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9:17 pm December 4, 2009
| Rocket-To-The-Moon
| | Altus, Oklahoma, USA | |
| Member | posts 685 | |
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Post edited 3:39 am – December 5, 2009 by Rocket-To-The-Moon
 
Here is my concept for a hybrid modular booster. The oxidizer is stored in the tank at the top and it is fed to the bottom through a metal pipe. The fuel surrounds the pipe and fills the entire volume of the booster. The idea is that it is lit from the bottom and burns upward. As the fuel burns upward it melts the metal oxidizer pipe (lead or some other low melting point metal) so that the oxidizer is constantly at the top of the combustion chamber.
The bottom of the oxidizer pipe starts 1 meter from the bottom of the combustion chamber and the fuel is shaped to maximize its surface area.
Does this make sense? I could be totally off course on how to actually design the innards; I'll be researching some more.
After reading over this PDF I can see that the idea of melting away the oxidizer pipe might be a bit crazy. A more traditional design will simplify things.
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Main Workgroups: Propulsion & Spacecraft Engineering
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9:39 pm December 4, 2009
| Luke Maurits
| | Adelaide, Australia | |
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What is the motivation for having the fuel burn from bottom to top? I have never seen or read anything about this configuration. That's not to say it is a bad idea, but it seems (slightly) less simple than the more common configuration, and all our steps away from simplicity should be justified by an expected performance gain or price drop.
With regards to the use of a low melting point metal, I would worry about the pipe melting higher than the current line of combusion, which could irregularities or even interruptions in the oxidiser flow. If the pipe melted right through we may even see combusion happening along the length of the melted section.
I am a little nervous about endorsing such an odd design without more knowledge of rocketry.
Also, I am not sure that the use of a pipe would allow the effect that makes paraffin fuels so effective, where fast moving oxidiser whips up a fine spray of liquid fuel which burns faster than the solid fuel. We are not sold on paraffin yet, of course, but I don't think we should commit to a design that rules it out yet either.
I don't mean to be too negative, I am a huge fan of your ongoing SketchUp work, I think it will do a lot to inspire interest in the project, but I don't think we should produce conceptual sketches in this level of detail too far ahead of proper technical planning and actual experience. Certainly I think it is too soon to be deciding on any kind of scale, like the 1 meter distance from the bottom of the pipe to the bottom of the combustion chamber – we don't really have any idea what sorts of values would be optimal for that yet.
If you do want to produce an internal-view sketch of the modular booster now (and for the record I think it would be a good idea to do so), my advice would be to keep it fairly generic and low detail for now – basically just show an oxidiser tank and a fuel grain connected by some quite generic looking thing so people understand the overall concept.
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Main CLLARE workgroups: Mission Planning, Navigation and Guidance. I do maths, physics, C, Python and Java.
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9:41 pm December 4, 2009
| Rocket-To-The-Moon
| | Altus, Oklahoma, USA | |
| Member | posts 685 | |
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I totally agree with everything you said. I kind of jumped the gun on this one. I'll be making a more traditional design ASAP.
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Main Workgroups: Propulsion & Spacecraft Engineering
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9:59 pm December 4, 2009
| Rocket-To-The-Moon
| | Altus, Oklahoma, USA | |
| Member | posts 685 | |
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Here is a more traditional style hybrid rocket. The fuel is denoted by the pink shaded area. I have not included the actual nozzle structure for simplicity.
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Main Workgroups: Propulsion & Spacecraft Engineering
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10:06 pm December 4, 2009
| Luke Maurits
| | Adelaide, Australia | |
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Fantastic, looks good. :)
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Main CLLARE workgroups: Mission Planning, Navigation and Guidance. I do maths, physics, C, Python and Java.
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10:12 pm December 4, 2009
| Rocket-To-The-Moon
| | Altus, Oklahoma, USA | |
| Member | posts 685 | |
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Of course the fuel/oxidizer ratio in the render is meaningless but it gives the general idea.
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Main Workgroups: Propulsion & Spacecraft Engineering
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10:18 pm December 4, 2009
| brmj
| | Rochester, New York, United States | |
| Member | posts 402 | |
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You might want to adjust the over-all geometry somewhat. That looks like it might be to little oxydizer, proportionally, (based on spaceship one's engine, for example.). Also, single port grain configurations tend to require relatively long and thin rockets, while multiport designs introduce complexity and inefficiency. Otherwise, it looks great.
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Main work groups: Propulsion (booster), Spacecraft Engineering, Computer Systems, Navigation and Guidance (software)
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11:12 pm December 4, 2009
| brmj
| | Rochester, New York, United States | |
| Member | posts 402 | |
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Rocket-To-The-Moon said:Of course the fuel/oxidizer ratio in the render is meaningless but it gives the general idea.
Either you just edited that post, that was a large coincidence or causality was violated.
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Main work groups: Propulsion (booster), Spacecraft Engineering, Computer Systems, Navigation and Guidance (software)
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11:12 pm December 4, 2009
| brmj
| | Rochester, New York, United States | |
| Member | posts 402 | |
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Post edited 5:13 am – December 5, 2009 by brmj
Accidental double post. Pay this no mind.
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Main work groups: Propulsion (booster), Spacecraft Engineering, Computer Systems, Navigation and Guidance (software)
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11:21 pm December 4, 2009
| Rocket-To-The-Moon
| | Altus, Oklahoma, USA | |
| Member | posts 685 | |
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Post edited 5:22 am – December 5, 2009 by Rocket-To-The-Moon
brmj said:
Rocket-To-The-Moon said:Of course the fuel/oxidizer ratio in the render is meaningless but it gives the general idea.
Either you just edited that post, that was a large coincidence or causality was violated.
I guess that I must have edited it as you were typing your response.
Actually, upon closer inspection it doesn't say that it was edited.
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Main Workgroups: Propulsion & Spacecraft Engineering
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