Abstract
Attitude maneuvers are required for reorienting the satellite for meeting various mission objectives. A higher satellite slew rate during maneuvers is a desirable characteristic for any mission design. At the same time, a higher slew rate demands a higher actuator torque capacity which is always constrained due to the physical limits of the actuator. This paper discusses the satellite attitude maneuver problem under slew rate and actuator capacity constraints. A quaternion feedback controller with quaternion and angular rate feedback is implemented to achieve a rest to rest reorientation maneuver. The control gains are computed based on the slew rate limits while the control commands incorporate the actuator limits. Three different configurations of four reaction wheels, (a) pyramid configuration, (b) skew configuration with three wheels along the body axes and the fourth wheel along body diagonal and (c) skew configuration with skew angle of 45°, are studied. The paper further discusses single reaction wheel failure conditions for all the three configurations and demonstrates satellite rest to rest maneuver within the slew rate and actuator limits.
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References
Sidi MJ (1997) Spacecraft dynamics and controls, vol 1, no 7. Cambridge University Press, Cambridge, UK, pp 152–208
Boskovic JD, Li S-M, Mehra RK (2001) Robust adaptive variable structure control of spacecraft under control input saturation. J Guid Control Dyn 24:14–22
Lin T, Shinje XU (2012) Attitude control considering variable input saturation limit for a spacecraft equipped with flywheels. Chin J Aeronaut 25:437–445
Cruz G, Yang X, Weiss A (2011) Torque saturated, inertia free spacecraft attitude control. In: AIAA guidance, navigation and control conference, Portland, Oregon, pp 1–25
Weiss H, Wie B, Araposthathis A (1989) Quaternion feedback regulator for spacecraft eigenaxis rotations. J Guidance 12(3):375–380
Wie B, Lu J (1995) Feedback control logic for spacecraft eigenaxis rotations under slew rate and control constraints. AIAA 18(6):1372–1379
Junkins JL, Turner JD (1986) Optimal spacecraft rotation manoeuvres, vol 3. Elsevier, Amsterdam
Santosh K, Yuvaraj S, Rakshit, Sahay D, Tejaswini GS (2017) Reaction wheel control, testing and failure analysis for STUDSAT-2. IEEE, pp 1–11
Crassidis JL, Markley FL (2014) Fundamentals of spacecraft attitude determination and control. Springer, New York, pp 123–341
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Sahu, A., Mahodaya, A.K., Chokkadi, S. (2020). Slew Rate and Control Constrained Spacecraft Attitude Maneuver with Reaction Wheel Failure. In: Sastry, P.S., CV, J., Raghavamurthy, D., Rao, S.S. (eds) Advances in Small Satellite Technologies. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-15-1724-2_12
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DOI: https://doi.org/10.1007/978-981-15-1724-2_12
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