Rocket Engine Design with MATLAB and SolidWorks - Method of Characteristics Nozzle Tutorial!
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- Опубликовано: 20 авг 2024
- NOTE: Please watch the 2023 updated video:
• Create a Rocket Engine...
Hey Everyone,
If you're a student in Mechanical or Aerospace Engineering, this tutorial will teach you how to design a custom rocket engine nozzle in a programming language (MATLAB) and create a CAD model of it in SolidWorks (or any other CAD software). You can use this as a means to design, build and potentially test your own rocket engine.
You can then import this nozzle into ANSYS to perform a fluid dynamic simulation as I have done here:
• ANSYS Fluent: Rocket E...
This algorithm uses the Method of Characteristics (MoC) which is a very popular tool to design a rocket engine. It is used by academics as well as industry professionals to design rocket engine nozzles for optimum flight performance!
Topics covered in this video include
- Compressible Flow Basics (Overexpanded, Under expanded, Shock waves, Isentropic Flow)
- MATLAB Fundamentals (For Loops, If Statements, Importing from Excel using xlsread)
- Method of Characteristics Algorithm (Mach Angle, Expansion Fans, Prandtl-Meyer Function)
- Exporting to SolidWorks
- Designing the 3D CAD model of the Nozzle
- SolidWorks Fundamentals (Sketching, Offset, Loft, Importing csv files)
Watch my other rocket engine videos for a more clear understanding of the code!
How a Rocket Engine Works: • How does a Rocket Engi... and • How does a Rocket Engi...
Rocket Nozzle Structural Analysis: • ANSYS: Rocket Nozzle F...
Thank you for watching! Be sure to subscribe for more videos like this.
VDEngineering
~~My Udemy Courses on Motion Planning / Navigation / Trajectory Planning:
www.udemy.com/...
My Instagram: / vinayak_desh
My Website: www.vinayakd.com/ 
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Please watch the 2023 updated video of the Method of Characteristics!
ruclips.net/video/WJkTGog_aK0/видео.html
In this video I had made a lot of assumptions and I realized I did not very clearly explain the algorithms. There are also numerous inaccuracies which will lead to potentially incorrect results.
Great video and I love what you do. Could you try going into a bit more detail on how these lines are generated? Perhaps show a thorough calculation for one characteristic? That would be really helpful, thanks so much.
You can watch the video posted by ANSYS Learning. Explains the theory very well along with the calculation derivations.
Love this video mate, wish our projects got to to use so many industry tools
Your university probably has student licenses, that's what I used pretty much
you probably consolidated lots of the main topics and words in a simple package. So helpful. It made my life easier to find the topics in academia.
Just wish you also had links to lectures, books and more source material since some topics grow in complexity beyond what you can cover on youtube.
VD you are the best, clear and specific at the same time . Your video are very balanced in theory background and practice , really a precious resource
Respect
Great video, thanks a lot.
The coefficient of heats should be lower due to the pressure and temperature. The value 1.4 is at standard conditions
Really useful mate, great video. i'm currently in my third year of an Aerospace degree and i'm doing a project about rocket nozzles.
If I want to change the code to axisymmetric should i put radius^2 in every formulas?
@@pawekaminski5110 Were you able to find the answer to this question ? I need to do axisymmetric as well .
Very nice video bro :)
u r king bro really.
Can you advise some books where MOC is described, please. Thank you for the great job.
See pinned comment
First, thank you so much for your help
please can you point us to some references in order to understand more the characteristics methode
Any recommended books to learn about this kinda stuff? I'm in high school rn and I barely understood anything but I really want to learn!📖
A degree in mechanical/aerosapce engineering
Yes- specifically for engine design; modern engineering design of liquid propellant rocket engines by Huzel and Huang. It’s great
You can also read rocket propulsion by george p. sutton
Super bro
Can you show the code for shifting equilibrium? Also do you know how to find the right converging contour and how to do combustion chamber sizing? Your contents are much appreciated.
Hello, this project is from a while ago, if I find it yes I will share for sure, thanks for your comments:). The combustion chamber sizing is not that critical, as long as it maintains the pressure initially (when t = 0) right before the engine is started, and that it's structure (pressure vessel) can withstand the stress. The converging contour shape is any which minimizes drag (or does not lead to wakes), and is dependent on the rocket size etc.
