| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | AIRCRAFT WITH FORWARD OPENING INLAY SPOILERS FOR YAW CONTROL | EP03816226.9 | 2003-12-16 | EP1587734B1 | 2006-11-29 | CLARK, Walter, Dennis |
| An aircraft (50) comprises first (68) and second (70) wings positioned on opposite sides of a longitudinal axis, a first forward opening control surface (52) attached to an upper surface of the first wing (68), and a second forward opening control surface (54) attached to an upper surface of the second wing (70) , wherein each of the first (56) and second hinges (58) is canted (01, 02) with respect to a direction perpendicular to a longitudinal axis of the aircraft. A method of providing yaw control of an aircraft is also provided. The method comprises the steps of providing a first forward opening, canted spoiler in a top surface of a first wing of the aircraft, providing a second forward opening, canted spoiler in a top surface of a second wing of the aircraft, and operating the first and second spoilers differentially to create a yaw moment. The creation of yaw moments without any down force has application in sweptback wings where the tips are behind the center of gravity of the aircraft. The advantage is in reducing radar cross section over traditional (forward hinged, rearward opening) spoilers where there must be a spoiler on the bottom side to counter the down force created by the top spoiler. | ||||||
| 102 | SINGLE SURFACE MULTI AXIS AIRCRAFT CONTROL | EP99925548.2 | 1999-04-06 | EP1071607B1 | 2006-07-05 | ARATA, Allen, A. |
| In accordance with the present invention, there is provided an aerodynamic control device for integrated use with an aircraft having an inboard lifting member. The inboard lifting member having a leading edge, a pair of opposing distal edges and a trailing edge. The control device is provided with a movable outboard member which extends substantially about the leading, distal and trailing edges of the inboard lifting member and is spaced apart therefrom. The outboard member is provided with a leading edge portion, a pair of opposing distal edge portions, and a trailing edge portion which are collectively movable in unison in relation to the inboard lifting member to form an uninterrupted airfoil surface extending about the inboard lifting member and the outboard member for achieving desired aerodynamic control of the aircraft. | ||||||
| 103 | AIRCRAFT WITH TOPSIDE ONLY SPOILERS | EP04809418.9 | 2004-05-26 | EP1631493A2 | 2006-03-08 | CLARK, Walter, D. |
| An aircraft (10) with swept back wings (16, 18) and spoilers (30,32) inlaid into the top surface (36) near the tips of the wings. The aircraft also includes an elevator (34) formed in the center back portion of the aircraft, which is also aft of the spoilers. It is aft to allow an auxiliary control in the elevator signal to cancel the unwanted pitch up moment caused by the spoilers only going up and being aft of the center of gravity of the aircraft. Roll is achieved with these spoilers by the direct action of the lift dumping on one side or the other and by taking advantage of the transformation of yaw into roll by the sweep back of the wings. | ||||||
| 104 | AIRCRAFT WITH FORWARD OPENING INLAY SPOILERS FOR YAW CONTROL | EP03816226.9 | 2003-12-16 | EP1587734A1 | 2005-10-26 | CLARK, Walter, Dennis |
| An aircraft (50) comprises first (68) and second (70) wings positioned on opposite sides of a longitudinal axis, a first forward opening control surface (52) attached to an upper surface of the first wing (68), and a second forward opening control surface (54) attached to an upper surface of the second wing (70) , wherein each of the first (56) and second hinges (58) is canted (01, 02) with respect to a direction perpendicular to a longitudinal axis of the aircraft. A method of providing yaw control of an aircraft is also provided. The method comprises the steps of providing a first forward opening, canted spoiler in a top surface of a first wing of the aircraft, providing a second forward opening, canted spoiler in a top surface of a second wing of the aircraft, and operating the first and second spoilers differentially to create a yaw moment. The creation of yaw moments without any down force has application in sweptback wings where the tips are behind the center of gravity of the aircraft. The advantage is in reducing radar cross section over traditional (forward hinged, rearward opening) spoilers where there must be a spoiler on the bottom side to counter the down force created by the top spoiler. | ||||||
| 105 | Double jet engine inlet | EP02075713.4 | 2002-02-22 | EP1243782A3 | 2005-03-02 | Seidel, Gerhard E. |
A dual boundary layer engine inlet for a turbofan propulsion engine of an aircraft having a first air inlet positioned generally within the boundary layer flowing around the exterior surface of the aircraft. A first passageway fluidly interconnects the first air inlet and the turbofan propulsion engine to provide air from the boundary layer to the bypass to reduce aerodynamic drag. A second air inlet is positioned generally outside of the boundary layer. This second passageway fluidly interconnecting the second air inlet and the turbofan propulsion engine to provide air outside of the boundary layer to the core and compressor of the turbofan engine to maintain engine efficiency. |
