Parameter selection method adopting onboard control moment gyroscope group vibration-isolating platform

Abstract

The invention relates to a parameter selection method adopting an onboard control moment gyroscope group vibration-isolating platform and belongs to the field of the attitude control and the vibration and shaking control of a spacecraft. (1) an idea of the cube vibration-isolating platform is adopted, the cube vibration-isolating platform is arranged between a configuration consisting of a plurality of control moment gyroscopes and a satellite body and the high frequency vibration caused by a plurality of control moment gyroscopes is isolated to the greatest extent; and (2) by reasonably selecting parameters of the onboard control moment gyroscope group vibration-isolating platform, the problem of effectiveness loss of other onboard systems, which is caused after the vibration-isolating platform is applied on a satellite, is avoided.

Description

technical field [0001] The invention relates to a parameter selection method of an on-board control moment gyroscope group vibration isolation platform, belonging to the fields of spacecraft attitude control and vibration jitter control. Background technique [0002] In recent years, high-precision and high-stability space observation and remote sensing satellites have become the focus of research in the field of aerospace engineering and applications. The optical payload carried on it has extremely strict requirements on the attitude stability and structural vibration level of the spacecraft. At present, this type of spacecraft mostly uses a flywheel or a control moment gyroscope (CMG) as an actuator to achieve attitude control. However, due to factors such as the static and dynamic unbalance characteristics of the high-speed rotor of this type of actuator and the design defects of the bearing, they have become the main source of disturbance on the star. When the vibratio...

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Problems solved by technology

For CMG, it is mostly to improve the performance of a single unit by using a vibration isolation strut or a damper (Bennett V O, Wilson G W. Isolation Flexure For Gyroscopes[P].United States Patent: 4242917, 1981-01-06 ; Smith D W, Davis T S.Methods and apparatus for tuned axial damping in rotating machinery with floating dearing cartridge[P].United States Patent: 2005 / 0268735 A1, 2005-10-08; Harrell J P.Control Moment Gyro With Vibration Isolation[P].United States Patent: 5820078, 1998-10-13), but this kind of CMG stand-alone performance improvement is limited, and even causes the input cost to be much higher than the return benefit

For CMG, a vibration isolation platform can also be used for vibration isolation, but because the moment it provides always changes in a plane, and multiple CMGs are always installed in a certain position according to a certain configuration on the star, and then use such as The separate vibration isolation method of the flywheel will increase the difficulty of the work, and due to the large size of the CMG, the separate vibration isolation of the CMG will easily lead to waste of satellite space

[0004] In addition, for the parameter design of the vibration isolation platform, many studies focus on the special design of certain parameters of the vibration isolation platform to achieve the effect of the vibration isolation platform on vibration isolation, and do not analyze the vibration isolation when it is installed on a certain part of the star. impact on the satellite as a whole or on other systems on some components

In this way, the use of the vibration isolation platform will be hindered, and even the vibration isolation platform itself has excellent characteristics, but after being used on the satellite, other systems will fail.

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