| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244046000 |
Variable
| 65 |
| 244045000 |
Canard | 4 |
| 20080217486 | Small unmanned airborne vehicle airframe - An unmanned aerial vehicle (UAV) is designed for low-speed, low altitude, long endurance missions typical to UAVs of this size and class. The UAV structure is configured to be substantially impervious to small arms fire and to have a very small representative radar cross-section. The UAV is modular such that the main wings and tail wing assembly are quickly and easily, detached from the fuselage for ease of transport and to provide an airframe that is quickly and easily adapted to any particular mission. | 09-11-2008 |
| 20090008507 | AIRCRAFT WING - A powered aircraft wing is described including a flexible solid sheet having energy cells integrated with the sheet. | 01-08-2009 |
| 20090261207 | Stable aircraft - An aircraft is made stable via shortening the chord of the wings to shorten the travel of the wing's center of pressure. Since short chord wings have less wing area than normal wings, a multitude of short chord wings is necessary to regain the required lifting area for flight. The instant stability does not degrade aircraft maneuverability or high performance. | 10-22-2009 |
| 20100019099 | Integrally Ribbed Rogallo Wing Array - There is a Rogallo wing having an aerodynamic sheet having a leading end and a trailing edge. The trailing edge is curved to form a sheet of increasing concavity away from the leading edge. At least two folded edges extend between the leading end and the trailing edge are on opposed sides of the aerodynamic sheet, the two folded edges comprising integral ribs. A wind energy extraction apparatus comprises one or more concentrator wings that react with a flow of wind to induce a drop in static air pressure that is then used to drive one or more impellers and one or more power converters. The one or more concentrator wings are Rogallo wings. | 01-28-2010 |
| 20100051755 | TAIL-LESS BOXED BIPLANE AIR VEHICLE - An exemplary embodiment of the present invention sets forth an exemplary bi-plane air vehicle. The air vehicle may include, a plurality of wings coupled to one another in substantially a box configuration, wherein the bi-plane air vehicle has no tail. | 03-04-2010 |
| 20100200703 | AIRCRAFT PRESENTING TWO PAIRS OF WINGS - An aircraft comprises: a fuselage; a front pair of wings; a rear pair of wings; and a pair of bodies, each body interconnecting, at a distance from the fuselage, the front and rear wings that are situated on the same side of the fuselage. | 08-12-2010 |
| 20110031354 | Aircraft - An aircraft, particularly a solar powered, high altitude, long endurance, unmanned aerial vehicle, is equipped with a combination of canted down, raked back wing tips and trailing “tip tails” carried on booms from the tip regions of the mainplane. Each tip tail is positioned to be subject to the upwash field of the respective wing tip vortex, at least in the cruise condition of the aircraft. The wing tip form can achieve a reduction in induced drag and help to relieve wing root bending moment while the tip tails can act through their connections to the mainplane to provide torsional relief to the latter, particularly under lower incidence/higher speed conditions. In the higher incidence/lower speed cruise condition, however, the presence of the tip tails in the upwash fields of the wing tip vortices means that they can generate lift with a component in the forward direction of flight and hence contribute to the thrust requirements of the aircraft. | 02-10-2011 |
| 20110108675 | WING AND A MULTIPLE PROPELLER AIRCRAFT - A wing that includes a lower portion that is located between two curved portions; wherein the lower portion is substantially flat and the two curved portions extend above the lower portion; wherein the wing defines a space that is wider than twice a diameter of a propeller that introduces a quasi-laminar stream if positioned in proximity to the wing and is circulated at a desired speed. The curved portions can be arcuated ends of the wing. | 05-12-2011 |
| 20110248124 | AIRCRAFT WITH FORWARD LIFTING ELEVATOR AND RUDDER, WITH THE MAIN LIFTING SURFACE AFT, CONTAINING AILERONS AND FLAPS, AND AIRBRAKE - An area ruled forward lifting elevator aircraft | 10-13-2011 |
| 20110266398 | WING/FUSELAGE CONNECTION OF AN AIRCRAFT - A wing-fuselage connection of an aircraft, in which a wing ( | 11-03-2011 |
