| 摘要 |
FIELD: rocket engineering. SUBSTANCE: engine comprises housing 1 with thermal-protective coating 2 and solid-propellant charge 3. The housing consists of shell 4 secured to nozzle cover 5 provided with ring seal 7. The nozzle cover is provided with additional groove 8 made in front of the ring seal from the side of the charge. The thermal- protective coating consists of two parts. Part 9 is tubular, has flange and connected with shell 4. The other part is made up as disk 11 and is secured to nozzle cover 5. The wall of the flange is interposed between the planes which pass through the end faces of disk 11 to form a ring space filled with a sealing composition. The outer diameter of the disk is 0.85-0.97 of the outer diameter of the cover in zone 6 wherein it is secured to shell 4. An embodiment of the engine is provided with a spacer made of, e.g. cartoon, secured to end face 12 of disk 11, and overlaps ring space 16 between the flange and disk 11. EFFECT: enhanced reliability. 1 dwg |
