20 research outputs found
Theoretical analysis of the rolling motions of aircraft using a flicker-type automatic roll stabilization system having a displacement-plus-rate response
Get PDFTheoretical and Analog Studies of the Effects of Nonlinear Stability Derivatives on the Longitudinal Motions of an Aircraft in Response to Step Control Deflections and to the Influence of Proportional Automatic Control
Get PDFThrough theoretical and analog results the effects of two nonlinear stability derivatives on the longitudinal motions of an aircraft have been investigated. Nonlinear functions of pitching-moment and lift coefficients with angle of attack were considered. Analog results of aircraft motions in response to step elevator deflections and to the action of the proportional control systems are presented. The occurrence of continuous hunting oscillations was predicted and demonstrated for the attitude stabilization system with proportional control for certain nonlinear pitching-moment variations and autopilot adjustments
Theoretical and analog studies of the effects of nonlinear stability derivatives on the longitudinal motions of an aircraft in response to step control deflections and to the influence of proportional automatic control
Get PDFApplication of nonlinear aerodynamic stability characteristics to simplify missile control and guidance systems
Get PDFFlight Investigation to Determine the Hinge Moments of a Beveled-edge Aileron on a 45 Degree Sweptback Wing at Transonic and Low Supersonic Speeds
Get PDFMethod for determining the frequency-response characteristics of an element or system from the system transient output response to a known input function
Get PDFTheoretical Analysis of the Motions of an Aircraft Stabilized in Roll by a Displacement-response, Flicker-type Automatic Pilot
Get PDFObservations on an Aileron-Flutter Instability Encountered on a 45 Degree Swept-Back Wing in Transonic and Supersonic Flight
Get PDFIn the course of a flight test of a supersonic research pilotless aircraft (the NACA RM-1), large-amplitude aileron oscillations, probably aileron compressibility flutter, were encountered in the transonic and supersonic speed ranges. The wing was oscillating at the same frequency as the aileron. The aircraft was equipped with 45 degree swept-back wings of symmetrical NASA 65-010 airfoil section. Completely mass-balanced ailerons with 20 degree beveled trailing edges were installed on the wings. The ailerons were free floating with no mechanical restraining force other than the friction of the aileron hinges and servomechanism bearings throughout the high-speed interval of flight
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NACA Research Memorandums
Get PDFReport presenting a study of the supersonic longitudinal stability and control characteristics of a canard missile configuration using flight tests and wind-tunnel tests at a range of Mach numbers and Reynolds numbers. Good correlation was noted for the two techniques for slopes of lift and moment coefficients against angle of attack and for aerodynamic-center location
