Rocket nozzle design thesis

The book implied that a solid core engine could be devloped up to a specific impulse of 1000 seconds, with a max of 12,000 seconds (but at max you'll be spewing molten reactor bits in your exhaust). A later design in the book had a specific impulse of 1000 seconds and a ΔV capability of 15,000 m/s (which implies a mass ratio of about , which is a bit over the rule-of-thumb maximum of ) . Please note that the dimensions below were originally in feet and pounds in the book, that's why they are such odd numbers (., meters is 5 feet) .

You'll need a launching mechanism. I simply used a zip-tie launching mechanism mounted on a 1/2" pvc pipe and embedded a tire valve on the other end with a lot of epoxy. It took me about 3 hours to make once I had a design that included stabilizing the whole rig. If you have a multi stage rocket, you defiantly want a full bore nozzle for your booster, which the zip-tie method allows for. Otherwise a garden hose quick release valve system would be a lot easier to make.

From there you just attach a bike pump and with a little elbow grease, you've got yourself 100+psi.

Performance
We put each of the vacuums through a series of rigorous tests to assess how they would do with debris types you may encounter in your home. Our tests included Fruity Cheerios, a sand-and-sawdust mixture (to mimic fine particulate debris), pet hair, and human hair, collected from a hair extension kit. We performed every test three times each on three different surface types: low-pile carpet, mid-pile carpet, and hardwood/laminate floors. We also conducted a torture test, scattering ounces of bobby pins and small nuts on the low-pile carpet.

The effect of the combustion of propellant in the rocket engine is to increase the velocity of the resulting gases to very high speeds, hence producing a thrust. [ citation needed ] [ dubious – discuss ] Initially, the gases of combustion are sent in every direction, but only those that produce a net thrust have any effect. [ citation needed ] [ dubious – discuss ] The ideal direction of motion of the exhaust is in the direction so as to cause thrust. At the top end of the combustion chamber the hot, energetic gas fluid cannot move forward, and so, it pushes upward against the top of the rocket engine's combustion chamber . As the combustion gases approach the exit of the combustion chamber, they increase in speed. The effect of the convergent part of the rocket engine nozzle on the high pressure fluid of combustion gases, is to cause the gases to accelerate to high speed. The higher the speed of the gases, the lower the pressure of the gas ( Bernoulli's principle or conservation of energy ) acting on that part of the combustion chamber. In a properly designed engine, the flow will reach Mach 1 at the throat of the nozzle. At which point the speed of the flow increases. Beyond the throat of the nozzle, a bell shaped expansion part of the engine allows the gases that are expanding to push against that part of the rocket engine. Thus, the bell part of the nozzle gives additional thrust. Simply expressed, for every action there is an equal and opposite reaction, according to Newton's third law with the result that the exiting gases produce the reaction of a force on the rocket causing it to accelerate the rocket. [35] [nb 2]

Rocket nozzle design thesis

rocket nozzle design thesis

The effect of the combustion of propellant in the rocket engine is to increase the velocity of the resulting gases to very high speeds, hence producing a thrust. [ citation needed ] [ dubious – discuss ] Initially, the gases of combustion are sent in every direction, but only those that produce a net thrust have any effect. [ citation needed ] [ dubious – discuss ] The ideal direction of motion of the exhaust is in the direction so as to cause thrust. At the top end of the combustion chamber the hot, energetic gas fluid cannot move forward, and so, it pushes upward against the top of the rocket engine's combustion chamber . As the combustion gases approach the exit of the combustion chamber, they increase in speed. The effect of the convergent part of the rocket engine nozzle on the high pressure fluid of combustion gases, is to cause the gases to accelerate to high speed. The higher the speed of the gases, the lower the pressure of the gas ( Bernoulli's principle or conservation of energy ) acting on that part of the combustion chamber. In a properly designed engine, the flow will reach Mach 1 at the throat of the nozzle. At which point the speed of the flow increases. Beyond the throat of the nozzle, a bell shaped expansion part of the engine allows the gases that are expanding to push against that part of the rocket engine. Thus, the bell part of the nozzle gives additional thrust. Simply expressed, for every action there is an equal and opposite reaction, according to Newton's third law with the result that the exiting gases produce the reaction of a force on the rocket causing it to accelerate the rocket. [35] [nb 2]

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