Trajectory optimization method of midcourse guidance with constraints

Abstract

The invention discloses a trajectory optimization method of a midcourse guidance with constraints. The trajectory optimization method is used for reducing a shift velocity of a terminal guidance in anintercepting missile. The method comprises the following steps: establishing a kinematic equation of a whole trajectory in a longitudinal plane of the intercepting missile including a trajectory constraint and a terminal constraint, and constructing an intercepting missile trajectory optimization model according to an optimal trajectory of midcourse guidance with constraints set by the method; and optimizing a solution of the trajectory by adopting an hp self-adaptive pseudo-spectral method. According to the method, the shift velocity of the terminal guidance in the intercepting missile can be reduced, a good flight regime of the terminal guidance can be provided and an intercepting precision is improved. And the method is a promising trajectory manner.

Description

technical field [0001] The invention belongs to the field of ballistic optimization of missiles, in particular to a method for optimizing ballistics of intermediate guidance with constraints. Background technique [0002] When traditional interceptors face high-speed targets, they are limited by the performance of missile time constants, steering gear response time, and guidance control system response speed. If the relative speed is too high, it will lead to the failure of the mid-to-terminal guidance shift; even if the shift is successful, Guidance accuracy is bound to decrease, thereby affecting interception effectiveness. [0003] In view of the characteristics of large flight span and obvious characteristics of high-speed targets, the flight trajectory of the interceptor missile in the guidance stage can be optimized. By designing the climbing trajectory, gravity can be used to reduce the speed of the interceptor missile flying to the handover area, thereby reducing the...

AI Technical Summary

Problems solved by technology

[0004] Aiming at the problem of failure of mid-to-terminal guidance handover caused by excessive relative speed when intercepting high-speed targets, the present invention provides a constraint-based medium-to-terminal guidance ballistic trajectory optimization method. The terminal guidance flight state improves the interception accuracy

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