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Double-cam closed-loop feedback measurement device

A closed-loop feedback and measurement device technology, which is applied in gas turbine engine testing, jet engine testing, etc., can solve the problems of missile out of control, missile power-off and zero, engine thrust vector cannot be kept at zero, etc., to achieve easy installation and operation, Simple and compact structure

Active Publication Date: 2018-02-02
BEIJING RES INST OF PRECISE MECHATRONICS CONTROLS +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the current gas-hydraulic servo system rolls and controls the servo actuator, which cannot realize the synchronization of control feedback measurement, which will easily lead to the inability to "power off and return to zero" when the missile is flying, that is, when the servo system loses the control command signal, the thrust vector of the engine cannot be maintained at Zero position, prone to catastrophic failure of control open loop leading to complete loss of control of the missile

Method used

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  • Double-cam closed-loop feedback measurement device
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  • Double-cam closed-loop feedback measurement device

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Embodiment Construction

[0022] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.

[0023] Such as figure 1 , 2 , 3, the double-cam closed-loop feedback measurement device provided by the present invention includes an output shaft 1, a support 2, a feedback cam 3, an end cover 4, a dust-proof ring 5, a set screw 6, a flat key 7, Shaft retaining ring 8 and ball bearing 9. Two feedback cams 3 are installed in parallel outside the middle of the same output shaft 1. The two feedback cams 3 are installed at an angle of 45° in the radial direction of the output shaft 1. Only the flat key 7 is needed between the two feedback cams 3 and the output shaft 1. , The set screw 6 can be fixed by adding a punching point on the end face, and the installation and operation are simple and convenient. The right part of the output shaft 1 is covered with a support 2, and there is a gap between the support 2 and the two feedback cams 3; a ball...

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Abstract

The invention belongs to a feedback measurement device for a ballistic missile solid engine thrust vector control subsystem, and particularly discloses a double-cam closed-loop feedback measurement device. The device comprises an output shaft, a bearer, feedback cams, an end cap, a fastening screw, a flat key and a ball bearing. The feedback cams sleeve the middle art of the output shaft. The feedback cams are fixed to the output shaft through the flat key and the fastening screw. The bearer sleeve the right part of the output shaft. A clearance is reserved between the bearer and the feedbackcams. The ball bearing is nested between the output shaft and the bearer. The end cap which sleeves the output shaft is arranged outside the ball bearing. A plurality of feedback cams are arranged. The plurality of feedback cams parallelly sleeve the output shaft. A shaft backup ring is arranged between the ball bearing and the end cap. A dustproof ring is arranged between the end cap and the output shaft. The feedback measurement device can satisfy requirement for thrust vector machine feedback closed-loop rolling controlling and synchronous measurement, and simultaneously a high-reliabilityrequirement for clearing in powering-off. Furthermore the feedback measurement device has advantages of compact structure, and synchronization between feedback and measurement.

Description

technical field [0001] The invention belongs to a feedback measurement device for a thrust vector control subsystem of a ballistic missile solid engine, in particular to a double-cam closed-loop feedback measurement device for a rolling control servo actuator of a ballistic missile solid engine thrust vector control subsystem-gas hydraulic servo system. Background technique [0002] The gas-hydraulic servo system is a solid strategic missile thrust vector control execution subsystem. Its typical application is to implement thrust vector control by swinging the flexible nozzle of a solid engine. Among them, the roll control servo actuator provides rolling attitude control torque for the solid engine thrust vector. Due to the small space of the missile body, high power level (30 kilowatts), large load inertia, unstable center of gravity, and high reliability requirements, the gas-hydraulic servo system has become one of the key support technologies for the whole missile. Howev...

Claims

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Application Information

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IPC IPC(8): G01M15/14
CPCG01M15/14
Inventor 滕序翎陈飞滕怀海耿树鲲田福良
Owner BEIJING RES INST OF PRECISE MECHATRONICS CONTROLS