| 20120018590 | Bernoulli Micro Plane - A low cost method for motorized small indoor toy airplanes that significantly boosts the lifting forces resulting from Bernoulli Principle, and as such providing for a significantly reduced flying speed of that airplane, improved flight control, smaller turning radius and ability to fly in a much smaller room. | 01-26-2012 |
| 20120160968 | Mid-Wing Airplane - An airplane includes a wing mounted mid-level on a tubular fuselage. The wing includes carry-through that passes transversely through the fuselage and divides a cabin deck into fore and aft sections. At least one longitudinal passageway in the carry-through structure allows passenger/crew walk-through between the fore and aft sections of the deck. | 06-28-2012 |
| 20130221165 | OBLIQUE BLENDED WING BODY AIRCRAFT - An oblique wing aircraft designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment and an aft swept wing segment. A center oblique airfoil section connects the forward and aft swept wing segments. The center oblique airfoil section has a larger chord near its centerline than the chords of either of the forward or aft swept wing segments. The chord of the center oblique airfoil section tapers down more rapidly than the forward or aft wing segments as the center oblique airfoil section extends outboard toward the forward and aft swept wings. Preferably, the aircraft is an all-wing aircraft. | 08-29-2013 |
| 20130264428 | METHOD OF SEPARABLY COUPLING A PROPULSION MODULE AND A CARRIAGE MODULE OF AN AIRCRAFT, AND MODULAR AIRCRAFT IMPLEMENTING SAME - According to one embodiment, a modular aircraft includes a propulsion module dedicated to flight, combining avionic equipment—wing structures assembly, flight deck, engines, tail unit—and a module dedicated to the carriage of passengers and/or goods. These modules include external cells extending longitudinally along a main axis and having tubular end parts of the same outline in the region of two disconnectable-coupling structures, one axial-coupling structure for keeping an end face of the propulsion module against an end face of the carriage module, and one radial-coupling structure for keeping an end face of the propulsion module against an end face of the carriage module. The wing structures assembly of the propulsion module includes two wing structures having opposite sweeps which are connected at the end and by a longitudinal connecting spar. | 10-10-2013 |
| 20140042277 | FLYING DEVICE AND A WING CONSTRUCTION FOR THE SAME - Flying device, in which there is a fuselage ( | 02-13-2014 |
| 20140145040 | SYSTEM AND METHOD FOR MINIMIZING WAVE DRAG THROUGH BILATERALLY ASYMMETRIC DESIGN - An air vehicle having a bilaterally asymmetric configuration may include a body having a longitudinal axis. The air vehicle may further include longitudinally offset engine nacelles, asymmetrically lengthened engine nacelles, and/or longitudinally offset protruding aerodynamic surfaces. | 05-29-2014 |
| 20140151511 | AIRCRAFT WITH AT LEAST TWO AIRCRAFT FUSELAGES AND TWO MAIN WINGS - An aircraft includes at least two aircraft fuselages and two elongate main wings, wherein the main wings each have an extension direction which are at an angle to one another that differs from zero. Each of the two main wings is connected to the at least two aircraft fuselages. The main wings can thus be equipped mechanically simply and so as to have a low weight, and at the same time the transmission of forces between the wings and the fuselages is performed via a plurality of connections, and this leads to a relatively low material stress. | 06-05-2014 |
| 20140231593 | Multi-Role Aircraft With Interchangeable Mission Modules - A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft. | 08-21-2014 |
| 20150298787 | AN AIRFRAME LEADING EDGE - An airframe leading edge part designed to be replaceable fixed to a structural portion which during use moves through the air. The airframe leading edge part includes first and second longitudinal joint edges adapted to fit the structural portion. At least one joint is provided between the structural portion and at least one of the longitudinal joint edges. The joint is adapted to break in the event of a object strikes and deforms the airframe leading edge part during use. The joint is designed to break at beforehand determined maximum joint strength of the joint. Also a repair method for exchanging a damaged leading edge. | 10-22-2015 |
