Magnetic flowmeter burner measurement of a solid propellant pressure coupled imaginary response was investigated. The direct measurement of the acoustic velocity as a function of height above the burning propellant surface were combined with an acoustic analysis to determine the most accurate measurement of the pressure-coupled response of the propellant. A value of 10.0 was the maximum real part of the response measured over 97 tests spread among six different propellant formulations over a pressure range from 2.0 to 7.0 MPa. Am examination of the acoustic analysis that is combined with the measured amplitude ratios and phases shows that the real part of the pressure influences the phase angle between the velocity and pressure oscillations much more than it influences the amplitude ratio.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Fuel Technology
- Mechanical Engineering
- Space and Planetary Science