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Description of electronics used in Anthony Colette's  6" Subsonic Ramjet project

Back to progress report

Picture of components in the Subsonic Ramjet

Application of a liner Solid Booster For ramjet

Test of  a solid booster

Thrust and case pressure results for above test

I have been working with Jeroen (of AED electronics) on the data
acquisition system. The +- 50g accelerometer and altimeter are standard sensors on the RDAS

1) The +- 50g accelerometer will provide the acceleration and boost velocity provided by the solid booster rocket.

2) The altimeter will provide the local ambient pressure.
An add on board will contain:

3) The supplemental +- 5g accelerometer will be used to measure
acceleration &
velocity of the ramjet after booster rocket separation.

4) Diffuser dynamic pressure will be measured by a Motorola MPX mini
pressure
sensor.

5) Diffuser static pressure will be measured by a Motorola MPX mini
pressure
sensor.

6) Diffuser total temperature will be measured by way of a fast response
K-type
thermocouple.

7) Fuel tank pressure (thus fuel mass flow rate) will be measured by way
of an
MSI 0-1000 psia pressure transducer.

8) Combustion chamber static pressure will be measured by a Motorola MPX
mini
pressure sensor.

Because the ramjet geometry is known, these 8 channels of data will
provide a great deal of information for analysis. The combination of two or three different data types will allow calculation of unmeasured performance
parameters such as local mach number, inlet pressure recovery, inlet air mass flow rate, F/A ratio, combustion efficiency, net thrust, gross thrust, Isp, drag, drag coefficient, thrust coefficient, ambient temperature, combustion temperature, etc., etc.

Anthony Colette

rokitman@sprintmail.com