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Variable-thrust turbopump-feed liquid rocket engine

An engine system and liquid rocket technology, applied in the direction of rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of being unable to adapt to large-scale commercial aerospace, low-cost launches, and high rocket costs

Pending Publication Date: 2020-12-11
AEROSPACE SCI & IND KET TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

On the other hand, the high cost of traditional one-time-use rockets has gradually failed to meet the needs of large-scale and low-cost commercial space launches. Recovery and reusability after launch have become the focus of the development of launch vehicles.

Method used

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  • Variable-thrust turbopump-feed liquid rocket engine
  • Variable-thrust turbopump-feed liquid rocket engine

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Embodiment Construction

[0039] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0040] Firstly, the embodiment of the present invention discloses an adjustable cavitation venturi.

[0041] figure 1 It is a structural schematic diagram of an adjustable cavitation venturi tube according to an embodiment of the present invention, combined with figure 1 , which includes a first valve body 1 , a driving motor 8 , a second valve body 3 , a valve stem 6 and a third valve body 7 .

[0042] combine figure 1 , in the embodiment of the present inv...

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Abstract

The invention belongs to the technical field of aerospace power, and particularly relates to a variable-thrust turbopump-feed liquid rocket engine. A fuel pump of the system is provided with an inputend and two output ends, and the input end of the fuel pump is connected with a fuel source; an oxidizing agent pump is provided with an input end and two output ends, and the input end of the oxidizing agent pump is connected with an oxidizing agent source; a thrust chamber is respectively connected with one output end of the fuel pump and one output end of the oxidizing agent pump; a fuel gas generator is connected with the other output end of the fuel pump and the other output end of the oxidizing agent pump; a first adjustable cavitation venturi tube is arranged between the fuel gas generator and the other output end of the fuel pump; and a second adjustable cavitation venturi tube is arranged between the fuel gas generator and the other output end of the oxidizing agent pump. According to the variable-thrust turbopump-feed liquid rocket engine provided by the invention, the thrust of an engine can be adjusted to adapt to the recovery of rockets and the injection of loads.

Description

technical field [0001] The invention belongs to the technical field of aerospace power, in particular to a variable thrust pump pressure liquid rocket engine system. Background technique [0002] Liquid rocket engine is the main propulsion device of space launch vehicle, which has the characteristics of high thrust, high specific impulse and complex system structure. In order to simplify the system composition, reduce the difficulty of development, and improve reliability, traditional liquid rocket engines are usually designed to work only at the rated thrust, without the ability to adjust the thrust in real time during the working process. [0003] With the increasing number and types of space payloads, the requirements for the adaptability of launch vehicles are getting higher and higher. Launching multi-track and multiple satellites with one rocket has gradually become the main working mode of launch vehicles. On the other hand, the high cost of traditional one-time-use ...

Claims

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Application Information

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IPC IPC(8): F02K9/56F02K9/58F02K9/48F02K9/60
CPCF02K9/56F02K9/58F02K9/48F02K9/60
Inventor 王弘亚姜映福孙晓伟张召磊朱丹赵学光杨跃龚习马道远查雄权
Owner AEROSPACE SCI & IND KET TECH CO LTD
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