ap0r

I'm alive and well, thank you! I have abandoned the project, the design is almost done but I realized there's very little chance of actually building it given my personal and financial situation. You should check Totalitor's youtube channel (I'm a subscriber) for your DIY liquid fueled rocketry needs :)

I think I really got when i designed a real rocket engine was able to rendezvous and dock. The universe became my playground then. Before that I was limited by single launch mass.

No the rocket. Personal issues, which I'd rather not discuss in a public forum. I hope you can understand.

Yes, the project is still very much alive! It's just that I have some very complicated real life responsabilities and issues that prevent me from having free time, taking my notes and blueprints and making them into a good quality article. Also i've ran into some legal trouble and I'm pretty broke, so there really is no money to continue the hardware build in these days. But rest assured, this will be completed if it takes me 20 years!

Yeah sorry. My ISP is driving me crazy with microcuts

Wageera Aerospace, the same people who brought you the Kearjet Bussines/Leisure Jet, have the pleasure of bringing you a new design: The N2 Personal Shuttle is a SSTO spaceplane, designed to carry 1 crew plus baggage to orbit or to a space station and back in a safe and economical fashion. It is an excellent spacecraft for pilots seeking the challenge of precision flying and the ultimate in speed, and for space programs in need of a cheap way to level up their pilots, and bring science and crew to space stations and back. This spacecraft can reach anywhere on Kerbin either via long-range atmospheric cruise or a faster suborbital hop, and will always achieve orbit safely and with margin to spare as long as you follow the instructions provided here. In most cases, even if you somehow have managed to run out of fuel during climb, as long as your apoapsis at the time is at or near 65 km, and your speed is above 2 km/s you will be able to limp into orbit with the translation RCS system only. The amount of ΔV remaining after orbital insertion will depend heavily on the launch profile used and the parameters of the target orbit but the best we’ve seen in testing is 347 m/s ΔV remaining when inserted to a circular equatorial 71 km orbit. The usual ΔV remaining after inserting into a 100km circular equatorial orbit is about 300 m/s ΔV plus about 600 kg of monopropellant, wich is more than enough to perform a rendezvous and dock to a refuel station with very wide margins of safety. After refueling in orbit, you can get up to 1.44 km/s ΔV. A typical cruise speed in atmosphere is about 1300 m/s (Mach 4.4) at 26 km altitude. Basic capabilities: Stability: Very stable in all regimes, up to and including hypersonic reentry. Just trim it as needed and it will fly hands-off, no SAS required. Stalls: Due to its mixed canard/elevon design, this spacecraft will not stall, but, upon reaching critical angle of attack, pitch authority will be lost, and the nose will drop, with no tendency to drop a wing as long as reasonable yaw angles are maintained. Stall recovery is the same as in a normal aircraft, but be conscious that it will take more height to recover. Achieving the critical angle of attack is almost impossible whenever full power is applied. Other unusual attitudes: For all tested anormal pitch, roll and yaw attitudes at speeds below Mach 1, centering all controls will result in either immediate self-stabilization or a mild dive from which you can then recover by slightly increasing pitch. Anormal attitudes above Mach 1 were not tested, due to the obvious risk, but our best guesses engineering models indicate that the spacecraft should recover in the same way. Aerobatics: The N2 was not designed to perform aerobatics, and consequently pitch and yaw are too sluggish for aerobatics, but it still can do cool aileron rolls and barrel rolls with ease. Variants: The plane comes in two variants, fully fueled, and jet fuel only, so you can easily fly a lighter, higher performance model for short hops that do not require oxidizer or monopropellant, without having to waste time manually editing fuel tank levels and worrying about potential center of mass issues. Included in your download, in classic Wageera Aerospace style, is a VERY comprehensive Pilot's Handbook with everything you might ever need to take the N2 Spaceplane to orbit and back. Download from: https://drive.google.com/file/d/0B7TPwnJRH1AYQ2pjLVdzaEVEbk0/view?usp=sharing

Working on 1.2, excellent for my miniature Space Shuttle. Thanks

It doesn't help. There is a large amount of individual operations required, but most of them are performed during flight planning and consist of simple addition/substracion/multiplication/division, rule of three, etc. Once in the air the amount of math is little and you have an electronic or mechanical calculator to help you. Also most of the time absolute precision is not a crucial requeriment, so rules of thumb and approximations work fine.

