利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

203 条记录 (耗时 0.014 秒)

    LANDESTOSSDÄMPFER
    91.
    发明公开
    LANDESTOSSDÄMPFER 失效

    公开(公告)号：EP0815007A1

    公开(公告)日：1998-01-07

    申请号：EP96907343.0

    申请日：1996-03-04

    申请人： STN ATLAS Elektronik GmbH

    发明人： CLAUSNITZER, Hans-Jürgen ,  SCHWEREN, Johann

    IPC分类号： B64D1 ,  B64G1 ,  F16F9

    CPC分类号： F16F9/049 ,  B64D1/14 ,  B64D2201/00 ,  B64G1/22 ,  B64G1/62

    摘要： A landing shock absorber for air loads or pilotless aircraft (10) equipped with brake parachutes has at least one inflatable landing shock absorbing bag (11) made of an inflatable inner bag (13) and of an outer bag (14) that encloses the inner bag (13). In order to easily modify the shock absorbing characteristics of the landing shock absorbing bag (11) and to individually adapt it to its intended use, the inner bag (13) is made of a pressure-tight, plastically deformable sheet and is subdivided into several inflatable air chambers (15, 16) that communicate through at least one hole (17), whereas the outer bag (14) is made of a tear-resistant fabric with low air permeability and has a plurality of precisely defined throttle openings (21).

    摘要翻译： 用于空气负载的着陆减震器或配备有制动降落伞的无人驾驶飞机（10）具有至少一个由可充气内袋（13）和外袋（14）制成的可充气着陆减震袋（11），所述外袋（14） 袋（13）。 为了容易地改变降落冲击吸收袋（11）的冲击吸收特性并单独使其适应其预期用途，内袋（13）由耐压，可塑性变形的薄片制成，并被细分成几个 通过至少一个孔（17）连通的充气气室（15,16），而外袋（14）由具有低透气性的抗撕裂织物制成，并具有多个精确限定的节气门开口（21） 。

    Deployment hinge apparatus
    93.
    发明公开
    Deployment hinge apparatus 失效
    部署铰链装置

    公开(公告)号：EP0776826A2

    公开(公告)日：1997-06-04

    申请号：EP97200219.0

    申请日：1995-09-26

    申请人： SPACE SYSTEMS / LORAL INC.

    发明人： Baghdasarian, Varouj G.

    IPC分类号： B64G1/22 ,  H01Q1/28 ,  E05D11/10

    CPC分类号： E05F1/1207 ,  B64G1/22 ,  E05D11/1007 ,  E05Y2900/502 ,  H01Q1/288 ,  Y10T16/532 ,  Y10T16/53828 ,  Y10T16/5387 ,  Y10T16/5389 ,  Y10T16/54 ,  Y10T16/540243 ,  Y10T16/5404 ,  Y10T16/5453

    摘要： A deployment hinge apparatus (120) comprises a stationary bracket (122) and a hinge arm (124) supporting an operating structure (126) and pivotally mounted on the stationary bracket for moving the operating structure between a stowed position and a deployed position. A bearing (128) is provided to pivotally mount the hinge arm (124) on the stationary bracket (122). A first stop (154) is provided on the stationary bracket (122), and a second stop (156) is provided on the hinge arm (124) and positioned to engage the first stop (154) when the hinge arm (124) is in the deployed position. A spring (146) biases the hinge arm (124) towards the deployed position with the second stop (156) engaged with the first stop (154), so as to retain the hinge arm (124) in the deployed position.

    摘要翻译： 展开式铰链装置（120）包括固定支架（122）和支撑操作结构（126）并枢转地安装在固定支架上的铰链臂（124），用于在收起位置和展开位置之间移动操作结构。 提供轴承（128）以将铰链臂（124）枢转地安装在固定支架（122）上。 第一止动件154设置在固定支架122上，并且第二止动件156设置在铰接臂124上并且定位成当铰接臂124是第一止动件154时接合第一止动件154。 在部署位置。 当第二止动件（156）与第一止动件（154）接合时，弹簧（146）将铰接臂（124）朝向展开位置偏置，以便将铰接臂（124）保持在展开位置。

    Transmitting apparatus for use in non-geostationary satellites
    95.
    发明公开
    Transmitting apparatus for use in non-geostationary satellites 失效
    在非地球同步卫星的使用发送装置

    公开(公告)号：EP0709288A3

    公开(公告)日：1996-07-31

    申请号：EP95117089.3

    申请日：1995-10-30

    申请人： NEC CORPORATION

    发明人： Ikebe, Kenichi, c/o NEC Corp.

