公开(公告)号：US20080173004A1

公开(公告)日：2008-07-24

申请号：US11788458

申请日：2007-04-20

申请人： Kenneth K. Kuo ,  J. Eric Boyer ,  Peter Joseph Ferrara

发明人： Kenneth K. Kuo ,  J. Eric Boyer ,  Peter Joseph Ferrara

IPC分类号： F02G1/00 ,  C06D5/00

CPC分类号： C06D5/10 ,  C06B47/02 ,  F02K9/70

摘要： A bi-propellant rocket motor having controlled thermal management is disclosed. The rocket motor produces thrust using a solid or gel-phase primary propellant that can be either fuel- or oxidizer-rich, with a complementary self-pressurizing secondary propellant selected to balance the primary propellant in terms of the equivalence ratio. The motor houses multiple propellant grains arranged in such a configuration that each chamber containing a primary grain serves as both propellant storage and the main combustion chamber for that propellant grain as it burns with the secondary propellant. The secondary propellant is stored separately, and the flow routed past the primary propellant chamber to provide cooling for adjacent primary propellant chambers limiting the temperature rise in the motor structure.

摘要翻译： 公开了具有受控热管理的双推进剂火箭发动机。 火箭发动机使用可以是燃料或富氧化剂的固体或凝胶相初级推进剂产生推力，其中选择相互补充的自加压次级推进剂以平衡初级推进剂的当量比。 电动机容纳多个推进剂颗粒，其布置成这样的构造，即当包含主颗粒的每个室用作推进剂储存和用于该推进剂颗粒的主燃烧室，其随着二次推进剂燃烧。 二次推进剂分开储存，流动通过主推进剂室，为相邻的主推进剂室提供冷却，限制电机结构的温升。

公开(公告)号：US07921638B2

公开(公告)日：2011-04-12

申请号：US11788458

申请日：2007-04-20

申请人： Kenneth K. Kuo ,  J. Eric Boyer ,  Peter J. Ferrara

发明人： Kenneth K. Kuo ,  J. Eric Boyer ,  Peter J. Ferrara

IPC分类号： F02K9/28 ,  B64G99/00

CPC分类号： C06D5/10 ,  C06B47/02 ,  F02K9/70

摘要： A bi-propellant rocket motor having controlled thermal management is disclosed. The rocket motor produces thrust using a solid or gel-phase primary propellant that can be either fuel- or oxidizer-rich, with a complementary self-pressurizing secondary propellant selected to balance the primary propellant in terms of the equivalence ratio. The motor houses multiple propellant grains arranged in such a configuration that each chamber containing a primary grain serves as both propellant storage and the main combustion chamber for that propellant grain as it burns with the secondary propellant. The secondary propellant is stored separately, and the flow routed past the primary propellant chamber to provide cooling for adjacent primary propellant chambers limiting the temperature rise in the motor structure.

摘要翻译： 公开了具有受控热管理的双推进剂火箭发动机。 火箭发动机使用可以是燃料或富氧化剂的固体或凝胶相初级推进剂产生推力，其中选择相互补充的自加压次级推进剂以平衡初级推进剂的当量比。 电动机容纳多个推进剂颗粒，其布置成这样的构造，即当包含主颗粒的每个室用作推进剂储存和用于该推进剂颗粒的主燃烧室，其随着二次推进剂燃烧。 二次推进剂分开储存，流动通过主推进剂室，为相邻的主推进剂室提供冷却，限制电机结构的温升。