Showing papers on "Air-to-air missile published in 1978"
Patent•
03 May 1978TL;DR: In this article, a floor track system is used to guide the movement of the missile racks within a cargo compartment of the fuselage for a continuous carousel movement for continuous missile launching sequence.
Abstract: An air launched cruise missile carrier airplane having a floor mounted track system for moving missile racks into a launch position adjacent to a side opening in the fuselage and ejecting missiles therethrough, then moving the empty missile racks from the launch location and repositioning a full rack of missiles thereat. A continuous missile launching sequence is provided by the floor track system which guides the movement of the missile racks within a cargo compartment of the fuselage for a continuous carousel movement.
34 citations
Patent•
30 May 1978TL;DR: In this article, the authors describe a system in which a target is tracked by a time optimal controller, followed by a proportional navigation in pitch of the target to the target by a pitch programmer.
Abstract: A missile system in which a missile is guided in a predetermined trajectoryrom launch or shortly thereafter in yaw by proportional navigation and in pitch first by a pitch programmer until said missile reaches a predetermined angle between a line of sight of a seeker of the missile and a centerline of the missile, then in pitch by a time optimal controller to direct the missile at a predetermined angle toward a target and finally by proportional navigation in pitch of the missile to the target.
20 citations
01 Jan 1978
TL;DR: In this paper, an extended Kalman filter is developed to aid the tracking of an air-to-air missile from a maneuvering target aircraft, which exploits knowledge of the dominant aerodynamically induced lift and drag forces of a non-thrusting missile employing proportional navigation guidance, and also accounts for the dynamic lag and bandwidth effects of the missile seeker, guidance and control systems.
Abstract: An extended Kalman filter is developed to aid the tracking of an air-to-air missile from a maneuvering target aircraft. The filter exploits knowledge of the dominant aerodynamically induced lift and drag forces of a non-thrusting missile employing proportional navigation guidance, and it also accounts for the dynamic lag and bandwidth effects of the missile seeker, guidance, and control systems. Incorporating the refined missile acceleration model enhances the filter's tracking estimate precision and provides meaningful threat predictive capabilities. Identifiability of parameters within the acceleration model is established, an adaptive filter is developed, and its performance capabilities portrayed through realistic Monte Carlo simulations.