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

A Method of Attitude Control for a Flexible Spacecraft

A flexible spacecraft and attitude control technology, applied in the field of aerospace systems, can solve problems such as the inability to accurately and effectively describe the dynamic behavior and attitude control of flexible spacecraft, and achieve the best attitude control effect

Active Publication Date: 2022-05-03
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
View PDF17 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide an attitude control method of a flexible spacecraft to solve the problems in the prior art that cannot accurately and effectively describe the complex dynamic behavior of the flexible spacecraft and effectively realize the attitude control

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
  • A Method of Attitude Control for a Flexible Spacecraft
  • A Method of Attitude Control for a Flexible Spacecraft
  • A Method of Attitude Control for a Flexible Spacecraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0021] The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Apparently, the described embodiments are some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0022] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, ...

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 present invention provides a method of posture control of deflection spacecraft, involving the field of spacecraft technology, and to solve the complex dynamic behavior and effectively realizing posture control of the existing technology.The attitude control method includes: through the analysis of the micro -dollar analysis of the deflection attachment, the general potential energy one and total kinetic energy of the deflection spacecraft are obtained;, Obtain the general potential energy two and total kinetic energy of the deflection spacecraft; according to the general potential energy two and the total kinetic energy two, establish a scores and digestion equation, and calculate the deflection aerospace according to the matrix form of the section of the digital dynamic equation.The scores and order space models of the device; according to the model, establish a posture controller, and use the controller to control the attitude of the deflection spacecraft.

Description

technical field [0001] The invention relates to the technical field of aerospace systems, in particular to an attitude control method of a flexible spacecraft. Background technique [0002] Space launch activities have strict restrictions on the total weight of the payload. Therefore, in order to save fuel and reduce launch costs, a large number of structures of modern spacecraft are widely designed and manufactured with lightweight flexible composite materials such as viscoelastic materials and polymer composite materials, and rigid satellite bodies and flexible composite materials have been developed. The structure in which the flexible appendages are coupled to each other is called a flexible spacecraft. However, although flexible composite materials reduce the weight of the spacecraft, they have complex dynamic characteristics, which are prone to continuous elastic vibration under the influence of attitude maneuvers or external disturbances, and even cause the spacecraf...

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 Patents(China)
IPC IPC(8): G05D1/08
CPCG05D1/0808
Inventor 徐世东文浩金栋平
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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