Method and system for reducing engine induced vibration amplitudes in an aircraft fuselage

• US 20040104302A1
• Filed: 08/11/2003
• Published: 06/03/2004
• Est. Priority Date: 08/10/2002
• Status: Abandoned Application

• Current Assignee: Detlef Schierenbeck
• Original Assignee: Detlef Schierenbeck
• Inventors: Schierenbeck, Detlef
• Application Number:
  US10/639,199
• Publication Number:
  US 20040104302A1
• Time in Patent Office: Days
• US Class Current: 244/10
• CPC Class Codes: B64C 2220/00 Active noise reduction systems
• CPC Class Codes: B64D 27/00 Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
• CPC Class Codes: F16F 15/02 Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems F16F15/005 takes precedence ; layered products B32B; suppression of vibration in ships B63; relieving load on bearings, using magnetic means F16C39/06

Abstract

Vertical and/or lateral acceleration sensors are mounted in or on the engines or pylons of an aircraft to measure the vibrations induced by the operating dynamics of the engines. The sensors provide measured vibration signals to a controller that generates control signals in response to and dependent on the measured vibration signals. The control signals are provided to the aileron actuators, so as to actuate the ailerons appropriately to counteract and thereby reduce the engine-induced vibrations. Thus, the engine-induced vibrations acting on the fuselage are diminished and the passenger flight comfort is significantly improved.

Claims

1. In an aircraft having a fuselage, right and left wings mounted to said fuselage, ailerons mounted on said right and left wings and actuated by respective actuators, and engines mounted by pylons respectively to said right and left wings,

an improvement comprising a system for reducing vibrations induced in said fuselage by operating dynamics of said engines, wherein said system comprises:

a controller including a computer processor;

at least one sensor mounted in or on at least one of said engines or at a forwardmost connection between one of said engines and an associated one of said pylons;

at least one sensor signal conductor line connecting said at least one sensor to said controller; and

at least one control signal conductor line connecting said controller to at least one of said actuators;

wherein said controller generates at least one control signal in response to and dependent on at least one sensor signal provided by said at least one sensor via said at least one sensor signal conductor line, and said at least one control signal is provided via said at least one control signal conductor line to said at least one actuator to control an actuation of said at least one actuator.

2. The system for reducing vibrations in the aircraft according to claim 1, wherein said at least one sensor comprises at least one acceleration sensor.

3. The system for reducing vibrations in the aircraft according to claim 2, wherein said at least one acceleration sensor includes an acceleration sensor with a sensitive axis oriented to sense vibrational accelerations in a vertical direction.

4. The system for reducing vibrations in the aircraft according to claim 3, wherein each said at least one acceleration sensor senses only vibrational accelerations in said vertical direction.

5. The system for reducing vibrations in the aircraft according to claim 2, wherein said at least one acceleration sensor includes an acceleration sensor with a sensitive axis oriented to sense vibrational accelerations in a lateral direction.

6. The system for reducing vibrations in the aircraft according to claim 5, wherein each said at least one acceleration sensor senses only vibrational accelerations in said lateral direction.

7. The system for reducing vibrations in the aircraft according to claim 5, wherein said at least one acceleration sensor further includes an acceleration sensor with a sensitive axis oriented to sense vibrational accelerations in a vertical direction.

8. The system for reducing vibrations in the aircraft according to claim 1, wherein said at least one sensor includes an acceleration sensor mounted in or on a respective one of said engines.

9. The system for reducing vibrations in the aircraft according to claim 1, wherein said at least one sensor includes an acceleration sensor mounted at said forwardmost connection between one of said engines and said associated one of said pylons.

10. The system for reducing vibrations in the aircraft according to claim 1, further comprising at least one additional acceleration sensor mounted in or on said fuselage and connected to said controller by at least one additional sensor signal conductor line.

11. A method of reducing an amplitude of vibrations induced in a fuselage of an aircraft by operating dynamics of engines of said aircraft, comprising the steps:

a) sensing a vibrational acceleration in or on at least one of said engines or on a forwardmost connection between one of said engines and a pylon mounting said one of said engines to a wing of said aircraft, and providing a first sensed acceleration signal corresponding to said vibrational acceleration;

b) executing at least one regulation rule to generate a first control signal responsive to and dependent on said first sensed acceleration signal; and

c) actuating at least one aileron on said wing of said aircraft responsive to and dependent on said first control signal so as to at least partially counteract said vibrational acceleration.

12. The method according to claim 11, wherein said vibrational acceleration is oriented in a vertical direction.

13. The method according to claim 11, wherein said vibrational acceleration is oriented in a lateral direction.

14. The method according to claim 11, wherein said vibrational acceleration includes an acceleration in a vertical direction and an acceleration in a lateral direction, which are both sensed.

15. The method according to claim 11, wherein said steps a), b) and c) are carried out respectively individually and independently for said wing on a right side of said aircraft and for another wing on a left side of said aircraft.

16. The method according to claim 11, wherein said steps a), b), and c) are carried out separately and individually for each one of said engines.

17. The method according to claim 11, further comprising sensing an additional acceleration in or on said fuselage and correspondingly providing an additional sensed signal, and taking said additional sensed signal into account as an additional input in said executing of said at least one regulation rule in said step b).

18. The method according to claim 11, further comprising sensing a second vibrational acceleration in or on a second one of said engines or on a forwardmost connection between said second engine and a second pylon to provide a second sensed acceleration signal corresponding to said second vibrational acceleration, and generating a second control signal that is symmetrical or anti-symmetrical relative to said first control signal by forming sums or differences of said first sensed acceleration signal and said second sensed acceleration signal.

19. The method according to claim 11, wherein said step a) comprises sensing said vibrational acceleration in or on said at least one of said engines.

20. The method according to claim 11, wherein said step a) comprises sensing said vibrational acceleration on said forwardmost connection between said one of said engines and said pylon.