A Multi-constraint Guidance Method for Air-launched Cruise Bounce Down Section Including Normal Acceleration Derivative

Abstract

The invention discloses a multi-constraint guidance method containing the normal acceleration derivative for a glide phase of an air-launched cruise missile. The multi-constraint guidance method specifically comprises the steps that firstly, missile aerodynamic parameters are determined, and parameters of an atmosphere model are established; secondly, a missile motion equation set is established according to the missile aerodynamic parameters and the parameters of the atmosphere model; thirdly, linear processing is conducted on the missile motion equation set; fourthly, a normal acceleration derivative equation is added in the equation set which is linearly processed, and an analytical algorithm equation set is obtained; fifthly, the tail end constraint and the path constraint which need to be met through the glide phase of a trajectory are determined; sixthly, the optimal controlled variable u is determined according to the analytical algorithm equation set and the optical control index function; and seventhly, an analytical guidance law is obtained by solving the optimal controlled variable u, and thus the glide phase of the trajectory of the missile meets the tail end constraint and the path constraint. The multi-constraint guidance method has the advantages that the constraints of the trajectory inclination angle, speed, normal acceleration and normal acceleration first derivative are met while the effect that the missile reaches the regulated tail end height is guaranteed, and the flying quality of the missile is improved.

Description

technical field [0001] The invention belongs to the fields of aerospace technology and weapons, and relates to an analytical solution of a multi-constraint guidance law for the downslope of an air-launched cruise missile, in particular to a multi-constraint guidance method for the downslope of an air-launched cruise missile that includes normal acceleration derivatives. Background technique [0002] An air-launched cruise missile refers to a cruise missile launched from the air, and its trajectory includes a glide phase, a level flight phase, and a dive phase. The glide phase not only needs to meet a number of terminal state constraints (mainly including the terminal height, ballistic inclination angle, velocity and attack normal acceleration constraints), but also shorten the glide phase time as much as possible to improve concealment. [0003] The traditional guidance method is ballistic tracking guidance. The standard trajectory used can be obtained by means of program tr...

AI Technical Summary

Problems solved by technology

[0004] The present invention aims at the problems in the prior art that the glide section of the missile cannot be lowered quickly, and the end of the glide section of the missile cannot be pulled up smoothly; a multi-constraint guidance method for the glide section of the air-launched cruise missile including the normal acceleration derivative is proposed, which ensures When the missile reaches the specified terminal height, it satisfies the constraints of ballistic inclination, velocity, normal acceleration and first derivative of normal acceleration, which improves the flight quality of the missile

Images