The patent relates to a method whereby a plurality of perforated tubes are placed longitudinally between the insulator layer and silicone rubber layer of a stress relieving rocket motor liner to insure proper pressure distribution within the motor during burn.
Rocket Motor Apparatus
1974
5 pages
Report
No indication
English
Rocket-motor spin-test apparatus
NTRS | 1964
|Rocket-Motor Spin-Test Apparatus
NTIS | 1965
|