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Design of launch vehicle flight control systems using ascent vehicle stability analysis tool
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Hall, Robert Bedossian, Nazareth Hall Sr., Charles Jackson, Mark Alaniz, Abran Jang, Jiann-Woei |
| Copyright Year | 2011 |
| Description | 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. |
| File Size | 836911 |
| Page Count | 16 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20110015701 |
| Archival Resource Key | ark:/13960/t4gn36590 |
| Language | English |
| Publisher Date | 2011-08-08 |
| Access Restriction | Open |
| Subject Keyword | Launch Vehicles And Launch Operations Stability Tests Robustness Mathematics Launch Vehicles Ascent Systems Engineering Flight Control Design Analysis Monte Carlo Method Frequency Domain Analysis Dynamic Pressure Environmental Control Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
