| タイトル | Effects of mass on aircraft sidearm controller characteristics |
| 本文（外部サイト） | http://hdl.handle.net/2060/19950005455 |
| 著者（英） | Wagner, Charles A. |
| 著者所属（英） | NASA Dryden Flight Research Center |
| 発行日 | 1994-09-01 |
| 言語 | eng |
| 内容記述 | When designing a flight simulator, providing a set of low mass variable-characteristic pilot controls can be very difficult. Thus, a strong incentive exists to identify the highest possible mass that will not degrade the validity of a simulation. The NASA Dryden Flight Research Center has conducted a brief flight program to determine the maximum acceptable mass (system inertia) of an aircraft sidearm controller as a function of force gradient. This information is useful for control system design in aircraft as well as development of suitable flight simulator controls. A modified Learjet with a variable-characteristic sidearm controller was used to obtain data. A boundary was defined between mass considered acceptable and mass considered unacceptable to the pilot. This boundary is defined as a function of force gradient over a range of natural frequencies. This investigation is limited to a study of mass-frequency characteristics only. Results of this investigation are presented in this paper. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 95N11868
NASA-TM-104277
H-2014
NAS 1.15:104277 |
| 権利 | No Copyright |
