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The last simulation before flight predicted an apogee of 31600', which proved to be very similar to the true performance of the rocket. At 2.5% error, it seems our RAS Aero model is accurate enough to predict future flights of comparable rockets. After the flight all of the data was plotted. The results are shown below. A discussion of the pre-flight vehicle descent velocity mis-estimation is in the recovery section. The University of Victoria payload altimeter cut out during vehicle descent. The cause of this failure is unknown.
Avionics
Payload
See the Hermes I Payload Analysis page
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Future efforts could faster-burning igniters (pyrogen or BKNO3), higher surface area propellants (pixie dust), or additional mechanical retention. While chuffing represents a minor issue on this flight, successful, rapid, and complete ignition is a necessary technical milestone for multistage flight. Care must still be taken to not over-pressurize the case or clog the nozzle with a large igniter.
Recovery
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Recovery
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The Telemetrum was configured as the primary altimeter, and the Raven was configured to fire 2 seconds after the Telemetrum for drogue, and 500 ft lower for the main. This was seen reflected in the post flight data.
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