Spacecraft orbit determination method, system, device and medium

A technology for spacecraft and target spacecraft, applied in the aerospace field, can solve problems such as inability to guarantee convergence, and achieve the effect of improving robustness and robustness

Pending Publication Date: 2022-08-09
CHINA XIAN SATELLITE CONTROL CENT
View PDF0 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] For the situation that the initial state of the spacecraft is outside the linear region and the observation noise is large, the traditional orbit determination algorithm cannot guarantee that the state estimation process will converge even with the increase of the observation data density

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 orbit determination method, system, device and medium
  • Spacecraft orbit determination method, system, device and medium
  • Spacecraft orbit determination method, system, device and medium

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0047]This embodiment discloses a method for quickly determining a spacecraft orbit based on nuclear techniques, which can provide a direct mapping relationship from ranging data to orbital elements without relying on prior orbital distribution and dynamic models. To verify the method, simulation verification is carried out in this embodiment. Orbit determination of geostationary satellites is carried out using ranging-only data from three ground measurement and control stations. The coordinates of the three stations are (46.8, 130.32, 0.101), (39.505, 75.929, 1.255), (18.313, 109.311, 0.018) corresponding to latitude (deg), longitude (deg), elevation (km), set GEO The prior distribution of satellite orbit parameters is:

[0048] a~U(42160.7,42170.7)km

[0049] e~U(0.0001,0.001)

[0050] i~U(0,0.05)deg

[0051] Ω~U(220,230)deg

[0052] ω~U(0,10)deg

[0053] M~U(45,50)deg

[0054] It should be stated here that the prior distribution of orbital parameters given here is on...

Embodiment 2

[0082] In order to verify the prediction results of the algorithm for sparse observation data, under the same conditions as in Example 1, modify the station to observe an observation point on each track for 12 hours, so that for the case of extrapolating the simulated track for one day, each track The orbit is equivalent to only two sampling points, so the format of the three-station ranging training data becomes (1200, 2, 3), which cannot be solved in the traditional orbit determination method. The probability distribution of prediction error of semi-major axis under the condition of 5m system noise and 10m random noise is as follows: figure 2 . Depend on figure 2 It can be seen that when using sparse data for orbit determination, the prediction error of the semi-major axis is about 20m, which is a problem that cannot be solved by traditional orbit determination methods. At the same time, in image 3 , the predicted error peak is on the right side of 0, that is, there is...

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 provides a spacecraft orbit determination method, device and system and a medium, and the method comprises the steps: firstly taking historical external measurement information of a plurality of spacecrafts as the input of an orbit determination method, taking orbit element information determined by a historical precise orbit as an output label, and then mapping the historical external measurement information into distribution information; and finally, solving the problem of inner product calculation between distributions by using a kernel technique, thereby establishing a mapping relation from the distribution information to the orbital elements, and providing the possibility of rapid determination for determining the spacecraft orbital through new observation information. According to the method, the influence of noise is fully considered during implementation, and under the condition that different random noise and system noise are added, the orbit determination result has high robustness.

Description

technical field [0001] The invention belongs to the field of aerospace technology, and relates to a method for determining the orbit of a spacecraft, in particular to a method, a system, a device and a medium for solving the orbit determination of a satellite in a geosynchronous orbit by using distributed regression machine learning. Background technique [0002] Orbit determination plays an important role in spacecraft measurement and control. The current orbit determination technology is mainly divided into primary orbit determination and precise orbit determination. Precise orbit determination can obtain accurate orbit determination results, but there are many restrictions for small spacecraft with high initial position uncertainty and non-cooperative targets. For cooperative targets, radar or GPS orbit determination can be used, but radar requires initial unknown uncertainty However, GPS is only suitable for low-orbit satellites, and the corresponding GPS system needs t...

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): G01C21/24
CPCG01C21/24
Inventor 姜春生沈红新李恒年杜卫兵呼延宗泊
Owner CHINA XIAN SATELLITE CONTROL CENT
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
Try Eureka
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap