Societe Europeenne De Propulsion

Societe Anonyme:societe Europeenne De Propulsion

Dino Crapiz

Richard Heidmann

Louis Daffix

Sectors of tubes are adhesively fixed around a prefabricated propellant, the sectors being juxtaposed edge to edge to constitute a cylindrical tube, and a winding is formed around the tube at least in circumferential direction. The front and rear walls which are equipped with a seating and a tuyere, can be joined to the tubular structure formed by the tube sectors, by adhesive means on the inside of that structure, or as a variant, by means of a helical winding formed simultaneously on the wall and on the tubular structure.

Method for the production of a combustion chamber for solid propellant

A tubular preform (10), fins (30), and fin supports (20) are made independently, with the fins and the fin supports being made by laying fibrous cloth impregnated with polymerizable binder to take up the appropriate shapes, and then polymerizing the binder, whereas the tubular preform is made by winding a thread impregnated with a polymerizable binder. Each fin support has a base integrated with the periphery of the tubular preform, and has fin attachment portions projecting from its base, with the bases of the fin supports and the periphery of the tubular preform being shaped in such a manner as to ensure circumferential continuity of the structure. The fin supports are integrated with the tubular preform by gluing together with at least one position of localized overwinding at the gaps in the fin supports between the fin attachment portions, thereby providing a perform which is smooth in structure both inside and outside. The assembly constituted by the tubular preform, the fin supports, and the overwinding is polymerized in order to obtain a tube for constituting a rocket, and the fins are subsequently assembled to the fin support by gluing the sides of the fins onto the attachment portion of the fin supports.

Composite rocket motor with integrated composite fins, and method of

Combustion chamber for rocket motor of the type comprising two domes, interconnected by a cylindrical shell, each of said domes and the intermediate shell being produced from a filamentary composite material, in which each dome comprises a slightly conical skirt of which the external face is joined over at least part of its length to the inner face of the shell, via a split cylindro-conical connection ring and at least opposite the conical skirt of the dome, one conical face having the same conicity as the conical skirt, the assembling of the three elements to be connected, i.e. dome, shell and ring, being achieved by adhesive bonding.

Combustion chamber for rocket motor and its assembling method

The simplified homing system comprises an accelerometric device mounted directly on the missile structure and associated with discriminating means for delivering signals representative of the lateral acceleration .gamma..sub.ext of the missle due to outside forces and the centrifugal acceleration .gamma..sub.c due to the rolling; target detection means directly mounted on the missile structure; passive means ensuring the keeping up of the rolling movement of the missile; means for determining from information supplied by the accelerometric device and discriminating means and by target detection means the serviceable values related to the vector V indicating the relative speed of the missile with respect to the air in a reference system related to the missile and to the vector u.sub.c representing the direction of the target with respect to the axis of the missile and means for elaborating a guiding force F.sub.p from the said predetermined serviceable values related to the vectors V and u.sub.c.

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Le Haillan, France

Dino Crapiz