CHAPTER 4

BALLISTICS

Ballistics is the science of the motion of projectiles and the conditions that influence their motion. The four types of ballistics influencing projectiles fired from helicopters are interior, exterior, aerial, and terminal. Each type produces dispersion, which is the degree that projectiles vary in range and deflection about a target.

4-1. INTERIOR BALLISTICS

Interior ballistics deal with characteristics that affect projectile motion inside the barrel or rocket tube. It also includes effects of propellant charges and rocket motor combustion. These characteristics affect the accuracy of all aerial-fired weapons. Aircrews cannot compensate for these characteristics when firing free-flight projectiles. The characteristics of interior ballistics are discussed below.

a. Barrel Wear. Gaseous action, propellant residue, and projectile motion wear away the barrel's inner surface or cause deposits to build up. These conditions result in lower muzzle velocity, a decrease in accuracy, or both.

b. Propellant Charges. Production variances can cause differences in muzzle velocity and projectile trajectory. Temperature and moisture in the storage environment can also affect the way propellants burn.

c. Projectile Weight. The weight of projectiles of the same caliber may vary. The variance is most noticeable in linked-ball projectiles. These variations do not significantly influence trajectory.

d. Launcher Tube Alignment. Individual rocket launcher tubes are aligned by the rocket launcher's internal or end bulkhead. However, the precise alignment of each tube may vary. Because of variances in alignment, the launcher boresight also varies from tube to tube. Proper boresighting of the launcher should include checking the boresight of several tubes and selecting the one that best represents the alignment of the entire launcher.

e. Thrust Misalignment.

(1) A perfectly thrust-aligned free-flight rocket would have thrust control, which would pass directly through its center of gravity during motor burn. In reality, free-flight rockets have an inherent thrust misalignment, which is the greatest cause of error in free flight. Spinning the rocket during motor burn reduces the effect of thrust misalignment.

(2) Firing rockets at a forward airspeed above ETL provides a favorable relative wind, which helps to counteract thrust misalignment. When a rocket is fired from a hovering helicopter, the favorable relative wind is replaced by an unfavorable and turbulent wind caused by rotor downwash. This unfavorable relative wind results in a maximum thrust misalignment and a larger dispersion of rockets.

(3) Rockets spin to counteract thrust misalignment. Rockets with MK66 motors exhibit less dispersion in the target effect area than those with MK40 motors according to data provided by Rock Island Arsenal.

4-2. EXTERIOR BALLISTICS

Exterior ballistics deal with characteristics that influence the motion of the projectile as it moves along its trajectory. The trajectory is the flight path of the projectile as it flies from the muzzle of the weapon to the point of impact. Aerial-fired weapons have all the exterior ballistic characteristics associated with ground-fired weapons. They also have other characteristics unique to helicopters. The characteristics of exterior ballistics are discussed below.

a. Air Resistance. Air resistance, or drag, is caused by friction between the air and the projectile. Drag is proportional to the cross‑section area of the projectile and its velocity. The bigger and faster a projectile is, the more drag it produces.

b. Gravity. The projectile's loss of altitude because of gravity is directly related to range. As range increases, the amount of gravity drop increases. This drop is proportional to time of flight (distance) and inversely proportional to the velocity of the projectile. Crew members that fire weapons without FCC solutions must correct for gravity drop. Table 4-1 shows gravity drop for different projectiles.

c. Yaw. Yaw is the angle between the centerline of the projectile and the trajectory. Yaw causes the projectile's trajectory to change and drag to increase. The direction of the yaw constantly changes in a spinning projectile. Yaw maximizes near the muzzle and gradually subsides as the projectile stabilizes.

d. Projectile Drift.

(1) When viewed from the rear, most projectiles spin in a clockwise direction. Spinning projectiles act like a gyroscope and exhibit gyroscopic precession. This effect causes the projectile to move to the right, which is called the horizontal plane gyroscopic effect. As the range to target increases, projectile drift increases.

