active (emitting) missile that is inertially guided and radar assisted. The missile is 69 inches long and weighs 108 pounds. D-6

5 Figure 3. Hellfire Dummy and SAL Training Missile. a) The Hellfire missile is also available as a dummy or training missile. 1 M34 dummy missile NOTE: The M34 missile will not show up on the aircraft inventory. a b c The M34 dummy missile has the same external shape and length as the AGM-114C. Internally, it contains no explosives or electronics but has ballast to simulate the weight and center of gravity of the AGM-114C. It is used to train armament personnel in uploading and downloading, and also to simulate a prescribed load of missiles for a specific training flight. 2 M36 SAL training missile a b c The M36 SAL training missile is used for captive flight training and cannot be launched. It has an operational laser seeker that can search for and lock on laser energy. The M36 contains no explosives but should be treated as a live tactical missile. NOTE: If an M36 training missile is on a launcher rail, live missiles will be coded N/A (Not Available) and cannot be launched. D-7

6 Figure 4. Hellfire Missile Common Components. b) Hellfire missile common components. The AGM-114 missile contains a shaped charge warhead that is capable of defeating any known-fielded tank. The maximum velocity of the missile is 475 m/sec (Mach 1.4). The missile is comprised of four major assemblies; the guidance section, the warhead group, the control section, and the propulsion section. 1 Guidance Section. The control interface group includes the missile autopilot, pneumatic accumulator, battery, and displacement gyros used to compute steering command data. The laser seeker converts reflected laser energy from the target into electronic guidance signals. 2 Warhead group a b c d The warhead group houses the warhead and fuse. The fuze, located behind the warhead, contains the ARM/SAFE device that arms the missile when its launch acceleration exceeds 10 G between 150 and 300 meters in front of the aircraft. The AGM-114C possesses a single shape charge to provide the explosive and piercing force necessary to destroy the target. The AGM-114F, 114K, and 114L use the same shape charge warhead but contain an additional small warhead forward of the main warhead to provide enhanced performance against reactive armor. 3 Control section. The control section, located just aft of the rocket motor, receives tracking commands from the guidance section and provides stabilization with a pneumatic actuation system to convert steering commands into mechanical fin movement. D-8

7 4 Propulsion section a b c d The propulsion section provides the thrust to launch and accelerate the missile. It consists of a single-stage, single-thrust, star-shaped, minimum-smoke, solidpropellant rocket motor; a motor squib; and cruciform wings. When thrust exceeds 500 to 600 pounds the missile leaves the rail. Thrust duration is approximately 2 to 3 seconds. Figure 5. c) Environmental Protective Cover (EPC) Environmental Protective Cover. 1 The EPC is a frangible glass dome that provides protection for the missile seeker from environmental elements that can degrade seeker performance. The EPC is removed by a command signal from the Weapons Processor (WP) prior to missile launch. The RF and SAL missile EPCs are not interchangeable. 2 When an EPC is installed on the RF missile, the cover must be removed prior to radar transmission. 3 Pressing the DEICE button will send a squib signal to remove the frangible dome on the next missile in the launch sequence. 4 The DEICE button is only presented when the missile type is SAL, the aircraft is armed, the missile system is actioned, and EPCs are installed. 5 Both missile types have very similar EPCs, with the connectors to the launcher rails being slightly different. D-9

8 CHECK ON LEARNING 1. What is the major difference between the SAL and RF missiles? ANSWER: 2. How will a live missile be coded if there is a M36 training missile loaded on a launcher rail? ANSWER: 3. The fuze contains the ARM/SAFE device that arms the missile when its launch acceleration exceeds g s between to meters in front of the aircraft. ANSWER: 4. When thrust exceeds to pounds the missile leaves the rail? ANSWER: 5. The thrust duration is approximately two to three seconds and the maximum velocity of the missile is. ANSWER: D-10

9 B. ENABLING LEARNING OBJECTIVE 2 ACTION: Identify the components of the M299 missile launcher. CONDITIONS: Given a written test without the use of student notes or references. STANDARD: In accordance with TM , TC 1-251, and FM (FM 1-140). 1. Learning Step/Activity 1 Identify the components of the M299 missile launcher. Figure 6. (a) M299 Hellfire missile launcher M299 Missile Launcher. 1) The LBHMMS is the primary armament of the AH-64D. 2) All variants of the SAL missile and the RF missile can be employed by the aircraft. 3) The LBHMMS consists of M299 launchers mounted on any of the four wing stations. One electrical connector on the hardback connects the launcher with the Pylon Interface Unit (PIU). 4) The PIU interfaces the launcher to the WP. (b) M299 Launcher components. The launcher consists of a hardback, removable Launcher Electronics Assembly (LEA), and four or two low-insertion-force rails. 1) The hardback houses the LEA, the 14-inch spacing bomb lugs, and the mounting points for the four missile rails. 2) The LEA performs the following functions: a) Processes commands from the aircraft to provide missile launch control. b) The ARM/SAFE switch provides for manually safing the launcher. The switch is manually safed and electronically armed via the WPN Utility (UTIL) page LNCHR (launcher) ARM selection. D-11

10 c) A Training Missile Emulator (TME) that can simulate up to four RF missiles on the launcher for training. Live missiles will be coded NA when operating in the train mode. CIU provides launch audio for simulated missile engagements. (c) Pylon Articulation. 1) Pylon Limits. Figure 7. Pylon Articulation. a) The Flight mode commands the pylons to a single fixed position (+4 ). b) Flight mode is automatically commanded at takeoff when the squat switch indicates airborne for more than 5 seconds. c) In flight, the pylons remain in the Flight Mode until missiles or rockets are actioned. Pylons are independently articulated through a range from +4.9 to 15. d) Upon landing, with squat switch activated, pylons move to Ground Stow position of -5º. e) GROUND STOW VAB can be selected on the WPN UTIL page. 2) SAL 3) RF a) When firing SAL missile the pylons are commanded to 6 above the target. b) This will allow A/C pitch angles of greater than 10 before the pylon limit inhibit is invoked, which is a performance inhibit in flight. a) Pylon position is dependent upon range and altitude. b) Minimum altitude for launch of RF missile is 66 feet (20 meters) before the pylons can be articulated down in order to prevent missile from striking ground if radar altitude becomes invalid. D-12

11 CHECK ON LEARNING 1. Can the M299 fire all variants of the Hellfire missile? ANSWER: 2. What component contains the Training Missile Emulator (TME) that simulates RF missile training? ANSWER: 3. What MPD page can you electronically arm the M299 missile launcher? ANSWER: 4. What are the normal pylon articulation limits when the missiles or rockets are actioned? ANSWER: D-13

12 C. ENABLING LEARNING OBJECTIVE 3 ACTION: CONDITIONS: Identify the icons and symbology of the Hellfire SAL and RF missile system. Given a written test without the use of student notes or references. STANDARD: In accordance with TM , TC 1-251, and FM (FM 1-140). 1. Learning Step/Activity 1 Identify the icons and symbology of the Hellfire SAL and RF missile system. Figure 8. (c) Hellfire missile launcher icons Hellfire Launcher Icons. 1) Hellfire missile launcher rail icons will be displayed to indicate that a launcher is present on that wing station. The top missile icons represent missiles on the upper rails; the bottom missile icons represent missiles that are on the lower rails. 2) The launcher rail icons indicate that no missile is at that station or that a dummy missile may be loaded. Dummy missiles (M34) do not show because there is no umbilical connection between the launcher and the missile. All of the launcher status icons will display either a normal or inverse mode, based on weapon system selection or actioned. 3) When a launcher ARM/SAFE switch is in the SAFE position, the white SAFE icon will replace the launcher rail and missile icons on that launcher. This SAFE icon may also be present with the ARM/SAFE switch in the ARM position. 4) If a launcher fails, a yellow FAIL icon will replace the launcher rail and/or missile icons on that launcher. 5) When the launcher is performing BIT, a white BIT launcher icon will be displayed around the launcher icon. The power lever does not need to be positioned in the off position in order for Hellfire on Bit to execute. 6) The white launcher load icon is displayed when the loading of key words to the launcher is in progress. D-14

13 Figure 9. Hellfire Missile Icons. (d) Missile icons. The missile icons are presented in their relative position on the aircraft wings and the missile status will be displayed within each missile icon. 1) The SAL missiles have a straight seeker line across the nose of the icon. 2) The RF missiles have a V seeker line across the nose of the icon. 3) The upper missiles are depicted as forward (on top) of the lower missiles. 4) Missile status and inventory codes are displayed within each missile icon. 5) FAIL is displayed in yellow when the launcher is inoperable. 6) SAFE is displayed when the launcher ARM/SAFE switch is set to SAFE. 7) NA will be displayed for missiles detected as not available. 8) When no missile is loaded on a rail the Empty Launcher Rail Icon will be displayed. D-15

14 2. Learning Step/Activity 2 Identify the icons and symbology of the Hellfire SAL and RF missile system. Figure 10. (a) WPN page missile selection WPN Page Missile Format. 1) If the missile, button is selected, the missile icons will become inverse video, and missile controls will be displayed. 2) The missile legend becomes boxed. 3) Selecting the missile button again will deselect the missiles. 4) If the missile system is actioned, the missile icons will become inverse video, and missile controls will be displayed. 5) The missile legend becomes boxed and nonselectable (barriered), and the other weapons selections (GUN and RKT) will blank. 6) The WAS must be used to deselect the missile system. D-16

15 (b) Missile constraints 1) Constraints boxes Figure 11. Missile Constraint Boxes. a) The missile constraint boxes are dynamic boxes displayed in two sizes. Constraint symbology will be displayed only when the missile system is actioned. b) The boxes apply to both SAL and RF missile launches. c) The missile constraints boxes are displayed in the same manner for SAL or RF missiles, with the inhibits covered under LBHMMS safety features. d) The LOBL constraints box (20 ) will be displayed when the missile system is in a LOBL missile launch mode. 1 For SAL missile engagements, the Laser Range Finder Designator (LRFD) must be designating in order for it to be considered a LOBL missile shot. 2 For RF missile engagements, the RF missiles onboard radar must be tracking the target. e) The LOAL constraints box (7.5 ) will be displayed when the missile system is in a LOAL missile launch mode. 1 For SAL missile engagements in the LO or HI trajectory, constraints are calculated based on the acquisition source chosen from the COORD page. This does not have to be the active acquisition source, but it must be selected as the target source. 2 For RF missile engagements, the RF missile s onboard radar is not tracking the target. NOTE: If the RF missile is tracking and the target range is 1 km, the allowable angle is 20º. IF the RF missile is tracking and the target range is <1km, the allowable angle is 5º. D-17

16 Figure 12. 2) Missile constraints symbology Missile Constraints Symbology. a) In the horizontal plane, the symbology presentation represents a total of 40 (±20 about the center, referenced to the sight reticle). b) The LOBL constraint box is approximately three times larger than the LOAL box. The box position provides steering cues to help align the aircraft with the target. This allows the aircraft to meet the target-offset limits for the type of engagement. 3) LOBL engagements a) The LOBL out-of-constraints symbol is a large dashed box. The missile should not be launched when the constraint box is dashed. b) The LOBL in-constraints symbol is a large solid box. c) The horizontal position represents a ±20 constraints from the aircraft ADL. d) The box is directional; turn toward the symbol to align the aircraft with the target line. e) The box is referenced to the missile seeker LOS with respect to the aircraft ADL. f) The constraints box is driven by the missile seeker. g) When the target is within ±20 of the aircraft ADL, and a missile seeker on the designated PRI CHAN is locked on and tracking reflected laser energy, the symbol will change to a solid box. This indicates in constraints and the missile may be launched. D-18

