The Research and Development of a Non-magnetism Deployment for Magnetic Field Instrument (MFI) of Satellite
|關鍵字:||衛星;伸臂;機構;磁場探測儀;共振頻率;展開機構;satellite;boom;mechanism;magnetic field instrument;resonant vibration frequency;deployment mechanism|
This research topic “The Research and Development of a Non-magnetism Deployment for Magnetic Field Instrument (MFI) of Satellite” is related to the first payload mechanism of satellite which is thoroughly researched and developed domestically since space technology burgeons in Taiwan. The research domain comprises functional requirements, specification set-up, mechanism design, fabrication, final testing and certification. Different from foreign magnetic potentiometers which merely provide signals regarding satellite position, the magnetic field Instrument in this research needs to detect weak magnetic field disturbances (small to 0.1nT) in the space. As a result, higher magnetic purity, high rigidity, and high availability should be taken into consideration when developing the mechanism, in order to assure it can meet the functional requirements. The development mechanism comprises several critical components all of which have respective special consideration in design. For instance, in respect of the design of potentiometer, it needs to consider non-magnetism and utilization of dry bearings; with regard to the design of rotation mechanism, Hinge and Damper, it requires non-magnetism, no vacuum leak, no power input, high availability and high rigidity; the design of Boom should be of light material and high intensity; the design of Sensor Frame requires thermal shock resistance, high temperature resistance, electrical insulation and no magnetic conductivity; the design of unlock/lock mechanism adopts the pin-puller with higher intensive locking status in order to resonant vibration frequency of MFI mechanism. If MFI can pass practical tests in the space environment and other functional tests, its key components and design philosophy can be objectively applied to various types of satellite payload mechanisms in the future. Based on the initial model of MFI mechanism developed in this research, the natural frequencies both for the locked and deployed status were 286.939Hz and 41.808Hz respectively. Boom Locked Status could meet the specification requirement of 140Hz. Although the frequency in the deployment status was below the standard of 50Hz, however the specification requirement will be satisfied in the future through changing materials of boom and rotation mechanism. Experience acquired in the research and development of MFI deployment mechanism in this dissertation, can be applied to the future development of the satellite payload system, enchance Taiwan’s satellite related technology, and reduces Taiwan’s dependency on the foreign technical supplies.