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| 106 | Dispositif d'accès a bord pour aéronef et aile volante équipée d'un tel dispositif | EP01403024.1 | 2001-11-26 | EP1209077B1 | 2005-01-26 | Depeige, Alain; Jarrige, Jean-Luc |
| 107 | FLUGGERÄT MIT EINEM AUFTRIEB ERZEUGENDEN RUMPF | EP02771971.5 | 2002-11-06 | EP1444130A1 | 2004-08-11 | SCHAFROTH, Konrad |
| The invention relates to an aircraft comprising a lift-producing fuselage (1) whose largest span (11) lies in the middle third (14) of the total length and whose horizontal projection progressively diminishes in the front third (13) and in the rear third (15). The aircraft also comprises two wings (2), whereby the surface of the projection of both wings represents, in a horizontal plane, less than thirty percent of the total lift surface, and the wings are located in the middle third (14) of the total length of the fuselage. The aircraft additionally comprises a horizontal tail unit (4) situated in the rear third of the fuselage. The aircraft has a shape similar to that of a fish. | ||||||
| 108 | Dispositif d'accès a bord pour aéronef et aile volante équipée d'un tel dispositif | EP01403024.1 | 2001-11-26 | EP1209077A1 | 2002-05-29 | Depeige, Alain; Jarrige, Jean-Luc |
Dispositif d'accès à bord pour aéronef et aile volante équipée d'un tel dispositif. Le dispositif d'accès comprend au moins un tunnel (20) rapporté à l'extérieur du carénage aérodynamique (12) de l'aéronef. Plus précisément, ce tunnel est fixé sur le bord de fuite du carénage (12) et il s'étend vers l'arrière sensiblement parallèlement à l'axe longitudinal de l'aéronef. Une porte (22) ferme la communication entre le compartiment passagers (10) et le tunnel (20). La partie arrière (26) du tunnel (20) est articulée et/ou détachable. Pour assurer l'évacuation de secours des passagers, la partie avant fixe (24) du tunnel peut être équipée d'un toboggan gonflable ou d'un plancher articulé. |
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| 109 | SINGLE SURFACE MULTI AXIS AIRCRAFT CONTROL | EP99925548.2 | 1999-04-06 | EP1071607A2 | 2001-01-31 | ARATA, Allen, A. |
| In accordance with the present invention, there is provided an aerodynamic control device for integrated use with an aircraft having an inboard lifting member. The inboard lifting member having a leading edge, a pair of opposing distal edges and a trailing edge. The control device is provided with a movable outboard member which extends substantially about the leading, distal and trailing edges of the inboard lifting member and is spaced apart therefrom. The outboard member is provided with a leading edge portion, a pair of opposing distal edge portions, and a trailing edge portion which are collectively movable in unison in relation to the inboard lifting member to form an uninterrupted airfoil surface extending about the inboard lifting member and the outboard member for achieving desired aerodynamic control of the aircraft. | ||||||
| 110 | Reconfiguration control system for an aircraft wing | EP98202463.0 | 1998-07-22 | EP0899190A2 | 1999-03-03 | Wakayama, Sean R. |
Independently deflectable control surfaces are located on the trailing edge of the wing of a blended wing-body aircraft. The reconfiguration control system of the present invention controls the deflection of each control surface to optimize the spanwise lift distribution across the wing for each of several flight conditions, e.g., cruise, pitch maneuver, and high lift at low speed. The control surfaces are deflected and reconfigured to their predetermined optimal positions when the aircraft is in each of the aforementioned flight conditions. With respect to cruise, the reconfiguration control system will maximize the lift to drag ratio and keep the aircraft trimmed at a stable angle of attack. In a pitch maneuver, the control surfaces are deflected to pitch the aircraft and increase lift. Moreover, this increased lift has its spanwise center of pressure shifted inboard relative to its location for cruise. This inboard shifting reduces the increased bending moment about the aircraft's x-axis occasioned by the increased pitch force acting normal to the wing. To optimize high lift at low speed, during take-off and landing for example, the control surfaces are reconfigured to increase the local maximum coefficient of lift at stall-critical spanwise locations while providing pitch trim with control surfaces that are not stall critical. |
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| 111 | Aircraft | US15793529 | 2017-10-25 | US09994330B2 | 2018-06-12 | Matthew Moxon |
| An aircraft comprises at least first and second gas turbine engines arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine comprising at least one compressor or turbine rotor disc defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors of at least one of the engines is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine is nonintersecting with another engine. | ||||||
| 112 | AN AIRCRAFT | US15793529 | 2017-10-25 | US20180057179A1 | 2018-03-01 | Matthew MOXON |
| An aircraft comprises at least first and second gas turbine engines arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine comprising at least one compressor or turbine rotor disc defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors of at least one of the engines is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine is nonintersecting with another engine. | ||||||
| 113 | Aircraft | US14795406 | 2015-07-09 | US09878788B2 | 2018-01-30 | Linden S. Blue; Austin J. N. Blue |
