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    • 2. 发明公开
    • Flexible data communication among partitions in integrated modular avionics
    • Bordelektronik的柔性数据分配器
    • EP2743830A1
    • 2014-06-18
    • EP12380054.2
    • 2012-12-13
    • EUROCOPTER ESPAÑA, S.A.
    • Catalan Alarcon, José AntonioEsparcia Perez, Antonio
    • G06F9/54
    • G06F9/542G06F9/544G06F2209/544
    • In an aircraft (1), a distributed architecture compliant to the specification ARINC653 forms an IMA (3) with Partitions (5) in hardware Modules (6), where shared memories (13) are mapped with shared I/O memory (20).
      For flexible communication among Partitions (5), a circular buffer (19) and a concurrent programming algorithm (23) are coupled to each shared I/O memory (20). A Publisher Component (16) builds new messages with datum and topics (21). A Subscriber Component (17) goes through a local message buffer searching for those ones matching a topic (21). A selective communication is performed by elected areas of the shared I/O memory (20). Finally are set as read previously delivered messages in order to prevent duplicated readings.
      The invention is distinct from data transfer via classical channels, thus being useful to obtain high reusability, portability and scalability.
    • 在飞机(1)中,符合规范ARINC653的分布式架构在硬件模块(6)中形成具有分区(5)的IMA(3),其中共享存储器(13)被映射为共享I / O存储器(20) 。 为了在分区(5)之间的灵活通信,循环缓冲器(19)和并行编程算法(23)耦合到每个共享I / O存储器(20)。 发布商组件(16)使用基准和主题构建新消息(21)。 用户组件(17)通过本地消息缓冲器来搜索与主题匹配的那些(21)。 共享I / O存储器(20)的选择区域执行选择性通信。 最后设置为读取先前传递的消息,以防止重复的读数。 本发明与通过经典通道的数据传输不同,因此有助于获得高可重用性,便携性和可扩展性。
    • 4. 发明公开
    • Air drag reduction for an undercarriage with skids of a rotary wing aircraft
    • Luftwiderstandsverringerungfürein Fahrwerk mit Landekufen einesDrehflügler
    • EP2610170A1
    • 2013-07-03
    • EP11380105.4
    • 2011-12-28
    • EUROCOPTER ESPAÑA, S.A.
    • Jimenez Garcia, Juan Manuel
    • B64C25/52
    • B64C25/52B64C2025/325B64C2230/20Y02T50/166
    • The invention pertains to an undercarriage (2) having skids for a rotary wing aircraft (1).
      For air drag reduction, the undercarriage (2) is equipped with a device (3), suitable for creating an artificial flow of air around the undercarriage (2), particularly at the vicinity of transverse elements (10-11), in order to delay / displace rearwards the location of the breaking point (27) and in order to increase the boundary layer energy.
      An embodiment proposes a series of slots or nozzle bores, allocating an extra airflow into the boundary layer, with the result of reducing the overall air drag of the undercarriage (2) as well as the air drag of the whole rotary wing aircraft (1), and thus provoking an air drag reduction effect.
    • 本发明涉及一种具有用于旋转翼飞机(1)的滑行板的起落架(2)。 为了减少空气阻力,起落架(2)装备有适于在起落架(2)周围产生人造气流的装置(3),特别是在横向元件(10-11)的附近,以便 延迟/向后移位断点(27)的位置,以便增加边界层能量。 一个实施例提出了一系列槽或喷嘴孔,将额外的气流分配到边界层中,结果是减小了起落架(2)的整体空气阻力以及整个旋翼飞机(1)的空气阻力, ,从而引起空气阻力降低效果。