Novel controlling moment gyro framework assembly structure

A technology for controlling the torque gyroscope and component structure, which is applied in the direction of rotating gyroscopes, etc., can solve the problems of changing the loading state of high-speed bearings, affecting the power consumption, vibration level and working life of the control torque gyroscope, and achieves the reduction of micro-vibration level, Ensure accurate loading and reduce the power consumption of the whole machine

Active Publication Date: 2017-04-05
BEIJING INST OF CONTROL ENG
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

These two frame assembly structures have common disadvantages: when the frame assembly is subjected to the difference in internal and external atmospheric pressure, the force deformation of the frame assembly will change the loading state of the high-speed bearing, and affect the overall power consumption, vibration level and working life of the control moment gyroscope

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  • Novel controlling moment gyro framework assembly structure
  • Novel controlling moment gyro framework assembly structure
  • Novel controlling moment gyro framework assembly structure

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Embodiment Construction

[0018] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0019] Such as Figure 1-4 As shown, the novel frame assembly structure of the present invention includes a sealing cover 1 , a frame width 2 , a sealing cover spacer 3 , a frame edge 4 and an externally threaded conical pin 5 . The sealing cover 1 is an arc-shaped thin shell, the frame width 2 is an eight-claw support structure, the sealing cover pad 3 is a solid block in the shape of a cuboid, and the frame edge 4 is a cylindrical shell. The externally threaded tapered pin 5 is an externally threaded structure at the other end of a conical cone. There are 2 frame widths 2 and 8 externally threaded conical pins 5. The externally threaded conical pins 5 position the frame width 2 on the upper and lower sides inside the frame edge 4, and then fasten the frame width 2 to the frame edge with screws The upper and lower ends of 4 are used...

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Abstract

The invention relates to a novel controlling moment gyro framework assembly structure. The novel controlling moment gyro framework assembly structure comprises a sealed cover, a frame, a sealed cover cushion block, a frame rim and an external thread taper bolt. The external thread taper bolt is used by the frame for positioning the frame rim, the frame is used by a screw for fastening the frame rim, and is used for supporting a high-speed rotor, the screw is used by the sealed cover cushion block for fastening the frame rim, and is used for positioning the sealed cover. According to the novel framework assembly structure, a bearing member / sealing member separating structure is employed, a sealing system composed of the sealed cover and the frame rim is used for bearing atmospheric pressure difference of the framework assembly, the frame is used for supporting the high-speed rotor, a high-speed shaft is far from a solder side of the sealed cover, accurate loading of a high-speed bearing is ensured, and whole machine power consumption is reduced, influence on the high-speed shaft by instantaneous high heat during a welding process is eliminated, and the assembling precision detection and high-grade dynamic balancing precision are realized.

Description

technical field [0001] The invention relates to a novel control moment gyroscope frame assembly structure, which is especially suitable for improving the ability of the frame assembly to resist atmospheric pressure difference, ensuring the shape and position accuracy of the frame assembly, and reducing the power consumption of the whole machine. Background technique [0002] The control moment gyroscope is the key actuator for attitude control of long-running spacecraft such as space stations, remote sensing satellites, and optical satellites, which directly affects the pointing accuracy and stability of the spacecraft. Since the 1960s, the United States and Russia have successfully applied control moment gyro products to large spacecraft such as the Mir space station, Skylab and the International Space Station. [0003] The frame assembly structure is an important part of the control moment gyroscope, which is used to support the high-speed rotor and provide a sealed and cl...

Claims

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Application Information

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IPC IPC(8): G01C19/06
Inventor 魏大忠田兴田利梅武登云来林罗睿智宋萌张雪王英广王晓伟
Owner BEIJING INST OF CONTROL ENG
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