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    • 22. 发明申请
    • AN AIRCRAFT PROPULSIVE POWER UNIT
    • 飞机推进动力单元
    • WO1994016945A1
    • 1994-08-04
    • PCT/GB1994000131
    • 1994-01-24
    • SHORT BROTHERS PLCCOLE, DerekSHERRY, Philip, DavidBLAIR, Alan, John
    • SHORT BROTHERS PLC
    • B64D29/00
    • B64D29/08B64D29/00
    • An aircraft propulsive power unit (19) comprises a nacelle structure (20) housing an engine and having a forward nacelle portion (21) and a rearward nacelle portion (131). The rearward end of the forward nacelle portion (21) in an operational position adjoins the forward end of the rearward nacelle portion (131) and the forward end of the forward nacelle portion (21) includes an intake opening leading to an intake barrel (28) upstream of the engine for the supply of intake air to the engine. The forward nacelle portion (21) has an uninterrupted or substantially uninterrupted low drag exterior surface thereover and the power unit includes support structure to support the forward nacelle portion (21) while permitting it to be moved forwardly on the support structure from the operational position to a forward position in which it is supported by the support structure forwardly of the operational position to provide access to components of the power unit (19) which are inaccessible with the forward nacelle portion (21) in the operational position.
    • 飞机推进动力单元(19)包括容纳发动机并具有前部机舱部分(21)和后部机舱部分(131)的机舱结构(20)。 前部机舱部分(21)的后端处于操作位置,邻接后部机舱部分(131)的前端,并且前部机舱部分(21)的前端包括通向进气筒(28)的进气口 ),用于向发动机供应进气。 前部机舱部分(21)在其上方具有不间断的或基本上不间断的低阻力外表面,并且动力单元包括支撑结构以支撑前部机舱部分(21),同时允许其在支撑结构上从操作位置向前移动到 前部位置,其中由支撑结构向前支撑在操作位置,以提供进入动力单元(19)的部件,这些部件在前部机舱部分(21)处于操作位置时是不可接近的。
    • 27. 发明申请
    • THERMAL ANTI-ICING OF AIRCRAFT STRUCTURES
    • 飞机结构的热防护
    • WO1993006005A1
    • 1993-04-01
    • PCT/GB1992001710
    • 1992-09-17
    • SHORT BROTHERS PLCARNOLD, Michael, JohnCOLE, Derek
    • SHORT BROTHERS PLC
    • B64D15/04
    • B64D15/04B64D33/02B64D2033/0206B64D2033/0233B64D2033/0286F02C7/047
    • An aircraft structural component comprises a forward compartment (17) formed by a forward bulkhead (19) and a skin structure (21) which extends forwardly of the forward bulkhead (17) and which has an outer surface which requires to be protected from accumulation of ice thereon, and a rear compartment (18) formed between the forward bulkhead (19) and a rear bulkhead (20). A supply duct (25) extends through the rear compartment (18) and into the forward compartment (17) for the delivery thereto of pressurised hot gases for distribution over the inner surface of the skin structure (21) to prevent accumulation of ice on the outer surface of the skin structure (21). A protective shroud duct (31) surrounds the supply duct (25), extends from the rear bulkhead (20) to the forward bulkhead (19) and forms an annular space between the protective shroud duct (31) and the supply duct (25). The annular space is closed off at its rear end at the rear bulkhead (20) and throughout its length within the rear compartment (18) by the protective shroud duct (31) and is open at its forward end to provide gaseous flow communication with the forward compartment (17), whereby leakage of hot gases from the supply duct (25) upon rupture are prevented by the protective shroud duct (31) from entering into the rear compartment (18) and pass into the forward compartment (17). A discharge duct is provided for discharging spent gases from the forward compartment (17) to atmosphere.