Redundant single gimbal control moment gyroscope singularity analysis

Bedrossian, Nazareth; Paradiso, Joseph A.; Bergmann, E.; Rowell, Derek

doi:10.2514/3.20584

Cited by 86 publications

(39 citation statements)

References 2 publications

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“…Jacot and Liska (1966), Margulies and Aubrun (1978), and Oh and Vadali (1991), made contributions by capturing the exact nonlinear equations of satellite motion using CMGs, including single-and double-gimbal configurations, gimbal lock singularities, and CMG steering control laws [64][65][66]. Further accomplishments in the late 1980s and early 1990s by Bedrossian, Paradiso, Bergmann, Rowell, Walker, and others described different CMG singularity avoidance methods [67][68][69][70][71]. This work enabled Ford and Hall's efforts, who were the first to investigate the generic nonlinear equations of motion for momentum exchange devices (i.e.…”

Section: Cmgs/vscmgsmentioning

confidence: 99%

“…[76]. The VSCMG development was predicated on the detailed CMG theory offered by Jacot and Liska [64], Marguilles and Aubrun [65], Oh and Vadali [66], Wie [147], and several others [67][68][69]. Following Richie et.…”

Section: Literary Backgroundmentioning

confidence: 99%

“…It shows that for a redundant set of n−VSCMGs (e.g. 4 arranged in a pyramid configuration), a satellite reference attitude profile can be tracked while maintaining a desired power profile [66][67][68][69][70][74][75][76][77].…”

Section: Vscmgs For Energy Storagementioning

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: Cmgs/vscmgsmentioning

confidence: 99%

Section: Literary Backgroundmentioning

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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“…The first category is given by local-gradient methods, 2,3) that rely on null motion. 4) If the CMG cluster has a redundant number of wheels (for example >3) there are null motions that do not affect the total angular momentum and output torque.…”

Section: Introductionmentioning

confidence: 99%

“…This singularity problem has discouraged their use on spacecraft, especially small satellites that do not always require large control torques. Many control methods have been proposed to solve the singularity problem of a SGCMG, [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20] and singular states have been analyzed and visualized. 1) The methods developed so far to tackle the singularity problem of a SGCMG can be divided into three categories.…”

Section: Introductionmentioning

confidence: 99%

Receding Horizon Control on Steering of Control Moment Gyro for Fast Attitude Maneuver

Takada

Kojima

2009

Trans. Japan Soc. Aero. S Sci.

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A Control Moment Gyro (CMG) is a momentum-exchange torque generator. Compared to other momentumexchange torque generators, such as reaction wheels, this device has advantages of high output torques and rapid responses. Despite these advantages, singularities and the nonlinear nature of the steering logic of this device have hampered its application in small spacecraft control. Although there have been many studies of singularity avoidance, in practice, attitude settling times of maneuvers using CMG have been slow when trajectories produced by this control method pass through or near the singularities. In this works, we applied Receding Horizon (RH) control to CMG steering to overcome such problems described and obtain fast attitude maneuver times. This is achieved by choosing the difference between the current attitude and the target attitude as a performance index with which to determine controller gains for this control method. The results of numerical simulations show that our method achieves superior attitude maneuvering times to singularity avoidance steering laws when singularities are encountered.

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Active Attitude Control Mechanisms

Horri

Palmer

Giffen

2010

Encyclopedia of Aerospace Engineering

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This section describes the fundamentals, operating principles, and dynamical modeling of the actuators used for active spacecraft attitude control. Magnetic torquers and thrusters are presented as a way of applying external control torques to a spacecraft to alter both attitude and momentum. Momentum exchange devices, consisting of reaction and momentum wheels and control moment gyros are then presented as means of generating internal control torques for the operational attitude control of a spacecraft. The evolution of space applications is putting increasingly stringent requirements on satellite attitude control performance, thence the increasing importance of attitude control hardware.

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Redundant single gimbal control moment gyroscope singularity analysis

Cited by 86 publications

References 2 publications

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

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

Receding Horizon Control on Steering of Control Moment Gyro for Fast Attitude Maneuver

Active Attitude Control Mechanisms

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