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Variable-thrust rocket engine and rocket with same

A rocket engine and variable thrust technology, which is applied in the direction of rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems such as the complex structure of variable thrust rocket engines, and achieve the effect of simplifying the structure

Inactive Publication Date: 2019-06-21
BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Therefore, the technical problem to be solved by the present invention is to provide a technical defect that overcomes the complex structure of the variable thrust rocket engine in the prior art, thereby providing an electric variable thrust rocket engine and a rocket with it.

Method used

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  • Variable-thrust rocket engine and rocket with same
  • Variable-thrust rocket engine and rocket with same

Examples

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Embodiment 1

[0041] Such as figure 1 As shown, the present embodiment provides an electric variable thrust rocket engine, which includes: a thrust chamber 1; a supercharging device, which injects fuel and an oxidant into the thrust chamber 1; a gas generator 15, which drives the supercharging The device is running; the first electric pump 16 is driven by a motor with adjustable speed to provide oxidant to the gas generator 15; the second electric pump 17 is driven by a motor with adjustable speed to provide fuel to the gas generator 15 .

[0042] It drives the first electric pump 16 and the second electric pump 17 through a motor to provide oxidant and fuel for the gas generator 15 respectively. Since the motor speed is adjustable, it can change the ratio of the oxidant and fuel entering the gas generator 15. The gas generated by the gas generator 15 drives the supercharging device and changes the power of the supercharging device; the supercharging device changes the flow rate of fuel an...

Embodiment 2

[0054] This embodiment provides a rocket, which has the electric variable thrust rocket motor described in Embodiment 1. The rocket provided in this embodiment drives the first electric pump and the second electric pump through a motor to provide oxidant and fuel for the gas generator respectively when the thrust is variable. Since the motor speed is adjustable, it can Change the flow rate of the oxidant and fuel entering the gas generator, the gas produced by the gas generator drives the turbo pump, and changes the power of the turbo pump; the turbo pump changes the fuel and oxidant injected into the thrust chamber flow, thereby regulating the thrust of the rocket engine. Moreover, the first electric pump and the second electric pump are also used as rocket engine starting devices to realize multiple starts of the engine, thus simplifying the structure of the rocket.

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Abstract

The invention relates to the technical field of spaceflight propulsion, in particular to a variable-thrust rocket engine and a rocket with the same. The variable-thrust rocket engine drives a first electric pump and a second electric pump through a motor so as to provide an oxidant and a fuel for a gas generator respectively, due to the fact that the rotating speed of the motor is adjustable, theflow of the oxidant and the fuel entering the fuel gas generator can be changed, fuel gas generated by the fuel gas generator drives a pressurizing device, and the power of the pressurizing device ischanged; and the pressurizing device is used for changing the flow of the fuel and the oxidant which are injected into a thrust chamber, so that the pushing force of the rocket engine is adjusted. Moreover, the first electric pump and the second electric pump are also used as a starting device of the rocket engine, so that multiple starting of the engine is realized, and the structure of the variable-thrust rocket engine is simplified.

Description

technical field [0001] The invention relates to the field of aerospace propulsion technology, in particular to a variable thrust rocket engine and a rocket with the same. Background technique [0002] Existing rocket engines adjust the flow rate of the gas generator through valves, that is, adjust the gas flow rate driving the turbine, change the output power of the turbine, and then change the engine flow rate to adjust the engine thrust. For example, Chinese patent CN108953003A discloses a method of using oxygen-enriched gas propulsion to realize the afterburning cycle engine system and thrust depth adjustment method. It discloses that the fuel is fed into the gas generator through the control of the generator fuel valve, and the oxidant is controlled into the gas generator through the oxygen valve. The generator, after full combustion, generates oxygen-enriched gas to drive the main turbine to work, thereby supplying fuel to the thrust chamber through the thrust chamber f...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/46F02K9/56F02K9/80F02K9/95
Inventor 不公告发明人
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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