Is it possible to find the area and throat area if I have the Force it needs to produce? I also have the specific impulse.
Also, why is R = 355?
Sir could you make the related video of measurement of quantity of fuel flow from the Central fuel tank in the fuselage of aircraft
Would you be able to explain how to do this for a dual bell nozzle.
Why every parameter in the inputs of the excel file is in the 30s where the temperature is given 1200K and pressure 2.27e6 Pa in the design problem?
Can somebody kindly guide me?
Amazing video.... I just have one question can you make a video that explain how create the geometrie of the nozzle ? please
Hi! You're video is saving my life, I have a question, can OCTAVE also work?
It should yes
Please do code for axisymmetric nozzle using method of characteristic. You r the best C:
I am having difficulty exporting graph data to excel .can you explain how the xslwrite command works.
Thank you for your effort. I need to do MOC for combustor design.Can you please give me some suggestions to start with?
Hello sir, such valuable content and helped us a lot, quick question please;
what if i want to simulate the separation of an overflow case, what modifications should be taken into consideration while designing? Or is it just a matter of pressure boundary conditions?
Thanks in advance.
So this is a bell-shaped nozzle that you have designed. How can we design a dual bell nozzle using the method of characteristics? Is there any way we can make changes in the code to make it a dual bell nozzle?
i wanna be a rocket scientist when i geow up
Why do you have n=T_max*2 in 8:11
It's the number of divisions. It ran fine on my PC. If you're getting error convert n into an int.
Just wondering, in the equation: pt=((2/(g+1))^(g/(g-1)))*2.068 what exactly is that 2.068? Is this a mach number for the midline of the nozzle according to the parameters? Just trying to understand more fully
Love the video though really helpful in trying to get my own code to work. Forgot to say this in the above comment.
@@terencecostigan4585 please, have you found an answer for your question above 2.068 ?
@@toufikkhattara4406 Not yet. I haven't seen that equation for critical throat pressure either. So I don't know.
@@terencecostigan4585 Did you found the answer?
@@toufikkhattara4406 have you found an answer for 2.068 ?
Has anyone solved the throat temperature problem at 5:19 minutes? is the formula correct? thank you all!
Yes that formula must be wrong. Should be TT = 2*T_1/(g+1)
The Excel sheet will not grant me permission to edit it for my parameters. What should I do?
Hello. Could you please upload the MATLAB code?
The chamber pressure depends on the nozzle design, so how you calculate it ?
Isn't this assuming Mach number varies linearly through the x direction of the nozzle?
Hey, if I want to simulate flow in the cd nozzle for merlin engine, but I take inviscid flow and air instead of the real propellants, will my chamber tmeperature and pressure be the same as the real values used in the engine?
I dont understand the calculations for exit pressure such as T = -131.21 + 0.00299*ALT ; and T = 15.04 - 0.00649*ALT. Why -131 and 0.00299*ALT. I have been searching for the formula off the nasa website but couldn't see it either. I hope you will see my question and explain. Thank you in advance
www.grc.nasa.gov/www/k-12/airplane/atmosmet.html
Given that n is computed as n = 2*T_max, and assuming that is a float, how can you run a loop that goes from 2 to n+1? It surely given an error...
Did u find why it gave an error@martina formidabile
@@viralstock2784 yes, it says n is a float and it cannot run the loop with the index being a float. It must be an integer...
How Did u solved it then..?@martina formidabile...
It ran fine on my computer, m goes to 56 and n is 55.3, to fix this just use floor to make n an integer.
@@VDEngineering Bro, thanks for this explanation and for taking the time to explain the code, but I have a question, why you take n=2*T_max? I believe the length of the for loop vector should be n=1*T_max. the final T(m) should be equal to T_max no 2*T_max. that's twice the deflection of the wall. Am I missing something?
what is chamber pressure here ? i could not find where it really defines
The link to the code please do provide
Im having trouble exporting the points into excel file. seems like the transpose function isnt working properly..... please help!
line 111 gives an error message of an unrecognized function or variable "LAST"
[HELP!!! ] I have another Matlab code that gives me non-dimensional coordinates, how do I properly convert them to match my design, please help
hi
first think you for your help
so i try to run your programme but a get this message errore
You can either set desired thrust OR mass flow rateError using fzero (line 290)
The function values at the interval endpoints must differ in sign.
