Maker Pro
Maker Pro

Bravo to the SpaceShipOne team!

R

Rich Grise

Jan 1, 1970
0
I've done the numbers - listen up. They arrive at orbital height with
no velocity. To achieve orbit they need 17,500mph. In space parlance
that is called delta vee, and it doesn't come for nothing. Sure I
could put together a spreadsheet with some guestimates in it for the
amount of fuel you would need to do that, but back-of-a-cigarette pack
calculations say that it is a lot - like the amount you use to put a
normal rocket into space. That stuff doesn't happen by accident, you
know.

Now I have presented you with a simple, undisputed fact - orbital
height, and no velocity. You are making the extraordinary suggestion
that somehow (and I can only assume magic) they can find 17,500mph
from nowhere. So it is over to you - the extraordinary proposition is
yours - justify it with some numbers.

All I was asking was that you show me the numbers like you've done just now.
I stand informed. Thanks.

But it's not like anybody has to invent a new science or anything - it's
just engineering from here. SSTO _has_ been done, and WTF - use a B-1 or
something for the loft vehicle! Heck, we could save a lot by saving the
shuttle external tanks, or tossing them up in a low parking orbit, to
use for future building material.

My personal fantasy is a mass driver up the side of a mountain. :)

Cheers!
Rich
 
D

Dirk Bruere at Neopax

Jan 1, 1970
0
Clifford said:
Without actually "doing the rocket equation", consider this:
Suppose that the rocket+500lb payload totals 500Kg. 17,000mph is
about 7800m/s, so the orbital kinetic energy (mv^2) is around 30GJ.
Using a fuel yielding say 20MJ/kg, you need all the energy from 1.5
tonnes of fuel at apogee, with none being wasted in accelerating
said fuel. So realistically, you probably need 5 tonnes of fuel.
That makes your vehicle 10 times heavier at apogee, so the launch
system must get *that* up to 100km. It starts to add up... or in
this case, multiply up :-(.

Here's the bottom line.
A single stage to orbit craft requires a mass ration of 8.8 ie 88% of the weight
must be high Isp fuel.
http://www.totse.com/en/technology/space_astronomy_nasa/ssto.html

--
Dirk

The Consensus:-
The political party for the new millenium
http://www.theconsensus.org
 
J

Jonathan Kirwan

Jan 1, 1970
0
A single stage to orbit craft requires a mass ration of 8.8 ie 88% of the weight
must be high Isp fuel.
http://www.totse.com/en/technology/space_astronomy_nasa/ssto.html

Interesting. I'd already done that calculation just last night and came out
with about 88%, too. I'd used an estimated 400 seconds for the specific impulse
to capture most technologies I've read about.

I think Rutan's extending work on hybrid engines was well-placed because it can
lighten the engine/structure and it's that kind of advance that's needed as a
piece in the puzzle for an SSTO.

Jon
 
D

Don Pearce

Jan 1, 1970
0
Interesting. I'd already done that calculation just last night and came out
with about 88%, too. I'd used an estimated 400 seconds for the specific impulse
to capture most technologies I've read about.

I think Rutan's extending work on hybrid engines was well-placed because it can
lighten the engine/structure and it's that kind of advance that's needed as a
piece in the puzzle for an SSTO.

Jon

The problem with SSTO is that the speed gets too high too soon - you
go hypersonic while there is still too much air around. So you need
some way to delay peak thrust (as in "Go for throttle up" on the
shuttles). This means that essentially dead weight fuel has to be
carried for the critical part of the flight. That sends the 88% figure
way past 90%.

As for hybrid engines - standard ones are dangerous enough for me! The
idea of sitting in a plane using a scramjet gives me the horrors. (And
I speak as one with more air miles than I will ever be able to use).

d
Pearce Consulting
http://www.pearce.uk.com
 
J

Jonathan Kirwan

Jan 1, 1970
0
Well, at least you showed the numbers, rather than saying I had to
go look it up myself.

That kind of mindset irks me a little, Rich. So let me apologize right now for
my own emotion on this point...