Projectile	Approximate Muzzle Velocity (feet per second)	Range (meters)	Approximate Gravity Drop (mils)
7.62 mm	2,800	1,000	7
.50 cal	2,900	1,000/1,500	9/18
20 mm	3,380	1,000/1,500	9/21
30 mm	2,640	1,000/2,000	15/60
40 mm	795	1,000	87

Table 4-1. Gravity drop

(2) To compensate for this effect in aircraft without FCC solutions, the gunner increases any correction, such as elevation, depression, or deflection, to hit the target. To compensate for projectile drift, the gunner establishes combat sight settings or adjusts rounds toward the target. This compensation is known as using "burst on target." Figure 4-1 shows projectile drift.

e. Wind Drift. The effect of wind on a projectile in flight is called wind drift. The amount of drift depends on the projectile's time of flight and the wind speed acting on the cross-sectional area of the projectile. Time of flight depends on the range to the target and the average velocity of the projectile. When firing into a crosswind, the gunner must aim upwind so that the wind drifts the projectile back to the target. Firing into the wind or downwind requires no compensation in azimuth but will require range adjustment.

4-3. AERIAL BALLISTICS

a. Common Characteristics. Characteristics of aerial-fired weapons depend on whether the projectiles are spin-stabilized or fin-stabilized and whether they are fired from the fixed mode or the flexible mode. Some characteristics of aerial-fired weapons are discussed below.

(1) Rotor downwash error. Rotor downwash acts on the projectile as it leaves the barrel or launcher. This downwash causes the projectile's trajectory to change. A noticeable change in trajectory normally occurs when the helicopter is operating below effective translational lift.

Figure 4-1. Projectile drift

(a) Although rotor downwash influences the accuracy of all weapon systems, it most affects the rockets. Maximum error is induced by rotor downwash when the weapon system is fired from an aircraft hovering IGE, as shown in Figure 4-2. Air flows downward through the rotor system and causes the rocket to pitch up as it leaves the launcher.

(b) When the rocket passes beyond the rotor disk, air flows upward and causes the rocket to wobble. This air flow causes both lateral (azimuth) and linear (range) errors.

(c) When the aircraft is hovering OGE (Figure 4-2) the relative wind strikes the rocket only from above after it leaves the launcher. This condition decreases the lateral error. However, the velocity of the rotor downwash increases because of the additional power required to maintain OGE hover, which may increase linear dispersion.

(d) High-density altitudes and heavily loaded aircraft further increase linear dispersion. During IGE and OGE hovering flight, the true airspeed vector of the helicopter affects the position of rotor downwash and the speed of the downwash at the rocket launchers. For example, holding a position over the ground during a right crosswind results in a true airspeed vector to the right and a shift of the downwash to the left. This shift affects the left rocket for a longer time during launch than the right rocket. The left rocket also will pitch up to a higher quadrant elevation and go farther

Figure 4-2. Rotor downwash error

than the right rocket. Detailed system testing has not shown that differences of QE are required for right versus left launchers during hover fire.

(e) To prevent a divergence of trajectories, the aircraft can drift with the wind if the terrain allows. Drifting with the wind allows the aircraft to remain stable and provides a more consistent rotor downwash for both launchers.

(2) Angular rate error.

(a) Angular rate error is caused by the motion of the helicopter as the projectile leaves the weapon. It affects most weapon systems. The exceptions are TOW, Hellfire, and Stinger missiles. For example, a pilot using the running-fire delivery technique to engage a target with rockets at 5,000 meters may have to pitch the nose of the helicopter up to place the reticle on the target. When the weapon is fired, the movement of the helicopter imparts an upward motion to the rocket. The amount of error induced depends on the range to the target, the rate of motion, and the airspeed of the helicopter when the weapon is fired.

(b) Angular rate error occurs when aircrews fire rockets from a hover using the pitch-up delivery technique. Anytime a pitch-down motion is required to achieve the desired sight picture, the effect of angular rate error causes the projectile to land short of the target.

b. Spin-Stabilized Projectiles. Certain ballistic characteristics are peculiar to spin-stabilized projectiles fired from weapons with rifled barrels. These weapons include the .50-caliber and 7.62-mm machine guns, and the 20- and 30-mm cannons. When fired in the fixed mode (straight ahead of the helicopter), the projectiles generally have the same ballistic characteristics as ground-fired weapons. However, relative wind changes and the velocity of the helicopter increase or decrease the velocity of the projectile. Ballistic characteristics influencing spin-stabilized projectiles fired from positions other than a stabilized hover are discussed below.

