MANUFACTURE OF COMBUSTION CHAMBER FOR SOLID PROPELLANT ROCKET ENGINE

摘要

PURPOSE: To facilitate the assembly of a combustion chamber which withstands internal pressure by adhesively fixing the sectorial parts of a tube which are juxtaposed edge to edge around a propellant and constitute the cylindrical tube and forming a winding part in at least circumferential direction around this tube. CONSTITUTION: The tubular structure of the combustion chamber is made of the tube 20 longitudinally divided to the sectorial parts 22, 24 in a longitudinal direction. The sectorial parts 22 and 24 are fixed to the circumference of the propellant 10 by the adhesives. The diameter of the tube 20 fits to the diameter of the propellant 10 in order to reconstitute the tubular structure by assembling the sectorial parts edge to edge. The winding is formed on the resulted tubular structure. The winding 28 consists of spiral windings of an extremely small pitch, plural layers of which are superimposed to a required thickness. The tubular structure farms a skirt part 26 which extends beyond the front wall 16 and rear wall 14 of the combustion chamber and may be connected to another element.