INVESTIGATION ON A PASSENGER RIDE-COMFORT IMPROVEMENT SYSTEM WITH LIMITED CONTROL SURFACE ACTUATOR PERFORMANCE FOR A FLEXIBLE AIRCRAFT.

Results of investigations on passenger ride comfort in aircraft are reported. For the low wing-loading aircraft, considered in this investigation, vertical acceleration appeared to be an important factor concerning passenger comfort. To reduce vertical motions, a ride-comfort improvement system was introduced. Determination of parameters of the system, like gains and allowable performance limitations, required analog simulation because of strong nonlinearities. Symmetric aircraft dynamics, ride-comfort improvement system and atmospheric turbulence were represented by mathematical models. The aircraft's model consisted of two rigid body and three structural modes. The ride comfort improvement system comprised fast-moving auxiliary flaps, over the entire flap span, being commanded by a vertical acceleration sensor.