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Meeting	ACGS Committee Meeting 108 - Gettysburg - October 2011
Agenda Location	11 SUBCOMMITTEE E – FLIGHT, PROPULSION, AND AUTONOMOUS VEHICLE CONTROL SYSTEMS 11.3 Integrated Adaptive Guidance and Control for Future Responsive Access to Space Technology
Title	Integrated Adaptive Guidance and Control for Future Responsive Access to Space Technology Best Presentation Award
Presenter	Dale F. Enns
Affiliation	Honeywell Systems Research Center
Available Downloads*	presentation
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Abstract	Integrated Adaptive Guidance and Control for Future Responsive Access to Space Technology Dale Enns, Steve Pratt, Darryl Busch, Raj Bharadwaj Honeywell Aerospace (dale.enns@honeywell.com) Mike Oppenheimer Air Force Research Laboratory Honeywell is developing an autonomous guidance and control system for a reusable launch vehicle under the Air Force Research Laboratory’s Future-responsive Access to Space Technology (FAST) Contract FA865008-D07803. The autonomous guidance and control system provides aerodynamic surface, reaction control system, propulsion throttle and thrust vectoring commands to perform the complete mission. The mission and guidance and control system have been parameterized such that the results can be easily applied to different missions and vehicle performance, and to facilitate recovery in the event of a failure. The guidance and control system is integrated with a Health Management system that provides information about failed or degraded actuation and propulsion components. We discuss results obtained from a nonlinear simulation of a 6 degree-of-freedom model of the launch vehicle. The vehicle takes off vertically, flies out of the atmosphere, performs staging, rockets back, descends, and lands horizontally near the launch site. We consider different nominal missions and off nominal conditions such as single engine failures and autonomous reconfiguration of the healthy engines to complete the mission. The autonomous responses include selecting new timing sequences for engine throttling, and on-board trajectory re-planning. We postulate failures of actuation devices of various kinds, e.g. stuck, floating as well as engine failures at different time points throughout the trajectory. Our conclusions based on several examples indicate that autonomous guidance and control parameterized for a class of launch vehicles allows a wide range of missions and permits the vehicle to complete its mission after failures have occurred that would otherwise have led to loss of vehicle.