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

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...

AI Technical Summary

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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