| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | Airplane | US28866928 | 1928-06-27 | US1724883A | 1929-08-13 | MORRIS GEORGE A |
| 162 | METHODS OF DYNAMICALLY CONTROLLING AIRFLOW BEHIND A CARRIER AIRCRAFT TO REDIRECT AIR FLOW DURING AN IN-FLIGHT RECOVERY OF AN UNMANNED AERIAL VEHICLE AND AN APPARATUS THEREFOR | EP17172934.6 | 2017-05-25 | EP3248872A1 | 2017-11-29 | BERNHARDT, Roger D; LEE, Alexander D; HUPP, Ryan L; GISSEN, Abraham N; ROTHACKER, Benjamin A |
An apparatus (100, 700, 1100, 1500) is provided for dynamically controlling airflow behind a carrier aircraft to redirect air flow during an in-flight recovery of an unmanned aerial vehicle (UAV). The apparatus comprises a frame (110, 910, 1110, 1310) attached to an end portion of an arm member extending from the carrier aircraft. The apparatus comprises a plurality of vanes (120, 720, 1220, 1320, 1510, 1520) disposed within the frame. Each vane is controllable between an opened position and a closed position to dynamically modify the airflow behind the carrier aircraft during the in-flight recovery of the UAV. Alternatively, or in addition to, the apparatus comprises a plurality of compressed air jets (950, 1050, 1150, 1350) disposed on the frame, wherein each jet is controllable to provide active airflow to dynamically modify the airflow behind the carrier aircraft during the in-flight recovery of the UAV.
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| 163 | ORTHOTROPIC BIMORPH FOR IMPROVED PERFORMANCE SYNTHETIC JET | EP15174291.3 | 2015-06-29 | EP2966700B1 | 2017-08-09 | WHALEN, Edward A.; GRIFFIN, Steven F. |
| 164 | SURFACES WITH IMMOBILIZED ENZYMES AND ANTI-ICING PROTEINS | EP09742382.6 | 2009-04-28 | EP2276836B1 | 2017-01-18 | BAUER, Karin; BOLZMACHER, Christian; FRIEDBERGER, Alois; REIDT, Ulrich |
| 165 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | EP14751133 | 2014-02-10 | EP2956356A4 | 2016-11-30 | FREUND DONALD |
| A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist. | ||||||
| 166 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | EP14751877 | 2014-02-10 | EP2956355A4 | 2016-11-02 | FREUND DONALD |
| A system for controlling a magnitude of a sonic boom caused by off-design operation of a supersonic aircraft includes a sensor configured to detect a condition of the supersonic aircraft. The system further includes a control surface that is mounted to a wing of the supersonic aircraft. The system still further includes a processor communicatively coupled to the sensor and operatively coupled with the control surface. The processor is configured to (1) receive information from the sensor indicative of the condition of the supersonic aircraft, (2) determine that there is a deviation between a lift distribution and a design-condition lift distribution based on the information, and (3) control the control surface to move in a manner that reduces the deviation. The magnitude of the sonic boom is reduced when the deviation is reduced. | ||||||
| 167 | WING FOR GENERATING LIFT FROM AN INCIDENT FLOW | EP11716668.6 | 2011-04-14 | EP2558361B1 | 2016-10-26 | MUSTERS, Robert Jan |
| 168 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | EP14751884.9 | 2014-02-10 | EP2956358A1 | 2015-12-23 | FREUND, Donald |
| A system for controlling a magnitude of a sonic boom caused by off-design operation of a supersonic aircraft includes a sensor configured to detect a condition of the supersonic aircraft. The system further includes a control surface that is mounted to a wing of the supersonic aircraft. The system still further includes a processor communicatively coupled to the sensor and operatively coupled with the control surface. The processor is configured to (1) receive information from the sensor indicative of the condition of the supersonic aircraft, (2) determine that there is a deviation between a lift distribution and a design-condition lift distribution based on the information, and (3) control the control surface to move in a manner that reduces the deviation. The magnitude of the sonic boom is reduced when the deviation is reduced. | ||||||
| 169 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | EP14751160.4 | 2014-02-10 | EP2956357A1 | 2015-12-23 | FREUND, Donald |
| A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist. | ||||||
| 170 | A MULTIFUNCTIONAL EROSION PROTECTION STRIP | EP13857582.4 | 2013-11-20 | EP2922753A1 | 2015-09-30 | NORDIN, Pontus; STRINDBERG, Göte |
| 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. | ||||||
| 171 | FLEXIBLES FLÜGELPROFIL | EP11830104.3 | 2011-11-26 | EP2646316B1 | 2015-07-22 | Schaller, Felix |
| 172 | AERODYNAMIC STRUCTURE WITH ASYMMETRICAL SHOCK BUMP | EP09715399.3 | 2009-02-17 | EP2247497B1 | 2015-07-01 | WOOD, Norman |
| An aerodynamic structure comprising a shock bump (3) extending from its surface. The shock bump is asymmetrical about a plane of asymmetry, and the plane of asymmetry: passes through a centre (6) of the shock bump, is parallel with a principal direction of air flow over the structure, and extends at a right angle to the surface of the structure. | ||||||
| 173 | Rotor hub fairing system for a counter-rotating, coaxial rotor system | EP13178492.8 | 2013-07-30 | EP2692633A2 | 2014-02-05 | Matalanis, Claude G.; Wake, Brian E. |
A rotor hub fairing system (36) for use in a counter-rotating, coaxial rotary wing aircraft is provided including an upper hub fairing (38) defined about an axis. A lower hub fairing (40) is similarly defined about the axis. An airfoil shaped shaft fairing (42) is disposed between the upper hub fairing (38) and the lower hub fairing (40). The airfoil shaped shaft fairing (42) has a thickness to chord (t/c) ratio in the range of about 20% and about 45%.
