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Adaptive rescue trajectory planning method based on numerical optimization algorithm

A technology of numerical optimization and trajectory planning, applied in adaptive control, instruments, control/regulation systems, etc., and can solve problems such as lack of

Active Publication Date: 2019-03-19
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST +1
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Problems solved by technology

At present, my country's launch vehicles do not have the ability to deal with failures and plan rescue trajectories

Method used

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  • Adaptive rescue trajectory planning method based on numerical optimization algorithm
  • Adaptive rescue trajectory planning method based on numerical optimization algorithm
  • Adaptive rescue trajectory planning method based on numerical optimization algorithm

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Embodiment Construction

[0080] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0081] The present invention is an adaptive rescue trajectory planning method based on a numerical optimization algorithm. After the failure of the launch vehicle, it is judged whether the rescue trajectory needs gravity-assisted gliding; Find the optimal rescue trajectory in the current orbital plane, as well as the rescue orbit that the launch vehicle can send the payload into; if gravity-assisted gliding is required, consider changing the orbital plane, and adjust the timing of orbit change by introducing gravity-assisted gliding to improve The utilization rate of the remaining fuel can be optimized to obtain the optimal rescue trajectory and the rescue trajectory that the launch vehicle can send the payload into. According to the evaluation of the remaining carrying capacity, the initial value of the trajectory planning numerical ...

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Abstract

The invention provides an adaptive rescue trajectory planning method based on a numerical optimization algorithm. According to the method, after a launch vehicle fails, it is judged whether or not therescue trajectory needs gravity-assisted taxiing after a fault; if no, remaining fuel and thrust are used for looking for an optimal rescue trajectory in the current orbital plane and a rescue orbitwhich the launch vehicle can send payload into; if yes, it is considered that the situation of the orbital plane is changed, taxiing is assisted by introducing gravity, the orbital transfer time is adjusted, and the utilization rate of the remaining fuel is increased, thereby obtaining the optimal rescue trajectory and the rescue orbit which the launch vehicle can send payload into through optimization. According to the evaluation of the remaining carrying capacity, the initial value of the trajectory planning numerical optimization algorithm is adaptively generated, and according to the initial value of the state of the rescue trajectory, the numerical optimization algorithm is used for determining the rescue trajectory, improving the solution convergence and efficiency of the rescue trajectory, and reducing the solution difficulty of the problems.

Description

technical field [0001] The invention relates to an adaptive rescue trajectory planning method based on a numerical optimization algorithm, belonging to the technical field of launch vehicle control. Background technique [0002] In the history of aerospace at home and abroad, there are many cases of launch vehicle failures due to power system failures. One of the non-fatal failures is the thrust drop of the rocket at a certain point after launch. After this type of failure, the rocket could not keep up with the nominal flight trajectory designed on the ground due to insufficient acceleration, resulting in a final crash. In order to enhance the performance capability of the launch vehicle and avoid or reduce the economic losses caused by such failures, it is a feasible method to re-plan the flight trajectory and rescue trajectory online according to the failure situation. The current iterative guidance algorithm of the launch vehicle is an effective method to improve the acc...

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 宋征宇王聪巩庆海
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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