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

Load prediction method for pyrotechnic impact source of spacecraft

A pyrotechnic shock and spacecraft technology, which is applied in the fields of instruments, special data processing applications, electrical digital data processing, etc., and can solve problems such as the indeterminacy of shock loads.

Inactive Publication Date: 2016-07-13
BEIJING INST OF SPACECRAFT SYST ENG +1
View PDF5 Cites 10 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In view of this, the purpose of the present invention is to provide a method for predicting the load of a spacecraft pyrotechnic shock source, through the modeling and analysis of the spacecraft pyrotechnic shock source, to solve the problem that the shock load cannot be determined in the prediction of the spacecraft pyrotechnic shock mechanical environment The problem

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
  • Load prediction method for pyrotechnic impact source of spacecraft
  • Load prediction method for pyrotechnic impact source of spacecraft
  • Load prediction method for pyrotechnic impact source of spacecraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0049] The complete spacecraft structure to be determined using the point-type satellite-rocket separation structure includes several parts such as the reverse thrust explosion separation nut, the satellite bracket on the carrying side, the satellite joint, and the main structure of the spacecraft.

[0050] According to the definition of the vibration source system and the near-field structure of the present invention, the point-type separation spacecraft structure is systematically divided (see image 3 ). During the explosive separation process of the point separation structure, with the detonation and unlocking of the explosive separation nut, the support on the carrying side is separated from the satellite joint, and the head of the separation nut falls off with the carrying satellite support. The contact surface between the satellite support and the satellite joint is Real energy separation plane. Therefore, the contact surface between the satellite bracket and the satel...

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 load prediction method for a pyrotechnic impact source of a spacecraft. The details of explosive explosion, initiating explosive device rupture and explosive stress wave propagation in an initiating explosive device can be simulated; the coupling effect caused by initiating explosive device explosion in structure can be well processed, so that the vibration source characteristic is analyzed; effective extraction on a vibration source force function is a reasonable way for obtaining a pyrotechnic impact vibration source function. According to the method, a feasible way is provided for determination of the pyrotechnic impact source function of the spacecraft; and a foundation is laid for solving the problem of response prediction of the pyrotechnic impact of the spacecraft from engineering.

Description

technical field [0001] The invention belongs to the technical field of spacecraft dynamic shock response, and in particular relates to a method for predicting the load of a spacecraft pyrotechnic shock source. Background technique [0002] The spacecraft pyrotechnic shock environment refers to the response of the shock load generated by the pyrotechnic detonation on the spacecraft to the main load-bearing structure, which constitutes the shock mechanics environment of the spaceborne equipment. The impact mechanical environment of spacecraft pyrotechnics is one of the harshest mechanical environments experienced during spacecraft launch and on-orbit work. The material stress wave and structural resonance response caused by the explosion of pyrotechnics can affect the impact of instruments and equipment containing sensitive components. Cause fatal damage, resulting in the failure of the space mission. [0003] Quantitative description of pyrotechnic shock source is the premis...

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
CPCG06F30/23G06F30/367
Inventor 赵欣韩增尧邹元杰丁继锋郑世贵
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