Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Spacecraft multi-stage driving rigid-flexible coupling response acquisition method

A rigid-flexible coupling and acquisition method technology, which is applied in the field of spacecraft dynamics, can solve problems such as the coupled dynamics calculation of complex mechanism motion and elastic vibration of spacecraft

Active Publication Date: 2015-07-29
BEIJING INST OF SPACECRAFT SYST ENG
View PDF3 Cites 15 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, and to provide a method for obtaining the rigid-flexible coupling response of the multi-stage drive of the spacecraft, by providing a set of generalized flexible multi-body dynamics analytical model, and Solve the model to obtain the dynamic response of the spacecraft, and solve the problem of coupling dynamics between the complex mechanism motion and elastic vibration of this type of spacecraft, which can be used for dynamic modeling and rigid-flexible coupling Response calculation, control system design, and co-simulation with control system provide technical support

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
  • Spacecraft multi-stage driving rigid-flexible coupling response acquisition method
  • Spacecraft multi-stage driving rigid-flexible coupling response acquisition method
  • Spacecraft multi-stage driving rigid-flexible coupling response acquisition method

Examples

Experimental program
Comparison scheme
Effect test

specific Embodiment approach

[0041] The implementation process of the whole invention is as follows: image 3 shown. The specific implementation is described in detail as follows:

[0042] (1) Component flexible modeling

[0043] against image 3 For the i-th component in , its dynamic model is established below, and its vibration equation can be written as

[0044] x · · + kx = f - - - ( 1 )

[0045] Among them, m is the mass matrix, k is the stiffness matrix, f is the internal force including the connection with the i-1th structure and the i+1th structure, and x is the node response.

[0046] When component i is connected with front and rear components, its connection interface points need to be considered, such as Figure 4 ξ in ai,1 and ξ ai,2 . Therefore, according to the internal coordinates and interfa...

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 spacecraft multi-stage driving rigid-flexible coupling response acquisition method, which comprises steps: (1) the spacecraft is considered to be composed of three structures: a body, parts and joints; (2) kinetic energy and potential energy of the body, the parts and the joints are built respectively; (3) according to a connection condition, kinetic energy and potential energy of the entire spacecraft are built; (4) the kinetic energy and the potential energy of the spacecraft obtained in the third step are used, and a Lagrange equation is adopted to build a kinetic equation of the spacecraft; (5) the kinetic equation obtained in the fourth step is solved, and a rigid-flexible coupling kinetic response of the spacecraft during the multi-stage driving process is acquired. The method of the invention can be applied to a complex spacecraft with flexible multi-body motion features, a precise kinetic response to the motion process of the spacecraft of the complex multi-body structure is acquired, and an important role is played in control system design and system level simulation verification.

Description

technical field [0001] The invention belongs to the field of spacecraft dynamics and relates to a dynamic response acquisition method for flexible multi-body spacecraft. Background technique [0002] With the development of manned spaceflight and communication technology, the spacecraft is gradually developing from a single-axis driven solar wing to a multi-body direction, such as a manned space manipulator, a dual-axis driven solar wing, and a multi-degree-of-freedom driven antenna. This hybrid system of rigid body and flexible body has a large range of rotational driving motion between the bodies, and the elastic vibration of the flexible body is superimposed. This complex dynamic effect of rigid-flexible coupling, as well as the control-structure cross-coupling with the control system, makes the dynamic characteristics analysis of this type of complex spacecraft, especially the dynamic model of the flexible multi-body system in the verification of the GNC control scheme ...

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): G05B17/02
Inventor 葛东明于伟邹元杰史纪鑫范晶岩关晓东
Owner BEIJING INST OF SPACECRAFT SYST ENG
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

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

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com