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Liquid Rocket Engine Thrust and Mixing Ratio Adjustment Redundancy Electromechanical Servo System

An electromechanical servo system and thrust adjustment technology, which is applied in the direction of rocket engine devices, control/regulation systems, engine control, etc. The problem of low inherent reliability of the drive can be solved, and the effect of improving the adjustment control characteristics, improving reliability, improving reliability and using maintainability

Active Publication Date: 2020-06-09
XIAN AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] (1) The size and weight of redundant electromechanical actuators are large, which cannot meet the application requirements of small and light liquid rocket engines
[0008] (2) The inherent reliability of the servo drive is low, and the failure rate is high, which is the weak link in the reliability of the electromechanical servo control

Method used

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  • Liquid Rocket Engine Thrust and Mixing Ratio Adjustment Redundancy Electromechanical Servo System

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Embodiment Construction

[0036] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.

[0037] The present invention proposes an electromechanical servo system capable of realizing "three-redundancy control and double-redundancy drive" for thrust and mixing ratio, high reliability, high precision, and quick response adjustment. Such as figure 1 As shown, it includes servo controller 1, thrust adjustment servo driver 2, mixing ratio adjustment servo driver 3, thrust adjustment electromechanical actuator 4, mixing ratio adjustment electromechanical actuator 5, thrust adjustment position sensor 6, and mixing ratio adjustment position sensor 7. Thrust regulator 8 and mixing ratio regulator 9.

[0038] The servo controller 1 is a three-redundancy servo controller: it receives the engine thrust adjustment command issued by the rocket-borne computer and the position information of the thrust regulator 8 fed back by the thrust adjustmen...

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Abstract

The invention discloses a redundant degree electromechanical servo system for liquid rocket engine thrust and mixing ratio adjustment, including a three-redundancy servo controller, a double-redundancy servo driver, a double-winding electromechanical actuator, a three-redundancy position sensor, a thrust regulator and Mixing ratio regulator. The engine thrust and mixing ratio adjustment command and the position feedback signal of the three-redundancy position sensor are input to the three-redundancy servo controller, and the three-redundancy servo controller outputs the thrust and the mixing ratio adjustment PWM wave control signal to the double-redundancy servo driver. The high-speed servo driver outputs three-phase variable-frequency variable-amplitude sine wave current to drive the double-winding electromechanical actuator to drive the thrust regulator and the mixing ratio regulator to move, so as to realize the adjustment of engine thrust and mixing ratio. The servo system is simple and has excellent control characteristics. It has the capability of "controlling two-degree failure and driving one-degree failure", which significantly improves the reliability and maintainability of liquid rocket engine thrust and mixing ratio adjustment.

Description

technical field [0001] The invention relates to an electromechanical servo system for adjusting redundancy of thrust and mixing ratio of a liquid rocket engine, and belongs to the field of adjusting and controlling thrust and mixing ratio of a liquid rocket engine. Background technique [0002] Early liquid rocket engines generally use electro-hydraulic servo control or stepper motor control. The SSME main engine of the American space shuttle has its own controller to control the electro-hydraulic servo-actuated valve to realize the closed-loop adjustment of thrust and mixing ratio. Russian RD-171M and RD-180 engines use seven-digit electro-hydraulic servo-actuated valves to realize closed-loop adjustment of thrust and mixing ratio. The actuator energy is provided by the ground motor pump supply device before the engine starts, and the engine starts to a certain working condition Then switch to the fuel pump drainage supply. Russian NK-33 and RD-0120 engines use stepping m...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/56
CPCF02K9/56F05D2270/62F05D2270/66F02K9/60F05D2270/3015F15B18/00F02K9/42F02K9/58G06F11/1641G05B9/03
Inventor 张晓光陈晖杨亚龙魏京芳董国创马冬英蒲星星
Owner XIAN AEROSPACE PROPULSION INST
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