The 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 Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall bo subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number.

No abstract

Space vehicle programs consistently endeavor to reduce satellite bus mass to increase payload capacity and/or reduce launch and fabrication costs. At the same time, performance demands on satellite systems continue to increase, creating a formidable challenge to space vehicle technology development. Flywheelbased systems providing both energy storage and attitude control functionality address both of these issues. In particular, the Flywheel Attitude Control, Energy Transmission and Storage (FACETS) system should combine all or part of the enerby storage, attitude control, and power management and distribution

Public reporting burden Tor this collection ot ntormation is estimated to average 1 hour per response, including the time tor reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the colection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302, and The recent advent of miniature single gimbal control moment gyroscopes has spawned interest in variable speed versions for combined energy storage and attitude control systems on small satellites. Although much has been studied on the theory behind such a system, little has been done in optimally sizing these actuators for small satellite applications. Therefore, this paper investigates the fundamental design concepts, optimal sizing, and mission benefits for these actuators. Given a set of small satellite agility and energy storage requirements, an optimal, nonlinear programming method is applied to this problem.

This paper describes the Variable Speed Control Moment Gyroscope (VSCMG) Workbench, a simulation software tool developed at Georgia Tech. This program will provide the Air Force Research Laboratory (AFRL) with a tool for studying spacecraft control system design for vehicles equipped with VSCMG actuators for combined attitude control and energy storage.