| 20150298791 | MULTIFUNCTIONAL EROSION PROTECTION STRIP - An airfoil article including a composite skin having a first surface and a second surface opposite first surface, forming a leading edge. The leading edge is during use subjected to an airflow meeting the leading edge at stagnation points. The leading edge includes an elongated member. The outer surface of the elongated member is arranged flush with the first surface of the composite skin such that an essentially smooth aerodynamic surface of the leading edge is formed. The elongated member is adapted to serve as an erosion protection of the leading edge and to function as an electrode of a plasma generating system. | 10-22-2015 |
| 20150298792 | DEFORMABLE WING INCLUDING A MOBILE UPPER SURFACE - Morphing aircraft wing with a mobile upper surface comprising a double skinning on the upper surface of the wing wherein one of the skinnings corresponds to the leading edge and the other corresponds to the trailing edge and they overlap in the central area of the wing with the possibility of relative displacement between the two skinnings and they extend in the direction of the chord of the wing profile, the wing comprises actuators that are positioned on the main wing spars and which exert a reaction force against said spars when they exert the force required to morph the wing displacing the skinnings in the direction of the chord of the profile to the configuration of low speed flight, take-off and landing. | 10-22-2015 |
| 20150298794 | AIRCRAFT WITH FORWARD SWEEPING T-TAIL - An aircraft includes a propulsor supported within an aft portion of the fuselage. A thrust reverser is supported proximate the propulsor for redirecting thrust forward to slow the aircraft upon landing. A tail extending from the aft portion of the fuselage is angled forward away from the aft portion and out of the discharge of airflow from the thrust reverser. | 10-22-2015 |
| 20150360765 | DOWNWARDLY EXTENDING WING TIP DEVICE - An aircraft including a wing, the end of the wing having a wing tip device, wherein the wing tip device includes a moveable region that is rotatable, about an axis of rotation extending out of the plane of the wing tip device, between: (i) a high-altitude cruise configuration in which the moveable region extends downwardly below the wing; and (ii) a ground-operating configuration in which the moveable region extends rearwardly behind the wing such that the ground clearance of the wing tip device is increased. | 12-17-2015 |
| 20150360787 | GAS TURBINE ENGINE WITH DISTRIBUTED FANS DRIVEN ON ANGLED DRIVE SHAFT - A gas turbine engine includes a gas generator that has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of the at least one gas generator turbine rotor. The fan drive turbine drives a driveshaft and the driveshaft engages gears to drive at least three fan rotors. The driveshaft extends away from the gas generator such that at least one of the fan rotors that is positioned remotely from the fan drive turbine on the driveshaft is spaced to be either more forward or more rearward of the fan drive turbine relative to at least one of the fan rotors positioned closer to the fan drive turbine. An aircraft is also disclosed. | 12-17-2015 |
| 20160009367 | RIB FOOT | 01-14-2016 |
| 20100224735 | CANARDED DELTOID MAIN WING AIRCRAFT - Canarded deltoid main wing aircraft idea allows for design of large supersonic civil and military aircraft with cruising speeds of up to Mach 3 at the altitude of over 25,000 meters. The fuel consumption per unit of payload of such aircraft would be at least twice lower with a longer range of over 50% when compared to existing supersonic aircraft of the same size. Simultaneously, the flight safety and ride quality during takeoff and landing at low speeds would be similar to the existing subsonic passenger aircraft. A low fuel consumption, long range, high ride quality, and high flight safety of these aircraft are widely opening a door for design of supersonic long range continental and intercontinental passenger aircraft that would be highly competitive with existing long range high subsonic passenger aircraft. | 09-09-2010 |
