EP 0238724 B1 19910515 - MISSILE
Title (en)
MISSILE
Publication
Application
Priority
DE 3546269 A 19851228
Abstract (en)
[origin: US4712748A] The missile (10) comprises at its rear end in flying direction (A) tail fins (14, 16, 18) whose front edges (14F, 16F, 18F) are sharpened at both sides. Intermediate the tail fins, outflow openings (22) are arranged on the body (12) to eject therethrough fuel into the supersonic external flow forming about the body (12). Due to supersonic flow, there are generated shock wave fronts extending from the front edges (14F, 16F, 18F) and being reflected by adjacent tail fins, said shock waves of the shock wave fronts interfering with the supersonic flow passing along the body so that recirculation fields are formed between the tail fins. The said recirculation fields are formed within the range of corner flow and outlfow openings (22) so that fuel discharged from the latter is burnt down with the formation of a locally stable flame. As a result of the volume increase resulting from the combustion, a high-pressure area develops between the tail fins. The pressure produces a force directed transversely to the flying direction and causing a control of the missile (10).
IPC 1-7
IPC 8 full level
F42B 10/66 (2006.01)
IPC 8 main group level
F42B (2006.01)
CPC (source: EP US)
F42B 10/668 (2013.01 - EP US)
Designated contracting state (EPC)
FR GB SE
DOCDB simple family (publication)
US 4712748 A 19871215; DE 3546269 C1 19870813; EP 0238724 A1 19870930; EP 0238724 B1 19910515; IL 81005 A0 19870331
DOCDB simple family (application)
US 94052086 A 19861210; DE 3546269 A 19851228; EP 86117113 A 19861209; IL 8100586 A 19861217