Relative position control of a two-satellite formation using the SDRE control method

Date

2014-01-01

Author

Gomroki, Mohammad Mehdi
Tekinalp, Ozan

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The relative position and formation attitude control of a two-spacecraft utilizing coulomb forces as well as thrusters is addressed. The nonlinear control is realized through state dependent Riccati equation (SDRE) control method. To this end the equations of motion of the formation is properly manipulated to obtain a suitable form for SDRE control. The state-dependent coefficient (SDC) form is then formulated to include the non-linearities in the relative dynamics. The effectiveness of the controllers is demonstrated through simulations.

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=84940755046&origin=inward
https://hdl.handle.net/11511/106676

Conference Name

24th AAS/AIAA Space Flight Mechanics Meeting, 2014

Collections

Department of Aerospace Engineering, Conference / Seminar

Citation Formats

M. M. Gomroki and O. Tekinalp, “Relative position control of a two-satellite formation using the SDRE control method,” Mexico, Amerika Birleşik Devletleri, 2014, vol. 152, Accessed: 00, 2023. [Online]. Available: https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=84940755046&origin=inward.