Multi-variable redundancy numerical control servo system using multi-source hydrogen energy
A servo system and multi-variable technology, applied in the field of launch vehicle control, can solve problems such as the inability to use high-power servo systems
Active Publication Date: 2017-03-22
BEIJING RES INST OF PRECISE MECHATRONICS CONTROLS +1
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[0005] Domestic CZ-3A\CZ-3B rocket 8T liquid hydrogen and liquid oxygen engine thrust vector control electro-hydraulic servo mechanism adopts the energy scheme of draining high-pressure hydrogen from the hydrogen turbine pump of the engine to drive the small-power vane-type pneumatic transmission variable hydraulic pump, see attached Figure 17 , this kind of pneumatic energy solution is only applicable to the servo mechanism system of relatively small power, and cannot be used for the high-power servo system required by the present invention
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[0077] The multi-variable redundancy numerical control servo system of the present invention is applied to liquid hydrogen and liquid oxygen engines, and includes a servo controller, a servo mechanism A, two servo mechanisms B, a servo mechanism C and a servo mechanism D; the servo mechanism C Same as servo mechanism A; said servo mechanism D is the same as servo mechanism B;
[0078] The servo controller is a three-redundancy digital servo controller;
[0079] The servo mechanism A is as figure 1 As shown, a servo mechanism integrating a hydrogen turbo pump, the servo mechanism includes a hydrogen turbo pump 1, a cooler 2, a turbo pump mounting seat 3, a cooler ear seat 4, a servo actuator A5, and a flexible graphite gasket 6 , sealing ring 7, bolt 8, bolt 9, bolt 10 and bolt 11;
[0080] The hydrogen turbopump 1 includes an end cover, a casing and a pump wheel; the top of the casing is fixedly connected to the end cover, the bottom of the casing is fixedly connected to th...
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The invention relates to a multivariable redundancy numerical control servo system adopting multisource hydrogen energy for a launch vehicle and belongs to the technical field of launch vehicle control. A system-level three-redundancy design scheme is adopted in a servo system control circuit, each three-redundancy servo valve is provided with three independent prestages, and each three-redundancy displacement sensor is provided with three independent redundancy channels. A servo controller receives three-redundancy numerical control commands on a 1553B bus, meanwhile, each sub-controller of the servo controller acquires three paths of linear displacement of the three-redundancy displacement sensor of one servo mechanism, a linear displacement majority voting algorithm and a data closed-loop control algorithm are executed by a central processing unit of the controller for processing, servo valve control current is output after D / A conversion and power amplification, the current is output to one prestage of the three-redundancy servo valve of one servo mechanism, majority voting is achieved on a power-level slide valve of the corresponding servo valve, and one-redundancy obstacles of the redundancy channels can be eliminated.
Description
technical field [0001] The invention relates to a servo system, in particular to a multi-variable redundancy numerical control servo system for multi-source hydrogen energy used in a launch vehicle, and belongs to the technical field of launch vehicle control. Background technique [0002] Servo system is a general term for the subsystems of the launch vehicle flight control actuator in my country. The typical application is the thrust vector control of the swing engine. The liquid hydrogen and liquid oxygen engine uses liquid hydrogen and liquid oxygen as fuel, and has the advantages of non-toxic, non-polluting, high cost performance, and convenient use and maintenance. It is currently a mainstream launch vehicle engine in the world. Correspondingly, the servo system supporting the liquid hydrogen and liquid oxygen engine is also a necessary equipment. [0003] The thrust vector control electro-hydraulic servo mechanism of large-thrust rocket engines at home and abroad usu...
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IPC IPC(8): F02K9/80
CPCF02K9/805F05D2220/80
Inventor 曾广商张晓莎张文海景光辉秦向明刘俊琴张淑敏陈祖希郭薇妮赵守军
Owner BEIJING RES INST OF PRECISE MECHATRONICS CONTROLS