18436 results about "Propeller" patented technology

The invention is a modular vehicle having an air vehicle that can be coupled to cargo containers, land vehicles, sea vehicles, medical transport modules, etc. In one embodiment the air vehicle has a plurality of propellers positioned around a main airframe, which can provide vertical thrust and / or horizontal thrust. One or more of the propellers may be configured to tilt forward, backward, and / or side-to-side with respect to the airframe.

An implant for insertion into a disc space between vertebrae, wherein the implant includes a spacer portion, a plate portion coupled to the spacer portion, two bone fixation elements for engaging the vertebrae and a retention mechanism for preventing the bone fixation elements from postoperatively backing-out of the plate portion. The retention mechanism may be in the form of a spring biased snapper element that is biased into communication with the bone fixation elements so that once the bone fixation element advances past the snapper element, the snapper element is biased back to its initial position in which the snapper element interfaces with the bone fixation elements. Alternatively, the retention mechanism may be in the form of a propeller rotatable between a first position in which the bone fixation elements are insertable to a second position where the bone fixation elements are prevented from backing-out.

An unmanned aerial vehicle (UAV) for transporting a payload is provided. The UAV comprises a body and one or more propellers rotatably connected to the body. The UAV further comprises a battery mounted to the body. The battery is releasable from the bottom of the UAV. The UAV further comprises a payload container mounted to the body. The payload container is releasable from the bottom of the UAV to a landing platform associated with a UAV station.

An unmanned air vehicle is provided, which includes an airframe and a parallel hybrid-electric propulsion system mounted on the airframe. The parallel hybrid-electric propulsion system includes an internal combustion engine and an electric motor. A hybrid controller is configured to control both the internal combustion engine and the electric motor. A propeller is connected to a mechanical link. The mechanical link couples the internal combustion engine and the electric motor to the propeller to drive the propeller. An alternate unmanned air vehicle includes a second propeller driven by the electric motor. In this alternate unmanned air vehicle, the internal combustion engine is decoupled from the electric motor.

The present invention relates to an unmanned flying vehicle using a PCB including a main board controlling power supply and flying operation, a motor rotating a propeller by changing electric energy into mechanical energy, a PCB frame changing a signal from a remote controller and connecting the main board with the motor, a propeller generating an impellent force by from rotation by the motor, a receiver receiving a control signal of the remote controller, and a remote controller controlling a motor rotation speed of a quadrotor and direction change, and accordingly, the structure of the unmanned flying vehicle can be simplified so that the flying vehicle can be down-sized and light-weighted, and assemblability can be improved.

An unmanned aerial vehicle (UAV) copter for consumer photography or videography can be launched by a user throwing the UAV copter into mid-air. The UAV copter can detect that the UAV copter has been thrown upward while propeller drivers of the UAV copter are inert. In response to detecting that the UAV copter has been thrown upward, the UAV copter can compute power adjustments for propeller drivers of the UAV copter to have the UAV copter reach a predetermined elevation above an operator device. The UAV copter can then supply power to the propeller drivers in accordance with the computed power adjustments.

A vertical axis tower fan apparatus having an adjustable support column. The tower fan apparatus is comprised of a support base, a telescopic support column adjustable between fixed, retracted and extended positions, a vertical axis propeller encased within a housing, and a motor. The vertical axis propeller is contained within the cylindrical housing, wherein the housing is rotatably coupled to one end of the support column. The fan is rotatably connected to the top of the support column and is adapted to rotate freely thereon, when activated. The opposing end of the column is insertable into the support base. The telescopic column is comprised of a hollow pillar and an extendable member removably inserted within the hollow pillar. The column is manually adjustable to a variety of heights to provide cooling air to different target heights via the use of an adjustable locking sleeve. The sleeve may be loosened, to allow the extendable member to be extracted from within the hollow pillar and raised until the fan reaches a desirable height. Conversely, the extendable member may be retracted until the fan reaches another target height. When the desired height is reached, the sleeve is tightened thereby preventing the member from moving within the pillar. A keypad located in the housing cover, or a remote control unit allows the user to program the fan, via the use of a microcontroller within the fan housing, to achieve a variety of speeds and wind patterns, as well as activating an oscillation mode and a timer.

Modern farming is currently being done by powerful ground equipment or aircraft that weigh several tons and treat uniformly tens of hectares per hour. Automated farming can use small, agile, lightweight, energy-efficient automated robotic equipment that flies to do the same job, even able to farm on a plant-by-plant basis, allowing for new ways of farming. A hybrid airship-drone has both passive lift provided by a gas balloon and active lift provided by propellers. A hybrid airship-drone may be cheaper, more stable in flight, and require less maintenance than other aerial vehicles such as quadrocopters. However, hybrid airship-drones may also be larger in size and have more inertia that needs to be overcome for starting, stopping and turning.

