利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

41 条记录 (耗时 0.015 秒)

    DECELERATION PLATFORM
    3.
    发明公开
    DECELERATION PLATFORM 有权
    DELAY平台和方法

    公开(公告)号：EP2137070A1

    公开(公告)日：2009-12-30

    申请号：EP08736918.7

    申请日：2008-04-09

    申请人： Babcock Integrated Technology Limited

    发明人： SCHAFER, David Richard ,  BORLAND, Gavin

    IPC分类号： B64D1/14

    CPC分类号： B64D1/14

    摘要： A platform (1) for the aerial delivery of payloads into aquatic environments has a staged v cross-section formed by two walls extending from an end part. The portions (6) of the two walls adjacent to the end part diverge from it at an angle and, together with the end part, form the tip of the platform. The remaining portions (7) of the two walls, remote from the end part, form the body of the platform, and diverge at an angle that is greater than the angle. When the platform is deployed onto the surface of a fluid, it initially experiences a period of low deceleration as the tip penetrates the surface, followed by a period of higher deceleration, as the body contacts the surface.

    IMPROVED AERIAL DELIVERY PLATFORM
    4.
    发明公开
    IMPROVED AERIAL DELIVERY PLATFORM 有权
    改进的空气DROP DECK

    公开(公告)号：EP1562825A1

    公开(公告)日：2005-08-17

    申请号：EP03772411.9

    申请日：2003-11-06

    申请人： Airborne Systems Limited

    发明人： PARKINSON, Stephen Thomas

    IPC分类号： B64D1/14

    CPC分类号： B64D1/14 ,  B64D2201/00

    摘要： An aerial delivery platform (1) comprising a generally flat base (2) for supporting a payload, at least one pair of inflatable airbags (3) mounted underneath the base and capable of inflation during aerial descent, the airbags having a main body part (4) extending downwardly of the base, and an extension part (5) adjacent the main body part extending outwardly thereof and having a sidewall (8) which, upon airbag inflation, extends to the region (6) of at least one base member edge (7), the extension part (5) also forming an extension to the base of the main body part. Embodiments of the present aerial delivery platform can provide an enhanced impact area and therefore greater protection to the framework of the platform, and less risk of damage to the platform or payload thereon particularly during descents in prevailing side wind conditions.

    STEERABLE PARACHUTE CONTROL SYSTEM AND METHOD
    5.
    发明公开
    STEERABLE PARACHUTE CONTROL SYSTEM AND METHOD 审中-公开
    控系统及应税降落伞程序

    公开(公告)号：EP1463663A2

    公开(公告)日：2004-10-06

    申请号：EP02797214.0

    申请日：2002-12-09

    申请人： Atair Aerospace, Inc.

    发明人： PRESTON, Daniel

    IPC分类号： B64D17/34

    CPC分类号： F42B10/56 ,  B64D1/08 ,  B64D1/14 ,  B64D17/025 ,  B64D17/04 ,  B64D17/08 ,  B64D17/34 ,  B64D17/38 ,  B64D17/54 ,  B64D17/74 ,  F42B4/28 ,  F42B10/58 ,  G05D1/105

    摘要： An autonomous guided parachute system for cargo drops that divides the requirements of guidance and soft landing into separate parachutes. Said invention includes a high wing-loaded ram air parachute for guidance, a larger round parachute for soft landing, a harness/container system, flight computer, position sensors and actuation system. The system is dropped from an airplane, a predetermined period of drogue fall ensures a stable position prior to deploying the guidance parachute. The flight controller determines a heading to intersect with an area substantially above the desired target and controls the guidance parachute via pneumatic actuators connected to the parachutes steering lines to fly on that heading. At a minimum altitude prior to the systems impact with the ground the flight computer transitions the system from the fast high performance guidance parachute to a larger landing parachute by releasing the guidance parachute to static line extract and deploy the landing parachute. If the system reaches a position substantially above target area prior to the parachute transition altitude flight computer controls the system into a spiral dive or other rapid altitude dropping maneuver until the transition altitude is reached. Once transitioned to the landing parachute the system descends for a brief period unguided under the landing parachute until touchdown.

    Verfahren zur Verhinderung des Überschlagens bei der Landung eines Luft- oder Raumfahrtgerätes
    6.
    发明公开
    Verfahren zur Verhinderung des Überschlagens bei der Landung eines Luft- oder Raumfahrtgerätes 失效
    飞行器或航天设备的着陆过程中用于预防翻倒的方法

    公开(公告)号：EP0861780A1

    公开(公告)日：1998-09-02

    申请号：EP98100353.6

    申请日：1998-01-12

    申请人： Daimler-Benz Aerospace Aktiengesellschaft

    发明人： Menne, Stefan, Dr. ,  Ovadya, Yasar, Ing. ,  Schmidt, Bernhard, Dipl.-Ing. ,  Wagner, Adalbert, Dipl.-Ing.

    IPC分类号： B64D1/14

    CPC分类号： B64D1/14

    摘要： Das Verfahren zur Verhinderung des Überschlagens bei der Landung eines Luft- oder Raumfahrtgerätes mit Hilfe eines Airbag-Landestoss-Dämpfungssystems, welches vor der Landung mit Gas aufgeblasen wird und aus dem während der Landung über Auslassventile Gas austritt, besteht darin, dass als Airbag-Landestoss-Dämpfungssystem ein in mehrere unabhängig voneinander mit Gas aufblasbare und gasablassende Kammern unterteiltes System verwendet wird und dass bei der Landung ein Druckunterschied in den einzelnen Kammern des Airbag-Landestoss-Dämpfungssystems erzeugt wird.

    摘要翻译： 该方法包括防止到空气或空间飞行器其中在制动或制动的状态接近地球表面的倾覆，通过使用气囊着陆减震系统的所有其在着陆之前充有气体，并从其中的气体让 走出着陆在相应的气体出口阀期间。 该系统是细分成的海誓山盟膨胀和可收缩室的若干unabhängig，并在单独的腔室的压力差是在着陆过程中产生的，在寻求方式，做了前室相对于飞行方向，具有较高的气体压力比 后部腔室。