17 h) At very short LOBL ranges, it is important to adhere to the tighter azimuth alignment requirements. This requirement is not reflected in the LOBL constraint box indication. At these shorter ranges, the pilot should turn the aircraft toward the box, reducing the launch offset angle to less than 5. i) During autonomous LOBL operation, an additional requirement must be met to be within constraints: the tracking missile seeker must be within ±2 of the TADS sensor line of sight to the target to obtain a solid LOBL box. If the TADS LOS and seeker LOS are not within 2º, the message BACKSCATTER will be displayed in the WPNS INHIBIT section of HAD and the missile cannot be launched. To correct the condition turn the laser off and use LOAL DIR with at least 2 seconds delayed designation from missile launch. 4) LOAL engagements a) The LOAL out-of-constraints symbol is a small dashed box. The missile should not be launched when the constraint box is dashed. b) The horizontal position indicates ±7.5 constraints from the aircraft ADL, the box will be dashed when it is positioned greater than approximately one-third of the distance to either the left or right display edge. c) The box is directional. Turn toward the symbol to align the aircraft ADL with the target. d) For LOAL DIR autonomous or remote, the constraints box is driven by the TADS LOS. For LOAL LO and LOAL HI, the constraints box is referenced to the target coordinates stored in the WP, as selected on the target/navigation (NAV) in the Acquisition (AQC) selection, with respect to the aircraft's present position and heading. e) The LOAL in-constraints symbol is a small solid box with the same characteristics as the LOAL out-of-constraints symbol, except that the box is solid. f) When the target is within ±7.5 of the aircraft ADL, the box will be solid, indicating in constraints. g) If visibility is less than 5 km and/or laser delays near the recommended maximum are used, then a +5 offset is recommended. D-19

18 Figure 13. Weapon Action Switches (WAS) 5) Weapon Action Switch (WAS) a) Purpose. The WAS are used to select (action) a weapon system for operation from a specific crewstation. b) Location. WAS is located on both cyclics and on the TEDAC Left Handgrip (LHG). c) Description 1 The WAS is a five-position spring-loaded switch with the missile position designated by a M on the cyclic WAS and MSL on the TEDAC LHG WAS. 2 The missile is selected, from any crewstation, at the 3 o clock position of the WAS. d) Function. Placing the WAS momentarily to the desired position actions the weapon. Placing the WAS to the selected weapon again will deselect the weapon system. Actioning any other weapon position will deselect the current weapon and action the newly selected weapon. 1 The WAS used in the CPG station must be associated with the intended trigger. a b If the weapon is actioned on the cyclic, the cyclic trigger must be used. If the weapon is actioned on the TEDAC LHG, the trigger on the TEDAC LHG must be used. 2 The last crewmember to action missiles will have control. D-20

19 Figure 14. Weapons Triggers 6) Weapons triggers a) Purpose. The weapons triggers are used to fire the selected weapon system. b) Location. The weapons triggers are located on both cyclics and on the TEDAC LHG. c) Description. The weapons triggers are a three-position, two detent switch that are protected from accidental weapons firing by a cover which must be raised to gain access to the trigger. d) Function. The weapons triggers are active in a crewstation only when the ARM/SAFE switch is armed and a weapon has been actioned by that crewmember. Each trigger has two detents. 1 Pressing the trigger to the first detent with no weapon inhibits, the missile will be launched 1 second after trigger pull. 2 Pressing the trigger to the second detent will override weapon performance inhibits and fire the missile. NOTE: Safety inhibits can never be overridden. D-21

20 CHECK ON LEARNING 1. A SAL missile icon that has not been coded will display. ANSWER: 2. RF missiles have a instead of a straight line at the seeker. ANSWER: 3. An RF missile that has an overtemp condition will display. ANSWER: 4. A hangfire will display in the missile icon. ANSWER: 5. If a missile has failed, the icon will display. ANSWER: D-22

21 D. ENABLING LEARNING OBJECTIVE 4 ACTION: Identify the Hellfire SAL missile controls and displays. CONDITIONS: Given a written test without the use of student notes or references. STANDARD: In accordance with TM and TC Learning Step/Activity 1 Identify the Hellfire SAL missile controls and displays. (a) SAL missile controls Figure 15. 1) PRI or ALT CHAN buttons Missile PRI and ALT CHAN CODE. a) The PRI or ALT CHAN buttons are used to designate the PRI or ALT CHAN for coding SAL missiles. b) The ALT button is not selectable when there is no PRI CHAN selected. c) Selecting the PRI or ALT button provides the CHAN options displayed in the CHANNELS status window. d) When PRI and ALT CHANs are selected, the quantity defaults to three for both CHAN if sufficient missiles are available. e) In the NORM mode, the PRI CHAN is allocated the maximum number of missiles before any are allocated to the ALT CHAN. In the MAN mode only the selected missile is coded. Only missiles on the PRI CHAN can be launched. f) In RIPL mode, the quantity is evenly divided between the two channels, with the PRI CHAN assigned the extra missile in the case of an odd number of missiles available. g) As missiles are launched in the RIPL mode, the PRI and ALT labels alternate or switch positions within the PRI and ALT buttons to indicate the automatic PRI and ALT selections on the WPN page. h) PRI and ALT CHAN selections are common to both crewstations. D-23

22 2) SAL SEL Figure 16. SAL Missile Select. a) The SAL SEL button is used to select the type of SAL missile as follows: 1 AUTO allows for automatic selection of a SAL 1 or SAL 2 missile. If the code type is PRF the missile will select SAL 2 first, if available, over SAL 1 missiles. If the code type is PIM the system will select only SAL 2. 2 SAL 1 allows for firing of only SAL 1 missiles. SAL 1 missiles are only capable of PRF laser code operation. 3 SAL 2 allows for firing of only SAL 2 missiles. SAL 2 missiles are capable of PRF and PIM laser code operations. 3) TYPE button a) The TYPE button selection allows for selecting SAL or RF type missiles. b) If the selected sight is FCR, the missile TYPE will be barriered, and the mode will default automatically to RF. c) TYPE selections are independent in each crewstation. D-24

23 4) MODE button Figure 17. SAL Missile Mode. a) The MODE button is used to select the operational mode of the missile system. b) Missile MODE selections are common in each crewstation. c) Missile MODE selections include: 1 The NORM mode will maintain three PRI CHAN missiles ready until the SAL missiles are depleted. 2 The RIPL mode automatically will alternate between the PRI CHAN and the ALT CHAN for missile engagements. The RIPL mode will not be selectable when no missile channel is selected as alternate. 3 The MAN mode allows the crewmember to use the MAN Advance (ADV) switch to select and ready a single missile to the PRI CHAN for firing. D-25

24 5) Trajectory (TRAJ) button Figure 18. SAL Missile Trajectory. a) The TRAJ button is used to select the desired missile launch LOAL trajectory. b) DIR will select the direct LOAL trajectory. c) LO will select the low LOAL trajectory. d) HI will select the high LOAL trajectory. e) If the missile is locked-on before launch, it will default to LOBL and fly the LOBL trajectory. f) TRAJ selections are independent in each crewstation. D-26

25 Figure 19. Range Logic. 6) In either crewstation, the crew will be unable to enter a manual range (from NAV range) when employing SAL missiles with missile trajectory set to LO or HI. The missile constraints box for LOAL LO and LOAL HI engagements are driven from target data located at (B5) except when TRN is the ACQ selection. When TRN is the ACQ selection the missile constraints box is driven by the TRN point. 7) Deice controls Figure 20. Deice Controls. a) The missile DEICE button is used to manually remove the EPC s protecting the SAL missile seekers in preparation for missile launch. D-27

26 b) The DEICE button is only presented when the missile type is SAL, the aircraft is armed, the missile system is actioned, and EPCs are installed. The missile to have the EPC removed when the DEICE button is selected are as follows: 1 MAN mode. The selected missile EPC will be removed. 2 NORM mode. The next missile in the firing sequence on the PRI CHAN will have its EPC removed. 3 RIPL mode. The next missile in the firing sequence on the PRI and ALT CHANs will have their EPCs removed. NOTE: A signal command to remove the missile seeker deice cover is part of any missile launch sequence regardless of the above deice functions. 8) Missile Counter-Counter Measure (MSL CCM) button a) The MSL CCM button enables the CCM routine within the laser missile. b) This selection narrows the Pulse Repetition Frequency (PRF) number of Pulses Per Second (PPS) tracking capability of the missile to the precise PRF of the selected laser code. 9) Laser codes Figure 21. MSL CHAN Set Page. a) Laser codes available for SAL missile coding are presented in the CHANNELS status window located below the aircraft icon. b) The SAL missile CHANNELS status window displays four missile channels for rapid selection. c) The codes selected for the PRI and ALT CHANs are identified with a box around the PRI and ALT CHANs. d) The CHAN page button allows for selection of 16 different missile channel codes. e) Use one of the four CHANNEL buttons to select the code CHANNEL to be changed. When selected, the CHANNEL number will appear in the upper center of the display. D-28

27 f) Press the desired code button to assign that code to the selected channel. g) When all selections are made, pressing the CHAN button will return the display to the WPN page. h) The new codes will be displayed in the missile CHANNELS status window. 10) CODE page Figure 22. CODE Page. a) Selecting the SET button on the CODE page will alternate between Laser Spot Tracker (LST) and LRFD. b) With the desired system (LST or LRF/D) selected, selecting one of the code (A through R, excluding I and O) buttons will assign that code. c) When the desired codes are selected, pressing the CODE button will return the display to the WPN page. d) The CODE RANGE, and keyword status window is located in the center of the CODE, FREQ, and CHAN pages. e) CODE RANGES indicates the laser code ranges that are supported by the laser keywords resident on the Data Transfer Card (DTC). 1 It is capable of supporting the tri-service PRF laser codes and USAF, Hellfire, and Copperhead Pulse Interval Modulation (PIM) laser codes. 2 In order for the LRFD and Hellfire subsystem to use a PIM laser code, the appropriate keyword for the specific code range is required: a b c d e Tri-Service, PRF USAF, PIM Hellfire-A, PIM Hellfire-B, PIM Hellfire-C, PIM D-29

28 f g Hellfire-D, PIM 5000 through 8888 reserved for Copperhead and SAL2 missiles. f) The STATUS area indicates the code range status for the LRFD and Hellfire subsystem. 1 FAIL: indicates the DTC laser keyword for this code range has a checksum error. 2 N/A: indicates that the LRFD and the Hellfire subsystem are not capable of using this code range. 3 MSL ONLY: indicates that only the missile subsystem is capable of using this code range. 4 LRFD ONLY: indicates that only the LRFD is capable of using this code range. 11) CODE FREQ page Figure 23. CODE FREQ Page. a) The frequency of the laser codes may be modified through the CODE FREQ page. b) Selecting the FREQ button on the CODE page will display the CODE FREQ page. c) Selecting a laser code button will enable the Keyboard Unit (KU) to accept a new frequency to be assigned to the selected laser code. d) When the frequencies have been set as desired, pressing the FREQ button will return the display to the CODE page. e) Frequencies of the laser codes may be reviewed by selecting the CODE button and edited by selecting the FREQ button. D-30

29 12) PIM FAULT Advisory Figure 24. Laser Keyword Fail. a) A PIM FAULT Advisory will be displayed on the UFD and MPD if the WP has determined that Laser code keywords are resident on the DTC, but no PIM LEU is installed or that anomalies exist in at least one of the following: 1 LEU upload errors. 2 Individual HF launcher errors. 3 LST upload errors. b) This message will be removed from the EUFD when the CODE page is selected. D-31

30 CHECK ON LEARNING 1. The ALT CHAN button is only selectable after a CHAN has been entered. ANSWER: 2. The quantity defaults to for both channels if sufficient missiles are available. ANSWER: 3. What is the sequence to edit a laser code? ANSWER: 4. What is the tri-service pulse repetition frequency (PRF) code range? ANSWER: D-32

