초록 ▼

A control device for aircraft for reducing the turbulence and gust influences on the flying characteristics is designed to generate an additional incidence angle drive signal for control surfaces on surfaces which generate an air force, in particular wing and/or tailplane as a function of an instant

A control device for aircraft for reducing the turbulence and gust influences on the flying characteristics is designed to generate an additional incidence angle drive signal for control surfaces on surfaces which generate an air force, in particular wing and/or tailplane as a function of an instantaneous bank angle (Φ) and sideslip angle (β).

대표청구항 ▼

The invention claimed is: 1. A control device for aircraft for reducing the turbulence and gust influences on the flying characteristics, comprising: a sideslip angle sensor for determining the instantaneous sideslip angle (β); a bank angle sensor for determining the instantaneous bank angle

The invention claimed is: 1. A control device for aircraft for reducing the turbulence and gust influences on the flying characteristics, comprising: a sideslip angle sensor for determining the instantaneous sideslip angle (β); a bank angle sensor for determining the instantaneous bank angle (Φ); and controller for generating an additional incidence angle drive signal for control surfaces on said aircraft which generate an air force as a function of the instantaneous bank angle (Φ) and sideslip angle (β), said additional incidence angle drive signal being provided to be added to a main drive signal for the control surfaces, wherein the control device determines the drive signal as a function of a component (αWf) of the wind incidence, caused by a vertical air mass movement, on the plane of symmetry of the aircraft, using the formula: α Wf = cos ⁡ ( ϕ ) ⁡ [ f ⁡ ( H . V ) - θ + cos ⁡ ( ϕ ) ⁢ ( α + q · r A ⁢ ⁢ ϕ ⁢ ⁢ A V ) + sin ⁡ ( ϕ ) ⁢ ( β - r · r A a ⁢ S V ) ] where Φ is the bank angle, {dot over (H)} is the vertical velocity of the aircraft, V is the airspeed of the aircraft with respect to the surrounding air, θ is the longitudinal attitude angle of the aircraft, α is the angle of attack, q is the pitch rate of the aircraft, rAoA is the distance between the incidence angle sensor and the center of gravity of the aircraft, r is the yaw rate and rAoS is the distance between the sideslip angle sensor and the center of gravity, and f ⁡ ( H . V ) is a function of the ratio of the vertical velocity {dot over (H)} to the airspeed V. 2. The control device as claimed in claim 1, wherein the control device is designed to determine the drive signal using the function f ⁡ ( H . V ) ⁢ ⁢ equal ⁢ ⁢ to ⁢ ⁢ H . V ⁢ ⁢ or ⁢ ⁢ arcsin ⁡ ( H . V ) . 3. The control device as recited in claim 1 wherein said additional incidence angle drive signal generated is for a wing. 4. The control device as recited in claim 1 wherein said additional incidence angle drive signal generated is for a tailplane. 5. A method for reducing the turbulence and gust influences on the flying characteristics of aircraft, comprising the steps of: determining the instantaneous sideslip angle (β); determining the instantaneous bank angle (Φ); and generating an additional incidence angle (αWf) control signal for control surfaces of said aircraft which generate an air force as a function of the control signal, said additional incidence angle drive signal being provided to be added to a main drive signal for the control surfaces, said control signal being a function of the instantaneous bank angle (Φ) and sideslip angle (β), said main drive signal together with the superimposed control signal controlling the control surfaces wherein said generating step uses the formula: α Wf = cos ⁡ ( ϕ ) ⁡ [ f ⁡ ( H . V ) - θ + cos ⁡ ( ϕ ) ⁢ ( α + q · r A ⁢ ⁢ ϕ ⁢ ⁢ A V ) + sin ⁡ ( ϕ ) ⁢ ( β - r · r A a ⁢ S V ) ] where Φ is the bank angle, {dot over (H)} is the vertical velocity of the aircraft, V is the airspeed of the aircraft with respect to the surrounding air, θ is the longitudinal attitude angle of the aircraft, α is the angle of attack, q is the pitch rate of the aircraft, rAoA is the distance between the incidence angle sensor and the center of gravity of the aircraft, r is the yaw rate and rAoS is the distance between the sideslip angle sensor and the center of gravity, and f ⁡ ( H . V ) is a function of the ratio of the vertical velocity {dot over (H)} to the airspeed V. 6. The method as claimed in claim 5, wherein the function is f ⁡ ( H . V ) ⁢ ⁢ equal ⁢ ⁢ to ⁢ ⁢ H . V ⁢ ⁢ or ⁢ ⁢ arcsin ⁡ ( H . V ) .