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The Hermes II main system is designed for deployment at 2000 ft above the launch site under a range of reasonable masses. It is designed to operate at a temperature of 150 F because it the inside of the rocket could reach that sitting on the pad.
Thoughts:
There are four inputs to the design process. The parachute parameters are derived from past flights and from the scientific literature. The rocket and environmental parameters encompass the estimated mass and the predicted air density. The force correction factor (Cx) is coefficient in the deployment force calculations that is interpreted by the designer from tables in the literature. The design factors encompass the joint efficiencies, abraision losses, etc. and the safety factors. and My intuition tells me that the design is too conservative. I feel this way because I am biased from anchored on the original design and the swivel suggests that the measured force was roughly 50% of the predicted force.
Fix safety factors, then determine Cx. We need to do it in that order so that we are not fi
I feel that the main design is too conservative, but I don't want to be rash and under design. Some issues with the current design are the drogue Cd, temperatures, mass range, safety factors, Cx, abrasion, and UV performance.
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