Avio Corporation

Snecma Propulsion Solide

Paolo Bellomi

Daniele Schiariti

Didier Boury

Bernard Bondon

Philippe Le Helley

Marco Telara

Gilles Uhrig

Roberto Mastronardi

Jean-Claude Tricot

Georgio Mastrangelo

Louis Jacques

Vincenzo Mancini

Christophe Magniére

Daniele Liuzzi

Mikhail Rudnykh

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 &#x3bc;m, density comprised between 0.30 and 0.34 g/cc and resistance to hydrostatic pressure greater than, or equal to, 4500 psi.

Inner coating layer for solid-propellant rocket engines

A solid-propellant rocket engine () has a casing () and a thermal protection () internally coating the casing and delimiting a housing (), which contains a mass of solid propellant (); the thermal protection has a fixed portion () and at least one movable portion () that adheres to the mass of solid propellant () and can be moved from a back position to a forward position with respect to the fixed portion () through a thrust system obtained by pressuring a chamberprovided by installing a membranebetween the fixed portionand the movable portion; the engine is tested by verifying the adhesion of the mass of solid propellant () to the movable portion () after having moved the movable portion () to the forward position by means of a thrust directed from the fixed portion towards the mass of solid propellant ().

Test method for testing a solid-propellant rocket engine, solid-propellant rocket engine and system for implementing the method

A solid propellant rocket motor has a tubular casing accommodating a mass of solid propellant material and at least one opening for the space in the casing to communicate with the outside closed by a closing head; the closing head being coupled to the casing by means of one or the other of two blocking portions with different strength both carried by a movement device which can be elastically deformed and operated from the outside.

Solid propellant rocket motor

The invention provides a system for passively controlling pressure oscillations of hydrodynamic origin in a solid propellant thruster comprising a body containing a charge of solid propellant, the system comprising at least one insert disposed in the thruster body transversely relative to the flow direction of the combustion gases of the solid propellant. The insert has an opening of non-axisymmetric shape so as to generate a three-dimensional effect on the flow and prevent axisymmetric turbulent modes from forming in the thruster. Thus, the control system of the invention serves to break the symmetry of the flow and thus prevents axisymmetric turbulence forming which is the source of instability that the present invention seeks to control. The present system is applicable to existing thrusters.

System and method of controlling pressure oscillations of hydrodynamic origin for a solid propellant thruster

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Rome, Italy

Paolo Bellomi