AeroVantage ~ Trim, Stability & Control - Stability 
Overview:
Note
Notes:
(To be later moved to an appropriate Item page)
- Vortex Ring State:
- 'It was argued that VRS could be initiated in one or both rotors simply by the effect of yaw rate or roll rate, even when the tilt-rotor aircraft was operating outside the steady state VRS boundary.' ~ Leishman, J.G.
- During hover and transition, will the short longitudinal and lateral moment arms result in the craft being very sensitive and unstable?
Will the wings and HS act as dampers and reduce any lack of stability. Will the gyro control be sufficient to maintain stability.
- Idea:
The V-22 limits were 800-fpm descent and 40 KTAS. This represents relatively low airflow velocities. It would appear that lightweight device(s) could be deployed while the craft is operating below these settings. This device(s) might be gas filled aerodynamic balloon with cables to each wing, additional retractable stabilizers, etc. In other words, anything to resist roll and yaw. The wings, which are subjected to very little downwash, so help resist a rapid descent; as long as their planform is horizontal. Alternatively, consider substituting a parasail for the 'balloon', which is automatically furled and stowed upon landing. None of the above devices are intended to slow the descent of the craft. They are intended to arrest any roll, and subsequent yaw, which may come about due to asymmetrical entry into a VRS.
- Also see;
OTHER: Aerodynamics - General - Vortex Ring State (settling with power)
- V–22 HIGH RATE OF DESCENT (HROD) TEST PROCEDURES AND LONG RECORD ANALYSIS Have on E-drive
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Last Revised: December 25, 2008