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51. 发明专利

JPS622145B2 失效
公开(公告)号：JPS622145B2
公开(公告)日：1987-01-17
申请号：JP7663079
申请日：1979-06-18
申请人： NISSAN MOTOR
发明人： ONOSHIMA NOBORU
IPC分类号： F02K9/18

52. 发明专利

JPS59128955A Rocket engine 失效
标题翻译： ROCKET发动机
公开(公告)号：JPS59128955A
公开(公告)日：1984-07-25
申请号：JP188583
申请日：1983-01-10
申请人： Daicel Chem Ind Ltd
发明人： WATANABE TADAHIKO
IPC分类号： F02K9/10 , F02K9/18 , F02K9/26
CPC分类号： F02K9/26
摘要： PURPOSE:To obtain optimum thrust force X time, by arranging in the axial direction a combustion control member, which is installed partially in the circumferential direction of grains loaded in a rocket chamber and which has a portion closed toward the periphery. CONSTITUTION:A combustion control member 3, which is installed in the circumferential direction of grains 1 loaded in a rocket chamber 4 and which has a portion closed toward the periphery, is arranged in the axial direction. Thereby the web according to the inner-surface combustion system will become a one having substantially a diameter 2-3 times as large as the grains' 1, to cause substantial increase of the combustion progressive web. The combustion pattern thus obtained will transfer from the combustion initial face 1a to the combustion progressive face A one after another, wherein a comparatively large thrust force is obtained in the initial stage, while a comparatively small, approx. constant and stable thrust force is obtained continuously after passage of a certain period of time. This provides effectiveness for launching an aeronautical body in vertical position to a high altitude, as well as the reach can be stretched even in launching aslant.
摘要翻译：目的：为了获得最佳推力X时间，通过沿轴向布置燃烧控制构件，该燃烧控制构件部分地安装在装载在火箭室中的颗粒的圆周方向上，并且具有朝向周边封闭的部分。构成：安装在装载在火箭室4中并且具有朝向周边封闭的部分的颗粒1的圆周方向上的燃烧控制构件3沿轴向布置。因此，根据内表面燃烧系统的纤维网将变成具有基本上直径为颗粒1的2-3倍直径的纤维网，从而引起燃烧进行幅材的显着增加。这样获得的燃烧模式将从燃烧初始面1a一个接一个地转移到燃烧渐进面A，其中在初始阶段获得相当大的推力，而相对较小的约经过一段时间后，连续获得恒定和稳定的推力。这提供了在高空垂直位置发射航空器的有效性，并且即使在发射时也可以伸展。

53. 发明专利

JPS562447A INTERNAL COMBUSTION TYPE PROPELLANT GRAIN 失效
公开(公告)号：JPS562447A
公开(公告)日：1981-01-12
申请号：JP7663079
申请日：1979-06-18
申请人： NISSAN MOTOR
发明人： ONOSHIMA NOBORU
IPC分类号： F02K9/18
摘要： PURPOSE:To prevent a concentration of stress from being generated in the connection part of inner holes, by connecting the inner holes with different cross sectional shaped from each other through an annular groove with a diameter equal to or larger than a maximum diameter of said inner hole. CONSTITUTION:In a propellant grain 1 of internal combustion type, the first inner hole 2 extensibly located in the direction of axial line is formed at one side of its interior. Said inner hole 2 consists of an inner hole part 2a and a pair of grooved parts 2b which are linked to said part 2a and separated 180 deg. from each other. While in the grain 1 the second inner hole 3 extensibly located in the direction of axial line is formed at its another side. Said inner hole 3 consists of an inner hole part 3a and a plurality of sector parts 3b which are linked to said part 3a and placed a prescribed angle apart from each other. In a connection part of these inner holes 2, 3 an annular groove 4 is formed, and its inside diameter (d) is made larger than a maximum diameter D of the inner holes 2, 3. In this way, a thermal stress acted upon the connection part of the both inner holes 2, 3 can be dispersed by the annular groove 4.

