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Method and a device for assisting the piloting of an aircraft, and an aircraft

A technology for assisting driving and aircraft, applied in the field of rotorcraft, which can solve the problems of pilots being disturbed

Active Publication Date: 2012-10-17
EUROCOPTER
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

While this would be advantageous, it should be understood that even when the pilot is not acting on the control levers used to control the blade pitch of the main rotor, the pilot will still be affected when observing changes in the limits. interference

Method used

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  • Method and a device for assisting the piloting of an aircraft, and an aircraft
  • Method and a device for assisting the piloting of an aircraft, and an aircraft
  • Method and a device for assisting the piloting of an aircraft, and an aircraft

Examples

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Embodiment Construction

[0080] Elements appearing in more than one figure bear the same reference numerals in each figure.

[0081] figure 1 Shown is an aircraft 1 provided with a first rotor 5 having a plurality of first blades 6 with a first variable collective pitch and a second rotor 7 having a first rotor with a first Two plurality of second blades 8 with variable collective pitch.

[0082] By way of example, the aircraft 1 is a helicopter, the first rotor represents the main lift and propulsion rotor of the helicopter, and the second rotor represents the tail rotor of the helicopter.

[0083] The aircraft 1 also has a first control system 80 and a second control system 82, the first control system comprising a first control 81 of the lever type, for example to control the collective pitch to allow the pilot to control the first collective pitch, while the second control The system includes a second control 83 of the pedal type to allow the pilot to control the second collective pitch.

[008...

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PUM

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Abstract

A method of assisting the piloting of an aircraft (1) comprising a first rotor (5) having a plurality of first blades (6) with a first variable collective pitch, and a second rotor (7) having a plurality of second blades (8) with a second variable collective pitch. According to the method, a computer determines a power limit curve (70) and displays said limit curve (70) in a diagram (60) to inform the pilot of the first and second collective pitch margins available before reaching the limits of at least one operating rating of the power plant of the aircraft.

Description

technical field [0001] This application originates from French patent application FR11 / 00936 filed on March 30, 2011, the contents of which are incorporated herein by reference. [0002] The present invention relates to methods and devices for assisting the piloting of aircraft, and also to aircraft, in particular rotorcraft provided with main lift and propulsion rotors and a tail rotor for providing yaw control. Background technique [0003] Rotorcraft are generally provided with a power plant comprising at least one engine, for example a turboshaft engine of the free-turbine type. That is, power is drawn from the low pressure stage of each free turbine rotating substantially in the range of 20,000 revolutions per minute (rpm) to 50,000 rpm. Therefore, since the rotational speed of said rotors is substantially in the range of 200 rpm to 400 rpm, the power plant comprises a reduction gearbox for connecting the free turbine to the main thrust and lift rotors; this gearbox is...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/04B64C27/28B64D43/00
CPCG01D7/10B64D35/04B64D43/00G01D2207/10B64D45/00G01C23/00G06F3/14B64C27/00
Inventor A·科尔普龙S·佩迪特
Owner EUROCOPTER
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