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US3558081A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Airborne vehicles
Assignee: Airmarine Corp
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Filing: 1969-02-20
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Granted: 1971-01-26
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Expires: 1989-02-20
Abstract
Abstract An airborne vehicle provided with a rotor assembly consisting of a hub and a plurality of blades spaced axially of the hub, each blade including an inboard section having a forwardly inclined torque vector and an outboard section having a rearwardly inclined torque vector, the chord of the inner section being greater than that of the outer section.
Inventors
- 👤 Paul E Williams
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 16:00
CPC Classifications
B; B64; B64C; B64C27/00; B64C27/04; B64C27/08; B64C27/10
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
285 words
A helicopter comprising: a body having a longitudinal axis; a rotor assembly including a central, normally vertical rotatable shaft, a hub secured to said shaft, and at least two axially spaced rotor blades operably secured to and extending away from said hub; a prime mover operably connected to said rotor blade comprising a vertical drive shaft parallel to said rotatable shaft and operably secured thereto for rotating said shaft; means mounting said rotor assembly and said prime mover on said body for pivotal movement in a vertical plane parallel to a vertical plane through said longitudinal axis of said body; each rotor blade comprising a radially inner portion having a chord and a radially outer portion having a chord, the juncture of the inner and outer sections being smooth and unobstructed, the inner portion having a positive pitch angle and at least the outer end of the outer portion having a negative pitch angle, said chord of said inner portion being substantially greater than said chord of said outer portion; said prime mover comprising a gas operated motor having an inlet and an outlet, a liquid vaporizer, means connecting said vaporizer and said inlet, a condenser, means connecting said outlet and said condenser, means connecting said condenser and said vaporizer, and means for controlling the flow of a fluid through said prime mover; and said prime mover also including a nonmagnetizable housing having a magnetizable strip on the periphery thereof, means for pivoting said mounting means in said vertical plane including a series of selectively energizable magnetic means positioned on said body adjacent said prime mover for selectively attracting said magnetizable strip and said prime mover to move said rotor assembly in said vertical plane.
Claim 2
Dependent Claim
285 words
A helicopter comprising: a body having a longitudinal axis; a rotor assembly including a central, normally vertical rotatable shaft, a hub secured to said shaft, and at least two axially spaced rotor blades operably secured to and extending away from said hub; a prime mover operably connected to said rotor blade comprising a vertical drive shaft parallel to said rotatable shaft and operably secured thereto for rotating said shaft; means mounting said rotor assembly and said prime mover on said body for pivotal movement in a vertical plane parallel to a vertical plane through said longitudinal axis of said body; each rotor blade comprising a radially inner portion having a chord and a radially outer portion having a chord, the juncture of the inner and outer sections being smooth and unobstructed, the inner portion having a positive pitch angle and at least the outer end of the outer portion having a negative pitch angle, said chord of said inner portion being substantially greater than said chord of said outer portion; said prime mover comprising a gas operated motor having an inlet and an outlet, a liquid vaporizer, means connecting said vaporizer and said inlet, a condenser, means connecting said outlet and said condenser, means connecting said condenser and said vaporizer, and means for controlling the flow of a fluid through said prime mover; and said prime mover also including a nonmagnetizable housing having a magnetizable strip on the periphery thereof, means for pivoting said mounting means in said vertical plane including a series of selectively energizable magnetic means positioned on said body adjacent said prime mover for selectively attracting said magnetizable strip and said prime mover to move said rotor assembly in said vertical plane.
Claim 3
Dependent Claim
163 words
A rotatable blade comprising: an inner section having a root, a leading edge, a trailing edge and a cHord; an outer section integral with said inner section: having a tip, a leading edge, a trailing edge and a chord; the leading edge of said outer section forming an obtuse angle with the leading edge of said inner section; said inner section having a positive pitch angle; the pitch angle of said inner section decreasing from the root to its juncture with said outer section; said outer section curving from a slight positive pitch angle to a negative pitch angle adjacent its juncture with said inner section; the negative pitch angle increasing progressively toward the tip, to reduce pressure and decrease turbulence at the tip and redirect air flow toward the inner section; and the chord of said inner section being greater than the chord of the outer section to compensate for increased pressure due to increased speed of rotation of the outer section.
Claim 4
Dependent Claim
163 words
A rotatable blade comprising: an inner section having a root, a leading edge, a trailing edge and a cHord; an outer section integral with said inner section: having a tip, a leading edge, a trailing edge and a chord; the leading edge of said outer section forming an obtuse angle with the leading edge of said inner section; said inner section having a positive pitch angle; the pitch angle of said inner section decreasing from the root to its juncture with said outer section; said outer section curving from a slight positive pitch angle to a negative pitch angle adjacent its juncture with said inner section; the negative pitch angle increasing progressively toward the tip, to reduce pressure and decrease turbulence at the tip and redirect air flow toward the inner section; and the chord of said inner section being greater than the chord of the outer section to compensate for increased pressure due to increased speed of rotation of the outer section.
