| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | AIRCRAFT WITH RECIPROCATING ENGINES PARTIALLY EMBEDDED IN THE FUSELAGE | US12582262 | 2009-10-20 | US20100096495A1 | 2010-04-22 | Jean-Loic Hervé LECORDIX; Marc Patrick Tesniere; Stéphane Jacques Francois Thomas |
| Aircraft provided with turbojet engines of which the nacelles are partially embedded in the fuselage of the aircraft, characterised in that it comprises on engine nacelles an internal space comprising a platform capable of supporting personnel and maintenance equipment, with the portions of the nacelles located inside the aircraft comprising trapdoors or means for accessing inside the engines from the platform. | ||||||
| 182 | AIRCRAFT ENGINE SYSTEM WITH GEARBOX UNIT | US11850871 | 2007-09-06 | US20090212156A1 | 2009-08-27 | Eric W. Blumer |
| An engine system for an aircraft includes an engine and a gearbox. The engine is mounted in a nacelle region of the aircraft. The gearbox is coupled to the engine, and is mounted in a fuselage region of the aircraft. The fuselage region is separated from the fuselage region by a structure. | ||||||
| 183 | Aircraft having a pivotable powerplant | US11451216 | 2006-06-12 | US20090072079A1 | 2009-03-19 | Arthur V. Hawley |
| Aircraft including an airframe having a fuselage extending between a forward end and an aft end opposite the forward end. The aircraft further includes a powerplant pivotally connected to the fuselage adjacent the aft end. The powerplant produces exhaust during operation of the aircraft. The powerplant is selectively pivotable to direct exhaust at multiple angles with respect to the fuselage. | ||||||
| 184 | Aircraft configuration | US12000881 | 2007-12-18 | US20080245925A1 | 2008-10-09 | Kenneth F. Udall |
| Some aircraft configurations have an engine arrangement comprising engines as part of an aft fuselage. In order to accommodate such engine arrangement positions, wings are rearwardly displaced compared to other aircraft configurations for balance across the fuselage. By creating empennage functions utilising the nacelle of engines as well as flaps to create rudder and elevator functions, it is possible to accommodate larger engine sizes more suitable for noise control with a reduced necessity for designed rearward movement of wings. | ||||||
| 185 | Aircraft propulsive power unit | US10261832 | 2002-09-30 | US20030102405A1 | 2003-06-05 | Finbarr McEvoy |
| An aircraft having a propulsive power unit supported in a fuselage mounted configuration and including an engine and a nacelle structure housing the engine. The nacelle structure is provided with upper and lower displaceable nacelle portions, such as thrust reverser cowls and fan cowl doors which are displaceable between closed dispositions which they occupy during operational conditions of the aircraft and open dispositions which they take up to provide access to engine components. The upper and lower nacelle portions are so mounted as to be displaceable to their open and closed dispositions in movements in which one is assisted by gravitational force and the other is displaced against gravitational force. A force transfer mechanism is provided for transfer during opening and closing movements of the nacelle portions of gravitational force assisting displacement of one of the nacelle portions to assist in displacement of the other nacelle portion being displaced against gravitational force. | ||||||
| 186 | Twin engine aircraft | US09132273 | 1998-08-11 | US06199795B1 | 2001-03-13 | Samuel B. Williams |
| A jet aircraft has a generally conical front fuselage section, a cylindrical intermediate fuselage section defining a passenger compartment, a generally conical aft fuselage section, and a single vertical stabilizer. The aircraft's propulsion engines are mounted on pylons on the conical aft fuselage section with the air inlets thereof disposed entirely within a rearward projection of the lateral cross section of the intermediate fuselage section thereby to preclude the ingestion of foreign objects into the engines while minimizing the effect of boundary layer airflow. The exhaust nozzles extend rearwardly past the vertical stabilizer to minimize side line noise. | ||||||
| 187 | Single engine aircraft | US898138 | 1997-07-22 | US6089504A | 2000-07-18 | Samuel B. Williams; Elbert L. Rutan |
