117 research outputs found
Tests of a Centering Spring Used as an Artificial Feel Device on the Elevator of a Fighter Airplane
Some Effects of Varying the Damping in Pitch and Roll on the Flying Qualities of a Small Single-rotor Helicopter
Flight investigation of a mechanical feel device in an irreversible elevator control system of a large airplane
Flight Investigation of a Mechanical Feel Device in an Irreversible Elevator Control System of a Large Airplane
Report presents the results of measurements of the longitudinal stability and control characteristics of a large airplane using a mechanical feel device in combination with a booster incorporated in the elevator-control system. Tests were made to investigate the feasibility of eliminating the aerodynamic control forces through use of a booster and of providing control-feel forces mechanically. The feel device consisted of a centering spring which restrained the control stick through a linkage which was changed as a function of the dynamic pressure. Provisions were made for trimming and for manual adjustment of the force gradient. The system was designed to approximate the control-force characteristics that would result with a conventional elevator control with linear hinge-moment characteristics
Effects on Longitudinal Stability and Control Characteristics of a B-29 Airplane of Variations in Stick-force and Control-rate Characteristics Obtained Through Use of a Booster in the Elevator-control System
The longitudinal stability and control characteristics of a B-29 airplane have been measured with a control surface booster incorporated in the elevator-control system. The measurements were obtained with the booster operating to provide various control-force gradients and various maximum rates of control motion. Results are presented which show the effect of these booster parameters on the handling qualities of the test airplane
Study of Exit Phase of Flight of a Very High Altitude Hypersonic Airplane by Means of a Pilot-controlled Analog Computer
Flight Investigation of the Effectiveness of an Automatic Aileron Trim Control Device for Personal Airplanes
A flight investigation to determine the effectiveness of an automatic aileron trim control device installed in a personal airplane to augment the apparent spiral stability has been conducted. The device utilizes a rate-gyro sensing element in order to switch an on-off type of control that operates the ailerons at a fixed rate through control centering springs. An analytical study using phase-plane and analog-computer methods has been carried out to determine a desirable method of operation for the automatic trim control
Instrument-flight Results Obtained with a Combined-signal Flight Indicator Modified for Helicopter Use
Helicopter Instrument Flight and Precision Maneuvers as Affected by Changes in Damping in Roll, Pitch, and Yaw
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