Risk reduction is the objective of the X-57 Maxwell aeroelasticity team. The X-57, NASA’s experimental electric propulsion aircraft, has a long thin wing with primary propulsion systems located at the wing tips and high lift motors distributed along the span. Many of the classical aeroelastic concerns associated with such a configuration were addressed through early design decisions. The as-designed intermediate flight vehicle configurations show flutter mechanisms associated with flexible models of control surface systems –the stabilator, flaps and ailerons. Improvements to the analytical models, based on ground test data and project decisions about flight operations, show improved prospects of the vehicle being aeroelastically stable throughout the flight envelope. On-going ground testing and further analyses will lend credibility to the flutter predictions and vehicle safety.
Status Report on Aeroelasticity in the Vehicle Development for X-57 Maxwell
2018
18 pages
Report
No indication
English
Aircraft , Test Facilities & Equipment , Aeroelasticity , Aircraft design , Nacelles , Propulsion system configurations , Propulsion system performance , Risk assessment , Safety factors , Structural design , Wings , X-57 maxwell , Control surfaces , Electric batteries , Electric motors , Electric propulsion , Flight tests , Flutter analysis , Ground tests , Leading edges
Status Report on Aeroelasticity in the Vehicle Development for X-57 Maxwell (AIAA 2018-3487)
British Library Conference Proceedings | 2018
|FLIGHT VEHICLE AEROELASTICITY - Nonlinear Aeroelasticity
Online Contents | 2003
|FLIGHT VEHICLE AEROELASTICITY - Computational Aeroelasticity: Success, Progress, Challenge
Online Contents | 2003
|