A platform for research: civil engineering, architecture and urbanism
A platform for research: civil engineering, architecture and urbanism
E-design and manufacturing approach for Cubesat solar panel deployment mechanism
The Cube Satellites short named as CubeSat, have received significant attention. Most essentially, advanced CubeSat missions have been developed and demonstrated thus the CubeSat has very quickly become the key for future space industry. However, one of the main Cubesat constraints is the on-board electrical subsystem, which needs to have better increased value of the available power. This paper describes the design and manufacturing process of a standard deployable solar panel system, which can be used on-single board (1U), double (2U) and triple (3U) Cubesat. The system developed is the basis for an active approach, which will allow better control for maneuvering capability, comparing different deployment concepts and architectures. We have realized a prototype of the system for a 1U Cubesat, based on MEMS technologies highlighting the active method for deployment mechanisms. Additionally, an experimental investigation of the proposed solution based on an online design and manufacturing process has been proven. Also, we have fabricated and tested a demonstration model of a printed circuit board using 3D software, achieved the functionality of the mechanism under various test conditions and verified the structural safety of the proposed solution in a launch vibration environment through sinus and random vibration tests at the qualification level.
E-design and manufacturing approach for Cubesat solar panel deployment mechanism
The Cube Satellites short named as CubeSat, have received significant attention. Most essentially, advanced CubeSat missions have been developed and demonstrated thus the CubeSat has very quickly become the key for future space industry. However, one of the main Cubesat constraints is the on-board electrical subsystem, which needs to have better increased value of the available power. This paper describes the design and manufacturing process of a standard deployable solar panel system, which can be used on-single board (1U), double (2U) and triple (3U) Cubesat. The system developed is the basis for an active approach, which will allow better control for maneuvering capability, comparing different deployment concepts and architectures. We have realized a prototype of the system for a 1U Cubesat, based on MEMS technologies highlighting the active method for deployment mechanisms. Additionally, an experimental investigation of the proposed solution based on an online design and manufacturing process has been proven. Also, we have fabricated and tested a demonstration model of a printed circuit board using 3D software, achieved the functionality of the mechanism under various test conditions and verified the structural safety of the proposed solution in a launch vibration environment through sinus and random vibration tests at the qualification level.
E-design and manufacturing approach for Cubesat solar panel deployment mechanism
Int J Interact Des Manuf
Zafrane, Mohammed Amine (author) / Bouchahma, Abdelghafour Azzouz (author) / Abes, Bachir (author) / Zafrane, Bachir (author) / Freh Bengabou, Mokhtar (author)
2022-12-01
16 pages
Article (Journal)
Electronic Resource
English
Cubesat , Online design and manufacturing , Software aided design , Deployment system , Commercial off-the-shelf and microelectromechanical systems components , Numerical analysis Engineering , Engineering, general , Engineering Design , Mechanical Engineering , Computer-Aided Engineering (CAD, CAE) and Design , Electronics and Microelectronics, Instrumentation , Industrial Design
Flight Software Design and Implementation for a CubeSat
| IEEE | 2023
Payload challenges for CubeSat
British Library Online Contents | 2010