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1. 发明授权

US4121606A Inflatable air inlet duct 失效
标题翻译：充气进气管
公开(公告)号：US4121606A
公开(公告)日：1978-10-24
申请号：US845172
申请日：1977-10-25
申请人： Charles L. Holland , George B. Nicoloff
发明人： Charles L. Holland , George B. Nicoloff
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0286 , Y10T137/0536
摘要： An air inlet duct for a jet propulsion missile or other vehicle which is movable between a housed, pre-launch position and an extended or deployed flight position. A method of manufacturing the duct is also disclosed. The duct system includes a flexible leading edge attached to a double-wall inflatable duct body. Drop threads extend between the duct body walls to hold an exact desired contour when the duct is inflated. A pivotable plate moves the inflatable duct between a housed, deflated, position and an inflated flight position. Manufacture of the inflatable duct is basically accomplished by preparing a foamed plastic form in the desired duct wall shape, covering the form with fabric, stitching through the foam and fabric, coating the fabric with a flexible sealing compound, dissolving away the foamed plastic and attaching the resulting inflatable duct to other missile components.
摘要翻译：用于喷气推进导弹或其他车辆的进气管道，其可在容纳的预发射位置和延伸或部署的飞行位置之间移动。还公开了制造管道的方法。管道系统包括连接到双壁可充气管道主体的柔性前缘。当管道膨胀时，落纱线在管体壁之间延伸以保持精确期望的轮廓。可枢转板将可充气管道移动到容纳的，放气的位置和充气的飞行位置之间。充气管道的制造基本上是通过制备所需导管壁形状的泡沫塑料形式，用织物覆盖形式，缝合通过泡沫和织物，用柔性密封化合物涂覆织物，将泡沫塑料和附着物所产生的充气管道与其他导弹部件。

2. 发明授权

US4185373A Method of manufacturing an inflatable air inlet duct 失效
标题翻译：制造充气进气管道的方法
公开(公告)号：US4185373A
公开(公告)日：1980-01-29
申请号：US922248
申请日：1978-07-05
申请人： Charles L. Holland , George B. Nicoloff
发明人： Charles L. Holland , George B. Nicoloff
IPC分类号： B64D33/02 , F42B15/00
CPC分类号： F42B15/00 , B64D33/02 , B64D2033/0286 , Y10T29/4981
摘要： An air inlet duct for a jet propulsion missile or other vehicle which is movable between a housed, pre-launch position and an extended or deployed flight position. A method of manufacturing the duct is also disclosed. The duct system includes a flexible leading edge attached to a double-wall inflatable duct body. Drop threads extend between the duct body walls to hold an exact desired contour when the duct is inflated. A pivotable plate moves the inflatable duct between a housed, deflated, position and an inflated flight position. Manufacture of the inflatable duct is basically accomplished by preparing a foamed plastic form in the desired duct wall shape, covering the form with fabric, stitching through the foam and fabric, coating the fabric with a flexible sealing compound, dissolving away the foamed plastic and attaching the resulting inflatable duct to other missile components.
摘要翻译：用于喷气推进导弹或其他车辆的进气管道，其可在容纳的预发射位置和延伸或部署的飞行位置之间移动。还公开了制造管道的方法。管道系统包括连接到双壁可充气管道主体的柔性前缘。当管道膨胀时，落纱线在管体壁之间延伸以保持精确期望的轮廓。可枢转板将可充气管道移动到容纳的，放气的位置和充气的飞行位置之间。充气管道的制造基本上通过制备所需导管壁形状的泡沫塑料形式，用织物覆盖形式，缝合穿过泡沫和织物，用柔性密封化合物涂覆织物，将泡沫塑料和附着物所产生的充气管道与其他导弹部件。

3. 发明授权

US4307839A Variable exit area ramjet nozzle 失效
标题翻译：可变出口区域冲压喷嘴
公开(公告)号：US4307839A
公开(公告)日：1981-12-29
申请号：US968348
申请日：1978-12-11
申请人： George B. Nicoloff , Clark Kerr, Jr.
发明人： George B. Nicoloff , Clark Kerr, Jr.
IPC分类号： F02K1/12 , F02K9/97 , B64C15/06
CPC分类号： F02K9/978 , F02K1/12
摘要： A ramjet missile with a variable size exhaust nozzle formed by a plurality of flaps having heat resistant blocks displaced circumferentially about the nozzle which are latched within the divergent contour of the nozzle during missile climb condition and extendable radially into the exhaust nozzle exit area to reduce the size thereof for missle cruise and descent. These heat resistant blocks are jetisonable so that the nozzle exit area may be increased to its original size upon the missile return to low level flight condition. Actuators are also provided for operating the flaps for unlatching, extending and jetisoning the heat resistant blocks at the appropriate time.
摘要翻译：具有可变尺寸排气喷嘴的冲击弹导弹，其由多个翼片形成，所述多个翼片具有围绕喷嘴周向移动的耐热块，其在导弹爬升状态期间锁定在喷嘴的发散轮廓内并可径向延伸到排气喷嘴出口区域中，以减少大小为missle巡航和下降。这些耐热块是可发射的，使得在导弹返回到低水平飞行状态时，喷嘴出口面积可以增加到其原始尺寸。还提供致动器用于操作翼片以在适当的时间解锁，延伸和喷射耐热块。

4. 发明授权

US4221230A Variable air inlet for a ramjet powered missile 失效
标题翻译：用于冲压式导弹的可变进气口
公开(公告)号：US4221230A
公开(公告)日：1980-09-09
申请号：US968347
申请日：1978-12-11
申请人： George B. Nicoloff , Clark Kerr, Jr.
发明人： George B. Nicoloff , Clark Kerr, Jr.
IPC分类号： F02C7/057 , F42B15/36 , F02K1/00
CPC分类号： F42B15/36 , F02C7/057 , Y10T137/0536
摘要： A ramjet powered missile having means for controlling the air inlet geometry for best efficiency at a given end-of-boost-take-over Mach number and for changing the inlet geometry for best efficiency at a higher Mach number for fuel economy and extended flight range comprising a first jetisonable air inlet formed of a plurality of removable lip sections held in place by connecting struts and pyrotechnic thrusters. The explosive charge of the thrusters when activated eject the lip sections and struts outward and clear of the missile thus providing a second inlet of a different geometry.
摘要翻译：一种冲压喷气发动机的导弹具有控制进气口几何形状的装置，以便在给定的升压 - 接管马赫数结束时获得最佳效率，并改变进气口几何形状，以获得更高的马赫数，以获得更高的马赫数以获得燃油经济性和延长的飞行范围包括通过连接支柱和烟火推进器而保持在适当位置的多个可移除的唇部形成的第一可喷射空气入口。推动器的激活装置在激活时将外壳部分和支柱向外弹出并从导弹中排出，从而提供不同几何形状的第二个入口。

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