公开(公告)号：US4796839A

公开(公告)日：1989-01-10

申请号：US001804

申请日：1987-01-08

申请人： Hubert P. Davis

发明人： Hubert P. Davis

IPC分类号： B64G1/00 ,  B64G1/14 ,  B64G1/40 ,  B64G1/62

CPC分类号： B64G1/14 ,  B64G1/002 ,  B64G1/402 ,  B64G1/62

摘要： A rocket launch vehicle comprising a rocket body having a forward section and an aft section, a first rocket engine fixedly mounted to the aft section of the rocket body and axially aligned with the rocket body, a second rocket engine detachably mounted to the aft section of the rocket body and aligned axially parallel with the first rocket engine, a third rocket engine detachably mounted to the aft section of the rocket body and aligned axially parallel with the first rocket engine and being on the side of the first rocket engine opposite the second rocket engine, a first recovery structure fastened to the second rocket engine, a second recovery structure attached to the third rocket engine, and a plurality of propellant supply tanks connected to the first, second, and third rocket engines. Each of the rocket engines is a Space Shuttle main engine. The propellant tanks are detachably mounted to the exterior of the rocket body. Fuel tanks are affixed to the interior of the aft section of the rocket body and communicate with the first rocket engine. The recovery structure includes a parachute deployment arrangement for selective deployment of a parachute within a reentry vehicle fixedly attached to each of the second and third rocket engines. The forward section of the rocket body is a modified Titan 4 payload fairing.

摘要翻译： 一种火箭运载火箭，包括具有前部和后部的火箭主体，第一火箭发动机固定地安装在火箭主体的后部并与火箭主体轴向对准，第二火箭发动机可拆卸地安装到 火箭主体并且与第一火箭发动机轴向平行地对准，第三火箭发动机可拆卸地安装到火箭主体的后部并且与第一火箭发动机轴向平行且与第二火箭相对的第一火箭发动机的一侧 发动机，紧固到第二火箭发动机的第一回收结构，附接到第三火箭发动机的第二回收结构以及连接到第一，第二和第三火箭发动机的多个推进剂供应罐。 每个火箭发动机都是航天飞机主机。 推进剂罐可拆卸地安装在火箭体的外部。 燃料箱固定在火箭主体后部的内部并与第一火箭发动机连通。 恢复结构包括用于在固定地连接到第二和第三火箭发动机中的每一个的再入式车辆中选择性地部署降落伞的降落伞部署装置。 火箭身体的前部是修改的Titan 4有效载荷整流罩。