Single Axis Attitude Control and DC Bus Regulation With Two Flywheels PDF Download
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Author:
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ISBN:
Category :
Languages : en
Pages : 13
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 13
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Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721525652
Category :
Languages : en
Pages : 30
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Book Description
A computer simulation of a flywheel energy storage single axis attitude control system is described. The simulation models hardware which will be experimentally tested in the future. This hardware consists of two counter rotating flywheels mounted to an air table. The air table allows one axis of rotational motion. An inertia DC bus coordinator is set forth that allows the two control problems, bus regulation and attitude control, to be separated. Simulation results are presented with a previously derived flywheel bus regulator and a simple PID attitude controller. Kascak, Peter E. and Jansen, Ralph H. and Kenny, Barbara and Dever, Timothy P. Glenn Research Center NASA/TM-2002-211812, NAS 1.15:211812, E-13507, IECEC-2002-20078
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721636761
Category :
Languages : en
Pages : 24
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Book Description
The energy storage and attitude control subsystems of the typical satellite are presently distinct and separate. Energy storage is conventionally provided by batteries, either NiCd or NiH, and active attitude control is accomplished with control moment gyros (CMGs) or reaction wheels. An overall system mass savings can be realized if these two subsystems are combined using multiple flywheels for simultaneous kinetic energy storage and momentum transfer. Several authors have studied the control of the flywheels to accomplish this and have published simulation results showing the feasibility and performance. This paper presents the first experimental results showing combined energy storage and momentum control about a single axis using two flywheels. Kenny, Barbara H. and Jansen, Ralph and Kascak, Peter and Dever, Timothy and Santiago, Walter Glenn Research Center NASA/TM-2004-212935, E-14373, IEEEAC-1261
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721672134
Category :
Languages : en
Pages : 28
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Book Description
The NASA Glenn Research Center (GRC) has been working to advance the technology necessary for a flywheel energy storage system for the past several years. Flywheels offer high efficiency, durability, and near-complete discharge capabilities not produced by typical chemical batteries. These characteristics show flywheels to be an attractive alternative to the more typical energy storage solutions. Flywheels also offer the possibility of combining what are now two separate systems in space applications into one: energy storage, which is currently provided by batteries, and attitude control, which is currently provided by control moment gyroscopes (CMGs) or reaction wheels. To date, NASA Glenn research effort has produced the control algorithms necessary to demonstrate flywheel operation up to a rated speed of 60,000 RPM and the combined operation of two flywheel machines to simultaneously provide energy storage and single axis attitude control. Two position-sensorless algorithms are used to control the motor/generator, one for low (0 to 1200 RPM) speeds and one for high speeds. The algorithm allows the transition from the low speed method to the high speed method, but the transition from the high to low speed method was not originally included. This leads to a limitation in the existing motor/generator control code that does not allow the flywheels to be commanded to zero speed (and back in the negative speed direction) after the initial startup. In a multi-flywheel system providing both energy storage and attitude control to a spacecraft, speed reversal may be necessary. Fehrmann, Elizabeth A. and Kenny, Barbara H. Glenn Research Center NASA/TM-2004-213295, E-14742, AIAA Paper 2004-5602
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781724089625
Category : Science
Languages : en
Pages : 26
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Book Description
Glenn Research Center has completed the redesign of the D1 flywheel module. The redesign includes a new rotor with a composite rim, motor/generator, touchdown bearings, sensors, and a magnetic actuator. The purpose of the relatively low cost module upgrade is to enable it to continuously operate throughout its speed range of 0 to 60,000 RPM. The module will be used as part of a combined attitude control and bus regulation experiment. Jansen, Ralph H. and Wagner, Robert C. and Duffy, Kirsten P. and Hervol, David S. and Storozuk, Ronald J. and Dever, Timothy P. and Anzalone, Salvatore M. and Trudell, Jeffrey J. and Konno, Kevin E. and Kenny, Andrew Glenn Research Center NASA/TM-2002-211788, IECEC-2002-20075, NAS1.15.211788, E-13483
Author: George Meyer
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 60
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Book Description
