| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | Propeller | US14532837 | 1937-05-28 | US2146481A | 1939-02-07 | MANNING RAY B |
| 62 | Compression propeller | US64456032 | 1932-11-22 | US2088255A | 1937-07-27 | LUTHER ADAMS HERBERT |
| 63 | Variable diameter propeller | US68915233 | 1933-09-12 | US2002712A | 1935-05-28 | PATRIARCHE VALANCE H |
| 64 | Storage-battery attachment for airships. | US1910549887 | 1910-03-17 | US984667A | 1911-02-21 | HEARST JOHN W |
| 65 | Motor-fan | US616712D | US616712A | 1898-12-27 | ||
| 66 | Churn-dasher | US586754D | US586754A | 1897-07-20 | ||
| 67 | Improvement in combined fly-brushes and casters | US157294D | US157294A | 1874-12-01 | ||
| 68 | Adjustable paddle-wheel | US12621D | US12621A | 1855-04-03 | ||
| 69 | Optimization of downstream open fan propeller position and placement of acoustic sensors | US14079550 | 2013-11-13 | US09637221B2 | 2017-05-02 | Matthew David Moore; Kelly L. Boren; Robin Blair Langtry |
| A method and apparatus for controlling a propeller of a contra-rotation open fan (CROF) engine of an aircraft is provided. A diameter of the propeller is set to be at a first diameter during at least a portion of a first flight condition of the aircraft. The diameter of the propeller is set to be at a second diameter, different from the first diameter, during at least a portion of a second flight condition of the aircraft. | ||||||
| 70 | OPTIMIZATION OF DOWNSTREAM OPEN FAN PROPELLER POSITION AND PLACEMENT OF ACOUSTIC SENSORS | US14079550 | 2013-11-13 | US20140308124A1 | 2014-10-16 | Matthew David Moore; Kelly L. Boren; Robin Blair Langtry |
| A method and apparatus for controlling a propeller of a contra-rotation open fan (CROF) engine of an aircraft is provided. A diameter of the propeller is set to be at a first diameter during at least a portion of a first flight condition of the aircraft. The diameter of the propeller is set to be at a second diameter, different from the first diameter, during at least a portion of a second flight condition of the aircraft. | ||||||
| 71 | Vertical takeoff and landing aircraft | US13103530 | 2011-05-09 | US08505846B1 | 2013-08-13 | Stanley Gordon Sanders, II |
| An aircraft has a fuselage, a lifting free wing, and a nose section. The fuselage has a front end, a rear end, and a longitudinal axis. The lifting free wing is pivotally connected to the fuselage with a pivot. The nose section is pivotally mounted on the front end of the fuselage, and includes a pair of engines, and a pair of counter-rotating propellers. A canard free wing is pivotally connected to the nose section with a pivot. A pair of vertical stabilizers are mounted on the rear end of the fuselage and each includes a rudder and a pair of landing gear. | ||||||
| 72 | PROPELLER ARRANGEMENT | US13027653 | 2011-02-15 | US20110223020A1 | 2011-09-15 | Alexander V. LAVRENKO |
| A propeller arrangement has a first propeller assembly providing a row of first propellers, and a second propeller assembly, rearward of the first propeller assembly, providing a row of second propellers. The first and second propellers are radially extendable and retractable. The propeller arrangement further has a control system for controlling the extension and retraction of the first and second propellers. The control system is arranged such that when the propellers of one of the first and second propeller assemblies extend, the propellers of the other of the first and second assemblies retract. | ||||||
| 73 | Optimization of Downstream Open Fan Propeller Position | US12643554 | 2009-12-21 | US20110150645A1 | 2011-06-23 | Matthew D. Moore; Kelly L. Boren; Robin B. Langtry |
| A method and apparatus for controlling a propeller of a contra-rotation open fan (CROF) engine of an aircraft. A diameter of the propeller is set to be at a first diameter during at least a portion of a first flight condition of the aircraft. The diameter of the propeller is set to be at a second diameter, different from the first diameter, during at least a portion of a second flight condition of the aircraft. | ||||||
| 74 | Methods and apparatus for adjustable surfaces | US11670736 | 2007-02-02 | US07777165B2 | 2010-08-17 | Terry M. Sanderson; Jamie W. Clark |
| Methods and apparatus for systems having deployable elements according to various aspects of the present invention comprise a system including a deployable surface and an adaptive actuator including a polymer foam. In one embodiment, the system comprises a vehicle including a deployable wing comprising an exterior surface. The exterior surface may be adjusted by adjusting the shape, size, position, and/or orientation of the adaptive actuator. | ||||||
| 75 | Propeller with Flexible Variable Blades | US12115457 | 2008-05-05 | US20090274557A1 | 2009-11-05 | Khymych Vasyl |
