Aircraft with active support

Patent metadata

Field	Value
Publication number	US-11198503-B2
Application number	US-201816210699-A
Country	US
Kind code	B2
Filing date	Dec 5, 2018
Priority date	Dec 8, 2017
Publication date	Dec 14, 2021
Grant date	Dec 14, 2021

Abstract

An aircraft is disclosed having a structure at least part of which is capable of generating aerodynamic lift. A body having a mass is movably mounted to a portion of the structure by an active support. The active support includes an actuator to move the body relative to the portion of the structure, and a controller for controlling movement of the actuator in response to a dynamic input. The active support provides a range of movement for the body in at least one degree of freedom. The actuator moves the body across the entire range of movement in that one degree of freedom in a time period of less than 3 seconds. The actuator moves the body sufficiently rapidly to generate an inertial force that is equal to or greater than any aerodynamic force generated by the body during that movement of the body. The active support may be used to reduce loads on the aircraft structure.

First claim

The invention claimed is:

1. An aircraft comprising a structure at least part of which is capable of generating aerodynamic lift, and a body exposed to airflow over the aircraft and having a mass movably mounted to a tip end of a wing of the structure by an active support,
wherein the active support includes an actuator configured to move the body relative to the tip end of the wing of the structure, and a controller for controlling movement of the actuator in response to a dynamic input,
wherein the active support is configured to provide a range of movement for the body in at least one degree of freedom, and the actuator is configured to move the body across the entire range of movement in said at least one degree of freedom in a time period of less than 3 seconds, and
wherein the controller is configured to control the movement of the actuator to move the body sufficiently rapidly to generate an inertial force that is equal to or greater than the aerodynamic force generated by the body on the body during that movement of the body.

2. An aircraft according to claim 1 , wherein the body includes one or more of: a wing tip fuel tank, auxiliary fuel tank, podded fuel tank, a main engine, an auxiliary power unit, a landing gear, a wing tip device or payload of the aircraft.

3. An aircraft according to claim 1 , wherein the dynamic input is a signal from a sensor mounted to the aircraft.

4. An aircraft according to claim 3 , wherein the sensor is one or more of: an air pressure sensor, a position sensor, an accelerometer, an air densitometer, an angle of attack vane or strain gauge.

5. An aircraft according to claim 1 , wherein the active support is configured to provide a range of movement for the body in up to six degrees of freedom.

6. An aircraft according to claim 1 , wherein the mass of the body is substantially constant.

7. An aircraft according to claim 6 , wherein the mass of the body is substantially constant either during the 3 second time period or for at least a duration of greater than the 3 second time period.

8. An aircraft according to claim 1 , wherein the dynamic input is representative of an aerodynamic load or a ground load acting on the aircraft, or of an unbalanced dynamic load generated by a part of the aircraft.

9. An aircraft according to claim 1 , wherein the dynamic input is an aerodynamic gust load.

10. An aircraft according to claim 1 , wherein the controller is configured to provide loads alleviation for the structure of the aircraft.

11. An aircraft according to claim 1 , wherein the aircraft has a passenger cabin, and the controller is configured to reduce the magnitude of external loads on the structure that are imparted to the passenger cabin.

12. An aircraft according to claim 1 , wherein the aircraft is a fixed or rotary wing aircraft.

13. The aircraft of claim 1 , wherein the mass is directly movably mounted to the tip end of the wing.

14. The aircraft of claim 1 , wherein the dynamic input is representative of a load acting on the aircraft, and wherein the actuator is configured to move the body sufficiently rapidly to generate an inertial force so as to counteract the load acting on the aircraft.

15. A method of reducing loads on an aircraft structure having at least a part capable of generating aerodynamic lift, and a body exposed to airflow over the aircraft and having a mass movably mounted to a tip end of the wing of the structure by an active support, wherein the active support includes an actuator configured to move the body relative to the tip end of the wing of the structure, wherein the active support is configured to provide a range of movement for the body in at least one degree of freedom, and the actuator is configured to move the body across the entire range of movement in said at least one degree of freedom in a time period of less than 3 seconds,
the method comprising moving the body relative to the tip end of the wing of the structure in response to a dynamic input and sufficiently rapidly to generate an inertial force equal to or greater than the aerodynamic force generated by the body on the body during that movement of the body.

16. A method according to claim 15 , wherein the dynamic input is representative of an aerodynamic load or a ground load acting on the aircraft, or of an unbalanced dynamic load generated by a part of the aircraft.

17. A method according to claim 15 , wherein the dynamic input is an aerodynamic gust load sensed a distance in front of and/or at any point on the aircraft.

18. A method according to claim 15 , which provides loads alleviation for the structure of the aircraft.

19. A method according to claim 15 , wherein the aircraft has a passenger cabin, and the method reduces the magnitude of external loads on the structure that are imparted to the passenger cabin.

20. A method according to claim 15 , wherein the dynamic input is either received from a sensor forming part of a loads alleviation system coupled to one or more flight control surfaces of the aircraft or is a pilot controlled input.

21. The method of claim 15 , wherein the mass is directly movably mounted to the tip end of the wing.

22. The method of claim 15 , wherein the dynamic input is representative of a load acting on the aircraft, and wherein moving the body relative to the tip end of the wing counteracts the load acting on the aircraft.

Assignees

• Airbus Operations Ltd

Inventors

• Gambioli Francesco
• Edwards Henry

Classifications

• Y02T50/40

  Weight reduction · CPC title

• B64C5/08

  mounted on, or supported by, wings · CPC title

• G05D1/83

  Limitation of acceleration or structural stress · CPC title

• B64C13/16 Primary

  actuated automatically, e.g. responsive to gust detectors · CPC title

• B64D27/04

  of piston type · CPC title