A general procedure for the design and analysis of three-axis, large-angle attitude control systems has been developed. Properties of three-dimensional rotations are used to formulate a model of such systems. The model is general in that it is based on those properties which are common to all attitude control systems, rather than on special properties of particular components. Numerical values are assigned to attitude error by means of error functions. These functions are used to construct asymptotically stable control laws. The overall (global) behavior of the system is characterized by the envelope of all time histories of attitude error generated by every possible combination of initial condition, target attitude motion, and disturbance. A method for computing upper bounds on the response envelope is presented. Applications of this method indicate that it provides a useful alternative to Liapunov analysis for the determination of system stability, responsiveness, and sensitivity to disturbances, parameter variations, and target attitude motion.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721521906
Category :
Languages : en
Pages : 26
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Book Description
A flywheel system and its operator interface are described. Measurements of magnetic bearing negative stiffness are performed. Two digital magnetic bearing control algorithms (PD and estimator based) are defined and their implementations are described. Tuning of each controller is discussed. Comparison of the two controllers' stability, damping noise, and operating current are described. Results describing the superiority of the estimator-based controller are presented and discussed. Dever, Timothy P. and Brown, Gerald V. and Jansen, Ralph H. Glenn Research Center NASA/TM-2002-211795, NAS 1.15:211795, IECEC-2002-20161, E-13490
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725086142
Category :
Languages : en
Pages : 34
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Book Description
Control Dynamics Company (CDy), in conjunction with NASA Marshall Space Flight Center (MSFC), has supported the U.S. Air Force Wright Aeronautical Laboratory (AFWAL) in conducting an investigation of the implementation of several DOD controls techniques. These techniques are to provide vibration suppression and precise attitude control for flexible space structures. AFWAL issued a contract to Control Dynamics to perform this work under the Active Control Technique Evaluation for Spacecraft (ACES) Program. The High Authority Control/Low Authority Control (HAC/LAC) and Positivity controls techniques, which were cultivated under the DARPA Active Control of Space Structures (ACOSS) Program, were applied to a structural model of the NASA/MSFC Ground Test Facility ACES configuration. The control systems design were accomplished and linear post-analyses of the closed-loop systems are provided. The control system designs take into account effects of sampling and delay in the control computer. Nonlinear simulation runs were used to verify the control system designs and implementations in the facility control computers. Finally, test results are given to verify operations of the control systems in the test facility. Seltzer, S. M. and Irwin, D. and Tollison, D. and Waites, H. B. Marshall Space Flight Center NASA-TM-100338, NAS 1.15:100338 ...
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Navigation (Astronautics)
Languages : en
Pages : 64
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Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725086630
Category :
Languages : en
Pages : 30
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Book Description
Over 39 years and a long list of missions, the guidance, navigation, and control (GN&C) groups at the Goddard Space Flight Center have gradually developed approaches to the design and implementation of successful spacecraft attitude control systems. With the recent creation of the Guidance, Navigation, and Control Center at Goddard, there is a desire to document some of these design practices to help to ensure their consistent application in the future. In this paper, we will discuss the beginnings of this effort, drawing primarily on the experience of one of the past attitude control system (ACS) groups at Goddard (what was formerly known as Code 712, the Guidance, Navigation, and Control Branch). We will discuss the analysis and design methods and criteria used, including guidelines for linear and nonlinear analysis, as well as the use of low- and high-fidelity simulation for system design and verification of performance. Descriptions of typical ACS sensor and actuator hardware will be shown, and typical sensor/actuator suites for a variety of mission types detailed. A description of the software and hardware test effort will be given, along with an attempt to make some qualitative estimates on how much effort is involved. The spacecraft and GN&C subsystem review cycles will be discussed, giving an outline of what design reviews are typically held and .what information should be presented at each stage. Finally, we will point out some of the lessons learned at Goddard. ODonnell, James R., Jr. and Mangus, David J. Goddard Space Flight Center AAS-98-309 ...
