Nozzle Design & C/C Composite Based Nozzle

[bilencekic]

Hi,

I have a grad project about carbon carbon composite (thermal barrier coatig on it) based rocket nozzle.

Well,

First, i need a rocket design and simulation program, do you know any of them ?

It must give me, the exhaust flow directions, turbulances, heat affected zones, temperature changes and program let me to design nozzle :=).

I am interested on aerospike nozzle design, what do you think about it ? I heard that it has many advantages on low atmosphere pressures.

Edited November 25, 2009 by bilencekic

[Eric70]

Hello bilencekic and welcome,

Based on your questions I think you are in the wrong forum This is a pyrotechnic forum where members discuss a craft primarily based on decades and centuries old techniques. Pyrotechnic rockets are a precursor to missiles and aerospace rockets, but most of us pyros are on a different boat than you.

 

Try some of these sites:

 

Amateur Rocketry Forum:

http://moncom.net/moncomrocketry.asp

 

Amateur Icelandic Rocketry:

http://www.eldflaug.com/forum/

 

UKRocketman.com

http://www.ukrocketman.com/rocketry/index.shtml

 

 

 

 

Hi,

I have a grad project about carbon carbon composite (thermal barrier coatig on it) based rocket nozzle.

Well,

First, i need a rocket design and simulation program, do you know any of them ?

It must give me, the exhaust flow directions, turbulances, heat affected zones, temperature changes and program let me to design nozzle :=).

I am interested on aerospike nozzle design, what do you think about it ? I heard that it has many advantages on low atmosphere pressures.

[bilencekic]

thx for your answer :=)

i was making , bp rockets 4-5 years ago :=) now working on serious ones

i wanted to try my chance that anyone know about this subject

i think i will try matlab :=) but it is not enough

http://www.mathworks.com/matlabcentral/fil...d-nozzle-design

 

 

thx

[mike_au]

IIRC, solidworks has an engineering component that can do fluid flow modeling with pressure and temperature data, but I don't know if it would be able to deal with something that actually creates heat by burning (as opposed to heat build up from friction). Also it is extremely expensive, but I assume the uni would pay for it (or possibly already have it) anyway.

[Yafmot]

Subscribe to NASA Tech Briefs. They've got ads for all kinds of multiphysics software. They've also got points of contact for every research center they run, plus JPL. Most of the engineers & scientists are tickled to talk all day about stuff they're working on. Especially scientists. They can get downright desperate to find real world applications for their work. That's what keeps the funding coming in. NASA also loans & rents software. Some of the codes can't be had anywhere else. Some can't be had period (classified or proprietary).

 

Another is Desktop Engineering, which does comparisons of various types of engineering software, as well as workstations and peripheral goodies. Plus they've got various online goodies.

 

Both of these publications are free.

 

I have an accquaintance at the Air Force Research Lab who has done some pioneering work in aerospikes, including two dimensional/steerable ones, and some other external combustion work. I haven't spoken with him in quite some time (25 yrs?), but I stumble across his papers once in a while. I should be able to track him down.

 

Carbon/Carbon? You've come to the right place. I've been working with that stuff for decades, including rocket motor nozzles & thrust chambers. I've got some slabs of it laying around my garage. As far as thermal barriers go, stay away from metals. Most refractory metals, such as Rhenium, have a CTE similar to steel. C/C has, as a practical matter, none. A company I worked for was developing lightweight, hypergolic apogee kicks for the Air Force, and these gold plated geniuses didn't want to heed my warnings. I attended the tests, and won some bets on that one. We were testing subscale, and I'd bet that the thing wouldn't make it past 30 seconds burn time. (This was burning MMH & NTO.) At 23 seconds, it failed at the nozzle throat.

 

What you need is an ultra high temperature ceramic. We got the Air Force to bite the bullet and eat the added expense of a Hafnium Carbide coating. Done right, I think it will fulfill your requirements.

 

By the way, what kind of fiber are you using? Oxidized PAN? Pitch? And what precursor matrix? Phenolic? And what kind of densification? Hydrostatic pitch infusion, Furfuryl Alcohol, or just the old methane-based CVI?

 

One more thing. You want to REALLY impress the Gods-who-Give-the-Grades? Do this without a damned computer. Come up with a reliable & efficient high performance nozzle without having everything shown to you on a screen. If you can't get a vision in your head, you're in the wrong business.

 

Send me a PM and we'll continue this conversation.

[bilencekic]

hi

thx for message.

i sent you PM and E-mail.

i wsih you receive it.

 

simply,

we are using yttra stabilized ZrO2 for thermal barrier coating. I looked the phase diagram and it is ok on 2500-2700 degree celcius.

It does what we need.

But in other way, we have an option like

ZrBr2 - SiC composite material which stays stable on 3000 degree celcius.

Those ceramic barriers will protect our carbon/carbon from oxidizing and temperature.

But c/c composite is a hard material and low impact strentgh, it is fragile, we have to make it more stable against impacts.

Now i need some nozzle geometry .

The rocket engine with bell-shaped nozzle has been brought to its full development up to

now and it is difficult to essentially improve its performance to a great extent. Compared with conventional

rocketengine, aerospike nozzle engine characterized by small scale, lightweight, highperformance during all

altitudes and better utilization.

So i need some properties of ideal spike nozzle.

i read about 15 articles from science direct but i need more information.

 

we are planning to use pitch for carbon fibers.

Edited December 5, 2009 by bilencekic