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1.发明申请公开(公告)号：US20050269454A1
公开(公告)日：2005-12-08
申请号：US11037125
申请日：2005-01-19
CPC分类号： F42B10/46 , F42B12/105
摘要： It is an object of the present invention to provide a flying object using a thin elongated nose cone with a small tip angle for reducing the air resistance during flying, wherein the maximum loading capacity can be increased without decreasing the volume efficiency of the flying object by limitations placed on the accommodation space, regardless of the structure thereof. In the flying object in accordance with the present invention, which comprises a nose cone in the tip portion, the nose cone portion has a compressed structure in the axial direction during accommodation and expands on the tip side in the axial direction during flying, due to an expandable nose cone structure such that a disk with a small diameter is disposed in the forward position and the disks with a successively increasing diameter are disposed in the axial direction. After separation, the nose cone expands in the axial direction, deep cavities are formed between the disks, and a fine elongated nose cone with a small tip angle is provided, whereby the air resistance is reduced.
摘要翻译： 本发明的目的是提供一种飞行物体，其使用具有小尖角的细长鼻锥，以减少飞行期间的空气阻力，其中可以增加最大承载能力，而不会降低飞行物体的体积效率 不管其结构如何，对住宿空间的限制。 在根据本发明的飞行物体中，其包括尖端部分中的鼻锥，鼻锥部在调节期间在轴向方向上具有压缩结构，并且在飞行期间在轴向方向上的尖端侧膨胀，由于 可扩展的鼻锥结构，使得具有小直径的盘被设置在向前位置，并且具有连续增加的直径的盘沿轴向设置。 分离后，鼻锥在轴向上膨胀，在圆盘之间形成深空腔，并提供具有小尖角的细长鼻锥，由此减小空气阻力。
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2.发明授权公开(公告)号：US07118072B2
公开(公告)日：2006-10-10
申请号：US11037125
申请日：2005-01-19
IPC分类号： B64C1/38
CPC分类号： F42B10/46 , F42B12/105
摘要： It is an object of the present invention to provide a flying object using a thin elongated nose cone with a small tip angle for reducing the air resistance during flying, wherein the maximum loading capacity can be increased without decreasing the volume efficiency of the flying object by limitations placed on the accommodation space, regardless of the structure thereof.In the flying object in accordance with the present invention, which comprises a nose cone in the tip portion, the nose cone portion has a compressed structure in the axial direction during accommodation and expands on the tip side in the axial direction during flying, due to an expandable nose cone structure such that a disk with a small diameter is disposed in the forward position and the disks with a successively increasing diameter are disposed in the axial direction. After separation, the nose cone expands in the axial direction, deep cavities are formed between the disks, and a fine elongated nose cone with a small tip angle is provided, whereby the air resistance is reduced.
摘要翻译： 本发明的目的是提供一种飞行物体，其使用具有小尖角的细长鼻锥，以减少飞行期间的空气阻力，其中可以增加最大承载能力，而不会降低飞行物体的体积效率 不管其结构如何，对住宿空间的限制。 在根据本发明的飞行物体中，其包括尖端部分中的鼻锥，鼻锥部在调节期间在轴向方向上具有压缩结构，并且在飞行期间在轴向方向上的尖端侧膨胀，由于 可扩展的鼻锥结构，使得具有小直径的盘被设置在向前位置，并且具有连续增加的直径的盘沿轴向设置。 分离后，鼻锥在轴向上膨胀，在圆盘之间形成深空腔，并提供具有小尖角的细长鼻锥，由此减小空气阻力。
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公开(公告)号：US07322179B2
公开(公告)日：2008-01-29
申请号：US10759014
申请日：2004-01-20
CPC分类号： F02C7/042 , B64D33/02 , B64D2033/026 , F05D2220/80 , F05D2250/141 , F05D2250/90 , Y10T137/0645
摘要： An air intake includes a spike and a cylindrical cowl. The spike is composed of a plurality of plates which are arranged axial symmetrically around a central axis thereof, and the cowl includes an inner wall parallel to the central axis and is formed so as to enclose a rear portion of the spike via a given space. The adjacent ones of the plates form respective aerodynamic compressive surfaces in spaces formed by the adjacent ones. The distances between the adjacent ones of the plates are variable, and the distance between the forefront of the spike along the central axis and the cowl is variable.
