公开(公告)号：WO2011005278A1

公开(公告)日：2011-01-13

申请号：PCT/US2009/064655

申请日：2009-11-16

Applicant: WILLIAMS AEROSPACE, INC. ,  WILLIAMS, Jeffrey, L.

Inventor： WILLIAMS, Jeffrey, L.

IPC: B64C3/10

CPC classification number: B64C3/10 ,  A63H27/02 ,  A63H30/04 ,  B64C3/16 ,  B64C39/024 ,  B64C39/028 ,  B64C2039/105 ,  B64C2201/028

Abstract: A Blended Wing Body SUAV and MUAV is disclosed having a novel airfoil profile, wing configuration, rigging and tractor pull propeller placement that provide improved stability and safety characteristics over prior art SUAVs and MUAVs of comparable size and weight. This unique blended wing design includes wing twist on the outboard wing and an inverted "W" shaped planform to provide lateral and longitudinal stability, and smooth, even flight characteristics throughout the range of the expected flight envelope. These flight characteristics are crucial to providing a stable reconnaissance platform with favorable stall speeds, an increased payload and the ability to hand launch without the danger of exposing ones hands or wrist to a propeller.

Abstract translation: 混合翼体SUAV和MUAV被公开具有新颖的机翼轮廓，机翼构造，索具和拖拉机拉拔螺旋桨放置，其提供相当于相当尺寸和重量的现有技术的SUAV和MUAV的改进的稳定性和安全性。 这种独特的混合机翼设计包括在外侧机翼上的机翼扭转和倒置的“W”形平面，以提供横向和纵向的稳定性，以及在预期飞行包线的整个范围内的平滑，均匀的飞行特性。 这些飞行特征对于提供稳定的侦察平台，具有良好的失速速度，增加的有效载荷和手动发射的能力，而不会将一只手或手腕暴露于螺旋桨的危险至关重要。

公开(公告)号：WO2007018785A1

公开(公告)日：2007-02-15

申请号：PCT/US2006/024739

申请日：2006-06-26

Applicant: THE BOEING COMPANY ,  STUHR, Victor, K.

Inventor： STUHR, Victor, K.

IPC: B64C23/06 ,  B64C3/10

CPC classification number: B64C23/069 ,  Y02T50/164

Abstract: Methods and systems for efficiently increasing the wing area of an aircraft are disclosed herein. An integrated wingtip extension (310) configured in accordance with one embodiment of the invention includes a tapered wing section and a winglet (304). The tapered wing section (308) includes an inboard end portion (306) having a first chord length (L1) and an outboard end portion (306) having a second chord length (L2) that is less than the first chord length (L1). The winglet (304) is fixedly attached to the outboard end portion (3016). The inboard end portion (306) is configured to be fixedly attached to a tip portion of an aircraft wing (302). In one embodiment, the tapered wing section (308) and the winglet (304) can be integrally formed from composite materials.

Abstract translation: 本文公开了用于有效增加飞行器翼面积的方法和系统。 根据本发明的一个实施例构造的集成翼尖延伸部（310）包括锥形翼部和小翼（304）。 锥形翼部（308）包括具有第一弦长（L1）的内侧端部（306）和具有小于第一弦长（L1）的第二弦长（L2）的外侧端部（306） 。 小翼（304）固定地附接到外侧端部（3016）。 内侧端部（306）构造成固定地附接到飞机机翼（302）的尖端部分。 在一个实施例中，锥形翼部（308）和小翼（304）可以由复合材料一体地形成。

公开(公告)号：WO2006114493A2

公开(公告)日：2006-11-02

申请号：PCT/FR2006000795

申请日：2006-04-11

Applicant: AIRBUS FRANCE ,  CROS CHRISTOPHE

Inventor： CROS CHRISTOPHE

IPC: B64C3/10

CPC classification number: B64C3/10

Abstract: The invention relates to an aircraft with low noise, such as during take-off and landing. According to the invention, the aircraft comprises: two wings (2, 3) which have a reverse sweep (f) and which do not support an engine; a rear vertical tail unit consisting of at least two fins (5, 6) and forming a channel (8) together with the rear part (7) of the fuselage (4), which is disposed on the back of same; and at least one turboshaft engine (9, 10) which is disposed on the back of the fuselage (4), such that the gas streams generated by the turboshaft engine (9, 10) enter the channel (8) and such that the downstream noise of the engine (9, 10) is masked laterally and downwardly by said channel. The root sections (11, 12) of the wings (2, 3) are disposed close to the air inlet (15, 16) of the turboshaft engine (9, 10) such that the upstream noise generated thereby is masked laterally and downwardly by said wings (2, 3).

