EP 0838656 B1 20020213 - Guided missile with ram jet engine
Title (en)
Guided missile with ram jet engine
Title (de)
Lenkflugkörper mit Staustrahlantrieb
Title (fr)
Missile guidé à statoréacteur
Publication
Application
Priority
DE 19635847 A 19960904
Abstract (en)
[origin: EP0838656A2] The propulsion mechanism extends over most or all the cross-section of the missile interior, and has two air inlets in the bottom part connected by tail-pipes (8,9) to the rear end. At the latter are four radial and pivoting guidance rudders (11-14). The shafts of the two bottom rudders extend inside the tail-pipes. Rigid rudders are mounted on the missile, extending from the middle to the front part. Each rudder has a linear adjusting-drive unit. In each tail-pipe are two of the adjusting-drive units, offset in the lengthwise and peripheral directions, and working in the lengthwise direction. Each rudder has a linkage coupling point (A1) clear of its pivot axis (R1,R2). For each of the two bottom rudder the coupling between drive unit and coupling point is by a rod with hinge- or ball-joints at both ends. In the case of the top rudders, the coupling is achieved by a double-armed lever (26) hinging on an axis (S) and a rod with a ball-joint at both ends.
IPC 1-7
IPC 8 full level
F42B 10/64 (2006.01)
CPC (source: EP US)
F42B 10/64 (2013.01 - EP US)
Designated contracting state (EPC)
DE FR GB IT SE
DOCDB simple family (publication)
DE 19635847 A1 19980312; DE 19635847 C2 19980716; DE 59706370 D1 20020321; EP 0838656 A2 19980429; EP 0838656 A3 20000119; EP 0838656 B1 20020213; US 5904319 A 19990518
DOCDB simple family (application)
DE 19635847 A 19960904; DE 59706370 T 19970814; EP 97114018 A 19970814; US 91998297 A 19970828