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Automatic dual rotor speed control for helicopters

A technology for helicopters and speed controllers, which is applied in electric speed/acceleration control, altitude or depth control, non-electric variable control, etc., can solve the problem of increasing the noise level of the helicopter, increasing the main rotor and tail Rotor speed etc.

Inactive Publication Date: 2009-07-29
SIKORSKY AIRCRAFT CORP
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  • Summary
  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

More specifically, it is known to design a helicopter with a flight control system that reduces / increases the main and tail rotors when manually activated / deactivated by the pilot speed, thereby reducing / increasing the noise level of the helicopter

Method used

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  • Automatic dual rotor speed control for helicopters
  • Automatic dual rotor speed control for helicopters
  • Automatic dual rotor speed control for helicopters

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Embodiment Construction

[0015] Referring to the drawings and in particular to FIG. 1 , a flight control system according to the invention is indicated generally at 10 and is shown configured for a helicopter (not shown) having two engines. Advantageously, flight control system 10 includes an automatic rotor speed controller 12 resident thereon.

[0016] Rotor speed controller 12 is configured to automatically transition the helicopter's main and tail rotors from high to low speeds based on one or more types of received flight information. In this way, the flight control system 10 with the rotor speed controller 12 can transition to and from the low noise mode of operation without any action from the pilot.

[0017] Flight control system 10 includes a full authority digital engine controller (FADEC) 14 for each engine. Preferably, flight control system 10 includes a primary FADEC 14a and a secondary FADEC 14b for each engine. Controller 12 resides on each FADEC 14 .

[0018] The remainder of the fl...

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PUM

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Abstract

A flight control system for a helicopter having a main rotor and a tail rotor is provided. The flight control system includes an automatic rotor speed control being configured to transition the main rotor and the tail rotor between a high speed and a low speed based upon a plurality of received information without requiring any pilot action, the plurality of received information comprising height above ground level, knot indicated air speed, outside air temperature, barometric altitude, pressure altitude, density altitude, and an engine operational status.

Description

[0001] Cross References to Related Applications [0002] This application claims the benefit of US Provisional Application No. 60 / 726,883, filed October 3, 2006, the contents of which are incorporated herein by reference. technical field [0003] The invention relates to helicopter rotor speed control. More specifically, the present invention relates to automatic dual rotor speed control that automatically shifts between high and low rotor speeds based on received flight information. Background technique [0004] Many helicopters include a main rotor and a tail rotor integrally connected together and driven by one or more engines. One known method for reducing the noise level of a helicopter is to reduce the speed of the main and tail rotors. That is, it is known in the art to design a helicopter with a system that includes a transmission that enables the pilot to manually change the speed of the main and tail rotors from normal mode (e.g., high rotor speed) to quiet mod...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C11/00B64C27/54
CPCG05D1/0858B64C27/57G05D1/06G05D13/62
Inventor G·W·巴恩斯E·F·霍尔伯里E·W·雅各布斯K·J·布克曼
Owner SIKORSKY AIRCRAFT CORP
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