1. 3-D Dynamics of a Satellite with Flexible Elements By Abdullah Ahmed Alhumaidan 422004549

2. Overview ● Project Objectives ● Introduction ● Case Studies ● CASE STUDY - 1

3. Project Objectives ■ 3D satellite dynamics. ■ Study the motion of satellite struck by a space meteorite ■ The stresses developed at the base of a flexible antenna. ■ Mathematical modeling and analysis of a vibration absorber fixed to a satellite

4. Introduction ● L.E.O (Low Earth Orbit) micro satellites (since 1957). ● Small satellites (less than 1,000 kg ) ● microsatellite (less than 100 kg ) ● nanosatellites (less than 10 kg) ● picosatellites (less than 1 kg)

5. The Flexible Antenna ● Function ● ( s-band,c-band, x-band, ku – band )

6. The micro-vibration of the satellite

7. Case Studies ● A satellite with a flexible antenna. ● A satellite with rigid antenna. ● Satellite with single axis vibration absorber

8. A satellite with a flexible antenna

9. A satellite with rigid antenna

10. Satellite with single axis vibration absorber

11. CASE STUDY - 1

12. Development of The Equation of Motion

13. Time response of the antenna

14. The influence of satellite spin rate on the max. vibration amplitude Өmax.

15. The influence of satellite spin rate on the response frequency of the antenna model

16. the influence of satellite spin rate on the max. moment on a boom at point A

17. Design of the antenna base

19. Stresses

20. The base dimensions based on Max. Shear stress theory Factor of Safety=1.5 σy=400MPa

21. Work to be completed ● For the flexible antenna case study, the influence of changing precession and spin rates of the satellite on the antenna support design will be investigated. ● The effect of meteorite velocity and direction on the satellite attitude will be studied. ● For the rigid antenna case, the maximum stress developed at the antenna base will be calculated for several meteorite velocities and directions. ● The dynamic response of the absorber attached to the satellite which is aligned in x-direction as shown in figure ( 6) will be evaluated for several values of satellite spin and precession rates.

22. THANK YOU