Disclosed is a space cold gas thruster operating with a solid propellant. The cold gas thruster includes a tank suitable for containing a solid propellant and a tank heating device suitable for sublimating the solid propellant and forming gaseous propellant, the tank having an aperture for transferring the gaseous propellant outside the tank, such as a nozzle. Also disclosed is a process for determining the amount of remaining propellant in the propellant tank of the disclosed cold gas thruster.

The present invention relates to resin compositions, fiber reinforced polymeric structures and electromagnetic induction processes for making same. Such magnetic induction processes are pulsed processes that can be optionally coupled with cooling steps between pulses. The aforementioned fiber reinforced polymeric structures can take forms that include, but are not limited to, pipes; pressure vessels, including rocket motor cases and fire extinguishers; golf club shafts; tennis and badminton racquets; skis; snowboards; hockey sticks; fishing rods; bicycle frames; boat masts; oars; paddles; baseball bats; and softball bats. In addition, such fiber reinforced polymeric structures can be supplemented with other materials, such as a rocket propellant, to form articles, for example, a rocket motor.

A polymer composite composition for use in high temperature applications such as furnaces, heat shields and aeronautical jet and rocket motors. In a particular application, the disclosed composition is applied to the manufacture of rocket motor cases, or parts thereof, to provide rigid thermal protection (RTP). The polymer composite composition comprises cyanate ester resin, fine lengths of carbon fibre and refractory filler material.

A polymer composite composition for use in high temperature applications such as furnaces, heat shields and aeronautical jet and rocket motors. In a particular application, the disclosed composition is applied to the manufacture of rocket motor cases, or parts thereof, to provide rigid thermal protection (RTP). The polymer composite composition comprises cyanate ester resin, fine lengths of carbon fibre and refractory filler material.

A power generation system includes a manifold having multiple plenums, capable of receiving multiple solid rocket motors. Initiators are coupled to the manifold, and are operatively coupled to respective of the plenums, to selectively fire different groups of the rocket motors coupled to respective of the plenums. The rocket motors act in parallel, to provide thrust in a single direction. The initiators may activate ignition charges that are in the plenums. The plenums may be annular plenums, which may be located in an annular manifold. The plenums may be lined with an insulator material. A cover may be used to cover the plenums, and also to receive the rocket motors. The rocket motors may be solid-fuel rocket motors, with propellant grains and nozzles. The individual rocket motors may have separate ignition booster charges coupled to the plenum, which are ignited by the ignition charge.

An inner coating layer for solid-propellant rocket engines, constituted by a material comprising from 45% to 55% wt. of a a cross-linkable, unsaturated-chain polymer base, from 11% to 13% wt. of silica, from 15% to 25% wt. of vulcanizing agents and plasticizers, from 5% to 7% wt. of aramid fiber and from 10% to 15% wt. of microspheres made of a material selected among glass, quartz and nano clay, having diameter lower than 200 μm, density comprised between 0.30 and 0.34 g/cc and resistance to hydrostatic pressure greater than, or equal to, 4500 psi.

A preceramic resin formulation comprising a polycarbosilane preceramic polymer and an organically modified silicon dioxide preceramic polymer. A ceramic material comprising a reaction product of the polycarbosilane preceramic polymer and organically modified silicon dioxide preceramic polymer is also described. Articles comprising the ceramic material are also described, as are methods of forming the preceramic resin formulation and the ceramic material.

A barrier coating resin formulation comprising at least one polycarbosilane preceramic polymer, at least one organically modified silicon dioxide preceramic polymer, at least one filler, and at least one solvent. A barrier coating comprising a reaction product of the at least one polycarbosilane preceramic polymer and the at least one organically modified silicon dioxide preceramic polymer and the at least one filler is also disclosed, as are articles comprising the barrier coating, rocket motors comprising the barrier coating, and methods of forming the articles.

The invention relates to a method for assembling a first metal part with a second part made of an organic matrix composite material, the first part having a first connecting portion and the second part having a second connecting portion, the method comprising the steps of: causing the first connecting portion and the second connecting portion to overlap, a through-hole of the second connecting portion opening onto the first connecting portion, forming a protective layer on the side wall of the through-hole, forming a seal between the protective layer and the first connecting portion, and forming, by additive manufacturing using cold gas spray deposition of metal powder, a fastening element which extends into the through-hole, is fastened to the first connecting portion and encloses the second connecting portion.

An apparatus and method for protecting an inner radial surface of a radial member of a turbomachine from corrosion are provided. The method may include shaping the inner radial surface of the radial member and a corresponding outer radial surface of a corrosion-resistant liner. The method may also include heating the radial member to increase a diameter of the inner radial surface of the radial member, and inserting at least a portion of the corrosion-resistant liner into the radial member. The method may further include attaching the corrosion-resistant liner to the inner radial surface of the radial member to thereby protect the inner radial surface of the radial member of the turbomachine from corrosion.