| An aircraft is provided that is convertible in flight between a rotary wing configuration and a fixed wing configuration. In its fixed wing configuration the aircraft resembles a Blended Wing Body (BWB) having a swept wing angle β. Conversions from the fixed wing configuration to the rotary wing configuration, and vice versa, are accomplished by flipping an outboard portion of one wing through 180° to reorient the leading edge of the outboard portion by an angle of 2β to establish a reverse sweep. In its rotary configuration, the entire aircraft is rotated. | ||||||
| 114 | Propeller | US14560964 | 2014-12-04 | US09849968B2 | 2017-12-26 | Jonathon J. Linch; Kyle M. Rahrig |
| A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. At least one propeller blade is fixedly attached to both the hub and ring shroud and extends radially therebetween for mutual rotation therewith. At least one stub blade has a first stub end radially spaced from a second stub end. The first stub end is fixedly attached to a selected one of the hub and ring shroud. The second stub end is cantilevered from the first stub end and is radially interposed between the first stub end and the selected one of the hub and ring shroud. | ||||||
| 115 | AIRCRAFT CELL COMPRISING A DOOR OPENING IN RECTILINEAR TRANSLATION | US15385379 | 2016-12-20 | US20170183077A1 | 2017-06-29 | Olivier Cazals; Jaime GENTY DE LA SAGNE |
| In order to simplify the connection of a door to the outer envelope of an aircraft cell, it is provided to dispose the door into a portion of the outer envelope having tilted sides, as is the case at the nose cones and the tail cones of conventional airplanes, and in various portions of blended wing body airplanes and flying wings. Thus, the door can be configured to displace, in rectilinear translation, from one of its extreme opening and closing positions to the other, without requiring that the door protrudes outside of the outer envelope in the closing position. | ||||||
| 116 | SOLAR RELAY AIRCRAFT POWERED BY GROUND BASED SOLAR CONCENTRATOR MIRRORS IN DUAL USE WITH POWER TOWERS | US14155360 | 2014-01-15 | US20170137138A9 | 2017-05-18 | John William Hunter |
| A solar relay aircraft system includes a solar relay aircraft having an upper surface, and a lower surface, and equipped with a solar radiation receiver on said lower surface and capable of converting solar energy to electrical energy. An electric motor in electrical connection with said solar radiation receiver to receive the electrical energy and drives a propeller to propel the solar relay aircraft. A number of ground-based reflector arrays include a plurality of reflecting mirrors for receiving solar radiation from the sun and direct the solar radiation from the sun towards the solar relay aircraft. | ||||||
| 117 | Multi-Role Aircraft With Interchangeable Mission Modules | US15352465 | 2016-11-15 | US20170066532A1 | 2017-03-09 | Abe Karem |
| 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. | ||||||
| 118 | COUPLING DEVICE, WING ASSEMBLY FOR AN AIRCRAFT COMPRISING SUCH COUPLING DEVICE AND AIRCRAFT COMPRISING SUCH WING ASSEMBLY | US15213636 | 2016-07-19 | US20170021911A1 | 2017-01-26 | Andreas Wildschek; Stefan Storm; Stephen Rolston; Martin Herring |
| A coupling device for supporting a first wing section against a second wing section of an aircraft, and configured for passive flight load alleviation includes a housing including a chamber including a first portion and a second portion and filled with a fluid, a piston device movably arranged in the chamber and separating the first portion from the second portion in a fluid tight manner, a first fluid pathway connecting the first portion to the second portion, a first pressure relief valve arranged in the first fluid pathway and blocking the first fluid pathway, if the pressure in the second portion is smaller than a first relief pressure and opening the first fluid pathway, if the pressure in the second portion is greater than the first relief pressure. In addition, the coupling device can be used to actuate the second wing section against the first wing section. | ||||||
| 119 | AIRCRAFT | US14795406 | 2015-07-09 | US20170008622A1 | 2017-01-12 | Linden S. Blue; Austin J. N. Blue |
| An aircraft is provided that is convertible in flight between a rotary wing configuration and a fixed wing configuration. In its fixed wing configuration the aircraft resembles a Blended Wing Body (BWB) having a swept wing angle β. Conversions from the fixed wing configuration to the rotary wing configuration, and vice versa, are accomplished by flipping an outboard portion of one wing through 180° to reorient the leading edge of the outboard portion by an angle of 2β to establish a reverse sweep. In its rotary configuration, the entire aircraft is rotated. | ||||||
| 120 | AIRCRAFT | US14976414 | 2015-12-21 | US20160207630A1 | 2016-07-21 | Matthew MOXON |
| An aircraft (2) comprises at least first and second gas turbine engines (10a, 10b) arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine (10a, 10b) comprising at least one compressor or turbine rotor disc (32-42) defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors (32-42) of at least one of the engines (10a, 10b) is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine (10a, 10b) is nonintersecting with another engine (10a, 10b). | ||||||
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