| 20120032033 | Wing piercing airplane - My invention is a wing piercing airplane design based on the Catamaran (or trimaran) boat design. The concept behind the wind piercing airplane is a airfoil that consist of forward pointed triangular shaped wing on the left & right side of the fuselage, triangular shaped forward pointed vertical fins, triangular shaped forward pointed horizontal tail, triangular forward pointed wingtips to pierce the oncoming air like a Catamaran boat pierce the water as it travels forward. Essentially applying water wave piercing physics to aeronautic flight theory. The objective of the new airfoil design is to exhibit wind piercing effects in the air for reduce drag for greater fuel efficiency, lower radar cross section when radar beam hits it head on for stealth military application, flight efficiency at both low subsonic and high supersonic speed in this same fix wing plane without the need for a swing wing geometry configuration. All airfoils from small propeller airplanes to supersonic jet fighters can have this same type of wind piercing fix wing airfoil without the need for a swing wing geometry configuration. This airfoil will replace straight wing aircraft and swept wing aircraft due to that the fact that this wing piercing airfoil is flight efficient at low speeds like a straight wing airplane and flight efficient at high speeds like a swept wing airplane. | 02-09-2012 |
| 20150336655 | BOX WING WITH ANGLED GAS TURBINE ENGINE CORES - An aircraft including a fuselage having a forward portion and an aft portion with a propulsion system mounted within the aft portion of the fuselage. A burst zone is defined that extends outward from the propulsion system. The aircraft includes a box wing extending from the aft portion of the fuselage to a forward portion of the fuselage that is disposed outside of the burst zone. | 11-26-2015 |
| 20160046375 | FORWARD MOUNTED AUXILARY AIRFOILS WITH SPOILERS - An axillary airfoil located as far forward as practicable on the fuselage of an airliner. During high speed cruise, the airfoil can be adjusted to provide supplemental lift to move the center of pressure forward, thereby reducing the amount of downforce needed to be produced by the vertical stabilizer. This would result in saving fuel. Spoilers mounted on the airfoils would be programmed to automatically deploy to return the center of pressure rearward whenever flight conditions require greater longitudinal stability. | 02-18-2016 |
| Entries |
| Document | Title | Date |
|---|
| 20080217486 | Small unmanned airborne vehicle airframe - An unmanned aerial vehicle (UAV) is designed for low-speed, low altitude, long endurance missions typical to UAVs of this size and class. The UAV structure is configured to be substantially impervious to small arms fire and to have a very small representative radar cross-section. The UAV is modular such that the main wings and tail wing assembly are quickly and easily, detached from the fuselage for ease of transport and to provide an airframe that is quickly and easily adapted to any particular mission. | 09-11-2008 |
| 20090008507 | AIRCRAFT WING - A powered aircraft wing is described including a flexible solid sheet having energy cells integrated with the sheet. | 01-08-2009 |
| 20090261207 | Stable aircraft - An aircraft is made stable via shortening the chord of the wings to shorten the travel of the wing's center of pressure. Since short chord wings have less wing area than normal wings, a multitude of short chord wings is necessary to regain the required lifting area for flight. The instant stability does not degrade aircraft maneuverability or high performance. | 10-22-2009 |
| 20100019099 | Integrally Ribbed Rogallo Wing Array - There is a Rogallo wing having an aerodynamic sheet having a leading end and a trailing edge. The trailing edge is curved to form a sheet of increasing concavity away from the leading edge. At least two folded edges extend between the leading end and the trailing edge are on opposed sides of the aerodynamic sheet, the two folded edges comprising integral ribs. A wind energy extraction apparatus comprises one or more concentrator wings that react with a flow of wind to induce a drop in static air pressure that is then used to drive one or more impellers and one or more power converters. The one or more concentrator wings are Rogallo wings. | 01-28-2010 |
| 20100051755 | TAIL-LESS BOXED BIPLANE AIR VEHICLE - An exemplary embodiment of the present invention sets forth an exemplary bi-plane air vehicle. The air vehicle may include, a plurality of wings coupled to one another in substantially a box configuration, wherein the bi-plane air vehicle has no tail. | 03-04-2010 |
