Autonomous Flight Envelope Estimation for Loss-of-Control Prevention
A nonlinear aircraft dynamics modeling and system identification approach is formulated and used to derive a rapid, convex optimization-based algorithm for the estimation of aerodynamic force coefficients from noisy sensor data, with uncertainty quantification. Furthermore, with the aerodynamic forc...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Schuet, Stefan [verfasserIn] |
|---|
| Format: |
Artikel |
|---|---|
| Sprache: |
Englisch |
| Erschienen: |
2016 |
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| Übergeordnetes Werk: |
Enthalten in: Journal of guidance, control, and dynamics - New York, NY, 1982, 40(2016), 4, Seite 847 |
|---|---|
| Übergeordnetes Werk: |
volume:40 ; year:2016 ; number:4 ; pages:847 |
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10.2514/1.G001729 |
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| 520 | |a A nonlinear aircraft dynamics modeling and system identification approach is formulated and used to derive a rapid, convex optimization-based algorithm for the estimation of aerodynamic force coefficients from noisy sensor data, with uncertainty quantification. Furthermore, with the aerodynamic force coefficients identified, a computationally fast method for generating the corresponding aircraft trim envelope given safe limits on achievable thrust and angle of attack is presented. This unified approach achieves the online Bayesian inference of the aircraft aerodynamic performance capability while running in the background as the aircraft is controlled independently by the pilot or automation system. The resulting information is readily incorporated into the determination of the extended safe maneuvering envelope, pilot displays, and automation algorithms for flight planning, trajectory generation, and guidance: all to help maintain safe aircraft operations under both nominal and off-nominal flight conditions. Presented as Paper 2014-0268 at the AIAA Guidance, Navigation, and Control Conference, National Harbor, MD, 13-17 January 2014 | ||
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| 700 | 1 | |a Shish, Kimberlee |4 oth | |
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| abstract |
A nonlinear aircraft dynamics modeling and system identification approach is formulated and used to derive a rapid, convex optimization-based algorithm for the estimation of aerodynamic force coefficients from noisy sensor data, with uncertainty quantification. Furthermore, with the aerodynamic force coefficients identified, a computationally fast method for generating the corresponding aircraft trim envelope given safe limits on achievable thrust and angle of attack is presented. This unified approach achieves the online Bayesian inference of the aircraft aerodynamic performance capability while running in the background as the aircraft is controlled independently by the pilot or automation system. The resulting information is readily incorporated into the determination of the extended safe maneuvering envelope, pilot displays, and automation algorithms for flight planning, trajectory generation, and guidance: all to help maintain safe aircraft operations under both nominal and off-nominal flight conditions. Presented as Paper 2014-0268 at the AIAA Guidance, Navigation, and Control Conference, National Harbor, MD, 13-17 January 2014 |
| abstractGer |
A nonlinear aircraft dynamics modeling and system identification approach is formulated and used to derive a rapid, convex optimization-based algorithm for the estimation of aerodynamic force coefficients from noisy sensor data, with uncertainty quantification. Furthermore, with the aerodynamic force coefficients identified, a computationally fast method for generating the corresponding aircraft trim envelope given safe limits on achievable thrust and angle of attack is presented. This unified approach achieves the online Bayesian inference of the aircraft aerodynamic performance capability while running in the background as the aircraft is controlled independently by the pilot or automation system. The resulting information is readily incorporated into the determination of the extended safe maneuvering envelope, pilot displays, and automation algorithms for flight planning, trajectory generation, and guidance: all to help maintain safe aircraft operations under both nominal and off-nominal flight conditions. Presented as Paper 2014-0268 at the AIAA Guidance, Navigation, and Control Conference, National Harbor, MD, 13-17 January 2014 |
| abstract_unstemmed |
A nonlinear aircraft dynamics modeling and system identification approach is formulated and used to derive a rapid, convex optimization-based algorithm for the estimation of aerodynamic force coefficients from noisy sensor data, with uncertainty quantification. Furthermore, with the aerodynamic force coefficients identified, a computationally fast method for generating the corresponding aircraft trim envelope given safe limits on achievable thrust and angle of attack is presented. This unified approach achieves the online Bayesian inference of the aircraft aerodynamic performance capability while running in the background as the aircraft is controlled independently by the pilot or automation system. The resulting information is readily incorporated into the determination of the extended safe maneuvering envelope, pilot displays, and automation algorithms for flight planning, trajectory generation, and guidance: all to help maintain safe aircraft operations under both nominal and off-nominal flight conditions. Presented as Paper 2014-0268 at the AIAA Guidance, Navigation, and Control Conference, National Harbor, MD, 13-17 January 2014 |
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Autonomous Flight Envelope Estimation for Loss-of-Control Prevention |
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Lombaerts, Thomas Acosta, Diana Kaneshige, John Wheeler, Kevin Shish, Kimberlee |
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