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A Fast Trajectory Optimization Method for Hypersonic Vehicle Based on State Integral Gradient-Repair Algorithm

A trajectory optimization, hypersonic technology, applied in missile ballistics, rocket field

Active Publication Date: 2020-04-24
HARBIN INST OF TECH
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Problems solved by technology

[0005] The purpose of the present invention is to solve the problem of rapid trajectory optimization of hypersonic aircraft in complex flight environments, and provides a method for rapid trajectory optimization of hypersonic aircraft based on the gradient-repair algorithm of state integrals

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  • A Fast Trajectory Optimization Method for Hypersonic Vehicle Based on State Integral Gradient-Repair Algorithm
  • A Fast Trajectory Optimization Method for Hypersonic Vehicle Based on State Integral Gradient-Repair Algorithm
  • A Fast Trajectory Optimization Method for Hypersonic Vehicle Based on State Integral Gradient-Repair Algorithm

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[0101] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0102] combine figure 1 , the present invention proposes a hypersonic vehicle rapid trajectory optimization method based on a gradient-repair algorithm of state integrals, comprising the following steps:

[0103] Step 1: Perform dimensionless processing on the dynamic model of the hypersonic vehicle, reasonably transform the process constraints and terminal constraints in trajectory optimization, select the sampling point density and determine the trajectory opt...

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Abstract

The invention discloses a state integral gradient-repair algorithm based fast trajectory optimization method of a hypersonic aerocraft. The method comprises the steps as follows: 1, performing dimensionless processing on a dynamical model of the hypersonic aerocraft, performing reasonable transformation on process constraint conditions and terminal constraint conditions in trajectory optimization,selecting a sampling point density based on a precision demand of the trajectory optimization and determining a trajectory optimization model; 2, judging a satisfaction condition of the flight trackof the hypersonic aerocraft for a constraint equation and an optimal equation under an initial condition or after gradient approximation operation; and 3, smoothening the obtained optimization result,removing jump points in a controlled quantity result and smoothening by applying an interpolation method. The state integral gradient-repair algorithm based fast trajectory optimization method of thehypersonic aerocraft solves the fast trajectory optimization problem of the hypersonic aerocraft in a complex flight environment.

Description

technical field [0001] The invention relates to a hypersonic vehicle rapid trajectory optimization method based on a gradient-restoration algorithm of state integrals, and belongs to the technical field of rocket and missile ballistics. Background technique [0002] With the vigorous development of aerospace technology, the trajectory design problem of aircraft under multiple constraints has become the focus of many scholars' research, and it is an effective solution to transform the above problems into aircraft trajectory optimization problems by applying optimization methods. At first, scholars focused on the analytical method, that is, deriving the analytical solution of the optimal trajectory of the aircraft according to the optimal control theory. Using this method needs to simplify the aircraft trajectory design problem, and the obtained results are difficult to meet the requirements of the aircraft trajectory in complex flight environments. Designed application requir...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04G05D1/10
CPCG05B13/042G05D1/101
Inventor 崔乃刚韦常柱杨峰李源浦甲伦
Owner HARBIN INST OF TECH
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