| 20100200703 | AIRCRAFT PRESENTING TWO PAIRS OF WINGS - An aircraft comprises: a fuselage; a front pair of wings; a rear pair of wings; and a pair of bodies, each body interconnecting, at a distance from the fuselage, the front and rear wings that are situated on the same side of the fuselage. | 08-12-2010 |
| 20110031354 | Aircraft - An aircraft, particularly a solar powered, high altitude, long endurance, unmanned aerial vehicle, is equipped with a combination of canted down, raked back wing tips and trailing “tip tails” carried on booms from the tip regions of the mainplane. Each tip tail is positioned to be subject to the upwash field of the respective wing tip vortex, at least in the cruise condition of the aircraft. The wing tip form can achieve a reduction in induced drag and help to relieve wing root bending moment while the tip tails can act through their connections to the mainplane to provide torsional relief to the latter, particularly under lower incidence/higher speed conditions. In the higher incidence/lower speed cruise condition, however, the presence of the tip tails in the upwash fields of the wing tip vortices means that they can generate lift with a component in the forward direction of flight and hence contribute to the thrust requirements of the aircraft. | 02-10-2011 |
| 20110108675 | WING AND A MULTIPLE PROPELLER AIRCRAFT - A wing that includes a lower portion that is located between two curved portions; wherein the lower portion is substantially flat and the two curved portions extend above the lower portion; wherein the wing defines a space that is wider than twice a diameter of a propeller that introduces a quasi-laminar stream if positioned in proximity to the wing and is circulated at a desired speed. The curved portions can be arcuated ends of the wing. | 05-12-2011 |
| 20110248124 | AIRCRAFT WITH FORWARD LIFTING ELEVATOR AND RUDDER, WITH THE MAIN LIFTING SURFACE AFT, CONTAINING AILERONS AND FLAPS, AND AIRBRAKE - An area ruled forward lifting elevator aircraft | 10-13-2011 |
| 20110266398 | WING/FUSELAGE CONNECTION OF AN AIRCRAFT - A wing-fuselage connection of an aircraft, in which a wing ( | 11-03-2011 |
| 20120018590 | Bernoulli Micro Plane - A low cost method for motorized small indoor toy airplanes that significantly boosts the lifting forces resulting from Bernoulli Principle, and as such providing for a significantly reduced flying speed of that airplane, improved flight control, smaller turning radius and ability to fly in a much smaller room. | 01-26-2012 |
| 20120160968 | Mid-Wing Airplane - An airplane includes a wing mounted mid-level on a tubular fuselage. The wing includes carry-through that passes transversely through the fuselage and divides a cabin deck into fore and aft sections. At least one longitudinal passageway in the carry-through structure allows passenger/crew walk-through between the fore and aft sections of the deck. | 06-28-2012 |
| 20130221165 | OBLIQUE BLENDED WING BODY AIRCRAFT - An oblique wing aircraft designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment and an aft swept wing segment. A center oblique airfoil section connects the forward and aft swept wing segments. The center oblique airfoil section has a larger chord near its centerline than the chords of either of the forward or aft swept wing segments. The chord of the center oblique airfoil section tapers down more rapidly than the forward or aft wing segments as the center oblique airfoil section extends outboard toward the forward and aft swept wings. Preferably, the aircraft is an all-wing aircraft. | 08-29-2013 |
| 20130264428 | METHOD OF SEPARABLY COUPLING A PROPULSION MODULE AND A CARRIAGE MODULE OF AN AIRCRAFT, AND MODULAR AIRCRAFT IMPLEMENTING SAME - According to one embodiment, a modular aircraft includes a propulsion module dedicated to flight, combining avionic equipment—wing structures assembly, flight deck, engines, tail unit—and a module dedicated to the carriage of passengers and/or goods. These modules include external cells extending longitudinally along a main axis and having tubular end parts of the same outline in the region of two disconnectable-coupling structures, one axial-coupling structure for keeping an end face of the propulsion module against an end face of the carriage module, and one radial-coupling structure for keeping an end face of the propulsion module against an end face of the carriage module. The wing structures assembly of the propulsion module includes two wing structures having opposite sweeps which are connected at the end and by a longitudinal connecting spar. | 10-10-2013 |
