公开(公告)号：WO2014118299A1

公开(公告)日：2014-08-07

申请号：PCT/EP2014/051847

申请日：2014-01-30

Applicant: REITER, Johannes

Inventor： REITER, Johannes

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/102

Abstract: The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first rotary wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The first wing arrangement (110) is adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) do not rotate around the fuselage axis (101). The first wing arrangement (110) is further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) is tilted around the respective first rotary wing axis (111) with respect to its orientation in the fixed-wing flight mode and that the first wing arrangement (110) rotates around the fuselage axis (101). The aircraft further comprises an extendible lift increasing system which is arranged to the first wing arrangement (110) for selectively amending a lift area of the first wing arrangement (110) in the fixed-wing flight mode and the hover flight mode.

Abstract translation: 本发明涉及一种飞行器，其包括机身（100），其包括机身轴线（101），第一机翼装置（110）和第二机翼装置（120）。 第一机翼装置（110）被安装到机身（100），使得第一机翼装置（110）围绕第一机翼装置（110）的第一旋转翼轴线（111）可倾斜，并且使得第一机翼装置 （110）能够围绕机身轴线（101）旋转。 第一机翼装置（110）以这种方式适配，使得在固定翼飞行模式中，第一机翼装置（110）不围绕机身轴线（101）旋转。 第一机翼装置（110）进一步适应于在悬停飞行模式中，第一机翼装置（110）围绕其相应的第一旋转翼轴线（111）相对于其固定方向的取向倾斜， 机翼飞行模式，并且第一机翼装置（110）围绕机身轴线（101）旋转。 该飞机还包括可伸缩提升增加系统，该系统布置在第一机翼装置（110）上，用于以固定翼飞行模式和悬停飞行模式选择性地修理第一机翼装置（110）的提升区域。

公开(公告)号：WO2013120918A1

公开(公告)日：2013-08-22

申请号：PCT/EP2013/052911

申请日：2013-02-13

Applicant: REITER, Johannes

Inventor： REITER, Johannes

IPC: B64C29/02 ,  B64C39/02 ,  B64C29/00 ,  B64C39/00 ,  B64C27/16 ,  B64C27/18

CPC classification number: B64C27/00 ,  B64C3/385 ,  B64C27/001 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0075 ,  B64C29/02 ,  B64C39/008 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: The present invention relates to a device for generating aerodynamic lift and in particular an aircraft (100) for vertical take-off and landing. A wing arrangement (110) comprises at least one propulsion unit (111), wherein the propulsion unit (111) comprises a rotating mass which is rotatable around a rotary axis (117). The wing arrangement (110) is mounted to a fuselage (101) such that the wing arrangement (110) is tiltable around a longitudinal wing axis (112) of the wing arrangement (110) and such that the wing arrangement (110) is rotatable with respect to the fuselage (101) around a further rotary axis that differs to the longitudinal wing axis (112). An adjusting mechanism adjusts a tilting angle of the wing arrangement (110) around the longitudinal wing axis (112) under influence of a precession force (Fp) which forces the wing arrangement (110) to tilt around the longitudinal wing axis (112).

Abstract translation: 本发明涉及一种用于产生空气动力升降装置，特别涉及用于垂直起飞和着陆的飞机（100）。 机翼装置（110）包括至少一个推进单元（111），其中推进单元（111）包括围绕旋转轴线（117）旋转的旋转块。 机翼装置（110）被安装到机身（101），使得机翼装置（110）围绕机翼装置（110）的纵向翼轴线（112）可倾斜，并且使得机翼装置（110）可旋转 相对于机身（101）围绕与纵向翼轴（112）不同的另一旋转轴线。 调节机构在促使机翼装置（110）围绕纵向机翼轴线（112）倾斜的进动力（Fp）的影响下调节机翼装置（110）围绕纵向翼轴线（112）的倾斜角度。

