Device for reducing line noise inside a rotary-wing aircraft, especially a helicopter
First Claim
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1. A rotary-wing aircraft, comprising:
- an engine;
a main gearbox;
a drivetrain;
a flight deck;
a fuselage;
a number of sensors for measuring the values of at least one vibrational and/or acoustic parameter representing a vibrational and/or acoustic effect of at least one source of noise of said aircraft;
a number of mechanical means which can be controlled and capable of creating a force capable of reducing the vibrational and/or acoustic effect of said source of noise; and
a single control unit for controlling said mechanical means on the basis of the values measured by said sensors, wherein said sensors are fixed to at least some of the following parts of said aircraft;
a mount for fixing said engine to said fuselage of said aircraft;
a bearing in said drivetrain;
a bar for fixing said main gearbox to said fuselage;
a mechanical suspension of said main gearbox;
said fuselage of said aircraft;
a device for fixing lining panels of said aircraft; and
a panel for lining said flight deck, wherein the aircraft comprises P sensors Cp arranged at points Mp, P being a predefined integer and p being an integer between 1 and P, which sensors are capable of measuring one same vibrational and/or acoustic parameter, and Q mechanical means Aq, Q being a predefined integer and q being an integer between 1 and Q, these means being capable respectively of creating forces capable of reducing one same vibrational and/or acoustic effect, and wherein said control unit repeatedly performs the following succession of operations;
it calculates, for each of said P sensors Cp, a value PIp that satisfies the equation;
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Abstract
The present invention relates to a device for reducing the noise inside a rotary-wing aircraft, especially a helicopter.
According to the invention, said device (1) comprises at least one sensor (Ca, Cb) for measuring the values of at least one vibrational and/or acoustic parameter representing a vibrational and/or acoustic effect of at least one source of noise, at least one mechanical means (A) that can be controlled and is capable of creating a force capable of reducing said vibrational and/or acoustic effect, and a control unit (UC) for controlling the mechanical means (A), on the basis of the values measured by the sensor (Ca, Cb).
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Citations
13 Claims
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1. A rotary-wing aircraft, comprising:
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an engine;
a main gearbox;
a drivetrain;
a flight deck;
a fuselage;
a number of sensors for measuring the values of at least one vibrational and/or acoustic parameter representing a vibrational and/or acoustic effect of at least one source of noise of said aircraft;
a number of mechanical means which can be controlled and capable of creating a force capable of reducing the vibrational and/or acoustic effect of said source of noise; and
a single control unit for controlling said mechanical means on the basis of the values measured by said sensors, wherein said sensors are fixed to at least some of the following parts of said aircraft;
a mount for fixing said engine to said fuselage of said aircraft;
a bearing in said drivetrain;
a bar for fixing said main gearbox to said fuselage;
a mechanical suspension of said main gearbox;
said fuselage of said aircraft;
a device for fixing lining panels of said aircraft; and
a panel for lining said flight deck, wherein the aircraft comprises P sensors Cp arranged at points Mp, P being a predefined integer and p being an integer between 1 and P, which sensors are capable of measuring one same vibrational and/or acoustic parameter, and Q mechanical means Aq, Q being a predefined integer and q being an integer between 1 and Q, these means being capable respectively of creating forces capable of reducing one same vibrational and/or acoustic effect, and wherein said control unit repeatedly performs the following succession of operations;
it calculates, for each of said P sensors Cp, a value PIp that satisfies the equation;
- View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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Specification