| 20140042277 | FLYING DEVICE AND A WING CONSTRUCTION FOR THE SAME - Flying device, in which there is a fuselage ( | 02-13-2014 |
| 20140145040 | SYSTEM AND METHOD FOR MINIMIZING WAVE DRAG THROUGH BILATERALLY ASYMMETRIC DESIGN - An air vehicle having a bilaterally asymmetric configuration may include a body having a longitudinal axis. The air vehicle may further include longitudinally offset engine nacelles, asymmetrically lengthened engine nacelles, and/or longitudinally offset protruding aerodynamic surfaces. | 05-29-2014 |
| 20140151511 | AIRCRAFT WITH AT LEAST TWO AIRCRAFT FUSELAGES AND TWO MAIN WINGS - An aircraft includes at least two aircraft fuselages and two elongate main wings, wherein the main wings each have an extension direction which are at an angle to one another that differs from zero. Each of the two main wings is connected to the at least two aircraft fuselages. The main wings can thus be equipped mechanically simply and so as to have a low weight, and at the same time the transmission of forces between the wings and the fuselages is performed via a plurality of connections, and this leads to a relatively low material stress. | 06-05-2014 |
| 20140231593 | Multi-Role Aircraft With Interchangeable Mission Modules - A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft. | 08-21-2014 |
| 20150298787 | AN AIRFRAME LEADING EDGE - An airframe leading edge part designed to be replaceable fixed to a structural portion which during use moves through the air. The airframe leading edge part includes first and second longitudinal joint edges adapted to fit the structural portion. At least one joint is provided between the structural portion and at least one of the longitudinal joint edges. The joint is adapted to break in the event of a object strikes and deforms the airframe leading edge part during use. The joint is designed to break at beforehand determined maximum joint strength of the joint. Also a repair method for exchanging a damaged leading edge. | 10-22-2015 |
| 20150298791 | MULTIFUNCTIONAL EROSION PROTECTION STRIP - An airfoil article including a composite skin having a first surface and a second surface opposite first surface, forming a leading edge. The leading edge is during use subjected to an airflow meeting the leading edge at stagnation points. The leading edge includes an elongated member. The outer surface of the elongated member is arranged flush with the first surface of the composite skin such that an essentially smooth aerodynamic surface of the leading edge is formed. The elongated member is adapted to serve as an erosion protection of the leading edge and to function as an electrode of a plasma generating system. | 10-22-2015 |
| 20150298792 | DEFORMABLE WING INCLUDING A MOBILE UPPER SURFACE - Morphing aircraft wing with a mobile upper surface comprising a double skinning on the upper surface of the wing wherein one of the skinnings corresponds to the leading edge and the other corresponds to the trailing edge and they overlap in the central area of the wing with the possibility of relative displacement between the two skinnings and they extend in the direction of the chord of the wing profile, the wing comprises actuators that are positioned on the main wing spars and which exert a reaction force against said spars when they exert the force required to morph the wing displacing the skinnings in the direction of the chord of the profile to the configuration of low speed flight, take-off and landing. | 10-22-2015 |
| 20150298794 | AIRCRAFT WITH FORWARD SWEEPING T-TAIL - An aircraft includes a propulsor supported within an aft portion of the fuselage. A thrust reverser is supported proximate the propulsor for redirecting thrust forward to slow the aircraft upon landing. A tail extending from the aft portion of the fuselage is angled forward away from the aft portion and out of the discharge of airflow from the thrust reverser. | 10-22-2015 |
