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Matches 301 - 350 out of 571

Document Document Title
WO/2004/033292
Aircraft having cab portions with integrated windshields are disclosed. The cab portion can include a rounded nose (112) and a windshield (113) positioned above and aft of a forward extremity of the rounded nose (112). A contour (115) of...  
WO/2004/026689
A torsionally de-coupled engine mount system (13) for use in tilt rotor aircraft (11) applications is disclosed, in which an engine is mounted at its forward end to a prop rotor gear box by means of a forward mount (303) that is a simple...  
WO/2004/015796
A closed loop energy storage system configured with a hydrogen tank, an oxygen tank, a fuel cell stack and an electrolyzer. A heat exchanger freeze-dries the hydrogen and oxygen prior to their storage in their respective tanks. The heat ...  
WO/2004/007044
The invention relates to a power generator arrangement for motorglider-type aircraft or model aircraft using photovoltaic cells, said aircraft (1) comprising a propulsion unit (2) in the form of an electric motor. The invention is charac...  
WO/2003/100330
A method and apparatus is provided for generating an artificial heat sink below ambient temperature for a cryogenic condenser (32) by isothermally magnetizing a paramagnetic fluid and removing the magnetic field, thereby creating a tempe...  
WO/2003/100288
The invention relates to a link consisting of a rod (2) comprising a connecting element (3, 4) at each end thereof and a geometrical axis which passes through said two connecting elements (3, 4). The invention is characterised in that th...  
WO/2003/098016
A counter-rotating rotary-piston engine (10) has an output shaft (12) with a cylindrical inner cavity rotatably mounted on a single support spindle (14) in the frame of an aircraft. The output shaft (12) extends substantially through the...  
WO/2003/094320
A Solid Oxide Regenerative Fuel Cell (SORFC) (240) or a Solid Oxide Fuel Cell (SOFC) (750) is incorporated into an electrically powered airplane to provide either regenerative or primary electrical energy. The SORFC (240), the SOFC (750)...  
WO/2003/074359
The invention concerns an engine pylon suspension attachment (10) of an engine (16) under an aircraft center section (12) comprising a rigid structure as well as a mechanism attaching said structure under the wing section. Said mechanism...  
WO/2003/066429
A VTOL vehicle with tiltable nacelles (14 and 16), with counter rotating fans which are directly driven by two included rotary engines. In an alternate embodiment there are two additional nacelles with additional thrusters. A redundant c...  
WO/2003/057561
An aircraft equipped with peripherally configured directional thrust capability has an onboard primary power source producing compressed air, and at least two thrust producing modules (11). Each thrust producing module (11) has a fuel so...  
WO/2003/058072
A reciprocating fluid engine (31) is provided having a high frequency and a high stroke force. The reciprocating fluid engine may be used to power a vehicle, such as a toy ornithopter (51). The reciprocating fluid engine has a piston (7)...  
WO/2003/057331
The present invention in one embodiment includes an aircraft having a fuselage with a powered propeller. The aircraft further includes a cambered main wing positioned aft of the fuselage and has a non cambered portion connected to the fu...  
WO/2003/050415
The invention relates to devices producing a reactive force for moving aircraft. The inventive device is embodied in the form of a MHD generator which comprises a toroidal body (1) made of a non-magnetic material whose hermetical cavity ...  
WO/2003/047972
A support assembly (20) is provided for selectively supporting an aircraft engine cowling (36) on an aircraft, the latch assembly including a cowling support (42) mounted to the cowling, an aircraft support (24) mounted to the aircraft f...  
WO/2003/039700
A compressed air engine and a flying object using the engine are disclosed. The flying object includes the following elements. That is, the compressed air engine includes: a top member 11 provided with an air inlet 16; an upper cylinder ...  
WO/2003/027499
A propulsion device which takes advantage of the fact that the mass of an object will decrease if the energy density of the object changes rapidly. The energy density is changed by causing rapid changes in stress on the bonds between the...  
WO/2002/079031
An integrated and modular high-speed aircraft (200) and method of design and manufacture. The aircraft (200) can have a supersonic or near-sonic cruise Mach number. In one embodiment, the aircraft (200) can include an aft body integrated...  
WO/2002/066324
The present invention relates to an integrated aircraft system which comprises an aircraft frame (4), a primary gas turbine engine (14) mounted within the nacelle cowl (12), a secondary power system (30) incorporated within the nacelle c...  
WO/2002/064427
The invention relates to a water rocket, the water flowing out of a heated boiler under high pressure via a nozzle, thus supplying the thrust which is used to start vehicles which are started on water.  
WO/2002/057135
An integrated and/or modular high-speed aircraft (1200) and method of design. The aircraft (1200) can have a supersonic or near-sonic cruise Mach number. In one embodiment, the aircraft can include an aft body (1214) integrated with a de...  
WO/2002/049914
The invention concerns a suspension part (1) comprising ends supporting connecting rods (8 and 9) articulated to a turbojet engine (3) which is constructed such that the ends form a pair of yokes (5) separated by a slot (19) bisecting th...  
WO/2001/085541
The invention relates to a propulsion system for aircraft, especially for high-flying and long-distance flying unmanned aircraft, to the aircraft itself and to a method for controlling aircraft. Said propulsion system has a first jet tur...  
WO/2001/076941
Disclosed is an aircraft (101), configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The ai...  