31 E. ENABLING LEARNING OBJECTIVE 5 ACTION: Identify the Hellfire SAL missile operation. CONDITIONS: Given a written test without the use of student notes or references. STANDARD: In accordance with TM , TC 1-251, and FM (FM 1-140). 1. Learning Step/Activity 1 Identify the Hellfire SAL missile operation. Figure 25. SAL Missile Laser Seeker. (b) SAL Hellfire missile laser seeker functions and operational characteristics 1) The SAL Hellfire missile detects reflected laser energy that is of the same code as set into the seeker. 2) It is a passive (non-emitting) missile. 3) The SAL seeker produces steering signals to the missile guidance section when tracking laser energy (target). 4) The signals are acted on by the control section when the missile is in flight, which results in precise homing of the missile body to the laser spot. NOTE: The laser code determines the laser pulse FREQ. Prior to launch, the missile is programmed to receive a specific code. If the designator s code and the code programmed into the missile are not the same, the missile will not acquire or track the target. 5) The seeker detects properly coded laser energy and provides Line-Of-Sight (LOS) information to the WP while on the rail and to the missile autopilot after launch. 6) The seeker detector is gimbal-mounted and gyro-stabilized with a mass composed of the mirror, balance wheel, and a permanent magnet rotor spinning at 4200 rpm. 7) The detector, which does not rotate, has a ±30 gimbal limit from the missile centerline. D-33

32 (c) Operational seeker modes 1) Scan a) The seeker is moved in a predetermined scan pattern (box scan) to help it acquire and lock-on to a laser spot. b) This mode is employed prior to launch for Lock-On Before Launch (LOBL) remote mode and after launch for Lock-On After Launch (LOAL) mode. 2) Stare a) The seeker is commanded to look straight ahead along the missile body axis. b) All missiles, with the exception of the AGM-114K, can acquire and lock on if laser energy is detected. c) This mode is employed prior to launch for LOAL Direct (DIR), LO, or HI remote modes. 3) Slave a) The seeker is commanded to follow external LOS commands. It can acquire and lock on if laser energy is detected. b) This mode is employed prior to launch for all autonomous modes. 4) Track a) The seeker is commanded by the seeker electronics assembly to maintain the reflected laser energy centered on the detector/preamplifier assembly so that the optics assembly is pointed at the target. NOTE: How the missile reacts to loss of designation (loss of pulse correlation) depends on whether the missile is captive or launched and the mode of missile after launch. 5) Captive missile a) For all missiles, the seeker will revert to its selected pre-designation mode if loss of pulse correlation occurs before launch. 6) After launch. a) For all missiles, the seeker gimbal becomes inertially stable upon loss of pulse correlation. The seeker gimbal will continue to point to the same pitch and yaw angle relative to horizontal. D-34

33 Figure 26. (d) LBHMMS launch modes Autonomous/Remote Designation. 1) The LBHMMS may be operated in several different modes or a combination of modes based on the tactical situation and the battlefield environment. 2) When selecting a launch mode for a SAL Hellfire missile engagement, cloud ceiling, battlefield obscurants, range to target, designation delay times, and terrain features must be considered. The combination of these factors will influence the mode that the crew chooses for the SAL missile launch mode. 3) When the crew is engaging a target using SAL missiles, the following modes must be decided upon before the missile is launched. a) LOBL. LOBL modes are used when the SAL missile seeker has already locked onto return laser energy from the target before launch. This return energy can be from the onboard Target Acquisition and Designation Sight (TADS) laser or a remote laser designator. b) LOAL. LOAL modes are designed to allow the missile to be launched without a seeker being locked-on to return laser energy. c) Autonomous engagement. Autonomous designation occurs when the launching aircraft designates its own target. This method of designation may be used in either the LOBL or LOAL modes. For autonomous engagements the sight must be TADS, PRI channel must match the LRFD, and the Laser must be on. d) Remote engagement 1 Remote engagement occurs when the target is designated by an aircraft, other than the launching aircraft, or by a remote, ground-based designator. 2 This designation technique can be used in either the LOBL or LOAL modes. 3 Remote designation allows the launching aircraft to fire from a masked position with a longer standoff range than is possible with autonomous designation. CAUTION During remote designation, the remote designator should not be within a ±30 fan from the gun to target line. D-35

34 (e) Target illumination requirements. The Hellfire missile has a high probability of hitting and killing a target when, the following target designation conditions are met: 1) Illuminating the target by a laser designator that is set to the same code as the missile with sufficient beam intensity that the seeker can detect the reflected energy. 2) Only the laser spot should illuminate the target. 3) When the missile is in its last few seconds of flight before impact, it is critical that the entire laser spot be placed on the target. Even a momentary placement of laser energy on adjacent terrain can prevent the missile from hitting the target if the beam misplacement were to occur during the final few seconds of flight. 4) Once the seeker is tracking, the designator should not be turned off before all in-flight missiles have impacted. The seeker will not reinitiate box scan once the laser energy is lost. Figure 27. (f) Negative factors when illuminating targets 1) Underspill Negative Illuminating Factors. a) Underspill is caused by placing the laser spot too low on the target so that the spot, or a portion of the spot, spills onto the foreground. b) This can cause foreground false target, becoming more severe at long designation ranges. 2) Spot jitter a) The result of motion of the designator or of the beam developed by the designator around the intended aim point. b) This can give the laser spot a bouncing movement on the target, which increases with designator distance from the target. D-36

35 3) Attenuation a) A portion of the laser beam energy that is "scattered" by obscurants along the laser-totarget LOS and the missile-to-target LOS resulting in reduced laser energy to the seeker. b) If attenuation is severe, the seeker will not detect the laser energy from the target. 4) Beam divergence a) The farther the laser designator is from the target, the wider the spot will be on the target. b) The amount of beam divergence will vary between types of designators. 5) Overspill Figure 28. Effects of Overspill and Underspill. a) Overspill is caused by placing the laser spot too high on the target so that beam divergence and jitter cause the spot or a portion of the spot to spill over onto the terrain behind the target. b) This can cause intermittent background false target, becoming more severe at longer designation ranges. 6) Boresight error. The laser spot is not properly aligned with the TADS reticle, producing an error in the location of the spot on the target. NOTE: Even a small number of overspilled or underspilled laser pulses can cause the missile to follow false signals. If this occurs just before missile impact, the probability of a hit is significantly degraded. D-37

36 7) Backscatter Figure 29. Backscatter a) Backscatter is a term that applies to a portion of the laser beam energy reflected off atmospheric particles in the laser path back toward the designator. b) Backscatter energy competes with the reflected energy from the target, so that the seeker may lock-on to the backscatter rather than the target. c) Obscurants (fog, haze, rain, snow, smoke, dust, etc) in the laser-to-target LOS will also produce strong backscatter pulse returns. d) Backscatter can also occur in clear weather. e) Backscatter is much more likely to occur with autonomous lasing because of the proximity of the laser beam to the seeker even in clear (high visibility) conditions. f) If a target return is not detected, the seeker may track the backscatter return. If the seeker is tracking backscatter, the seeker LOS and TADS LOS will differ by more than 2, and the LOBL constraints box will be dashed, indicating an out-of-constraints condition with the message BACKSCATTER displayed in the weapons inhibit. g) Anytime the constraints box indicates an out-of-constraints condition, the crewmembers must correct the condition prior to launch. h) The seeker generally does not track backscatter after track has been established on the true target. i) Backscatter affects LOBL but can also affect LOAL if lock-on occurs too early in flight before the missile has time to climb above the laser beam. D-38

37 (g) Backscatter avoidance technique 1) If the launching aircraft is designating the target, and autonomous operation prerequisites are met, all seekers on the Priority (PRI) Channel (CHAN) will be slaved to the TADS LOS, pointed at the target when TADS is tracking the target. 2) Generally poor target reflectivity, co-located obscurants, or excessive designation cause invalid ranges. 3) If this occurs and the seeker LOS diverges from the TADS LOS by 2 or more, the LOBL constraints symbology will indicate out-of-constraints. 4) If the LOBL constraints box is intermittently switching in and out of constraints, a marginal target condition exists, and the missile should not be launched. NOTE: If primary CHAN track is achieved, and symbology indicates out of constraints, the missile cannot be launched. BACKSCATTER is a safety inhibit. 5) To eliminate a backscatter lock-on, stop lasing the target. Switch to LOAL DIR and use a minimum of 2 seconds of delayed designation from separation (3 seconds from trigger pull). Figure 30. LOBL Autonomous Launch Offset. 6) It is possible for the seeker to switch to tracking backscatter during the first second after missile separation in the LOBL autonomous mode if the target return is lost before the missile has climbed above the laser beam. 7) The aircraft heading should be moved 3 to 5 in the direction of the missile to be launched to ensure that the missile does not fly across the TADS LOS and degrade the TADS imagery. D-39

38 8) False target avoidance techniques a) Erratic range readings by the designating aircraft indicates that the seeker is tracking false targets. b) Backscatter, overspill, and underspill are the primary causes of this targeting error. c) If accurate designation does not correct the problem, the solution is to: 1 Change to a different designator. 2 Change to a different target. 3 Relocate the designator to a new position. (h) Rules for operation in obscurants 1) The launch envelopes defined earlier showed engagement capabilities in a clear environment. 2) Performance is reduced when obscurants degrade the seeker's lock-on range or create false targets. The following rules indicate how to determine if the situation supports a missile launch: a) The designating crew must have a clear image of the target for accurate placement of the laser spot on the target, without overspill or underspill. b) When the launch aircraft has a line of sight to the target, it must have a sufficient image in its TADS for the aircrew to recognize the general shape of the target. If the launch aircraft is masked, the designating aircraft must have a sufficient image in its TADS for the aircrew to recognize the general shape of the target. Otherwise, the seeker will probably not be able to achieve a true target lock-on, even after launch. c) Laser rangefinder readings must be taken by the designating aircraft (especially if FLIR is required to recognize the target), and the missile should not be launched unless steady, plausible range readings are indicated. d) For LOBL autonomous launches, constraints symbology must show in constraints. Otherwise, the seeker is locked-on to backscatter and LOAL DIR should be used with delay designation (2-second minimum from separation). 3) When the previous rules support LOAL launch, the launch aircraft should be aligned as closely as possible toward the target, if designation is remote. For autonomous designation, to assure that the missile does not fly across the TADS LOS, move the aircraft heading 3 to 5 toward the missile to be launched. D-40

39 Figure 31. (i) LOBL requirements and launch strategies 1) LOBL mode requirements LOBL. a) LOBL mode may be used when the target is within the missile LOS prior to launch, with either autonomous or remote designation. b) In this mode, the missile laser seeker has acquired and locked-on to the reflected laser energy from the target prior to launch. c) Missile constraints box is driven by the missile seeker. d) The LOBL mode may be used when the following conditions are present: 1 Direct LOS to the target exists. 2 The visibility conditions allow seeker lock-on at the launch range. 3 The cloud ceiling is higher than the LOBL maximum trajectory altitude for the required range. 4 The threat to the launch platform does not warrant the use of delay designation or launch from a defilade position. D-41

40 Figure 32. 2) LOBL autonomous launch envelope LOBL Launch Envelope. a) The minimum effective engagement ranges with a 0 or 20 target offset angle from the aircraft Armament Datum Line (ADL) are as follows: 1 AGM-114K a b 2 AGM-114C a b 3 AGM-114F a b 500 meters with a 0 target offset angle. 700 meters with a 20 target offset angle. 800 meters with a 0 target offset angle meters with a 20 target offset angle meters with a 0 target offset angle meters with a 20 target offset angle. D-42

41 Figure 33. 3) Nominal LOBL trajectories LOBL Trajectories Versus Cloud Cover. (K-Model) a) The trajectories of the LOBL missile are dependent on range. b) As the range increases, the trajectory altitude will increase as follows: 1 AGM-114K the missile will climb to an altitude of approximately 300 feet for a 3 km target, 500 feet for a 5 km target, and 600 feet for a 7 km target. 2 AGM-114C/F the missile will climb to an altitude of approximately 400 feet for a 3 km target, 1000 feet for a 5 km target, and 1700 feet for a 7 km target. The AGM-114F will be approximately 100 feet lower in this trajectory than the numbers listed. c) The AGM-114K is shown for reference. d) Example: For a maximum-range (7km) LOBL SAL missile engagement, the crew must ensure that they have a minimum of 600 feet above the aircraft launch altitude to ensure cloud clearance for the entire missile time of flight. e) Cloud cover is a major consideration when using SAL missiles. If a K-Model missile enters the clouds, laser tracking is lost. However, the missile seeker will continue to point at the target and the missile will be commanded to turn in the same direction as the seeker, resulting in the missile flying out of the clouds towards the target. This maximizes the probability of target reacquisition for the K-Model missile. Once the SAL 1 (F-Model) missile enters the clouds reacquisition will be unlikely. D-43