公开(公告)号：WO2013120912A1

公开(公告)日：2013-08-22

申请号：PCT/EP2013/052903

申请日：2013-02-13

Applicant: REITER, Johannes

Inventor： REITER, Johannes

IPC: B64C29/02 ,  B64C39/02 ,  B64C29/00

CPC classification number: B64C27/00 ,  B64C3/385 ,  B64C27/001 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0075 ,  B64C29/02 ,  B64C39/008 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first longitudinal wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The second wing arrangement (120) comprises at least one propulsion unit (122), wherein the second wing arrangement (120) is mounted to the fuselage (100) such that the second wing arrangement (120) is tiltable around a second longitudinal wing axis (121) of the second wing arrangement (120) and such that the second wing arrangement (120) is rotatable around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) and the second wing arrangement (120) do not rotate around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) and the second wing arrangement (120) are tilted around the respective first longitudinal wing axis (111) and the respective second longitudinal wing axis (121) with respect to its orientations in the fixed-wing flight mode and that the first wing arrangement (110) and the second wing arrangement (120) rotate around the fuselage axis (101).

Abstract translation: 本发明涉及一种飞行器，其包括机身（100），其包括机身轴线（101），第一机翼装置（110）和第二机翼装置（120）。 第一机翼装置（110）安装到机身（100），使得第一机翼装置（110）能围绕第一机翼装置（110）的第一纵向机翼轴线（111）倾斜，并且使得第一机翼装置 （110）能够围绕机身轴线（101）旋转。 第二机翼装置（120）包括至少一个推进单元（122），其中第二机翼装置（120）安装到机身（100）上，使得第二机翼装置（120）可围绕第二纵向机翼轴线 （121），并且使得所述第二机翼装置（120）能够围绕所述机身轴线（101）旋转。 第一机翼装置（110）和第二机翼装置（120）以这样的方式适配，使得在固定翼飞行模式中，第一机翼装置（110）和第二机翼装置（120）不围绕 机身轴（101）。 第一机翼装置（110）和第二机翼装置（120）进一步适于以悬停飞行模式，第一机翼装置（110）和第二机翼装置（120）围绕相应的 第一纵向翼片轴线（111）和相应的第二纵向翼片轴线（121）相对于其在固定翼飞行模式中的定向，并且第一翼形装置（110）和第二翼形装置（120）围绕机身旋转 轴（101）。

公开(公告)号：WO2007001373A2

公开(公告)日：2007-01-04

申请号：PCT/US2005/033235

申请日：2005-09-19

Applicant: AURORA FLIGHT SCIENCES ,  PARKS, Robert

Inventor： PARKS, Robert

IPC: B64C27/22

CPC classification number: B64C3/385 ,  B64C29/02 ,  G05D1/0669 ,  Y02T50/14

Abstract: A system for controlling inbound transition of an aircraft includes a fuselage and first and second freewings pivotably mounted on opposing sides thereof. The system includes an airspeed sensor that outputs an airspeed indication signal. The system includes a controller for increasing aircraft engine thrust to substantially maximum for inbound transition, and for generating pitch and freewing control signals. The system includes actuators for actuating aircraft control surfaces in response to the pitch control signal to rapidly increase pitch of the fuselage to decelerate the aircraft, and for actuating freewing control surfaces in response to the freewing control signal to adjust lift produced by the freewings to oppose climbing of the aircraft due to the increase in engine thrust and the increase in the fuselage pitch. The controller is configured to decrease the engine thrust as the aircraft decelerates until the aircraft is in a hover mode.

Abstract translation: 一种用于控制飞行器入境过渡的系统包括机身以及可枢转地安装在其相对侧上的第一和第二快门。 该系统包括输出空速指示信号的空速传感器。 该系统包括一个控制器，用于将飞机发动机推力增加到进入过渡的基本最大值，并产生俯仰和自由控制信号。 该系统包括用于响应于俯仰控制信号来致动飞机控制表面的致动器，以快速增加机身的俯仰以使飞行器减速，并且响应于自由转动控制信号来驱动释放控制表面，以调节由空档产生的升力来抵抗 由于发动机推力的增加和机身间距的增加，飞机上升。 控制器配置成当飞机减速直到飞机处于悬停模式时，减小发动机推力。

