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Kuczynski, W. A.

Publications and source records attributed to Kuczynski, W. A..

6 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1978

The RSRA Active Isolation/Rotor Balance System

The Rotor Systems Research Aircraft (RSRA) includes provisions for the installation of an Active Transmission Isolation/Rotor Loads Balance System (AIBS). The purpose of this system is to enable aircraft operation with an arbitrary rotor system over a wide rotor speed range and maneuver envelope without vibration envelope restrictions, while simultaneously providing measurement of rotor system loads. The present paper reviews the history of the design and development of this system, which culminated in successful flight test evaluation in 1977. Consideration is given to highlights of the design, ground test, and flight test.

Kuczynski, W. A.↗
NASA NTRS1976

Inflight Rotor Stability Monitor

An inflight rotor stability monitor developed at Sikorsky Aircraft to support stability testing of new rotorcraft is described. The monitor has as its core a damping estimation algorithm which embodies spectral analysis techniques. The interactive system is activated and controlled from a cathode ray tube (CRT) and operates on-line in a flight test telemetry environment. Accurate estimates of the level of damping of critical system modes are generated within one minute of the completion of a prescribed test maneuver. The stability monitor was used successfully to support various Sikorsky research and development flight programs including the UTTAS, CH-53E, S-67 Fan-in-Fin, and ABC.

Kuczynski, W. A.↗
NASA NTRS1972

Experimental Hingeless Rotor Characteristics at Full Scale First Flap Mode Frequencies (including Rotor Frequency Response to Shaft Oscillations), Phase 3

The completion of the High Advance Ratio Research Program is reported. The primary objectives of the program were to experimentally determine the rotor frequency response to shaft pitching and rolling oscillations and to acquire steady response and frequency response data at high advance ratios for hingeless rotors with typical, full-scale, first flap mode natural frequencies. Secondary objectives of the program included the further evaluation of both the hub moment feedback control system and the simplified rigid blade flapping theory with respect to shaft oscillations. The bulk of the text is devoted to the presentation and examination of representative experimental results. All the analyzed test data are documented in tabular and/or graphical formats.

Kuczynski, W. A.↗
NASA NTRS1972

Characteristics of hingeless rotors with hub moment feedback controls including experimental rotor frequency response, Volume 1

Wind tunnel tests to determine the dynamic characteristics of hingeless rotors with hub moment feedback controls and to acquire experimental hingeless rotor transfer functions are discussed. Rotor transfer functions were calculated from data acquired during open loop frequency response tests. The transfer functions are linear and present the rotor longitudinal and lateral frequency responses to collective pitch, longitudinal cyclic pitch, and lateral cyclic pitch. The theoretical analysis was based on the rigid blade flapping model coupled with appropriate control system and cyclic pitch actuator equations of motion.

Kuczynski, W. A.↗