Method of assisting piloting, piloting assistance means, and a piloting assistance device for a rotorcraft using said piloting assistance means to implement said piloting assistance method

• US 8,342,455 B2
• Filed: 06/14/2010
• Issued: 01/01/2013
• Est. Priority Date: 06/16/2009
• Status: Active Grant

• Current Assignee: Airbus Helicopters
• Original Assignee: Eurocopter
• Inventors: Allieta, Jean-Marie, Honnorat, Olivier, Chaduc, Bruno, Lafisse, Jean-Francois
• Primary Examiner(s): Collins, Timothy D
• Assistant Examiner(s): Stehle, Jamie S
• Application Number:
  US12/814,687
• Publication Number:
  US 20110031346A1
• Time in Patent Office: 932 Days
• Field of Search: 244/17.11, 244/17.13, 244/17.25, 244/194, 244/195
• US Class Current: 244/194
• CPC Class Codes: B64C 27/56 characterised by the control initiating means, e.g. manually actuated
• CPC Class Codes: B64C 27/68 using electrical energy, e.g. having electrical power amplification

Abstract

The present invention relates to a device and method of assisting the piloting of a rotorcraft, the rotorcraft having a flight control (10) for controlling a rotor (20, 21) via at least one linkage (35), during which method an additional force is generated by at least one piloting assistance means (100) mechanically linked to the linkage (35), the additional force being a function of the position of the flight control (10) and of an instantaneous force as measured on the linkage (35).

Claims

1. A method of assisting the piloting of a rotorcraft, the rotorcraft having a flight control for controlling a rotor via at least one linkage, in which method, in order to generate an additional force with the help of piloting assistance means arranged in parallel with the linkage and also as a function of a setpoint force relating to the position of the flight control and an instantaneous force as measured on the linkage, the following steps are performed:

measuring in real time an instantaneous force exerted on the linkage;

measuring the position of the flight control;

using at least one pre-established force relationship to determine a setpoint force that ought to be felt by the pilot operating the flight control when the flight control is at the measured position, and then determining the additional force to be equal to the difference between the setpoint force and the instantaneous force; and

determining the setpoint current to deliver to the piloting assistance means in order to cause the piloting assistance means to generate the additional force, and then electrically powering the piloting assistance means in compliance with the setpoint current.

2. A method according to claim 1, wherein the pre-established force relationship is changed as a function of flying conditions.

3. A method according to claim 1, wherein, for the piloting assistance means comprising at least one electric motor suitable for acting on the linkage to generate the additional force, the method comprises the steps of:

measuring the speed of rotation of the electric motor by differentiating the angular position of the electric motor; and

changing the force relationship as a function of the speed of rotation.

4. A method according to claim 1, wherein, for the rotorcraft being provided with a power plant driving the rotor via a gearbox, with utilization limits being imposed for the power plant or the gearbox, or the power plant and the gear box, the method consists in changing the force relationship on reaching one of the limitations by changing from a force relationship having shallow slope to a force relationship having a steep slope.

5. A method according to claim 1, wherein, for piloting assistance means having a plurality of connection plugs suitable for receiving a plurality of different connectors of the rotorcraft, the method consists in the piloting assistance means determining said at least one force relationship as a function of which plugs are connected to a connector.

6. A method according to claim 1, wherein for the additional force being generated with the help of at least one brushless electric motor of the piloting assistance means, the method consists in disconnecting the electric motor as soon as said electric motor'"'"'s electricity consumption exceeds an operating threshold.

7. A method according to claim 1, wherein the setpoint current for supplying to the piloting assistance means is determined by using a broadband vector control.

8. A method according to claim 1, wherein, for the rotorcraft including autopilot means suitable for controlling at least one series actuator in the linkage, the method including the step of using the piloting assistance means to anchor the flight control dynamically when the autopilot means operate the series actuator.

9. A method according to claim 1, wherein, for the rotorcraft including autopilot means suitable for controlling the piloting assistance means, if a pilot operates the control means so as to modify the instantaneous force by a predetermined value, the method consists in disengaging the autopilot means so that the autopilot means no longer control the piloting assistance means.

10. A method according to claim 1, wherein, for the rotorcraft including autopilot means suitable for controlling the piloting assistance means, the method consists in an emergency mode in the autopilot means controlling the piloting assistance means to perform a stabilizing function.

11. A method according to claim 1, including the following steps:

determining a force generated by the piloting assistance means using a pre-established electricity consumption relationship giving the generated force as a function of the electricity consumption of the piloting assistance means;

determining a real friction force equal to the difference between an instantaneous force exerted on the linkage as measured in real time and the generated force;

determining an ideal friction force for the linkage using a pre-established friction relationship; and

signaling an anomaly when the real friction force exceeds the ideal friction force by a given threshold.

12. A method according to claim 1, wherein, for the piloting assistance means including an electric motor controlled by control means, the control means being provided with a main computer unit and with a monitoring computer unit, each determining the additional force, the method consists in deactivating the piloting assistance means if the additional force as determined by the main computer unit differs from the additional force as determined by the monitoring computer unit.