Flexible spacecraft integrated modeling method

A flexible spacecraft and modeling method technology, applied in instrumentation, design optimization/simulation, special data processing applications, etc., can solve problems such as control deviation, controller design difficulties, uncontrollable decomposition, etc.

Active Publication Date: 2018-05-04
SHANGHAI AEROSPACE CONTROL TECH INST
View PDF12 Cites 3 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This makes it difficult for traditional dynamic modeling methods to qualitatively separate the influence of attitude motion from vibration or orbital motion, which makes it difficult to

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
  • Flexible spacecraft integrated modeling method
  • Flexible spacecraft integrated modeling method
  • Flexible spacecraft integrated modeling method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0093] In order to make the object, technical solution and advantages of the present invention clearer, the implementation manner of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0094] figure 1 Provided the composition schematic diagram of the central rigid body and the flexible attachment of the flexible spacecraft of the inventive method, set up the flexible spacecraft body coordinate system O b x b Y b Z b :O b is the center of mass of the satellite, O b Z b axis perpendicular to the star-to-ground mounting surface, O b x b The axis points to the direction of satellite flight, O b Y b The orientation of the axes is determined by the right-hand rule. Establish inertial coordinate system O I x I Y I Z I :O I is the center of mass of the satellite, O I Z I axis pointing to the center of the earth, O I x I Axis perpendicular to O in the orbital plane of the satellite I Z I Pointing to the d...

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

Provided is a flexible spacecraft integrated modeling method. A flexible spacecraft comprises flexible accessories and a central rigid body. The method includes the following steps of firstly, calculating the antithesis momentum of the flexible accessories relative to the mass center of the flexible spacecraft under dynamic conditions through a finite element method and an integration method underthe coordinate system of a flexible spacecraft body; secondly, calculating the antithesis momentum of the central rigid body relative to the mass center of the flexible spacecraft under dynamic conditions through the finite element method and the integration method under the coordinate system of the flexible spacecraft body; thirdly, summarizing the antithesis momentum of the flexible accessoriesrelative to the mass center of the flexible spacecraft in the first step and the antithesis momentum of the central rigid body relative to the mass center of the flexible spacecraft in the second step, and calculating the antithesis momentum of the flexible spacecraft relative to relative to the mass center of the flexible spacecraft under dynamic conditions; fourthly, calculating a flexible spacecraft posture orbit integrated kinetic equation according to the momentum theorem under the inertia coordinate system.

Description

technical field [0001] The invention relates to a spacecraft integrated modeling method, which belongs to the research field of spacecraft dynamics and control. Background technique [0002] At present, for the dynamic modeling of flexible spacecraft, most of them focus on attitude dynamic modeling. The usual method is to use the Newton-Eulerian method or Lagrangian method, and use the principle of mixed coordinates to derive the flexible attachment. A dynamic model of vibration effects on spacecraft attitude motion. For the influence of the vibration of the flexible attachment on the orbital motion of the spacecraft and the coupling effect between the attitude motion and the orbital motion of the spacecraft, there are very few studies on this at home and abroad, and most of the methods used are the Lagrangian method. The attitude motion and orbital motion of the flexible spacecraft are studied independently, and the attitude and orbital dynamics equations are established r...

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
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23
Inventor 孙俊张宪亮宋婷宁雷
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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