Method for designing a revisiting track of a spacecraft region

A spacecraft and regional technology, applied in the direction of aerospace vehicles, aerospace vehicle guidance devices, aircraft, etc., can solve problems such as revisiting orbits in areas not suitable for spacecraft, and achieve design efficiency, expand scope, and reduce constraints. Effect

Active Publication Date: 2019-01-01
BEIJING SPACE TECH RES & TEST CENT
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Problems solved by technology

In the existing technology, there is only a method for the design of the return orbit, which is not suitable for the de

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  • Method for designing a revisiting track of a spacecraft region
  • Method for designing a revisiting track of a spacecraft region
  • Method for designing a revisiting track of a spacecraft region

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Embodiment approach

[0051] Such as figure 1 Shown, according to an embodiment of the present invention, a kind of method for designing spacecraft area revisit track of the present invention comprises:

[0052] S1. Define the revisit area and revisit time interval of the orbit of the spacecraft sub-satellite point on the surface of the planet;

[0053] S2. Obtain the orbital parameters of the spacecraft's flight orbit according to the mission requirements of the spacecraft;

[0054] S3. Acquire the longitude range of the ascending node and the longitude interval of the ascending node of the sub-satellite track of the spacecraft in the revisiting area according to the orbital parameters, the revisiting area and the revisiting time interval;

[0055] S4. Comparing the longitude range of the ascending node with the longitude interval of the ascending node, obtaining the orbital parameters when the longitude range of the ascending node is greater than the longitude interval of the ascending node, and...

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Abstract

The invention relates to a method for designing a revisiting track of a spacecraft region, comprising: S1. defining a revisit region and a revisit time interval of a subsatellite point trajectory of the spacecraft on a planetary surface; S2, obtaining orbital parameters of the spacecraft flight trajectory according to mission requirements of the spacecraft; S3. according to the orbital parameters,the revisit region and the revisit time interval, obtaining the ascending intersection longitude range and the ascending intersection longitude interval of the subsatellite point trajectory of the spacecraft in the revisit region; S4. comparing the longitude range of the ascending intersection point with the longitude interval of the ascending intersection point, obtaining the orbital parameterswhen the longitude range of the ascending intersection point is larger than the longitude interval of the ascending intersection point, and generating a spacecraft region revisit orbit according to the orbital parameters. By adopting the method of matching the longitude range of the ascending intersection point with the longitude interval of the ascending intersection point to determine the orbital elements of the regional revisit orbit, the constraints among the orbital elements are reduced, and the orbital elements range satisfying the requirements of the regional revisit can be quickly determined.

Description

technical field [0001] The invention relates to a method for designing orbits, in particular to a method for designing spacecraft area revisit orbits. Background technique [0002] Regional revisit means that the orbit of the sub-satellite point of the spacecraft periodically passes through a certain area on the surface of the planet (such as the surface of the earth). The orbit with this characteristic is called the regional revisit orbit. There is a difference between periodically revisiting a track and returning to a track. The return orbit means that the sub-satellite point trajectory of the spacecraft overlaps periodically, that is, after a certain period of time, the sub-satellite point trajectory returns to the original route. This type of orbit is called a return orbit. The sub-satellite point trajectory of the regional revisit orbit passes through a certain area on the earth's surface periodically, but the sub-satellite point trajectory does not necessarily overlap...

Claims

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 陈伟跃黄震张亚锋张治国
Owner BEIJING SPACE TECH RES & TEST CENT
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