Abstract
In the mission of the Advanced Solid Rocket studied in JAXA, the launch‐pad is required to improve the operation performance as well as to reduce the cost. While, exhaust plume from the solid booster generates severe acoutic wave so that decrease in the acoustic level at lift‐off is also an important design issue. Preliminary trade‐off analysis is peformend by using computational fluid dynamics. Major noise sources such as the Mach wave and the impingement noise and their correlation with the vehicle’s altitude are revealed. The knowledge of the acoustic characteristics gives us idea how to decrease the acoustic level within the mission requirements. Based on the configuration found in the numerical study, subscale test using 1/43 scale mock‐up is planned to ensure the acoustic level around the vehicle.
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