Cubic satellite mass moment bi-symmetrical layout attitude control device

A control device, moment attitude technology, applied in the field of CubeSat mass moment double symmetrical layout attitude control device, can solve the problems of mutual interference of motion, thrust eccentric moment satellite attitude flip, etc., to achieve effective control, improve function density, reduce restrictions Effect

Inactive Publication Date: 2018-12-25
NANJING UNIV OF SCI & TECH
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  • Abstract
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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 t...

Method used

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  • Cubic satellite mass moment bi-symmetrical layout attitude control device
  • Cubic satellite mass moment bi-symmetrical layout attitude control device
  • Cubic satellite mass moment bi-symmetrical layout attitude control device

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Embodiment Construction

[0028] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0029] combine figure 1 , figure 2 and Figure 6 , a cube star dual symmetric mass moment attitude control device, its main part occupies a space of 100mm × 100mm × 40mm, through the four corner through holes and studs to realize the position of the mass moment device inside the cube star.

[0030] The cubic star mass moment attitude control device includes a control module 1, a motion mechanism 2 and a fixing device 3, the moving mechanism 2 is fixed on the top surface of the fixing device 3, the control module 1 is fixed directly above the fixing device, and the control module 1 is located at Directly above the kinematic mechanism 2.

[0031] combine image 3 , the control module 1 includes a system control board 5, 4 motor drive boards 4 and 4 linear motor connectors 20, and the 4 motor drive boards 4 are arranged on the top surface of the system cont...

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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...

Claims

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Application Information

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IPC IPC(8): B64G1/10B64G1/24G06F17/50
CPCB64G1/10B64G1/24G06F30/15B64G1/245
Inventor 陆正亮胡远东钱鹏俊查杨生马海宁张晓华
Owner NANJING UNIV OF SCI & TECH
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