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1. 发明授权

US08397486B2 Two-pulse rocket motor 有权
标题翻译：双脉冲火箭发动机
公开(公告)号：US08397486B2
公开(公告)日：2013-03-19
申请号：US12599874
申请日：2008-05-09
申请人： Chiyako Mihara , Katsunori Ieki
发明人： Chiyako Mihara , Katsunori Ieki
IPC分类号： F02K9/12
CPC分类号： F02K9/08 , F02K9/12 , F02K9/28 , F02K9/95
摘要： In the two-pulse rocket motor in accordance with the present invention, the second propellant is set outside of the first propellant in a motor case, and the inner surface of the first propellant is exposed throughout the almost entire length in the axial direction of the motor case. Therefore, the initial burning area can be secured without deteriorating the performance. Also, by providing a weak part by bonding the barrier membranes or shaping slits on the barrier membrane, the breaking portion of barrier membrane and the behavior of barrier membrane after breakage can be controlled. Further, by setting an igniter charge having higher ignitability and a higher burning rate than the second propellant between the inner surface of the second propellant and the inner barrier membrane, the detachment of barrier membrane and the ignition of the second propellant can be assisted.
摘要翻译：在根据本发明的双脉冲火箭发动机中，第二推进剂设置在电动机壳体中的第一推进剂的外部，并且第一推进剂的内表面在整个长度方向上沿着电机箱。因此，可以确保初始燃烧区域而不会降低性能。此外，通过在屏障膜上粘合阻隔膜或成形狭缝来提供弱的部分，可以控制阻隔膜的断裂部分和断裂后的阻隔膜的行为。此外，通过在第二推进剂的内表面和内阻挡膜之间设置具有比第二推进剂更高的点火性和更高燃烧速率的点火器电荷，可以辅助阻隔膜的分离和第二推进剂的点燃。

2. 发明授权

US09702320B2 Multi-pulse rocket motor and pulse unit thereof 有权
公开(公告)号：US09702320B2
公开(公告)日：2017-07-11
申请号：US13491725
申请日：2012-06-08
申请人： Chiyako Mihara , Tasuku Suzuki , Katsunori Ieki
发明人： Chiyako Mihara , Tasuku Suzuki , Katsunori Ieki
IPC分类号： F02K9/10 , F02K9/28 , F02K9/34
CPC分类号： F02K9/10 , F02K9/28 , F02K9/34
摘要： A pulse unit of a multi-pulse rocket motor has: a propellant in an internal-burning type shape or an internal-end-burning type shape that is loaded within a motor case; an igniter arranged at an end surface of the propellant; a barrier membrane arranged to cover a whole of an initial burning surface of the propellant and the igniter; a forward joint arranged at a forward end of the motor case; and a rearward joint arranged at a rearward end of the motor case. The forward joint is formed so as to be connectable with the rearward joint of another pulse unit. The rearward joint is formed so as to be connectable with the forward joint of yet another pulse unit.

3. 发明授权

US09261048B2 Combustion gas supply control device 有权
标题翻译：燃烧气体供应控制装置
公开(公告)号：US09261048B2
公开(公告)日：2016-02-16
申请号：US13546253
申请日：2012-07-11
申请人： Tasuku Suzuki , Chiyako Mihara , Katsunori Ieki
发明人： Tasuku Suzuki , Chiyako Mihara , Katsunori Ieki
IPC分类号： B63H11/00 , F02K9/28 , F02K9/12 , F02K9/38
CPC分类号： F02K9/28 , F02K9/12 , F02K9/38
摘要： A combustion gas generator has: a motor case; a first propellant loaded within the motor case to burn at a first pulse; a second propellant loaded within the motor case to burn at a second pulse subsequent to the first pulse; a front motor head fixed to a front portion of the motor case and having a combustion gas exhaust hole; and a rear motor head fixed to a rear portion of the motor case and having a combustion gas exhaust hole. A combustion gas supply control device prevents combustion gas of the first propellant at the first pulse from flowing into the combustion gas exhaust hole of the front motor head and supplies combustion gas of the second propellant at the second pulse to the combustion gas exhaust hole of the front motor head.
摘要翻译：燃烧气体发生器具有：电动机壳体; 装载在电动机壳体内的第一推进剂以第一脉冲燃烧; 负载在所述电动机壳体内的第二推进剂在所述第一脉冲之后的第二脉冲处燃烧; 固定在马达壳体的前部并具有燃烧气体排出孔的前部马达头部; 以及固定在马达壳体的后部并具有燃烧气体排出孔的后部马达头部。燃烧气体供给控制装置防止第一脉冲中的第一推进剂的燃烧气体流入前部电动机头的燃烧气体排出孔，并将第二推进剂的燃烧气体以第二脉冲供给到燃料气体排出孔前电机头。

4. 发明申请

US20100218481A1 TWO-PULSE ROCKET MOTOR 有权
标题翻译：双脉冲电机
公开(公告)号：US20100218481A1
公开(公告)日：2010-09-02
申请号：US12599874
申请日：2008-05-09
申请人： Chiyako Mihara , Katsunori Ieki
发明人： Chiyako Mihara , Katsunori Ieki
IPC分类号： F02K5/02
CPC分类号： F02K9/08 , F02K9/12 , F02K9/28 , F02K9/95
摘要： In the two-pulse rocket motor in accordance with the present invention, the second propellant is set outside of the first propellant in a motor case, and the inner surface of the first propellant is exposed throughout the almost entire length in the axial direction of the motor case. Therefore, the initial burning area can be secured without deteriorating the performance. Also, by providing a weak part by bonding the barrier membranes or shaping slits on the barrier membrane, the breaking portion of barrier membrane and the behavior of barrier membrane after breakage can be controlled. Further, by setting an igniter charge having higher ignitability and a higher burning rate than the second propellant between the inner surface of the second propellant and the inner barrier membrane, the detachment of barrier membrane and the ignition of the second propellant can be assisted.
摘要翻译：在根据本发明的双脉冲火箭发动机中，第二推进剂设置在电动机壳体中的第一推进剂的外部，并且第一推进剂的内表面在整个长度方向上沿着电机箱。因此，可以确保初始燃烧区域而不会降低性能。此外，通过在屏障膜上粘合阻隔膜或成形狭缝来提供弱的部分，可以控制阻隔膜的断裂部分和断裂后的阻隔膜的行为。此外，通过在第二推进剂的内表面和内阻挡膜之间设置具有比第二推进剂更高的点火性和更高燃烧速率的点火器电荷，可以辅助阻隔膜的分离和第二推进剂的点燃。

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