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    • 94. 发明授权
    • Structural supports and aircraft landing gears including such supports
    • 结构支撑和飞机起落架包括这种支架
    • US4537374A
    • 1985-08-27
    • US405647
    • 1982-08-05
    • Pierre BarnoinJacques M. N. MensGilbert Merle
    • Pierre BarnoinJacques M. N. MensGilbert Merle
    • B64C25/58B64C25/60F16F7/12
    • B64C25/60F16F7/125
    • A structural support comprises inner and outer elements which are telescopingly engaged, a cage secured to the inner element and having apertures in which balls are disposed which are disposed radially between the two elements, and a frangible connection securing the two elements against relative axial movement. In the locked relative positions of the elements, the outer element has locally an increased internal diameter portion and the balls are radially disposed in this position or are moved into the portion on being subjected to an axial force which breaks the frangible connection, so that the relative axial movement of the elements results in the ball plastically deforming the outer element and absorbing energy from the force to protect the body carried by the support. The support can be used to provide a brace operating as a strut and/or a tie, or a shock absorber, or, by mounting a damping piston slidably in the inner tubular element can provide a shock absorbing piston and cylinder unit. The outer tubular element may itself form an external cylinder or may be a liner in an external cylinder.
    • 结构支撑件包括可伸缩地接合的内部和外部元件,固定到内部元件的笼,并且具有设置在其中径向位于两个元件之间的球的孔,以及将两个元件抵抗相对轴向移动的易碎连接。 在元件的锁定的相对位置中,外部元件具有局部增加的内径部分,并且球径向地设置在该位置或者在经受破坏易碎连接的轴向力的部分中移动到该部分中,使得 元件的相对轴向运动导致球塑性地使外部元件变形并且从力吸收能量以保护由支撑件承载的身体。 支撑件可用于提供作为支柱和/或连接件或减震器操作的支架,或者通过可滑动地安装在内部管状元件中的阻尼活塞可以提供减震活塞和气缸单元。 外部管状元件本身可以形成外部圆筒,或者可以是外部圆筒中的衬套。
    • 96. 发明授权
    • Firing control system for a direct firing weapon mounted on a
rotary-wing aircraft
    • 用于安装在旋翼飞机上的直接射击武器的射击控制系统
    • US4528891A
    • 1985-07-16
    • US425392
    • 1982-09-28
    • Alain M. BrunelloGuy G. Catani
    • Alain M. BrunelloGuy G. Catani
    • F41G3/22F41G5/18
    • F41G5/18
    • Firing control system for a direct firing weapon mounted on a rotary-wing aircraft, which is designed to be actuated by the pilot himself and comprises an electronic computer, the said weapon being mounted for rotating about two transverse axes Y-Y' and Z-Z', due to driving means controlled by the said computer.According to the invention, said firing control system is characterized in that it comprises a sighting system on which a target and an adjusting mark can appear simultaneously, which adjusting mark can be moved on the said sighting system by a control of the pilot, as well as means to determine the coordinates of the position of the said adjusting mark with respect to a system of axes tied to the aircraft and to transmit them to said electronic computer at least when the said adjusting mark is brought to a position on the said sight finder where it is superposed on the said target.
    • 用于安装在转翼飞机上的直接射击武器的射击控制系统,其被设计成由飞行员自己驾驶并且包括电子计算机,所述武器被安装成绕两个横向轴线YY'和Z-Z'旋转, 由于由所述计算机控制的驱动装置。 根据本发明,所述点火控制系统的特征在于它包括瞄准系统,目标和调整标记可同时出现在该瞄准系统上,该调节标记可以通过飞行员的控制在所述瞄准系统上移动 作为用于确定所述调节标记相对于与飞机相关的轴系的坐标的坐标的装置,并至少当所述调节标记进入所述瞄准器上的位置时将其传送到所述电子计算机 其中叠加在所述目标上。
    • 97. 发明授权
    • Helicopter rotor with articulation means integrated in the root of the
blade
    • 具有铰接装置的直升机转子集成在叶片的根部
    • US4504193A
    • 1985-03-12
    • US423401
    • 1982-09-24
    • Rene L. Mouille
    • Rene L. Mouille
    • B64C27/32B64C27/35B64C27/48B64C27/51
    • B64C27/48B64C27/32B64C27/35B64C27/51
    • The invention concerns a helicopter rotor, the rigid hub (1) of which comprises a central drum (2) which is disposed substantially in line with the rotor mast (3) and which carries an upper plate (4) and a lower plate (6). This rigid hub (1) is connected to the root of each blade (26) by way of a laminated spherical stop (13) and a resilient-return drag brace. Each blade (26) comprises, in the zone of its root, a rigid loop (27) which surrounds the laminated spherical stop (13) in a continuous manner and is engaged in the inner movable fitting (24) of this stop (13) by means of a wedge (30) co-operating with the outer fixed fitting (15) of the stop (13).
    • 本发明涉及一种直升机转子,其刚性轮毂(1)包括中心鼓(2),其基本上与转子桅杆(3)成一直线设置并且承载上板(4)和下板(6) )。 该刚性轮毂(1)通过层叠的球形止动件(13)和弹性回复拖链连接到每个叶片(26)的根部。 每个叶片(26)在其根部的区域中包括以连续的方式围绕层压的球形止动件(13)并且接合在该止动件(13)的内部可动配件(24)中的刚性环(27) 通过与止动件(13)的外部固定配件(15)配合的楔形件(30)。
    • 98. 发明授权
    • Non-dissipative LC snubber circuit
    • 非耗散LC缓冲电路
    • US4489373A
    • 1984-12-18
    • US448016
    • 1982-12-08
    • Jacques G. M. du Parc
    • Jacques G. M. du Parc
    • H03K17/0814H02H7/122
    • H03K17/08146
    • Non-dissipative snubber for a D.C. power switching circuit comprising a main inductance connected in series with a load, a controlled switch, an inductance, and a D.C. voltage source. The snubber includes a branch circuit including a capacitor, a first diode, and an auxiliary inductance in series, mounted in parallel across the switch, with one terminal of the capacitor directly connected to the junction of the switch and the main inductance. The other terminal of the capacitor is connected through a second diode to a point of constant potential having a value about half that withstood by the switch. The snubber permits the use of a capacitor of lower voltage rating than heretofore required.
    • 包括与负载串联的主电感,受控开关,电感和直流电压源的直流电源开关电路的非耗散缓冲器。 缓冲器包括一个分支电路,包括串联的电容器,第一二极管和辅助电感器,并联安装在开关上,电容器的一个端子直接连接到开关和主电感的结。 电容器的另一个端子通过第二二极管连接到恒定电位的点,其值约为开关所经受的一半。 缓冲器允许使用比以前要求的更低的额定电压的电容器。