Abstract: A boresight correction system is disclosed that determines the existing error between an aircraft gunsight and its gun systems while prescribed aircraft maneuvers are performed and which automatically corrects the gunsight system to compensate for this error. The system includes a sensor for detecting bullet positions, hardware that determines the bullet positions relative to the gun boresight, a digital processor to determine the above mentioned error, and to correct the gunsight system according to this error, and a non-volatile memory in the digital processor to store a corrected boresight position.

Abstract: A system and method for providing a relative velocity sighting reference in an airborne gunsight system. A head-up display (HUD) frames the target in the pilot's line of sight and a computer-driven cathode ray tube (CRT) display projects an array of sighting indices or dots on the HUD. The computer receives air data and target tracking inputs and controls the CRT display so that the sighting array automatically overlays and follows the target and so that the indices thereof move in a direction and at a velocity to describe the motion of the line of sight of the target required for the target to intercept a bullet fired from the aircraft gun. The pilot maneuvers the aircraft to null the relative motion between the target and the sighting indices, whereby the gun is in position to fire.

Abstract: A system for aircraft gunnery training and accuracy evaluation wherein a head-up display unit employs a cathode ray tube for projecting simulated bullets on a pilot's sighting panel. The simulated bullets each comprise a pair of bullet trajectory indicia simulating the firing of the guns of the aircraft at an actual target. The indicia in a pair of bullet trajectory indicia are equidistantly spaced from the simulated trajectory path by an amount related to a selected dimension of the target. Each pair of bullet trajectory indicia are initially displayed to reflect the physical conditions of the aircraft at the time of firing, including the rates of aircraft roll, pitch and yaw, the aircraft lift acceleration, true aircraft airspeed, gun angle of attack, and relative air density. As the bullet trajectory indicia traverse the simulated trajectory path, the separation between the indicia comprising a pair of indicia is decreased to simulate increasing distance from the firing aircraft.

Abstract: An aircraft gun sighting system and method for use in executing high angle-off attacks wherein a headup display unit employs a cathode ray tube for projecting sighting indicia on the pilot's sighting panel. The sighting indicia appear as a plurality of straight lines lying along a circular sector on the lower portion of the sighting panel. The circular sector is defined by a center point on the panel representing the muzzle aiming point such that the sighting indicia define a fixed lead angle. Each sighting line represents the position of a hypothetical target travelling in a path which will, one bullet flight time later, intersect the path of a bullet fired by the attacking aircraft. The sighting lines are periodically reset to the outer limits of the circular sector whereupon they move along the sector toward convergence at the line defining the turning plane of the attacking aircraft.

Abstract: Method and sighting apparatus for aerial bombing from a curved approach path in a plane other than a vertical plane. Computer calculates and drives proper lead angle for sight which includes a reticle for target tracking with freedom to move in two dimensions. Computation, which is based on the relationship of lead angle and rate of turn of the aircraft in a curved flight path through the bomb release point, also considers airspeed, initial distance to target, bombing distance from target, aircraft mass, and can account for wind velocity, bomb characteristics and air density.