Aerospace Control and Guidance Systems Committee

Announcements

You must first log in to access prior meeting presentations, register for a meeting, or nominate some for the Ward Award.

If you do not have a login account, or cannot remember the email address associated with your account, please click on the Application Form link below.

Login

Site Search

Search our site:

Upcoming Events

Photos

Meeting Highlights New!

Subcommittee S

Prior Meetings

Abstracts may be viewed by anyone. Presentations are only available to active members who have logged in.

Meeting 133
(coming soon)

Meeting 132
(coming soon)

Home

Ward Memorial Award

Planning Advisory Board

Downloads

Constitution and By-Laws

About

History

Contact Us

← Return to agenda

Meeting	ACGS Committee Meeting 93 - Colorado Springs - March 2004
Agenda Location	9 SUBCOMMITTEE E – FLIGHT AND PROPULSION CONTROL SYSTEMS 9.4 Integrated Adaptive Guidance and Control for Reusable Launch Vehicles: Flight Test Results
Title	Integrated Adaptive Guidance and Control for Reusable Launch Vehicles: Flight Test Results
Presenter	John Schierman and David Ward
Affiliation	Barron Associates
Available Downloads*	presentation
	Downloads are available to members who are logged in and either Active* or attended this meeting.
Abstract	For next generation Reusable Launch Vehicles (RLVs), reconfigurable control, adaptive guidance, and on-line trajectory-command reshaping will often be required to recover the mission in the face of a major anomalous event such as an effector failure. In the fall of 2003 a team comprised of the Air Force, Barron Associates, Boeing, and General Dynamics conducted flight tests under AFRL’s Integrated Adaptive Guidance and Control (IAG&C) program. These tests used General Dynamics Total In-Flight Simulator (TIFS) research aircraft to simulate X-40A aerodynamics during approach and landing with and without failures. Both simulation and flight test results demonstrate IAG&C’s ability to maintain stability and manage vehicle energy under a variety of failure conditions that would have resulted in vehicle loss using the baseline X-40A G&C system. In addition to presenting the flight tests results, this talk will give an overview of the guidance and trajectory algorithms. Guidance adaptation is used to reduce feedback gains under failure to preserve stability margins when the inner-loop controller’s bandwidth is reduced due to failure and associated control saturation. The trajectory reshaping algorithm, known as the Optimum-Path-To-Go (OPTG) approach, estimates achievable lift and drag and then interrogates polynomial neural networks at regular intervals to obtain near-optimal reshaped trajectory commands. Based on the successful flight tests, the team is now porting the algorithms to the X-37 HIL simulator.