Method and a device for moving the center of gravity of an aircraft

Patent metadata

Field	Value
Publication number	US-11040768-B2
Application number	US-202016821194-A
Country	US
Kind code	B2
Filing date	Mar 17, 2020
Priority date	Mar 18, 2019
Publication date	Jun 22, 2021
Grant date	Jun 22, 2021

Abstract

An adjustment device for adjusting the position of the center of gravity of an aircraft, the aircraft having at least two thrust production units that contribute at least to providing the aircraft with lift, the adjustment device comprising at least one heavy member that is movable relative to an airframe of the aircraft and also at least one actuator for causing the heavy member to move. The adjustment device includes an avionics system configured to detect a failure of any one of the thrust production units and, in the presence of such a failure, to control the at least one actuator to cause the heavy member to move.

First claim

What is claimed is:

1. An adjustment device for adjusting the position of the center of gravity of an aircraft, the aircraft having at least two thrust production units that contribute at least to providing the aircraft with lift, the adjustment device comprising at least one heavy member that is movable relative to an airframe of the aircraft, the adjustment device comprising at least one actuator for causing the heavy member to move; the at least one actuator controlled to move the heavy member in the presence of a failure of at least one thrust production unit,
wherein the adjustment device includes an avionics system configured to detect the failure of any one of the thrust production units and, in the presence of the failure of at least one thrust production unit, to control the at least one actuator to cause the heavy member to move, the at least one actuator comprising at least one resilient member and a blocker, the blocker controlled by the avionics system to act directly or indirectly to prevent the resilient member from moving in the absence of the failure of at least one thrust production unit.

2. The adjustment device according to claim 1 ; wherein the heavy member includes at least one electrical energy storage member.

3. The adjustment device according to claim 1 ;
wherein the adjustment device includes a respective heavy member fastened in proximity to each thrust production unit, each heavy member carried by a slide that is movable in translation, the adjustment device including a respective said actuator for each slide, the actuator connected to a slide to move the slide in translation.

4. An aircraft having an airframe, the airframe carrying at least two thrust production units that contribute at least to providing the aircraft with lift;
wherein the aircraft includes an adjustment device for adjusting the position of the center of gravity of the aircraft, the adjustment device comprising at least one heavy member that is movable relative to the airframe of the aircraft, the adjustment device comprising at least one actuator for causing the heavy member to move; the at least one actuator controlled to move the heavy member in the presence of a failure of at least one thrust production unit,
wherein the adjustment device includes an avionics system configured to detect the failure of any one of the thrust production units and, in the presence of the failure of at least one thrust production unit, to control the at least one actuator to cause the heavy member to move, the at least one actuator comprising at least one resilient member and a blocker, the blocker controlled by the avionics system to act directly or indirectly to prevent the resilient member from moving in the absence of the failure of at least one thrust production unit.

5. A method of stabilizing the aircraft according to claim 4 , the aircraft having at least two thrust production units, each thrust production unit contributing at least to providing the aircraft with lift;
wherein the method comprises the following steps:
detecting by using the avionics system the failure of a thrust production unit; and
as a result of detecting the failure of a thrust production unit, movement by using the at least one actuator under the control of a heavy member to move from a current position to an emergency position in order to modify the position of the center of gravity of the aircraft.

6. The method according to claim 5 ; wherein each thrust production unit comprises two rotor systems, each rotor system comprising both a rotor and also a rotor provided with a plurality of blades, and wherein detecting the failure of a thrust production unit includes a step of detecting the failure of either one of the two rotor systems.

7. The method according to claim 5 ; wherein the emergency position is a stored position depending on the thrust production unit that has failed.

8. The method according to claim 5 ; wherein the method includes a step of calculating with the avionics system the emergency position as a function of a stored model while taking into consideration at least the thrust production unit that has failed.

9. The method according to claim 8 ; wherein the stored model takes into consideration at least the weight of a payload on board the aircraft or the speed of advance of the aircraft.

10. The method according to claim 5 ; wherein a respective heavy member is fastened in proximity to each thrust production unit, the movement comprising a step of causing the heavy member situated in proximity to the thrust production unit that has been detected as failing to move towards a center of the aircraft, or a step of causing the heavy member that is situated in proximity to a thrust production unit opposite from the thrust production unit that has been detected as failing to move away from the center.

11. An adjustment device for adjusting the position of the center of gravity of an aircraft having at least two thrust production units that contribute at least to providing the aircraft with lift, the adjustment device comprising at least one heavy member movable relative to an airframe of the aircraft, the adjustment device comprising an actuator capable of causing the heavy member to move upon a failure of at least one thrust production unit,
the adjustment device including an avionics system configured to detect the failure of any one of the thrust production units and, upon the failure of at least one of the thrust production units, to control the actuator to cause the heavy member to move, the actuator comprising a resilient member and a blocker, the blocker controllable by the avionics system to prevent the resilient member from moving in the absence of the failure of at least one thrust production unit.

12. The adjustment device according to claim 11 ; wherein the heavy member includes an electrical energy storage member.

13. The adjustment device according to claim 11 ; wherein the adjustment device includes a respective heavy member fastened in proximity to each of the thrust production units.

14. The adjustment device according to claim 11 ; wherein each of the heavy members is carried by a slide movable in translation.

15. The adjustment device according to claim 14 ; wherein the adjustment device including a respective actuator connected to one of the slides to move each of the respective one of the slides in translation.

Assignees

• Airbus Helicopters

Inventors

• Bailly Stephane

Classifications

• B64U2201/00

  UAVs characterised by their flight controls · CPC title

• B64U2101/61

  for transporting passengers · CPC title

• B64U40/20

  for in-flight adjustment of the base configuration · CPC title

• B64U50/19

  using electrically powered motors · CPC title

• B64U10/13

  Flying platforms · CPC title