42 Figure 34. 4) LOBL Field Of View (FOV) LOBL Remote Horizontal Distance Scan. a) The LOBL FOV depends on whether LOBL remote or LOBL autonomous is selected. b) LOBL remote 1 If LOBL remote operation is selected, the seeker or seekers are scanning and the FOV covered depends on the number of seekers. 2 The FOV of the scanning seekers are controlled by the WP by offsetting the pattern of adjacent missiles. As the range increases, the horizontal distance searched, in kilometers, increases. 3 In the LOBL remote mode, the scan time limits of the seeker are as follows: a b No time limit for continuous-scan operations (1) AGM-114C/F temperatures below 90 F (32 C) (2) AGM-114K temperatures below 125 F (52 C) 30 minute continuous-scan limit (1) AGM-114C/F missiles for temperatures above 90 F (2) AGM-114K for temperatures above 125 F (3) The missiles must be either deselected or placed in the LOAL mode to allow the seekers to cool. The seeker should be allowed to cool for 30 minutes if the tactical situation permits. NOTE: No time limit on the AGM-114C/F/K missiles in any LOAL mode. D-44

43 NOTE: The LOAL discussion will be general and not specific to either autonomous or remote engagements. The data applies to both types. (j) LOAL requirements and strategies 1) LOAL launch considerations Figure 35. LOAL. a) The seeker scans and locates the reflected laser energy after launch. b) This capability allows target designation to be delayed until the missile is closer to the target or to operate in low-visibility conditions, which shorten the seeker's lock-on range. c) It also allows the missile to be launched from an Apache that is hidden from the target by a terrain mask. d) For either remote or autonomous modes, if LOAL DIR, LO, or HI is selected, and properly coded laser energy is received prior to launch, the following occurs: 1 AGM-114C/F/K missile will default to LOBL, and the LOAL constraint box will change to a LOBL box. e) There are three LOAL modes which differ in the trajectory shape and seeker scan pattern. 1 LOAL-Direct (LOAL DIR) 2 LOAL-Low (LOAL LO) 3 LOAL-High (LOAL HI) D-45

44 2) LOAL modes Figure 36. LOAL Direct Mode. a) LOAL DIR: LOAL DIR mode provides the lowest missile trajectory. The LOAL DIR mode may be used when any of the following conditions exists: 1 Direct LOS. Direct LOS to target exists. 2 Low ceiling/visibility. Bad weather (low cloud ceilings and/or visibility) exists. 3 Laser detector on threat. The available threat data indicates, the target may have laser detectors. 4 Backscatter condition. Backscattered laser energy prevents the seeker from lockingon to the proper target before launch in the LOBL autonomous mode. 5 Constraints box is driven by the selected LOS. D-46

45 Figure 37. b) LOAL Direct Missile launch parameters LOAL Direct Launch Envelope. 1 The minimum effective engagement ranges with a 0 or 7.5 target offset angle from the aircraft ADL are as follows: a b c AGM-114K (1) 1500 meters with a 0 target offset angle. (2) 1700 meters with a 7.5 target offset angle. AGM-114C (1) 1900 meters with a 0 target offset angle. (2) 2000 meters with a 7.5 target offset angle. AGM-114F (1) 2000 meters with a 0 target offset angle. (2) 2500 meters with a 7.5 target offset angle. 2 Due to seeker look down limits, the minimum engagement range should be increased as follows: a b Increase minimum range by 500 meters for launch altitudes of 50 to 400 feet above the target. Increase minimum range by 1000 meters launch altitudes of 401 to 800 feet above the target. 3 The maximum effective engagement range that the missile can be launched from is limited by the TADS ability to accurately maintain the laser spot on the target and the seeker's ability to lock-on to the reflected laser energy. 4 The maximum effective engagement range for all missiles is 7 kilometers in the direct mode. D-47

46 5 Ranges beyond the maximum effective range will cause the probability of the missile hitting the target to decrease but does not mean that the missile will not hit the target. Figure 38. LOAL Direct Trajectories c) LOAL DIR trajectories: The maximum effective engagement range for all missiles is 7 km. The nominal LOAL DIR trajectories. 1 The trajectories of the LOAL DIR missiles are dependent upon designation delay and range to target. Longer designation delay times will result in lower trajectories. The AGM-114K is shown for reference. 2 The LOAL DIR mode provides the lowest trajectory and requires an LOS to the target. 3 LOAL DIR is used when low clouds prohibit the use of higher trajectories. It is used in low-cloud conditions and should be used when backscatter is detected in a LOBL autonomous mode. a b AGM-114K. With either a 4 or 12-second laser delay time, the missile will climb to an altitude of approximately 400 feet for a 7 km target. AGM-114C/F. With a 12-second laser designation delay time, the missile will climb to an altitude of approximately 400 to 800 feet with a 4-second delay for a 7 km target. 4 The missile flies lower trajectories for closer target. 5 Changing the laser delay time will change the AGM-114C/F missile trajectories. Short delays will produce higher trajectories than long delays. The AGM-114K trajectory is designed to be low for all laser delay times. D-48

47 Figure 39. LOAL LO Launch Envelope. d) LOAL LO: The minimum effective engagement ranges with a 0 or 7.5 target offset angle from the aircraft ADL are as follows: 1 AGM-114K a b 2 AGM-114C a b 3 AGM-114F a b 2000 meters with a 0 target offset angle meters with a 7.5 target offset angle meters with a 0 target offset angle meters with a 7.5 target offset angle meters with a 0 target offset angle meters with a 7.5 target offset angle 4 Due to seeker look down limits, the minimum engagement range should be increased as follows: a b Increase minimum range by 500 meters for launch altitudes of 50 to 400 feet above the target. Increase minimum range by 1000 meters launch altitudes of 401 to 800 feet above the target. 5 The maximum effective engagement range for all missiles is 8 kilometers in the LO mode. 6 The missile constraints box for LOAL LO and LOAL HI engagements are driven from target data located at (B5) except when TRN is the ACQ selection. When TRN is the ACQ selection the missile constraints box is driven by the TRN point. D-49

48 Figure 40. Nominal LOAL LO Trajectories Nominal LOAL LO trajectories e) Nominal LOAL LO Trajectories 1 The trajectories of the LOAL LO missiles are dependent on designation delay and range to the target. Trajectory for an 8 km target: a b c AGM-114K with a 4 or 15 second laser designation delay time, the missile will climb to an altitude of approximately 800 feet. AGM-114C/F with a laser designation delay of 15 seconds, the altitude is approximately 800 feet. With a delay of 4 seconds, the altitude is approximately 1400 feet. AGM-114F flies about 100 lower than the AGM-114C The missile flies lower trajectories to closer targets. 2 The LOAL LO mode may be used when the missile is required to clear a low mask, which may have been selected by the crew for aircraft protection. Figure 41. LOAL LO Mode. D-50

49 a b Mask may not be higher than 260 feet above aircraft altitude. Minimum standoff distance from the mask is 600 meters. 3 The maximum effective engagement range is 8 km, when the remote designator is close enough for accurate target designation. Figure 42. LOAL HI Launch Envelope. f) LOAL HI. The minimum effective engagement ranges with a 0 or 7.5 target offset angle from the aircraft ADL are as follows: 1 AGM-114K a b 3500 meters with a 0 target offset angle meters with a 7.5 target offset angle. 2 AGM-114C and AGM-114F a b 3500 meters with a 0 target offset angle meters with a 7.5 target offset angle. 3 Due to seeker look down limits, the minimum engagement range should be increased as follows: a b Increase minimum range by 500 meters for launch altitudes of 50 to 400 feet above the target. Increase minimum range by 1000 meters launch altitudes of 401 to 800 feet above the target. 4 The maximum effective engagement range for all missiles is 8 kilometers in the HI mode. D-51

50 Figure 43. Nominal LOAL HI Trajectories g) Nominal LOAL HI trajectories 1 The trajectories of the LOAL HI missiles are dependent on designation delay and range to the target. Trajectory for an 8 km target: a b c AGM-114K with a 4 or 15 second laser designation delay time, the missile will climb to an altitude of approximately 1400 feet. AGM-114C/F with a laser designation delay of 15 seconds, the altitude is approximately 1300 feet. With a delay of 4 seconds, the altitude is approximately 1600 feet. The missile flies lower trajectories to closer targets. 2 The LOAL HI mode may be used when the missile is required to clear a high mask, which may have been selected by the crew for aircraft protection. D-52

51 a b Figure 44. LOAL HI Mode. Mask may not be higher than 1000 feet above aircraft altitude. Minimum standoff distance from the mask is 1500 meters. 3 The maximum effective engagement range is 8 km, when the remote designator is close enough for accurate target designation. 3) Missile approximate flight time Range (km) T= 25 F T = 70 F T= 125 F ( 32 C) (21 C) (52 C) Figure 45. Hellfire Approximate Time Of Flight (TOF) (seconds) NOTE: These flight times are from launch separation. An additional 1 second is required from trigger pull to launch separation. The flight times are also applicable to all missile configurations and launch modes. D-53

52 a) Flight time will vary significantly with air temperature. For example: 1 On a 70 F (21 C) day, missile flight time to an 8 km target is 36 seconds. 2 At 25 F ( 32 C), flight time at the same distance is 44 seconds. 3 At 125 F (52 C), flight time at the same distance is 33 seconds. b) Note that this is a spread of 11 seconds. At shorter ranges, the TOF differences are less but can be significant. c) If the target is suspected of having a laser detector, the amount of time that the designator is held on the target should be kept to a minimum. d) This can be accomplished by delay and/or offset designation. e) The allowable delayed and/or offset designation time depends on the missile TOF to the target at various ranges. f) The time the designator can be delayed is limited by the amount of time the missile must be able to track the target in order to impact on the target. g) For example, at a 7 km target range, the missile TOF on a 70 F (21 C) day is 29 seconds. The designator should illuminate the target between 4 and 13 seconds after missile separation and continue until impact. h) At this range, a period of 7 seconds of steady on-target time (terminal guidance) is required prior to impact. D-54

53 ) Flight, designation delay, and on target times Range (km) *8 7 Approx. Time of Flight from Launch Separation at 70 F (21 C) ** (seconds) NOTE: *Indirect fire only Laser delay after Separation *** (seconds) **** Hellfire Approximate Time of Flight Steady on-target Time (prior to impact) (seconds) ** Additional 1 second is required to allow for the time from launch trigger pull to separation ***Laser designation must be initiated during this time interval. ****Not recommended: Delay times under 2 seconds may cause backscatter lock-on. a) The designation delays indicated are selected so as to maximize the effectiveness of the missile for launches in any LOAL mode. b) Earlier designation will result in higher trajectories for AGM-114C/F but not for AGM- 114K. c) Later designation could cause the missile to fly past the target without locking on. d) To offset-designate while manually tracking, place the M-TADS reticle on a target of at least tank size, about 50 to 100 meters to the front or side of the intended target, while keeping the intended target within the selected TADS sensor FOV. e) To offset-designate while in IAT, the primary target is first tracked using the IAT and then reposition the M-TADS line of sight out of the tracking gates in front or to the side of the target to be designated. f) When maximum delay time is reached, the CPG can select offset to return M-TADS LOS to the primary target to continue designation until missile impact. g) To determine maximum delay time: Take TOF ½ and subtract 2. D-55

