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| Content Provider | Springer Nature Link |
|---|---|
| Author | Gonseth, Stephan Rudolf, Felix Eichenberger, Christoph Durrant, Dick Airey, Phil |
| Copyright Year | 2015 |
| Abstract | In the framework of the demonstration of European capabilities for future space exploration mission, a high-performance miniaturized MEMS accelerometer detector is developed by Colibrys for incorporation into a compact inertial measurement unit (IMU). The envisaged missions where a miniaturized IMU is under development by SEA should cover: Aerobraking; Entry, descent, and landing (EDL); and Planetary rovers navigation. The accelerometer specifications were defined through an ESA study by providing accelerometer component as well as system level requirements for most future planetary application. Based on these needs, the feasibility of a MEMS, high accuracy, low power and miniaturized accelerometer has been successfully demonstrated with an available sensor designed for the aerospace market. The development toward TRL5 of a RadHard MEMS accelerometer is led by Colibrys, and will be made available on the open market for incorporation into IMU and standalone one and three axis accelerometer devices. This activity covers the development of the radiation hardened ASIC managed by our partner HMT, the design of a fully hermetic ceramic package and a full characterisation test of the accelerometer component. The key parameters are Analogue outputs (acceleration and temperature), 2 independent accelerometers (±1, ±20 g) in the same package, White noise: 5 µg/√Hz (1 g sensor), Power supply 3.3 V/power consumption per channel: 10 mW, Non-linearity: 0.5 %/bandwidth: DC to min 50 Hz and 50 krad radiation tolerance This paper presents the accelerometer performance, lifetime, and environmental requirements. The on-going accelerometer component design and technology will be presented as well as the planned accelerometer testing. The results of a preliminary radiation test single event effects (SEE) and total ionizing dose (TID) performed on a test chip ASIC will be discussed, and the select ASIC architecture with digital redundancy will be shown. |
| Starting Page | 263 |
| Ending Page | 270 |
| Page Count | 8 |
| File Format | |
| ISSN | 18682502 |
| Journal | CEAS Space Journal |
| Volume Number | 7 |
| Issue Number | 2 |
| e-ISSN | 18682510 |
| Language | English |
| Publisher | Springer Vienna |
| Publisher Date | 2015-05-06 |
| Publisher Institution | Council of European Aerospace Societies |
| Publisher Place | Vienna |
| Access Restriction | One Nation One Subscription (ONOS) |
| Subject Keyword | MEMS Accelerometer Inertial measurement unit (IMU) Navigation Entry, descent and landing (EDL) Aerospace Technology and Astronautics |
| Content Type | Text |
| Resource Type | Article |
| Subject | Aerospace Engineering Space and Planetary Science |
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