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Air-to-air missile

About: Air-to-air missile is a research topic. Over the lifetime, 445 publications have been published within this topic receiving 3165 citations. The topic is also known as: AAM & air intercept missile.


Papers
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Proceedings ArticleDOI
15 Jun 1988
TL;DR: In this paper, the assumptions, benefits, and limitations of recent applications of nonlinear filtering, adaptive filtering, modern control, adaptive control, dual control, differential game theory, and modern control design techniques to the air-to-air missile problem are discussed.
Abstract: This paper provides an assessment of current air-to-air missile guidance and control technology. Areas explored include target state estimators, advanced guidance laws, and bank-to-turn autopilots. The assumptions, benefits, and limitations of recent applications of nonlinear filtering, adaptive filtering, modern control, adaptive control, dual control, differential game theory, and modern control design techniques to the air-to-air missile problem are discussed.

56 citations

Journal ArticleDOI
TL;DR: The results show that the proposed guidance law is far superior to the guidance law that employs only augmented proportional navigation throughout the interception course, in regard to extending the launch boundaries or minimizing the interception time.
Abstract: An advanced midcourse guidance law for medium-range air-to-air missiles is proposed. The law consists of two different guidance modes: the final velocity maximum or the final time minimum, depending on the initial missile-target geometry. The former is preferable against a highly maneuverable target at a great distance, whereas the latter is demanded against a near target. This midcourse guidance law is combined with augmented proportional navigation in the homing phase. Performance is evaluated by computer simulations against conventional and advanced targets. The results show that the proposed guidance law is far superior to the guidance law that employs only augmented proportional navigation throughout the interception course, in regard to extending the launch boundaries or minimizing the interception time.

55 citations

Proceedings ArticleDOI
01 Jan 1996
TL;DR: In this article, two nonlinear autopilot design approaches for a tail-controlled high angle of attack air-to-air (A2A) missile are described, which employs a highly nonlinear, time varying pitch plane rigid-body dynamical model of a short range missile.
Abstract: Two nonlinear autopilot design approaches for a tail-controlled high angle of attack air-to-air missile are described. The research employs a highly nonlinear, time varying pitch plane rigid- body dynamical model of a short range missile. Feedback linearization technique together with linear control theory are then used for autopilot design. In order to manage the difficulties associated with "zerodynamics" that arise in tail controlled missiles, two distinct approaches for approximate feedback linearization are advanced. The first approach imposes a time-scale structure in the closed-loop dynamics, while the second technique redefines the output. Performance of these autopilots are illustrated in a nonlinear simulation.

52 citations

Journal ArticleDOI
TL;DR: In this paper, a receding horizon control scheme for an aircraft trying to avoid a closing air-to-air missile is proposed, where the optimal control of the aircraft over a short planning horizon is solved online by the direct shooting method at each decision instant.
Abstract: The paper introduces a receding horizon control scheme for obtaining near-optimal controls in a feedback form for an aircraft trying to avoid a closing air-to-air missile. The vehicles are modeled as point-masses. Rotation kinematics of the aircraft are taken into account by limiting the pitch and roll rates as well as the angular accelerations of the angle of attack and the bank angle. The missile utilizes proportional navigation and it has a boost-sustain propulsion system. In the proposed scheme, the optimal controls of the aircraft over a short planning horizon are solved on-line by the direct shooting method at each decision instant. Thereafter, the state of the system is updated by using only the first controls in the sequence, and the process is repeated. The performance measure defining the objective of the aircraft can be chosen freely. In this paper, six performance measures consisting of the capture time, closing velocity, miss distance, gimbal angle, tracking rate, and control effort of the missile are considered. The quality of the receding horizon solutions computed by the scheme is validated by comparing them to the off-line computed optimal open-loop solutions.

49 citations

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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
20233
20226
20212
20207
201911
20187