Lunar finite thrust multi-capture orbit realization method

Abstract

The invention discloses a lunar finite thrust multi-capture orbit realization method and belongs to the field of aerospace technology. According to the specific realization method, a prober finite thrust kinetic equation is established under a lunar inertial system; a single lunar capture maneuver is decomposed into multiple capture maneuvers, and parameters of each capture maneuver are optimized;and velocity pulses needed by the first maneuver and the remaining maneuvers are converted into an optimal finite thrust capture orbit, an initial work phase, a thrust direction and work time of an engine are optimized, optimal finite thrust capture is realized, and a target orbit is entered. Through the lunar finite thrust capture orbit realization method, the needed velocity increment is small,capture efficiency is high, the finite thrust capture orbit meeting constraint can be obtained, and convergence is good.

Description

technical field [0001] The invention relates to a method for realizing multiple capturing orbits with limited thrust of the moon, which is suitable for the design of lunar capturing orbits of probes using limited thrust, and belongs to the technical field of aerospace. Background technique [0002] The moon is the closest celestial body to the earth. It has important scientific exploration value and is also the starting point for human deep space exploration. At present, humans have carried out many lunar exploration missions, mainly large-scale detectors. Compared with large satellites, microsatellites have the characteristics of low cost, small size, and diverse functions. They are one of the focuses of current satellite development and will also be widely used in lunar exploration. The design of the lunar capture orbit is an important part of the lunar exploration mission. It requires the probe to use its own thrust brake to achieve the lunar capture. The capture process ...

AI Technical Summary

Problems solved by technology

For tiny satellites with small self-thrust, it takes a long time to generate the same speed increment, and the braking speed increment cannot be approximated as pulse processing, and the gravity loss is large, so it is not suitable for the moon capture design with limited thrust.

[0004] Prior technology [2] (see Li Junfeng, Gong Shengping, Mars exploration and capture strategy analysis of limited thrust model [J] Chinese Science: Physics, Mechanics and Astronomy, 2013,43(6):781-786.) studied the limited thrust of Mars rover For the capture problem, the strategies of fuel optimal capture, attitude uniform rotation and attitude inertial directional capture were analyzed. However, this study was still designed for detectors with high thrust, and only considered the case of a single capture orbit. The capture efficiency was low and the fuel consumption was low. Big

Images