Missile

About: Missile is a research topic. Over the lifetime, 12829 publications have been published within this topic receiving 94307 citations. The topic is also known as: guided missile & missiles.

Triangle Intercept Guidance for Aerial Defense

Abstract: This paper focuses on missile guidance methods for a defense missile trying to protect a cooperative aircraft from guided munitions which have the same thrust and maneuvering capabilities as that of the defense missile. A novel guidance law for the missile-to-missile intercept is developed via a simple geometrical approach. The potential of the guidance law is demonstrated and discussed with some simulation results. Performance comparison with a conventional guidance law is also presented. Nomenclature C a = BM acceleration command normal to velocity vector, m/s 2 BA = blue aircraft (cooperative aircraft) BM = blue missile (defense missile) I, J = performance indices LOS ij = line-of-sight from the vehicle j to the vehicle i (Subscripts, A, M, and T denote BA, BM, and RM, respectively.) N , d N = navigation constant of the TG RM = red missile (attacking missile or target) ij r , ij r = LOS ij vector, and LOS ij range, m

Active target defense differential game

Abstract: A pursuit-evasion differential game involving three agents is discussed. This scenario considers an Attacker missile pursuing a Target aircraft. The Target is however aided by a Defender missile launched by, say, its wingman, to intercept the Attacker before it reaches the Target aircraft. Thus, a team is formed by the Target and the Defender which cooperate to maximize the distance between the Target aircraft and the point where the Attacker missile is intercepted by the Defender missile, and the Attacker which tries to minimize said distance. The solution to this differential game provides optimal heading angles for the Target and the Defender team to maximize the terminal separation between Target and Attacker and it also provides the optimal heading angle for the Attacker to minimize the said distance.

Projectile trajectory control system

Abstract: Trajectory is controlled by a control system having fins that de-spin a section of the control system relative to a projectile or missile. The control system also includes aero- surfaces that produce a lift when brought to rotation speed of about 0 Hz relative to a reference fame and a brake that couples the guidance package to the rotational inertia of the projectile or missile. In one example, no electric motor is used in the trajectory control system, saving weight and increasing reliability.