The invention is a modular vehicle having an air vehicle that can be coupled to cargo containers, land vehicles, sea vehicles, medical transport modules, etc. In one embodiment the air vehicle has a plurality of propellers positioned around a main airframe, which can provide vertical thrust and / or horizontal thrust. One or more of the propellers may be configured to tilt forward, backward, and / or side-to-side with respect to the airframe.

An aircraft including an airframe having a fuselage which extends longitudinally, and having fixed wings including a main wing, a horizontal tail wing and a vertical tail wing. A propeller-rotor torque transmission has a bevel gear which transmits the rotation of an input shaft simultaneously to a propeller shaft and to a rotor shaft. An engine gearbox supplies the above-mentioned input shaft with rotationalal motive power. The aircraft further includes a propeller collective pitch controller, a rotor collective pitch controller, an engine power controller which controls the output of the above-mentioned engine gearbox for the purpose of changing the rotational speed of the input shaft, and a flight control system having a directional (yaw) control system which controls the flight direction of the aircraft by controlling the positions of the above-mentioned control surfaces.

A sensing device includes a propulsion system that is typically substantially or completely within the sensing device. The propulsion system may include, for example, a rotatable propeller. The sensing device may be an in-vivo autonomous capsule with an imager, but may be another type of sensing device.

The present invention concerns systems for storing energy and using the stored energy to generate electrical energy or drive a propeller (505). In particular, the present invention provides a method of storing energy comprising: providing a gaseous input, producing a cryogen from the gaseous input; storing the cryogen; expanding the cryogen; using the expanded cryogen to drive a turbine (320) and recovering cold energy from the expansion of the cryogen. The present invention also provides a cryogenic energy storage system comprising: a source of cryogen; a cryogen storage facility (370); means for expanding the cryogen; a turbine (320) capable of being driven by the expanding cryogen; and means (340, 350) for recovering cold energy released during expansion of the cryogen.

A combined submersible vessel and unmanned aerial vehicle preferably includes a body structure, at least one wing structure coupled to the body structure, at least one vertical stabilizer structure coupled to the body structure, and at least one horizontal stabilizer structure coupled to the body structure. A propulsion system is coupled to the body structure and is configured to propel the flying submarine in both airborne flight and underwater operation. Preferably, the propulsion system includes a motor, a gearbox coupled to the motor and configured to receive power generated by the motor and provide variable output power, a drive shaft coupled to the gearbox and configured to transfer the variable output power provided by the gearbox, and a propeller coupled to the drive shaft and configured to accept power transferred to it from the drive shaft. The propeller is further configured to rotate and propel the flying submarine in both an airborne environment and in an underwater environment.

A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, a pilot's compartment formed in the fuselage between the lift-producing propellers and substantially aligned with one side of the fuselage, a payload bay formed in the fuselage between the lift-producing propellers and opposite the pilot's compartment, and two pusher fans located at the rear of the vehicle. Many variations are described enabling the vehicle to be used not only as a VTOL vehicle, but also as a multi-function utility vehicle for performing many diverse functions including hovercraft and ATV functions. Also described is an Unmanned version of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles.

A rotary-wing apparatus that is aeronautically stable, easy to fly with a multidimensional control, small size, and safe to fly and low cost to produce. The rotary-wing apparatus includes a coaxial counter rotating rotor drive providing lifting power with an inherent aeronautical stability; Auxiliary propellers that face the direction of flight and are located on opposite sides of said coaxial Rotary-wing apparatus and enable flying forwards, backwards and perform yawing; A rotary-wing coaxial helicopter toy that is remotely controlled and safe to fly in doors and out doors, while performing exciting maneuvers even by untrained kids

A hovering remote-control flying craft having a molded frame assembly includes a plurality of arms extending from a center body with an electric motor and corresponding propeller on each arm. In various embodiments, the motor and propeller are mounted downward-facing at a distal portion of each arm with a motor cover over the motor. The center body can be formed of a two-piece molded structure that sandwiches a circuit board to provide structural support for the frame. The circuit board can include a plurality of tabs that facilitate mounting of wire connectors, and can also provide antennas and emitters for both IR and RF communications. In some embodiments, a removable safety ring protects the propellers from lateral contact.

Aircraft comprising an airframe having a forward end, an aft end opposite the forward end, a top extending between the forward end and the aft end, and a bottom opposite the top side. The aircraft further includes a power plant mounted on the airframe. In addition, the aircraft includes at least two propellers rotatably mounted on the airframe and powered by the power plant for moving the aircraft in a generally forward direction during operation of the propellers. Also, the aircraft includes at least two counter-rotatable fan sets mounted on the airframe and powered by the power plant for providing upward lift to the aircraft during operation of the fan sets.

A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and / or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage.

