Cubic satellite mass moment bi-symmetrical layout attitude control device

Abstract

The invention discloses a cubic satellite mass moment bi-symmetrical layout attitude control device, include control module, Kinematic mechanism and fixture, A control module includes a system control board and a motor drive board, Four motor drive panels are secured to the system control panel, A linear motor is connected with that flexible wire, Four linear motors are arranged in parallel and vertically symmetrically, the linear motor and the counterweight block constitute a motion mechanism, the fixing device limits the freedom of the motion mechanism, and the linear motor shaft is fixed,the linear motor can be translated freely in the guide rail slot, and the fixing device and the control module determine the relative position relationship through four-corner through holes and studs.The cubic satellite mass moment bi-symmetrical layout attitude control device uses the double symmetrical counterweight block layout mode, reduces the occupied space of the device, simplifies the kinematics and dynamics model of the satellite, and realizes the effective control of the actuator.

Description

technical field [0001] The invention belongs to the field of attitude control of spacecraft, and in particular relates to an attitude control device for a cubic star mass-moment double-symmetrical layout. Background technique [0002] With the continuous development of aerospace technology, the number of spacecraft launched by various countries is increasing. However, the current orbital maneuverability of the CubeSat platform is slightly insufficient compared with other platform technologies such as attitude control and communication. It is currently suitable for CubeSat orbital maneuvering missions. The propulsion system mainly includes cold air propulsion, liquid propulsion, solid propulsion, electric propulsion and solar sail propulsion. Among them, solid propulsion is more suitable for CubeSat platforms with small volume and power consumption due to its advantages of high density impulse, small volume occupied in the star, simple structure, short working time, and relia...

AI Technical Summary

Problems solved by technology

[0008] The object of the present invention is to provide a cubesat mass moment double symmetric layout attitude control device, which is suitable for the attitude control of the cubesat during the orbital maneuvering solid propulsion process, and can not only solve the problem that there is a large thrust when using a solid thruster to change orbit The eccentric moment causes the problem of satellite attitude flipping, and also solves the problem of mutual interference of motion encountered by two linear motors installed vertically and symmetrically in the same plane

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