Error in MOC (line 66)
M(m) = fzero(func,x_int);
can you help me to fix it
i too face d same prblm..did u got any solution to fix it...
if yes plzz help me out..
thank you!!
There is no reason to have thrust or mass flow rate in your code. It doesnt affect the nozzle exit mach at all, so I replaced Me as =FT/(m_dot*sqrt(g*R*T_e)); .
Cool
Hello, can you explain how you got the exit pressure equation, which was dependent on altitude?
google matlab stardard ISA for a very simple code
Which documents / books did you use during writing this code? I found many MOC codes and every of them is different.
See pinned comment
Hey man, another question, at 5:19 you explain how to get the throat temperature. When I run the MATLAB code, the throat temperature comes out to be 2982000 which doesn´t make sense. Sorry if im bothering you, I´m just trying to understand.
When doing a dimensional analysis, the units come out to be kJ/kg, not kelvin as one would expect.
i too have d same doubt...the formula izz wrong..
n i have a question that when we calculate exit mach from area ratio we get different value which is much different in exit mach we get from code.
cn u suggest e smthing..
If I want to change the code to axisymmetric should i put radius^2 in every formulas?
Has anyone solved the throat temperature problem at 5:19???
Try to put TT = 2*T_1/(g+1) instead
It does NOT seem the code has been validated comparing it with other sources, doesn't it?
Is the thrust parameter measured in newtons or kilonewtons?
It's in Newtons, cause everything else in the rocket thrust equation is in SI units.
@@theawsomedude37 Thanks man, much appreciated.
If I want to change the code to axisymmetric should i put radius^2 in every formulas?
Can you please help on how to design a Mach 2 nozzle design using MOC?
Use my code and set your pressure parameters to produce Mach 2 at the exit!
Also, what about the converging section? are the dimensions pretty much arbitrary?
Ye
Why is R = 355 ? What are the units?
Hi.
If I want to change the code to axisymmetric should i put radius^2 in every formulas?
You could try, but just use planar for now
@@VDEngineering Just wondering what are differences. I would like to compare both methods, but dont know how to change the code
Hey guys why iam getting area ratio 0.3! Is there any bug in the code? Please help me out!
Hi! I have a question what does the green line in the graphic represent. Thank you!
that's the first generated wall point at 11:18
sir can u make again the video of matlab and flightgear because so many members will understand clearly.please sir
I will make an improved one in the future, thanks
thank u sir
What unit is thrust and R in?
How good is the parabolic approximation of a bell nozzle?
Good enough
@@VDEngineering I'm currently part of a university team that's designing their own rocket engine, do you think the parabolic approximation is good enough for such projects?. Also thank you for replying
pt=((2/(g+1))^(g/(g-1)))*2.068 what exactly is that 2.068?
is the chamber pressure stagnation or static?
chamber pressures are always stagnation pressures
Where do i get this code from ?
Hello there,
I referred your video and facing an issue in the same can you please help me out. Please tell where can I get in touch with you.
ruclips.net/video/WJkTGog_aK0/видео.html&ab_channel=VDEngineering
Hi Sir, are you available to tutor?
Where is the code
5:54 isnt that a mistake? shouldnt be m_dot=FT*v_e; ?
throat temp = 2982000 :) this is impossible.
Your code works great, I've got to give you credit for that! But I can tell that you had a very poor understanding of what the variables were, and what they meant. Under "%% begin calculation," you said that TT is a temperature value, but R is not dimensionless, it's a specific enthalpy. Also, PR2 isn't a pressure ratio, it's temperature.
I think it would be great if you knew this so you could improve your code and documentation!
Also, I just saw your updated video. I started modifying your code well before you made that comment. Thx!
are you iranian ??
No
INDIAN CANADIAN
Don't waste your time trying a code with errors.
where is the code
ruclips.net/video/WJkTGog_aK0/видео.html&ab_channel=VDEngineering