US4934483A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Method of reducing the overflying noise of airplanes having a propeller driven by a piston engine
Assignee: Deutsches Zentrum für Luft- und Raumfahrt eV
•
Filing: 1988-10-18
•
Granted: 1990-06-19
•
Expires: 2008-10-18
Abstract
Abstract Method of reducing the overflying noise of airplanes having a propeller den by a piston engine. The propeller is arranged on the engine shaft in such a way that positive components of the engine sound pressure fall on negative components of the propeller sound pressure. It is preferable to use an engine/propeller combination in which the number of engine ignitions per revolution of the propeller shaft divided by the number of the propeller blades is an integer, preferably being equal to 1.
Inventors
- 👤 Michael Kallergis
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 18:16
CPC Classifications
B; B64; B64D; B64D33/00; B64D33/04; B64D33/06; G; G10; G10K; G10K11/00; G10K11/16; G10K11/175
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
164 words
A method of attenuating overflying noise of an airplane in a predetermined direction, the airplane including a propeller having a predetermined number of blades mounted on a propeller shaft and a piston engine driving the propeller shaft, wherein the piston engine has a predetermined number of ignitions per revolution of the propeller shaft, the number of engine ignitions per revolution of the propeller shaft divider by the number of blades of the propeller being a whole integer from one to four, said predetermined direction being radial with respect to said propeller shaft, said method comprising the step of arranging the propeller shaft relative to said engine so that sound pressure signals generated by the propeller are substantially in antiphase with sound pressure signals generated by the engine in said predetermined direction whereby the propeller sound pressure signals in said predetermined direction are attenuated by interference with the engine sound pressure signals to reduce the overflying noise emitted by said airplane in said predetermined direction.
Claim 2
Independent Claim
164 words
A method of attenuating overflying noise of an airplane in a predetermined direction, the airplane including a propeller having a predetermined number of blades mounted on a propeller shaft and a piston engine driving the propeller shaft, wherein the piston engine has a predetermined number of ignitions per revolution of the propeller shaft, the number of engine ignitions per revolution of the propeller shaft divider by the number of blades of the propeller being a whole integer from one to four, said predetermined direction being radial with respect to said propeller shaft, said method comprising the step of arranging the propeller shaft relative to said engine so that sound pressure signals generated by the propeller are substantially in antiphase with sound pressure signals generated by the engine in said predetermined direction whereby the propeller sound pressure signals in said predetermined direction are attenuated by interference with the engine sound pressure signals to reduce the overflying noise emitted by said airplane in said predetermined direction.
Claim 3
Dependent Claim
37 words
In the method of claim 1, said engine including an exhaust silencer having a variable efficiency a magnitude of the sound pressure signals generated by said engine being variable by varying the efficiency of said exhaust silencer.
Claim 4
Dependent Claim
19 words
In the method of claim 1, the direction of the sound pressure signals emitted by said engine being variable.
Claim 5
Dependent Claim
38 words
The method of claim 2 further comprising the step of adjusting said exhaust silencer to adjust the magnitude of the sound pressure signals generated by said engine in order to reduce the overflying noise emitted by said airplane.
Claim 6
Dependent Claim
31 words
The method of claim 3 further comprising the step of adjusting the direction of the sound pressure signals emitted by said engine to reduce the overflying noise emitted by said airplane.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1993-06-18 | 1993-12-18 | 1994-06-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1997-06-18 | 1997-12-18 | 1998-06-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2001-06-18 | 2001-12-18 | 2002-06-19 | $7700.00 | Window Closed / Lapsed |