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.

Application of Integrated Guidance and Control Schemes to a Precision Guided Missile

Abstract: Three optimal integrated guidance and control (IGC) laws for a tactical missile are developed. The three IGC design models include planar intercept kinematics and missile longitudinal dynamics in one mathematical framework. A target acceleration model and missile radome error compensation scheme are inluded in the state formulations. An optimality criterion which asymptotically imposes an infinite penalty on miss distance and angle-of-attack in the endgame as time-to-intercept goes to zero is minimied. Using reasonable approximations, an analytic solution is derived which can be easily implemented as an endgame guidance law/autopilot in current missile flight computers. Nonlinear six degree-of-freedom simulation results will be presented at the session to demonstrate the performance of these three algorithms.

A method for combatting of targets and projectile or missile for carrying out the method

Abstract: The invention relates to combatting of hostile targets (M) by firing of controllable explosive projectiles or missiles (P, PO) towards the target, which projectiles or missiles are provided with target tracking devices for automatic guidance of the projectile or missile by reception and detection of electromagnetic radiation originating from the target. In order to improve the accuracy of fire at least one projectile or missile fired in a burst is provided with transmitter means (T, A1) which are activated after detection of a target (M) for transmission of a signal indicating the position of the target relative to the projectile to following projectiles in the burst. In these following projectiles (P) a correction of the projectile trajectory in direction to a trajectory passing through the target is effected by means of the position indicating signal from the preceeding projectile (PO). Suitably all projectiles in a burst can be provided with such transmitter means (T, A1). Hereby each projectile in the burst will get a more correct trajectory towards the target as compared the closest foregoing projectile and reliable hit will be ensured after a relatively small number of projectiles. The target tracking device may be of any known type, as devices of radiometric type, radar or IR-type, electro-optical tracking device operating with visible light or laser light (Figure 1a).

Two non-linear problems in the flight dynamics of modern ballistic missiles

Abstract: : While the linear theory has been the backbone of ballistic missile design and has served with excellent success in its various forms over the years, recent spectacular missile flight failures have appeared unexpectedly and are unaccounted for by this linear theory. It is these flight failures which now require attention and consideration of the non-linearities in the fluid force and moment system which contribute to missile flight performance and dynamic stability. Two types of non-linear flight instability have been isolated and identified as NonLinear Magnus Instability, and Catastrophic Yaw. It is these 2 flight instabilities which will be discussed. Approximate mathematical models will be suggested for the evaluation of missile dynamic stability. Both experimental and analytical applications of these models will be made and discussed.