An experimental investigation of VTOL flying qualities requirements in shipboard landings

Radford, R. C.; Andrisani, Dominick

doi:10.2514/6.1980-1625

Cited by 3 publications

References 1 publication

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A nonlinear pilot model for hover

Andrisani

Gau

1985

Journal of Guidance, Control, and Dynamics

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This paper deals with persistent oscillations in position and attitude observed in flight on a piloted VTOL during precision hover. Properties of the oscillation are shown to correlate strongly with Cooper-Harper pilot ratings. A simple yet nonlinear pilot model is developed which predicts many of the properties of the pilot-inthe-loop system behavior. Configuration 217CK+ N(E) PR ll s Tx Nomenclature = properties of the ideal relay with dead zone (Af=0.25 in., >1 =0.125 in.) = configuration C of X-22A flight 217 = error in X position, -X C -X (ft) = amplitude of sinusoidal input to nonlinear element N(E) = pilot position error gain (in./ft) = ratio of steady state x translational velocity per inch of pilot's stick position (ft/s/in.) . = minimum pilot position error gain to maintain a stable limit cycle (in./ft) = describing function gain which is a nonlinear function of sinusoidal input amplitude E = Cooper-Harper pilot rating (Ref. 1) = quantization nonlinearity, Fig.9 = Laplace operator for differentiation = equivalent path mode time constant, s = fore and aft position, ft = commanded position, ft = pilot's stick position (positive stick aft, in.) -modified stick position (positive stick forward, in.) = -d s = body-axis pitch attitude, deg = limit-cycle frequency

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A nonlinear pilot model for hover

Andrisani

Gau

1985

Journal of Guidance, Control, and Dynamics

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Application of eigenstructure assignment to the design of STOVL flight control systems

Lee

Youssef

Hänel

1988

Guidance, Navigation and Control Conference

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Integrated Control and Display Research for Transition and Vertical Flight on the NASA V/STOL Research Aircraft (VSRA)

Foster

Moralez

Franklin

et al. 1987

SAE Technical Paper Series

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Results of a substantial body of ground-based simulation experiments indicate that a high degree of precision of operation for recovery aboard small ships in heavy seas and low visibility with acceptable levels of effort by the pilot can be achieved by integrating the aircraft flight and propulsion controls. The availability of digital fly-by-wire controls makes it feasible to implement an integrated control design to achieve and demonstrate in flight the operational benefits promised by the simulation experience. It remains to validate these systems concepts in flight to establish their value for advanced short takeoff vertical landing (STOVL) aircraft designs. This paper summarizes analytical studies and simulation experiments that provide a basis for the flight research program that will develop and validate critical technologies for advanced STOVL aircraft through the development and evaluation of advanced, integrated control and display concepts and lays out the plan for the flight program that will be conducted on NASA's V/STOL Research Aircraft (VSRA).

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An experimental investigation of VTOL flying qualities requirements in shipboard landings

Cited by 3 publications

References 1 publication

A nonlinear pilot model for hover

A nonlinear pilot model for hover

Application of eigenstructure assignment to the design of STOVL flight control systems

Integrated Control and Display Research for Transition and Vertical Flight on the NASA V/STOL Research Aircraft (VSRA)

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