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| 174 | DEVICE FOR REDUCING THE CROSS-STREAM FORCE GENERATED BY THE SECTION OF AIR REFUELLING BOOMS | EP07788694 | 2007-06-15 | EP2168869A4 | 2013-10-09 | RUIZ CALAVERA LUIS PABLO; MARISCAL SÁNCHEZ FRANCISCO JAVIER |
| 175 | WING FOR GENERATING LIFT FROM AN INCIDENT FLOW | EP11716668.6 | 2011-04-14 | EP2558361A2 | 2013-02-20 | MUSTERS, Robert Jan |
| The invention relates to a wing (1) for generating lift and comprises a trailing edge (5), a leading edge (3), an inner end (7), an outer end (9), a top surface (10) and a bottom surface (12). The wing comprises an aerofoil with a chord line and a span direction. The leading edge comprises a kink (21) between the inner (7) end and the outer end (9). The leading edge comprises a forward sweep part between the inner end and the kink extending towards the kink presenting an angle (a) relative to the span direction. The leading edge comprises a backward sweep part (35) between the kink and the outer end extending from the kink presenting an angle (β) relative to the span direction. The top surface comprises a flow control means (30) for controlling the lift at least partly located between a leading edge part between the kink and the outer end and located between the leading edge and the trailing edge. | ||||||
| 176 | Conformal aero-adaptive nozzle / aftbody | EP06425228.1 | 2006-04-03 | EP1710156A3 | 2011-08-17 | Miller, Daniel N.; Young, David D. |
The present invention provides flow field control techniques that adapt the aft body region flow field to eliminate or mitigate the development of massive separated flow field zones and associated unsteady vortical flow field structures. Embodiments of the present invention use one or more distributed arrays of flow control devices (submerged in the boundary layer) to create disturbances in the flow field that inhibit the growth of larger vortical structures and/or to energize the aft body shear layer to keep the shear layer attached the aft body surface. These undesirable aerodynamic phenomena produce increased vehicle drag which harms vehicle range, persistence, and loiter capabilities. Additionally, the unsteady nature of the turbulent vortical structures shed in the aft body wake region may produce increased dynamic buffeting and aft body heating by entraining nozzle jet exhaust (a.k.a. jet wash) - requiring additional structural support, shielding, and vehicle weight.
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| 177 | DEVICE FOR REDUCING THE CROSS-STREAM FORCE GENERATED BY THE SECTION OF AIR REFUELLING BOOMS | EP07788694.3 | 2007-06-15 | EP2168869A1 | 2010-03-31 | RUIZ CALAVERA, Luis Pablo; MARISCAL SÁNCHEZ, Francisco Javier |
Device to reduce the lateral force generated by an aerial refueling boom (11) of an aircraft characterized in that it comprises at least one plate (31), said plate (31) comprising two cantilevered wings (32, 33), said wings (32, 33) comprising perforations (34), so that the wake produced in the boom (11) has a lower dynamic pressure than that of the free stream. |
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| 178 | LANDING GEAR ASSEMBLEY | EP04726216.7 | 2004-04-07 | EP1613532B1 | 2008-12-10 | CHOW, Leung Choi; WOOD, Christopher Neil |
| An aircraft landing gear (9) includes a wheel (1) having a wheel rim (3) on which a tyre (4) is held. The gap (6) between the rim (3) and tyre (4) is bridged and covered by a sealing element (7), which thereby presents a smooth surface to the air flowing over the wheel during flight of the aircraft (8). Thus, noise that would otherwise be generated by the interaction of air and the parts of the wheel (1) and/or tyre (4) defining the gap (6) is reduced. Such noise reduction benefits may also be achieved by providing a tyre (4) and wheel (1) so shaped that there is no gap (6) between the tyre (4) and wheel rim (3). | ||||||
| 179 | Nacelle assembly having inlet airfoil for a gas turbine engine | EP08251047.0 | 2008-03-25 | EP1988266A2 | 2008-11-05 | Jain, Ashok K.; Winter, Michael |
A nacelle assembly (26) includes an inlet lip section (38) and an airfoil (50) adjacent to the inlet lip section (38). The airfoil (50) is selectively moveable between a first position (X) and a second position (X') to adjust the flow of oncoming airflow and to influence an effective boundary layer thickness of the nacelle assembly (26).
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| 180 | Helicopter | EP04252900.8 | 2004-05-19 | EP1479605A2 | 2004-11-24 | Shiraishi, Takayuki c/o Fuji Jukogyo Kabushiki K.; Tsuura, Seiichi c/o Fuji Jukogyo Kabushiki Kaisha; Kuramochi, Kenji c/o Fuji Jukogyo Kabushiki K. |
A helicopter (1) having: a flow control device (8) provided at one of a lower portion of a side surface (2a) of a fuselage (2) and a portion on a lower surface (2a) of the fuselage (2) near the side surface (2a) and extending downward. |
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