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1. 发明授权

US07383104B2 Low-noise flight support system 有权
标题翻译：低噪音飞行支援系统
公开(公告)号：US07383104B2
公开(公告)日：2008-06-03
申请号：US11196397
申请日：2005-08-04
申请人： Hirokazu Ishii , Kohei Funabiki , Yoshinori Okuno , Hiromi Gomi
发明人： Hirokazu Ishii , Kohei Funabiki , Yoshinori Okuno , Hiromi Gomi
IPC分类号： G06F7/00 , G06F17/00
CPC分类号： G01C21/32 , G01C23/00
摘要： It is an object of the present invention to provide a system that is used to provide support so that a pilot can perform flight operations that reduce noise pollution, by devising this system so that noise conditions on the ground are calculated and displayed on the basis of map information for the flight area in which facilities and the like are described, environmental conditions in the flight area such as the wind direction and wind velocity, or the temperature and density of the atmosphere, and noise generation data for the aircraft itself. The apparatus for supporting low-noise flight according to the present invention comprises means for estimating the noise generated by an aircraft using flight data such as the flight speed, the climb and descent rates, the engine power and the like of the aircraft, means for calculating the level at which the noise generated by the aircraft is propagated in the respective regions on the ground, and means for displaying the calculation results on a map in quantitative terms.
摘要翻译：本发明的目的是提供一种用于提供支撑的系统，使得飞行员可以通过设计该系统来执行降低噪声污染的飞行操作，从而基于地面上的噪声条件被计算和显示描述设施等的飞行区域的地图信息，飞行区域中的风向和风速的环境条件，大气的温度和密度，以及飞机本身的噪声产生数据。根据本发明的用于支持低噪声飞行的装置包括用于使用诸如飞行速度，爬升和下降速率，飞机功率等飞行数据来估计飞行器产生的噪声的装置，计算飞机产生的噪声在地面上相应区域中传播的水平，以及用于在地图上以数量显示计算结果的装置。

2. 发明授权

US4508680A Method of manufacturing a rocket combustion chamber 失效
标题翻译：制造火箭燃烧室的方法
公开(公告)号：US4508680A
公开(公告)日：1985-04-02
申请号：US500018
申请日：1983-06-01
申请人： Masayuki Niino , Nobuyuki Yatsuyanagi , Akinaga Kumakawa , Akio Suzuki , Hiromi Gomi , Hiroshi Sakamoto , Masaki Sasaki , Yoshimichi Masuda , Ryuzo Watanabe , Junjiro Takekawa , Etsuo Ohtsuki , Terashi Isago
发明人： Masayuki Niino , Nobuyuki Yatsuyanagi , Akinaga Kumakawa , Akio Suzuki , Hiromi Gomi , Hiroshi Sakamoto , Masaki Sasaki , Yoshimichi Masuda , Ryuzo Watanabe , Junjiro Takekawa , Etsuo Ohtsuki , Terashi Isago
IPC分类号： B22F5/00 , B22F5/10 , B22F5/12 , B22F7/08 , F02K9/64 , B22F7/00
CPC分类号： B22F7/08 , B22F5/10 , F02K9/64
摘要： The present invention is directed particularly to an improved method usingowder metallurgy for the manufacture of the grooved cooling wall of a liquid-propellant rocket combustion chamber. The surface of an inner cylinder constituting the cooling wall is formed with cooling grooves, and these grooves are densely filled up with a filler such as paraffin wax. Thereafter, metal powder which will provide an outer cylinder is compression-molded to a predetermined thickness around the inner cylinder. This metal powder is the same material as the material of the inner cylinder. After the paraffin wax which is the filler is evaporated and removed, the compression-molded metal powder body is sintered in a furnace. During this sintering heat treatment, the inner and outer cylinders are rigidly joined together by the sintering reaction between the atoms of the inner cylinder and the atoms of the metal powder.
摘要翻译：本发明特别涉及使用粉末冶金用于制造液体推进剂火箭燃烧室的带槽冷却壁的改进方法。构成冷却壁的内筒的表面形成有冷却槽，并且这些槽被诸如石蜡的填料密集地填充。此后，将提供外筒的金属粉末在内筒周围压缩成预定厚度。该金属粉末与内筒材料相同。在将作为填料的石蜡蒸发除去之后，将压缩成型的金属粉末体在炉中烧结。在该烧结热处理中，通过内筒的原子和金属粉末的原子之间的烧结反应将内筒和外筒刚性接合在一起。

