| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244065000 | Screw | 11 |
| 20090026310 | Variable pitch anti torque coaxial counter rotation bi-prop rotor - Single engine aircrafts, spot light, seaplanes, ultra-light planes, gyro-planes, power parachutes, trikes, airship etc commonly use fixed pitch low efficiency propellers that generate unbalancing torque. Pilots need to make offset turning to anti-torque. The subject novel anti torque coaxial counter rotation Bi-Prop Rotor fill out the empty of such variable and reversible thrust anti-torque propulsion device. The Bi-Prop Rotor comprises an on axis driving compact unobvious gear box; 2 sets multiple blades prop-rotors with variable pitch push rods and bearing-plate assemblies, co-axial tandem mounted at both sides of the gear box; a set sliding bridge mechanism that synchronized the tandem prop-rotors blade pitch turning; and a driving pulley chain or bell driving system. When engine power up the driving pulley, the primary prop-rotor mounted with the pulley rotates, and drives the gear box. The gear box converts rotation to counter direction in the same RPM, and drives the second prop-rotor on axis end rotating. This bi-prop rotor has multiple unique features: A, anti-torque; B, linear vary blade pitch angle and thrust; C, can reverse blade pitch direction to produce reversed thrust to do air speed deceleration, or air braking; D, has extraordinary aerodynamic efficiency; E, substantially produces a lot more thrust with same engine power. | 01-29-2009 |
| 20090127384 | Wake Ingestion Propulsion System for Buoyant Aircraft - A system for utilizing the slower boundary layer and aircraft wake to improve propulsive efficiency for buoyant and semi-buoyant aircraft is described. By ingesting air through an annular inlet located at the aft portion of the aircraft and accelerating it via an embedded ducted fan, maximum propulsive efficiency may be obtained, without the excessive losses due to viscous drag forces experienced in vehicles utilizing long ducts drawing air from inlets placed further forward. The method also reduces the acoustic signature when compared to unshrouded stem propellers or freestanding ducts. | 05-21-2009 |
| 20100116927 | Solar cell module - The present invention pertains to a solar cell module comprising at least one photovoltaic element encapsulated between a front layer on its light receiving surface side and a back layer, said front layer comprising at least one layer comprising a tetrafluoroethylene (TFE) polymer [polymer (F)], said polymer (F) comprising: recurring units derived from TFE; and from 15 to 25% wt of recurring units derived from at least one perfluoromonomer [monomer (CM)] chosen among: (i) perfluoroalkylvinylethers complying with formula CF | 05-13-2010 |
| 20100224723 | AERIAL VEHICLE - Various embodiments of an aerial vehicle with propulsion system and a protective frame is disclosed. The propulsion system has an air intake side and air outlet side. The protective frame surround both the intake and outlet side of the propulsion system to protect at least some components of the propulsion system from obstacles and other aerial vehicles. In some embodiments, the propulsion system includes one or more rotors or propellers. In some embodiments, protective frame also surrounds the radial ends of the rotor or propeller. | 09-09-2010 |
| 20110127373 | Autophagous multifunction structure-power system - A vehicle including at least one bladder for containing a fuel as liquid and gas at a predetermined pressure, with a bladder outlet arranged to releasing fuel from the bladder and to maintain the fuel in the bladder at the predetermined pressure, the fuel provides thrust to the vehicle upon combustion, the fuel-filled bladder providing initial structural integrity of the vehicle. In an exemplary embodiment, the vehicle is an unmanned anal vehicle. A combustion chamber and thermoelectric conversion module can generate electricity for a propellor and battery from the fuel supply. Internal vapor pressure is maintained until the fuel bladder is empty. | 06-02-2011 |
| 20110127374 | METHODS AND SYSTEMS FOR MINIMIZING FLOW DISTURBANCES IN AIRCRAFT PROPELLER BLADES CAUSED BY UPSTREAM PYLONS - Methods for minimizing the effects of pylori induced disturbances of the airflow at the propeller blades ( | 06-02-2011 |
| 20110186679 | AIRCRAFT WITH AT LEAST TWO PROPELLER DRIVES ARRANGED AT A DISTANCE FROM ONE ANOTHER IN THE SPAN WIDTH DIRECTION OF THE WINGS - An aircraft with a fuselage and two aerodynamic wings, which each accommodate at least two propeller drives spaced a apart from each other in the wingspan direction, each with a propeller rotational axis, wherein the aircraft has a controller for activating the propeller drives, wherein in one operating mode of the controller for generating propulsion, the propeller drives are activated in such a way that the outer section of a propeller secured to the respective propeller rotational axis is moved from the top down on the side facing the fuselage. | 08-04-2011 |
| 20120187241 | HANG GLIDER ELECTRIC PROPULSION SYSTEM AND METHOD - The system includes a keel fitting that can be rigidly attached directly to the keel of the hang glider. It also includes two elongated frame members symmetrically mounted on opposite sides of the keel fitting. At least one electrical motor is mounted on each frame member and there are at least two propellers, each in driving engagement with a corresponding one of the electrical motors. The system further includes an electrical power unit mounted on the back of the pilot. The electrical power unit includes at least one battery and a pilot-actuated control circuit to vary the electrical power supplied to the electrical motors. The system gives the pilot the capability of taking off from a flat terrain. Once airborne, the system is not operated and the hang glider can then be used as an unpowered one. | 07-26-2012 |
| 20160039529 | PROPELLER SAFETY FOR AUTOMATED AERIAL VEHICLES - The disclosure describes an automated aerial vehicle (AAV) and system for automatically detecting a contact or an imminent contact between a propeller of the AAV and an object (e.g., human, pet, or other animal). When a contact or an imminent contact is detected, a safety profile may be executed to reduce or avoid any potential harm to the object and/or the AAV. For example, if a contact with a propeller of the AAV by an object is detected, the rotation of the propeller may be stopped to avoid harming the object. Likewise, an object detection component may be used to detect an object that is nearing a propeller, stop the rotation of the propeller, and/or navigate the AAV away from the detected object. | 02-11-2016 |
| 244066000 | Tilting | 1 |
| 20090072082 | Propulsion system for an airship or hybrid aircraft - A propulsion system for an airship or hybrid aircraft includes a propeller and a pivot mechanism connected to the propeller. The pivot mechanism enables the propeller to pivot around a first pivot axis between a maneuver thruster position and an emergency ballonet fill position. Under normal conditions, when the propulsion system is disposed in the maneuver thruster position, the pivot mechanism also enables the propeller to pivot around a second pivot axis to control the attitude and thrust of the vehicle. However, in an emergency descent situation, the propeller may be rotated to the emergency ballonet fill position. | 03-19-2009 |
| 244069000 | Contra-propeller arrangements | 1 |
| 20110198440 | AIRCRAFT COMPRISING AT LEAST ONE ENGINE HAVING COUNTER-ROTATING ROTORS - The aircraft includes at least one engine having counter-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes a means capable of controlling the engine or at least one of the engines such that, at a given engine speed, the large axis of the ellipse or at least one of the ellipses extends in a direction for which the vibrations generated by the engine or engines have a minimum intensity in at least one predetermined site, particularly in a predetermined area, of the aircraft. | 08-18-2011 |