(1) Trajectory shift. When the boreline axis of the weapon differs from the flight path of the helicopter, the movement of the helicopter changes the trajectory of the projectile. For off-axis shots within ±90 degrees of the helicopter's heading, trajectory shift causes the round to hit left or right of the target. To correct for trajectory shift, the gunner leads the target. To lead the target, the gunner places fire on the near side of the target as the helicopter approaches. The amount of lead depends on the airspeed of the helicopter, angle of deflection, velocity of the projectile, and range of the target. Figure 4-3 shows trajectory shift. Table 4-2 shows some examples of how to compensate for trajectory shift.

Figure 4-3. Trajectory shift

Projectile	Approximate Muzzle Velocity (feet per second)	Helicopter Velocity (knots)	Lead Angle (mils)
7.62 mm	2,800	100	51
.50 cal	2,900	100	49
20 mm	3,380	100	47
30 mm	2,640	100	64
40 mm	795	100	182

Table 4-2. Typical lead angles for a 60-degree deflection

shot at 1,000 meters

(2) Port-starboard effect. Trajectory shift and projectile drift combine to constitute the port-starboard effect. When targets are on the left, the effects of drift and shift compound each other; both cause the round to move right. To hit the target, the

gunner must correct for both ballistic effects by firing to the left of the target. When targets are on the right, the effect of projectile drift (round moves right) tends to cancel the effect of trajectory shift (round moves left). Therefore, firing requires less compensation. The range and airspeed at which a target is engaged determine which effect is greater. For example, at ranges less than 1,000 meters, trajectory shift is greater. The gunner must fire to the right of the target. At ranges beyond 1,000 meters, the effect of projectile drift is greater and tends to cancel the effect of trajectory shift.

(3) Projectile jump (vertical plane gyroscopic effect).

(a) When a crew fires a weapon from a helicopter in flight and the weapon's muzzle is pointing in any direction other than into the helicopter's relative wind, the projectile will experience projectile jump. Projectile jump begins when the projectile experiences an initial yaw as it leaves the muzzle. The yaw is in the same direction as the projectile's direction of rotation. The jump occurs because of the precession (change in axis of rotation) induced by crosswind.

(b) The amount a projectile jumps is proportional to its initial yaw. Firing to the right produces a downward jump; firing to the left produces an upward jump. To compensate the gunner must aim slightly above a target on the right of a helicopter and slightly below a target on the left. The amount of compensation required increases as helicopter speed and angular deflection of the weapon increase. Compensation for projectile jump is not required when firing from a hover.

c. Fin-Stabilized Projectiles. The ballistic characteristics affecting fin-stabilized projectiles are important. They include--

(1) Propellant force. A bullet reaches its maximum velocity at or near the weapon's muzzle. However, a rocket continues to accelerate until motor burnout occurs. As the rocket reaches its greatest velocity, the kinetic energy in the rocket tends to overcome other forces and causes the rocket to travel in a flatter trajectory.

(2) Center of gravity. Unlike a bullet, the CG of a rocket is in front of the center of pressure. As the rocket propellant burns, the CG moves farther forward. The rocket's fins cause the center of pressure to follow the CG.

(3) Relative wind effect. When a helicopter is flown out of trim, either horizontally, vertically, or both, the change in the crosswind component deflects the rocket as it leaves the launcher. Because the rocket is accelerating as it leaves the launcher, the force acting upon the fins causes the nose to turn into the wind.

(a) A horizontal out-of-trim condition results when a pilot tries to align the sight on the target during a crosswind by cross-controlling, or slipping, the helicopter. For example, a pilot flies at 100 knots and maintains 10 degrees out of trim with a quartering crosswind component of 10 knots. This condition causes the rocket to turn into the relative wind after leaving the tube. As the velocity of the rocket increases and the motor burns out, the crosswind component decreases. After the motor burns out, the rocket drifts with the air mass (real wind). If the pilot is unable to align the helicopter into the wind, the gunsight must be corrected upwind. While firing from a hover or during slow flight, the pilot must make a downwind correction because the rocket will turn into the wind.

