초록 ▼

A device for damping at least one rigid body mode and/or at least one elastic mode of an aircraft, especially for blast load reduction and increase of stability and comfort, in an airplane having at least one sensor, a regulation unit connected to the sensor, and at least one actuator controlling, g

A device for damping at least one rigid body mode and/or at least one elastic mode of an aircraft, especially for blast load reduction and increase of stability and comfort, in an airplane having at least one sensor, a regulation unit connected to the sensor, and at least one actuator controlling, guiding and/or regulating surfaces of the aircraft. The controller modifies the rigid body modes and/or the one or more elastic modes of the aircraft. With only one sensor signal of a sensor, which is preferably an acceleration signal, an arbitrary number and an arbitrary combination of rigid body modes and/or elastic modes, respectively, may specifically be modified, and the modes obtained are not influenced.

대표청구항 ▼

What is claimed is: 1. A damping system for damping at least one of at least one rigid body mode of an aircraft and at least one elastic mode of the aircraft for at least one of blast load reduction, increase of stability and increase of comfort in an aircraft, the aircraft having thereon at least

What is claimed is: 1. A damping system for damping at least one of at least one rigid body mode of an aircraft and at least one elastic mode of the aircraft for at least one of blast load reduction, increase of stability and increase of comfort in an aircraft, the aircraft having thereon at least one of a controlling surface, a guiding surface and a regulating surface, at least two of the controlling surface, the guiding surface and the regulating surface being formed by at least one of an aileron, a rudder and a spoiler of the aircraft, the damping system comprising: a sensor positioned in the aircraft to detect a lateral force experienced by the aircraft and to generate a sensor signal relating to the lateral force; a controller connected to the sensor to receive the sensor signal and operable responsive to the sensor signal to modify the at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft; and an actuator connected to the controller and operable to receive controller signaling from the controller and responsive to the controller signaling to control and to modify the at least one of the controlling surface, the guiding surface and the regulating surface of the aircraft, wherein the controller comprises a respective resonance filter for each of the at least one rigid body mode and the at least one elastic mode to be modified, and each resonance filter comprises at least two phase correcting units operable to generate the controller signaling comprising at least two feedback signals for moving the at least two of the controlling surface, the guiding surface and the regulating surface for damping at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft. 2. The damping device of claim 1, wherein the sensor signaling comprises the sensor outputting a measurement signal relating to lateral acceleration detected by the sensor to the controller, and the measurement signal is operable for modifying the at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft. 3. The damping device of claim 1, wherein each resonance filter is parameterized by an eigenfrequency ω0 and by a damping for modifying the operation of the respective resonance filter to the at least one of the at least one rigid body mode and the at least one elastic mode to be modified. 4. The device of claim 1, further comprising: at least one amplifier for each of the at least two phase correcting units of each of the resonance filters, the at least one amplifier being connected after each of the phase correction units for generating at least one feedback signal which is supplied back to the at least one of the controlling surface, the guiding surface and the regulating surface of the aircraft via the actuator. 5. The damping device of claim 1, wherein the device has a maximal effective combination of the at least one of the controlling surface, the guiding surface and the regulating surface for minimizing wear of the actuator and a consumption of energy. 6. The damping device of claim 5, further comprising: at least one adder provided in the controller and operable to combine the at least two feedback signals to generate a combined feedback signal operable for driving the actuator, the controller being operable to modify at least two of the at least one rigid body mode and the at least one elastic mode of the aircraft, wherein the at least two feedback signals are generated from different ones of the resonance filters. 7. The damping device of claim 6, wherein in case of a phase shift of about 180째 between the two feedback signals, the respective phase correcting unit is replaceable with an inverter. 8. The damping device of claim 1, further comprising: a frequency measurement circuit for outputting a frequency signal representing the at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft, wherein the controller has an input for receiving the frequency signal. 9. A method of damping at least one of at least one rigid body mode and at least one elastic mode of an aircraft for at least one of blast load reduction, increase of stability and increase of comfort in an aircraft, the aircraft having thereon at least one of a controlling surface, a guiding surface and a regulating surface, at least two of the controlling surface, the guiding surface and the regulating surface being both formed by at least one of an aileron, a rudder and a spoiler of the aircraft, the damping method comprising: detecting by a sensor positioned in the aircraft a lateral force experienced by the aircraft; transmitting sensor signaling corresponding to the lateral forces detected from the sensor to a controller connected to the sensor; operating a resonance filter and at least two phase correction units comprised in the controller to generate, based on the sensor signaling, at least two feedback signals, and transmitting from the controller the at least two feedback signals to an actuator; according to the at least two feedback signals from the controller, modifying by the actuator the at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft by moving the at least two of the controlling surface, the guiding surface and the regulating surface of the aircraft, for damping at least one of the at least one rigid body mode and the at least one elastic mode of an aircraft. 10. The method of claim 9, further comprising the steps of: outputting a measurement signal from the sensor to the controller, the measurement signal operative for modifying the at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft. 11. The method of claim 9, wherein the modifying of the at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft further comprises the steps of: performing a resonance filtering of a signal relating to the at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft; and performing a phase correction of the resonance filtered signal of the at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft for forming the at least one feedback signal. 12. The method of claim 9, further comprising the steps of: performing a parameterisation of the resonance filter by an eigenfrequency ω0 and by a damping for modifying the operation of the resonance filter to the at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft to be modified. 13. The method of claim 9, further comprising the steps of: performing an amplification for forming the at least one feedback signal; supplying the feedback signal back to the at least one of the controlling surface, the guiding surface and the regulating surface of the aircraft via the respective actuator. 14. The method of claim 12, further comprising the step of: modifying at least two of the at least one rigid body mode and the at least one elastic mode of the aircraft; and combining the at least two feedback signals to a combined feedback signal for driving the actuator, wherein the at least two feedback signals stem from different ones of the resonance filters. 15. The method of claim 11, further comprising the step of: inverting the resonance filtered signal of the at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft for forming the at least one feedback signal in case of a phase shift of about 180째 between two feedback signals. 16. The method of claim 9, further comprising the step of: supplying a frequency signal of a frequency measurement arrangement representing a frequency of the at least one of the at least one rigid body mode and the at least one elastic mode of the aircraft.