Claim 5
Dependent Claim
25 words
The structure of claim 2 wherein said chord of said inner portion is more than 2 percent greater than the chord of said outer portion.
Claim 6
Dependent Claim
16 words
The structure of claim 2 wherein said positive pitch has a maximum angle of about 48*.
Claim 7
Dependent Claim
47 words
The structure of claim 2 wherein the chord of the inner section is substantially constant throughout a major portion of its length, and decreases sharply adjacent its juncture with said outer section, the chord of the outer section being substantially constant to a point adjacent the tip.
Claim 8
Dependent Claim
199 words
A rotor structure including a hub having a plurality of blades thereon, the blades being offset relative to each other along the axis of rotation of the hub, each blade comprising: an inner section having a root, a leading edge, a trailing edge and a chord; an outer section integral with said inner section having a tip, a leading edge, a trailing edge and a chord; the leading edge of said outer section forming an obtuse angle with the leading edge of said inner section; said inner section having a positive pitch angle; the pitch angle of said inner section decreasing from the root to its juncture with said outer section; said outer section curving from a slight positive pitch angle to a negative pitch angle adjacent its juncture with said inner section; the negative pitch angle increasing progressively toward the tip, to reduce pressure and decrease turbulence at the tip, redirect air flow toward the inner section, and obtain a cascade effect through the axially offset blades; and the chord of said inner section being greater than the chord of the outer section to compensate for increased pressure due to increased speed of rotation of the outer section.
Claim 9
Dependent Claim
199 words
A rotor structure including a hub having a plurality of blades thereon, the blades being offset relative to each other along the axis of rotation of the hub, each blade comprising: an inner section having a root, a leading edge, a trailing edge and a chord; an outer section integral with said inner section having a tip, a leading edge, a trailing edge and a chord; the leading edge of said outer section forming an obtuse angle with the leading edge of said inner section; said inner section having a positive pitch angle; the pitch angle of said inner section decreasing from the root to its juncture with said outer section; said outer section curving from a slight positive pitch angle to a negative pitch angle adjacent its juncture with said inner section; the negative pitch angle increasing progressively toward the tip, to reduce pressure and decrease turbulence at the tip, redirect air flow toward the inner section, and obtain a cascade effect through the axially offset blades; and the chord of said inner section being greater than the chord of the outer section to compensate for increased pressure due to increased speed of rotation of the outer section.
Claim 10
Dependent Claim
208 words
A helicopter including a fuselage, a rotor, and a tail, said rotor comprising a hub, a plurality of vertically superposed radially offset blades to provide a cascade effect, each blade comprising: an inner section having a root, a leading edge, a trailing edge and a chord; an outer section integral with said inner section having a tip, a leading edge, a trailing edge and a chord; the leading edge of said outer section forming an obtuse angle with the leading edge of said inner section; said inner section having a positive pitch angle; the pitch angle of said inner section decreasing from the root to its juncture with said outer section; said outer section curving from a slight positive pitch angle to a negative pitch angle adjacent its juncture with said inner section; the negative pitch angle increasing progressively toward the tip, to reduce pressure and decrease turbulence at the tip and redirect air flow toward the inner section; and the chord of said inner section being greater than the chord of the outer section to compensate for increased pressure due to increased speed of rotation of the outer section to provide a substantially torque free rotor, eliminating the necessity for a tail rotor to compensate for torque.
Claim 11
Dependent Claim
208 words
A helicopter including a fuselage, a rotor, and a tail, said rotor comprising a hub, a plurality of vertically superposed radially offset blades to provide a cascade effect, each blade comprising: an inner section having a root, a leading edge, a trailing edge and a chord; an outer section integral with said inner section having a tip, a leading edge, a trailing edge and a chord; the leading edge of said outer section forming an obtuse angle with the leading edge of said inner section; said inner section having a positive pitch angle; the pitch angle of said inner section decreasing from the root to its juncture with said outer section; said outer section curving from a slight positive pitch angle to a negative pitch angle adjacent its juncture with said inner section; the negative pitch angle increasing progressively toward the tip, to reduce pressure and decrease turbulence at the tip and redirect air flow toward the inner section; and the chord of said inner section being greater than the chord of the outer section to compensate for increased pressure due to increased speed of rotation of the outer section to provide a substantially torque free rotor, eliminating the necessity for a tail rotor to compensate for torque.
Claim 12
Dependent Claim
32 words
The structure of claim 7 wherein the juncture of the inner section and the outer secTion is at substantially 43 percent of the length of the blade measured outwardly from the hub.
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) | 1974-01-25 | 1974-07-27 | 1975-01-26 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-01-25 | 1978-07-27 | 1979-01-26 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-01-25 | 1982-07-27 | 1983-01-26 | $7700.00 | Window Closed / Lapsed |