Pico-meter magnitude satellite orbit simulation method and system for deep space exploration

A technology for satellite orbit and deep space exploration, applied in the field of satellite orbit simulation, can solve problems such as insufficient accuracy of satellite orbit numerical simulation, and achieve the effect of wide applicability

Active Publication Date: 2022-06-24
NAT SPACE SCI CENT CAS
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Problems solved by technology

[0007] The purpose of the present invention is to overcome the problem of insufficient accuracy of satellite orbit numerical simulation in the current deep space exploration tasks, such as heliocentric space gravitational wave detection tasks, and propose a high-precision orbit numerical value suitable for heliocentric space gravitational wave detection tasks The simulation method and system, simulate the orbit of the satellite at the 1AU scale at the picometer level, and verify the correctness and effectiveness of the method

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  • Pico-meter magnitude satellite orbit simulation method and system for deep space exploration
  • Pico-meter magnitude satellite orbit simulation method and system for deep space exploration
  • Pico-meter magnitude satellite orbit simulation method and system for deep space exploration

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Embodiment Construction

[0044] The present invention designs a high-precision solution method for satellite orbits suitable for the heliocentric orbit space gravitational wave detection task, and evaluates the correctness and accuracy of the solution through the two-body problem. The method mainly includes four parts: underlying framework (C++), solver development, force model construction and orbit solution, including the following steps:

[0045] Step 1) add the gravitational field of several celestial bodies, and establish a satellite formation dynamics model;

[0046] Step 2) Set the required effective number of digits, the start time of satellite orbit simulation, the optimization parameters for satellite orbit initialization, the simulation step size and the parameters of the solver; The basic operation library solves the satellite formation dynamics model to obtain the position and velocity matrix of the satellite at the time corresponding to the simulation step in the set start time, wherein,...

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Abstract

The invention relates to the field of satellite orbit simulation, in particular to a picometer-scale satellite orbit simulation method and system for deep space exploration, and the method comprises the following steps: 1) adding a gravitational field of a plurality of celestial bodies, and building a satellite formation dynamics model; 2) setting required significant digits, starting time of satellite orbit simulation, optimization parameters for satellite orbit initialization, simulation step length and parameters of the solver; and calculating the satellite formation dynamics model through the solver and a basic operation library developed based on an MPFR library to obtain the position and speed matrix of the satellite at the moment corresponding to the simulation step length. According to the method, any significant digit floating point operation can be carried out, the simulation precision is not limited by double-precision 16 significant digits any more, and the precision is superior to 0.03 picometer magnitude.

Description

technical field [0001] The invention relates to the field of satellite orbit simulation, in particular to a picometer-level satellite orbit simulation method and system for deep space exploration. Background technique [0002] The space laser interferometric gravitational wave antenna is an ultra-precise measurement system. The "Tai Chi" plan proposed by the Chinese Academy of Sciences plans to use a three-star formation running in a heliocentric orbit to detect gravitational waves in space. The satellite formation is about 1 AU from the center of the sun. (1AU is approximately equal to 1.496×10 11 m), each satellite contains two test masses. Using the test mass as a gravitational wave sensor, a high-precision laser interferometric ranging system is used to measure the picometer level (1×10) between two free test masses that are separated by millions of kilometers caused by gravitational waves. -12 m) The distance changes, and then the gravitational wave signal is inverted...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F119/14
CPCG06F30/20G06F2119/14
Inventor 韩晓晴唐文林彭晓东杨震马晓珊强丽娥
Owner NAT SPACE SCI CENT CAS
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