3. 发明申请

US20060111818A1 Low-noise flight support system 有权
标题翻译：低噪音飞行支援系统
公开(公告)号：US20060111818A1
公开(公告)日：2006-05-25
申请号：US11196397
申请日：2005-08-04
申请人： Hirokazu Ishii , Kohei Funabiki , Yoshinori Okuno , Hiromi Gomi
发明人： Hirokazu Ishii , Kohei Funabiki , Yoshinori Okuno , Hiromi Gomi
IPC分类号： G01C23/00
CPC分类号： G01C21/32 , G01C23/00
摘要： It is an object of the present invention to provide a system that is used to provide support so that a pilot can perform flight operations that reduce noise pollution, by devising this system so that noise conditions on the ground are calculated and displayed on the basis of map information for the flight area in which facilities and the like are described, environmental conditions in the flight area such as the wind direction and wind velocity, or the temperature and density of the atmosphere, and noise generation data for the aircraft itself. The apparatus for supporting low-noise flight according to the present invention comprises means for estimating the noise generated by an aircraft using flight data such as the flight speed, the climb and descent rates, the engine power and the like of the aircraft, means for calculating the level at which the noise generated by the aircraft is propagated in the respective regions on the ground, and means for displaying the calculation results on a map in quantitative terms.
摘要翻译：本发明的目的是提供一种用于提供支撑的系统，使得飞行员可以通过设计该系统来执行降低噪声污染的飞行操作，从而基于地面上的噪声条件被计算和显示描述设施等的飞行区域的地图信息，飞行区域中的风向和风速的环境条件，大气的温度和密度，以及飞机本身的噪声产生数据。根据本发明的用于支持低噪声飞行的装置包括用于使用诸如飞行速度，爬升和下降速率，飞机功率等飞行数据来估计飞行器产生的噪声的装置，计算飞机产生的噪声在地面上相应区域中传播的水平，以及用于在地图上以数量显示计算结果的装置。

4. 发明授权

US4703620A Rocket combustion chamber cooling wall of composite cooling type and method of manufacturing the same 失效
标题翻译：火箭燃烧室冷却墙复合冷却型及制造方法相同
公开(公告)号：US4703620A
公开(公告)日：1987-11-03
申请号：US18790
申请日：1987-02-24
申请人： Masayuki Niino , Nobuyuki Yatsuyanagi , Akiraga Kumakawa , Akio Suzuki , Hiromi Gomi , Hiroshi Sakamoto , Masaki Sasaki , Yoshimichi Masuda , Ryuzo Watanabe , Junjiro Takekawa , Etsuo Ohtsuki , Terashi Isago
发明人： Masayuki Niino , Nobuyuki Yatsuyanagi , Akiraga Kumakawa , Akio Suzuki , Hiromi Gomi , Hiroshi Sakamoto , Masaki Sasaki , Yoshimichi Masuda , Ryuzo Watanabe , Junjiro Takekawa , Etsuo Ohtsuki , Terashi Isago
IPC分类号： B22F7/06 , F02K9/64 , F02K9/97 , F02K9/40 , F02K9/42
CPC分类号： B22F7/06 , F02K9/64 , F05D2260/203 , Y10S60/909
摘要： In the cooling wall of a regenerative cooling rocket combustion chamber, the throat portion thereof in which the heat load is highest is formed of a porous material having a perspiring cooling action. The other portion in which the heat load is relatively low is designed to be cooled by conventional forced convection. By such a composite cooling system, a high cooling effect is provided and yet the pressure loss in the cooling passages is small and light weight and long life of the engine are attained concurrently.
摘要翻译：在再生冷却火箭燃烧室的冷却壁中，热负荷最高的喉部由具有出汗冷却作用的多孔材料形成。热负荷相对较低的其他部分被设计为通过常规的强制对流来冷却。通过这种复合冷却系统，提供了高冷却效果，而冷却通道中的压力损失小，同时实现了发动机重量轻，使用寿命长。

5. 发明授权

US4584171A Method of producing rocket combustors 失效
标题翻译：生产火箭燃烧器的方法
公开(公告)号：US4584171A
公开(公告)日：1986-04-22
申请号：US653012
申请日：1984-09-21
申请人： Masayuki Niino , Nobuyuki Yatsuyanagi , Akinaga Kumakawa , Akio Suzuki , Masaki Sasaki , Hiromi Gomi , Hiroshi Sakamoto , Yoshimichi Masuda , Ryuzo Watanabe , Junjiro Takekawa , Yoshihiko Doi , Nobuhito Kuroishi , Yoshinobu Takeda , Shigeki Ochi
发明人： Masayuki Niino , Nobuyuki Yatsuyanagi , Akinaga Kumakawa , Akio Suzuki , Masaki Sasaki , Hiromi Gomi , Hiroshi Sakamoto , Yoshimichi Masuda , Ryuzo Watanabe , Junjiro Takekawa , Yoshihiko Doi , Nobuhito Kuroishi , Yoshinobu Takeda , Shigeki Ochi
IPC分类号： B22F7/08 , B22F5/00 , B22F5/10 , B22F7/06 , F02K9/62 , F02K9/64 , B22F7/00
CPC分类号： B22F7/06 , F02K9/64 , Y10T29/49346 , Y10T29/4981
摘要： A method of producing rocket combustors wherein in forming an outer cylin by a powder metallurgical method on the outer side of a cylinder provided on its outer periphery with a cooling wall of channel construction having a plurality of grooves, a low-melting alloy is used as a filler to be filled into the grooves. It is also possible to form the outer cylinder after forming a Cu plating shell on the periphery of the inner cylinder filled with the low-melting alloy.
摘要翻译：一种制造火箭燃烧器的方法，其中在通过粉末冶金方法在其外周设置的圆筒的外侧上形成具有多个槽的通道结构的冷却壁的外筒，使用低熔点合金作为要填充到槽中的填料。也可以在填充有低熔点合金的内圆筒的周边形成Cu电镀外壳之后形成外筒。

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