AIRCRAFT FOR VERTICAL TAKE-OFF AND LANDING WITH TWO WING ARRANGEMENTS
    1.
    发明申请
    AIRCRAFT FOR VERTICAL TAKE-OFF AND LANDING WITH TWO WING ARRANGEMENTS 审中-公开
    用于双向安装的垂直起落架的飞机

    公开(公告)号:US20150232178A1

    公开(公告)日:2015-08-20

    申请号:US14378604

    申请日:2013-02-13

    Inventor: Johannes Reiter

    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)。

    WING ADJUSTING MECHANISM
    2.
    发明申请
    WING ADJUSTING MECHANISM 审中-公开
    WING调整机制

    公开(公告)号:US20150028155A1

    公开(公告)日:2015-01-29

    申请号:US14378633

    申请日:2013-02-13

    Inventor: Johannes Reiter

    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 相对于与纵向翼轴(112)不同的另一旋转轴线的机身(101)。 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。

    Tilt Wing Rotor VTOL
    3.
    发明申请
    Tilt Wing Rotor VTOL 审中-公开
    倾斜翼转子垂直起落架

    公开(公告)号:US20140008498A1

    公开(公告)日:2014-01-09

    申请号:US13824363

    申请日:2011-09-16

    Inventor: Johannes Reiter

    Abstract: An aircraft for vertical take-off and landing. The aircraft comprises a first wing, a second wing and a fuselage. The first wing comprises a first longitudinal wing axis and the second wing comprises a second longitudinal wing axis. The first wing extends along the first longitudinal wing axis and the second wing extends along the second longitudinal wing axis from the fuselage. The first wing is tiltable with a first rotational direction around the first longitudinal wing axis and the second wing is tiltable with a second rotational direction around the second longitudinal wing axis. In a fixed-wing flight mode, the wings do not rotate around a second axis. In a hover flight mode, the wings are tilted around the longitudinal wing axis with respect to its orientation in the fixed-wing flight mode and that the wing rotates around the second axis.

    Abstract translation: 一架垂直起飞和着陆的飞机。 飞机包括第一机翼,第二机翼和机身。 第一翼包括第一纵向翼轴线,第二翼片包括第二纵向翼轴线。 第一翼沿着第一纵向翼轴线延伸,并且第二翼沿着机身的第二纵向翼轴线延伸。 第一翼可围绕第一纵向翼轴线以第一旋转方向倾斜,并且第二翼可围绕第二纵向翼轴线以第二旋转方向倾斜。 在固定翼飞行模式下,机翼不能绕第二轴旋转。 在悬停飞行模式中,机翼相对于其在固定翼飞行模式中的定向围绕纵向翼轴线倾斜,并且机翼围绕第二轴线旋转。

Patent Agency Ranking