EP 0886122 B1 20000830 - Solid propellant rocket motor with low vulnerability
Title (en)
Solid propellant rocket motor with low vulnerability
Title (de)
Feststoffraketenmotor mit geringer Empfindlichkeit
Title (fr)
Moteur, à propergol solide, de faible vulnérabilité.
Publication
Application
Priority
FR 9707429 A 19970616
Abstract (en)
[origin: EP0886122A1] The motor consists of a solid propellant charge (11) with a thermal protection layer (2) inside a metal casing (5) with end covers, one of which has an exhaust nozzle. The casing has a number of large apertures (6) set at intervals round it which are temporarily blocked by sealed stoppers (8) held in place between the thermal protection layer and a composite winding of impregnated fibres, e.g. of aramide fibres such as 'Kevlar' (RTM), or carbon fibres, in an epoxy resin. The stoppers, which have outer surfaces of the same curvature as the casing, are released by the accidental degradation of the composite winding. The thermal protection layer is e.g.an elastomer obtained by reticulation of a polybutadiene with a filling of refractory materials (SiO2) in the form of powder and fibres.
IPC 1-7
IPC 8 full level
F42B 39/20 (2006.01)
CPC (source: EP US)
F42B 39/20 (2013.01 - EP US)
Designated contracting state (EPC)
BE CH DE FR GB IT LI SE
DOCDB simple family (publication)
EP 0886122 A1 19981223; EP 0886122 B1 20000830; DE 69800278 D1 20001005; DE 69800278 T2 20010104; FR 2764646 A1 19981218; FR 2764646 B1 19990716; NO 321831 B1 20060710; NO 982751 D0 19980615; NO 982751 L 19981217; US 6148606 A 20001121
DOCDB simple family (application)
EP 98401419 A 19980611; DE 69800278 T 19980611; FR 9707429 A 19970616; NO 982751 A 19980615; US 9661398 A 19980612