| The proposed propeller consists of the rotor disc assembly 1, two or more flexible variable-length blades 2, a precise number of which depends on the desired lifting force; carrying capacity and the airflow involved in the process of the aircraft take off and retention in the air, device or devices, which control retraction of blades, and devices which controls blade pitches 3. The blade represents a flexible strip made of steel composite or any other suitable material. The flexible nature of the strip and the fixture of the inner end of each blade on the barrel 4 located within the rotor disc assembly on which blades are reeled when retracted; provides for the blades pulling out automatically with minimal effort and no additional effort or engine force. This effect is reached through the blades being dragged out by the centrifugal force created by the rotation of the rotor and amplified by the load attached to the outer end of each blade. Centrifugal force when reaches appropriate level, keeps the blades in straighten and stiffen state, which allows for the operation of the aircraft similar to any propeller with fixed-length blades. | ||||||
| 76 | METHODS AND APPARATUS FOR ADJUSTABLE SURFACES | US11670736 | 2007-02-02 | US20090206192A1 | 2009-08-20 | Terry M. Sanderson; Jamie W. Clark |
| Methods and apparatus for systems having deployable elements according to various aspects of the present invention comprise a system including a deployable surface and an adaptive actuator including a polymer foam. In one embodiment, the system comprises a vehicle including a deployable wing comprising an exterior surface. The exterior surface may be adjusted by adjusting the shape, size, position, and/or orientation of the adaptive actuator. | ||||||
| 77 | METHODS AND APPARATUS FOR ADJUSTABLE SURFACES | US12181490 | 2008-07-29 | US20090072094A1 | 2009-03-19 | Terry M. Sanderson; Jamie W. Clark |
| Methods and apparatus for systems having deployable elements according to various aspects of the present invention comprise a system including a deployable surface and an adaptive actuator including a polymer foam. In one embodiment, the system comprises a vehicle including a deployable wing comprising an exterior surface. The exterior surface may be adjusted by adjusting the shape, size, position, and/or orientation of the adaptive actuator. | ||||||
| 78 | Rotor system having alternating length rotor blades and positioning means therefor for reducing blade-vortex interaction (BVI) noise | US569390 | 1995-12-11 | US5735670A | 1998-04-07 | Robert C. Moffitt; David G. Matuska; Evan A. Fradenburgh |
| A Variable Diameter Rotor (VDR) system (4) having telescoping odd and even blade assemblies (O.sub.b, E.sub.b) wherein the odd blade assemblies define a radial length R.sub.O and the even blade assemblies define a radial length R.sub.E. Each blade assembly (O.sub.b, E.sub.b) defines an internal chamber (64) for accepting a positioning means (70) operative to effect telescopic translation of the blade assemblies (O.sub.b, E.sub.b) such that the radial length R.sub.E of the even blade assemblies (E.sub.b) is equal to the radial length R.sub.O of the odd blade assemblies (O.sub.b) in a first operating mode, and such that the radial length R.sub.E is between about 70% to about 95% of the length R.sub.O in a second operating mode. The positioning means (70) includes a centrifugal restraint assembly (80) disposed within each internal chamber (64) of the rotor blade assemblies (O.sub.b, E.sub.b), a stop surface (64s) formed internally of each internal chamber (64), and an actuation means (90) operative for transpositioning the centrifugal restraint assemblies (80) within the internal chambers (64) such that, in one operating mode, the centrifugal restraint assemblies (80) are disposed in abutting engagement with the stop surfaces (64s) and, in another operating mode, the actuation means (90) is disposed in abutting engagement with the centrifugal restraint assemblies (80) of at least one of the blade assemblies (O.sub.b, E.sub.b). | ||||||
| 79 | Mechanism for synchronously varying diameter of a plurality of rotors and for limiting the diameters thereof | US812309 | 1977-07-01 | US4142697A | 1979-03-06 | Evan A. Fradenburgh |
| A plurality of variable diameter rotors with mechanism for varying the diameter of the rotors synchronously, and including mechanism to limit the diameter of the rotors. | ||||||
| 80 | Locking control and overtravel safety stop system for variable length rotor blades | US700455 | 1976-06-28 | US4074952A | 1978-02-21 | Evan A. Fradenburgh; Jay M. Yarm |
| A locking control system and an overtravel safety stop system are presented for a variable length rotor blade system. The lock system has a lock mechanism operated by a pilot actuated lock shaft to lock and unlock the blade adjustment system. A traveling nut locks the blade adjustment system to prevent overretraction or overextension. | ||||||
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