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.
Papers published on a yearly basis
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TL;DR: In this article, a linear parameter-varying (LPV) control technique was used for the design of a high performance missile autopilot, which provided exponential stability guarantee and performance bound in terms of induced L 2 norm for the missile plant.
Abstract: The missile autopilot was designed using linear parameter-varying (LPV) control techniques. The controller provides exponential stability guarantee and performance bound in terms of induced L2 norm for the missile plant. The systematic gain-scheduling approach is motivated by the recent development in LPV control theory and provides a well founded and systematic procedure for high performance missile autopilot design problem.
59 citations
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TL;DR: This paper discusses the case where the Defender is endowed with a positive capture radius and a differential game is presented where the Target–Defender team strives to maximize the terminal separation between the Target and the Attacker at the time instant where the attacker is intercepted by the Defender.
Abstract: In air combat, an active countermeasure against an attacking missile homing into a Target aircraft entails the launch of a defending missile. The Target is protected by the Defender, which aims to intercept the Attacker before the latter reaches the Target aircraft. A differential game is presented where the Target–Defender team strives to maximize the terminal separation between the Target and the Attacker at the time instant where the Attacker is intercepted by the Defender, whereas the Attacker strives to minimize the said separation. This paper discusses the case where the Defender is endowed with a positive capture radius. Optimal strategies for the three agents are derived and simulation examples illustrate the effectiveness of the proposed approach.
59 citations
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CACI1
TL;DR: In this article, a full-envelope, hybrid bank-to-turn (BTT)/ skid-toturn (STT) autopilot design for an air-breathing airto-air missile is carried out using the state-dependent Riccati equation (SDRE) technique of nonlinear control.
Abstract: Nomenclature A full-envelope, hybrid bank-to-turn (BTT)/ skid-to-turn (STT) autopilot design for an air-breathing air-to-air missile is carried out using the state-dependent Riccati equation (SDRE) technique of nonlinear control. Hybrid BTT/STT autopilot command logic is used to convert the guidance law's commanded acceleration to angle of attack, side-slip, and bank angle reference commands for the autopilot. In the midcourse and terminal phases of flight, BTT control is employed to prevent engine flameout. In the endgame, STT control is employed to increase response time. As the missile approaches the endgame phase and passes a preset time-to-go threshold, STT commands are ramped into the BTT commands over a preselected time interval to attenuate transient responses. During this interval, the missile is flying hybrid BTT/STT. An SDRE nonlinear outer-loop controller converts the angle-of-attack, sideslip, and bank angle commands to body rates commands for the inner loop. An inner-loop SDRE nonlinear controller converts the body rate commands to fin commands. Hard bounds on the fin deflections are embedded within the inner-loop controller dynamics ensuring that the autopilot only commands deflections that are achievable. The nonlinear design is evaluated using a detailed six-degrees-of-freedom simulation.
59 citations
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TL;DR: Choosing the missile's lateral acceleration (latax) to enforce sliding mode on a switching surface defined by the line-of-sight angle leads to a guidance law that allows the achievement of the desired terminal impact angle.
Abstract: In this brief, variable structure systems theory based guidance laws, to intercept maneuvering targets at a desired impact angle, are presented. Choosing the missile's lateral acceleration (latax) to enforce sliding mode, which is the principal operating mode of variable structure systems, on a switching surface defined by the line-of-sight angle leads to a guidance law that allows the achievement of the desired terminal impact angle. As will be shown, this law does not ensure interception for all states of the missile and the target during the engagement. Hence, additional switching surfaces are designed and a switching logic is developed that allows the latax to switch between enforcing sliding mode on one of these surfaces so that the target can be intercepted at the desired impact angle. The guidance laws are designed using nonlinear engagement dynamics for the general case of a maneuvering target.
59 citations
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TL;DR: In this article, the authors proposed a new criterion termed as the Lethal Envelop, which is more relevant for coming generation of infrared-guided missiles, because of advancements in the infrared detection technology.
59 citations