Multi-orbit design method for launch vehicle fire-striving launching and fire-striving launching control method

Abstract

The invention provides a multi-orbit design method for carrier rocket fire-striving launching and a fire-striving launching control method. The fire-strike launching multi-orbit design method comprises the steps that task data of P Mars orbit entrances specified by a fire-strike launching task are obtained, the task data of each Mars orbit entrance comprises a launching window where a detector is located at the Mars orbit entrance, and P is a natural number larger than 2; an iterative optimization method is adopted, P fire-strike launching orbits where the carrier rocket carries the detector to fly are designed, and target points of the P fire-strike launching orbits are in one-to-one correspondence with the P Mars orbit entrances; and when the carrier rocket is controlled to fly according to any one of the P fire-striving launching orbits, the carrier rocket carries the detector to the Mars orbit entrance corresponding to the fire-striving launching orbit. According to the design method, the design efficiency is improved, the complexity of flight data is reduced, and reliable launching and accurate orbit injection of the large low-temperature carrier rocket can be realized.

Description

technical field [0001] The invention belongs to the field of overall design and launch task planning of a carrier rocket, and relates to a multi-track design method and a control method for the rush-fire launch of a carrier rocket. Background technique [0002] Both Earth and Mars are satellites of the sun, and both revolve around the sun while they are self-biography. In space, the relative positions of Earth and Mars are constantly changing. Launching a vehicle from the earth to launch a probe to Mars (hereinafter referred to as a fire launch), the opportunity for deep space exploration of Mars is only once every 26 months on average. [0003] In order to realize the reliable launch of a large liquid cryogenic launch vehicle (hereinafter referred to as the launch vehicle) under the complex meteorological environmental conditions of the coastal launch site on the earth, and after the separation of the vehicle and the rocket, the probe can accurately enter the entrance of t...

AI Technical Summary

Problems solved by technology

[0005] In view of the above problems, the present invention provides a multi-track design method and a fire launch control method of a carrier rocket, so as to solve one or more of the problems of high complexity and low launch reliability of the multi-track design method in the prior art. indivual

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