WO/2001/064513
A method for placing satellites in low earth orbit, uses a spacecraft which includes at least a turbofan engine (20), a rocket engine, and a payload, and comprises the steps of launching the spacecraft using the turbofan engine, flying t...  
WO/2001/058759
An engine arrangement (14) comprises a gas turbine engine unit (16) and first and second support members (18, 20). The support members (18, 20) extend from a structural component (24) of the engine casing (22) to support the engine unit ...  
WO/2001/058758
This disclosure provides a solar rechargeable aircraft (10) that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. The...  
WO/2001/058756
This disclosure provides a solar rechargeable aircraft (10) that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Tra...  
WO/2001/058757
This disclosure provides a solar rechargeable aircraft (10) that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. The...  
WO/2001/054981
A propulsion module (21) including a wave rotor detonation engine having a rotor (35a) with a plurality of fluid flow channels (35). The fluid flow channels (35) extend between an inlet rotor plate (34), which has a pair of fixed inlet p...  
WO/2001/054978
An improved aerobatic aircraft design having a first engine (18) located in the nose portion (14) of the fuselage (12) and a second engine (22) located in the tail portion (16) of the fuselage (12). The thrust components of both the firs...  
WO/2001/053151
The invention concerns a novel supersonic aircraft design whereof the fuel consumption and the take-off noise level are considerably less than those of existing aircraft or being designed. Said design is characterised in that it consists...  
WO/2001/030652
The aircraft comprises a central cabin (1), which is located in the center of a circular wing (3). Several pivotal electric drive units (102-112) are arranged in a gap between the central cabin and the circular ring. In hover flight, the...  
WO/2001/017851
The vehicle suitable for traveling and transportation is a spacecraft aimed at facilitating air, land or space transportation of all types of loads. Said vehicle is characterized in that the energy used for displacement is derived from g...  
WO/2000/071876
The present invention provides a fan speed indication system enabling the operator to control engine rotational speed to match specific thrust performance to flight requirements. The invention accommodates variations in engine thrust per...  
WO/2000/024633
The invention concerns a novel design for a supersonic aeroplane whereof the engine burn is much less than that of existing aeroplanes or those being planned. Said design is characterised by the use engines having very different characte...  
WO/2000/017049
A multi-linkage suspension system (20) including isolators positioned at the outboard ends of the linkages (26) for suspending and isolating an engine (22), such as an Auxiliary Power Unit (APU), from a structure (24), such as an aircraf...  
WO/2000/012382
A jet aircraft has an elongated fuselage (12) with an intermediate section (16) of maximum lateral cross section, a generally conical aft fuselage section (18) of relatively smaller cross section and a single vertical stabilizer (20) ext...  
WO/2000/009392
A jet aircraft (10) has a generally conical front fuselage section (14), a cylindrical intermediate fuselage section (16) defining a passenger compartment, a generally conical aft fuselage section (18), and a single vertical stabilizer (...  
WO/1999/050140
The invention relates to a propulsion system comprising at least two independent internal combustion engines (4, 5) which are positioned directly next to each other and synchronized and which each act on a common drive shaft (9). Means a...  
WO/1999/029570
The present invention relates to a system for the transformation of a traditional self-sustained horizontal take-off and landing aircraft into hybrid, integrated, self-sustained vertical take-off and landing and horizontal flight compris...  
WO/1999/024320
The invention concerns a device for locking an engine on an aircraft pylon (10) comprising a main lock-on structure and a standby lock-on structure (52). The main lock-on structure comprises a bracket (16) fixed to the pylon (10), and at...  
WO/1999/020527
An aircraft having a frame (1) and at least a rotor (2a, 2b) for providing lift for the aircraft. The aircraft comprises a means for accommodation purposes. Furthermore, solar cells (5) are arranged on the aircraft for exploiting solar e...  
WO/1999/007804
The invention relates to a method for actuating nonsystem-connected vehicles by means of high-temperature accumulators and for the operation of stationary energy storage using material with high evaporation enthalpy as storage media for ...  
WO/1998/047763
The invention concerns a traction system for a propeller-driven transport aeroplane comprising at least a first and second pair of propellers (11, 12; 31, 32) mounted in the aeroplane wing plane. Each pair of propellers comprises two pro...  
WO/1998/039207
A reusable rocket airplane (10) which may be utilized to launch satellites (26) and other payloads into space. The airplane may also be used for rapid surface to surface flight. The reusable rocket airplane (10) may be safely supplied wi...  
WO/1998/025821
Aircraft equipped with pod-mounted rotary piston and contra-rotating propeller jet engines. One aspect of the invention consists in the adaptation of the rotary piston and contra-rotating propeller piston jet engines (3) to any aircraft ...  
WO/1998/021092
First and second pylon flaps (30, 32) are located on aft portions of the first and second jet engine pylons, respectively. The first and second pylon flaps (30, 32) are moveable between retracted pylon flap angular orientations and exten...  
WO/1998/010984
An apparatus and method for reducing noise within the fuselage of a propeller driven aircraft (20). In one embodiment the propeller blades (38) are spaced apart and in front of an offset inlet (48). The inlet (48) provides air to a gas t...  
WO/1998/005553
The present invention provides a tailcone and power assembly (10) mountable to the body of an aircraft using a height adjustable dolly (11). The tailcone assembly comprises a longitudinal support member (14), a gas turbine engine (12) mo...  

Matches 301 - 350 out of 571