CALIBRATION RESULTS OF A NOVEL MICRO SUN SENSOR FOR NANOSATELLITE ATTITUDE DETERMINATION
- Paper number
IAC-08.C1.8.8
- Author
Prof. Michele Grassi, University of Naples "Federico II", Italy
- Coauthor
Dr. Giancarlo Rufino, University of Naples "Federico II", Italy
- Coauthor
Mr. Danilo Rolfi, University of Naples, Italy
- Year
2008
- Abstract
Micro-technology is an enabling technology for future space programs [1]. Among the relevant applications, the development of micro-accelerometers, micro-gyros, and CMOS-based electro optical sensors for accurate navigation and attitude determination is one of the most challenging one, coexisting the demanding requirement of autonomy for aerospace GN&C systems. Autonomy can be achieved also by fusion of several sensors’ output. In this view, micro /nano technology is very promising allowing the development of compact and miniaturized systems. In the miniaturization of electro optical sensors, the Active Pixel Sensor technology is playing a dominant role since it allows integrating detector and electronics into a single chip. Latest generation star trackers and sun sensors adopting such components are being studied and developed [2,3]. In this framework, the research team at the university of Naples is developing a digital sun sensor based on CMOS technology and COTS components. The sensor flight module is being developed as part of a program sponsored by the Italian Space Agency to fly a number of technological payloads on board the first Italian microsatellite standard platform, scheduled for flight in 2011. In order to validate the sensor concept a laboratory prototype and a test facility have been developed. One of the main goal of the test campaign is validating the sensor performance improvement produced by an innovative design of the sensor optical head, allowing simultaneous multiple measurements of the sun line. Specifically, the sensor exploits sun images on the focal plane and neural networks to produce sun line measurements with high accuracy and precision. Precision is drastically improved by processing multiple sun images produced with a multi-hole mask. The paper describes the sensor prototype as well as the adaptive calibration procedure and algorithm conceived to exploit a variable number of sun images for sun line determination. Preliminary laboratory results show that the sensor can offer accuracy and precision of 1 arcminute and 1 arcsec., respectively. References: 1. Dreischer T., Advanced miniature optical terminals for inter-satellite links in spacecraft constellations, Proc. Of the 2nd Round Table on Micro/Nanotechnology for Space, ESTEC, The Netherlands, 1997 2. Hales J. H., and Pedersen M., Two-axes MOEMS Sun Sensor for Pico Satellites, Proc. 16th Annual AIAAA/USU Conf. on Small Satellites, Logan, USA, 2002 3. Liebe C.C., Alkalay L., Domingo G., Hancock B., Hunter D., Mellestrom J., Ruiz I., Sepulveda C., and Pain B., Micro APS Based Star Tracker, Proc. 5th IEEE AeroConf, Big Sky, USA, 2002
- Abstract document
- Manuscript document
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