Apparatus and method of preventing ground resonance of aircraft

Patent metadata

Field	Value
Publication number	US-12503222-B2
Application number	US-202418595634-A
Country	US
Kind code	B2
Filing date	Mar 5, 2024
Priority date	Oct 4, 2023
Publication date	Dec 23, 2025
Grant date	Dec 23, 2025

Abstract

An apparatus and method of preventing ground resonance of an aircraft, in which ground resonance may be prevented by detecting vibrations caused by rotation of a rotor in the aircraft and adjusting stiffness and damping performance of a landing gear, are provided. The apparatus for preventing ground resonance of an aircraft includes a at least one sensor for monitoring rolling of a fuselage of the aircraft according to rotation of a rotor; a vibration sensing unit installed on the fuselage and detecting vibrations of the fuselage; a damper installed on the fuselage, constituting landing gear, and varying a natural frequency of the fuselage; and a control unit controlling stiffness of the damper based on a phase difference between vibration signals and the rolling of the fuselage.

First claim

What is claimed is:

1 . An apparatus for preventing ground resonance of an aircraft, comprising:
at least one sensor configured to monitor rolling, of a fuselage of the aircraft; a vibration sensor installed on the fuselage and configured to detect vibrations of the fuselage; a damper installed in landing gear of the aircraft and configured to vary a natural frequency of the fuselage; and a controller configured to control a stiffness of the damper based on:
a phase difference between vibration signals from the vibration sensor, and
the monitored rolling of the fuselage.

2 . The apparatus of claim 1 , wherein the damper comprises,
a cylinder having a hollow shape; a piston, having a hollow shape, configured to be partially inserted into a first end of the cylinder and to move in a reciprocating linear motion relative to the cylinder; a magnetic force generator disposed on the piston and comprising a coil wound to generate, based on application of power to the coil, a magnetic field within the piston; and a magnetorheological fluid inside the cylinder and the piston, having viscosity configured to change based on the magnetic field generated by the coil.

3 . The apparatus of claim 2 , wherein the damper further comprises,
a metering pin fixed to a second end of the cylinder and protruding toward the first end, of the cylinder, and toward an end of the piston inserted into the cylinder, wherein the metering pin has a tapered shape that tapers away from the second end of the cylinder; an orifice portion fixed to the end of the piston, wherein a hole formed in the orifice portion is configured to:
accept insertion of the metering pin thereinto, and
allow the magnetorheological fluid to flow through a gap between the hole and the metering pin; and
a separator movably disposed inside the piston to divide an internal space of the piston into a first space and a second space, wherein the first space is filled with the magnetorheological fluid moved from the cylinder, and the second space is filled with a buffer fluid.

4 . The apparatus of claim 2 , wherein the controller is communicatively connected to the at least one sensor, the vibration sensor and a power source, and is configured to:
based on a determination that ground resonance has occurred, apply power from the power source to the coil to cause the magnetic force generator generate a magnetic field in the magnetic force generator to change the viscosity of the magnetorheological fluid so as to control the stiffness of the damper and the vibrations of the fuselage.

5 . The apparatus of claim 1 , wherein the at least one sensor is configured to monitor the rolling of the fuselage by continuously detecting, based on data from an inertial navigation system installed in the fuselage, a roll angle of the fuselage.

6 . The apparatus of claim 1 , wherein the vibration sensor comprises,
a first acceleration sensor configured to detect vibrations, of the fuselage, at a first location on the fuselage, and a second acceleration sensor configured to detect vibrations, of the fuselage, at a second location on the fuselage.

7 . The apparatus of claim 6 , wherein the vibration sensor is configured to determine, based on whether a phase difference between a first vibration signal, output from the first acceleration sensor, and a second vibration signal, output from the second acceleration sensor, converges, whether ground resonance occurred.

8 . The apparatus of claim 7 , wherein the controller comprises a timer, and
wherein the controller is configured to stop, based on the phase difference not converging after a predetermined time has elapsed, an operation of a rotor or the aircraft.

9 . A method of preventing ground resonance of an aircraft, the method comprising:
monitoring, based on the aircraft being in contact with a ground via landing gear and based on a rotor of the aircraft rotating, rolling of a fuselage of the aircraft; detecting vibrations of the fuselage; analyzing, based on the fuselage rolling at an angle satisfying a predetermined critical angle, vibration signals based on the detected vibrations; and based on the analyzed vibration signals indicating that ground resonance occurred, increasing a stiffness of a damper of the landing gear.

10 . The method of claim 9 , wherein the monitoring the rolling of the fuselage comprises detecting, based on data from an inertial navigation system, a roll angle of the fuselage and determining whether the roll angle satisfies the predetermined critical angle.

11 . The method of claim 9 , wherein the analyzing the vibration signals comprises determining whether a phase difference between a first vibration signal, of the vibration signals and output by a first acceleration sensor mounted at a first location on the fuselage, and a second vibration signal, of the vibration signals and output by a second acceleration sensor mounted at a second location on the fuselage, diverges or converges, wherein the analyzed vibration signals diverging indicate that the ground resonance occurred.

12 . The method of claim 9 , wherein the damper comprises,
a magnetic force generator comprising a coil wound to generate, based on application of a power from a power source, a magnetic field; and a magnetorheological fluid having viscosity configured to change based on the magnetic field generated by the magnetic force generator, wherein the increasing the stiffness of the damper comprises controlling the power source to apply the power to the coil to change the viscosity of the magnetorheological fluid.

13 . The method of claim 9 , further comprising:
based on a determination that the ground resonance is not occurring, preparing the aircraft for takeoff; and based on a Weight-On-Wheel (WOW) signal not being received, terminating control to prevent the ground resonance.

14 . The method of claim 9 , further comprising, based a predetermined time elapsing from a first time at which the analyzed vibration signals indicated that the ground resonance occurred, stopping an operation of the rotor.

Assignees

• Hyundai Motor Co Ltd
• Kia Corp

Inventors

• Kim Choung Hyoung
• Lee Jung Hyun
• Hwang Eu Gene

Classifications

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title

• G01H1/14

  Frequency · CPC title

• F16F9/0281

  Details · CPC title

• F16F9/0227

  characterised by the piston construction · CPC title

• F16F9/535

  Magnetorheological [MR] fluid dampers (springs comprising magnetorheological [MR] elastomers F16F1/361) · CPC title