In the framework of the combustion stability assessment program for the Ariane 5 P230 Solid Rocket Motor (SRM), experimental studies have been performed at SNPE and ONERA. The unsteady characterization of two solid propellants used during the course of these experimental studies has been realized in the frequency range between 20 and 800 Hz. For the low frequency range (below 200 Hz), the direct microwave measurement technique developed by ONERA has been used. Between 300 and 600 Hz, the ONERA modulated exhaust jet motor has been used. Tests with the SNPE T-burner have been performed between 300 and 800 Hz. The Results obtained with the Ariane 5 metallized solid propellant and a basic non-metallized solid propellant are presented. All methods give results in reasonably good agreement. The non-metallized propellant has been found to present an almost linear real part of the pressure-coupled response function in the 0-800 Hz frequency range, while the Ariane 5 propellant presents an unusual maximum around 200-300 Hz.
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