(b) A vertical out-of-trim condition results from an improper power setting. This condition creates a vertical relative wind on the rocket during launch, causing the rocket to turn into the wind. If the pilot fires the rocket while applying power (as in a climb), the relative wind will be from above. The relative wind will cause the rocket to hit beyond the aiming point. To maintain a vertical trim condition, the pilot must maintain a constant power setting that will produce the desired airspeed and altitude.

4-4. TERMINAL BALLISTICS

Terminal ballistics describes the characteristics and effects of the projectiles at the target. Projectile functioning, including blast, heat, and fragmentation, is influenced as described below.

a. Impact Fuzes. Impact fuzes activate surface and subsurface bursts of the warhead. The type of target engaged and its protective cover determine the best fuze for the engagement. Engage targets on open terrain with a superquick fuze that causes the warhead to detonate upon contact. Engage targets with overhead protection, such as fortified positions or heavy vegetation, with either a delay or forest penetration fuze. As shown in Figure 4‑4 these fuzes detonate the warhead after it penetrates the protective cover.

Figure 4-4. M433 multioption fuze/2.75-inch high-explosive warhead

b. Remote Set or Variable Time Fuzes. Timed fuzes produce airbursts and are most effective against targets with no overhead protection. Flechette, smoke, and illumination warheads incorporate a timed fuze, which depends on motor burnout. The range for this type of fuze is fixed. Remote range-set fuzes are in use for high explosive, multipurpose submunition, smoke, illumination, and chaff warheads. The range is variable for this type of fuze and can be set by the crew in the AH-1E/F, AH‑64, and OH-58D (KW).

c. Wall-In-Space Fuze.

(1) Multipurpose submunition warheads provide a large increase in target effectiveness over standard unitary warheads. The MPSM warhead helps to eliminate range-to-target errors because of variations in launcher/helicopter pitch angles during launch. The M439 fuze is remotely set from the aircraft with range (time) to the target data.

(2) Once fired, the initial forward motion of the rocket begins fuze time. At the computer-determined time (a point slightly before and above the target area), the M439 fuze initiates the expulsion charge. The submunitions eject and each ram air decelerator inflates. Inflation of the RAD separates the submunitions, starts the arming sequence, and causes each submunition to enter a near vertical descent into the target area. Figure 4-5 shows the wall-in-space concept.

Figure 4-5. Wall-in-space concept

d. Surface Conditions. The surface of the target area (such as sand, rocks, or vegetation) affects the lethality of the projectile. If superquick fuzes are used against targets covered by heavy foliage, they will function high in the tree canopy but will be ineffective at ground level. However, the same fuze would be effective against a target area with a sandy surface. To get maximum effectiveness from the warhead, use the proper fuze for the surface condition.

e. Warheads. The type of target to be engaged determines which warhead to use. A large variety of warheads are available. The factors of METT-T help determine the proper mix of warheads for the particular mission.

f. Angle of Impact. The altitude from which the projectile is fired and the range to the target determine the angle of impact and fragmentation pattern. Weapons fired with a high angle of impact produce fragmentation patterns that are close together. A projectile fired from NOE altitudes at the midrange of the weapon forms an elongated pattern with the projectile impacting at shallow angles. As the range increases, the impact angle of the projectile increases. The length of the fragmentation pattern decreases while the width increases. Figure 4-6 shows the angle of impact.

