| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244073000 | Fluid | 10 |
| 20080283677 | Single-stage hypersonic vehicle featuring advanced swirl combustion - A single-stage hypersonic vehicle is comprised of a low-speed and a high-speed propulsion system. The low-speed propulsion system propels the single-stage vehicle to a threshold velocity, after which the high-speed propulsion system then takes over. The low-speed propulsion system includes a combined-cycle engine featuring a swirl generator that is integrated into a turbojet engine to provide a compact turbojet and swirl afterburner-ramjet propulsion system. The high-speed propulsion system includes a hypersonic engine that is operable at the threshold takeover velocity and beyond. In various embodiments, the high-speed propulsion system comprises a scramjet, rocket, or scramjet/rocket engine depending requirements. Benefits of the swirl generator design include its ability to rapidly and efficiently atomize, vaporize, mix and burn the fuel and oxidizer for the low speed propulsion system, significantly reduce length, weight, cooling requirements and complexity for both propulsion systems, while maintaining high propulsion performance and reducing propulsion and launch costs. | 11-20-2008 |
| 20090057494 | Propulsion system with integrated rocket accelerator - The present invention relates to a propulsion system for a vehicle. The propulsion system has an airframe integrated hydrocarbon fueled airbreathing engine, such as a ramjet or a scramjet. The propulsion system further has at least one rocket positioned so as to use the aft body contour of the vehicle directly for flow expansion. In a preferred embodiment, a plurality of rockets are arrayed across the width of the engine nozzle. | 03-05-2009 |
| 20110079684 | Centrifugal Engine and Vehicle Featuring Same - A centrifugal engine features a round enclosure centered on an axis and having an outer wall closing the interior around the axis between a base and a cover. An inner surface of the outer wall slopes outwardly away from the axis where the outer wall extends away from the base toward the cover. A liquid is contained within the sealed interior space. A drive system carried with the enclosure is operable to effect rotation of the round enclosure about the axis at sufficient speed to force the liquid outwardly away from the axis against the sloping inner surface of the outer wall and thereby exert pressure against the cover. This force of this pressure displaces the enclosure and the drive system carried therewith in a direction along the axis. Vehicle can employ multiple engines of this type along perpendicular axes to produce movement in different directions. | 04-07-2011 |
| 20110240804 | Integrated aircraft - In a jet aircraft according to the invention the jet engines are embedded in the wings and exhaust through fishtail diffuser ducts, from high aspect ratio nozzles located at a small control flap at the wing trailing edge. The jet engines are very-high bypass ratio geared turbofans operating at a lower than typical temperature. The jet aircraft according to the invention exhibits exceptionally low zero-lift drag leading to exceptionally high lift-to-drag ratios. | 10-06-2011 |
| 20130134265 | AIRCRAFT - An aircraft ( | 05-30-2013 |
| 20130161451 | APPARATUS AND METHOD FOR PARAGLIDERS - Apparatus and method for propelling a user wearing paragliding equipment are disclosed The apparatus includes at least one thruster for providing thrust in a predetermined direction; and an attachment element for attaching the at least one thruster to a user's body such that the thruster is secured against the front portion of the user's body. | 06-27-2013 |
| 20130175405 | PLASMA ACTUATING PROPULSION SYSTEM FOR AERIAL VEHICLES - A plasma propulsion nozzle incorporates a cylinder having an inlet and an outlet. A plurality of substantially cylindrical planarly disbanded electrodes with sandwiched dielectric spacers is cascaded in an array to be concentrically expanding from the inlet through an interior chamber to the outlet for a nozzle. A voltage source applies a periodic signal with rapidly reversing polarity to the electrodes with differential phase applied to adjacent electrodes in the array creating and expelling plasma clusters at each dielectric spacer inducing flow from the nozzle outlet to produce thrust. | 07-11-2013 |
| 20140097301 | Aircraft Lift And Propulsion From Disparate Air Flows - Generally, an inventive aircraft ( | 04-10-2014 |
| 20160152334 | PROPULSION SYSTEM FOR AN AERIAL VEHICLE | 06-02-2016 |
| 20160169214 | PLASMA ACTUATING PROPULSION SYSTEM FOR AERIAL VEHICLES | 06-16-2016 |
