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, a parametric affine missile model adopts acceleration as the controlled output and considers the couplings between the forces as well as the moments and control fin deflections.
Abstract: This paper presents a new practical autopilot design approach to acceleration control for tail-controlled skid-to-turn (STT) missiles. The approach is novel in that the proposed parametric affine missile model adopts acceleration as the controlled output and considers the couplings between the forces as well as the moments and control fin deflections. The aerodynamic coefficients in the proposed model are expressed in a closed form with parameters that can be fitted over the whole operating range. The parameters are fitted from aerodynamic coefficient lookup tables by the proposed function approximation technique, which is based on the combination of local parametric models through curve fitting using the corresponding influence functions. In addition, a feedback linearizing controller is designed by using the proposed parametric affine missile model. Stability analysis for the overall closed-loop system is provided, considering the uncertainties arising from approximation errors. The validity of the proposed modeling and control approach is demonstrated through simulations for an STT missile.
42 citations
01 Jan 1992
TL;DR: In this paper, a gain-scheduled design for a missile longitudinal autopilot is presented, which does not involve linearizations about trim conditions of themissile dynamics, but instead brings themissile dynamics to a quasi-linear parameter varying (LPV)form via a statetransformation.
Abstract: This paper presents a gain-scheduled design for a missile longitudinal autopilot. Thegain-scheduled design is novel inthat itdoes notinvolve linearizations about trim conditions ofthemissile dynamics. Rather, themissile dynamics arebrought toa quasi-linear parameter varying(LPV)formviaa statetransformation. AnLPV systemisdefined asalinear systemwhose dynamics depend on anexogenousvariable whose valuesareunknown apriori butcanbemeasured upon systemoperation. In this case,thevariable istheangle-of-attack. This isactually anendogenous variable, hence the expression "quasiLPV".Onceina quasi-LPV form, a robust controller using p-synthesis isdesigned toachieve normal acceleration control viafindeflections. Thefinal design isan inner/outer loopstructure, withangle-of-attack control being theinner-loop, andnormal-acceleration control beingtheouterloop.
42 citations
TL;DR: In this article, two types of guidance and control design concepts are explored: a traditional separated approach and an integrated one, using the integrated approach, two different guidance systems are presented: a single-loop guidance law and a two-loop autopilot-guidance law.
Abstract: Two types of guidance and control design concepts are explored: a traditional separated approach and an integrated one. Using the integrated approach, two different guidance systems are presented: a single-loop guidance law and a two-loop autopilot-guidance law. In the two-loop case, the autopilot loop is designed separately from the guidance one, but all the states are fed back into the guidance loop. It is proven that the integrated guidance laws achieve the same performance for single-input single-output systems. The performance of the three guidance laws is evaluated and compared via a thrust vector control missile. It is shown that the performance of the separated guidance law is inferior to that of the integrated laws.
42 citations
TL;DR: It is proved that zero miss distance can always be guaranteed for some initial conditions and it is shown that for the tail control a switching surface at some constant time before interception exists in the game-space, resulting from its nonminimum-phase nature.
Abstract: A new guidance law tailored for an interceptor missile having forward and aft controls is proposed. The guidance law is derived using a differential games formulation with bounded controls. For the derivation, the interceptor closed-loop dynamics is represented by two first-order bi-proper transfer functions. Possible game-space structures are investigated, including a new one with two closed singular regions. The effect of the direct lift associated with the canard and tail controls is investigated, and it is proved that zero miss distance can always be guaranteed for some initial conditions. It is also shown that for the tail control a switching surface at some constant time before interception exists in the game-space, resulting from its nonminimum-phase nature.
42 citations
04 Jun 2007
TL;DR: It will be shown that a digital cross-eye system with several antenna units can be seriously affected by scattering from sea waves and terrain.
Abstract: Radar seeking missiles present a serious threat towards ships and aircraft. In cross-eye jamming a missile seeker is deflected by signals from two onboard antennas transmitting out of phase with signals of nearly equal strength. The limits on cross-eye performance imposed by scattering have been studied when scattering takes place far from the propagation path. It will be shown that a digital cross-eye system with several antenna units can be seriously affected by scattering from sea waves and terrain.
42 citations