子分类：
- B64C11/001： .{闭式螺旋桨}
- B64C11/002： .{制动螺旋桨,如用于测量发动机的功率输出}
- B64C11/003： .{可变直径的螺旋桨;相关的机械装置}
- B64C11/005： .{螺旋形螺旋桨}
- B64C11/006： .{桨轮}
- B64C11/007： .{推进盘,即具有专用于推进目的表面的推进盘}
- B64C11/008： .{以振动吸收或平衡装置为特点的(用于旋翼飞机B64C27/001)}
- B64C11/02： .桨毂结构
- B64C11/16： .桨叶
- B64C11/30： .桨叶变距机构
- B64C11/46： .多个螺旋桨的配置或其特有的结构特征{(B64C11/306优先)}
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | ROTOR ASSEMBLY AND UNMANNED AERIAL VEHICLE HAVING THE SAME | US15934239 | 2018-03-23 | US20180208301A1 | 2018-07-26 | Fangming YE |
| A rotor assembly includes a motor, a propeller, and a connection assembly. The motor includes a stator and a rotator rotatable with respect to the stator. The connection assembly includes a locking member provided between the propeller and the rotator. The locking member is configured to rotate with respect to the rotator and the propeller to lock the propeller to the motor. | ||||||
| 182 | PROPELLER | US15897767 | 2018-02-15 | US20180186439A1 | 2018-07-05 | Gregory Charles Sharrow |
| A propeller having a means for creating fluid flow in a non-axial direction and redirecting it in an axial direction. | ||||||
| 183 | EMERGENCY EJECTION SEAT WITH PROPULSION SYSTEM | US15686712 | 2017-08-25 | US20180162539A1 | 2018-06-14 | Seyednezam Azizi Pourzadeh |
| An emergency ejection seat with a propulsion system is disclosed. The propulsion system may be provided by a propeller-equipped brushless motor. The emergency ejection seat includes speed controllers that can accelerate and move the seat with two different speeds. Several wedge-shaped recesses along the rear of the seat help limit the effects of a vacuum. | ||||||
| 184 | Cone brake friction surface coating | US14991725 | 2016-01-08 | US09995355B2 | 2018-06-12 | Kyle A. Hassler; Sean Warrenburg; Joseph A. Swift; Kevin Mock; Mark Winely |
| An exemplary cone brake device includes a brake drum and a thermal sprayed coating deposited and bonded to the outer surface. The thermal sprayed coating is configured to engage a friction lining when one of the brake drum and the friction element is moved toward the other of the brake drum and the friction element, so as to decrease the speed of an aerospace propeller. | ||||||
| 185 | System and method for coordinating a propeller with an electronic engine control | US15434085 | 2017-02-16 | US09945301B2 | 2018-04-17 | Christopher Roy Carrington |
| A method and system are provided for coordinating a propeller with a controller module including a machine having a controller module and a propeller mounted to a propeller shaft at a hub. The shaft is arranged to be received in the machine, and a sensor is mounted to the machine, connected to the electronic controller module, and configured to sense the propeller when the propeller shaft is received in the machine. | ||||||
| 186 | Propeller | US15605764 | 2017-05-25 | US09926058B2 | 2018-03-27 | Gregory Charles Sharrow |
| A propeller having a means for creating fluid flow in a non-axial direction and redirecting it in an axial direction. | ||||||
| 187 | Single blade propeller with variable pitch | US14493274 | 2014-09-22 | US09889925B2 | 2018-02-13 | Blaine K. Rawdon |
| An improved performance propeller employs a single propeller blade having an axis of rotation and a centripetal force about the axis. A pitch control unit is mounted opposite the single propeller blade and has a compensating centripetal force with respect to the single propeller blade about the axis. | ||||||
| 188 | INTENTIONALLY IMBALANCING PROPELLERS FOR PERFORMANCE AND NOISE-SHAPING | US15658168 | 2017-07-24 | US20170334546A1 | 2017-11-23 | Brian C. Beckman; Allan Ko |
| Aerial vehicles may be operated with discrete sets of propellers, which may be selected for a specific purpose or on a specific basis. The discrete sets of propellers may be operated separately or in tandem with one another, and at varying power levels. For example, a set of propellers may be selected to optimize the thrust, lift, maneuverability or efficiency of an aerial vehicle based on a position or other operational characteristic of the aerial vehicle, or an environmental condition encountered by the aerial vehicle. At least one of the propellers may be statically or dynamically imbalanced, such that the propeller emits a predetermined sound during operation. A balanced propeller may be specifically modified to cause the aerial vehicle to emit the predetermined sound by changing one or more parameters of the balanced propeller and causing the balanced propeller to be statically or dynamically imbalanced. | ||||||