摘要翻译： 进气口包括一个钉和一个圆柱形的整流罩。 尖钉由围绕其中心轴线对称布置的多个板组成，并且整流罩包括平行于中心轴线的内壁，并且形成为经由给定空间包围尖峰的后部。 相邻的板在由相邻板形成的空间中形成相应的空气动力学压缩表面。 相邻板之间的距离是可变的，并且沿着中心轴和整流罩的尖峰的最前沿之间的距离是可变的。
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4.发明授权Method for improving the performance of a cryogenic heat exchanger under frosting conditions 有权在结霜条件下提高低温热交换器性能的方法公开(公告)号：US06301928B1
公开(公告)日：2001-10-16
申请号：US09345480
申请日：1999-07-01
申请人： Nobuhiro Tanatsugu , Kenya Harada
发明人： Nobuhiro Tanatsugu , Kenya Harada
IPC分类号： F25J100
CPC分类号： B01D53/265 , F28F19/006
摘要： The present invention provides a method for preventing the decrease of the efficiency of heat transfer, caused by frost formation, in a precooler of an air breathing engine. In the precooler, the heat exchanger tube is provided. Into the heat exchanger tube, liquid hydrogen serving as a coolant is supplied. The main air flow is sent to the precooler via the intake duct, and the main air flow which is cooled down there, is then sent to a compressor of the air breathing engine. Via the nozzle provided in the middle of the intake duct, ethanol is mixed into the main air flow. Ethanol is carried into the precooler, and condenses together with the water vapor on the surface of the heat exchanger tube. A frost layer thus formed has less cavities and low thermal resistance as compared to that formed when the water vapor condenses solely. Therefore, the decrease of the performance of the heat exchanger, which is caused by the frost formation, can be prevented.
摘要翻译： 本发明提供一种在空气呼吸发动机的预冷器中防止由结霜引起的传热效率降低的方法。 在预冷器中，设置有热交换器管。 进入热交换管，供给作为冷却剂的液态氢。 主空气流经由进气管道被送到预冷器，然后在那里冷却的主空气流被送到空气呼吸发动机的压缩机。 通过设在进气管中间的喷嘴，将乙醇混入主气流。 乙醇被运送到预冷器中，并与热交换器管表面上的水蒸气一起冷凝。 与仅形成水蒸汽时形成的霜层相比，由此形成的霜层具有较少的空腔和低的热阻。 因此，可以防止由霜结构引起的热交换器的性能的降低。
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公开(公告)号：US5694769A
公开(公告)日：1997-12-09
申请号：US439121
申请日：1995-05-11
CPC分类号： F02K9/72
摘要： A liquid oxidizer immersion hybrid rocket having a combustion chamber, a porous fuel material placed in the combustion chamber, a liquid oxidizer filled into pores of the porous fuel material, and two holding plates provided in the combustion chamber so as to hold opposite ends of the porous fuel material respectively. The porous fuel material comprises a large number of layers stacked one another in an axial direction of the combustion chamber.
摘要翻译： 一种具有燃烧室，放置在燃烧室中的多孔燃料的液体氧化器浸入式混合火箭，填充在多孔燃料材料的孔中的液体氧化剂，以及设置在燃烧室中的两个保持板， 多孔燃料。 多孔燃料材料包括在燃烧室的轴向上彼此堆叠的大量层。
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公开(公告)号：US4894989A
公开(公告)日：1990-01-23
申请号：US364556
申请日：1989-06-08
CPC分类号： F24J2/34 , F02G1/055 , F24J2/07 , F02G2243/00 , F02G2254/40 , F02G2270/20 , Y02E10/41
摘要： A heater for use with a Stirling engine and a method for heating a working fluid for a Stirling engine is disclosed. The heater has a burner, heater tubes disposed in the burner, a space formed around the heater tubes which is filled with heat-storing material, and a high-temperature heat source. The heat-storing material is sealed by a seal member. Heat produced by the high-temperature heat source is supplied to the heater tubes via the heat-storing material; hence the heat-storing material acts as a secondary heat source. Heat is stored in the heat-storing material in the form of sensible heat or latent heat, or a chemical reaction is employed.
摘要翻译： 公开了一种用于斯特林发动机的加热器和用于加热用于斯特林发动机的工作流体的方法。 加热器具有燃烧器，设置在燃烧器中的加热器管，填充有储热材料的加热器管周围形成的空间和高温热源。 储热材料由密封件密封。 由高温热源产生的热量经由蓄热材料供给加热管; 蓄热材料作为二次热源。 以显热或潜热的形式将热量储存在储热材料中，或者采用化学反应。
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