Thank you for choosing my project! It is taking WAY longer than expected, unfortunately real life issues have kept me away from the project these last months, but my motivation is still sky-high and can't wait to resume work in my liquid fuel engine!

That was exactly my tought process during most of the design, I have a pretty low math skill so this was a real challenge, but I also learned a ton.

That would be absolutely awesome. Right now the project is halted due to real life issues on my part, but rest assured I'm still highly motivated to finish it! I've learned a ton from what I've done so far, and am really looking forward to being able to continue the process. If you need 3D data, I can provide you with the CAD files.

If anything else, it should work as a whistle! (Puns aside, yes, it is difficult to build in such a small scale)

At that scale i'm guessing it makes no difference.

The numbers still work out somewhat but it's difficult fabricating on such a small scale I'd say fire this one, see what it does, then build a bigger one (10 pounds is about the absolute minimum without having to involve precision machining and the hassle and expense that goes with it.

It is definitely the opposite of the approach I'm using, and yet it seems really fun too Can't wait to see RUD-1 belching some flame!

Sorry for the LONG delay, @A Fuzzy Velociraptor, I've been having some seriously hectic days, and on top of it my ISP went poof for a whole week in my town. With respect to your question, I simply assume the chamber to be perfectly conductive (It's copper so the asumption is not a horrible one), and thus the heat input to the cooling system equals to the heat output from the engine. I further assume that the heat flow is 0.5 Kw/cm2/sec, or 3Btu/sq inch./sec . This is an educated guess based on other's people experience with similar engines. I wouldn't reccomend that you put the oxygen at right angles to the fuel, that might cause a bad mix and if pure oxygen touches the chamber walls they might oxidize quickly and damage the engine. Looking at the last figure, i've noticed that the chamber/nozzle looks to be assymetrical along the lenght axis. Or is that just due to the angle the picture was taken from?

This has been really helpful, thanks

Thanks @Gnou, this felt a bit cheaty but I use my reputation i.e perfect reputation a max 50 contracts, because such an esteemed agency should get to choose their missions, and low reputation less contracts.

Yeah, that and they are also subjected to pretty extreme forces, so they demand expensive materials and high precision machining.

Hi, sorry for the delay. There is no need for a turbopump to achieve the desired mass flow rates. My engine is very small! Yes, a turbopump + gas generator is a pretty simple concept, but the devil lies in the details, and implementation is a nightmare, and thus it should only be used if no other alternative exists. To quote from Rocket Propulsion Elements: "Engines with turbopumps are preferred for booster and sustainer stages of space launch vehicles, long-range missiles, and in the past also for aircraft performance augmentation."

Finally found a bit of time for a small update! The cooling system is finished, next up, injectors!

Yes, sorry. The original data was expressed in BTU's, that's the origin of the confussion. Should have used Joules and I got it from "Designing, Building and Testing Small Liquid fuel rocket engines" By using two reservoirs I mean the water pressure and flow rate straight from the tap or the tank where I live are not high enough to cover this, and thus I will need a reservoir and pump to provide the desired flow rate. Another update is coming as soon as I can find the time. Between work, flying, and studying I'm usually too knackered to do anything other than crawl into bed every night

Hello all... Not a real update today. I don't have time. But I-ve reviewed everything, fixed typos, added more data, a video on expansion, and a list of my reference material if any of you wants to do a similar project

Hello. The engine is designed for methanol-gox. Other propellants will result in different pressure, temperature, mass flow ratio, mix ratio, a different gamma value, and so on. Without making calculations I can't tell for sure. You can get potassium permanganate at any drugsture, it comes as purple pills that you dissolve in water to treat feet fungi. But then again, if you're using potassium permanganate as a catalyst to decompose the peroxide you're probably thinking of a monopropellant engine?

Yes, ethanol, methanol, gasoline, or kerosene as fuel, and gaseous oxygen, liquid oxygen, or nitrous oxide as oxidizer. They are all relatively safe, easy and cheap to obtain, and you can extract decent performance from them. I chose Methanol/GOX for my engine due to lower temps and pressures that greatly simplify both chamber and nozzle structural design, and reduce the magnitude of the cooling problem.