Figure 4-6. Angle of impact

4-5. DISPERSION

If several projectiles are fired from the same weapon with the same settings in elevation and deflection, their points of impact will be scattered about the mean point of impact of the group of rounds. The degree of scatter (range and azimuth) of these rounds is called dispersion. The mean point of impact with respect to the target center, or intended air point, is an indication of the weapon's accuracy. Both dispersion and accuracy determine whether a particular weapon can hit an intended target. Firing rockets at maximum ranges decreases range dispersion and normally increases accuracy. The reverse is true with other weapon systems; that is, as range increases, dispersion increases and accuracy decreases. Dispersion is caused by errors inherent in firing projectiles. These errors are influenced, in part, by the factors discussed in the ballistics paragraphs. In addition, they may be influenced by the vibrations in the mount and condition of the sighting systems.

a. Vibrations. Because mounts for weapons are fixed to the helicopter, vibrations in the helicopter transmit through the mounts. These vibrations affect azimuth and elevation.

b. Sights. The condition of the sights and the accuracy of their alignment with the bore axes of the weapons cause a displacement of the dispersion pattern of the projectiles.

c. Boresight. Proper boresighting of aircraft weapons is critical to accurate fires. Improper boresighting is a factor in dispersion differences between like aircraft.

4-6. AH-64D LONGBOW APACHE SPECIFIC BALLISTIC CONSIDERATIONS

The AH-64D compensates for various aspects of ballistics and the following is a brief summary of what and how it does this.

a. Interior Ballistics. (AH-64D LONGBOW APACHE SPECIFIC BALLISTICS)

(1) Barrel Wear. AH-64D pilots should be aware that gun duty cycle (heating and associated expansion of the barrel material) will also effect muzzle velocity. As such, the firing duty cycle guidelines presented in the operator’s manual (–10) must be followed to both preserve safety and to ensure proper gun accuracy is retained. Note that the AH-64D computes ballistic offsets based on a nominal muzzle velocity of 805 meters/second at 70 degrees Fahrenheit for the M788/M789 ammunition. The muzzle velocity variable used in the ballistics calculations is further adjusted based on the difference between 70 degrees Fahrenheit and the actual ambient temperature data received from the aircraft air data system (HIADC). However, no muzzle velocity or temperature sensor is fitted on the AH-64D cannon and as such, variations between computed and actual muzzle velocity can adversely effect accuracy most notably at appreciable i.e., longer, engagement ranges.

(2) Propellant Charges. AH-64D pilots should recognize that propellant burn variation, as a function of ambient temperature, is also a significant contributor to muzzle velocity variations and is addressed in the AH-64D ballistics algorithms via the aforementioned muzzle velocity temperature compensation. Propellant charge variations as well as variations in ambient temperature will manifest as increased dispersion at appreciable engagement ranges.

(3) Launcher Tube Alignment. The AH-64D aircraft employs Pylon Interface Units in each pylon assembly and aligns each pylon for launch based on its independent error sources as measured with the CBHK.

b. Exterior Ballistics. (AH-64D LONGBOW APACHE SPECIFIC BALLISTICS)

(1) Air Resistance. The AH-64D ballistics calculations factor air density ratio, based on data received from the aircraft air data system (HIADC), in the gun and rocket time-of-flight calculations which ultimately impact the aimpoint adjustment (ballistic correction). Projectile time of flight increases in denser air masses. The opposite is true in thin air. Any increase in the munition time-of-flight equates to a larger ballistic correction due to the effects of gravitational “drop” (see gravity to follow).

(2) Gravity. AH-64D pilots should note that the 30mm velocity is highest at barrel exit and decays rapidly as a function of range. The MK66 rocket achieves maximum velocity at approximately 500 meters from the launch aircraft and like the 30mm projectile, decays rapidly thereafter. Since gravity is a fixed value of 9.806 meters/second², projectile time of flight is directly proportional to gravitational drop and dictates use of progressively larger ballistic compensation as a function of time to target. AH-64D pilots should note that the AH-64D ballistics algorithms, and associated rocket and gun coefficients, automatically address gravitational drop as a function of time of flight.

(3) Yaw. Yaw error is minimized by spin stabilization. In the case of the AH-64D 30mm, spin stabilization is implemented via barrel rifling, which imparts spin rate on the projectile while traveling down the barrel. Yaw error is largest at muzzle exit due to tip-off not lack of spin stabilization. Yaw error is also introduced at appreciable range when the spin stabilization is compromised due to decaying projectile velocity and angle of attack wherein the round begins to corkscrew and eventually tumbles due to increased drag. This phenomenon is most apparent at ranges beyond 3Km. In the case of rockets, the MK66 motor flutes impart a high spin rate in excess of 30 revolutions/second during the boost phase of motor burn (approximately 1 second). Thereafter, the folding fins reverse the roll rate and sustain the spin stabilization for the remainder of the munition free flight profile. However, not unlike 30mm projectiles, tip-off error is also a major cause of yaw instability in rockets.

