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

Self boundary marking method based on forecast filtering and UPF spacecraft shading device

A technology for predictive filtering and spacecraft, applied in the field of aerospace navigation, can solve the problems of inability to meet high-precision spacecraft, simple algorithm and low accuracy, and inability to improve the accuracy of spacecraft attitude determination, and achieve fast filtering convergence and high filtering accuracy. Effect

Active Publication Date: 2009-02-18
BEIHANG UNIV
View PDF0 Cites 1 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The two methods do not establish an accurate gyro model, and the algorithm is simple and the accuracy is low. Therefore, the existing technology cannot meet the requirements of high-precision spacecraft self-calibration, and cannot improve the accuracy of spacecraft attitude determination.

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
  • Self boundary marking method based on forecast filtering and UPF spacecraft shading device
  • Self boundary marking method based on forecast filtering and UPF spacecraft shading device
  • Self boundary marking method based on forecast filtering and UPF spacecraft shading device

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0016] Such as figure 1 Shown, the concrete realization steps of the present invention are as follows:

[0017] 1. Establish the spacecraft self-calibration state equation based on attitude kinematics:

[0018] (1) Gyro measurement model

[0019] Considering the influence of the gyro error source on the drift error of the gyro, an accurate gyro model is established, and the gyro error sources (such as: gyro scale factor error, gyro misalignment error, gyro constant value drift, gyro output noise) are built into the gyro model:

[0020] ω g =ω+b+g sf +g ma +n a (1)

[0021] In the formula, ω g is the measured value of the gyro, ω is the true value of the gyro, b is the constant drift of the gyro, g sf is the gyroscope scale factor error, g ma Gyro misalignment error, n a Output noise for the gyro.

[0022] g sf =diag([g sfx g sfy g sfz ]) ω (2)

[0023] g ma = ...

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

There are a sort of predictive filtering and the self-demarcation of the UPF spaceflight, it relates to the spaceflight airmanship field. It applies to the self-demarcation of the spaceflight peg-top, especially it relates to a sort of spaceflight self-demarcation method of the inertia / starlight which bases the predictive filtering and the UPF (Unscented Particle Filter) information coalescence, thereby it applies to the navigation determining gesture of the spaceflight. First it establishes the self-demarcation state equations of the spaceflight, and then it makes the gesture information which is observed by the star sensing device to become the measuring equations, finally it adopts the self-demarcation arithmetic which bases the predictive filtering and the UPF spaceflight to estimate and amend the drift error of the peg-top, thereby it obtain the high exact gesture of the spaceflight.

Description

technical field [0001] The present invention relates to the field of aerospace navigation technology, and can be used for self-calibration of spacecraft gyro, in particular to an inertial / starlight combined spacecraft self-calibration method based on predictive filtering and UPF (Unscented Particle Filter, Chinese name is given) information fusion, and then applicable to For navigation and attitude determination of spacecraft. Background technique [0002] With the development of the national economy, there is an urgent need to use wide-format and large-range satellites to conduct high-resolution earth observation and monitoring of ocean, environment, agriculture, forestry and other resources. . In order to effectively realize this task, it is necessary to break through the high-precision spacecraft attitude determination technology. [0003] The spacecraft has been flying in space for a long time, and its autonomous attitude determination is very important. Therefore, in ...

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): G01C21/00G01C21/02G01C21/18
Inventor 房建成徐帆韩晓英全伟宫晓琳钟慧敏
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