EP 0081421 B1 19890125 - TERMINAL GUIDANCE METHOD AND GUIDED MISSILE USING IT
Title (en)
TERMINAL GUIDANCE METHOD AND GUIDED MISSILE USING IT
Publication
Application
Priority
FR 8123025 A 19811209
Abstract (en)
[origin: US4568040A] A guidance method is provided for the terminal portion of the trajectory of a guided missile having a sensor and comprising two sections coupled together by a central shaft and free to rotate with respect to one another about the longitudinal axis of the missile; one section comprises a drive means for controlling the roll attitude of this section and a gas generator which feeds a nozzle for providing a transverse throat force and the other section has a stabilizing tail unit formed by a set of fins able to be opened out.
IPC 1-7
IPC 8 full level
F42B 15/01 (2006.01); F41G 7/22 (2006.01); F42C 13/00 (2006.01)
CPC (source: EP US)
F41G 7/222 (2013.01 - EP US); F41G 7/2233 (2013.01 - EP US); F41G 7/2253 (2013.01 - EP US); F41G 7/2293 (2013.01 - EP US); F42B 10/661 (2013.01 - EP US); F42C 13/006 (2013.01 - EP US)
Designated contracting state (EPC)
AT BE CH DE FR GB IT LI LU NL SE
DOCDB simple family (publication)
EP 0081421 A1 19830615; EP 0081421 B1 19890125; AT E40467 T1 19890215; CA 1209232 A 19860805; DE 3279397 D1 19890302; FR 2517818 A1 19830610; FR 2517818 B1 19850222; IL 67424 A 19890331; JP H0449040 B2 19920810; JP S58127100 A 19830728; US 4568040 A 19860204
DOCDB simple family (application)
EP 82402180 A 19821130; AT 82402180 T 19821130; CA 417036 A 19821206; DE 3279397 T 19821130; FR 8123025 A 19811209; IL 6742482 A 19821206; JP 21535782 A 19821208; US 44672882 A 19821203