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Differential Geometry maneuvering target intercept guidance law

Author: LiKeBo
Tutor: ChenLei
School: National University of Defense Science and Technology
Course: Aeronautical and Astronautical Science and Technology
Keywords: Missile guidance Differential Geometry Curvature and torsion sight Instantaneous rotation plane Capture region Fixed differential geometric guidance
CLC: TJ765
Type: Master's thesis
Year: 2010
Downloads: 290
Quote: 1
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Abstract

In this paper, the end of the maneuvering target intercept guidance law for the study, the main thought in differential geometry studied terminal guidance law application. Proposed a new idea for the line of sight rotation, the rotation of the line of sight into the instantaneous rotation of the plane of rotation of the plane of rotation, and the instantaneous rotation, and with the resistance Frey - Competition Ray (Frenet-Serret) equation is established by combining rotation system based on the line of sight missile target relative motion equation. In this equation on the basis of maneuvering target intercept guidance law research. First, based on differential geometry Thought sight rotation and made eye curvature and torsion of the concept of the curvature and torsion got sight rate expressions. Based on the curvature and torsion of the line of sight has been playing the target relative motion equations, the use of the missile target relative motion equation of proportional navigation law, and with the line of sight coordinate system of the classic proportional navigation law comparative studies, also studied the introduction of the line of sight angle rotor rate derivative proportional navigation law, and proportional navigation law of its comparative analysis. Secondly, in-depth study of Chiou and Kuo proposed arc domain differential geometric guidance, as well as domestic Lichao Yong et al, the time domain of differential geometry guidance law based on the proposed use of Chapter II missile target relative motion equations to study the differential geometric guidance principles and characteristics of the plane of rotation proposed instantaneous differential geometric guidance, and to prove that the guidance law has two forms: TPN forms and differential geometry motorized forms (PPN form). Differential Geometry maneuver in which the form and time domain differential geometric guidance law has the same characteristics. Then on the interceptor missile maneuver in the form of differential geometry conditions for initial capture theory. Again, in Chapter II of the missile target relative motion equations based on the use Feng Tyan capture area proposed research methods, the plane of rotation of the three instantaneous guidance law capture regional analysis. The study found, Feng Tyan capture area of relative motion is used when a multi-variable equation of the form of complex and not conducive to understanding the shortcomings of using the proposed target relative motion equation of the elastic, can effectively improve these shortcomings. Finally, the guidance law project implementation and simulation were studied. Using cubic spline function for the line of sight angle of the filter analysis, from the theoretical study of the control system delay the impact on guidance law. Then chapter examines the differential geometry of practical guidance law is proposed to introduce the instantaneous rotation plane LOS rate derivative corrected differential geometric guidance, avoiding the direct introduction of target maneuver acceleration. Through simulation analysis, we found that the guidance law can effectively compensate for maneuvering target acceleration, and its performance in simulation directly into the target differential geometry acceleration guidance law is basically the same, compared with the proportional navigation law has improved greatly. Projectile proposed relative motion equation, which is derived based on the curvature of the line of sight rotation and torsion, and the traditional sight coordinate system relative motion equation compared to more simple forms and more clear physical meaning. Based on relative motion equation proposed research terminal guidance law instantaneous plane of rotation, the three-dimensional problem is reduced to a two-dimensional block analysis, reducing the analysis of the problem more difficult. The traditional differential geometric guidance on the interceptor and target speed has limitations (size constant speed, acceleration perpendicular to the direction of the velocity), this paper presents the instantaneous rotation of the plane of the differential geometric guidance of its two motorized forms of interceptor missile and the target does not have a limit, acceleration interceptor missile guidance commands can be perpendicular to the line of sight and perpendicular to the velocity of the two directions to choose, within the atmosphere and thus meet the dual needs of atmospheric interceptors. The proposed amendment differential geometric guidance only need to introduce LOS rate derivatives, which can compensate for maneuvering target acceleration and significantly reduce overload and interceptor missile miss distance, with good usability.

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