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An orbit design method near the translation point of the Earth-Moon triangle

A design method and translation point technology, applied in the aerospace field, can solve the problem of solving the long-term task orbit limitation of the design, and achieve the effect of meeting the task accuracy requirements, high precision, and easy to call directly.

Active Publication Date: 2022-07-12
NANJING UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In short: Compared with the actual Earth-Moon system, the double-circle model or the flat Earth-Moon-Sun model still has certain dynamic differences, so the designed orbit is consistent with the actual orbit of the probe. There are qualitative differences between them, and the design of long-term mission trajectories based on them will be limited

Method used

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  • An orbit design method near the translation point of the Earth-Moon triangle
  • An orbit design method near the translation point of the Earth-Moon triangle
  • An orbit design method near the translation point of the Earth-Moon triangle

Examples

Experimental program
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Effect test

Embodiment 1

[0067] Assuming that the starting epoch of the mission orbit is March 21, 2021 01:01:32.0 seconds (GMT), and the constructed orbit maintenance time is 10 years, it is necessary to construct the orbit near the small-amplitude dynamic replacement orbit near the L4 point, then Set the amplitude parameters in the above formula as α=0.005, β=0.005.

[0068] According to the semi-analytical solution, the time interval between nodes is selected to be 4 days, and a total of 915 orbital nodes are required for a 10-year orbit; the mission orbit is numerically iteratively designed under the complete ephemeris model by using the multi-point shooting method.

[0069] Output the designed orbital node data for analysis and plotting. figure 2 and image 3 According to the output data, the images of the trajectory of the designed orbit (maintained for 10 years) in the earth-centered celestial coordinate system and the earth-moon instantaneous meeting coordinate system (the projection of the ...

Embodiment 2

[0071] Assuming that the initial epoch of the mission orbit is 3:15:0.0 on September 22, 2025, and the constructed orbit maintenance time is 10 years, it is necessary to construct a large-amplitude dynamic replacement orbit itself near the L5 point, then set the amplitude in the above formula The parameters are α=0.0, β=0.0. According to the semi-analytical solution, the position and velocity of the detector in the geocentric celestial coordinate system at the initial epoch are given, and the 10-year mission orbit is generated by integration.

[0072] Output the designed orbital node data for analysis and plotting. Figure 4 and Figure 5 According to the output data, the images of the trajectory of the designed orbit (maintained for 10 years) in the earth-centered celestial coordinate system and the earth-moon instantaneous meeting coordinate system (the projection of the orbit on the x-y, x-z, y-z planes and in the three-dimensional space) are respectively given. image in ...

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Abstract

The invention discloses an orbit design method near the triangular translation point of the Earth and Moon, comprising the following steps: (1) constructing the semi-analytical solution approximation of the motion near the triangular translation points L4 and L5 under the ephemeris model; (2) designing Under the ephemeris model, the mission orbits of the earth-moon triangular translation points L4 and L5 are maintained for a certain period of time; (3) the output orbit design results, that is, the detectors in the earth-centered celestial coordinate system and the earth-moon instantaneous meeting coordinate system are generated at certain time intervals position and velocity vector. The invention can start to design and maintain the task orbit for a long time from any moment, the adopted semi-analytical solution has higher precision, is suitable for two triangular translation points, and is easy to be directly invoked by orbit designers.

Description

technical field [0001] The invention relates to the technical field of aerospace, in particular to an orbit design method near the translation point of the Earth-Moon triangle. Background technique [0002] The theoretical research results under the existing ephemeris model are not comprehensive, and there is a certain distance from the actual engineering application requirements. The orbits designed near the triangular translation point under the simplified circular restricted three-body problem usually diverge very quickly in the actual Earth-Moon system. Taking the L4 point under the circular restricted three-body problem as an example, under the simplified circular restricted three-body problem model, the detector will be fixed at this point and keep its position unchanged, but this orbit is in the actual Earth-Moon system. The runtime diverges quickly and is not suitable as a mission track. In short: the orbit under the circular restricted three-body problem model doe...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20G06F17/17G06F17/12
CPCG06F30/20G06F17/17G06F17/12Y02T90/00
Inventor 侯锡云王鹏辛晓生
Owner NANJING UNIV
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