54 CHECK ON LEARNING 1. What negative factor during target illumination will cause the laser spot to spill over the target? ANSWER: 2. What are the three LOAL trajectory modes? ANSWER: 3. When the TADS LOS and the seeker LOS differ by more than degrees a BACKSCATTER message will display in the weapons inhibit section of the HAD. ANSWER: 4. The safety inhibit backscatter is generally caused by,, and. ANSWER: 5. If the aircraft is 50 to 400 feet above the target you would increase the minimum range for LOAL launch by meters. ANSWER: 6. Your target is 5000 meters away and you need to clear a mask that is 900 feet above the aircraft, what trajectory would you select to engage that target? ANSWER: 7. For a 5000 meter hellfire engagement the last seconds needs to be steady-on-target time (terminal guidance). ANSWER: D-56

55 F. ENABLING LEARNING OBJECTIVE 6 ACTION: Identify the SAL missile designation modes. CONDITIONS: Given a written test without the use of student notes or references. STANDARD: In accordance with TM , TC 1-251, and FM (FM 1-140). 1. Learning Step/Activity 1 Identify the SAL missile designation modes. (k) Designation strategy Figure 46. Designation Strategy. 1) The Hellfire missile can operate with different designators and operating modes. 2) The selection of the designator and missile modes must be based on the specific mission, enemy, troops, terrain, and time factors for the particular engagement. 3) The following guidelines are suggested: a) Autonomous designation 1 Maximum standoff range a b The launching aircraft should designate the target when the aircraft can fire from a position close enough to the target for accurate designation without extensive exposure of the launching aircraft to the enemy threat. Maximum autonomous designation range, in a clear atmosphere, is limited by the TADS ability to maintain the total laser spot on the target. D-57

56 2 Manual tracking method a b c When manually tracking a target, the TADS reticle should be maintained as close as possible on the base of the turret in elevation and centered laterally, using smooth, deliberate reticle movement with the MAN tracker, avoiding overspill and underspill. Smooth tracking of a steadily moving target can be improved by engaging the Linear Motion Compensator switch on the TADS Electronic Display And Control (TEDAC) Left Hand Grip (LHG). Because MAN track usually produces larger jitter errors than IAT, the maximum autonomous designation standoff ranges with MAN track should be less than with IAT. 3 IAT tracking method a b c d e f g A target can be tracked using the M-TADS either by manually using the MAN tracker or by using the MTT mode. The IAT generally produces more stable tracking (less jitter) than the MAN mode. Therefore, IAT is less likely to illuminate false target or degrade the missile accuracy than a less-stable MAN designation. However, under some target conditions, the IAT can provide a more-stable laser spot on the wrong portion of the target, such as the bottom of the tank hull due to the digital tracker which locks on to specific features of a target. In such cases, if the CPG can recognize that the MTT is tracking the wrong part of the target, the aim point should be adjusted inside the tracking gates reposition M-TADS LOS to desired point and press IAT. If desired aim point is outside tracking gates place M-TADS LOS inside tracking gates and press IAT/OFS to IAT and hold for greater than 0.6 seconds to activate the manual sizing to cover the desired aim point and then release the IAT switch. Position M-TADS to the desired aim point and momentarily select IAT. During daytime and in a clear atmosphere, the Day Television (DTV) provides better tracking than the FLIR. 4 LOBL/LOAL (autonomous) a b c d If the missile is to be launched from the left side, turn the aircraft left; if the missile is to be launched from the right side, turn the aircraft right, past center, until there is a 3-5 offset. The purpose of this offset is to cause the missile to fly an arc outside the TADS target LOS. This will aid in the prevention of both TADS break lock and video washout out in FLIR and smoke obscuration in DTV. Whenever possible, select a missile from the side of the aircraft such that the wind will blow the smoke away from the TADS. D-58

57 b) Remote designation Figure 47. Remote Designation. 1 The portion of the target that is illuminated must be seen by the missile. This requirement imposes a 60 limit on the angle between the gun target line and the remote designator to target line. 2 The probability of killing a target depends on the missile flight path at impact and target attack azimuth but generally is maximized if the laser spot can be held stable on the base of the tank turret. 3 Maximum designation range. Remote designation allows the launch aircraft to stand off at greater distances from the target. This standoff range can be out to the maximum missile effective engagement ranges defined earlier. Remote designation also allows the launch aircraft to be masked from the target, using the LOAL HI or LOAL LO launch modes. 4 Remote designation also allows a single Apache to provide the weapons for other designators. Remote designators may include another AH-64A/D aircraft, OH-58D, Ground Laser Target Designator (GLTD), or one of the various designators of other services or foreign allies 5 Remote designators must be within their maximum designation range from the target, as determined by their laser beam divergence and aiming errors (spot jitter which leads to overspill and underspill). 6 This can vary from one designator type to another. For remote designation by an Apache, the maximum designator standoff ranges are the same as the maximum autonomous Apache standoff ranges defined earlier. D-59

58 Figure 48. c) Remote designator safety Remote Designation. 1 When the remote designator is located in an offset position in azimuth from the launch aircraft, care must be taken to assure that the laser spot is on a section of the target that is visible to the missile. The remote designator should not be displaced more than ±60 in azimuth from the launch aircraft to target line. 2 The remote designator should take precautions to prevent possible injury, which could result from the missile tracking backscatter from the remote designator. 3 The designator should not be positioned within the ±30 fan either side of the launching aircraft to target line or outside the ±60 designator offset angle. NOTE: Offset angles greater than 45 degrees may significantly reduce the missiles ability to acquire laser energy reflected off the target and should be avoided to assure a higher probability of hit. D-60

59 (l) Multiple-missile launch techniques 1) Rapid-fire engagements Figure 49. Rapid Fire. a) Rapid fire is a mode of fire controlled by the PLT or CPG, as opposed to the WP, which involves firing multiple SAL missiles with the same laser code. b) The rapid-fire technique allows a single aircraft to engage several targets with less total exposure time than required for sequential single-target engagements. c) Rapid fire engagements may be employed for autonomous or remote engagements (LOBL/LOAL). d) The first missile is launched at the first target; a second missile is launched (on the same laser code) 8 seconds after the first, and a third missile could be launched 8 seconds after the second. e) Subsequent missiles launched will be flying to the same target as the previous missile or to the spot transitioning over the foreground to the next target. f) When the first missile impacts on the first target, the laser spot is moved to the second target and held until the second missile impacts. g) A single Apache in one engagement may fire the entire load of missiles, each with 8- second spacing, using the rapid-fire mode. h) To use this technique, the targets should be relatively close (approximately 100 meters maximum separation for missiles launched 8 seconds apart). i) This will allow time for the second missile and subsequent missiles to correct their flight path to the new target. j) When manually tracking, the MAN tracker is used to slew the designator from the first target to the second target. D-61

60 k) The spot movement must be smooth and deliberate over a 1 to 3 second interval. l) During the movement, the spot must continuously illuminate the foreground between the targets (not a background tree line or hill that could be a considerable distance behind the target). m) The closest target should be engaged first, unless smoke from the first missile impact would obscure the second target. NOTE: In rapid fire, if designation commences before the second missile is launched, the second missile will fly the LOBL flight trajectory even if LOAL was previously selected. 2) Ripple (RIPL) fire engagements Figure 50. Ripple Fire. a) When two designators are available (which may or may not include the launch aircraft), two missiles may be fired against two targets (both targets within the missile s footprint) without the 8-second launch delay. b) This is accomplished by using the RIPL fire technique. c) With RIPL fire, the SAL mode option on the WPN page is set to RIPL, the PRI CHAN is set to the laser code of one of the designators, and the Alternate (ALT) CHAN is set to the code of the second designator. d) One missile from the PRI CHAN may be launched, then a missile from the ALT CHAN may be launched 1.5 seconds later. e) Each pair of missiles is actually the result of two trigger pulls, so that the second missile may be fired 1.5 seconds after the first. f) Each missile will fly toward its own target. g) Performing multiple launches in this mode is quicker than in rapid fire and does not involve the process of slewing laser spots while the tracking missiles are in flight. h) Prelaunch coordination between the launch platform and the remote designator is required. D-62

61 CHECK ON LEARNING 1. What is the maximum offset limit between the gun target line and the remote designator to the target line? ANSWER: 2. Maximum autonomous designation range is limited by the. ANSWER: 3. During remote designation, the remote designator should not be within a ± fan from the gun to target line. ANSWER: 4. During rapid fire engagement the maximum separation between targets should not exceed meters, with at least an second separation between missile launches. ANSWER: 5. In the Ripple mode, after the primary channel missile is launched the alternate channel ANSWER: missile may be launched after seconds separation. D-63

62 G. Enabling Learning Objective 7 ACTIONS: Identify the Hellfire RF missile controls and displays. CONDITIONS: Given a written test without the use of student notes or references. STANDARD: In accordance with TM , TC 1-251, FM (FM 1-140). 1. Learning Step/Activity 1 Identify the Hellfire RF missile controls and displays. (a) RF missile controls 1) Missile mode Figure 51. RF Missile Mode. a) The MODE button is used to select the operational mode of the missile system. b) Missile MODE selections is common in both crewstations. c) Missile MODE selections include the following: 1 The NORM mode powers RF missiles according to the missile PWR selection. 2 The MAN mode allows the crewmember to use the MAN ADV switch on the TEDAC right handgrip or collective to select and power a single RF missile for firing. This mode also allows the crew to advance manually through the RF missiles to select a desired missile for power application. 3 When the MAN mode is selected, the missile PWR selections are removed. D-64

63 Figure 52. RF Missile Power Options. 2) Missile POWER options a) The missile POWER grouped option buttons are used to manage the power requirements of the RF missiles. b) The RF missiles could go into an over temperature condition if they stay powered continuously. c) The missiles also can overheat if they are radiating (tracking) a target for more than 3 minutes. d) This is a cumulative time that will overheat a missile if adequate time for cooling is not allowed. 1 The ALL button will power-up all available RF missiles. There is no automatic power management in the ALL mode; missile can overheat and display the OT in the missile icon. 2 The NONE button will remove power from all RF missiles. 3 The AUTO button will enable automatic power management. The number of missiles powered is based on the total RF missile inventory available. In the AUTO mode, missiles will be powered up at 10-minute intervals. This does not occur when the missiles are actioned. D-65

64 e) RF missile PWR selection is common to both crewstations. Missiles Available Missiles Powered 8 or more 4 4 to to Automatic RF Missile Power Management Figure 53. LOBL Inhibit and 2 ND Target Inhibit. 3) LOBL INHIBIT button a) The LOBL INHIBIT button will inhibit the missile from radiating prior to launch. b) Selecting the LOBL INHIBIT button will mode the RF missile system to fire the RF missiles in a LOAL mode. c) This capability reduces or eliminates the RF signature on the battlefield and allows for firing missiles at FCR LOBL targets from a defilade position. 4) 2ND target INHIBIT button a) The 2ND target INHIBIT button prevents the FCR from assigning secondary target data to the missile during FCR target handover. b) When receiving stationary LOAL target assignments in the prelaunch mode, a missile will receive two target positions. This will provide the missile with an additional target in the event it loses track of the initial target. D-66

65 c) This feature could be necessary when friendly targets are possibly near the engagement area. If friendly vehicles are in the vicinity of the target being engaged, it is possible that the missile could target the friendly vehicle if missile tracking is lost. d) Normally, the missile will search for a second target if it loses tracking on a primary STI and cannot reacquire it within a prescribed time period. 5) Loading of RFmissiles should be balanced between both sides of the aircraft, primarily on outboard launchers. The WP determines missile selection and firing order. No more than two RF missiles are allowed to actively track targets simultaneously. The WP will always keep the NTS and ANTS missiles on opposite sides of the aircraft to avoid interfering with each other when radiating. If missiles are only present on one side, only one missile will be assigned a target D-67

