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Meeting Number:   30

April 3, 2013


Topic

Autonomous Determination of Relative Attitude and Speed of Spacecraft About an Asteroid


Speaker

Dr. Brian Sequeira
Johns Hopkins University Applied Physics Laboratory


Date

Wednesday, April 3, 2013


Time

6:30 PM:   Snacks
7:00 PM:   Talk begins


Location

National Electronics Museum (NEM)
1745 W. Nursery Road, Linthicum, MD 21090
410-765-0230
http://www.nationalelectronicsmuseum.org


Registration

https://meetings.vtools.ieee.org/meeting_view/list_meeting/17431

To register for this meeting, go to the above link. Click on the ‘Click Here to Register’ button. You need to fill in the following information: Name, Member Number (if IEEE member), City, Country, State/Province, E-mail Address. After you fill in the information, click on the ‘Register’ button to register.


Please Respond To

ronald_aloysius@ieee.org

Please respond to ronald_aloysius@ieee.org if you are planning to join us afterwards for dinner so I can make reservations. Only the speaker’s dinner is paid for. The rest of us need to pay our own way.


Abstract

The path of a probe around a small irregularly-shaped body is difficult to predict. The irregular distribution of mass of the body, and its rotational motion, produce a gravitational force on the probe that is non-central and time-varying. Other forces, such as solar pressure, are comparable with the weak gravitational force caused by the body. Therefore, the probe trajectory is non-planar, may not close on itself, is not periodic, and is very sensitive to initial conditions (prevalent at time of "orbit" insertion). The definition and maintenance of spacecraft attitude is confounded by the irregular shape of the object and trajectory alike. Nadir may not be uniquely the shortest distance to the body's surface nor the local normal to the surface. And yet, the spatial context is crucial for the probe's suite of instruments. In order to schedule spacecraft observations, mission planners ordinarily need to know spacecraft locations and attitudes several days in advance. Clearly, such planning is not feasible for probe trajectories around small irregularly shaped bodies. The planners' job will be greatly simplified if the spacecraft can, in real time, establish nadir, measure probe vector velocity relative to the body, and accurately determine probe altitude along the nadir. This talk will present one instrument that can accomplish these objectives.


Biography

H. Brian Sequeira (Senior Member, IEEE) is a Principal Professional Staff member of the Johns Hopkins University Applied Physics Laboratory. His research interests include communications systems for near-Earth and deep space applications, and radar instruments for planetary exploration. Most recently, he was involved with mini-RF Synthetic Aperture Radar instruments that flew on the Chandrayaan-1 and Lunar Reconnaissance Orbiter (LRO) missions. He received the M.S. degree in physics, M.Tech. degree in Engineering Physics, and the Ph.D. degree in electrical engineering.



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