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Method for determining initial orbit of spacecraft based on precise orbit model

A technology of precise orbit and determination method, which is applied in the field of aerospace navigation, can solve the problems of no reference orbit and high real-time requirements, and achieve the effect of improving calculation accuracy

Active Publication Date: 2019-05-14
CHINA XIAN SATELLITE CONTROL CENT
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Problems solved by technology

The real-time requirements of the initial orbit calculation after the separation of the satellite and the rocket are relatively high and there is no real reference orbit, which makes it quite different from the post-event precise orbit determination in the calculation method.

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  • Method for determining initial orbit of spacecraft based on precise orbit model
  • Method for determining initial orbit of spacecraft based on precise orbit model
  • Method for determining initial orbit of spacecraft based on precise orbit model

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Embodiment Construction

[0042] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0043] A method for determining the initial orbit of a spacecraft based on an accurate orbit model, such as figure 1 As shown, follow the steps below:

[0044] Step 1, system state initialization, estimate the initial position of the orbit and the initial velocity vector of the spacecraft after the separation of the spacecraft and the rocket in the J2000 inertial system;

[0045] The estimated value of the initial position and initial velocity vector can be obtained by using the radar measurement data to determine the initial value of the initial orbit, or directly using a point in the position and velocity (GNSS, Beidou, etc.) observation data;

[0046] Step 2, fusing different types of orbit measurement data, and calculating the improved values ​​of the initial position and velocity based on the iterative weighted least squares method.

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Abstract

The invention discloses a method for determining an initial orbit of spacecraft based on a precise orbit model. On the basis of the precise orbit model and a laplace equation, a weighted least squaresconditional equation of ground-based radar orbit measurement data, space-based optical angle measurement data, GNSS and Beidou orbit measurement data is established, and improved values of initial positions and velocity are iteratively solved by integrating different kinds of orbit measurement data by using two methods of a direct synthesis method or a federated synthesis method. According to themethod for determining the initial orbit of spacecraft based on the precise orbit model, the complete or incomplete external ballistic observation data, the position and velocity component observation data and the space-based angle measurement data can be directly combined to carry out the satellite-rocket separation initial orbit calculation, and the unique initial orbit output is produced.

Description

technical field [0001] The invention belongs to the technical field of aerospace navigation, and relates to a method for determining an initial orbit of a spacecraft based on an accurate orbit model, in particular to a method for determining an initial orbit by a unit vector method based on an accurate orbit model and integrating multiple types of observation data sources. It is suitable for the rapid determination of the orbit of the spacecraft after the separation of the satellite and the rocket, and other unpowered flight stages. Background technique [0002] The calculation of the initial orbit of the spacecraft after the separation of the satellite and rocket is one of the most important contents in the launch process of the spacecraft, and it is the basis for evaluating whether the launch is successful or not and for the follow-up orbit control of the spacecraft. The real-time requirements of the initial orbit calculation after the separation of the satellite and the r...

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Application Information

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IPC IPC(8): G01C21/24
Inventor 李恒年淡鹏张智斌王丹张定波黄普黄岸毅
Owner CHINA XIAN SATELLITE CONTROL CENT
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