| A jet aircraft has a generally cylindrical fuselage section defining a passenger compartment and a generally conical aft fuselage section having a maximum lateral dimension substantially smaller than the lateral dimension of the fuselage section. A propulsion engine is mounted on the vertical stabilizer of the fuselage and has an air inlet disposed entirely within a rearward projection of the fuselage passenger compartment to preclude the ingestion of foreign objects into the engine. | ||||||
| 188 | Twin engine aircraft | US897771 | 1997-07-21 | US5957405A | 1999-09-28 | Samuel B. Williams |
| A jet aircraft has a generally conical front fuselage section, a cylindrical intermediate fuselage section defining a passenger compartment and a generally conical aft fuselage section having a maximum lateral dimension substantially smaller than the maximum lateral dimension of the intermediate fuselage section. The aircraft's propulsion engines are mounted on combination vertical and horizontal stabilizers in spaced relation to the conical aft fuselage section with the air inlets and exhaust nozzles thereof disposed entirely within a rearward projection of the lateral cross section of the intermediate fuselage section to preclude the ingestion of foreign objects thereinto and maximize efficiency of boundary layer air flow. | ||||||
| 189 | Multi-purpose aircraft | US812823 | 1997-03-06 | US5850990A | 1998-12-22 | David E. Gevers |
| Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water. | ||||||
| 190 | Aircraft pylon | US37764 | 1987-04-13 | US5156353A | 1992-10-20 | Philip R. Gliebe; Rudramuni K. Majjigi |
| An aircraft propulsion system includes at least one pusher propeller mounted to a nacelle mounted to the aircraft by a pylon which produces a wake which impinges upon the propeller. The wake from the pylon is modified to reduce noise and vibration produced by the propeller interaction with the wake. The propulsion system may include a pair of counterrotating pusher propellers. | ||||||
| 191 | Aircraft pylon | US81772 | 1987-08-05 | US4966338A | 1990-10-30 | Bruce J. Gordon |
| In an aircraft propulsion system which includes a pusher propeller driven by an engine which is mounted to a fuselage by a pylon, the invention concerns apparatus for reducing turbulence generated by the pylon. In one example, a flap or vane attached to the pylon postpones the onset of flow separation, thereby reducing turbulence. | ||||||
| 192 | Mounting assembly for unducted prop engine and method | US157911 | 1988-02-19 | US4917336A | 1990-04-17 | Loyd D. Jacobs; Belur N. Shivashankara |
| An engine assembly comprising an engine having an unducted propeller mounted in a pusher configuration. The engine is supported by a mounting strut located upstream of the propeller. The trailing edge portion of the strut discharges air through a rearwardly facing slot to diminish discontinuity of airflow moving from the region of the strut to the propeller, so that load variations on the propeller are diminished, and also improves flow of the intersection of the strut and the fuselage. | ||||||
| 193 | Modifications to jet aircraft having aft fuselage-mounted nacelles overlapping the wing assemblies | US941349 | 1978-09-11 | US4311289A | 1982-01-19 | Thomas Finch |
| Modifications to a jet aircraft of the type having aft fuselage-mounted engine nacelles overlapping trailing edge portions of the aircraft's wings, wherein a channel area defined by the fuselage, wing, pylon and attached nacelle is shaped to prevent air flowing therethrough from forming a shock wave during flight operation in the transonic regime, resulting in significant drag reduction as compared to an unmodified jet aircraft of a similar type. Further modifications to the jet aircraft's wings provide additional lift while significantly reducing drag as compared to a similar, unmodified aircraft. The present invention is particularly adaptable for use with Gates Learjet type aircraft, especially Models 23, 24, 25 and other models having similar nacelle, pylon and inboard wing arrangements. | ||||||
| 194 | Aircraft with boundary layer control | US41513764 | 1964-12-01 | US3253808A | 1966-05-31 | LA FAVE ELMA O |
| 195 | TRANSVERSE-MOUNTED POWER TURBINE DRIVE SYSTEM | PCT/US2014070061 | 2014-12-12 | WO2015134081A3 | 2015-12-30 | LORD WESLEY K |