公开(公告)号：WO1998012106A1

公开(公告)日：1998-03-26

申请号：PCT/FR1997001655

申请日：1997-09-19

Applicant: S.C.I. CHANEAC ET FILS ,  CHANEAC, André ,  CHANEAC, Jean

Inventor： S.C.I. CHANEAC ET FILS

IPC: B64C29/02

CPC classification number: B64C29/02

Abstract: The invention concerns an aircraft with vertical take-off and landing having a passenger cabin (3) remaining horizontal whatever the angle of inclination of the aircraft, characterised in that the support stands (69), (70), (71) and (72) in contact with the ground are supported each by a beam bearing a change-over flap (77), (78), (79) and (80) pivoting about an axis perpendicular to the aircraft axis and located in the vertical extension of the beam, the aircraft being vertical.

Abstract translation: 本发明涉及一种具有垂直起飞和着陆的飞行器，其中客舱（3）不依赖于飞行器的倾斜角度而保持水平，其特征在于支撑架（69），（70），（71）和（72 与所述地面接触的每一个都由支撑有一个转动翼片（77），（78），（79）和（80）的梁支撑，所述转动翼片围绕垂直于所述飞行器轴线的轴线枢转并且位于所述飞行器的垂直延伸部 梁，飞机垂直。

公开(公告)号：WO2018187844A1

公开(公告)日：2018-10-18

申请号：PCT/AU2018/050332

申请日：2018-04-12

Applicant: IRIDIUM DYNAMICS PTY LTD

Inventor： LAMB, Ian Conway ,  LAMB, Christopher Conway

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C3/385 ,  B64C29/02 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: A dual flight mode aircraft enables efficient forward-flight and hover modes. The aircraft comprises: a fuselage defining a nose and a tail, including a wing attachment region positioned between the nose and the tail, and a tail surface attachment region positioned between the wing attachment region and the tail; a starboard wing connected to the wing attachment region using a starboard spar, the starboard wing also connected to a starboard motor; a port wing connected to the wing attachment region using a port spar, the port wing also connected to a port motor; a rotation mechanism connected to the fuselage for rotating the starboard wing about a longitudinal axis of the starboard spar, and for rotating the port wing about a longitudinal axis of the port spar, wherein the starboard wing rotates generally counter to a direction of rotation of the port wing; and a tail surface connected to the tail surface attachment region.

公开(公告)号：WO2018070867A1

公开(公告)日：2018-04-19

申请号：PCT/NL2017/050664

申请日：2017-10-10

Applicant: TECHNISCHE UNIVERSITEIT DELFT

Inventor： REMES, Bart Diane Walter

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/108

Abstract: An aerial vehicle (50) for vertical take-off and landing and horizontal flight comprises two wings (31, 32) extending substantially parallel to a Y-axis in spanwise direction, substantially parallel to an X-axis in chordwise direction, and extending substantially parallel to a Z- axis in thickness direction. The wings are substantially symmetrical with respect to a XZ-plane. The aerial device comprises at least four propulsion units (3, 4, 5, 6), each propulsion unit being rigidly mounted to the wings with a respective nacelle and configured to generate a force vector along a respective imaginary force vector line, said force vector line, for a subset of at least two of the propulsion units, when projected on the XY-plane, being oriented at a first angle with respect to the X-axis, and when projected on the XZ- plane, is further oriented at a second angle with respect to the X-axis.

Abstract translation: 用于垂直起飞和着陆以及水平飞行的飞行器（50）包括两个基本上平行于翼展方向上的Y轴延伸的翼（31,32），所述翼基本上平行于X轴， 并且在厚度方向上与Z轴大致平行地延伸。 这些翼相对于XZ平面基本对称。 所述空中设备包括至少四个推进单元（3,4,5,6），每个推进单元利用相应的机舱刚性地安装到所述机翼并且被配置为沿着相应的虚构力矢量线产生力矢量，所述力矢量 当投影到XY平面上时，对于推进单元中的至少两个的子集，其相对于X轴以第一角度取向，并且当投影到XZ平面上时进一步取向为 第二个角度相对于X轴。

