| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Engine arrangement | US09768590 | 2001-01-25 | US06543718B2 | 2003-04-08 | Michael J Provost |
| An engine arrangement (10) comprises propulsion means for propelling the aircraft (12), and drive means to drive the propulsion means. The arrangement (10) further includes mounting means to mount at least the propulsion means in a location spaced above the upper surface of the aircraft (10). In the preferred embodiment, the propulsion means is in the form of tip driven fans (14), and the drive means comprises gas generators (34) mounted within the body of the aircraft (10) fixedly connected by intake ducts (36) to the underside of the aircraft (10). | ||||||
| 82 | Separate boundary layer engine inlet | US09816985 | 2001-03-23 | US06527224B2 | 2003-03-04 | Gerhard E. Seidel |
| 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. | ||||||
| 83 | Blended wing and multiple-body airplane configuration | US09892275 | 2001-06-26 | US20020003190A1 | 2002-01-10 | Mithra M.K.V. Sankrithi; Steven J. Wald |
| A partial blended wing body airplane configuration combining the advantages of a pure blended wing configuration with the advantages of conventional aircraft design. A blended tri-body airplane configuration wherein three pressurized body elements are connected by and blended with a pressurized centerwing element. The sidebodies and centerbody are blended into the wing structure, producing a multi-body airplane whose body sections are interconnected utilizing wing payload carrying sections. | ||||||
| 84 | Engine arrangement | US09768590 | 2001-01-25 | US20010011691A1 | 2001-08-09 | Michael J. Provost |
| An engine arrangement (10) comprises propulsion means for propelling the aircraft (12), and drive means to drive the propulsion means. The arrangement (10) further includes mounting means to mount at least the propulsion means in a location spaced above the upper surface of the aircraft (10). In the preferred embodiment, the propulsion means is in the form of tip driven fans (14), and the drive means comprises gas generators (34) mounted within the body of the aircraft (10) fixedly connected by intake ducts (36) to the underside of the aircraft (10). | ||||||
| 85 | Delta-shaped aircraft with variable camber fuselage and wing | US157745 | 1998-09-21 | US6129308A | 2000-10-10 | Richard F. Nastasi; Walter S. Soeder |
| In accordance with the present invention, there is provided a variable camber delta-shaped aircraft. The aircraft is provided with an integrated fuselage/wing generally defining the aircraft and having longitudinal and lateral axes. The fuselage/wing has a forward section which is rotably attached to an aft section about the lateral axis. The aircraft is further provided with an aerodynamic lifting surface which is disposed about the fuselage/wing and defined by a camber. The forward section has a downwardly deflected position when rotated relative to the aft section. The forward and aft sections are cooperatively formed to increase the camber of the lifting surface when the forward section is in the deflected position. | ||||||
| 86 | Multi-service common airframe-based aircraft | US756154 | 1996-11-26 | US5897078A | 1999-04-27 | Robert W. Burnham; Michael F. Fitzpatrick; Dennis A. Muilenberg; Joseph K. Schoebelen; Laurence B. Trollen |
| A modular approach to the manufacture of high performance military aircraft allows different aircraft to be manufactured at affordable cost and with high part number commonality. An aircraft so constructed includes a delta wing; a forebody section, including a cockpit, which is mounted to the front of the wing; and a propulsion system support frame mounted beneath the forebody section and the underside of the wing. The propulsion system is supported within this frame. The aircraft can also include an aftbody section mounted to the aft end of the wing, which includes a 2-D variable thrust vectoring nozzle and a pair of canted vertical tails. The forebody section includes a chin inlet below the cockpit. The wing is preferably constructed using thermoplastic welding. | ||||||
| 87 | Rib for blended wing-body aircraft | US878628 | 1997-06-19 | US5893535A | 1999-04-13 | Arthur V. Hawley |
| Structural ribs for providing structural support for a structure, such as the pressure cabin of a blended-wing body aircraft. In a first embodiment, the ribs are generally "Y-shaped", being comprised of a vertical web and a pair of inclined webs attached to the vertical web to extend upwardly and outwardly from the vertical web in different directions, with only the upper edges of the inclined webs being attached to a structural element. In a second embodiment, the ribs are generally "trident-shaped", whereby the vertical web extends upwardly beyond the intersection of the inclined webs with the vertical web, with the upper edge of the vertical web as well as the upper edges of the inclined webs being attached to the same structural element. | ||||||
| 88 | Lifting-fuselage/wing aircraft having low induced drag | US642998 | 1996-05-13 | US5813628A | 1998-09-29 | Robert W. Hahl |
| A lifting-fuselage/wing aircraft having low drag at a selected cruise condition. The aircraft includes (a) a lifting fuselage having a cross-section constituting an airfoil in a majority of vertical planes taken parallel to the flight direction and an aspect ratio (AR.sub.f) of 0.33 to 1.10; (b) wings fixed to the fuselage having an aspect ratio (AR.sub.w) of at least 5.0; (c) a mechanism controlling aircraft attitude; and (d) a mechanism propelling the aircraft; wherein the wings and fuselage produce lift in varying proportions depending upon flight conditions as follows: (i) the aircraft has a cruise design point in which the fuselage lift coefficient (C.sub.LF) is 0.08 or less, and (ii) the fuselage lift coefficient is at least 0.50 at an angle of attack (.alpha..sub.LZo) of 10.degree., in level flight at sea level (ISA) with all movable lift enhancing devices retracted. | ||||||
| 89 | Aircraft | US25639472 | 1972-05-24 | US3869102A | 1975-03-04 | CARROLL CHARLES A |
| A cargo aircraft. A non-pressurized hull, which can comprise a number of substantially identical hull modules, defines a rectangular cargo area. The hull has an outer skin portion which, in its vertical, longitudinal section, conforms to an air foil shape. This air foil configuration generates substantially all the lift necessary to offset the combined weights of the hull and a reasonable load. The hull supports wings, engines and a pressurized cabin for an operating crew and other elements necessary for operating the aircraft.
