Eureka AIR delivers breakthrough ideas for toughest innovation challenges, trusted by R&D personnel around the world.

Pulsar/starlight angle combination navigation method of high orbit satellite

A technology of starlight angular distance and high-orbit satellites, which is applied in the field of navigation and can solve the problems that high-orbit satellites are difficult to achieve autonomous positioning.

Inactive Publication Date: 2014-08-27
NAT UNIV OF DEFENSE TECH
View PDF2 Cites 19 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The technical problem to be solved by the present invention is: aiming at the problem that the current high-orbit satellites are difficult to realize autonomous positioning, the autonomous navigation and positioning of high-orbit satellites is completed by using the pulsar / starlight angular-distance combined navigation method based on dynamic and static nonlinear filters

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
  • Pulsar/starlight angle combination navigation method of high orbit satellite
  • Pulsar/starlight angle combination navigation method of high orbit satellite
  • Pulsar/starlight angle combination navigation method of high orbit satellite

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0096] Such as figure 1 As shown, an autonomous navigation algorithm for medium and high orbits based on pulsar and starlight angular distance, the specific implementation steps are as follows:

[0097] (1) Establish orbital dynamics equations for near-Earth satellites;

[0098]In the geocentric inertial system J2000.0, the orbital dynamics equation of the near-Earth satellite is established as

[0099]

[0100] Among them, x=[r T ,v T ] T is the state vector of the spacecraft, w=[w r T w v T ] T is dynamic model noise, which can be modeled as zero-mean white Gaussian noise. The variance matrix of this noise is Q. a=a TB +a NS +a T +a H.O.T is the acceleration experienced by the spacecraft, including the following items.

[0101] 1)a TB =-μ E r / |r| 3 is the two-body gravitational acceleration of the spacecraft, where μ E is the gravitational constant of the earth.

[0102] 2) is the non-spherical gravitational perturbation of the earth. UNSE can be e...

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 pulsar / starlight angle combination navigation method of a high orbit satellite. The method comprises the following steps: establishing an orbital dynamic equation of a near earth satellite; establishing a pulsar navigation observation equation; establishing a starlight angle observation equation; using a dynamic filter to process a dynamic model and starlight angle distance information; and fusing the obtained filter result with the pulsar observation information by using a static filter. The combination navigation method uses the dynamic and static nonlinear filter to realize the optimal fusion of the original observation information of the pulsar with the starlight angle distance information, so compared with a pulsar navigation system, a combination navigation system has the advantages of small size, less power consumption short measurement period; and compared with CNS, the combination navigation system can obtain high precision navigation information.

Description

technical field [0001] The invention mainly relates to the field of navigation methods, in particular to a high-orbit satellite pulsar / starlight angular-distance combined navigation method. Background technique [0002] High-orbit satellites (orbit altitudes above 20,000km) play an important role in climate detection, disaster warning, and data relay. Accurate position information is an important factor to ensure the effective work of high-orbit satellites. At present, the orbit determination of high-orbit satellites is mostly based on ground measurement and control stations. However, with the increase in the number of high-orbit satellites, the burden on ground monitoring and control stations is gradually increasing. At the same time, the increasingly complex space environment also puts forward an urgent demand for the autonomy of high-orbit satellites. Having a highly reliable and stable autonomous navigation system is a necessary prerequisite for realizing the autonomy...

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): G01C21/02
CPCG01C21/24
Inventor 郑伟王奕迪汤国建张大鹏
Owner NAT UNIV OF DEFENSE TECH
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
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