| The present disclosure relates generally to an aircraft with counter-rotating pusher props powered by a gas turbine engine having a power turbine disposed substantially perpendicular to the compressor, combustor and turbine gas generator power core axis, as well as to the aircraft longitudinal axis. | ||||||
| 196 | REAR SECTION OF AN AIRCRAFT INCLUDING AN ENGINE MOUNTING STRUCTURE SWINGABLY MOUNTED ON THE FUSELAGE | PCT/FR2010050566 | 2010-03-29 | WO2010112742A3 | 2011-03-17 | LAFONT LAURENT; SAUCRAY JEAN MICHEL; QUIROZ-HERNANDEZ ESTEBAN; ANTYPAS JEROME; BONNET MATHIEU; JOURNADE FREDERIC |
| The invention relates to a rear section of an aircraft including two connecting rods (66) symmetrically arranged on either side of a vertical median plane (P), each connecting rod having an end mounted on an engine mounting structure (14) and another end mounted on the fuselage (6), said section being designed so as to enable, by rotating the connecting rods (66) about the rotational axes thereof, a limited amplitude swinging movement of the assembly (23) formed by the mounting structure and the engines, relative to the fuselage (6), through first and second openings (18) of the fuselage. | ||||||
| 197 | FLIGHT DYNAMICS FOR AN AIRCRAFT | PCT/US2007088725 | 2007-12-21 | WO2008080135A2 | 2008-07-03 | BUTLER CLARK M |
| An aircraft (100) including a wing (110) and a pylon (1 14), wherein the pylon provides an airfoil (134) inverted for an airfoil of the wing, and an improvement and method for improved flight dynamics for 20 and 30 Series Learjets are disclosed. The improvement includes an increased distance (106) between a leading edge (108) of a wing and an intake of an engine (102) of the aircraft, which reduces drag and increases lift for improved flight dynamics of the aircraft. The inverted airfoil of the pylon negates an influence of the pylon on flight dynamics for improved overall flight dynamic of the aircraft. The method includes steps of removing an original engine (12) from an original pylon (24), removing the original pylon from the fuselage (22) of the aircraft, and mounting a new pylon in a new location adjacent the fuselage (112), wherein the new location is aft of the original location. | ||||||
| 198 | Fuselage rear end of an aircraft | EP14382584.2 | 2014-12-30 | EP3040264B1 | 2018-07-11 | Arévalo Rodríguez, Elena; Cruz Domínguez, Francisco José; Moneo Peñacoba, Ana Reyes |
| Fuselage rear end of an aircraft, comprising: - a structural part (1) comprising a skin and longitudinal (30) and transversal reinforcing members (31, 32), and - a fairing (5). The structural part (1) longitudinally spans over the whole rear end and comprises a first portion (2) in which the transversal reinforcing members (32) occupy the whole perimeter of the corresponding fuselage section and at least a second portion (3) in which the transversal reinforcing members (31) occupy only a portion of the perimeter of the corresponding fuselage section, the fairing (5) being located below the second portion (3) of the structural part (1). | ||||||
| 199 | Gas turbine engine installation | EP14153969.2 | 2014-02-05 | EP2774852A3 | 2017-12-27 | Stretton, Richard |
A fuselage (36, 74, 144) mounted gas turbine engine installation (30, 70, 110), the installation (30, 70, 110) comprising at least one propeller stage (46, 82, 122) and a gas turbine core (50, 92, 132) arranged in use to drive the propeller stage (46, 82, 122). The core (50, 92, 132) is external to the fuselage (36, 74, 144) and the rotational axes of the core (50, 92, 132) and propeller stage (46, 82, 122) are offset with respect to each other.
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| 200 | An aircraft propulsion system and a method of controlling the same | EP12180220.1 | 2012-08-13 | EP2562082A3 | 2017-11-22 | Neuteboom, Martin |
An aircraft propulsion system (100) has a propulsive rotor assembly (20, 80) rotatable about an axis of rotation (24) and comprising a plurality of blades (22, 82) and a rotationally fixed vane assembly (60) located adjacent to the propulsive rotor assembly and arranged circumferentially around the axis of rotation. As airflow enters the propulsive rotor assembly, a portion of the airflow passes over the vane assembly which is configured to direct the airflow away from the rotor blades so as to reduce the relative velocity of the redirected airflow over the rotor blades. This results in a reduced tendency of the airflow through the propulsive rotor assembly to become choked.
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