Survey of Technology Developments in Flywheel Attitude Control and Energy Storage Systems

Lappas, V.; Richie, D.; Hall, Christopher D.; Fausz, Jerry L.; Wilson, Brian C.

doi:10.2514/1.32092

Cited by 52 publications

(21 citation statements)

References 24 publications

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“…Much of the combined flywheel energy storage and attitude control history through the year 2000 is well-documented in a 45-page report by Hall [19] while past, present, and future technology developments and ideas is well addressed in the combined works given in Refs. [20,21]. The reader is referred to these works for more detail.…”

Section: History and Description Of Key Esacs Technologymentioning

confidence: 99%

“…The performance for this wheel was anticipated to have 17 W-hr/kg with an operating speed range of 9500 to 19000 RPM. With a 24 in diameter rotor, tip-speeds of 306 m/s to 612 m/s could be achieved [21]. Disappointingly, Roes' article does not include using these wheels for attitude control.…”

Section: Flywheel Energy Storagementioning

confidence: 99%

“…As mentioned in [20,21], the NASA-sponsored IPACS concepts studies in aforementioned work by Notti and Cormack (ref. [2]) "considered IPACS for seven possible NASA spacecraft/missions and proposed conceptual designs for two of them.…”

Section: Chapter 2 State-of-the Art Reviewmentioning

confidence: 99%

“…As further mentioned in [20,21], two concurrent NASA Langley Research Center studies [33,35,36] presented experimental and simulation results of IPACS concepts for potential NASA missions.…”

Section: Chapter 2 State-of-the Art Reviewmentioning

confidence: 99%

“…The consensus design shifted toward a counter-rotating, magnetically-levitated momentum wheel-based system known as the CARES (Combined Attitude, Reference, and Energy Storage) system anticipated for ISS application. As mentioned in [21], reference [3] identified and prioritized critical technologies as: (1) According to Reference [4], a 1983 US Air Force sponsored study [50] concluded that flywheel energy storage for spacecraft was not advantageous. Since none of the studies discussed involved actual hardware or missions, their conclusions depend on initial assumptions including wheel geometry, material strength, various efficiencies, and mission characteristics.…”

Section: Chapter 2 State-of-the Art Reviewmentioning

confidence: 99%

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Combines Attitude Control and Energy Storage for Small Satellites using Variable Speed Control Moment Gyroscopes

Lappas¹

2008

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information SPONSOR/MONITOR'S ACRONYM(S) 9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)EOARD Unit 4515 BOX 14 APO AE 09421 SPONSOR/MONITOR'S REPORT NUMBER(S)Grant 05-3037 DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTThis report results from a contract tasking University of Surrey as follows: The Grantee will investigate three areas concerning energy storage and attitude control systems (ESACS) for small satellites: a.) Use of small satellite reference models to determine the relative scales for a combined variable speed control moment gyroscope (VSCMG) energy storage (ES) system. b.) Explore potential imbalances, derive mathematical descriptions of ESACS-imbalance systems and model the ESACS system in MATLAB/Simulink.. c.) Construct experimental hardware for power conversion demonstration: An experimental VSCMG system will be used to demonstrate combined attitude control and energy storage. The imbalances modeled in (b.) will be replicated in the experimental hardware. Derived control solutions to the imbalance problem will be implemented and validated in the experimental hardware. SUBJECT TERMS Government DisclaimerThe views expressed in this article are those of the authors and do not reflect the official policy or position of the United States Air Force, Department of Defense, or the U.S. Government. AcknowledgementsThe ii Summary This work presents the first known energy storage and attitude control subsystem (ESACS) for small satellites, proving this technology to be viable, applicable to more complex, demanding space missions, and laden with substantial benefits, such as agile slewing, robust singularity avoidance, increased lifetime, mass savings, and favourable peak power density. In capturing the key features of this novel system, it investigates the design sizing, feasibility, mission utility, experimentation, and performance benefits for using variable-speed control moment gyroscopes (VSCMGs) to store and drain energy while controlling satellite orientation.First, a novel optimal ESACS sizing algorithm is developed for a practical, miniature spotlight synthetic aperture RADAR (SAR) space mission. When given a set of small satellite agility and energy storage requirements, the design is cast as a constrained nonlinear programming problem using a performance index constructed from subsystem design margins including the attitude torque, peak power, energy capacity, and subsystem mass margins and solved using a reduced-o...

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Section: History and Description Of Key Esacs Technologymentioning

confidence: 99%

Section: Flywheel Energy Storagementioning

confidence: 99%