Title:
【発明の名称】持続推進装置
Document Type and Number:
Japanese Patent JP2818288
Kind Code:
B2
Abstract:
The high cost of fabrication of a turbojet propulsion system 12 for a missile having an engine 18, mounted within a casing 14, including an inlet 20 to a compressor 22 and an exhaust gas outlet 24 is avoided in a structure having a propulsion system 12 with an inlet 26, 28; 37 located forward of the engine 18 for directing free stream air to the inlet 20 of the compressor 22, an outlet 30, 33; 38, 40 located aft of the engine 18 for directing exhaust gas into the free stream air, an engine starter 42 aft of the engine outlet 24, and a fuel storing bladder 46 forward of the engine 18.
Inventors:
Jones, Anthony Sea
Webber, Henry A
Webber, Henry A
Application Number:
JP50117390A
Publication Date:
October 30, 1998
Filing Date:
September 29, 1989
Export Citation:
Assignee:
Sandstrand Corporation
International Classes:
F02K3/10; F02C7/04; F02C7/22; F02K1/40; F02K1/78; F02K7/18; F02K9/97; (IPC1-7): F02K9/97; F02K1/40; F02K7/18
Domestic Patent References:
| JPS62186925A | ||||
| JPS62140627A | ||||
| JPS62140629A | ||||
| JPS62140628A |
Other References:
【文献】米国特許4096803(US,A)
Attorney, Agent or Firm:
Mitsuteru Soga (4 outside)