66 CHECK ON LEARNING 1. The missile MODE selections are in each crewstation. ANSWER: 2. In the AUTO power mode, the missiles are powered-up at minute intervals. ANSWER: 3. 2 ND Target INHIBIT selection is used for targets? ANSWER: 4. The RF missiles can overheat (OT) if it is radiating (tracking) a target for more than minutes. ANSWER: 5. How many missiles will be powered with 6 missiles on board with the AUTO power mode selected?. ANSWER: D-68

67 H. ENABLING LEARNING OBJECTIVE 8 ACTION: Identify the RF Hellfire Missile Operation. CONDITIONS: Given a written test without the use of student notes or references. STANDARD: In accordance with TM , TC 1-251, and FM (FM 1-140). 1. Learning Step/Activity 1 Identify the RF Hellfire missile operation. Figure 54. RF Missile Operation. (a) RF missile modes 1) The RF missile operates in three modes: a) Standby b) Prelaunch c) Postlaunch D-69

68 Figure 55. RF Missile Operation. 2) Standby mode a) On aircraft power up, the missiles begin a startup process. During startup, the missiles initiate a power-up sequence; initialize in the standby mode; perform a Power on Built-in- Test (PBIT); and inform the WP that startup is complete and they are in the standby mode. When the outside air temperature is below -20 degrees C, the system will perform a power cycling of the missiles to prevent an under-temp condition. The AUTO missile power mode will prevent an overtemp condition by cycling power in 10 minute intervals. b) The missile will remain in the standby mode until it receives target handover data from the WP. D-70

69 Figure 56. RF Missile Transfer Alignment c) A Transfer Alignment (TA) is completed immediately after the PBIT sequence. TA allows the missile to receive continuously updated inertial position (present position), acceleration, and velocity data from the aircraft to align its own Inertial Navigation Unit (INU). d) The TA process accounts for known mechanical alignments between the systems, pylon articulation, and communications delays. e) The attitude and velocity of the aircraft are maintained during the TA function. While the missile is in the standby mode and transfer alignment is complete, it will display an R in its missile icon. f) TA compares attitude and velocity measurements from the aircraft Embedded GPS Inertial (EGI) to the missile Inertial Navigation System (INS) and updates it to the aircraft reference. g) Information included in the TA message is as follows: 1 Pitch and roll angle 2 True heading angle 3 Aircraft longitudinal, lateral, and vertical velocity 4 Inertial Navigation Unit (INU) time tag 5 Pressure and density altitude 6 Static temperature 7 Pylon position relative to Armament Datum Line (ADL) 8 Pylon position time tag (articulation with ACFT (aircraft) pitch and roll rates) 9 Aircraft pitch, roll, and yaw rate 10 Aircraft estimated heading error D-71

70 3) Prelaunch mode Figure 57. RF Prelaunch. a) Actioning the missile system Weapons Action Switch (WAS) with acceptable target data will initiate the missile prelaunch mode. b) Prelaunch mode occurs from the time the WP transfers target data to the missile until the missile is either launched or returned to the standby mode. Figure 58. FCR Target Handover D-72

71 c) The WP provides the missile target data three ways: 1 From the aircraft own FCR a b c d When the selected sight is FCR, and the 2ND target INHIBIT mode is not selected, the WP transfers target data for both a primary and secondary target when the targets are detected. If the primary target is stationary, a second stationary target may be supplied to the missile. This is the only mode of the three that supplies a secondary target. If the Hellfire system is actioned prior to an FCR scan, the WP initiates the target handover data at the completion of the scan. If the Hellfire system is actioned during an FCR scan, the WP immediately initiates target handover data of the Next-To-Shoot (NTS) target based on the targets detected up to that point, with subsequent Alternate Next-To-Shoot (ANTS) target data occurring after completion of the scan. Figure 59. TADS Target Handover 2 From the TADS a b c d When TADS is the selected sight, and the actioned missile type is RF, the TARGET DATA? will be displayed I the sight status section of the HAD. The target must be designated for approximately 3 seconds to receive the target handover data and remove the TARGET DATA? message. If the laser data is erratic, the message will not be removed, and the target handover data will not occur until, valid range is acquired. Upon TADS target handover to the RF missile, target velocities will be zeroed if the target velocities are under a specific threshold. This will more accurately reflect a stationary target. D-73

72 Figure 60. IDM Handover 3 From the Improved Data Modem (IDM) in the form of an RFHO a b c When the RFHO is received via the IDM RFHO, and the mission is accepted, the target handover data represents the target North-East-Down (NED) grid coordinates relative to the receiving aircraft. To receive an IDM RFHO in an aircraft with or without radar, you must have the FCR as your selected sight, and the missiles actioned. In a non-fcr aircraft, you must press the REC (receive) BTN (button) on the Tactical Situation Display (TSD) page prior to selecting the FCR as your sight; if not, the message FCR NOT INSTALLED will be displayed when selecting FCR prior to pressing the REC BTN. In this case, you will not receive the RFHO. The only timeout associated with a handover is the receiving aircraft must receive the RHFO within six minutes of the of the RFHO target data being received in the aircraft s IDM buffer. DATA INVALID message will be displayed in the HAD. d) Target handover data contains the following information: 1 Target status: ID, target type (air/ground), LOBL inhibit (on/off) 2 Target detection time: Time from initial detection until current update 3 Target update time: Time since last update 4 Target NED position: NED at time of detection 5 Updated NED position: NED position at update time 6 Target NED velocity 7 Crossrange: target handover data for crossrange 8 Height: target handover data for height 9 Range: target handover data for range D-74

73 10 Range rate: target handover data for radial velocity 11 Cross-range: target handover data for crossrange velocity 12 Aircraft time at request e) Target assignment Figure 61. Target Assignment. 1 The Longbow RF missile is capable of engaging moving and stationary targets at a range between 0.5 and 8 km. 2 After the WP transfers target NED data to the missile, the missile determines the launch mode, either LOBL or LOAL, based on target velocities (moving or stationary) and range to target. 3 The FCR target symbols that are displayed do not determine the type of missile mode for launch (that is, LOBL or LOAL). Therefore, it is possible to launch a LOBL missile at a LOAL target symbol and vice versa. 4 If the missile determines the target requires a LOBL acquisition, it will attempt to acquire it by radiating three times for approximately 3 seconds each. 5 During LOBL engagement, if the missile radar fails to acquire the target after three attempts, the radar will transition back to standby, but the inertial tracking of the target will continue. 6 Actioning the missile system again would allow for three more scan attempts on the same PRI target. f) RF missile LOBL and LOAL determination 1 Although the RF missile has the final authority whether it should be launched LOAL or LOBL, it generally follows a predetermined set of rules. a Moving target. All moving target are processed as Moving target Indicator (MTI) target and should be assigned as LOBL engagements from the minimum range of 500 meters to the maximum range of 8000 meters. D-75

74 b Stationary target. Stationary target assignments are processed as Stationary Target Indicator (STI) and are broken into three range areas, which include the following: to 1000 meters a. Targets are too close for an LOAL engagement and must be made a LOBL engagement. (out-of-constraints LOBL box). b. When the missile to target range or target motion requires a LOBL trajectory and a NO TRK occurs, the NO ACQUIRE message will appear in the weapons inhibit section of the HAD and this safety inhibit will preclude the missile from being launched to 2500 meters a. An RF missile will try to acquire while displaying an LOAL box for targets between 1000 and 2500 meters. b. If the missile acquires the target, it becomes LOBL box and will be made LOBL engagement. If no acquisition is made, the LOAL is authorized. This range uses High Range Resolution (HRR) for STIs to 8000 meters a. Targets between 2500 and 8000 meters will be LOAL using Doppler Beam Sharpening (DBS). b. RF missiles can only receive a target handover data from the TADS or via RFHO for a target between 6000 and 8000 meters because the FCR is unable to process stationary targets at ranges greater than 6000 meters.. Figure 62. RFHO Delay. D-76

75 g) Target handover delays 1 Missile performance against moving and stationary target is a function of many factors. The most important factor is the RFHO error at the start of the target acquisition process. 2 The target handover data error grows as the time between FCR detect and the missiles receipt of the target handover data increases. 3 In the example above, the time between accepting the IDM RFHO and the time the actual target handover data occurs (WASing) could cause an acquisition attempt in the wrong area. 4 It is very important to minimize this handover latency for best performance; however, the missile does optimize its performance by selecting the appropriate acquisition mode and submode for best target detection and tracking performance based on handover latency and initial target RFHO error. 4) Postlaunch mode Figure 63. RF Postlaunch Mode. a) The postlaunch mode is initiated when the firing command (weapon trigger pull) occurs. b) The WP verifies launch constraints (safety and performance inhibits, launcher and missile Built-In-Test (BIT) status, missile gimbal angles, and RF tracking status for LOBL missiles and, if no constraints are active, issues the release consent message to the launcher. c) Once the release consent message is received, the launcher issues the launch command to the designated missile and, at the same time, issues commands to enable the missile battery and pneumatic actuator control system. D-77

76 d) When the launch commands are received by the missile, the system mode transitions to postlaunch. e) The launcher verifies battery power and, if valid, digital communication with the missile ceases and the motor fire command is sent to the missile. f) The missile achieves separation and leaves the rail approximately 1 second after the launch command is issued. g) The warhead is armed when the missile achieves 10 G acceleration (150 to 300 meters). D-78

77 2. Learning Step/Activity 2 Identify the RF Hellfire missile radar modes. (a) RF missile radar modes Figure 64. RF Missile Radar Modes. 1) The target acquisition and tracking modes are terms used to explain the different ways the missile seeker improves its chances of locating and hitting LOBL and LOAL targets. 2) The missile radar has three target acquisition modes tailored to specific target characteristics. All modes require target handover data from the WP. 3) The missile has three acquisition modes: a) Terminal Track Acquisition (TTA) Used for short-range stationary target LOAL and LOBL. b) Preterminal Acquisition (PTA) Used for long-range stationary targets LOAL. c) Moving Target Acquisition (MTA) Used for moving target LOBL. 4) The missile has two tracking modes: a) Preterminal Track (PTT). Used for tracking of medium-to-long-range stationary and moving targets. b) Terminal Track (TT). Performs the final phase tracking of stationary and moving targets. D-79

78 Figure 65. High Range Resolution. (b) Missile acquisition modes. The two stationary-target acquisition modes (TTA and PTA) use different types of processing to separate targets from the surrounding clutter, based on range. 1) TTA a) The TTA mode utilizes HRR to process target from 0.5 to 2.5 km for both LOBL and LOAL short-range targets. b) The missile cannot perform DBS trajectory on short-range targets under 2.5 km. c) HRR is utilized to detect stationary targets in ground clutter by providing much tighter range bins per range gate. d) This technique produces a much better resolution of the designated target. e) With smaller range bins, this mode assists target detection by measuring the size of the radar return for comparison with target handover classification. f) The LOAL mode is exercised at ranges greater than 1 km to meet performance requirements for longer-range HRR operations and reduced Radar Cross Section (RCS) targets. g) For targets between 1 and 2.5 km a LOAL status will be supplied to the launch platform; however, the radar will immediately attempt to acquire and track the target LOBL. h) This is why between the ranges of 1 and 2.5 km the missile mode can be either LOAL or LOBL. D-80

79 Figure 66. Doppler Beam Sharpening. 2) PTA. PTA is designed to acquire long-range stationary target in the LOAL mode at ranges between 2.5 to 8 km using a technique called DBS. a) DBS 1 DBS uses a curved trajectory to induce relative motion between a stationary target and its background by flying an off-axis flight path to the target. DBS significantly enhances the probability of detection and tracking stationary targets at long ranges. 2 Standard Doppler processing (missile flying direct to the target) would cause a stationary target to be included in the same Doppler bin as all of the main lobe clutter return since both types of return exhibit the same relative range rate. 3 DBS, due to the angular difference between the missile s forward velocity vector and the target LOS, causes the relative range rate of the target to be different than that of the background, spreading the return over many Doppler bins. 4 The resulting spread increases the target signal-to-clutter ratio in the target Doppler bin, enabling the radar to identify and locate the target. 5 DBS is selected for ground-clutter rejection during stationary-target PTT or when a target that was initially an MTI has become an STI during flight. If this occurs, the missile would switch from a straight trajectory to a DBS trajectory in flight. 6 There are two constraints involved when the missile evokes the in-flight DBS option: a b First, the switch is not allowed near the terminal phase, where missile kinematics cannot support the trajectory switch. Second, the trajectory will not switch from DBS back to a straight trajectory. The probability of an in-flight DBS is very low. D-81

