Rocket power fixed-point landing guidance method

A power and rocket technology, which is applied in the field of fixed-point landing of rocket power, can solve problems such as the inability to achieve fixed-point landing, few constraints, and the inability to effectively consider the impact of trajectory planning, to achieve a balance between fuel optimization and guidance robustness, and to improve convergence performance, and the effect of improving landing safety

Active Publication Date: 2021-01-22
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] 1) There are few constraints to consider, and fixed-point landing cannot be achieved under large deviation conditions;
[0005] 2) The influence of aerodynamic drag on trajectory planning during powered landing cannot be effectively considered;

Method used

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  • Rocket power fixed-point landing guidance method
  • Rocket power fixed-point landing guidance method
  • Rocket power fixed-point landing guidance method

Examples

Experimental program
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Embodiment

[0070] This embodiment provides a rocket-powered fixed-point landing guidance method, such as figure 1 As shown, the specific implementation is as follows:

[0071] The first step is to input the current state parameters, aircraft parameters and environment parameters

[0072] 1) For rocket-powered landing aircraft, calculate the feasible range of flight time according to the current aircraft position, speed, remaining fuel, and main engine specific impulse and thrust adjustment parameters, etc.

[0073]

[0074] Among them, ||v(t)|| is the current speed, m dry is the structural mass of the landing vehicle, m fuel The current remaining fuel for landing, T min , T max Adjust the upper and lower limits for the engine thrust, ρ 1 , ρ 2 It is the adjustment value of the control margin, α=1 / (I sp g 0 ), I sp is the specific impulse of the engine, g 0 is the gravitational acceleration on the surface of the landing celestial body.

[0075] 2) Determine the guidance targ...

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Abstract

The invention provides a rocket power fixed-point landing guidance method. The rocket power fixed-point landing guidance method mainly comprises the steps of rocket power fixed-point landing guidancemodel establishment considering aerodynamic resistance, guidance model convexity processing and second-order cone programming problem rolling time domain optimization calculation. The method aims to solve the problem of fixed-point landing guidance under the synergistic effect of thrust and aerodynamic resistance of an engine in a power descending stage of an aircraft, and converts the original rocket power fixed-point landing guidance problem into a sequential second-order cone programming problem to be solved by adopting a technology of combining lossless relaxation and sequence iteration. Acurrent guidance period instruction is calculated through rolling time domain optimization, the adaptability of the guidance method to model parameter uncertainty and motion state deviation is improved, meanwhile, fuel optimality and guidance robustness are balanced through a control margin adjustment method, and return safety and landing control precision are effectively improved.

Description

technical field [0001] The invention relates to a rocket-powered fixed-point landing method, which is suitable for the mission of returning to the earth and fixed-point vertical landing of a carrier rocket sub-stage, and belongs to the technical field of guidance, navigation and control of space transport vehicles. It can also be applied to fixed-point soft landing missions on extraterrestrial bodies such as the moon and Mars, and has broad market prospects and application value. Background technique [0002] Rocket-powered fixed-point soft-landing guidance method is an important content of the program design of launch vehicle reentry return and landing control system. At present, the application of this method is mainly focused on extraterrestrial celestial body landing missions and commercial rocket first-stage vertical recovery missions in recent years, such as the Apollo moon landing project in the last century and the Mars Science Laboratory (MSL) in recent years. The M...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24B64G1/62
CPCB64G1/244B64G1/62
Inventor 甘庆忠陈海朋王禄湛康意张宇星张浩张飞王海鹰
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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