Forward flight trim calculation and frequency response validation of a high-order helicopter simulation modelThis paper describes a new trim procedure, that includes the calculation of the steady-state response of the rotor blades, and that is applicable to straight flight and steady coordinated turns. This paper also describes the results of a validation study for a high order linearized model of helicopter flight dynamics, that includes rotor, inflow, and actuator dynamics. The model is obtained by numerical perturbations of a nonlinear, blade element type mathematical model. Predicted responses are compared with flight test data for two values of flight speed. The comparison is carried out in the frequency domain. Numerical simulations show that the trim algorithm is very accurate, and preserves the periodicity of the aircraft states. The results also indicate that the predictions of the linearized model are in good agreement with flight test data, especially at medium and high frequencies.
Document ID
19920031713
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kim, Frederick D. (Maryland Univ. College Park, MD, United States)
Celi, Roberto (Maryland, University College Park, United States)
Tischler, Mark B. (NASA Ames Research Center; U.S. Army, Aeroflightdynamics Directorate, Moffett Field CA, United States)