公开(公告)号：US5572865A

公开(公告)日：1996-11-12

申请号：US299782

申请日：1994-09-01

Applicant: Robert L. Sackheim ,  Dale L. Hook ,  Gary W. Joseph

Inventor： Robert L. Sackheim ,  Dale L. Hook ,  Gary W. Joseph

IPC: B64G1/40 ,  B64G1/00 ,  B64G1/24 ,  B64G1/26 ,  F02K9/42 ,  F02K9/44 ,  F02K9/50 ,  F02K9/52 ,  F02K9/54 ,  F02K9/58 ,  F02K9/64 ,  F02K9/68

CPC classification number: F02K9/42 ,  B64G1/401 ,  B64G1/402 ,  B64G1/406 ,  F02K9/50 ,  F02K9/52 ,  F02K9/54 ,  F02K9/58 ,  F02K9/64 ,  F02K9/68 ,  B64G1/007 ,  B64G1/242 ,  B64G1/26

Abstract: In the preferred embodiment of the invention, a cooled bipropellant thruster 70 for controlling the on-orbit position and orientation of a spacecraft is provided. The cooled bipropellant thruster 70 uses a liquid fuel and liquid oxidizer. The liquid fuel is decomposed in a first chamber 72 with a catalytic bed of decomposition material 74 and produces at least one reaction gas, which flows to the second reaction chamber 90. The second reaction chamber 90 is heated by the reaction gas, but is cooled by liquid oxidizer flowing through cooling passages 92, 94, 98, and 102, which brings the oxidizer into a heat exchange relationship with the second reaction chamber 90. During the heat exchange relationship, heat is transferred from the second reaction chamber 90 to the oxidizer and the oxidizer transforms into a gas. The gaseous oxidizer is fed into a second reaction chamber 90 to secondarily react with the reaction gas.

公开(公告)号：US5417049A

公开(公告)日：1995-05-23

申请号：US748990

申请日：1991-08-21

Applicant: Robert L. Sackheim ,  Dale L. Hook ,  Gary W. Joseph

Inventor： Robert L. Sackheim ,  Dale L. Hook ,  Gary W. Joseph

IPC: B64G1/40 ,  B64G1/00 ,  B64G1/24 ,  B64G1/26 ,  F02K9/42 ,  F02K9/44 ,  F02K9/50 ,  F02K9/52 ,  F02K9/54 ,  F02K9/58 ,  F02K9/64 ,  F02K9/68 ,  F02K9/28

CPC classification number: F02K9/42 ,  B64G1/401 ,  B64G1/402 ,  B64G1/406 ,  F02K9/50 ,  F02K9/52 ,  F02K9/54 ,  F02K9/58 ,  F02K9/64 ,  F02K9/68 ,  B64G1/007 ,  B64G1/242 ,  B64G1/26

Abstract: In the preferred embodiment of the invention, a cooled bipropellant thruster 70 for controlling the on-orbit position and orientation of a spacecraft is provided. The cooled bipropellant thruster 70 uses a liquid fuel and liquid oxidizer. The liquid fuel is decomposed in a first chamber 72 with a catalytic bed of decomposition material 74 and produces at least one reaction gas, which flows to the second reaction chamber 90. The second reaction chamber 90 is heated by the reaction gas, but is cooled by liquid oxidizer flowing through cooling passages 92, 94, 98, and 102, which brings the oxidizer into a heat exchange relationship with the second reaction chamber 90. During the heat exchange relationship, heat is transferred from the second reaction chamber 90 to the oxidizer and the oxidizer transforms into a gas. The gaseous oxidizer is fed into a second reaction chamber 90 to secondarily react with the reaction gas.

Abstract translation: 在本发明的优选实施例中，提供了用于控制航天器的在轨位置和取向的冷却双组元推进器推进器70。 冷却的双组元推进剂推进器70使用液体燃料和液体氧化剂。 液体燃料在分解材料74的催化床的第一室72中分解，并产生至少一个流到第二反应室90的反应气体。第二反应室90被反应气体加热，但被冷却 通过液体氧化剂流过冷却通道92,94,98和102，其使氧化剂与第二反应室90成热交换关系。在热交换关系期间，热量从第二反应室90转移到氧化剂 氧化剂转化为气体。 将气态氧化剂进料到第二反应室90中以与反应气体二次反应。