Integral type liquid rocket stamping combined power device

Abstract

The invention discloses an integral type liquid rocket stamping combined power device, and belongs to the technical field of wide-speed-range combined power. Comprising a lateral air inlet channel, a storage box device, an ejection rocket, an ejection mixing section, a mixing combustion chamber and an exhaust nozzle. The ejector rocket is fixed to the center of the ejecting and mixing section, the storage box device is placed at the head of the ejector rocket, the side air inlet channel is arranged on the periphery of the storage box device, the rear end of the ejecting and mixing section is connected with the mixing combustion chamber, eight fuel short supporting plates are arranged on the wall face of the mixing combustion chamber, and the ejector rocket and the mixing combustion chamber share one exhaust nozzle. The liquid rocket can control the working state of the rocket, and it is guaranteed that the device has high performance under various working conditions. The molded surface of the petal-shaped injection mixing section is matched with the rocket plume, so that the suction effect on incoming flow of the air inlet channel can be improved, and the amount of air captured by the low-Mach-number air inlet channel is increased. The engine performance is guaranteed, the length of the engine is shortened, and the weight of the engine is reduced; the storage box is large in volume, compact in structure and high in space utilization rate.

Description

technical field [0001] The invention belongs to the technical field of wide-speed range combined power, and in particular relates to an integral liquid rocket stamping combined power device. Background technique [0002] In the 1960s, the United States took the lead in carrying out the research program of the reusable space transportation system. Under this background, the research work on the rocket-ramjet combined propulsion system was first started. In the launch and propulsion system development roadmap TA-01 released by NASA in 2012 , the rocket-ramjet combination engine is listed as one of the two engines with the highest priority in the air-breathing propulsion system (Lei Shi, Guojun Zhao, Yiyan Yang, Da Gao, Fei Qin, Xianggeng Wei, Guoqiang He. Research progress on ejector mode of rocket-based combined-cycle engines[J]. Progress in Aerospace Sciences, 2019, 107.). [0003] my country began to conduct follow-up research on rocket ramjet technology in the 1970s. In t...

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Problems solved by technology

[0004]Aiming at the application prospect of rocket ramjet combined engine in supersonic long-range cruise missiles and recoverable reconnaissance strike devices, the following main problems exist in existing rocket ramjet power devices: Most launch rockets use solid rockets, and it is difficult to control the working state of the rocket. It is difficult to ensure that the combined power plant has high performance under various working conditions; The airway is easily affected by it; the mixing effect in the mixing section is poor, resulting in an excessively long engine length; the fuel support plate is arranged in the center of the flow channel to withstand the high-temperature wake of the rocket, resulting in difficulties in thermal protection

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