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| 90 | All-wing aircraft | US8508749 | 1949-04-02 | US2650780A | 1953-09-01 | NORTHROP JOHN K; CERNY WALTER J |
| 91 | Aircraft | US21040538 | 1938-05-27 | US2210642A | 1940-08-06 | THOMPSON STEPHEN W |
| 92 | PROPELLER HAVING EXTENDING OUTER BLADES | EP16829009.6 | 2016-07-06 | EP3328729A2 | 2018-06-06 | LINCH, Jonathon J.; RAHRIG, Kyle M. |
| 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. The ring shroud includes an inner ring surface and a radially spaced, oppositely facing outer ring surface. At least one propeller blade is fixedly attached to both the hub and the inner ring surface and extends radially therebetween for mutual rotation therewith. At least one extending blade has a first extending blade end radially spaced from a second extending blade end. The first extending blade end is fixedly attached to the outer ring surface. The second extending blade end is cantilevered from the first extending blade end and is radially spaced from the ring shroud. | ||||||
| 93 | AIRCRAFT HAVING SUPPORTING FUSELAGE | EP16761131.8 | 2016-03-09 | EP3279082A1 | 2018-02-07 | Bosio Blanco, Carlos Conrado; Blanco, Roberto Horacio; Klarenberg, Alejandro Jose |
The aircraft defines a lifting volume including at least part of the central body housing the transported payload. Said volume has a conventional aerodynamic profile along the longitudinal direction of the aircraft, with portions of wings projecting symmetrically and transversely at both sides thereof From the longitudinal axis said wings at each side shows corresponding first sections with negative dihedral and forward swept until reaching corresponding inflexion points from which two distal second sections or tracts projects with positive dihedral and back swept until reaching the wingtips of the projected wingspan. |
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| 94 | PROPULSION SYSTEM FOR AN AERIAL VEHICLE | EP14816561 | 2014-06-25 | EP3016859A4 | 2017-04-26 | PRISELL ERIK |
| The invention relates to a propulsion system concept that is a propulsion system that is integrated in the hull of an aerial vehicle (1), which propulsion concept comprises at least one differential velocity fan (4), which is arranged on a shaft driven by one or more power units (2). The propulsion concept is intended to provide short takeoff and landing distances, high flight speed (high subsonic to transsonic) and to be able to provide low IR signature, low radar signature, a small cross section and low air resistance. The propulsion concept is called HPVO (High Performance Optimized Versatile propulsion). The invention is useful both for air vehicles of the type for conventional takeoff and landing, “CTOL” (Conventional Take Off and Landing), “Chair” and for vertical takeoff and landing, “V (t) OL” (Vertical (Take) Off and Landing’) and the flying wing (blended-body). The concept is applicable to both large and small aircraft, manned as well as unmanned aerial vehicles. | ||||||
| 95 | AN AIRCRAFT | EP15201624.2 | 2015-12-21 | EP3048048A1 | 2016-07-27 | Moxon, Matthew |
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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| 96 | RECESSED LIFT SPOILER ASSEMBLY FOR AIRFOILS | EP14792283.5 | 2014-04-28 | EP2991896A1 | 2016-03-09 | EMERICK, Mark F. |
| A spoiler assembly is provided that is engageable to a UAV that defines a body, an outer surface and an inner surface. The spoiler assembly comprises a spoiler, translatably connected to the UAV inner surface adjacent a first portion of the spoiler aperture. The spoiler defines an upper surface and an outer surface, the upper surface being substantially the same size and shape as the spoiler aperture. A spoiler shroud is connected to the UAV inner surface and extends within the UAV body about at least a portion of the spoiler aperture. A spoiler activating mechanism is secured to the UAV inner surface and connected the spoiler lower surface. The mechanism is operative to translate the spoiler between a first position wherein the spoiler upper surface is substantially flush with the UAV outer surface, and second a position, wherein the spoiler upper surface is disposed substantially within the UAV body. | ||||||