Abstract translation: 本发明涉及一种低噪音的飞机，例如在起飞和降落期间。 根据本发明，飞行器包括：具有反向扫掠（f）并且不支撑发动机的两个翼部（2,3） 一个由至少两个翅片组成的后部垂直尾翼单元，与机身背面的后部部分一起形成一个通道; 以及设置在所述机身背面的至少一个涡轮轴发动机（9,10），使得由所述涡轮轴发动机（9,10）产生的气流进入所述通道（8），并且使得所述下游 发动机（9,10）的噪声被所述通道横向和向下掩蔽。 翼部（2,3）的根部部分（11,12）设置成靠近涡轮轴发动机（9,10）的进气口（15,16），使得由此产生的上游噪声被横向和向下通过 所说的翅膀（2,3）。

公开(公告)号：WO2005084156A2

公开(公告)日：2005-09-15

申请号：PCT/US2004/019746

申请日：2004-06-21

Applicant: AEROVIRONMENT, INC.

Inventor： MACCREADY, Paul, B. ,  HIBBS, Bart, D. ,  SWANSON, Kyle, D. ,  CURTIN, Robert, F.

IPC: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/02 ,  B64C39/10 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30

CPC classification number: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

Abstract translation: 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的功率，同时以无阻碍的向下观看的方式支持通信平台。 飞机在翼的前缘包括可延伸的板条，以及反射的后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 该飞机还包括被配置为经由燃料电池提供电力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中的燃料的沸腾率。 燃料电池压缩氧化剂的环境空气，并在低于一个大气压的燃料和氧化剂下操作。 本发明的飞行器包括支撑结构，该支撑结构包括多个支撑件，其中支撑件形成固定在机翼上的四面体。

公开(公告)号：WO2003059736A3

公开(公告)日：2003-07-24

申请号：PCT/US2003/000985

申请日：2003-01-14

Applicant: CARR, Robert, Jonathan

IPC: B64C3/10

Abstract: An aircraft (12) comprising three wings located on either side of the fuselage (14). The forward wing (22) has a downward angle with a curved top and bottom surface. The upper wing (24) is located towards the rear of the aircraft and above the forward wing (22). The lower wing (26) is located below the upper wing (24) and slightly forward and located to the rear and below of the forward wing. The outer ends of all three wings come into contact at one point. The forward wing (22) uses the Coanda effect to increase the airflow across the top surface of the bottom wing. One embodiment of the aircraft has two turbines (58), shaft-coupled to a power source, located on either side of the forward end of the fuselage. Each engine (58) has part of its thrust (63) diverted through and directed by a plenum disposed internal of the Coanda toward both sides of the fuselage so that an equal amount of thrust (63)flows through the duct (65) and over the wings on either side of the fuselage (14).

公开(公告)号：WO2022167875A1

公开(公告)日：2022-08-11

申请号：PCT/IB2022/050246

申请日：2022-01-13

Applicant: C.I.R.A. (CENTRO ITALIANO RICERCHE AEROSPAZIALI) S.C.P.A.

Inventor： PERSECHINO, Giuseppe ,  BARANIELLO, Vincenzo Rosario ,  BORSA, Roberto

IPC: B64C3/10

Abstract: There is described a hybrid aircraft (1) of the unmanned type, configured for the joint and optimized use of aerostatic and aerodynamic force, comprising an inflatable body (10) including an outer shell (11) and a load-bearing structure (20) inside said outer shell (11), said inflatable body (10) being adapted to assume a closed wing operating configuration.

