Topic
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.
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TL;DR: In this article, the trajectories of an ideal missile homing on a target according to the proportional navigation law were analyzed and conditions were determined which enable one to demonstrate that the missile always reaches the target regardless of the initial conditions at launch; the rotational rate of the line of sight is decreasing at the pursuit end.
Abstract: This paper represents a study of the trajectories of an ideal missile homing on a target according to the proportional navigation law. A qualitative study is performed and conditions are determined which enable one to demonstrate that: 1) the missile always reaches the target regardless of the initial conditions at launch; 2) the rotational rate of the line of sight is decreasing at the pursuit end.
240 citations
TL;DR: In this article, the authors derived linear quadratic guidance laws that explicitly enable imposing a predetermined intercept angle for arbitrary-order linear missile dynamics, which are dependent on the well-known zero-effort miss distance and on a new variable denoted zeroeffort angle.
Abstract: Linear quadratic guidance laws that explicitly enable imposing a predetermined intercept angle are presented. Two such guidance laws are derived, using optimal control and differential game theories, for arbitrary-order linear missile dynamics. The obtained guidance laws are dependent on the well-known zero-effort miss distance and on a new variable denoted zero-effort angle. It is shown that imposing the terminal angle constraint raises considerably the gains of the guidance laws. Theoretic conditions for the existence of a saddle-point solution in the differential game are also derived. These conditions show that imposing the terminal angle constraint requires a higher maneuverability advantage from the missile. The performance of the proposed guidance laws is investigated using a nonlinear two-dimensional simulation of the missile's lateral dynamics and relative kinematics, while assuming first-order dynamics for the target's evasive maneuvers. Using a Monte Carlo study, it is shown that, for the investigated problem, a target can be intercepted with a negligible miss distance and intercept angle error even when the target maneuvers and there are large initial heading errors.
228 citations
TL;DR: In this article, a linear closed loop guidance law was proposed to compensate for the acceleration and time varying navigation gain in short-range intercept trajectories, which is applicable to short range air-to-ground and airto-air interception.
Abstract: Introduction "IVTISSILE dynamic time lags, guidance command satura1? JL tion, and target acceleration are major factors contributing to excessive terminal miss distances resulting from shortrange intercept trajectories. The objective of this Technical Note is to describe a linear closed loop guidance law which compensates for these factors. Optimal control theory is utilized where the missile dynamics, represented as a single time lag, and target acceleration are defined in the constraint equations. A quadratic performance index is employed which implicitly effects a "soft" limit on the acceleration command. A zero terminal miss distance is the only boundary constraint imposed on the problem. The final form of the guidance law which includes a time varying navigation gain represents an extension of the guidance laws discussed by Bryson, Garber, and Abzug and is applicable to short range air-to-ground and air-to-air interception.
217 citations
TL;DR: It is shown how the target can lure in the attacker, allowing its defender to intercept the attacking missile even in scenarios in which the defender's maneuverability is at a disadvantage compared with the attacking ballistic missile.
Abstract: Optimal-control-based cooperative evasion and pursuit strategies are derived for an aircraft and its defending missile. The aircraft-defending missile team cooperates in actively protecting the aircraft from a homing missile. The cooperative strategies are derived assuming that the incoming homing missile is using a known linear guidance law. Linearized kinematics, arbitrary-order linear adversaries' dynamics, and perfect information are also assumed. Specific limiting cases are analyzed in which the attacking missile uses proportional navigation, augmented proportional navigation, or optimal guidance. The optimal one-on-one, noncooperative, aircraft evasion strategies from a missile using such guidance laws are also derived. For adversaries with first-order dynamics it is shown that depending on the initial conditions, and in contrast to the optimal one-on-one evasion strategy, the optimal cooperative target maneuver is either constant or arbitrary. These types of maneuvers are also the optimal ones for the defender missile. Simulation results confirm the usefulness and advantages of cooperation. Specifically, it is shown how the target can lure in the attacker, allowing its defender to intercept the attacking missile even in scenarios in which the defender's maneuverability is at a disadvantage compared with the attacking missile.
185 citations
Journal Article•
TL;DR: In this paper, a variable structure control (VSC) based guidance law for a single-missile system is proposed, where the acceleration command is determined considering the target acceleration information as uncertainty.
Abstract: New missile guidance law is proposed via variable structure control. The acceleration command is determined considering the target acceleration information as uncertainty. Target and missile are assumed to be point masses moving in the two dimensional plane. According to the property of the missile acceleration command, the proposed guidance laws are classified into IPN type and RTPN type. Moreover, it is shown that the conventional proportional guidance laws can be derived from the proposed guidance law. Numerical simulation results show that the proposed guidance law exhibits better performance compared to the conventional proportional guidance laws.
182 citations