초록 ▼

A method for reducing yawing motions of an aircraft in-flight, wherein a spoiler adjustment drive of a spoiler and a regulating flap adjustment drive of a regulating flap of the same respective airfoil are adjusted in a time segment in such a way that the motion of the spoiler being adjusted and the

A method for reducing yawing motions of an aircraft in-flight, wherein a spoiler adjustment drive of a spoiler and a regulating flap adjustment drive of a regulating flap of the same respective airfoil are adjusted in a time segment in such a way that the motion of the spoiler being adjusted and the motion of the regulating flap of the same airfoil deflect in mutually opposite directions in the time segment. The spoiler and the regulating flap are adjusted on the airfoil, on which the adjusted deflections counteract the respectively occurring yawing motion. Also provided are a computer program product for carrying out this method and an aircraft with a directional stabilization device for carrying out this method.

대표청구항 ▼

1. A method for reducing yawing motions of an aircraft in-flight, wherein a spoiler adjustment drive of a spoiler and a second regulating flap adjustment drive of a second regulating flap of the same respective airfoil are adjusted in a time segment such that a motion of the spoiler being adjusted a

1. A method for reducing yawing motions of an aircraft in-flight, wherein a spoiler adjustment drive of a spoiler and a second regulating flap adjustment drive of a second regulating flap of the same respective airfoil are adjusted in a time segment such that a motion of the spoiler being adjusted and a motion of the second regulating flap of the same airfoil deflect in mutually opposite directions in the time segment,identifying a predetermined characteristic of a Dutch Roll by comparing characteristics of yawing motions of the aircraft with target specifications, andadjusting the spoiler and the second regulating flap on the same airfoil in mutually opposite directions to counteract the yawing motions of the aircraft. 2. The method of claim 1, wherein the predetermined characteristic of a respectively detected yawing motion is defined by a predetermined limiting value for a respectively detected yaw rate and a limiting value for a minimum time period of an exceedance of the predetermined limiting value by the respectively detected yaw rate in one respective direction, and wherein a comparison function identifies the predetermined characteristic of the respectively detected yawing motion if the comparison function determines that the respectively detected yaw rate exceeds the predetermined limiting value for the respectively detected yaw rate and the predetermined limiting value for the minimum time period,wherein the predetermined limiting value for the respectively detected yaw rate amounts to more than 3 degrees per second and the limiting value for the minimum time period amounts to more than one second. 3. The method of claim 1, wherein a comparison function identifies the predetermined characteristic of the respectively detected yawing motion if the following function is fulfilled as the predetermined characteristic of the respectively detected yawing motion: (ωxBx)2+(ωzBz)2>1; wherein: ωz is the current yaw rate of the aircraft,ωx is the current roll rate of the aircraft,Bx is a scaling factor for the current yaw rate ωx of the aircraft that lies in the range between 10 degrees/second and 20 degrees/second, andBz is a scaling factor for the current roll rate ωz of the aircraft that lies in the range between 10 degrees/second and 20 degrees/second. 4. The method of claim 1, wherein comparing the characteristics of a respectively detected yawing motion with the target specifications and generating an actuating command for the spoiler adjustment drive and the second regulating flap adjustment drive comprise: comparing lateral control commands executed with a lateral control input device with target specifications in order to identify a predetermined characteristic of the lateral control commands, wherein the predetermined characteristic of the lateral control commands is defined in such a way that a multiple change of an adjusting direction of lateral control takes place in an adjustment period with a minimum value of the lateral control commands such that the adjusting direction respectively alternates for successive lateral control commands, andgenerating an actuating command for deflection of the spoiler in dependence on the respectively detected lateral control commands and transmitting the actuating command to the spoiler adjustment drive of the spoiler for deflection of the spoiler, as well as generating an actuating command for deflection of the second regulating flap in dependence on the respectively detected lateral control commands and transmitting the actuating command to the second regulating flap adjustment drive based on identification of the predetermined characteristic of the lateral control commands, wherein the spoiler and the second regulating flap are moved in mutually opposite directions on the same airfoil, and wherein the actuating commands are specified in such a way that the respectively detected yawing motion is reduced. 