Variable speed control moment gyroscopes (VSCMGs) device with pentagonal pyramid configuration

Abstract

The invention provides a variable speed control moment gyroscopes (VSCMGs) device with a pentagonal pyramid configuration, and belongs to the technical field of space flight and aviation. The device is characterized by comprising a pentagonal protective shell mechanism and five identical variable speed control moment gyroscope devices, wherein the pentagonal protective shell mechanism comprises abase, a bearing shell and a top cover; and the variable speed control moment gyroscope devices comprise gyroscope frame systems, frame supporting and driving systems and pentagonal fixing parts, wherein the gyroscope frame systems are fixedly connected with an external supporting seat system, the frame supporting and driving systems are fixedly connected with the base in the pentagonal protectiveshell mechanism, and the pentagonal fixing parts are fixedly connected with the frame supporting and driving systems. According to the variable speed control moment gyroscopes (VSCMGs) device with thepentagonal pyramid configuration, the included angle between rotating shafts of the gyroscope frame systems and the horizontal plane is 63.49 degrees, and the device can be used for carrying out input simulation verification on a kinetic equation of modeled gyroscopes with the pentagonal pyramid configuration and can also be used for carrying out an attitude control experiment.

Description

technical field [0001] The invention relates to the field of aerospace technology, and specifically proposes a variable speed control moment gyro group (VSCMGs) device in a pentagonal pyramid configuration. Background technique [0002] The Control Moment Gyro (CMG) can not only generate a large control moment, but also achieve high-precision attitude control without consuming non-renewable working fluid. It is an ideal actuator for spacecraft attitude control. Single frame control moment gyroscope (SGCMG) has become the best choice for sensitive small spacecraft attitude control actuator because it only generates control moment of one degree of freedom, simple structure, large output torque and good dynamic response. In traditional research, the frame shaft of SGCMG is fixedly connected to the star body, and the change of the angular momentum direction of the rotor can only depend on the rotation of the frame around the frame shaft, so as to achieve the purpose of torque ou...

AI Technical Summary

Problems solved by technology

At the same time, the main disadvantage of SGCMGs in application is the singularity problem. When the torque output directions of all SGCMGs are coplanar or collinear, SGCMGs cannot output the control torque on the plane or the normal direction of the line, and SGCMGs are in a singular state at this time; Therefore, the most important basic problem facing the design of single-frame moment gyroscopes is to solve the singular problem of controlling the moment gyroscopes

Images