| 20150360765 | DOWNWARDLY EXTENDING WING TIP DEVICE - An aircraft including a wing, the end of the wing having a wing tip device, wherein the wing tip device includes a moveable region that is rotatable, about an axis of rotation extending out of the plane of the wing tip device, between: (i) a high-altitude cruise configuration in which the moveable region extends downwardly below the wing; and (ii) a ground-operating configuration in which the moveable region extends rearwardly behind the wing such that the ground clearance of the wing tip device is increased. | 12-17-2015 |
| 20150360787 | GAS TURBINE ENGINE WITH DISTRIBUTED FANS DRIVEN ON ANGLED DRIVE SHAFT - A gas turbine engine includes a gas generator that has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of the at least one gas generator turbine rotor. The fan drive turbine drives a driveshaft and the driveshaft engages gears to drive at least three fan rotors. The driveshaft extends away from the gas generator such that at least one of the fan rotors that is positioned remotely from the fan drive turbine on the driveshaft is spaced to be either more forward or more rearward of the fan drive turbine relative to at least one of the fan rotors positioned closer to the fan drive turbine. An aircraft is also disclosed. | 12-17-2015 |
| 20160009367 | RIB FOOT | 01-14-2016 |
| 20100224735 | CANARDED DELTOID MAIN WING AIRCRAFT - Canarded deltoid main wing aircraft idea allows for design of large supersonic civil and military aircraft with cruising speeds of up to Mach 3 at the altitude of over 25,000 meters. The fuel consumption per unit of payload of such aircraft would be at least twice lower with a longer range of over 50% when compared to existing supersonic aircraft of the same size. Simultaneously, the flight safety and ride quality during takeoff and landing at low speeds would be similar to the existing subsonic passenger aircraft. A low fuel consumption, long range, high ride quality, and high flight safety of these aircraft are widely opening a door for design of supersonic long range continental and intercontinental passenger aircraft that would be highly competitive with existing long range high subsonic passenger aircraft. | 09-09-2010 |
| 20120032033 | Wing piercing airplane - My invention is a wing piercing airplane design based on the Catamaran (or trimaran) boat design. The concept behind the wind piercing airplane is a airfoil that consist of forward pointed triangular shaped wing on the left & right side of the fuselage, triangular shaped forward pointed vertical fins, triangular shaped forward pointed horizontal tail, triangular forward pointed wingtips to pierce the oncoming air like a Catamaran boat pierce the water as it travels forward. Essentially applying water wave piercing physics to aeronautic flight theory. The objective of the new airfoil design is to exhibit wind piercing effects in the air for reduce drag for greater fuel efficiency, lower radar cross section when radar beam hits it head on for stealth military application, flight efficiency at both low subsonic and high supersonic speed in this same fix wing plane without the need for a swing wing geometry configuration. All airfoils from small propeller airplanes to supersonic jet fighters can have this same type of wind piercing fix wing airfoil without the need for a swing wing geometry configuration. This airfoil will replace straight wing aircraft and swept wing aircraft due to that the fact that this wing piercing airfoil is flight efficient at low speeds like a straight wing airplane and flight efficient at high speeds like a swept wing airplane. | 02-09-2012 |
| 20150336655 | BOX WING WITH ANGLED GAS TURBINE ENGINE CORES - An aircraft including a fuselage having a forward portion and an aft portion with a propulsion system mounted within the aft portion of the fuselage. A burst zone is defined that extends outward from the propulsion system. The aircraft includes a box wing extending from the aft portion of the fuselage to a forward portion of the fuselage that is disposed outside of the burst zone. | 11-26-2015 |
| 20160046375 | FORWARD MOUNTED AUXILARY AIRFOILS WITH SPOILERS - An axillary airfoil located as far forward as practicable on the fuselage of an airliner. During high speed cruise, the airfoil can be adjusted to provide supplemental lift to move the center of pressure forward, thereby reducing the amount of downforce needed to be produced by the vertical stabilizer. This would result in saving fuel. Spoilers mounted on the airfoils would be programmed to automatically deploy to return the center of pressure rearward whenever flight conditions require greater longitudinal stability. | 02-18-2016 |