    IPC分类号： B64G1/22

    CPC分类号： B64G1/66 ,  B64G1/1007 ,  B64G1/1085 ,  B64G1/22 ,  B64G1/24 ,  B64G1/365 ,  H01Q1/288 ,  H01Q3/24 ,  H04B7/18513 ,  H04B7/18515

    摘要： A transmitting apparatus for use in non-geostationary satellites which allows compliance with the restrictions placed on PFD even when the Earth is located between the geostationary satellite and the non-geostationary satellite. The transmitting apparatus 10 for use in non-geostationary satellites having a transmitting section 16 which sends a transmitting signal to the geostationary satellite, comprises an Earth-sensing section 19 for detecting the presence of the Earth in the direction of transmission and a transmission direction-shifting section 20 for shifting the direction of transmission of the transmitting signal in response to detection of the Earth-sensing section 19 to prevent the Earth from being exposed to the transmitting signal. Instead of the transmission direction-shifting section 20, there may be used a power supply-suspending section which automatically suspends power supply to the transmitting section 16 thereby stopping transmission of the transmitting signal.

    Deployment hinge apparatus
    96.
    发明公开
    Deployment hinge apparatus 失效
    部署铰链装置

    公开(公告)号：EP0704373A3

    公开(公告)日：1996-07-31

    申请号：EP95306759.2

    申请日：1995-09-26

    申请人： SPACE SYSTEMS / LORAL INC.

    发明人： Baghdasarian, Varouj G.

    IPC分类号： B64G1/22 ,  H01Q1/28 ,  E05D11/10

    CPC分类号： E05F1/1207 ,  B64G1/22 ,  E05D11/1007 ,  E05Y2900/502 ,  H01Q1/288 ,  Y10T16/532 ,  Y10T16/53828 ,  Y10T16/5387 ,  Y10T16/5389 ,  Y10T16/54 ,  Y10T16/540243 ,  Y10T16/5404 ,  Y10T16/5453

    摘要： Deployment hinge apparatus comprises a stationary U-shaped bracket including a flange defining a retention recess. A hinge arm for supporting an operating structure such as a communication antenna reflector is pivotally mounted on the stationary bracket for movement between a stowed position and a deployed position. The hinge arm includes a deployment and latching cam which extends to a projecting nose member. A latch arm is pivotally mounted at one end to the stationary bracket and includes a cam follower at its other end operatively engageable with the cam. A spring biases the cam follower into engagement with the cam and is thereby effective to rotate the hinge arm from the stowed position to the deployed position such that, in the deployed position, the nose member and the cam follower are together snugly received in the retention recess, locking the hinge arm in the deployed position. In a simplified embodiment, which does not utilize a latch arm or a cam and cam follower, a bearing pivotally mounts the hinge arm on the stationary bracket. A first stop member is provided on the stationary bracket and a second adjustable stop member is provided on the hinge arm positioned to engage the first stop member when the hinge arm is in the deployed position. A spring biases the hinge arm toward the deployed position with the second stop member engaged with the first stop member and is effective to retain the hinge arm in the deployed position.

    Self-deploying helical structure
    100.
    发明公开
    Self-deploying helical structure 失效
    自我部署的螺旋结构

    公开(公告)号：EP0666612A2

    公开(公告)日：1995-08-09

    申请号：EP94120944.7

    申请日：1994-12-30

    申请人： ORBITAL SCIENCES CORPORATION

    发明人： Robinson, Anthony D.

    IPC分类号： H01Q11/08 ,  H01Q1/28 ,  B64G1/22

    CPC分类号： B64G1/66 ,  B64G1/22 ,  B64G9/00 ,  H01Q1/288 ,  H01Q11/086 ,  Y10T16/5253

    摘要： A helical antenna structure is deformable and capable of being stowed in a small volume. At deployment, the helical antenna structure uses the stored strain energy in its resilient helices to revert to its original shape without the use of any outside force. Multiple antenna structures can be linked using a plurality of resilient lenticular shaped hinges.

    摘要翻译： 螺旋天线结构是可变形的并且能够存放在小体积中。 在部署时，螺旋天线结构利用其弹性螺旋中存储的应变能恢复到其原始形状，而无需使用任何外力。 多个天线结构可以使用多个弹性透镜状铰链连接。