Method and system for planning escape route for spacecraft

A path planning and spacecraft technology, applied in control/regulation systems, instruments, integrated navigators, etc., can solve problems such as complex solution process, long time-consuming, and reduced solution complexity, to achieve accurate positioning and reduce problem dimensions Effect

Active Publication Date: 2019-01-18
NAT UNIV OF DEFENSE TECH
View PDF5 Cites 20 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The present invention proposes a spacecraft escape planning method and system to overcome the defects of complex solution process and long time-consuming in the prior art, reduce the complexity of the solution, greatly shorten the solution time, and meet the actual engineering requirements

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Method and system for planning escape route for spacecraft
  • Method and system for planning escape route for spacecraft
  • Method and system for planning escape route for spacecraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0041] Such as figure 1 As shown, the embodiment of the present invention provides a method for planning an escape path of a spacecraft, including the following steps:

[0042] S1, based on the near-circular deviation linear model, the difference between the track deviation elements of the tracking spacecraft and the escaping spacecraft is used as the state variable to construct the Hamiltonian function of the differential game, according to the Hamiltonian function and the tracking spacecraft successfully intercepts the escaping spacecraft as the end condition Construct the terminal constraint function of the differential game;

[0043] Said S1 comprises the following steps:

[0044] S101, describing the state equation of the differential game through the near-circle deviation equation;

[0045] see figure 2 , establish the orbital polar coordinate system O E -rθz, the origin of the coordinate system is at the center of the earth O, r is the projection of the orbital dis...

Embodiment approach 1

[0122] This embodiment is a chase-and-flight game between two spacecraft in low-earth orbit.

[0123] Such as figure 2 As shown, in this embodiment, a method for efficiently solving the saddle point of the survival-type pursuit-and-escape differential game of a spacecraft includes:

[0124] S0, input parameters, input the following scene parameters of the on-orbit chase and escape game:

[0125] Table 1 Embodiment 1 parameter configuration

[0126]

Semi-major axis / km

Eccentricity

Orbit inclination / °

ascending node right ascension / °

Angular distance of perigee / °

True anomaly / °

Acceleration / °

tracking device

7378.137

0.0004

20

29.6

0

0

0.09g

escape device

7578.137

0.0002

22.2

27.2

0

16

0.03g

reference point

7478.137

0

21.1

28.4

0

0

0g

[0127] The scenario parameters correspond to physical quantities:

[0128]

[0129] where x 0 is the initial val...

Embodiment approach 2

[0141] The steps of this embodiment are basically the same as those of Embodiment 1, and the main difference is that the initial parameters input in step S0 are different. In this embodiment, the two spacecrafts are pursuing and fleeing at the height of the geosynchronous orbit, and the maneuverability is not much different.

[0142] S0, input parameters, input the following scenario parameters of the pursuit-fleeing game at the height of the synchronous orbit:

[0143] Table 3 Embodiment 2 parameter configuration

[0144]

Semi-major axis / km

Eccentricity

Orbit inclination / °

ascending node right ascension / °

Angular distance of perigee / °

True anomaly / °

Acceleration / °

tracking device

42378.137

0.0004

0.8

0

0

0

0.006g

escape device

42578.137

0

0

0

0

14

0.004g

reference point

42478.137

0

0.4

0

0

0

0g

[0145] The scenario parameters correspond to physical q...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

PUM

No PUM Login to view more

Abstract

The invention discloses a method and a system for planning an escape route for a spacecraft. The method comprises steps of: 1) constructing a Hamilton function and a terminal constraint function of differential game based on a near circle deviation equation; 2) solving a co-state equation of the differential game to obtain an evolutionary formula for co-state quantity analysis; 3) solving an optimal control equation of the differential game to obtain an analytical expression of optimal control quantity; 4) solving a cross-section condition of the differential game to obtain terminal values ofHamilton quantity and co-state quantity; 5) solving a nonlinear equation set iteratively to obtain a saddle point of the differential game; and 6) planning the escape route for the spacecraft according to the saddle point of the differential game. According to the method and the system for planning the escape route for the spacecraft, the saddle point of the differential game of chase and escape in the spacecraft can be quickly solved, and by an optimal control law of the chase and escape corresponding to the saddle point, space threat can be evaded and a game route can be planned for the spacecraft. Therefore, the method and the system have the advantages of being correct and reasonable in design, fast in calculation, good in applicability to actual tasks, and the like.

Description

technical field [0001] The invention relates to the technical field of spacecraft pursuit and escape game path planning based on survival differential strategies, in particular to a spacecraft escape path planning method and system. Background technique [0002] Spacecraft pursuit and escape game path planning technology is a passive and defensive space technology, which is researched on the background of spacecraft pursuit and escape. When the tracking spacecraft tries to approach the target spacecraft, the maneuverable target spacecraft (also called escape spacecraft) can effectively avoid space threats and improve its survivability by planning the optimal escape path. Therefore, this technology is of great significance to my country's space security. [0003] The chasing and fleeing game between two spacecraft is a continuous and dynamic confrontation process, which can be modeled and analyzed using the theory of differential games. Differential games can be generally d...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

Application Information

Patent Timeline
no application Login to view more
Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/20G01C21/24G05D1/10
CPCG01C21/20G01C21/24G05D1/101
Inventor 罗亚中祝海李振瑜孙振江张进
Owner NAT UNIV OF DEFENSE TECH
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Try Eureka
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap