I have previously proposed high bypass rocket nozzle designs. This one is a more refined version of them. The objective is to contribute the ambient air to thrust. My proposed design looks like a cascade fountain nozzle however extended more towards the rocket’s fuselage. Its perfect design should be iterated between the minimum drag and maximum additional thrust. This design reduces the dimension of the rocket’s main nozzle. The cascaded bypass nozzle also improves the stability of the rocket together with the support fins. The outer bypass nozzle does not need to withstand high temperatures while it would be isolated from the exhaust gas by the air cushion.
This design like all other nozzles would perform best at a specific flight speed range and altitude. Therefore, they would be designed specifically for every rocket or missile depending on their trajectory. High Bypass Nozzle would work wherever there is air such as Earth, Mars and Venus.
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