80 b) DBS trajectory Figure 67. DBS Trajectory. 1 The missile does not always turn in the same direction when DBS occurs. The direction of the turn is determined at umbilical separation as a function of the LOS to the target. Missiles launched from either side of the aircraft will follow the same trajectory, based on the following data: a b c If the target is right of the missile centerline, the missile trajectory curve will be a left DBS trajectory to the target. If the target is left of the missile centerline, the missile trajectory curve will be a right DBS trajectory to the target. Targets close to the zero bearing may yield either a left or a right DBS trajectory. 2 In the event the missile loses radar track of the target, it will shift to DBS in an attempt to reacquire the target. 3 The primary parameters used to determine the extent of the DBS trajectory are the inertial guidance data of the missile (where it is at that instant), the last known point of the target (point the missile is tracking to), and, for moving targets, the last known velocity of the targets. 4 In the event the missile does not reacquire the target, it will use inertial guidance to fly to the calculated target location. D-82

81 c) Step scanning Figure 68. Step Scanning. 1 If a break lock occurs after launch against an STI, the PTA will exercise the reacquisition mode. 2 The reacquisition mode includes several PTA attempts over a series of azimuth antenna positions and range positions (step scanning). 3 The reacquisition sequence is repeated until the target is acquired or until the terminal track phase range is reached. 4 Azimuth scanning is required for LOAL operation in order to provide an adequate probability of the target being in the seeker angular FOV. D-83

82 Figure 69. d) Secondary target handover Secondary Target Handover. 1 During stationary target handovers, the FCR has the capability to handover two targets to the same missile. If the FCR acquires two targets with zero velocity within a certain footprint, it may supply both target vectors to the missile. Figure 70. Secondary Target Symbol. 2 A second target symbol will be displayed on the FCR and TSD page to indicate the second target was passed to the missile. 3 The secondary target will only be used if postlaunch acquisition or reacquisition of the primary target fails. D-84

83 4 The secondary-target position data, which is sent from the platform through the launcher via the secondary-target message, is a NED vector from the primary-target location. 5 This can only occur with stationary targets; the missile cannot calculate positions for two separate target handovers if either the primary or secondary targets are moving. 6 Once a reacquisition cycle (step scanning) is complete, the primary target was not found, and if a secondary target has been assigned, the missile will shift trajectory to the secondary target position. 7 In the event the missile does not acquire the second target, it will use inertial guidance to fly to the calculated location of the second target. 8 Do not confuse the primary and secondary target handover with the FCR NTS and ANTS target. 3) MTA Figure 71. Spotlight and Scan Submodes. a) MTA performs acquisitions on all moving targets. This mode uses Doppler processing created by the target velocity and operates from 500 to 8000 meters. b) Spotlight and Scan are both sub-modes of the MTA radar mode. The missile automatically selects the spotlight or scan submodes for MTA, based on the quality of the target handover data. c) RFHO data quality is the estimate of how well the aircraft acquisition sensor (FCR, TADS, IDM) was able to measure the position of the target. D-85

84 1 Spotlight submode a b The spotlight submode is selected when precision RFHO data is provided along with minimum handover latency. This submode acquires moving targets by maintaining the center of the antenna beam and range gates over the inertially tracked target position while collecting several dwells of radar data. 2 Scan submode a b The scan submode is selected when a nonprecision target handover data (based on RFHO quality and latency) is received. This submode acquires targets by collecting radar data while scanning over a scan width in azimuth that is calculated to encompass the crossrange region most likely to contain the target. Figure 72. Missile Track. d) Radar missile track modes. There are two radar track modes which use different signal processing to track targets. Both modes track moving and stationary targets; however, PTT employs DBS, while TT uses HRR. 1 PTT a b Performs tracking of medium-to-long-range stationary and moving targets Operates on the rail out to the TT mode and uses multiple trajectories and DBS to maximize target detection D-86

85 2 TT a b c d Performs the final phase tracking of stationary and moving targets Uses HRR processing to improve the aimpoint accuracy through missile impact If the missile is unable to acquire the primary target, it will continuously cycle through the reacquisition mode until it either reacquires the target or reaches a minimum range. Once the minimum range is reached without reacquisition, the missiles will transition into the TT mode and fly to the target last-known point. D-87

86 3. Learning Step/Activity 3 Identify the RF Hellfire missile trajectories. (a) RF missile trajectories Figure 73. RF Missile Elevation Flight Profiles. 1) Elevation flight profiles for moving LOBL and stationary LOAL targets: a) The RF missile flies a trajectory that is optimized for radar performance while maintaining lethality. The LOBL and LOAL elevation flight profiles are similar. b) The RF missile generally flies a higher trajectory than the SAL missile. Clouds are not a factor when employing an RF missile. The missile has its own onboard radar system that allows it to see through clouds. c) If the missile is tracking an STI and loses radar track, reacquisition failures may result in the missile changing its target to a secondary target passed to it in the prelaunch mode. D-88

87 Figure 74. (b) LOBL moving target azimuth flight profiles Direct Trajectory for RF LOBL/20 Degree Offset. 1) The missile flies a very direct azimuth flight profile for LOBL operations. 2) If the target becomes stationary after launch, the missile may fly an off-axis trajectory in an attempt to reacquire the target (DBS). 3) The illustration shows a direct trajectory relative to a trajectory with a 20 offset angle. The missile can fly out to 100 meters with an extreme offset angle because of the missile s initial energy before the guidance section can get the missile headed toward the target. 4) As the offset angle decreases, the trajectory is closer to the armament datum line. D-89

88 Figure 75. (c) LOAL stationary target azimuth flight profiles Stationary LOAL RF Missile Trajectories. 1) The LOAL azimuth flight profile is driven by a DBS trajectory, which is used for medium-to long-range stationary targets. This illustration shows trajectories with 1 and 20 offset angles. NOTE: Increasing the offset angle will slightly increase the distance of the trajectory from the armament datum line. D-90

89 CHECK ON LEARNING 1. What are the three RF missile modes? ANSWER: 2. Transfer alignment occurs in the missile mode. ANSWER: 3. In the pre-launch mode what are the three methods of target handover data to the RF missile? ANSWER: 4. Doppler Beam Sharpening (DBS) uses a curved trajectory to induce a relative motion for stationary targets (STI) to enhance the probability of detection and tracking between what ranges? ANSWER: 5. At a range of to meters, targets are too close for a LOAL engagement and must be a LOBL engagement or a NO ACQUIRE message will be displayed. ANSWER: 6. The three RF missile acquisition modes are,, and. ANSWER: D-91

90 I. Enabling Learning Objective 9 ACTION: CONDITIONS: Identify the LBHMMS safety features. Given a written test without the use of student notes or references. STANDARD: In accordance with TM , TC 1-251, and FM (FM 1-140). 1. Learning Step/Activity 1 Identify the LBHMMS safety features. Figure 76. RF Radiation Hazard Area. NOTE: During missile operation, the RF radiation hazard area should be avoided. This area extends from the missile nose outward 1-meter and 45 polar from the missile centerline. (a) LBHMMS safety features. The performance inhibits can be overridden by a trigger pull to the second detent, but the safety inhibits cannot be overridden. When applicable, the associated HAD message follows the inhibit description. 1) Missile Inhibits. Missile inhibits are organized into missile system safety inhibits and missile performance inhibits. D-92

91 SAFETY PERFORMANCE GENERIC ACCEL LIMIT YAW LIMIT SAFE ALT LAUNCH PYLON ANGLE TRAINING DATA INVALID GUN OBSTRUCT LOS INVALID PYLON ERROR PYLON LIMIT (AIR) RATE LIMIT ROLL LIMIT SKR LIMIT PYLON LIMIT (GND) BACKSCATTER LASER RANGE? MSL NOT RDY 2) Missile system safety inhibits Figure 77. Missile Inhibits. a) ACCEL LIMIT: Aircraft vertical Acceleration (ACCL) is less than 0.5 G. b) ALT LAUNCH: Within 2 seconds of a rocket launch. c) DATA INVALID: The FCR is the active sight, and the RFHO data (position error taken from both aircraft and/or FCR range deviation error) has exceeded optimum parameters to a magnitude that a safety inhibit is implemented. (RFHO in MSG REC file for more than 6 minutes) d) GUN OBSTRUCT: If the gun is out of coincidence, the WP will inhibit launch of missiles from the inboard stations of the inboard pylons. The inboard missiles will be coded NA. e) LOS INVALID: Indicates the selected LOS is either failed or invalid. f) PYLON ERROR: Indicates the aircraft is on the ground, and the pylons position is unknown, or the pylons are positioned such that the missile may strike the ground near the aircraft. g) PYLON LIMIT: Indicates that the commanded pylon position exceeded the pylon articulation limits (+4 to 5 on the ground), (+4 to 15 in the air). Performance or safety inhibit is dependant upon air/ground status. h) BACKSCATTER: Based on missile seeker versus TADS LOS, indicates the seeker is not tracking the TADS laser designation. i) LASER RANGE?: Indicates the ST/UPDT switch on the TEDAC LHG has been selected to the UPDT position, and the current range source is other than laser. j) MSL NOT RDY: Indicates that no hellfire missiles are ready for launch, and no SAL missile priority channel is selected, or that RF missile TA is not complete. D-93

92 3) Missile performance inhibits. The WP will inhibit missile firing if a performance constraint is detected, and the weapons trigger is not depressed to the second detent. a) YAW LIMIT: indicates yaw position of the aircraft with respect to the target is excessive; applies to LOAL mode only. 1 SAL missile LOAL LO or LOAL HI selected and any of the following conditions exists: a Azimuth angle between the target and the ADL is greater than 7.5. b c Selected target data is invalid. True heading data from the EGI is invalid. 2 SAL missile LOAL DIR selected and azimuth angle between the selected sight LOS and the ADL is greater than RF missile engagements when the target to be handed over has a LOS angle greater than 20 from the ADL. b) PYLON ANGLE: Indicates the pylon position is greater than 10 from the optimum launch position or that the pylon position is unknown. c) PYLON LIMIT: Indicates (either/or) that the commanded pylon position exceed the pylon articulation limits (+4 to -5 on the ground)(+4 to 15 in the air). Performance or safety inhibit is dependent upon air/ground status. d) RATE LIMIT: Indicates the aircraft pitch, roll, or yaw rate or acceleration is excessive. e) ROLL LIMIT: Indicates the aircraft roll position is excessive. 1 RF missile selected and roll magnitude is greater than SAL missile in LOBL mode and roll magnitude is greater than SAL missile in LOAL mode and roll magnitude is greater than 10. f) SKR LIMIT: indicates the missile seeker azimuth or elevation gimbal limit has been reached. 1 If the priority SAL missile is tracking and the seeker azimuth or elevation angle is greater than 20 from the missile body axis. 2 If the priority RF missile is tracking, the seeker azimuth angle is greater than 20 from the missile body axis, and the range is equal to or greater than 1 km. 3 If the PRIORITY RF missile is tracking, the seeker azimuth angle is greater than 5 from the missile body axis, and the range is greater than 1 km. 4) Other weapon inhibit status field messages: 1 SAFE: Indicates the weapon system has not been armed through the Armament Control panel. 2 TRAINING: Indicates the training mode is active, or the TESS is enabled, and the Armament Control is in the ARM state, and a weapon is actioned in either crew station. D-94

93 CHECK ON LEARNING 1. What inhibits can be overridden, and how is this accomplished? ANSWER: 2. Is the message BACKSCATTER a safety or performance inhibit? ANSWER: 3. What does the message ALT LAUNCH mean? ANSWER: 4. What is the RF missile radiation hazard area to be avoided? ANSWER: D-95

