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Ejection Query

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New Member
Apr 9, 2021
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I am designing the recovery system of a rocket with a 10,000ft apogee and I have a question about the ejection and splitting of a rocket halfway down the rocket as opposed to the nose cone.

We are planning to use a CO2 ejection system to pressurise the recovery bay from the engine block to the centring ring around the main chute (rough diagram; the shaded area is what will be pressurised). Shear pins will be used to hold the rocket together at the separation point and these will be sized according to the ejection force from the CO2 canisters. To calculate this force, I have completed an ideal gas law equation for CO2 and have used the resultant pressure to calculate the force exerted on the engine block at the end of the recovery bay. Would this be a correct assumption to make? We will be carrying out ground testing for the ejection system to confirm the system works. Furthermore, would the whole ejection system actually work in this way?
The main chute will be attached to the drogue chute by a shock cord and attached to the bulkhead at the bottom of the recovery bay with a tether consisting of an e-match that will be ignited at a specified altitude.

I would appreciate if you could help me figure out if it would be possible to split the rocket in half this way and if not, what would be a better way of splitting the rocket in this way.

Many thanks in advance! :)