(4) Projectile Drift. The amount of projectile drift is proportional to the spin rate of the projectile, which varies throughout the flight profile. AH-64D pilots should note that the LBA ballistics algorithms compensate for this phenomenon and no adjustments are required by the aircrew.

(5) Wind Drift. AH-64D pilots should recognize that wind drift compensation is performed automatically by the Weapons Processor. In addition, there are important wind compensation considerations that AH-64D pilots should understand:

a. Munition Sensitivity. Rockets weathervane into the wind vector during the motor boost phase and drift with the airmass during the motor coast phase. 30 mm rounds drift with the airmass throughout their free-flight trajectory. The amount of projectile drift attributed to wind effects is directly proportional to munition time of flight (which accounts for air density ratio), wind vector (angle), and wind magnitude.

b. Wind Compensation Characteristics. Longitudinal and lateral wind data received from the aircraft air data system is translated by the Weapons Processor to the predicted LOS (where the target will be at termination of munition free flight). Since the airmass characteristics are measured locally, the AH-64D ballistics algorithms apply wind sensitivity adjustment to the aimpoint as if the munition flies directly to the target and the measured winds are constant from ownship to target. However, as a function of increased range, gravitational effects dictate that the munition be aimed well above the target to achieve intercept. If the wind characteristics at these altitudes or target ranges do not reflect that measured locally by the aircraft air data system, appreciable error may result. To illustrate, consider a 30mm gun engagement at 150’ AGL with a slant range of 3.0 Km. In standard atmospheric conditions, ballistics will apply a 9.06 degree elevation correction above the LOS to achieve target intercept. In essence, the projectiles will achieve a peak altitude in excess of 1000 feet AGL. Clearly, surface winds at 1000 AGL can differ dramatically from 150 feet especially in an unstable airmass. A similar condition exists with MPSM (6MP) and illumination (6IL) rockets wherein the submunition payloads are deployed between 600 and 1900 feet above the target and exhibit high wind drift sensitivity due to their slow descent rate. Clearly, the potential for large wind variations exists under certain conditions.

c. Aerial Ballistics. (AH-64D LONGBOW APACHE SPECIFIC BALLISTICS)

(1) Rotor Downwash Error. Rockets are most sensitive to downwash effects as compared to 30mm projectiles. In essence, HIGE launch yields greater dispersion since the aircraft cannot apply appropriate downwash compensation. Note that the real reason rockets pitch up in hover, whether HIGE or HOGE apply, is weathervaning. As stated previously, rockets turn into the relative wind source during boost. The rotor downwash magnitude of the AH-64D varies appreciably as a function of aircraft gross weight. At 18,000 pounds, the downwash magnitude is nominally 21 meters/second or 40 Kts in stabilized hover. This wind source imparts a significant angular error (pitch axis) dependent on exposure time. At approximately 33 Kts forward airspeed (indicated), the rotor disk is pitched forward such that the influence vector is moved just aft of the rocket launcher front bulkhead thus reducing downwash to zero. When transitioning to rearward flight, downwash magnitude initially increases since the rotor disk is pitched aft and the rockets spend more time in the influence vector. However, as rearward airspeed is increased, the influence vector is translated from an orthogonal component to a longitudinal component, since the rotor is tipped progressively more aft, thus reducing downwash sensitivity. Note that the AH-64D ballistics algorithms automatically compute rotor downwash compensation for rockets based on aircraft gross weight, air density ratio, and longitudinal true airspeed. However, this compensation assumes rocket launch is initiated at HOGE altitudes. Downwash compensation is not applied for the gun due to the position of the muzzle with regard to the rotor disk and the short exposure time of the 30mm projectiles. When initiating rocket launch in crosswinds, the aircraft should be temporarily rolled level for munition release presuming terrain permits doing so. Automatic roll compensation of the rocket aimpoint (and pylon position angle) cannot be automatically implemented with any degree of effectiveness.

