Active landing gear damper

Patent metadata

Field	Value
Publication number	US-10053211-B2
Application number	US-201715637645-A
Country	US
Kind code	B2
Filing date	Jun 29, 2017
Priority date	Feb 24, 2014
Publication date	Aug 21, 2018
Grant date	Aug 21, 2018

Abstract

An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.

First claim

What is claimed is:

1. An aircraft, comprising:
avionics configured to determine aircraft state data;
a terrain database comprising terrain information;
a plurality of landing gear, wherein each landing gear comprises an adjustable damper configured to provide a damping force that opposes motion of a portion of the landing gear relative to an airframe of the aircraft, wherein each adjustable damper comprises:
an adjustable damper valve; and
a motor operable to adjust the damper valve to change a damping coefficient thereof; and

a controller configured to:
calculate, based on at least the determined aircraft state data and the terrain information, one or more predicted impact parameters comprising an aircraft center of gravity at a time of impact;
calculate, based on the one or more predicted impact parameters, a respective target damper force and a respective initial damper velocity for each adjustable damper;
operate the motor of each adjustable damper to adjust the respective damper valves to positions corresponding to damping coefficients that result in the respective target damper forces at the respective initial damper velocities; and
thereafter, operate the motor of each adjustable damper to reduce any difference between actual damper forces and the target damper forces of respective adjustable dampers.

2. The aircraft of claim 1 , wherein the one or more predicted impact parameters further comprises an impact attitude relative to the terrain at the time of impact,
wherein the controller calculates the target damper force based on a target landing gear load factor and the one or more predicted impact parameters, and
wherein the controller calculates the initial damper velocity based on the predicted impact parameters.

3. The aircraft of claim 1 , wherein the aircraft state data comprises at least one of:
pitch, pitch rate, and pitch acceleration data;
roll, roll rate, and roll acceleration data;
yaw, yaw rate, and yaw acceleration data;
a three-dimensional velocity vector;
a three-dimensional acceleration vector;
a position;
an altitude above ground level;
an aircraft weight; and
an aircraft center of gravity.

4. The aircraft of claim 1 , wherein the terrain information comprises at least one of:
terrain elevation;
terrain slope; and
terrain surface type.

5. The aircraft of claim 1 , wherein the motor of each of the plurality of landing gear comprises a continuously adjustable servomotor.

6. The aircraft of claim 1 , further comprising:
a gearbox arranged between the motor and the adjustable damper valve of the adjustable damper of each landing gear,
wherein the gearbox is configured to multiply torque from the motor and apply the multiplied torque to the adjustable valve.

7. The aircraft of claim 1 , wherein each adjustable damper further comprises:
a cylinder defining a damper volume therein; and
a housing arranged at an end of the cylinder, wherein a portion of the housing extends past a wall of the cylinder,
wherein the adjustable damper valve is arranged in the portion of the housing,
wherein the housing defines a channel therein that is in fluid communication with the damper volume and with the adjustable damper valve, and
wherein the damper valve defines a valve channel that is rotatable relative to the channel to provide varying degrees of alignment between the channel and the valve channel, such that rotation of the damper valve changes the damping coefficient of the adjustable damper.

8. The aircraft of claim 1 , wherein the controller is further configured to:
predict an impact event, wherein the target damper force and the initial damper velocity are calculated responsive to predicting the impact event, and
wherein operating the motor of each adjustable damper to reduce any difference between actual damper forces and the target damper forces is performed during the impact event.

9. The aircraft of claim 8 , wherein the controller is further configured to substantially maintain the target damper force for the duration of the impact event.

10. The aircraft of claim 8 , wherein the controller is further configured to:
determine that the impact event is completed responsive to determining that the adjustable damper valve is in a fully-closed position.

11. The aircraft of claim 8 , wherein the adjustable damper further comprises a damper force sensor, and
wherein the controller is further configured to:
determine that the impact event is completed responsive to determining that a force detected by the damper force sensor has not changed in a threshold time period.

12. The aircraft of claim 1 , wherein the one or more predicted impact parameters further comprise at least one of:
a terrain surface type;
an aircraft impact velocity;
an impact attitude relative to the terrain at the time of impact; and
an aircraft gross weight at the time of impact.

13. The aircraft of claim 1 , wherein the one or more predicted impact parameters further comprises a lift generated by the aircraft at the time of impact, and
wherein the target damper force is reduced by the lift.

14. An aircraft, comprising:
an airframe;
a landing gear comprising an adjustable damper configured to provide a damping force that opposes motion of a portion of the landing gear relative to the airframe, wherein the adjustable damper comprises a damper valve and a motor operable to adjust the damper valve to change a damping coefficient thereof; and
a controller configured to:
receive aircraft state data;
receive terrain information from a terrain database;
calculate, based on at least the aircraft state data and the terrain information, one or more predicted impact parameters comprising an impact attitude of the aircraft relative to the terrain at a time of impact;
calculate, based on the one or more predicted impact parameters, a target damper force and an initial damper velocity for the adjustable damper;
operate the motor to adjust the damper valve to a position corresponding to a damping coefficient that results in the target damper force at the initial damper velocity; and
thereafter, operate the motor to reduce any difference between an actual damping force and the target damper force.

15. The aircraft of claim 14 , wherein the controller is further configured to:
predict an impact event, wherein the target damper force and the initial damper velocity are calculated responsive to predicting the impact event, and
wherein operating the motor to reduce any difference between an actual damper forces and the target damper force is performed during the impact event.

16. The aircraft of claim 15 , wherein the controller is further configured to substantially maintain the target damper force for the duration of the impact event.

17. The aircraft of claim 15 , wherein the controller is further configured to:
determine that the impact event is completed responsive to determining that the adjustable damper valve is in a fully-closed position.

18. The aircraft of claim 15 , wherein the adjustable damper further comprises a damper force sensor, and
wherein the controller is further configured to:
determine that the impact event is completed responsive to determining that a force detected by the damper force sensor has not changed in a threshold time period.

19. The aircraft of claim 14 , wherein the one or more predicted impact parameters further comprises a lift generated by the aircraft at the time of impact, and
wherein the target damper force is reduced by the lift.

Assignees

• Boeing Co

Inventors

• Birchette Terrence S
• Bolukbasi Akif O

Classifications

• B64C25/58 Primary

  Arrangements or adaptations of shock-absorbers or springs (shimmy-dampers B64C25/50) · CPC title

• B64C25/60 Primary

  Oleo legs · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title