54. 实用新型

JPS4120487Y1 失效
公开(公告)号：JPS4120487Y1
公开(公告)日：1966-10-04
申请号：JP4560166
申请日：1966-05-18
IPC分类号： F02K9/18 , F02K9/04

55. 发明申请

WO2013001267A1 A BOMB FOR DEPLOYMENT FROM AN AIR VEHICLE 审中-公开
标题翻译：用于从空中车辆部署的物料清单
公开(公告)号：WO2013001267A1
公开(公告)日：2013-01-03
申请号：PCT/GB2012/000552
申请日：2012-06-28
申请人： MBDA UK LIMITED , IRVINE, Rodney, Andrew
发明人： IRVINE, Rodney, Andrew
IPC分类号： F02K9/18 , F02K9/22 , F42B15/10
CPC分类号： F02K9/10 , F02K9/12 , F02K9/18 , F02K9/22 , F02K9/95 , F42B10/38 , F42B15/10
摘要： A bomb for deployment from an air vehicle includes a rocket motor (1) for propelling the bomb. The rocket motor includes propellant (5) which at least partially defines a void (11) downstream of an initial burning surface. As the propellant (5) is burned the void 11 will be exposed, increasing the surface area of the burning surface (9) of the propellant (5) to increase the thrust of the rocket motor.
摘要翻译：用于从空中飞行器部署的炸弹包括用于推进炸弹的火箭发动机（1）。火箭发动机包括推进剂（5），其至少部分地限定初始燃烧表面下游的空隙（11）。随着推进剂（5）燃烧，空气11将被暴露，增加推进剂（5）的燃烧表面（9）的表面积以增加火箭发动机的推力。

56. 发明申请

WO2009134510A2 ROCKET MOTOR WITH PELLET AND BULK SOLID PROPELLANTS 审中-公开
标题翻译：带泡沫和块状固体推进剂的ROCKET电机
公开(公告)号：WO2009134510A2
公开(公告)日：2009-11-05
申请号：PCT/US2009/033694
申请日：2009-02-10
申请人： RAYTHEON COMPANY , CAVALLERI, Robert , OLDEN, Thomas
发明人： CAVALLERI, Robert , OLDEN, Thomas
IPC分类号： F02K9/10 , F02K9/12 , F02K9/18
CPC分类号： F02K9/08 , F02K9/10 , F02K9/24 , F02K9/346
摘要： There is disclosed a solid fuel rocket motor which may include a case and a nozzle coupled to the case. A plurality of fuel pellets may be disposed within the case. An igniter may be disposed to ignite at least a portion of the fuel pellets. A pellet retainer may be positioned within the case to retain the plurality of fuel pellets within the case. The pellet retainer may be perforated to allow exhaust gases to flow from the ignited fuel pellets to the nozzle while preventing unburned fuel pellets from being expelled through the nozzle.
摘要翻译：公开了一种固体燃料火箭发动机，其可以包括壳体和连接到壳体的喷嘴。多个燃料丸可以设置在壳体内。可以设置点火器以点燃至少一部分燃料颗粒。颗粒保持器可以定位在壳体内以将多个燃料颗粒保持在壳体内。颗粒保持器可以被穿孔以允许废气从点燃的燃料颗粒流到喷嘴，同时防止未燃烧的燃料颗粒通过喷嘴排出。

57. 发明申请

WO2021108001A1 AUGMENTED AEROSPIKE NOZZLE, ENGINE INCLUDING THE AUGMENTED AEROSPIKE NOZZLE, AND VEHICLE INCLUDING THE ENGINE 审中-公开
公开(公告)号：WO2021108001A1
公开(公告)日：2021-06-03
申请号：PCT/US2020/048178
申请日：2020-08-27
申请人： STOKE SPACE TECHNOLOGIES, INC.
发明人： LAPSA, Andrew , FELDMAN, Thomas
IPC分类号： F02C7/04 , F02K9/82 , F02K9/18 , F02K9/12 , F02K1/30
摘要： An augmented aerospike nozzle includes a throat, a centerbody extending aft of the throat, an inner expansion surface defined by the centerbody, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface. An engine includes a high pressure chamber and the augmented aerospike nozzle. A vehicle for supersonic flight includes the engine with the augmented aerospike nozzle.

