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    • 2. 发明授权
    • Multiple locking device insensitive to thermal variations especially
applicable to space vehicles
    • 多个锁定装置对于特别适用于太空车辆的热变化不敏感
    • US4491289A
    • 1985-01-01
    • US458690
    • 1983-01-17
    • Christian RinnGerard Vezain
    • Christian RinnGerard Vezain
    • B64G1/22B64G1/44B64G1/66
    • B64G1/222B64G1/44B64G1/66
    • A locking device for clamping or sheaving appendices aboard a satellite during the launching phase provides for temporary locking thereof which both limits the required holding forces and authorizes multiplication of the clamping or sheaving points for each appendix while being insensitive to temperature variations. It comprises a stop catch jointed to a foot rigidly secured to the satellite structure, to ensure immobilization of the element to be temporarily locked thereby, an elbow lever hinged to the stop catch and connected to a sheaving cable, and an elastic link exerting upon the lever a force to balance the holding force exerted by the sheaving cable. The locking device remains in the locked position as long as the shearing device for cutting off the cable has not been operated. Furthermore the combination of the elbow lever and the elastic link provides means for ensuring perfect locking, even in the case of significant differential dilatations between the body of the space vehicle and the sheaving cable.
    • 在发射阶段,用于在卫星上夹紧或剪接附件的锁定装置提供临时锁定,这两者限制了所需的保持力,并且授权每个附件的夹紧或剪切点的乘法,同时对温度变化不敏感。 它包括连接到牢固地固定到卫星结构上的脚的止挡钩,以确保被暂时锁定的元件的固定,肘杆铰接到止动钩并连接到绳索,并且弹性连杆施加在 杠杆力平衡由滑轮电缆施加的保持力。 只要切断电缆的剪切装置未被操作,锁定装置保持在锁定位置。 此外,肘杆和弹性连杆的组合提供了用于确保完美锁定的装置,即使在空间车辆的主体和滑轮之间存在显着的差异扩张的情况下。
    • 3. 发明授权
    • Torque limiter device and deployable lengthening piece of a space
instrument equipped with this device
    • 带有该装置的空间仪器的扭矩限制装置和可分配的加长件
    • US5082212A
    • 1992-01-21
    • US691345
    • 1991-04-25
    • Gerard VezainJacques AuternaudDaniel Viale
    • Gerard VezainJacques AuternaudDaniel Viale
    • B64G1/44B64G1/22F16B31/04
    • F16B31/04B64G1/222B64G1/44
    • So as to dampen the shock occuring at the end of deploying a deployable lengthening piece of a space instrument, such as a solar generator, without resorting to using a complex speed regulation or synchronization mechanism for deployment, the present invention offers a torque limiter device (28a) to be placed between each joint (12) and at least one of the adjacent elements (10a) of the lengthening piece. This device includes an elastic system, such as a stack of Belleville washers (48a) which presses the plate (24a) of the joint against the edge of the element (10a) with a predetermined and preferably adjustable force. At the end of deployment, this elastic system absorbs the energy of the shock by deforming, then it brings the two pieces (24a, 10a) back into contact with each other thus giving the lengthening piece with the desired rigidity. An accurate relative positioning is then ensured by a flexible plate (34a) whose lateral edges are secured to each of the pieces.
    • 为了减轻部署太阳能发电机等空间仪器的展开式延长部件结束时发生的冲击,而不需要采用复杂的调速或同步机构进行部署,本发明提供了一种扭矩限制装置( 28a)放置在每个接头(12)和延长件的相邻元件(10a)中的至少一个之间。 该装置包括弹性系统,例如一叠Belleville垫圈(48a),其以预定和优选可调节的力将接头的板(24a)压靠在元件(10a)的边缘上。 在展开结束时,这种弹性系统通过变形吸收冲击的能量,然后使两个部件(24a,10a)相互接触,从而使延长件具有所需的刚性。 然后通过柔性板(34a)确保精确的相对定位,所述柔性板(34a)的侧边固定到每个零件上。
    • 6. 发明授权
    • Device for the suspension and translational guidance of an item of
apparatus and item of apparatus equipped with such a device
    • 用于装备物品和配备有这种装置的装置的物品的悬挂和平移指导的装置
    • US5859731A
    • 1999-01-12
    • US895022
    • 1997-07-16
    • Gerard VezainSilvain Legrand
    • Gerard VezainSilvain Legrand
    • G02B7/02
    • G02B7/023
    • The present invention relates to a device for the suspension and translational guidance of an item of apparatus (1) intended to be displaced, parallel to its longitudinal axis (X--X) with respect to a stationary support (2), having one pair of suspension elements (4A, 4B) spaced along said longitudinal axis (X--X) while being flexible parallel to said axis, and controllable actuating means (10) intended to exert a force parallel to said axis (X--X) on said suspension elements.According to the invention, each of said suspension elements (4A, 4B) consists of at least one pair of blades (5A, 5B, 6A, 6B), one end of one of said blades being secured to said support (2) and one end of the other of said blades being secured to said item of apparatus (1), the other ends of said blades being secured to each other.
    • 本发明涉及一种用于悬挂和平移引导装置(1)的装置,该装置(1)旨在相对于固定支撑件(2)平行于其纵向轴线(XX)移位,具有一对悬挂元件 (4A,4B),沿着所述纵向轴线(XX)间隔开,同时平行于所述轴线是柔性的,以及可控制的致动装置(10),用于在所述悬架元件上施加平行于所述轴线(XX)的力。 根据本发明,每个所述悬挂元件(4A,4B)由至少一对叶片(5A,5B,6A,6B)组成,所述叶片中的一个叶片的一端固定到所述支撑件(2),一个 另一个所述叶片的端部被固定到所述装置(1)上,所述叶片的另一端彼此固定。
    • 9. 发明授权
    • Sensor release latch for space vehicle
    • 空间车辆的传感器释放闩锁
    • US4489329A
    • 1984-12-18
    • US438667
    • 1982-11-02
    • Gerard VezainJean-Claude Vermalle
    • Gerard VezainJean-Claude Vermalle
    • F16B1/02B64G1/22B64G1/44B64G1/64F42B3/00H01Q1/08H01Q1/28
    • B64G1/222B64G1/645B64G1/44Y10S343/02Y10T24/44436
    • A holding and releasing system provides temporary connection between a movable and a stationary part which are to be separated during the specific use thereof. It comprises a supporting foot connected to the fixed part, a rocker link hinged to said foot, a movable support hinged to said link, a sheaving bracket hinged to another end of said link; said link occupying two positions, i.e. a locking one in which the movable support bears on one face of the movable part, while the free end of the sheaving bracket bears on the other face of said movable part, to block the latter in a precise position, and a release position in which the movable support and said bracket are in a retracted position thereby releasing the movable part. The system is used especially in the space vehicle domain.
    • 保持和释放系统提供在特定使用期间待分离的可移动和静止部分之间的临时连接。 它包括连接到固定部分的支撑脚,铰接到所述脚的摇杆连杆,铰接到所述连杆的可动支架,铰链到所述连杆的另一端的滑轮架; 所述连接件占据两个位置,即锁定件,其中可移动支撑件承载在可移动部件的一个表面上,而滑轮托架的自由端承载在所述可移动部件的另一面上,以将其锁定在精确位置 以及释放位置,其中可移动支撑件和所述托架处于缩回位置,从而释放可移动部件。 该系统特别用于太空车辆领域。