Geofire short transfer orbit launching window searching method with deep space maneuver

Abstract

The invention provides a ground fire short transfer orbit launch window search method with deep space maneuver. The method comprises the following steps: establishing an orbit optimization design model, converting an orbit optimization design problem into a multi-dimensional nonlinear programming problem, determining orbit optimization design parameters and optimization indexes, and giving a constraint function when the model is optimized; the C3 energy contour map and the Lanbert theory are used for obtaining orbit optimization design parameter initial values; and the initial values of the orbit optimization design parameters are substituted into a multi-dimensional nonlinear programming problem solving process, and after optimization convergence, orbit scheme design key parameters are extracted to complete launch orbit window search. According to the method, one-time deep space maneuver is carried out in the ground fire short transfer considering the carrying launch constraint, the optimized method is adopted for window searching, the method can effectively adapt to the constraint of a carrier rocket on the detector, the launch window of the Mars probe is widened, and the method can be used for searching the ground fire transfer orbit launch window of the Mars probe.

Description

technical field [0001] The invention belongs to the field of design of interstellar transfer orbits for deep space exploration, in particular to a launch window search method for ground fire short transfer orbits with deep space maneuvering. Background technique [0002] There are many ways to fly from Earth to Mars, including direct transfer, low-energy transfer, and low-thrust transfer. The most commonly used method for Mars exploration is direct transfer, which is divided into short transfer and long transfer. Among them, the short transfer means that the probe reaches Mars before reaching the aphelion of the heliocentric elliptical orbit, and the transfer time is relatively short; while the long transfer means that the probe arrives at Mars after reaching the aphelion of the heliocentric elliptical orbit, and the transfer time is relatively long . [0003] my country's first Mars exploration mission puts forward the need to adopt a short transfer scheme. However, the ...

AI Technical Summary

Problems solved by technology

However, the short-transfer scheme faces engineering problems such as high requirements for launch conditions (such as launch direction and taxiing time), narrow launch window, and less residual mass for the probe to reach Mars.

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