Accession Number:

ADA071811

Title:

A Shock Tube Investigation of Silo-Launched Vehicle Aerodynamic Flow Asymmetries.

Descriptive Note:

Interim rept.,

Corporate Author:

AEROSPACE CORP EL SEGUNDO CA AEROPHYSICS LAB

Report Date:

1979-07-05

Pagination or Media Count:

59.0

Abstract:

A shock tube was used to simulate the initial transient flow from a rocket launching silo when the rocket motor was ignited. The object was to investigate the relationship between lateral loads observed on the missile being launched during the early transient flow and the silo exit geometry. A centerbody simulating the missile to be launched was installed in the shock tube and instrumented with pressure gages to detect the lateral loads. Three silo exit geometries were also modeled. The early transient flow in the silo is described along with the modeling of this flow by the shock tube. Finally, the pressures measured on the missile model are presented together with a correlation technique that was developed to display the effect of the silo exit geometries on the model pressure difference force. Also included are results from the application of this correlation technique to full-scale flight data, which appear to demonstrate a close relationship between on-board accelerometer measurments and the pressure difference force history. Author

Subject Categories:

  • Test Facilities, Equipment and Methods
  • Guided Missile Launching and Basing Support

Distribution Statement:

APPROVED FOR PUBLIC RELEASE