A Navigation Error Determination and Compensation Method for Satellite Starlight Refraction
A technology of starlight refraction and compensation method, which is applied in the field of astronomical navigation and can solve the problems such as the inability to meet the needs of accurate estimation of the navigation accuracy of the satellite starlight refraction navigation system, and the failure to comprehensively consider the influence of the navigation accuracy.
Active Publication Date: 2017-01-11
CHINA ACADEMY OF SPACE TECHNOLOGY
View PDF4 Cites 0 Cited by
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
Since the concept of starlight refraction navigation was proposed in 1982, it has attracted the attention of many scholars, and many navigation accuracy analysis methods have been proposed, but Robert, Robert and Eliezer (Guidance and Control Conference, Gatlinburg, TN, August 15-17, 1983: 359-367), Whilte, Thurman and Barnes (Proceedings of the Forty-First Annual Meeting, the Institute of Navigation, Annapolis, MD, June 25-27, 1985:83-89), Lair and Duchon (Acta Astronautica, 1988, 17 (10): 1069-1079), Ning and Fang (Aerospace Science and Technology 11(2007): 222-228) and other major researchers have not fully analyzed several major errors that affect the accuracy of starlight refraction navigation. source, only the influence of some main error sources on navigation accuracy is analyzed, and the influence of these error sources on navigation accuracy is not comprehensively considered, which cannot meet the needs of satellite starlight refraction navigation system for accurate prediction of navigation accuracy
[0003] Chinese Patent Publication No. CN 103616028A, dated March 5, 2014, titled "A Method for Autonomous Navigation of Starlight Refraction Satellites Based on a Single-Star Sensor", discloses a method based on a single-star sensor using the principle of starlight refraction The method of satellite autonomous navigation. This method introduces the basic idea of using starlight refraction for satellite autonomous navigation, and gives the simulation results of navigation accuracy. Although high-precision navigation accuracy is obtained, it is not based on a comprehensive analysis of errors. Basically, there is a certain gap between the results and the actual situation, and it cannot meet the needs of the satellite starlight refraction navigation system for accurate prediction of navigation accuracy.
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 moreImage
Smart Image Click on the blue labels to locate them in the text.
Smart ImageViewing Examples
Examples
Experimental program
Comparison scheme
Effect test
Embodiment
[0121] In order to illustrate the positioning error of starlight refraction navigation, the influence of three main factors, namely, the measurement accuracy of the refraction angle, the error of the atmospheric model, the number of refracting stars and the distribution uniformity, on the positioning accuracy is analyzed through simulation.
[0122] The input conditions of the simulation system are as follows:
[0123] 1) The simulated orbit is the GTO orbit of the satellite, the altitude ranges from 20000km to 36000km, and the orbit parameters are: a=24421.2km, e=0.726543, i=28.5°, Ω=139.3°, ω=75°;
[0124] 2) Technical indicators of starlight refraction sensor system:
[0125]
[0126] 3) Atmospheric model:
[0127] γ=2350.1074e -0.10326788h , where h is the atmospheric height, in km; γ is the atmospheric refraction angle, in ".
[0128] 4) The atmospheric model error is 1%.
[0129] Figure 10 According to the above input conditions, and select the refracting star b...
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
Login to View More Abstract
The invention relates to a satellite starlight refraction navigation error determination and compensation method. The method comprises the following steps: firstly, generating data of a satellite orbit by virtue of STK software; establishing a satellite attitude planning model; determining an actual observation visual field, and simulating an observation star map comprising refraction stars and non-refraction stars; calculating to obtain the tangential height h of the refraction stars; calculating to obtain the tangential height h'' of the refraction stars with errors of refraction angles and errors of an atmospheric model, wherein tangential height errors are mainly caused by the measurement precision errors of the refraction angles and the errors of the atmospheric model; calculating to obtain the position of a satellite under a geocentric inertial coordinate system; and performing filtration by an extended Kalman filtration method, and outputting a starlight refraction navigation estimated position and position errors. The method provided by the invention can realize accurate prediction of navigation precision of a satellite starlight refraction navigation system, and is comprehensive in error analysis and accurate and reliable in results.
Description
technical field [0001] The invention belongs to the field of astronomical navigation, and relates to a method for determining and compensating satellite starlight refraction navigation errors, which is suitable for accurate estimation of the positioning accuracy of a satellite starlight refraction navigation system. Background technique [0002] Starlight refraction astronomical navigation is a method of using optical sensors to measure the refraction of starlight when it passes through the atmosphere at the edge of the earth, and indirectly obtains the horizon information, obtains the position of the satellite in the geocentric coordinate system, and determines the satellite orbit. Since the concept of starlight refraction navigation was proposed in 1982, it has attracted the attention of many scholars and proposed more navigation accuracy analysis methods, but Robert, Robert and Eliezer (Guidance and Control Conference, Gatlinburg, TN, August 15-17, 1983: 359-367), Whilte,...
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
Login to View More Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/02G01C25/00
CPCG01C21/02G01C25/00
Inventor 李志李怀锋林亲宋亮
Owner CHINA ACADEMY OF SPACE TECHNOLOGY