Trajectory optimization method suitable for combined power hypersonic aircraft

Abstract

The invention belongs to the technical field of hypersonic aircraft design, and particularly relates to a trajectory optimization method suitable for a combined power hypersonic aircraft. The method comprises the following steps: S1, constructing a control-oriented mathematical model of the combined power hypersonic aircraft, wherein the control-oriented mathematical model comprises mathematical models of lift coefficients, resistance coefficients, thrust and specific impulse under independent work and combined work of all power assemblies; S2, constructing a kinetic model based on four statevariables of speed, height, track angle and mass of two control variables of attack angle and rocket flow opening degree; S3, determining constraint conditions during climbing of the combined power hypersonic aircraft, and selecting a set optimization target; and S4, solving an optimal climbing trajectory based on a Gauss pseudo-spectral method according to the optimization target. The trajectoryoptimization method based on the self-adaptive Gauss pseudo-spectral method is adopted, so the problems that a traditional trajectory optimization method is low in solving precision and low in speed are solved.

Description

technical field [0001] The application belongs to the technical field of hypersonic aircraft design, and in particular relates to a trajectory optimization method suitable for combined power hypersonic aircraft. Background technique [0002] As a potential new military and civilian aircraft in the future, hypersonic aircraft will have high economic value by promoting the development of its related technologies to help speed up its research process. [0003] The trajectory optimization problem of combined power hypersonic aircraft is a complex, highly nonlinear, multi-variable, multi-constraint optimal control problem. The research on this problem embodies aerodynamics, flight mechanics, modern control theory and optimization theory, etc. The intersection of many disciplines is the most challenging research problem in the superb field. There are mainly the following technical difficulties: [0004] (1) The unique dynamic mode of hypersonic aircraft, the three power modes of...

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Problems solved by technology

[0004] (1) The unique dynamic mode of hypersonic aircraft, the three power modes of turbine, ram, and rocket have different working characteristics, and lack of high-precision mathematical models;

[0005] (2) The flight corridor of combined power hypersonic aircraft is strictly constrained; the complexity of the intake and exhaust system leads to an increase in the amount of control, and the difficulty of trajectory control under multi-variable and multi-constraint conditions increases;

[0006] (3) The dynamic characteristics of hypersonic aircraft are complex, and traditional trajectory optimization methods (such as shooting methods, conventional pseudospectral methods, etc.) have disadvantages such as difficult selection of initial guess values, low solution accuracy, and slow solution speed.

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