I did it only because I enjoyed having to recall these things. I might just as
well have said nothing at all. And you still **should** have looked it up
yourself, Rich. Don was right.

Having an opinion, if there is to be any value at all to it, carries a burden --
a little bit of diligence. I cross-check facts in what I write routinely even
when all I want to do is just put out something quick. I "touch base" just to
make sure I'm not too far afield. This doesn't mean I'm right. But it does
mean that I've done the basic modicum of effort anyone has a right to expect of
me, when I say something. I owe others some small amount of due diligence
before I go on about some subject or take issue with someone else's comments.

Don said something that made sense when you look at the details. But does Don
owe you an education on the subject? Do you really think your comment was
well-advised given your ignorance on the subject? Why shouldn't you "go and
look it up," Rich? Was Don wrong to say so?
That was my only complaint about the previous post.

It's not a valid complaint. Don was right to suggest that you go and read up on
a subject that is very well explained in a variety of places and readily
available to you. He gave you the exact right key phrase to go look up for a
good start. That's not rancor or putting you down -- it's some honest help to
let you go see for yourself. Not so much help that he spells all the details
out for you, but probably just the right amount and in the right direction.
My only experience with SSTO was talking to a guy who did one of the
first ones back in the '60s. He was on the crew that found out that the
Earth is actually kind of oblate. And he claimed that on one shot, (out of
quite a few testruns) they put a whole rocket in orbit, in one stage.

Go here:

http://psas.pdx.edu/psas/Resources/ranacker_lecture_11-02-00_html/sld001.htm

Walk through the idea of a single stage LEO design. See where they wind up.
See why.

There is also an excellent, small book on the subject called "The Mathematics of
Space Exploration," written by Myrl Ahrendt in 1965. It was written for those
with a starting interest and does a good job at that task.

Regards an SSTO in the 60's, I don't know what you are referencing above, so
it's hard to comment on it.
And
there was that DC-X project, although I know that the Rutan project is
nowhere in that league - my point was, thanks for showing the numbers that
show why the Rutan ship isn't feasible for orbit - now somebody has to get
to work on the next "stage," so to speak.

The DC-X stands 42' and is an entirely experimental prototype with no provisions
for cargo or passengers. The DC-Y, which *was* intended for cargo, is three
times taller, five times heavier (when empty) and planned to be over 25 times
heavier, fueled and loaded. Both of them used Liquid Oxygen (LOX) and Liquid
Hydrogen engines. Making the DC-Y was estimated to require $300 million US in
1994. The project ran out of money and interest, I gather. (My recollection
from old days of rocketry stuff was that LOX+LH had an impulse of 388 seconds
and LH+fluorine was about 10 seconds more. I'm almost certain that Rutan's
vessel couldn't do better than 340 seconds and was probably more like 325.)

SSTO craft are technically hard on several fronts and if you read the above site
you'll see some of why other alternatives have been used in the past.

Do some work or your own, Rich. Think a little... then speak.

Jon


P.S. I just used to dabble some in amateur rocketry. I haven't done a darn
thing in it in 25+ years, but I used to use a small metal lathe when I was a kid
to build rocket nozzles I designed, based on ideas from another excellent book
no longer in print -- Bertrand Brinley's "Rocket Manual for Amateurs." I built
bunkers with sand bags, too, as these were steel rocket tubes and nozzles and I
was experimenting with various fuels. Sometimes, they blew up on the pad.
Sometimes, 10 feet up. So, the sand bags and wood paid off. Of course, some
actually worked very nicely! (Used to be easier to find areas to launch with
about 10-20 sq miles of human-free territory then, for those 4000 ft peak height
launches. These days, I'd need to run out to eastern Oregon -- a 3 hour drive
out or so.)

The modern incarnation of Brinley's book, the one that is the official NAR
handbook, "Handbook of Model Rocketry" is about toy rockets and has almost no
overlap at all with Brinley's book. Brinley's 1960 book is more a serious
experimenters' delight by comparison (with a forward by Willy Ley.) Brinley
covered various amateur fuels, nozzle design, and a lot of details that today
would be considered potentially dangerous areas to explore. Modern rocketry is
much safer today and much more accessible for just casual fun that it was. But
then, no where near as educational about chemistry and physics, for all that is
already done for you by the experts now.
 
