EP 0275766 B1 19900829 - BRAKE MECHANISM FOR A DEPLOYABLE WING AND GUIDED MISSILE THEREWITH
Title (en)
BRAKE MECHANISM FOR A DEPLOYABLE WING AND GUIDED MISSILE THEREWITH
Publication
Application
Priority
FR 8618084 A 19861223
Abstract (en)
[origin: US4852828A] The device of the invention provides for the substantially constant unfolding of unfoldable fins on a guided missile without damaging the bearing structure or the fin itself. The device comprises a deformation part placed around a bearing neck that is joined to the fin. Means are used to convert the rotational kinetic energy due to the unfolding of the fin into translational energy. These means comprise, in particular, a compression ring which is displaced and compresses the deformation part in conjunction with the rotation of the bearing neck due to the unfolding of the fin. The invention can be used in missiles, self-propelled rockets and similar devices.
IPC 1-7
IPC 8 full level
F42B 10/14 (2006.01)
CPC (source: EP US)
F42B 10/14 (2013.01 - EP US)
Designated contracting state (EPC)
CH DE GB IT LI SE
DOCDB simple family (publication)
FR 2608750 A1 19880624; FR 2608750 B1 19930226; DE 3764633 D1 19901004; EP 0275766 A1 19880727; EP 0275766 B1 19900829; US 4852828 A 19890801
DOCDB simple family (application)
FR 8618084 A 19861223; DE 3764633 T 19871218; EP 87402911 A 19871218; US 13526987 A 19871221