A mounting arrangement for a refrigerator fan, comprising an electric motor (11) to whose shaft is affixed a propeller (12) with an axial flow passing through a refrigerated air outlet (4b) provided through an internal divisional wall (6) of the refrigerator; a support frame (20) having a marginal portion (21) and incorporating a central hub (22) in which is affixed the electric motor (11); a flexible support (30) in the form of an annular flange presenting an outer portion (31), which is peripherally and removably affixed to the contour of the refrigerated air outlet (4b), an inner portion (32) provided with a central opening (35) and with retaining means (36), which are removably locked to the marginal portion (21) of the support frame (20); and an annular membrane portion (33) interconnecting the outer portion (31) and the inner portion (32), in order to allow for small relative axial and radial displacements therebetween.

A vertical takeoff and landing aircraft having a fuselage with three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are vertical for vertical flight, and horizontal for forward flight. The aircraft wings are placed such that the rear wing is above the middle wing which is placed above the front wing. The placement of each of the propulsion units relative to the center of gravity of the aircraft about the vertical axis inherently assures continued stability in vertical flight mode, following the loss of thrust from any one propulsion unit. The placement of the propulsion units, viewing the aircraft from the front, is such that each propulsion units' thrust wake does not materially disturb the propulsion unit to its rear. When engine driven propellers or rotors are utilized, flapped wing panels are attached outboard of the forward and / or rearward propulsion units to provide yaw control during vertical flight.

The invention discloses a wave wheel of a washing machine, comprising a base and a plurality of blades arranged on the base, wherein the blades are provided with veins and water propelling surfaces with slopes at two sides. The wave wheel is characterized in that a cone-shaped platform is arranged at the middle part of the base; raised propelling ribs of which the quantity is same as the quantity of the blades are arranged on the vertical face of the cone-shaped platform and smoothly connected to the corresponding veins; water propelling surfaces of each blade have different slopes; concave surfaces and convex surfaces are arranged on the water propelling surfaces; the veins are S-shaped for corresponding to the curve surface changes of the concave surfaces and convex surfaces of the water propelling surfaces; moreover, side-looking lines of the veins are continuous curves firstly concave and then convex outwards from the center of the base. According to the invention, the blades show a streamline shape like a propeller and the water propelling surfaces are smooth and temperate, but the motive power is strong and the washing ability is outstanding; meanwhile, water flow raised in the middle can be generated to ensure that clothes rotated to the central position of a wash bucket are scattered and effectively prevented from being intertwisted; in addition, the destroy of backward rotation to water flow trend is decreased to ensure that the anti-intertwist ability is further increased.

The purpose of the invention is a light aircraft, remotely supplied and remotely controlled, propelled by electrical motors coupled to propellers, this device being able to perform stationary flight and to move in the three space dimensions in a controlled way. The system includes an aircraft (1), a control unit (3) and a handling unit (4). The aircraft comprises four propellers, each of them driven by a electric motor, a gyroscopic device, tilt sensors, a yaw sensor and an extrenal protective body. The invention also describes the method for the fliht closed loop control. The main purpose of this invention is to provide a enjoyable and educative toy, mainly intended for indoor flight. In a variant of the invention, the aircraft is fitted with a miniaturized video camera, in order to perform remote inspections on buildings or elements difficult to access.

A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.

A vehicle, particularly a VTOL air vehicle, includes a duct carried by the vehicle frame with the longitudinal axis of the duct perpendicular to the longitudinal axis of the vehicle frame; a propeller rotatably mounted within the duct about the longitudinal axis of the duct to force an ambient fluid, e.g. air, therethrough from its inlet at the upper end of the duct through its exit at the lower end of the duct, and thereby to produce an upward lift force applied to the vehicle; and a plurality of parallel, spaced vanes pivotally mounted to and across the inlet end of the duct about pivotal axes perpendicular to the longitudinal axis of the duct and substantially parallel to the longitudinal axis of the vehicle frame. The vanes are selectively pivotal to produce a desired horizontal force component to the lift force applied to the vehicle. Various vane arrangements are disclosed for producing side, roll, pitch and yaw movements of the vehicle.

The invention provides an executing mechanism of a static pointing type rotary steerable drilling tool, and belongs to the technical field of rotary guide drilling tools. The executing mechanism comprises a shell (1) and a transmission shaft (2), wherein the shell (1) is connected with the transmission shaft (2) through joint connection units (4), the shell (1) is connected with the transmission shaft (2) through sealing units (5), and the sealing units (5) are used for isolating the joint connecting units (4) from drilling fluid. Each sealing unit (5) comprises at least one sealed spherical contact surface, wherein the spherical contact surface and the joint connection units (4) have the same central pivot point (P).

A helicoil interference fixation system comprising:a helicoil comprising a helical body comprising a plurality of turns separated by spaces therebetween, the helical body terminating in a proximal end and a distal end, and at least one internal strut extending between at least two turns of the helical body; andan inserter for turning the helicoil, the inserter comprising at least one groove for receiving the at least one strut;the helicoil being mounted on the inserter such that the at least one strut of the helicoil is mounted in the at least one groove of the inserter, such that rotation of the inserter causes rotation of the helicoil.