Mars capture braking strategy calculation method and system

Abstract

The invention provides a Mars capture braking strategy calculation method and system, and relates to the technical field of spacecraft overall design, and the method comprises the steps: S1, collecting related data of a hyperbolic progressive vector entering Mars, earth pointing and sun pointing, and building an auxiliary coordinate system; s2, calculating and capturing a semi-major axis of an orbit through the established auxiliary coordinate system; s3, calculating the eccentricity rate of the captured orbit through the established auxiliary coordinate system; s4, calculating and capturing an orbit inclination angle, an ascending node right ascension and a near fire point argument through the established auxiliary coordinate system; and S5, calculating related included angles with the earth and the sun through the established auxiliary coordinate system, and carrying out contrastive analysis on conditions including energy and communication in the capture stage according to related data obtained through calculation. According to the method, the calculation speed of the captured orbit parameters and the design efficiency of the Mars capture strategy can be improved.

Description

technical field [0001] The invention relates to the technical field of the overall design of spacecraft, in particular to a method for quickly calculating a Mars capture and braking strategy, and in particular to a method and system for calculating a Mars capture and braking strategy. Background technique [0002] Mars capture braking refers to the process in which the probe is decelerated from a hyperbolic orbit through a near-fire point to form a ring-fire orbit. Since the speed increment of the capture braking is large and the deceleration braking time is long, the capture effect directly determines the success or failure of the entire task. The design of the near-fire capture strategy needs to consider the accuracy of the orbit determination in the near-fire section, the visible arc of the measurement and control station, the Mars occultation duration of the ground communication, the Mars shadow time, the height of the Martian atmosphere, the orbit control error, the sel...

AI Technical Summary

Problems solved by technology

In the phase of capture strategy design and comparison, it is necessary to quickly calculate the capture orbit parameters. Aiming at the time-consuming problem of numerical integration method in state setting and numerical integration calculation, it is necessary to propose a calculation method to improve the calculation speed of capture orbit parameters and Mars capture. Strategy Design Efficiency

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