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.

Missile system and method for performing automatic fire control

Abstract: A missile system and method for performing automatic fire control in which a reconnaissance vehicle is used to gather video reference information of a target and this information is then communicated to a launching vehicle from which missiles are caused to be trained on the selected target by utilizing an automatic target handoff correlator that identifies the selected target, causes an autotracker to be locked on and finally a computer is signaled by the automatic target handoff correlator to cause a missile to be fired.

Fixed-Time Cooperative Guidance Law With Angle Constraint for Multiple Missiles Against Maneuvering Target

Abstract: This paper addresses the problem of the fixed-time cooperative guidance (FxTCG) law for multi-missiles against a single maneuvering target with constraints of both the interception time and the line-of-sight (LOS) angle. Firstly, by utilizing the consensus protocol and the fixed-time consensus theory, a new FxTCG in the LOS direction is presented to guarantee that the multiple missiles intercept the incoming target synchronously. Moreover, the acceleration of the target causes disturbance, so a simple fixed-time disturbance observer (FxTDO) is introduced to compensate FxTCG with the disturbance estimation. Subsequently, the FxTCG in the normal direction of the LOS is designed based on an adaptive fixed-time convergence reaching law and the proposed FxTDO, which ensures the fixed-time convergence of the LOS angular velocity and LOS angle between each missile and the maneuvering target. Finally, numerical simulations and adequate analyses are carried out to illustrate the accuracy, effectiveness, and robustness of the proposed FxTCG scheme.

Robust Missile Autopilot Design Using Two Time-Scale Separation

Abstract: In this paper, time-scale separation, feedback linearization (FL), and extended state observer (ESO) based new design for an acceleration tracking pitch autopilot of a tail controlled, skid-to-turn tactical missile is presented. The pitch plane dynamics has been split into pitch rate dynamics as fast, and the acceleration dynamics as a slow subsystem by exploiting the naturally existing time-scale separation between them. FL-based controllers are then designed for the subsystems separately. To achieve robustness in the presence of uncertainties and disturbances, an ESO is designed for each of the subsystem separately. The ESOs estimate the effect of uncertainties in the respective subsystem and the estimate is used to robustify the feedback linearizing controller designed for the respective nominal subsystem. The design neither requires accurate plant model nor any information about the uncertainty. Closed-loop stability for the overall system is established. The effectiveness of the design in meeting specified tracking performance in the presence of significant uncertainties, unmodeled dynamics, measurement noise, control input, and rate saturation, and in varying missile velocity and altitude scenario is illustrated by simulation. Furthermore, to analyze the performance for different initial conditions and parameter perturbations, Monte Carlo simulation study is carried out and the results are presented. Finally, performance comparison of the proposed design with some existing controllers is presented to showcase the efficacy of the proposed design.

Static self-contained laser seeker system for active missile guidance

Abstract: Four pulse-repetition-frequency coded laser diode arrays emit four beams in quadrature relationship having a central optical axis coinciding with the missile axis. The returned reflected energy from a target impinges upon an optically centered holographic quadrant selector detection system which provides quadrature output signals. These quadrature output signals are passed through respective pulse-repetition-frequency discriminators corresponding to the quadrature prf coded transmitted beams. The outputs from the discriminators are processed through a null comparison circuit to provide output signals for actuating the servo guidance system of the missile to center the optical axis, which is also the missile axis, on the target so that the missile continuously seeks and eventually flies into the target.

Multiple Model Adaptive Evasion Against a Homing Missile

Abstract: Multiple model adaptive evasion strategies from an incoming homing missile are presented. The problem is formulated in the context of an evading target aircraft having imperfect information on the relative state and on the employed guidance law and guidance parameters of the missile. The missile’s guidance strategy is assumed to belong in a finite set of linear guidance laws and to be fixed throughout the engagement. Arbitrary-order linear missile and target dynamics, bounded target control, and nonlinear kinematics are also assumed. The filter used to identify the missile’s guidance strategy is a nonlinear adaptation of the multiple model adaptive estimator, in which each model represents a possible guidance law and corresponding guidance parameters of the attacking missile. Specific limiting cases are carefully analyzed in which the attacking missile uses proportional navigation, augmented proportional navigation, or an optimal guidance law. Matched optimal evasions from these specific cases are also de...