94 J. ENABLING LEARNING OBJECTIVE 10 ACTION: CONDITIONS: Identify the Training Missile Emulator (Tme) operation. Given a written test without the use of student notes or references. STANDARD: In accordance with TM , TC 1-251, and FM (FM 1-140). 1. Learning Step/Activity 1 Identify the Training Missile Emulator (TME) operation. (a) TME Figure 78. Training Missile Emulator. 1) The TRAIN button enables the TME LEA. There is one TME in each launcher. 2) The TME is a software program loaded in the LEA, which provides the capability of simulating RF missile operations. 3) The TME can replicate the functioning of four LBHMMS missiles on each launcher. 4) The TRAIN mode emulates the control decision making process of the RF missile. 5) The TME will also replicate the missile s launch mode selection processing, target acquisition and target tracking functions, missile BIT routines, and thermal management characteristics. (b) TME BITs 1) Selecting the TRAIN mode will emulate PBIT and IBIT functions with appropriate delays built in for accurate simulation. 2) IBIT can be initiated when the system is in the standby or prelaunch modes. 3) It may be commanded at power on, but cannot be acted upon until startup is complete. 4) Emulated IBIT will run in 17 seconds. 5) Due to the manner in which the emulator deals with memory, the startup routine will rerun upon completion of the IBIT. D-96

95 6) This will cause an additional 9-second delay for the restart, resulting in a 26-second delay to run IBIT. (c) TME thermal management 1) The TME provides for thermal management monitoring and control. 2) The TME is allowed a cumulative ON time of 30 minutes. 3) If this time is exceeded, an Over Temperature (OT) symbol will appear on the affected missile icon on the WPN page. 4) Turning the missile system off and back on from the WPN UTIL page can reset the timer. (d) TRAIN mode 1) Operation of tactical missiles is not possible while the TRAIN mode is enabled and all tactical missiles will be coded as NA. However, while in the TRAIN mode with the ARM/SAFE switch set to ARM, the laser is fully functional. 2) TRAIN mode functions include the following: a) Off. This is the default function of the missile when the emulator is first turned on. It simulates the missile system in a no power condition. b) Standby 1 This function is established by a power-on command from the launcher, which is initiated from the missile system power selection on the WPN UTIL page. 2 The emulator will simulate the delay (9 seconds) that occurs during missile spin-up and PBIT routines when power-up is commanded. 3 TA will also be initiated during this function, and will run continuously through the prelaunch function. c) Prelaunch 1 The TRAIN mode will transition from standby to prelaunch when a target assignment is received. 2 The TME will then simulate prelaunch radar (MTA, TTA) and launch mode control decisions (LOAL versus LOBL) based on target characteristics, relative position, handover accuracy (TADS versus FCR), whether the target is in the seeker FOV, and the number of previous acquisition attempts d) Acquisition and track radar modes 1 The TRAIN mode will simulate the appropriate acquisition and track modes based on the target assignment. Target-to-aircraft location is continuously updated to provide the TME with the proper data with which to make the mode and launch decisions. e) TME operation 1 The LOBL/LOAL decision will be based primarily on target range and the MTI/STI indicator. If LOBL becomes the designated launch mode, the TME will exercise acquisition attempts based on FOV limits and range. 2 Once acquisition has occurred, the radar mode will transition to an appropriate track mode and continuously update the aircraft and target positions to determine if the TME is still capable of tracking the target. 3 If the track is lost due to the target going outside the FOV or crossing the LOAL/LOBL range boundaries, reacquisition will be attempted every 2.7 seconds after the break. D-97

96 4 The TME will remain in the track mode until after the third reacquisition cycle, after which the TME will cease target processing and revert to the prelaunch mode. f) TRAIN mode operational sequence 1 When the TME is in the Standby mode, all empty rails will show an RF missile present and all rails with Hellfire SAL training missiles loaded will show SAL missiles present. 2 When the missile system is actioned, the TME transitions to the prelaunch mode and target assignments from the FCR are passed to the firing missile. 3 In the prelaunch mode, the TME will replicate the acquisition and track characteristics identified above. 4 The appropriate messages in the High Action Display (HAD) (for example, RF MSL TRACK, LOAL NORM, NO ACQUIRE) will be displayed along with the appropriate missile icons (for example flashing R or T). 5 The missile constraints box will be presented with a "T" centered in the box when the weapon system is actioned. 6 The weapon inhibits field will display SAFE when the aircraft is in the safe mode and TRAINING when the aircraft is armed. 7 When the TME calculates that the firing missile has met all prelaunch constraints, it will notify the WP, which will display the in-constraints box on the weapons symbology display. 8 The crewmember can then pull the weapons trigger to initiate launch commands. 9 The TME will then display a successful launch by signaling the WP to blank the firing missile icon from the WPN page. 10 The WP will also cause the target on the FCR page to change to the "shot-at" icon. Figure 79. Training Missile Emulator. D-98

97 g) Tactical Engagement Simulation System (TESS) 1 TESS is an interactive simulation system that allows aircrew training for all of the AH- 64D sight and weapon systems. a b This provides Real Time Casualty Assessment (RTCA) for Force-On-Force (FOF) training for Combat Training Center Instrumentation (CTC-I) and Home Station Instrumentation (HSI). TESS will interface with the ground instrumentation at CTCs and HSI. TESS is apportioned into two component systems. 1. The A-Kit is composed of modifications to the AH-64D software and fixed hardware required to interface with the removable B-Kit. 2. The B-Kit a. The B-Kit contains an eye safe laser rangefinder/miles laser designator that physically replaces the TADS laser rangefinder/designator and laser spot tracker. b. The eye-safe laser rangefinder/miles laser designator functionally replaces the TADS laser rangefinder/designator. The laser spot tracking is simulated during TESS training. c. The B-Kit also adds a TADS internal boresight adapter. 3. Simulated weapons inventory is used to provide realistic interaction between aircrew, aircraft, and targets. a. TESS incorporates the capability to interact with ground-based After Action Review (AAR), Executive Control (EXCON), and targeting systems. b. Information is provided from the aircraft systems to the B-Kit for processing and transmission to the ground instrumentation systems. c. The ground instrumentation system elements can provide real-time status display, administrative control, data archiving, target position tracking, and RTCA of targets. 4. When the TESS Electronic Control Unit (TECU) is installed without the TESS Training Missile (TTM): a. The aircraft enters a live-fire instrumentation configuration and transmits tactical weapon event data to the TECU for recording and transmission to ground instrumentation systems, which is used for training. b. When in this configuration, the WP will transmit tactical weapon event data to the TECU for recording and transmission to ground instrumentation systems. 2 Simulated weapons inventory for TESS training: a b c Weapons inventory is simulated by administrative input to the TECU and subsequent transmission to the WP. Simulated inventory is uploaded upon TESS B-Kit power up and by subsequent administrative input. If any Hellfire missile or rocket is detected during the initial stores inventory or if a gun-rounds inventory of greater than zero is stored: D-99

98 d e a. A LIVE AMMO indication will be displayed in the HAD weapon-inhibit field, and TESS training will not be enabled. b. The specific type of ammunition will be indicated on the Up-Front Display (UFD). Gun-rounds count and rocket-type entries are only changed by administrative input to the TECU and subsequent transmission to the WP or by simulated gun/rocket fire. Simulated inventory is not considered in aircraft gross weight and performance calculations. Figure Symbology/HAD indications: a b Missile Constraint Boxes. The Hellfire missile constraints boxes are used to indicate the delivery mode and direction to orient the aircraft for the Hellfire missile launch. 1. A dashed line type indicates the missiles are out of constraints. 2. A solid line indicates the missiles are within constraints. Constraint boxes are displayed in two sizes and will be displayed only when the missile system is actioned. Boxes apply to SAL and RF missile launches. 1. LOBL constraint box (20º): a. The LOBL constraint box will be displayed when the missile system is in a LOBL missile launch mode. b. For SAL missile engagements, the LRFD must be designating in order for it to be considered a LOBL missile shot. 2. LOAL constraints box (7.5º): D-100

99 a. The LOAL constraint box will be displayed when the missile system is in a LOAL missile launch mode. b. For SAL missile engagements in the LO or HI trajectory, constraints are calculated based on the acquisition source chosen from the COORD page (Txx, Cxx, Wxx, TRN, or Hxx). (ACQ B5) c. LOAL does not have to be the active acquisition source, but it must be selected as the target source. 1. A centered "T" will be displayed in the Hellfire constraints cursor symbols when TESS training is enabled and the missiles are actioned. 2. The HAD weapon inhibit: Whether the aircraft is ARMed or SAFE with TRAIN mode selected the weapons inhibit field (HAD) will display TRAINING. Figure 81. RTCA Status. 4 Weapons effects during TESS training: a b With a simulated Hellfire missile launch, rocket launch, or gun firing, the Communications Interface Unit (CIU) will provide the respective weapon launch/firing audio effect. The TESS B-Kit will provide an external visual effect (firing flash). 5 During TESS training the TECU determines, either from the Laser Warning Receiver (LWR) or administrative input, that an RTCA event has occurred, and the TECU will transmit the RTCA status and a weapon Identification (ID) code to the aircraft. 6 The CIU will provide the aircrew with an RTCA audio effect (tone with voice messages): a b c Tone, YOU HAVE BEEN KILLED. Tone, YOU HAVE BEEN HIT. Tone, NEAR MISS. D-101

100 7 The RTCA status will be displayed on the UFD hit and near miss for 8 seconds; kill continuously: a b c "SIM KILL." "SIM HIT." "SIM MISS." Figure 82. Aircraft Kill Indicator (AKI). 8 The RTCA status and weapon ID code will be made available on the WPN UTIL page. 9 If a kill status is received: a b The aircraft will be inhibited from firing any weapon. The TTM will power the external Aircraft Kill Indicator (AKI) to indicate the RTCA status. If the flashing AKI indication creates a hazard to flight, the capability to turn off the AKI is available to the aircrew via the WPN page AKI button. 10 The weapons TRAIN button is not available when TESS is enabled. 11 During TESS training the TECU determines that an RTCA kill event has been revoked by administrative input of a resurrect or reset status, the TECU will transmit the resurrect or reset command to the aircraft. a b c The CIU will provide the aircrew with resurrect or reset audio effect: 1. "SIMULATION IS RESET." 2. "SIMULATION IS RESURRECTED." The RTCA status will be removed from the UFD. The RTCA status and weapon ID code will be removed from the WPN UTIL page. D-102

101 d e f g The resurrect or reset status will be displayed on the UFD for 8 seconds. 1. SIM RESET indicates that TESS has commanded the aircraft to a reset state. 2. SIM RESURR indicates that TESS has commanded the aircraft to a resurrect state. The aircraft will be permitted to fire any weapon, and the TTM will power off the external AKI. If a resurrect signal is received, the TECU will update the weapon stores inventory with the same inventory that was available before the kill was processed. If a reset signal is received, the TECU will update the weapon stores inventory with the initial inventory that was available upon power up. D-103

102 1. How many TMEs are on each aircraft? ANSWER: CHECK ON LEARNING 2. Tactical missiles will be coded while in the training mode. ANSWER: 3. The TME allows for thermal management of the missiles by allowing for a cumulative time ON of minutes. ANSWER: 4. With the TRAIN mode selected and a weapon system is actioned the weapons inhibit field will display. ANSWER: 5. The constraints box will display a centered in the box when the weapon system is actioned in the training mode. ANSWER: D-104

103 D-105

104 D-106

105 D-107

106 D-108

107 Figure 1. Remote HF Chart 1) Left column, read up to Shooting Aircraft NAV Range to TGT 2) Right to OFFSET angle column 3) Shooting gun-target-line designator LTL. Must be within 60º. 4) Displayed Range is DESIGNATORS MIN RANGE to TGT. If designators range is less, consider possible max laser delay or reposition aircraft. D-109