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

Spacecraft inertia/fixed star starlight vector/starlight refraction combined navigation method

A technology of starlight refraction and combined navigation, applied in astronomical navigation, navigation through speed/acceleration measurement, navigation and other directions, can solve the problem of inability to correct position and speed, and achieve the effect of improving positioning

Pending Publication Date: 2021-10-26
BEIHANG UNIV
View PDF2 Cites 4 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The technical problem to be solved by the present invention is to overcome the problem that the traditional inertial / astronomical integrated navigation can only correct the attitude, but cannot correct the position and speed, and provide a kind of inertial / stellar starlight vector / starlight refraction combined navigation method for the spacecraft. Provide high-precision position, velocity and attitude information

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 inertia/fixed star starlight vector/starlight refraction combined navigation method
  • Spacecraft inertia/fixed star starlight vector/starlight refraction combined navigation method
  • Spacecraft inertia/fixed star starlight vector/starlight refraction combined navigation method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0051] The present invention will be described in detail below with reference to the drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0052] figure 1 The flow chart of the spacecraft inertial / stellar starlight vector / starlight refraction combined navigation method is given. The specific implementation process:

[0053] 1. Taking the spacecraft platform misalignment angle, velocity error, position error, gyro drift and accumulator bias as the state quantities, establish the state equation of the integrated navigation system;

[0054] The state equation of integrated navigation system can be expressed as:

[0055]

[0056] where the state quantity is [φ E φ N φ U ] T Mathematical platform misalignment angles representing east, north and sky directions, are the speed errors in the east direction, north direction and sky direction respecti...

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 relates to a spacecraft inertia / fixed star starlight vector / starlight refraction combined navigation method. The method utilizes a fixed star starlight vector to correct a platform misalignment angle and utilizes starlight refraction to correct a spacecraft position error so as to realize the purpose of simultaneously correcting a spacecraft position error and a spacecraft attitude error. The method comprises the following steps: firstly, establishing a system state model based on an inertial navigation error equation according to an inertial navigation resolving principle by taking a platform misalignment angle, a spacecraft position error, a speed error, gyroscopic drift and overmetering bias as system state quantities; and then establishing a measurement model by taking the fixed star starlight vector and the star point pixel coordinates of the refracted star as measurement. Because the system state model and the measurement model are nonlinear equations, the UKF (Unscented Kalman Filter) is used to estimate the system state quantity, and then the position, speed and attitude information of the spacecraft is obtained. The method belongs to the field of autonomous navigation of spacecrafts, can provide high-precision position, speed and attitude information for the spacecrafts, and has important practical significance for autonomous navigation of the spacecrafts.

Description

technical field [0001] The invention belongs to the field of spacecraft autonomous navigation, and relates to a spacecraft inertial / stellar starlight vector / starlight refraction combined navigation method, which is suitable for high-precision autonomous positioning and attitude determination of spacecraft. Background technique [0002] In recent years, the inertial / astronomical integrated navigation system has been widely used in aerospace, national defense and military fields due to its strong autonomy, no error accumulation over time, and good concealment. The stellar starlight vector is the quantity measurement directly obtained by the star sensor. In practical applications, it is often used to obtain high-precision attitude information of spacecraft. The celestial navigation method based on starlight refraction is to use high-precision star sensor to sensitively refract starlight, and to accurately sense the horizon through the mathematical model of starlight refraction ...

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): G01C21/16G01C21/20G01C21/02
CPCG01C21/165G01C21/20G01C21/02Y02T90/00
Inventor 宁晓琳杨雨青黄月清宋光欣房建成
Owner BEIHANG UNIV
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