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Research On Guidance Law Of Maneuvering Target Interception

Posted on:2022-07-18Degree:MasterType:Thesis
Country:ChinaCandidate:S Z XieFull Text:PDF
GTID:2492306572460484Subject:Control Engineering
Abstract/Summary:PDF Full Text Request
In the traditional terminal guidance interception,when designing a guidance law with angle of attack constraints,it often assumes that the target is moving at a constant speed or is at a standstill,without considering the target maneuver.In addition,the scope of applicability of various guidance laws designed by different scholars is ambiguous,so there is no clear plan for which guidance law to choose under the constraints of different interception performance indicators.Aiming at the above problems,this paper designs a filtering algorithm for maneuvering target motion transition and a guidance law with angle of attack constraints.Through interception simulation experiments,a guidance law selection strategy under the constraints of different interception performance indicators is proposed.The specific research content includes the following aspects:Firstly,the six-degree-of-freedom model of the missile is established from the aspects of missile kinematics and dynamics,and the dynamic model of missile attitude control is given.Secondly,different target maneuvering forms are designed,the target motion model is established,two target tracking filtering algorithms based on the azimuth angle and the relative distance of the projectile and eye are designed,and the error of the target motion state estimation error of the two algorithms is compared.Next,the relative kinematics model of the bullet and eye is established,the attack angle constraint problem is transformed into the line of sight angle constraint problem,and the design based on bias proportional guidance,linear integral sliding film,nonlinear integral sliding mode and nonlinear interference observer Four guiding laws of nonlinear integral synovium.Finally,the factors affecting the interception performance of the guidance law in the terminal guidance stage are analyzed,and the interception simulation experiment based on the control variable method is designed.The interception effects of the four guidance laws under different constraints are compared,and the choice of guidance law is given.
Keywords/Search Tags:state estimation of maneuvering target, impact angle constraint, nonlinear integral sliding mode control
PDF Full Text Request
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