公开(公告)号：WO2018026397A1

公开(公告)日：2018-02-08

申请号：PCT/US2017/022126

申请日：2017-03-13

Applicant: KITTY HAWK CORPORATION

Inventor： VANDER LIND, Damon ,  REICHERT, Todd

IPC: B64C11/30 ,  B64C11/32 ,  B64C11/40 ,  B64C11/42 ,  B64C11/44

CPC classification number: B64C11/325 ,  B64C11/18 ,  B64C11/343 ,  B64C11/46 ,  B64C27/08 ,  B64C27/467 ,  B64C27/80 ,  B64C29/02 ,  B64C2201/108

Abstract: A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion, of the blade and a second structure coupled to the blade when the bia.de is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

Abstract translation: 螺旋桨包括可自由旋转的刀片。 当叶片处于旋转运动范围的第一端处的第一位置时，第一止动件定位成机械地接合叶片的第一部分和联接到叶片的第一结构中的一个或两个。 第二止动件定位成当偏置件在限定的旋转范围的第二端处于第二位置时机械地接合叶片的第二部分和联接至叶片的第二结构中的一个或两个。 当螺旋桨沿第一方向旋转时，叶片抵抗第一止动件旋转到第一位置，而当螺旋桨沿第二方向旋转时，叶片抵抗第二止动件旋转到第二位置。

公开(公告)号：WO2017107661A1

公开(公告)日：2017-06-29

申请号：PCT/CN2016/103749

申请日：2016-10-28

Applicant: 丰唐物联技术(深圳)有限公司

Inventor： 郑少华 ,  黎剑辉 ,  张圳 ,  朱一伟 ,  罗海彬 ,  湛浩

IPC: A01D34/00 ,  B64C29/02

CPC classification number: A01D34/00 ,  B64C29/02

Abstract: 一种飞行割草方法及装置，该装置包括割草器和无人机，该割草器安装在无人机上。该割草方法包括如下步骤：获取割草器安装在无人机上的位置；根据割草器安装的不同位置，控制无人机执行相应的飞行模式进行割草。该装置通过无人机进行割草，提高了割草效率，减轻了用户的劳动强度。

公开(公告)号：WO2017072519A1

公开(公告)日：2017-05-04

申请号：PCT/GB2016/053347

申请日：2016-10-28

Applicant: BAE SYSTEMS PLC

Inventor： WRIGHT, Julian, David ,  COLOSIMO, Nicholas, Giacomo, Robert ,  WARSOP, Clyde

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/18

Abstract: An air vehicle (10) comprising a main body (12)and a pair of opposing wing members (14a, 14b) extending substantially laterally from the main body (12), at least a first propulsion device (16) associated with a first of said wing members (14a) and a second propulsion device (16) associated with a second of said wing members (14b), each said propulsion device (16) being arranged and configured to generate linear thrust relative to said main body (12), in use, the air vehicle further comprising a control module for generating a control signal configured to change a mode of flying of said air vehicle, in use, between a fixed wing mode (Figure 2) and a rotary wing mode (Figure 3), wherein, in said fixed wing mode of flying, the direction of thrust generated by the first propulsion device (16) relative to the main body (12) is the same as the direction of thrust generated by the second propulsion device (16), and in said second mode of flying, the direction of thrust generated by the first propulsion device (16) relative to the main body is opposite to that generated by the second propulsion device (16).

Abstract translation: 一种飞行器（10），包括主体（12）和从所述主体（12）大致横向延伸的一对相对的翼构件（14a，14b），至少第一推进装置 （14a）的第一个和与第二个所述翼部件（14b）相关联的第二推进装置（16）相关联的第二推进装置（16），每个所述推进装置（16）被布置和构造成相对于所述翼构件 在使用中，所述飞行器还包括控制模块，所述控制模块用于生成控制信号，所述控制信号被配置成在使用中改变所述飞行器在固定翼模式（图2）和飞行模式 其中，在所述固定翼飞行模式中，由所述第一推进装置（16）相对于所述主体（12）产生的推力的方向与由所述第一推进装置（16）产生的推力的方向相同 第二推进装置（16），并且在所述第二飞行模式中，产生推力的方向 由第一推进装置（16）相对于主体的运动与由第二推进装置（16）产生的运动相反。