The National Space Development Agency of Japan (NASDA) conducted the first static firing test of the H-2 Launch Vehicle solid rocket booster (SRB) on April 15, 1988 at the static firing test facility for solid motors in the Tanegashima Space Center using a full-size SRB. The firing test was intended to verify the basic firing characteristics of the solid motor and the heat resistance of the nozzle, to obtain data of the dynamic characteristics of the movable nozzle and to measure the environmental conditions (acoustics, vibration, heat, etc.) during motor firing. The SRB was set horizontally and was ignited. The SRB was fired normally for approx. 93 seconds, during which time an operational test to drive the movable nozzle to its maximum rudder angle of 5 degrees was performed. Roughly 290 pieces of data were obtained, such as thrust, motor internal pressure, distortion and heat radiation. The test was successful in that motor firing performance almost reached the forecasted values. The movable nozzle was operated smoothly during firing and the thrust vector control (TVC) system functions presented no problems. The nozzle errosion value was less than the design value, indicating that the design value has a sufficient error margin.
Static Firing Test of the H-2 Launch Vehicle Solid Rocket Booster
1988
23 pages
Report
No indication
English
Space Launch Vehicles & Support Equipment , Rocket Engines & Motors , Booster rocket engines , Heavy lift launch vehicles , Solid propellant rocket engines , Static firing , Japanese space program , Rocket engine design , Nozzle efficiency , Rocket firing , Thermal resistance , Thrust vector control , Vibration tests , Foreign technology
Solid Rocket Booster Water Impact Test
NTIS | 1982
|Solid rocket booster water impact test
NTRS | 1982
|