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477 条记录 (耗时 0.015 秒)

    Vertical take-off aircraft
    41.
    发明授权
    Vertical take-off aircraft 失效
    垂直起飞飞机

    公开(公告)号：US5042747A

    公开(公告)日：1991-08-27

    申请号：US328195

    申请日：1989-02-09

    申请人： Denis Rabouyt

    发明人： Denis Rabouyt

    IPC分类号： B64C5/16 ,  B64C27/02

    CPC分类号： B64C27/02 ,  B64C5/16

    摘要： An aircraft of any type supported by a rotor and having an auxiliary tail is provided with means that allows, at the moment of take-off, at least part of its tail to take an inclined position in relation to the position of flight. The invention is particularly applicable to autogyros.

    摘要翻译： PCT No.PCT / FR87 / 00205 Sec。 371日期1989年2月9日第 102（e）日期1989年2月9日PCT Filed 1987年6月10日PCT公布。 出版物WO88 / 09746 日期为1988年12月15日。由转子支撑并具有辅助尾部的任何类型的飞机设置有能够在起飞时刻至少部分尾部相对于 飞行的位置。 本发明特别适用于autogyros。

    Convertiblade
    42.
    发明授权
    Convertiblade 失效

    公开(公告)号：US4059247A

    公开(公告)日：1977-11-22

    申请号：US723661

    申请日：1976-09-15

    申请人： Richard H. Prewitt

    发明人： Richard H. Prewitt

    IPC分类号： B64C27/28 ,  B64C27/02 ,  B64C27/26

    CPC分类号： B64C27/28

    摘要： An aircraft which operates between the surface and the air as a rotating wing aircraft (helicopter-autogiro). When airborne a rotor pylon latch is released and the pilot flies the rotor system aft about its pivot to the fuselage to form the tail of a high speed jet propelled airplane. Altering the pitch angle of the blades controls the aircraft, called a convertiblade, for helicopter-autogiro and airplane configurations and for moving the rotor between its configurations. The rotor is revved up with rocket fuel piped to burner jet nozzles located at the blade tips. A jump-take-off may be used to efficiently get the convertiblade airborne at a good climbing speed. Prior to landing, the rotor blades are released from their operation as roll control surfaces for the airplane configuration; then, they are permitted to rev-up and act as a brake to reduce the speed of the airplane. At a suitable speed, the pylon is released from the fuselage and the rotor system is flown by the pilot's controls up into autogiro configuration where it automatically latches permitting the pilot to make a flared autogiro landing. The transition between autogiro and airplane takes place in a very short period of time. The fuselage is kept stable during the transitions by the pilot's controls and by establishing lateral, directional, and longitudinal stability through relationships between the center of gravity and the center of all fin-areas of the aircraft for each regime of flight. Several methods of augmenting the rotor controls during transition are presented including the use of combined wing tip elevators and ailerons.

    摘要翻译： 一种在地面和空中作为旋转翼飞机（直升机 - 自动化）之间运行的飞机。 当机载转子塔架闩锁被释放并且飞行员将转子系统的枢轴绕其机身飞行到机身以形成高速喷射推进飞机的尾部时。 改变叶片的桨距角控制称为变速器的飞机，用于直升机 - 自动和飞机配置，并在其配置之间移动转子。 转子用火箭燃料喷射到位于叶片尖端的燃烧器喷嘴上。 可以使用跳跃起飞来有效地获得机载飞机的爬坡速度。 在着陆之前，转子叶片作为飞机配置的滚动控制表面从其操作中释放; 那么他们被允许升级并作为制动来降低飞机的速度。 以适当的速度，塔架从机身释放，转子系统由飞行员的控制器飞行到自动配置，其中它自动锁定，允许飞行员进行喇叭自动降落。 autogiro和飞机之间的过渡发生在很短的时间内。 在飞行员的控制过渡期间，机身保持稳定，并通过每个飞行方向的重心和飞机所有飞翼区域的中心之间的关系建立横向，定向和纵向的稳定性。 提出了在转换期间增加转子控制的几种方法，包括使用组合式翼尖升降机和副翼。

    Vtol aircraft with cruciform rotor wing
    43.
    发明授权
    Vtol aircraft with cruciform rotor wing 失效
    垂直起降飞机与冲击转子

    公开(公告)号：US3792827A

    公开(公告)日：1974-02-19

    申请号：US3792827D

    申请日：1972-11-10

    申请人： TELEDYNE RYAN AERONAUTICAL INC

    发明人： GIRARD P

    IPC分类号： B64C27/02 ,  B64C27/22

    CPC分类号： B64C27/026

    摘要： An aircraft having a combined rotary and fixed wing providing aerodynamic support in vertical take-off and landing and in high speed cruising flight. The wing is cruciform in configuration, with four similar arms extending radially from a center body, the outer portions of the arms being pivotal and controllable in the manner of helicopter rotor blades in the rotating mode of the wing. In fixed wing mode the wing is locked with two arms longitudinal to the aircraft and the other two extending laterally, one or both of the lateral arm portions being used for roll control in forward flight. The wing arms may have air brakes to slow rotation and stop the wing in proper alignment. A common turbojet power source provides propulsion for wing rotation and cruising flight.

    摘要翻译： 具有组合的旋转和固定翼的飞行器在垂直起飞和着陆以及高速巡航飞行中提供空气动力学支持。 机翼十字形​​构造，四个相似臂从中心体径向延伸，臂的外部部分以机翼的旋转模式的直升机转子叶片的方式枢转和控制。 在固定翼模式下，机翼以两臂纵向锁定在飞行器上，另外两个侧向延伸，一个或两个侧臂部分用于向前飞行中的滚动控制。 机翼臂可能有空气制动器来缓慢旋转，并使机翼正确对准。 普通的涡轮喷气发动机为翼转和巡航飞行提供推进。

    Rigid hubs for variable pitch rotors
    44.
    发明授权
    Rigid hubs for variable pitch rotors 失效
    RIGID HUBS可变式转盘转子

    公开(公告)号：US3606575A

    公开(公告)日：1971-09-20

    申请号：US3606575D

    申请日：1969-02-10

    申请人： SOC D CONST ET D EXPLOIT DE MA

    发明人： LERMUSIAUX LUCIEN EDMOND

    IPC分类号： B64C27/02 ,  B64C27/32 ,  B64C27/33 ,  B64C27/38

    CPC分类号： B64C27/32 ,  B64C27/021 ,  B64C27/33

    摘要： THE HUB COMPRISES A ROTARY AXLE, A HUB BODY RIGIDLY SECURED TO THIS AXLE, AND ARMS FIXED TO THE HUB BODY, THE VARIABLE PITCH BLADES ARE FIXED TO THE FREE ENDS OF THE ARMS. EACH ARM COMPRISES AT LEAST THREE BUNDLES OF PILED STRIPS, THESE BUNDLES BEING DISTRIBUTED ABOUT THE PITCH VARIATION AXIS OF THE CORRESPONDING BLADE. THE BUNDLES OF ANY ONE ARM ARE CONNECTED TO EACH OTHER AND TO THE HUB BODY BY HOLDING MEANS-NAMELY RIGID COLLARS AND SHEETS-SUCH THAT THE ARM POSSESES A HIGH RESISTANCE TO FLEXION AND A RELATIVELY LOW RESISTANCE TO TORSION.