A launch window search method for ground-fire short transfer orbit with deep space maneuvering

Abstract

The invention provides a ground-fire short-transfer orbit launch window search method with deep space maneuvering, including: establishing an orbit optimal design model, transforming the orbit optimal design problem into a multi-dimensional nonlinear programming problem, determining orbit optimal design parameters, optimizing the orbit index, and give the constraint function during model optimization; use the C3 energy contour diagram and Lambert theory to obtain the initial values ​​of the track optimization design parameters; bring the initial values ​​of the track optimization design parameters into the multi-dimensional nonlinear programming problem solving process, After the optimization has converged, the key parameters of the orbit scheme design are extracted to complete the launch orbit window search. The method of the invention proposes to perform a deep space maneuver in the short ground-fire transfer considering the constraints of the launch, and use an optimized method to search for the window, which can effectively adapt to the constraints of the launch vehicle on the probe and widen the launch window of the Mars probe. It can be used to search the launch window of the Mars rover's ground-fire transfer orbit.

Description

technical field [0001] The invention belongs to the field of deep space exploration interstellar transfer orbit design, and in particular relates to a ground-fire short transfer orbit launch window search method with deep space maneuvering. Background technique [0002] There are many ways to fly from Earth to Mars, including direct transfer, low-energy transfer, and small-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 is that the probe reaches Mars before reaching the aphelion of the heliocentric elliptical orbit, and the transfer time is short; while the long transfer is that the probe reaches Mars after reaching the aphelion of the heliocentric elliptical orbit, and the transfer time is longer. . [0003] my country's first Mars exploration mission raised the need for a short transfer scheme. However, the short transfer scheme faces engineerin...

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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