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Cluster type control moment gyroscope vibration isolation method for inhibiting posture adjustment resonance

A control torque gyro, cluster technology, applied in non-rotational vibration suppression, special data processing applications, instruments, etc., can solve problems such as control torque gyro resonance

Active Publication Date: 2021-01-15
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The present invention aims to solve the problem that the vibration displacement generated by the control motor on the current control torque gyroscope and a certain order mode of the control torque gyroscope equipped with a vibration isolator will be coupled, resulting in the resonance of the control torque gyroscope

Method used

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  • Cluster type control moment gyroscope vibration isolation method for inhibiting posture adjustment resonance
  • Cluster type control moment gyroscope vibration isolation method for inhibiting posture adjustment resonance
  • Cluster type control moment gyroscope vibration isolation method for inhibiting posture adjustment resonance

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Embodiment 1

[0056] The present invention provides a cluster control moment gyro vibration isolation method for suppressing attitude adjustment resonance, such as figure 1 Shown, it is characterized in that, described method comprises the following steps:

[0057] Step 1. The bracket is installed on a fixed plane, and multiple control torque gyroscopes are installed on the bracket. According to the connection positions of multiple control torque gyroscopes and the bracket, a clustered control torque gyroscope solid model is constructed, and four vibration isolators are installed on Between the bracket and the fixed plane, a dynamic model is constructed according to the connection positions of the upper fulcrum and the lower fulcrum of the vibration isolator with the bracket and the fixed plane respectively. The damper composition;

[0058] Step 2. Obtain the natural frequency according to the cluster control moment gyroscope entity model and the dynamic model, and obtain the theoretical v...

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Abstract

The invention discloses a cluster type control moment gyroscope vibration isolation method for inhibiting posture adjustment resonance, and relates to the field of vibration isolation. The invention aims to solve the problem of resonance of a control moment gyroscope caused by coupling of vibration displacement generated by a control motor on the existing control moment gyroscope and a certain-order vibration mode of the control moment gyroscope provided with a vibration isolator. The method includes: constructing a cluster type control moment gyro entity model and a kinetic model; obtaining an inherent frequency according to the two models, and obtaining a theoretical value of space coordinates of a lower fulcrum of the vibration isolator according to the inherent frequency; correcting the theoretical value of the space coordinates of the lower supporting point of the vibration isolator to obtain final space coordinates of the lower supporting point of the vibration isolator; obtaining structural parameters of a plurality of springs and dampers according to the final space coordinates of the lower fulcrum of the vibration isolator, and designing a spring model and a damper model;according to the spring model, the damper model and the final damper lower fulcrum space coordinates, adjusting the vibration isolator structure and the connecting positions of the four vibration isolator lower fulcrums and the fixed plane. The method is used for determining the installation position of the vibration isolator.

Description

technical field [0001] The invention relates to the vibration isolation design of a spaceborne control moment gyroscope, in particular to a vibration isolation design of a cluster control moment gyroscope for suppressing attitude adjustment resonance. It belongs to the field of vibration isolation. Background technique [0002] As an important mechanism in satellite attitude control, Control Moment Gyroscopic (CMG) is widely used in large-scale high-performance satellite platforms due to its characteristics of no propellant consumption, high control precision, and fast response speed. However, CMG mainly relies on the rotation of its internal momentum wheel and the reciprocating motion driven by the control motor to complete the specified tasks. Both the momentum wheel and the control motor will generate a large degree of vibration, which will have a negative impact on the satellite's attitude adjustment accuracy. . In view of this phenomenon, by designing a suitable vibra...

Claims

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Application Information

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IPC IPC(8): G06F30/17G06F30/23F16F15/04G06F119/14
CPCF16F15/04G06F30/17G06F30/23G06F2119/14
Inventor 于开平廖宝鹏胡迪科臧旭柳超然赵锐
Owner HARBIN INST OF TECH
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