| タイトル | Biomechanically Induced and Controller Coupled Oscillations Experienced on the F-16XL Aircraft During Rolling Maneuvers |
| 本文（外部サイト） | http://hdl.handle.net/2060/19960047507 |
| 著者（英） | Montgomery, Terry; Smith, John W. |
| 著者所属（英） | NASA Dryden Flight Research Center |
| 発行日 | 1996-07-01 |
| 言語 | eng |
| 内容記述 | During rapid rolling maneuvers, the F-16 XL aircraft exhibits a 2.5 Hz lightly damped roll oscillation, perceived and described as 'roll ratcheting.' This phenomenon is common with fly-by-wire control systems, particularly when primary control is derived through a pedestal-mounted side-arm controller. Analytical studies have been conducted to model the nature of the integrated control characteristics. The analytical results complement the flight observations. A three-degree-of-freedom linearized set of aerodynamic matrices was assembled to simulate the aircraft plant. The lateral-directional control system was modeled as a linear system. A combination of two second-order transfer functions was derived to couple the lateral acceleration feed through effect of the operator's arm and controller to the roll stick force input. From the combined systems, open-loop frequency responses and a time history were derived, describing and predicting an analogous in-flight situation. This report describes the primary control, aircraft angular rate, and position time responses of the F-16 XL-2 aircraft during subsonic and high-dynamic-pressure rolling maneuvers. The analytical description of the pilot's arm and controller can be applied to other aircraft or simulations to assess roll ratcheting susceptibility. |
| NASA分類 | Aircraft Stability and Control |
| レポートNO | 96N33173
NASA-TM-4752
H-2031
NAS 1.15:4752 |
| 権利 | No Copyright |
