System and method for finite element simulation of helicopter tu

Education and demonstration – Vehicle operator instruction or testing – Flight vehicle

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434 29, G09B 942

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active

058608079

ABSTRACT:
The present invention provides a turbulence model that has been developed for blade-element helicopter simulation. This model uses an innovative temporal and geometrical distribution algorithm that preserves the statistical characteristics of the turbulence spectra over the rotor disc, while providing velocity components in real time to each of five blade-element stations along each of four blades, for a total of twenty blade-element stations. The simulator system includes a software implementation of flight dynamics that adheres to the guidelines for turbulence set forth in military specifications. One of the features of the present simulator system is that it applies simulated turbulence to the rotor blades of the helicopter, rather than to its center of gravity. The simulator system accurately models the rotor penetration into a gust field. It includes time correlation between the front and rear of the main rotor, as well as between the side forces felt at the center of gravity and at the tail rotor. It also includes features for added realism, such as patchy turbulence and vertical gusts in to which the rotor disc penetrates. These features are realized by a unique real time implementation of the turbulence filters. The new simulator system uses two arrays one on either side of the main rotor to record the turbulence field and to produce time-correlation from the front to the rear of the rotor disc. The use of Gaussian Interpolation between the two arrays maintains the statistical properties of the turbulence across the rotor disc.
The present simulator system and method may be used in future and existing real-time helicopter simulations with minimal increase in computational workload.

REFERENCES:
patent: 2486488 (1949-11-01), Lukacs
patent: 3346969 (1967-10-01), Marvin
patent: 4268979 (1981-05-01), Minnich
patent: 4958786 (1990-09-01), Ogawa et al.
patent: 5354017 (1994-10-01), Levich
patent: 5375794 (1994-12-01), Bleeg
R.E.McFarland, "Simulation of Rotor Blade Element Turbulence," NASA Technical Memorandum 198862, Jan. 1995.
Costello, M. F., "A Theory for the Analysis of Rotorcraft Operating in Atmospheric Turbulence," Proceedings of the 46th Annual National Forum of the American Helicopter Society, Washington, D. C., May 1990, pp. 1003-1015.
Prasad, J. V. R., Riaz, J., Gaonkar, G. H., Yingyi, D., "Real Time Implementation Aspects of a Rotorcraft Turbulence Simulation Method," 49th Annual Forum of the American Helicopter Society, St. Louis, MO, May 1993, p. 459.
Dahl, H. J. and Faulkner, A. J., "Helicopter Simulation in Atmospheric Turbulence," Vertica, vol. 3, 1979, pp. 65-78.
Judd, M. and Newman, S. J., "An Analysis of Helicopter Rotor Response due to Gust and Turbulence," Vertica, vol. 1, 1977, pp. 179-188.
Dang, Y., G. Gaonkar, Prasad, J., Zhang, H., "Parallel Computing of Helicopter Response to Turbulence Toward Real-Time Implementation," 50th Annual Forum of the American Helicopter Society, Washington, D.C., vol. 2, May 1994, pp. 869-882.

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