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Questions tagged [rocketry]

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What are the advantages of an asymmetrical missile nose cone?

Some rocket- and missile designs sport an asymmetrically conical nose cone. A prime example being the Stunner missile in "David's Sling" surface-to-air system. Several sources (such as ...
Elmore's user avatar
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How to minimize temperature increase caused by compression of a cryogenic liquid in a multistage high pressure turbopump?

The cryogenic fuel I'm using is methane at 100 K and 300,000 Pa. Based on my calculations, after compression, the pressure is 55 MPa and using the ideal gas equation the temperature is approx. 800 K. ...
Matt01's user avatar
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In orbit rocket launch

If fuel is sent into space in bulk using space station as a "Fuel Depot", then how fast and efficient could in orbit launches of objects like probes, etc be? Rockets use huge amounts of fuel ...
LazyReader's user avatar
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How to design a pressure regulator test?

We're designing a pressure regulator test. It is taking an input from an N2 tank at 300 bars, output pressure should be around 70 bars. We are thinking of using 2 pressure transducers, a solenoid to ...
cookingoil2000's user avatar
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What is the optimal weight ratio for a multistage water rocket?

I do know about the Tsiolkovsky rocket equation for optimising multistage rockets, however the equation requires a fixed exhaust velocity which is something that water rockets don't have, so for this ...
notanengineer's user avatar
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F-1 rocket engine - gas generator data

I’m doing some research on Rocketdyne F-1 engine of Saturn V. In particular I am searching geometric data of the gas generator that feeds the turbo pump. Has someone found this kind of data? It seems ...
daniele__'s user avatar
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How to use a high current 2 Second current pulse to actuate a servo - First year Electrical Engineer

I am using a dual deployment system controller, an Eggtimer Quark REVC2 which at apogee outputs a high current 2 second pulse. I don't have time to buy a more advanced Eggtimer which outputs proper ...
Engineerin.com's user avatar
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Flow through an Annular Orifice for Pintle Injector

Our rocket team is trying to finalize the design of our injector for a small liquid rocket engine. The current analysis challenge is verifying the correct pressure drop across the annular orifice ...
WhisperingShiba's user avatar
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Isp Output of NASA CEA

I have 2 questions related to NASA CEA's Isp values in the output file. When looking through the output of NASA's CEA tool, I am trying to understand the difference between its "Ivac" output and its "...
Unique Worldline's user avatar
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1 answer
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What's the minimum area ratio required to achieve choking in Converging nozzle?

Is there any equation for minimum area ratio (Throat area (At)/ Combustion Chamber area (Ac) ) required for choked flow in convergent nozzle (just like equations for minimum Pressure ratio and ...
SRD's user avatar
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Method of Characteristics nozzle - outputs area ratio?

I am designing a rocket engine as my final project at college, and I tried using a MatLab code developed by youtuber JoshTheEngineer. However, after running the code, it seems that the output points ...
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Is it possible to protect electronics on a cubesat from 100-1000g of acceleration

I am currently researching the feasibility of setting up a coilgun that launches Cubesats for a paper.
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What factors besides nozzle geometry and propellant's affect engine ISP? How can one optimize ISP?

In the design of a Rocket engines, it is understandably desirable to have a more efficient engine. Ensuring the gasses coming out of the engine comes out straight, and the chemistry of the ...
WhisperingShiba's user avatar