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Meeting	ACGS Committee Meeting 113 - Englewood, Colorado - March 2014
Agenda Location	6 SUBCOMMITTEE B – MISSILES AND SPACE 6.4 Design of Launch Vehicle Flight Control Systems
Title	Design of Launch Vehicle Flight Control Systems
Presenter	Abran Alaniz
Affiliation	Draper Laboratory
Available Downloads*	presentation
	Downloads are available to members who are logged in and either Active* or attended this meeting.
Abstract	A launch vehicle represents a complicated flex-body structural environment for flight control system design. The Ascent-vehicle Stability Analysis Tool (ASAT) is developed to address the complicity in design and analysis of a launch vehicle. The design objective for the flight control system of a launch vehicle is to best follow guidance commands while robustly maintaining system stability. Control allocation is also looked at for 3-axis control using multiple gimbals. A constrained optimization approach takes the advantage of modern computational control techniques to simultaneously design multiple control systems in compliance with required design specs. “Tower Clearance” and “Load Relief” designs have been achieved for liftoff and max dynamic pressure flight regions, respectively, in the presence of large wind disturbances. The robustness of the flight control system designs has been verified in the frequency domain Monte Carlo analysis using ASAT.