Reusable carrier rocket core first-stage rocket body recycling power system

Abstract

The invention provides a reusable carrier rocket core first-stage rocket body recycling power system. An intermediate engine is a swing engine; the axis of the intermediate engine is superposed with the axis of the core first-stage rocket body; three circumferential engines are arranged uniformly in the circumferential direction of the intermediate engine; and the thrust directions of the intermediate engines and the circumferential engines are parallel with the axis of the core first-stage rocket body. The intermediate engine and the circumferential engines do not have mounting angles, pitching and yaw control in the ascent stage of the core first-stage rocket body are realized by throttling ability of a liquid oxygen methane engine, rolling control is realized by a last-stage auxiliary power system, the intermediate engine and the circumferential engines work for one time in the re-entry process, speed reduction and attitude control of the core first-stage rocket body are realized bythe throttling ability of the circumferential engines, and accurate landing control is realized by the intermediate engine before landing, so that the intermediate engine and the three circumferential engines only need to have twice starting ability to fulfill the above aims, and the development difficulty and cost of the liquid oxygen methane engine are reduced.

Description

technical field [0001] The invention relates to a recovery power system for a first-stage rocket body of a reusable launch vehicle core, and belongs to the technical field of reusable launch vehicles. Background technique [0002] The core stage of the reusable launch vehicle usually adopts multiple engine layout schemes. For example, the core stage of the Falcon 9 rocket uses 9 liquid oxygen kerosene engines. During the reentry process, some engines work to achieve attitude stability and precise landing control. [0003] The engine is the core component of the launch vehicle. If the number of engines is too small, the engine needs to be adjusted in depth, which increases the difficulty of developing the engine system. How to achieve control during flight and recovery control during reentry with the least number of engines is an engineering problem faced by reusable launch vehicles at home and abroad. [0004] The traditional layout of the engine on the rocket body is the l...

AI Technical Summary

Problems solved by technology

[0004] The traditional layout of the engine on the rocket body is the layout of "+" and "×". Taking the CZ-2C, CZ-2F, and CZ-3A series rockets as examples, both the "+" and "×" are installed There are four engines, but all four engines have installation angles, which will result in a loss of engine thrust, and the thrust advantage of the launch vehicle engine cannot be maximized

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