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Rapid optimization design method for GEO satellite emergency transfer orbit based on moon leveraging

A technology for optimizing the design and transfer of orbits, applied in the field of spacecraft orbits, can solve the problems of emergency transfer orbit design with many variables and difficult optimization, and achieve the effect of solving the problem of rapid optimization design of lunar leverage parameters

Active Publication Date: 2019-08-06
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

The present invention can effectively solve the problems of many GEO satellite emergency transfer orbit design variables and great difficulty in optimization, and provide useful reference for the rapid optimization design and analysis of GEO satellite emergency transfer orbit

Method used

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  • Rapid optimization design method for GEO satellite emergency transfer orbit based on moon leveraging
  • Rapid optimization design method for GEO satellite emergency transfer orbit based on moon leveraging
  • Rapid optimization design method for GEO satellite emergency transfer orbit based on moon leveraging

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Embodiment

[0042] The present invention relates to a method for quickly optimizing the orbit of GEO satellite emergency transfer based on lunar leverage. The design idea is mainly reflected in the following two points:

[0043] First, for the lunar leverage orbit model, it is assumed that the radius of the moon’s gravitational influence sphere is zero, and the number of design variables is reduced to 2, which effectively reduces the difficulty of optimal design.

[0044] Second, by drawing the contour map of the key parameters of the return orbit, the mechanism of the lunar leverage orbit is intuitively clarified, and at the same time, it provides an accurate initial value guess for the optimal design of the return orbit, which is conducive to the rapid design of the emergency transfer orbit.

[0045] In the present invention: taking the GEO satellite emergency transfer orbit as the research object, an emergency transfer orbit model based on the moon's leverage is established, the optimiz...

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Abstract

The invention relates to a rapid optimization design method for a GEO satellite emergency transfer orbit based on moon leveraging in the technical field of spacecraft orbits, and the method comprisesthe following steps of 1, building a high-precision orbit dynamics model, and completing the search of a lunar transfer window and the preliminary design of a lunar orbit; step 2, establishing a moonleveraging track model, drawing a key parameter contour map of a return track after leveraging, and providing an initial value for leveraging parameter optimization design; and step 3, optimizing theleveraging parameters by using the drawn contour map and the return track design constraint to complete the design of the leveraging return track. According to the method, the moon leveraging parameter rapid optimization design problem is effectively solved, an effective method is provided for the rapid formulation of the GEO satellite emergency transfer scheme, and the numerical calculation result shows the effectiveness of the method.

Description

technical field [0001] The invention relates to the technical field of spacecraft orbits, in particular to an optimal design method for spacecraft low-earth orbits and moon-powered orbits. Background technique [0002] Geostationary Orbit (GEO) satellites have two main phases during their mission, one is the transfer from Geosynchronous Transfer Orbit (GTO) to GEO, and the other is the GEO orbit mission execution phase. The transfer of a satellite from GTO to GEO involves a large change in orbital inclination and perigee elevation, which requires a large amount of fuel, which is usually close to the dry weight of the satellite. Therefore, once the launch vehicle fails during the ascent process and fails to send the satellite into the scheduled GTO orbit, the satellite may not be able to enter the GEO orbit due to insufficient fuel, resulting in mission failure. The lunar leverage orbit is one of the effective technologies to solve the emergency transfer of GEO satellites. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F2119/06G06F30/20Y02T90/00
Inventor 郑艺裕黄欣宋效正
Owner SHANGHAI SATELLITE ENG INST
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