公开(公告)号：WO2022056597A1

公开(公告)日：2022-03-24

申请号：PCT/AU2021/051078

申请日：2021-09-17

Applicant: AMSL INNOVATIONS PTY LTD

Inventor： MOORE, Andrew Dudley ,  SWALLOW, Alfred Leonard

IPC: B64C39/06 ,  B64C39/08 ,  B64C1/26 ,  B64C3/10 ,  B64C29/00 ,  B64C1/10

Abstract: An aircraft structure (10) comprising a fuselage (24), first and second forward wings (20, 22) mounted to and/or extending from opposing sides of the fuselage (24), a continuous rear wing span (34) defining first and second rear wings (30, 32) and a central static connecting portion (36), a first wing connecting member (42) extending between the first forward wing (20) and the first rear wing (30), a second wing connecting member (42) extending between the second forward wing (22) and the second rear wing (32), wherein the rear wing span (34) is supported by a centrally located V tail joint defined by first and second angularly inclined arms (100, 110), first and second electric motors each having rotors, are mounted to each wing (20, 22, 30, 32), each rotor is pivotal between a first configuration for vertical flight, and a second configuration for forward flight.

公开(公告)号：WO2021020999A1

公开(公告)日：2021-02-04

申请号：PCT/RU2020/000376

申请日：2020-07-22

Applicant: СЕРГЕЕВ, Виктор Георгиевич

Inventor： СЕРГЕЕВ, Виктор Георгиевич

IPC: B60V1/08 ,  B64C3/10

Abstract: Изобретение относится к экранопланам аэродинамической компоновки «составное крыло». Технический результат: повышение безопасности за счёт обеспечения статической, апериодической и колебательной устойчивости экраноплана, и уменьшение индуктивного сопротивления путём затягивания срыва потока на консолях составного крыла в области их примыкания к центроплану. Экраноплан имеет составное крыло с центропланом (1) и консолями (2), концевые шайбы (3) в концевых сечениях центроплана (1), силовую установку, вертикальное (4) и горизонтальное (5) оперение. Удлинение составного крыла λ=l 2 /(Sцп+2Sк)≥2,5, центроплана (1) 0,5≤λцп=1цп 2 /Sцп≤0,9, относительная площадь консолей (2) 0,25≤2Sк/Sцп≤0,4, продольный статический момент экраноплана 0,3≤А=(LгоSго+2LкSк)/ВAцпSцп

公开(公告)号：WO2020003657A1

公开(公告)日：2020-01-02

申请号：PCT/JP2019/012330

申请日：2019-03-25

Applicant: 新明和工業株式会社

Inventor： 大西　雄介 ,  宮内　空野 ,  宮腰　哲弥 ,  服部　悟 ,  柴田　認

IPC: B64C29/00 ,  B64C3/10 ,  B64C27/08 ,  B64C27/20 ,  B64C27/26

Abstract: 左右一対のロータおよび機体中心線上に配置されたロータと、固定翼とを備え、垂直離着陸時の機体の安定性に優れた航空機を提供することを目的とする。　航空機（１）は、胴体（１０）と、後退翼からなる固定翼（２０）と、前方推力を発生するプロペラ（４０）と、機体中心線（ＣＬ）の左側に配置された左ロータ（３１）と、機体中心線（ＣＬ）の右側に配置された右ロータ（３２）と、機体中心線（ＣＬ）上に配置された中央ロータ（３３）と、を備える。左ロータ（３１）の回転中心線（３１ｃ）と右ロータ（３２）の回転中心線（３２ｃ）と中央ロータ（３３）の回転中心線（３３ｃ）とを結んでなる三角形（５０）の内側に、機体重心（ＣＧ）が配置されている。

公开(公告)号：WO2019090191A1

公开(公告)日：2019-05-09

申请号：PCT/US2018/059111

申请日：2018-11-03

Applicant: UBER TECHNOLOGIES, INC.

Inventor： MOORE, Mark ,  BADALAMENTI, John ,  VILLA, Ian ,  WARMOTH, Adam ,  JOSEPHSON, David

IPC: B64C11/48 ,  B64D27/24 ,  B64C11/20 ,  B64C11/00 ,  B64C29/00 ,  B64C3/10

Abstract: A vertical landing and take-off aircraft VTOL transitions from a vertical takeoff state to a cruise state where the vertical takeoff state uses propellers to generate lift and the cruise state uses wings to generate lift. The aircraft has an M-wing configuration with propellers located on the wingtip nacelles, wing booms, and tail boom. The wing boom and/or the tail boom can include boom control effectors. Hinged control surfaces on the wings, tail boom, and tail tilt during takeoff and landing to yaw the vehicle. The boom control effectors, cruise propellers, stacked propellers, and control surfaces can have different positions during different modes of operation in order to control aircraft movement and mitigate noise generated by the aircraft.