(2) Angular Rate Error. The phenomenon is effectively negligible for 30mm projectiles. Angular rate error can effect rocket accuracy if rates are appreciable. The articulating pylons address angular rates in the pitch axis up to 10 degrees/second.

(3) Trajectory Shift. AH-64D pilots should recognize that compensation for this error is accomplished automatically by the AH-64D ballistics algorithms when the TADS or FCR serve as the selected sight. If TADS is the selected sight, the Weapons Processor employs a 7 state Kalman filter-based target state estimator that determines actual target velocities with respect to the TADS LOS. The target state estimator uses aircraft linear velocity and body rate data from the EGI, TADS LOS position from the TEU, TADS pitch and yaw rate inputs from the TADS turret, and laser range data from the TEU (pre-processed using the AH-64D Laser Range Validator (LRV) algorithm) to arrive at a proper lead angle. In essence, the target state estimator differentiates aircraft induced rates from true target rates. Once true target rates are derived, the lead predictor computes the appropriate lead angle based on computed time-of-flight of the projectile. If FCR is the selected sight, the FCR provides target velocity data as a function of scan-to-scan correlation. If the FCR NTS target velocity data is valid, the lead predictor is also called and the appropriate lead angle is derived. In addition to computation of lead angle, rate compensation is automatically applied to the pointing command to address servo delays and transport delay latency associated with increased target, ownship, or collateral rates.

(3) Projectile Jump. Projectile jump correction is indeed required in hover if a relative wind exists. AH-64D pilots should recognize that compensation for “aeroballistic drop” is accomplished automatically by first deriving the munition angle of attack with respect to the wind vector and then applying the appropriate jump correction to the aiming algorithm.

d. Terminal Ballistics. (AH-64D LONGBOW APACHE SPECIFIC BALLISTICS) Remote Set or Variable Time Fuzes. Fixed time-base fuzes detonate and release their payloads at a fixed time after rocket launch. Fixed time-base fuzes are employed in the 6IL and IL7 (CRV-7) illumination rockets and the associated function time is 9.0 seconds after motor burnout. Optimum release range is established as 3.5Km for the 6IL and approximately 4.0 Km for the IL7 (due to increased motor velocity). Airburst fuzes (M439) permit the host aircraft to establish a variable time-of-function from 0.95 to 25.575 seconds. The ballistic algorithms define the optimum fuze time-of-function value based on conventional ballistics compensation, use of a prescribed range and height offset associated with the payload, and submunition free-flight characteristics. M439 fuzes are employed in the following rockets:

MP7 – CRV-7 motor, multi-purpose submunition warhead

SK7 – CRV-7 motor, smoke warhead

6MP – MK66 motor, multi-purpose submunition warhead

6SK – MK66 motor, smoke warhead

6FL – MK66 motor, flechette warhead (growth)

e. Dispersion.

AH-64D pilots should note that the nominal 30mm “round to round” dispersion is approximately 3Mr in a given burst using a stationary target. The nominal MK66 rocket unitary munition dispersion exceeds 10Mr when fired from the aircraft. Turret bending is the single largest contributor to perceived dispersion associated with the AH-64D 30mm cannon. Specifically, the airframe and gun turret experience flexure in response to sustained recoil. As such, the AH-64D ballistics algorithms must employ a turret bending compensation table to normalize this adverse effect. The table is developed using multiple AH-64D aircraft define the average “bending” trend at various azimuth and elevation pointing angles. No compensation is required for the first round in a burst since recoil effects do not yet apply. The aimpoint is adjusted for ½ of the bending table value for the second round in a burst and full table values are applied thereafter until gunfire is terminated. Another major source of round to round dispersion or aimpoint biases is faulty recoil adapters. If the recoil dampers (either or both) are incorrectly serviced or dysfunctional altogether, a significant variation can exist in first vice subsequent round placement. Finally, excessive turret backlash and component wear also contribute to dispersion and aimpoint variations. The AH-64D aircraft employs a gun dynamic harmonization algorithm to permit aircrews to rapidly compensate for the aforementioned error sources to the extent that the majority of the burst will be placed on target.