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A method for depositing cruise missile of a military aircraft

机译:一种存放军用飞机巡航导弹的方法

摘要

A method for depositing on an extendible platform or on a airdrop - pylon cruise missile arranged by means of a military aircraft airdrop in the case of great height and the usual speed, with the steps of:a. pulling out of the extendible platform or the airdrop - pylons the cruise missiles by means of the rear, open loading ramp of the pilot parachute transport aircraft by means of an unfolded,example, after sensing of the intended airdrop-operation by means of the cruise missiles by means of discrete signals and a separate sensor system, the ignition of cartridges of a pylon of the extendible platform or the airdrop - pylons by means of the cruise missiles via umbilical-connection for the purpose of the separation of the extendible platform or the airdrop - pylon only when the cruise missiles is sensed, that it is stable in a nearly vertical position downward together with the extendible platform or with the airdrop - pylon depends on the pilot parachute and the pendulum motion has decayed,c. after the separation of the cruise missile of the extendible platform or from the airdop - pylon by means of a plunger, and after provision of the required energy of the pivoting blades cruise missile be opened and the covers of the removed engine air intakes,d. in the connection, a swoop maneuver of the cruise missile, during which the march missile turboprop is started,e. after reaching the idling speed of the engine, the cruise missiles a intercept maneuver in order to achieve a horizontal attitude by, whereinf. of the cruise missiles after reaching a horizontal attitude attempts have been made to carry out the pre-planned mission.
机译:一种用于在高度和通常速度较高的情况下通过军用飞机空投放置在可扩展平台或空投塔式巡航导弹上的方法,其步骤如下:在通过巡航检测到预期的空投操作之后,例如通过展开,例如通过飞行员降落伞运输机的后部,开放的装载坡道,将巡航导弹拉出可扩展平台或空投塔。导弹通过离散信号和单独的传感器系统,可扩展平台的塔架或空投塔架的点火通过巡航导弹通过脐带连接来点火,以分离可扩展平台或空投-定向塔只有在感测到巡航导弹时才能与可扩展平台或空投-定向塔一起稳定在向下的垂直位置,这取决于飞行员的降落伞,并且摆锤的运动减弱了。在将可扩展平台的巡航导弹或通过柱塞从空中操纵塔分离出来之后,并在提供所需的枢转叶片能量后,打开巡航导弹,并取下已取下的发动机进气口盖,d。在此过程中,对巡航导弹进行俯冲操纵,在此期间,启动了行进导弹涡轮螺旋桨飞机,e。在达到发动机的空转速度后,巡航导弹进行拦截操作,以达到水平姿态,其中f。在达到水平姿态后,对巡航导弹进行了尝试,以进行预先计划的任务。

著录项

  • 公开/公告号DE102004042989B4

    专利类型

  • 公开/公告日2014-10-30

    原文格式PDF

  • 申请/专利权人 MICHAEL GRABMEIER;

    申请/专利号DE20041042989

  • 发明设计人 GLEICH PATENTINHABER;

    申请日2004-09-06

  • 分类号B64D1/04;B64D7/08;

  • 国家 DE

  • 入库时间 2022-08-21 15:38:08

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