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. 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.
Design of Launch Vehicle Flight Control Systems Using Ascent Vehicle Stability Analysis Tool
2011
16 pages
Report
No indication
English
Design of Launch Vehicle Flight Control Systems Using Ascent Vehicle Stability Analysis Tool
British Library Conference Proceedings | 2011
|Hybrid Adaptive Launch Vehicle Ascent Flight Control
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|Hybrid Adaptive Launch Vehicle Ascent Flight Control
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