Idea project of a spaceplane

[alvise]

hi everyone. i have designed a spaceplane on paper. if i give someone the technical data can someone design it here on orbiter??? i am available to pay if necessary. for example on the resistancee of the material put thickness and poisson coefficient and resistance of material to pressure on resistance to atmospheric re entry put the emissivity of the material , thickness and termal conductivity.

 

[Urwumpe]

hi everyone. i have designed a spaceplane on paper. if i give someone the technical data can someone design it here on orbiter??? i am available to pay if necessary. for example on the resistancee of the material put thickness and poisson coefficient and resistance of material to pressure on resistance to atmospheric re entry put the emissivity of the material , thickness and termal conductivity.

Why don't you do it yourself? It isn't too hard and the community can help you with your problems.

Throwing around money is of course an option, but I would not expect too much resonance, at least not as much resonance as genuine interest into Orbiter.

 

[Boxx]

can you show/PM the drawings?

 

[alvise]

can you show/PM the drawings?

Yes. How can i do it?

 

[Urwumpe]

Yes. How can i do it?

You can simply attach them to your post or send him a private message and attach them there.

 

[barrygolden]

Here is a Space plane to look at I think it would launch on a vulcan

 

[Urwumpe]

Here is a Space plane to look at I think it would launch on a vulcan

You can also take a look at this company there: https://polaris-raumflugzeuge.de/Technology/Future-Heavy-Spaceplane

 

[jedidia]

i am available to pay if necessary.

People always say that until they see the average hourly rate of freelancers...

 

[Urwumpe]

People always say that until they see the average hourly rate of freelancers...

Don't mention the war.

 

[barrygolden]

You can also take a look at this company there: https://polaris-raumflugzeuge.de/Technology/Future-Heavy-Spaceplane

Thats a pretty cool project I think useful l SSTO might still be out of reach. I did a little work on the X 33 and it could have flown with conventional fuel tanks but NASA said it did not advance technology far enough " ? " and Lockheed couldn''t raise the funding for Venture Star so it was canceled.
I did work some on the X 38 and you had to have the little ball no top to make it controllable so this manned Dream Chaser is interesting

 

[Urwumpe]

Thats a pretty cool project I think useful l SSTO might still be out of reach. I did a little work on the X 33 and it could have flown with conventional fuel tanks but NASA said it did not advance technology far enough " ? " and Lockheed couldn''t raise the funding for Venture Star so it was canceled.
I did work some on the X 38 and you had to have the little ball no top to make it controllable so this manned Dream Chaser is interesting

Yeah, I quite like the concept, especially the capability of aerial refueling did not yet make it into Orbiter, which could really make the difference there regarding a SSTO. And yes, we likely talk about a large (Sänger II or HOTOL class) SSTO there, possibly even larger than Skylon.

 

[jedidia]

which could really make the difference there regarding a SSTO

I don't quite see how... refueling would happen at low velocity and altitude (for something that's going to orbit, anyways), is the recovered bit really worth that much? Also, I guess that would technically still be two-stage, though I have to admit that it would be a new way to look at the concept of "staging"...

 

[Urwumpe]

I don't quite see how... refueling would happen at low velocity and altitude (for something that's going to orbit, anyways), is the recovered bit really worth that much? Also, I guess that would technically still be two-stage, though I have to admit that it would be a new way to look at the concept of "staging"...

Well, pretty much, I think the real advantage is tanking most of the kerosene late in flight, so the take-off and climb to altitude is easier.

 

[jedidia]

I think the real advantage is tanking most of the kerosene late in flight, so the take-off and climb to altitude is easier.

Ahhhh... So, it's not to recover lost propellant, but to make the thing HOTOL-capable by not having to carry all the tons of propellant needed later in the flight. Which, I guess, would result in some significant cost savings otherwise, like landing gear, wing area, engine power etc. Ok, looks like that is a good idea!

 

[alvise]

can you show/PM the drawings?

here is the project of the spaceplane

TECNICAL DATA OF SPACEPLANE

GENERAL DATA

empty mass 1628 kg including 4 people

7158 leters dodecane

16391 leters liquid oxygen

24053 kg propellants

mass ratio 15.77

exhaust velocity 21758 km per hour

maximum mass flow of propellants 50 kg per second

combustion time 8 minutes

maximum acceleration 28 Gs regulateble

average acceleration 4 . 07 Gs bearable

resisitance to g force yes

resistance to thrust yes

resistance to aerodinamice pressure yes

resistance to explosive decompression yes

colour white except on wings and nose where it is blacck

MATERIAL

internal balsa wood 1 cm

external carbon fiber 0.5 cm

lenght 8.5 m

width 3 meters

seen from behind the shape of the fuselage is a half ellipse

hight semi ellipse 2 meters

thryst 30 tonns force

thermal shield 1 milllimeter carbon fiber

+ 5 cm rigid expanded poliurethane

+ 10 cm of emptyness

+ 5 cm rigid expanded poliurethane

ATMOSPHERIC FLIGHT

2 air breathing engines (air augmented rockets.

total thrust 775837 newtons at sea level

maximum speed 3213 km per hour

maximum speed 3213 km per hour

altitude of flight higher thn 10,000 meters

propellants total mass flow rate 27,7 grams per second

total amount of propellants 50 kg

the 2 air breathing engines are cilinders

each has 0.5 meters of diameter and is long 2 meters

COCKPIT TERMAL ISOLATION

1.5 centimeters of i rigid expanded poliurethane except windows where 1.5 cm aerogel

COMBUSTION CHAMBER

carbon fiber 2 cm

volume 2.355 cubic meters (2 . 355)

OTHER

delaval nozzle not considered in the lenght of the spaceplane

the spaceplane has a heat pump of 6000 watts of power.

 

[Boxx]

Thank you for sharing your ideas. I think the design should be matured further before modeling anything seriously. The community here may be willing to suggest technical performances like thrust, Isp that seem to me very low for space flight (but I'm not specialist).

 

[Urwumpe]

Thank you for sharing your ideas. I think the design should be matured further before modeling anything seriously. The community here may be willing to suggest technical performances like thrust, Isp that seem to me very low for space flight (but I'm not specialist).

5800 Ns/kg is pretty OK for a rocket engine, on the high end for chemical propulsion. Using km/h as unit for specific impulse instead of the proper "Ns/kg" is of course confusing. I doubt that using the unusual Dodecane as fuel will result in such a high specific impulse, it has a lower hydrogen content than other fuels. Also, the high melting point can cause issues.