| 189 | ROTORCRAFT CONFIGURATION AND METHOD OF ROTORCRAFT DESIGN | US15513886 | 2015-09-29 | US20170297697A1 | 2017-10-19 | Blake Almy Moffitt; Brian E. WAKE; Peter F. Lorber |
| A rotorcraft is provided and includes a fuselage. The fuselage includes drag generating portions, a main rotor assembly and an auxiliary propulsor having an expected propulsion efficiency. The auxiliary propulsor is disposed to ingest boundary layer flows and in wake regions associated with the drag generating portions and is provided with a corresponding increase in the expected propulsion efficiency thereof. | ||||||
| 190 | Selecting propellers for performance and noise shaping | US14975563 | 2015-12-18 | US09745050B2 | 2017-08-29 | Brian C. Beckman; Allan Ko |
| Aerial vehicles may be operated with discrete sets of propellers, which may be selected for a specific purpose or on a specific basis. The discrete sets of propellers may be operated separately or in tandem with one another, and at varying power levels. For example, a set of propellers may be selected to optimize the thrust, lift, maneuverability or efficiency of an aerial vehicle based on a position or other operational characteristic of the aerial vehicle, or an environmental condition encountered by the aerial vehicle. At least one of the propellers may be statically or dynamically imbalanced, such that the propeller emits a predetermined sound during operation. A balanced propeller may be specifically modified to cause the aerial vehicle to emit the predetermined sound by changing one or more parameters of the balanced propeller and causing the balanced propeller to be statically or dynamically imbalanced. | ||||||
| 191 | VARIABLE-PITCH FAN WITH LOW PITCH OF A TURBINE ENGINE | US15398133 | 2017-01-04 | US20170191495A1 | 2017-07-06 | Nils Edouard Romain BORDONI; Michel Gilbert Roland BRAULT; Romain Guillaume CUVILLIER; Guillaume Patrice KUBIAK; Arnaud Nicolas NEGRI; Nathalie NOWAKOWSKI |
| A fan of a turbine engine, the fan including a fan disk provided with blades on its periphery, the blades being pivotally mounted on the disk around a pivoting axis and having a center of gravity, and a pitch change mechanism for the blades, each blade being configured so that its center of gravity is positioned on or at a small distance from a fictitious plane which passes through the pivoting axis of the blade and which is perpendicular to the axis of revolution of the fan when the blade is in a minimum drag position. | ||||||
| 192 | PIEZOELECTRIC TRANSDUCERS ON PROPELLER BLADES FOR SOUND CONTROL | US15189861 | 2016-06-22 | US20170174334A1 | 2017-06-22 | Brian C. Beckman; Vedran Coralic; Gur Kimchi |
| The present disclosure is directed to controlling, reducing, and/or altering sound generated by an aerial vehicle, such as an unmanned aerial vehicle (“UAV”), while the aerial vehicle is airborne. For example, one or more transducers, such as piezoelectric thin-film transducers, or carbon nanotube transducers may be applied or incorporated into or on the surface of propeller blades that are used to aerially navigate the aerial vehicle. As the propeller blade rotates and generates sound, the transducers may be activated to generate one or more anti-sounds that cancel, reduce, or otherwise modify the sound generated by the rotation of the propeller blade. The anti-sound combines with the sound and causes interference such that the combined, or net-effect, is an overall cancellation, reduction, or other modification of the sound. | ||||||
| 193 | SELECTING PROPELLERS FOR PERFORMANCE AND NOISE SHAPING | US14975563 | 2015-12-18 | US20170174317A1 | 2017-06-22 | Brian C. Beckman; Allan Ko |
| Aerial vehicles may be operated with discrete sets of propellers, which may be selected for a specific purpose or on a specific basis. The discrete sets of propellers may be operated separately or in tandem with one another, and at varying power levels. For example, a set of propellers may be selected to optimize the thrust, lift, maneuverability or efficiency of an aerial vehicle based on a position or other operational characteristic of the aerial vehicle, or an environmental condition encountered by the aerial vehicle. At least one of the propellers may be statically or dynamically imbalanced, such that the propeller emits a predetermined sound during operation. A balanced propeller may be specifically modified to cause the aerial vehicle to emit the predetermined sound by changing one or more parameters of the balanced propeller and causing the balanced propeller to be statically or dynamically imbalanced. | ||||||
