Method and an aircraft for minimizing the risks of the aircraft toppling on the ground

Patent metadata

Field	Value
Publication number	US-9796470-B2
Application number	US-201314024756-A
Country	US
Kind code	B2
Filing date	Sep 12, 2013
Priority date	Sep 13, 2012
Publication date	Oct 24, 2017
Grant date	Oct 24, 2017

Abstract

A method of assisting a pilot in order to minimize the risks of an aircraft rolling over on the ground, the aircraft having a main rotor and a yaw movement control rotor ( 4 ), together with lateral cyclic pitch control means for the main rotor and yaw movement control means for the yaw movement control rotor. At least one measurement is taken relating to left forces exerted on a left side undercarriage and to right forces exerted on a right side undercarriage in order to evaluate asymmetry, if any, between the left and right forces, and then a recommended position ( 26 ) is determined for at least one of the yaw and lateral cyclic pitch control means in order to make the left and right forces more symmetrical. Each recommended position is displayed on a display unit.

First claim

What is claimed is:

1. A method of assisting a pilot to minimize the risk of an aircraft rolling over on the ground, the aircraft having a main rotor and a yaw movement control rotor, the aircraft having controls including a lateral cyclic pitch control to control the main rotor and a yaw movement control to control the yaw movement control rotor, the aircraft having landing gear provided with at least one left side undercarriage and at least one right side undercarriage that are arranged on either side of an anteroposterior longitudinal plane of the aircraft, wherein during a utilization stage the following steps are performed:
taking at least one measurement relating to the left forces exerted on the left side undercarriage and to the right forces exerted on the right side undercarriage in order to evaluate asymmetry, if any, between the left and right forces;
when the at least one measurement reveals asymmetry between the left and right forces, determining a recommended position for at least one of the yaw movement control and lateral cyclic pitch control in order to make the left and right forces more symmetrical; and
using a display unit to display each recommended position to inform the pilot of the position to be reached by at least one of the yaw movement control and the lateral cyclic pitch control in order to keep the aircraft within a domain of roll stability on the ground.

2. A method according to claim 1 , wherein during an initialization stage the influence of the yaw movement control and lateral cyclic pitch control on the asymmetry of the left and right forces is determined in order to establish at least one database providing the at least one recommended position for making the left and right forces more symmetrical, the database being used to determine each recommended position during the utilization stage.

3. A method according to claim 2 , wherein:
during the initialization stage, the influence of the yaw movement control and lateral cyclic pitch control on the asymmetry of the left and right forces is determined as a function of the speed of rotation of the main rotor and/or of the yaw movement control rotor; and
during the utilization stage, at least one measurement is taken relating to the left forces exerted on the left side undercarriage and to the right forces exerted on the right side undercarriage, and at least one measurement is taken relating to each speed of rotation taken into consideration during the initialization stage.

4. A method according to claim 1 , wherein with a recommended position for at least one of the controls being determined and displayed, a current position is determined of each controls for which a position is recommended, and the current position is displayed on the display unit.

5. A method according to claim 1 , wherein, in order to display a recommended position for the lateral cyclic pitch control and for the yaw movement control, a single symbol is displayed in a two-dimensional representation in which the dimensions relate respectively to the position of the lateral cyclic pitch control and to the position of the yaw movement control.

6. A method according to claim 1 , wherein priority is given to a single flight control for keeping the aircraft in the stable domain by displaying a recommended position on a scale either for the lateral cyclic pitch control or for the yaw movement control depending on the movement of the aircraft relative to the ground.

7. A method according to claim 6 , that is determined whether the aircraft is taxiing on the ground, and if the aircraft is taxiing, a recommended position is displayed solely for the lateral cyclic pitch control.

8. A method according to claim 6 , that is determined whether the aircraft is taxiing on the ground, and if the aircraft is not taxiing, a recommended position is then displayed solely for the yaw movement control.

9. A method according to claim 1 , wherein the at least one measurement relating to the left forces exerted on the left side undercarriage and to the right forces exerted on the right side undercarriage is performed indirectly by determining a roll angle of the aircraft.

10. A method according to claim 9 , wherein the following steps are performed:
determining an initial roll angle before starting the rotors of the aircraft;
determining a current roll angle of the aircraft over time; and
determining a recommended position for at least one of the yaw movement control and lateral cyclic pitch control and displaying it on the display unit so that the current roll angle tends towards the initial roll angle.

11. A method according to claim 10 , wherein the following steps are performed:
determining an initial roll angle before starting the rotors of the aircraft over a given period of time in order to determine a maximum initial roll angle and a minimum initial roll angle reached during the period; and
inhibiting the display of each recommended position when the difference between the maximum initial roll angle and the minimum initial roll angle exceeds a threshold difference.

12. A method according to claim 1 , wherein at least one measurement relating to the left forces exerted on the left side undercarriage and to the right forces exerted on the right side undercarriage is performed directly in order to evaluate said asymmetry by determining the forces exerted on the left undercarriage and on the right undercarriage by using measurement means arranged on each undercarriage.

13. A method according to claim 12 , wherein said at least one measurement relating to the left forces exerted on the left side undercarriage and to the right forces exerted on the right side undercarriage is performed directly in order to determine whether asymmetry exists by applying at least one of the following methods:
the left and right forces are determined by means for measuring forces proper;
the left and right forces are determined by devices for measuring pressure by measuring the pressure within a shock absorber in each undercarriage; and
the left and right forces are determined by devices for measuring position by measuring the position of at least one movable member of each undercarriage.

14. A method according to claim 1 , wherein potential asymmetry of loading is evaluated by taking a single measurement relating to the left forces exerted on the left side undercarriage and to the right forces exerted on the right side undercarriage, by applying at least one of the following methods:
measuring a pressure difference between a pressure existing within a shock absorber of a right undercarriage and a pressure existing within a shock absorber in a left undercarriage; and
measuring a position difference between a position of at least one movable member of a right undercarriage and a position of at least one movable member of a left undercarriage.

15. A method according to claim 1 , wherein an alert is triggered when the at least one measurement relating to the left forces exerted on the left side undercarriage and to the right forces exerted on the right side undercarriage reveal asymmetry between the left and right forces that exceeds a certain threshold.

16. An aircraft having a main rotor and a yaw movement control rotor, the aircraft having controls including a lateral cyclic pitch control to control the main rotor and a yaw movement control to control the yaw movement control rotor, the aircraft including landing gear having at least one left side undercarriage and at least one right side undercarriage that are arranged on either side of an anteroposterior longitudinal plane of the ai

Assignees

• Airbus Helicopters

Inventors

• Dequin Andre-Michel

Classifications

• B64D43/00 Primary

  Arrangements or adaptations of instruments · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64C27/57 Primary

  automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust · CPC title