| 97 | OBLIQUE BLENDED WING BODY AIRCRAFT | EP08798974 | 2008-08-29 | EP2193079A4 | 2013-11-13 | MCDONNELL WILLIAM RANDALL |
| An oblique wing aircraft (1) designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment (27) on one side of the wing and an aft swept wing segment (29) on the opposite side of the wing. A center oblique airfoil section (25) 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. The center oblique airfoil section is not shaped solely to function as a circular fairing to fill the gap between an oblique wing and a fuselage at different oblique wing angles, nor is it a second wing in an X wing configuration. Preferably, the aircraft is an all-wing aircraft. | ||||||
| 98 | Verfahren zur Erzeugung des Kräftesystems für ein Mehrzweckluftverkehrsmittel und Mehrzweckluftverkehrsmittel zur Durchführung des Verfahrens | EP09008047.4 | 2009-06-19 | EP2179903A2 | 2010-04-28 | Spashchenko, Victor |
Die Erfindung betrifft ein Verfahren zur Erzeugung des Kraftsystems für ein Mehrzweckflugverkehrsmittel, einschließlich der Erzeugung von Auftriebs-, Zug- und Steuerkräften unter Einsatz der Energie eines Antriebs-Drucksystems, dass das Antriebs-Drucksystem innerhalb eines Luftwegs ein Luftarbeitsmittel bildet und der Luftweg ein Kanal- und Klappensystem zur Regelung des Arbeitsmittelstroms aufweist, wobei das Profil des Arbeitsmittels eine aerodynamische Form hat und das komplette Antriebs-Drucksystem im hinteren Teil des Rumpfkörpers angeordnet ist und wobei innerhalb des Rumpfkörpers ein Luftweg mit Kanälen ausgebildet wird. Die Auftriebskräfte des Mehrzweckluftverkehrsmittel lassen sich unter gleichzeitiger Verbesserung des Fahrverhaltens beim senkrechten Aufsteigen und senkrechtem Abstieg vergrößern. Die Profile der Antriebsmittel und die gesamte Gestaltung des Mehrzweckflugverkehrsmittels erhalten eine bestimmte Form, und im Körper (Rumpf) des Mehrzweckluftverkehrsmittels werden Luftkanäle mit Lüftern und Düsen an ganz bestimmten Stellen vorgesehen.
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| 99 | Integrated inward turning inlets and nozzles for hypersonic air vehicles | EP07102293.3 | 2007-02-13 | EP1818257A3 | 2009-12-16 | Elvin, John D. |
A hypersonic waverider aircraft is disclosed that includes a first engine (106) and an inlet including a throat (108). The inlet is configured to generate three-dimensional flow compression during hypersonic flight with a weak shock wave that begins at the leading edge surfaces of the inlet and coalesces ahead of the throat, and a weak shock wave that begins at the point of coalescence of the weak shock wave and extends to the throat. The inlet includes a v-shaped lip open to freestream airflow in one side of the inlet.
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| 100 | EINRICHTUNG ZUR NOT-EVAKUIERUNG, INSBESONDERE FÜR EIN NURFLÜGEL-FLUGZEUG | EP06792072.8 | 2006-09-14 | EP1924496A1 | 2008-05-28 | ANGER, André; SCHÖNE, Wolfram |
| A system for selective emergency evacuation of persons from a first level (I) to a second level (II) located above the first level (I) or to a third level (III) located under the first level comprises for evacuation to the upper level a stairs-shaped arrangement (1). According to the invention, the system is connected at one end with the first level (I) and at the other end it can be displaced between the upper level (II) and the lower level (III) or vice-versa, and can be altered to take the form of a slide (2) for evacuation to the lower level (III). In particular, the system can be advantageously used for selective emergency evacuation of persons from a deck which forms the first level (I), in particular a passenger deck (17) of a tailless aeroplane (20), to the upper side (18) of the tailless aeroplane (20), which forms the second, upper level (II), or to the underside (19) of the tailless aeroplane (20), which forms the third, lower level (III). | ||||||
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