Attitude guidance is a concept for implementing performance enhancing rotational maneuvers that uses a conventional closed-loop attitude control system to track an optimized maneuver trajectory. Minimum-time attitude guidance is presently being used for executing fast occultation avoidance maneuvers on NASA’s Lunar Reconnaissance Orbiter (LRO). A challenge in operationalizing the idea is related to the limited size of the spacecraft’s command buffer, which was not designed with maneuver tracking in mind. In this paper, we propose an interpolating pre-filter built on B-splines that can be used on board to process downsampled maneuver commands (to save buffer space) and provide attitude control inputs at the servo-rate. The approach is validated using a high-fidelity simulation of the LRO developed at NASA’s Goddard Space Flight Center.
KarpenkoMPolyardTAudoV, et al.Attitude guidance: reducing the cost of rotating from ‘A’ to ‘B’. In: 44th Annual AAS Guidance, Navigation And Control Conference, February 4–9, 2022, Breckenridge, CO. Paper number: AAS 22-056.
2.
WieB. Space vehicle dynamics and control. Reston, VA: AIAA, 1998.
3.
SidiMJ. Spacecraft dynamics and control: a practical engineering approach. New York: Cambridge University Press, 2000.
4.
MarkleyFLCrassidisJL. Fundamentals of spacecraft attitude determination and control. New York, NY: Springer, 2013.
5.
LeveFAHamiltonBJPeckMA. Spacecraft momentum control systems. New York, NY: Springer, 2015.
6.
LiuCYueXShiK, et al.Spacecraft attitude control: a linear matrix inequality approach. Cambridge, MA: Elsevier, 2022.
7.
BedrossianNBhattSKangW, et al.Zero-propellant maneuver guidance. IEEE Control Systems Magazine, 2009, pp. 53–73.
8.
KarpenkoMBhattSBedrossianN, et al.Flight implementation of shortest-time maneuvers for imaging satellites. Journal of Guidance, Control and Dynamics2014; 37(4): 1069–1079.
9.
FlemingASekhavatPRossIM. Minimum-time reorientation of a rigid body. Journal of Guidance, Control, and Dynamics2010; 33(1): 160–170.
KarpenkoMRossIMStonekingE, et al.A micro-slew concept for precision pointing of the kepler spacecraft. In: AAS/AIAA Astrodynamics Specialist Conference. Vail, CO, 2015. Paper number: AAS-15-628.
13.
RossIMLeeDKarpenkoM, Method and apparatus for contingency guidance of a CMG-actuated spacecraft, US Patent2015; 9.
HalversonJHsuOCalhounP, et al.Testing of the lunar reconnaissance orbiter attitude control system Re-design without a gyro. In: 42nd Annual AAS Guidance and Control Conference, January 31 to February 6, 2019, Breckenridge, CO. Paper number: AAS 19-108.
16.
WuY-HHuY-BHuaB, et al.A time suboptimal method for real-time spacecraft attitude agile maneuvering with angular velocity constraint. Proc Institution of Mech Eng Part G: Journal Aerospace Engineering2019; 233(2): 561–572.
17.
LeeUMesbahiM. Feedback control for spacecraft reorientation under attitude constraints via convex potentials. IEEE Transactions on Aerospace and Electronic Systems2014; 50(4): 2578–2592.
18.
HuQLiuYDongH, et al.Saturated attitude control for rigid spacecraft under attitude constraints. Journal of Guidance, Control, and Dynamics2020; 43(4): 790–805.
19.
AudoVMKarpenkoMWadeBM. Encoding optimal attitude control solutions with long-short term memory neural networks. In: AAS/AIAA astrodynamics specialist conference. South Lake Tahoe, CA, 2020. Paper number: AAS 20-576.
20.
KarpenkoMHalversonJKBesserR. Waypoint following dynamics of a quaternion error feedback attitude control system. Proc Institution of Mech Eng Part G: Journal Aerospace Engineering2022; 236(2): 281–293.
UnserM. Splines: a perfect fit for signal and image processing. IEEE Signal Processing Magazine. 1999: 22–38.
23.
LouembetCCazaurangFZolghadriA, et al.Path planning for satellite slew manoeuvres: a combined flatness and collocation-based approach. IET Control Theory and Applications2009; 3(4): 481–491.
24.
SanchezJCGavilanFVazquezR, et al.A flatness-based predictive controller for six-degrees of freedom spacecraft rendezvous. Acta Astronautica2020; 167: 391–403.
25.
CalaonRSchaubH. Constrained attitude maneuvering via modified Rodrigues parameters based motion planning algorithms. Journal of Spacecraft and Rockets2022; 59(4): 1342–1356.
26.
HogenauerEB. An economical class of digital filters for decimation and interpolation. IEEE Transactions on Acoustics, Speech and Signal Processing1984; 29(2): 155–161.
27.
FrerkingM. Digital signal processing in communication systems. Boston: Kluwer Academic Publishers, 1994.
28.
CalhounPCGarrickJC. Observing mode attitude controller for the lunar reconnaissance orbiter. In: 20th international Symposium on space flight dynamics, Annapolis, MD, 2007.
29.
KarpenkoMBarkerMKHalversonJK. Multi-leg occultation avoidance maneuvers for the lunar reconnaissance orbiter. In: 2020 AAS/AIAA astrodynamics specialist conference, 2020. South Lake Tahoe, CA. Paper number: AAS 20-574.
30.
RossIM. Enhancements to the DIDO optimal control toolbox, 2020. arXiv preprint arXiv:2004.13112.
31.
BergerRDennisAEckhardtD, et al.RAD750 SpaceWire-enabled flight computer for lunar reconnaissance orbiter. In: International Spacewire Conference, 2007. Scotland, UK: Dundee.
32.
FranklinGFPowellJDWorkmanML. Digital control of dynamic systems. 3rd ed.Menlo Park, CA: Addison Wesley Longman Inc., 1998.
33.
VaidyanathanPP. Multirate systems and filter banks. Prentice Hall, 1993.
34.
HarrisFJ. Multirate signal processing for communication systems. Upper Saddle River, NJ: Prentice Hall Professional Technical Reference, 2004.
35.
SmithJO. Introduction to digital filters with audio applications”. W3K Publishing, 2007.
36.
OgataK. Discrete-time control systems. 2nd ed.Upper Saddle River, NJ: Prentice-Hall, 1995.
