Vortex driven pressure oscillations in the Titan IV solid rocket motor upgrade

Author:

Dotson K,Koshigoe S,Pace K

Publisher

American Institute of Aeronautics and Astronautics

Reference17 articles.

1. b. The frequency tracks for stage numbers m=5 and m=7-12 are generally in good agreement with the results of Equation 2. The slopes of the frequency tracks for stagenumbers m=7-12, however, are smaller than those of the empirical model. Thisdiscrepancy is addressed in Section 7.

2. Fig. 7 Strouhal numbersforstage numberm=6 assumingshear layer initiation at forward or aft cavity face. Impingement st nozzlethroat. Timecorrespondstonominalpmpellsnt burn rate. Largest pressure oscillations occur in the time period 159-65 seconds.

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2. POD-X Program: towards the SRM Pressure Oscillation Demonstrator first firing test;49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference;2013-07-12

3. Large Eddy Simulation for Low Frequency Oscillations in Tail-Pipe Nozzle Solid Rocket Motors;46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit;2010-07-25

4. Full 3-D Simulation of Turbulent Flow in the RSRM;42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit;2006-07-09

5. Thrust Oscillations in Reduced Scale Solid Rocket Motors Part I : Experimental Investigations;41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit;2005-07-10

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