5. The method of claim 1, wherein comparing the characteristics of the detected Dutch roll with the target specifications and generating an actuating command for the spoiler adjustment drive and for the second regulating flap adjustment drive are carried out when at least one of the following conditions are fulfilled: an aircraft speed VCAS determined during the method exceeds a speed threshold that lies in a range between 180 and 220 knots anda flight altitude is greater than an altitude threshold value that lies in a range between 200 and 400 m. 6. The method of claim 1, further comprising comparing lateral control commands generated with a lateral control input device with target specifications in order to recognize a predetermined characteristic of the lateral control commands, wherein the predetermined characteristic of the lateral control commands is defined such that a multiple change of an adjusting direction of lateral control takes place in an adjustment period with a minimum value of the lateral control commands such that adjusting directions respectively alternate for successive lateral control commands, andgenerating and transmitting an actuating command for the spoiler flap adjustment drive of the spoiler for deflection of the spoiler, as well as generating and transmitting an actuating command for the second regulating flap adjustment drive of the second regulating flap for deflection of the second regulating flap to counteract the respectively detected yawing motion and, in particular, a yaw rate of the aircraft with the identified predetermined characteristic. 7. The method of claim 6, wherein the predetermined characteristic of the lateral control commands for generating a logical lateral control command confirmation signal comprises: a time period, in which an adjustment of the spoiler adjustment drive and of the second regulating flap adjustment drive respectively takes place, amounts to at least double and no more than a period of the natural oscillations of the aircraft or a periodic time of a side slipping oscillation of the aircraft,at least three successive lateral control commands with changing adjusting directions and with a respective minimum value of the lateral control command are present,wherein the respective minimum value of the lateral control commands amounts to at least 25% of a maximum deflection of the lateral control input device. 8. The method of claim 7, wherein a lateral motion adjusting device is formed by control pedals in a cockpit that serve for actuating a rudder. 9. The method of claim 6, wherein actuating commands for the spoiler adjustment drive and for the second regulating flap adjustment drive determined by an adjustment function upon identification of the predetermined characteristic of the lateral control commands are determined in dependence on the respectively detected lateral control commands, and wherein the adjustment function is configured to transmit the determined actuating commands to the spoiler adjustment drive and to the second regulating flap adjustment drive no earlier than after a second of the successive lateral control commands with changing the adjusting directions and with the respective minimum value of the lateral control commands. 10. The method of claim 6, wherein the second regulating flap that is arranged on the respective airfoil and is adjustable in two directions from a neutral position is an aileron. 11. The method of claim 6 further comprising carrying out the method on a program-controlled device. 12. An aircraft comprising: airfoils with at least one respective regulating flap is adjustable in two directions from a neutral position and at least one spoiler, a rudder unit with a rudder, a directional stabilization device, and a flight computer, wherein the flight computer is configured for carrying out the method of claim 6. 13. The method of claim 1, further comprising: monitoring a control system of the aircraft for a presence of a fault in an actuation system of a rudder of the aircraft by determining deviations of an adjusted actuating command for an adjustment drive of the rudder from a respective actual position of the rudder and generating a logical fault state confirmation signal if one of the deviations exceeds a predetermined limiting value, andadjusting a fall-back operating mode in a flight control device of the aircraft in a presence of the logical fault state confirmation signal, wherein directional stability is influenced by generating and transmitting at least one actuating command for the spoiler adjustment drive of the spoiler on one of the airfoils for deflection of the spoiler, as well as an actuating command for the second regulating flap adjustment drive of the second regulating flap on the same airfoil for deflection of the second regulating flap in a direction that extends opposite to the deflection of the spoiler, wherein the actuating commands for influencing the directional stability are specified such that the aircraft seeks a yaw rate to be adjusted in order to influence the directional stability. 14. The method of claim 13, wherein at least one of the spoiler and the second regulating flap that is arranged on each airfoil and is adjustable in two directions from a neutral position is an aileron. 15. The method of claim 13 further comprising carrying out the method on a program-controlled device. 16. An aircraft comprising: airfoils with at least one respective regulating flap that is adjustable in two directions from a neutral position and the spoiler, a rudder unit with a rudder, a directional stabilization device, and a flight computer, wherein the flight computer is configured for carrying out the method of claim 13.