公开(公告)号：US06616092B1

公开(公告)日：2003-09-09

申请号：US10178428

申请日：2002-06-24

申请人： Kenneth H. Barnes ,  William M. Butler ,  Paul E. Hagseth

发明人： Kenneth H. Barnes ,  William M. Butler ,  Paul E. Hagseth

IPC分类号： B64C3702

CPC分类号： B64G1/40 ,  B64D5/00 ,  B64G1/14

摘要： According to one embodiment of the invention, a rocket booster for launching a payload into space includes a fuselage adapted to support one or more fuel tanks inside the fuselage and a booster engine coupled to an aft portion of the fuselage. The booster engine is operable to provide thrust during an ascent phase of operation of the rocket booster. The rocket booster further includes a nacelle coupled to a forward portion of the fuselage and a flyback engine disposed within and coupled to the nacelle. The flyback engine is operable to provide thrust during a flyback phase of operation of the rocket booster. The rocket booster also includes one or more control surfaces coupled to the fuselage that are operable to control a flight pattern of the rocket booster during the flyback phase of operation. The flyback engine of the rocket booster is located forward of an aerodynamic center of the rocket booster.

摘要翻译： 根据本发明的一个实施例，用于将有效负载发射到空间中的火箭助推器包括适于支撑机身内的一个或多个燃料箱的机身和联接到机身的后部的增压发动机。 增压发动机可操作以在火箭助推器的上升运行阶段提供推力。 火箭助推器还包括联接到机身的前部的机舱和设置在机舱内并联接到机舱的反激式发动机。 反激式发动机可操作以在火箭助推器的回扫阶段期间提供推力。 火箭助推器还包括耦合到机身的一个或多个控制表面，其可操作以在操作的回扫阶段期间控制火箭助推器的飞行模式。 火箭助推器的反激发动机位于火箭助推器的空气动力学中心的前方。

公开(公告)号：USD312604S

公开(公告)日：1990-12-04

申请号：US17798

申请日：1987-02-24

申请人： Kenneth H. Barnes ,  Alexander M. Zrolka, Sr.

设计人： Kenneth H. Barnes ,  Alexander M. Zrolka, Sr.