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Method for determining deep space detector equivalent transfer orbit

A technology for deep space detectors and transfer orbits, which is applied in the direction of instruments, measuring devices, surveying and navigation, etc., and can solve the problems of no introduction

Active Publication Date: 2009-01-28
AEROSPACE DONGFANGHONG SATELLITE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

There are many equivalent methods involved in the available patent literature, but the concept of "equivalent" has not been introduced in the orbit design of deep space probes

Method used

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  • Method for determining deep space detector equivalent transfer orbit
  • Method for determining deep space detector equivalent transfer orbit
  • Method for determining deep space detector equivalent transfer orbit

Examples

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Embodiment

[0077] The "Kuafu" program is an international cooperation project aimed at solar-terrestrial space weather detection and forecasting. The mission orbit of the "Kuafu-A" star is a halo orbit around the L1 point of the sun and the earth, and the distance between the orbit and the earth is not less than 1.27 million kilometers. The "Kuafu A" star is directly sent by rocket into a transfer orbit with a perigee altitude of 200 kilometers and an apogee of 1.27 million kilometers. The "Kuafu A" star is not only affected by the gravitational force of the earth, but also by the gravitational force of the larger moon and the sun in the transfer orbit. The space mechanics environment is complicated, and its orbital shape is no longer a simple ellipse, such as image 3 shown; image 3 Shown in is the projection of the precise transfer orbit in the ecliptic plane (the reference coordinate system is the geocentric ecliptic rotation coordinate system), so it can be seen that this is a space...

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Abstract

The invention discloses a method for determining an equivalent transfer orbit of a deep space probe, which comprises the steps: (1) the equivalent transfer orbit of the deep space probe is designed according to an orbit dynamic model, and the orbit parameter of the designed transfer orbit is extracted; (2) the near-earth equivalent parameter of the transfer orbit of the deep space probe is solved according to the orbit parameter extracted in the step (1) and the spatial geometric relationship. By the method of the invention, when a carrier rocket directly sends a probe into the transfer orbit, the carrying party does not need to establish a complex dynamic model for the deep space probe, and the existing model used for estimating the launching precision can estimate the transmission precision more correctly, thereby solving the problem that the current carrier rocket in China does not have an upper stage and can not send the probe into the transfer orbit by using the upper stage for firing. The method of the invention adopts the concept of equivalence to solve the problem and is simple and reliable.

Description

technical field [0001] The invention relates to an equivalent parameter design method for a transfer orbit of a deep-space probe, in particular to an equivalent parameter design method for a transfer orbit of a deep-space probe directly launched into the transfer orbit by a carrier rocket. Background technique [0002] Although there is no unified definition of "deep space" and "deep space exploration" in the world, the definitions of deep space in the encyclopedias and dictionaries of European and American countries, the aerospace volume of the Encyclopedia of China, and the International Telecommunication Union When specifying the use of communication frequencies in space exploration activities, the definition of "deep space" and "non-deep space" can be found: the distance between the detection target of the detector and the earth in deep space exploration activities is greater than or equal to the distance between the earth and the moon . [0003] Judging from the above-...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/00
Inventor 张燕杨芳刘胜利
Owner AEROSPACE DONGFANGHONG SATELLITE
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