| 194 | Simulated ground effect for aerial vehicles | US14975491 | 2015-12-18 | US09643718B1 | 2017-05-09 | Brian C. Beckman; Allan Ko |
| Ground effect acting on an aerial vehicle, such as an unmanned aerial vehicle, may be simulated by discharging a gas around propeller blades of the aerial vehicle while the propeller blades are rotating. For example, a gas, such as air, may be discharged at or near the tip of the propeller blades with enough velocity to disrupt the airflow around the blade tips, thereby altering the sound generated by rotation of the propeller blade. | ||||||
| 195 | Resistive-inductive propeller blade de-icing system including contactless power supply | US14203813 | 2014-03-11 | US09638044B2 | 2017-05-02 | Jacek F. Gieras; Lubomir A. Ribarov |
| An aircraft propeller de-icing system comprises at least one propeller blade coupled to a rotatable prop assembly. The prop assembly is configured to rotate in response to rotatably driving a propeller shaft. At least one resistive-inductive heating unit is coupled to the at least one propeller blade. The resistive-inductive heating unit is configured to generate eddy currents that induce inductive heat in response to an electric current. A contactless power transfer system generates the electrical current in response to transferring power across an air gap separating the propeller shaft from the contactless power transfer system. | ||||||
| 196 | ROTOR DRIVEN AUXILIARY POWER APPARATUS AND METHOD | US15280116 | 2016-09-29 | US20170066539A1 | 2017-03-09 | Jacob J. van der Westhuizen; David Groen |
| Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. The generator may be used to charge a battery during autorotation or descending. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. | ||||||
| 197 | AIRCRAFT DOOR WITH COMPRESSIBLE HEADER | US14719420 | 2015-05-22 | US20160340019A1 | 2016-11-24 | Robert J. Telmos |
| The disclosed embodiments relate to an aircraft having an interior door with a compressible header. Accordingly to non-limiting embodiments, a slideable door panel includes an opening in a top portion thereof to receive a compressible header configured to reside in the opening of the slideable door panel. The compressible header includes a biasing mechanism configured to upwardly bias the compressible header against the headliner when closed. The compressible header is also configured to allow lateral movement of the compressible header within the opening. The compressibility of the compressible header and lateral movement resist the formation of gaps between the compressible header and the headliner during flight. | ||||||
| 198 | ELEVON CONTROL SYSTEM | US14796906 | 2015-07-10 | US20160185445A1 | 2016-06-30 | CARLOS THOMAS MIRALLES; ROBERT NICKERSON PLUMB; TONY SHUO TAO; NATHAN OLSON |
| A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements. | ||||||
| 199 | ChetProp air or water propeller and spinner with front and back leg assemblies attached to spinner | US14669341 | 2015-03-26 | US09278744B1 | 2016-03-08 | Frank Chester |
| An air or watercraft propeller comprises a plurality of blade systems wherein each blade system is composed of a front leg attached to a back blade. The front legs pull air or water towards spinner while the back legs use vertical suction to draw air or water towards the spinner to complement the air or water flow created by the front legs. The back legs are angularly attached to the spinner at approximately 60 degrees rotated from the spinner center line. The back legs are also tilted to an angle of approximately 60 degrees from the surface of the spinner. The front legs are attached to the back legs at an angle of approximately 60 degrees. The propeller system presents several equilateral triangles to maximize propulsion efficiency. The front legs are rigidly attached to the spinner while the back legs may be adjusted for pitch. | ||||||
| 200 | Single-piece propeller and method of making | US13484007 | 2012-05-30 | US09266603B2 | 2016-02-23 | Danny Ball; Kevin Pfeiffer |
| A method for making a propeller product is disclosed. The propeller is formed using polyurethane cores adhered to a laminate hub to form a core assembly. An encapsulating structural laminate skin is then formed on the core assembly using a resin-transfer-molding process to create a single-piece composite propeller. | ||||||
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