Integrated design method for gliding section guidance and attitude control of hypersonic aircraft

Abstract

The invention discloses an integrated design method for gliding section guidance and attitude control of a hypersonic aircraft. The method comprises the steps of taking the geocentric distance of thecurrent moving target and the latitude and longitude of the moving target as the input of a gliding section guidance and attitude control integrated model of the hypersonic aircraft; and generating acontrol rudder deflection angle according to a control scheme of the gliding section guidance and attitude control integrated control model of the hypersonic aircraft, inputting the control rudder deflection angle into a six-degree-of-freedom motion model of the hypersonic aircraft, and enabling the hypersonic aircraft to fly to a motion target to complete a flight task. According to the method, acontrol scheme of a hypersonic aircraft gliding section guidance and attitude control integrated model is designed based on a block dynamic surface method; according to the method, the attitude control task requirement of the gliding section of the aircraft is met, the guidance and control precision is high, the whole-course output change of the control quantity is smooth, the task adaptability of the aircraft is improved, and the problem that the guidance and control of the hypersonic aircraft are difficult to coordinate is effectively solved.

Description

technical field [0001] The invention relates to the field of aircraft control, in particular to a guidance and control method for the glide section of a hypersonic aircraft. Background technique [0002] The basic process of the gliding flight of a hypersonic vehicle is to control the stable flight of the vehicle to reach the preset target end point while satisfying various process constraints. For the "boost-glide" hypersonic vehicle, long-term unpowered gliding flight in adjacent space is its biggest advantage compared with traditional ballistic missiles, which effectively improves the range and attack capability of the vehicle. [0003] However, due to the extremely high flight speed of the hypersonic vehicle, the motion of the center of mass and the motion around the center of mass both present the characteristics of fast time-varying, nonlinear, strong coupling, and uncertainty. The traditional aircraft guidance and control system is mainly based on the spectrum separa...

AI Technical Summary

Problems solved by technology

[0004] At present, the research on hypersonic vehicles is mainly aimed at the separation design of the guidance and control system of hypersonic vehicles and the integrated design method of the guidance and attitude control system in the glide phase. There are few achievements, and no relevant technologies have been disclosed so far

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