| Autor: |
Giiligan Eric, Tannen S. VanZwieten, Curtis E. Hanson, Christopher J. Miller, John H. Wall, Jeb S. Orr |
| Rok vydání: |
2015 |
| Předmět: |
|
| Zdroj: |
AIAA Guidance, Navigation, and Control Conference. |
| DOI: |
10.2514/6.2015-1775 |
| Popis: |
NASA's Space Launch System (SLS) Flight Control System (FCS) includes an Adaptive Augmenting Control (AAC) component which employs a multiplicative gain update law to enhance the performance and robustness of the baseline control system for extreme off-nominal scenarios. The SLS FCS algorithm including AAC has been flight tested utilizing a specially outfitted F/A-18 fighter jet in which the pitch axis control of the aircraft was performed by a Non-linear Dynamic Inversion (NDI) controller, SLS reference models, and the SLS flight software prototype. This paper describes test cases from the research flight campaign in which the fundamental F/A-18 airframe structural mode was identified using post-flight frequency-domain reconstruction, amplified to result in closed loop instability, and suppressed in-flight by the SLS adaptive control system. |
| Databáze: |
OpenAIRE |
| Externí odkaz: |
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