58. 发明申请

WO2013019898A1 SYSTEMS AND METHODS FOR CASTING HYBRID ROCKET MOTOR FUEL GRAINS 审中-公开
标题翻译：混合式电动机燃料颗粒的系统和方法
公开(公告)号：WO2013019898A1
公开(公告)日：2013-02-07
申请号：PCT/US2012/049218
申请日：2012-08-01
申请人： THE AEROSPACE CORPORATION , FULLER, James, K.
发明人： FULLER, James, K.
IPC分类号： F02K9/18 , F02K9/32 , B29C33/52 , B64G1/40 , B29C67/00 , B29C39/26
CPC分类号： F02K9/18 , B21D53/00 , B29C33/3857 , B29C33/52 , B29C39/006 , B29C39/26 , B29C64/106 , B29C67/0055 , B29L2031/3097 , B33Y50/00 , B64G1/403 , B64G1/404 , C06B21/005 , C06B21/0058 , C06B45/00 , F02K9/14 , F02K9/32 , F02K9/36 , F02K9/72 , F05D2230/21
摘要： Embodiments of the invention relate to systems and methods for casting hybrid rocket motor fuel grains. In one embodiment, a method for casting a rocket motor fuel grain can be provided. The method can include providing a positive image of a port made from at least one material. The method can further include disposing at least one fuel material around at least a portion of the positive image of the port. Further, the method can include removing the at least one material, wherein a negative image of the port is formed in the at least one fuel material.
摘要翻译：本发明的实施例涉及用于铸造混合火箭发动机燃料颗粒的系统和方法。在一个实施例中，可以提供用于铸造火箭发动机燃料颗粒的方法。该方法可以包括提供由至少一种材料制成的端口的正像。该方法还可以包括在端口的正像的至少一部分周围设置至少一种燃料材料。此外，该方法可以包括去除至少一种材料，其中端口的负像形成在至少一种燃料材料中。

59. 发明申请

WO2013019876A3 SYSTEMS AND METHODS FOR FABRICATING HYBRID ROCKET MOTOR FUEL GRAINS 审中-公开
公开(公告)号：WO2013019876A3
公开(公告)日：2013-02-07
申请号：PCT/US2012/049185
申请日：2012-08-01
申请人： THE AEROSPACE CORPORATION , FULLER, James, K.
发明人： FULLER, James, K.
IPC分类号： C06B21/00 , C06B45/00 , F02K9/18 , F02K9/24 , B29C67/00
摘要： Embodiments of the invention relate to systems and methods for fabricating hybrid rocket motor fuel grains. In one embodiment, a method for fabricating a rocket motor fuel grain can be provided. The method can include providing a platform operable to support a rocket motor fuel grain during fabrication. The method can also include disposing at least one fuel material onto the platform to form a material layer. Further, the method can include successively disposing additional fuel material onto the material layer in small amounts, wherein the rocket motor fuel grain is formed on the platform.

60. 发明授权

US10883448B2 Solid rocket motor with vortex inducing feature 有权
公开(公告)号：US10883448B2
公开(公告)日：2021-01-05
申请号：US15571270
申请日：2016-07-26
申请人： Aerojet Rocketdyne, Inc.
发明人： Samuel Steven Schlueter
IPC分类号： F02K9/18 , F02K9/34 , F02K9/08 , F02K9/16 , F02K9/10 , B64G1/40 , F02K9/24
摘要： A solid rocket motor includes a propellant grain structure defining an axial bore and a vortex inducing feature.

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