J

Jonathan Kirwan

Jan 1, 1970
0
The problem with SSTO is that the speed gets too high too soon - you
go hypersonic while there is still too much air around. So you need
some way to delay peak thrust (as in "Go for throttle up" on the
shuttles). This means that essentially dead weight fuel has to be
carried for the critical part of the flight. That sends the 88% figure
way past 90%.

Yes, my calculations used a rather modest value for delta vee loss through air
drag -- a poor guess, probably. And your point here is right on, as delaying
the peak thrust only gives more time (t) for the -g*t part of the equation to
eat your fuel. Nasty.
As for hybrid engines - standard ones are dangerous enough for me! The
idea of sitting in a plane using a scramjet gives me the horrors. (And
I speak as one with more air miles than I will ever be able to use).

I've kind of thought of rockets (and fighter jets, too) as generally along the
idea of being pasted to the very tip of a very large pile of high explosives,
lit up and burning fast, and hopefully just "this side" of exploding.

Jon
 
D

Dirk Bruere at Neopax

Jan 1, 1970
0
Don said:
The problem with SSTO is that the speed gets too high too soon - you
go hypersonic while there is still too much air around. So you need
some way to delay peak thrust (as in "Go for throttle up" on the
shuttles). This means that essentially dead weight fuel has to be
carried for the critical part of the flight. That sends the 88% figure
way past 90%.

The obvious answer is the one used - use a second craft to get above most of the
dense air, add some substantial velocity, and launch from there. Not SSTO but
still totally reusable and almost as cheap.

--
Dirk

The Consensus:-
The political party for the new millenium
http://www.theconsensus.org
 
D

Don Pearce

Jan 1, 1970
0
The obvious answer is the one used - use a second craft to get above most of the
dense air, add some substantial velocity, and launch from there. Not SSTO but
still totally reusable and almost as cheap.

Do you mean a two-stage rocket? However you do it, you still have to
carry the fuel up from the ground; there is no such thing as "launch
from there".

d
Pearce Consulting
http://www.pearce.uk.com
 
D

Dirk Bruere at Neopax

Jan 1, 1970
0
Don said:
Do you mean a two-stage rocket? However you do it, you still have to
carry the fuel up from the ground; there is no such thing as "launch
from there".

I mean launching something substantial eg 70-80 tonnes from (say) a 747 at
40,000ft and 500mph


Dirk

The Consensus:-
The political party for the new millenium
http://www.theconsensus.org
 
J

John Woodgate

Jan 1, 1970
0
I read in sci.electronics.design that Don Pearce <[email protected]>
wrote (in said:
Do you mean a two-stage rocket? However you do it, you still have to
carry the fuel up from the ground; there is no such thing as "launch
from there".

But the mass-ratio requirement of a two-stage is less severe than that
of an SSTO. And your argument about feasibility is based on mass ratio.
Of course, it's nothing new; it's in the classic book by Willy Ley and
Chesley Bonestell, published about 1948.
 
D

Don Pearce

Jan 1, 1970
0
I mean launching something substantial eg 70-80 tonnes from (say) a 747 at
40,000ft and 500mph


Dirk
Neither of those figures is particularly substantial. Certainly 500mph
is next to nothing in terms of velocity, and 40,000 ft, although
reasonably attenuated, still has a lot of air.

d
Pearce Consulting
http://www.pearce.uk.com
 
D

Don Pearce

Jan 1, 1970
0
I read in sci.electronics.design that Don Pearce <[email protected]>


But the mass-ratio requirement of a two-stage is less severe than that
of an SSTO. And your argument about feasibility is based on mass ratio.
Of course, it's nothing new; it's in the classic book by Willy Ley and
Chesley Bonestell, published about 1948.

Absolutely - without multi-stage rockets, the space race would never
even have got started. As for mass ratio, it is not payload to fuel
that matters, but payload plus vehicle to fuel. Not a pretty
calculation.

d
Pearce Consulting
http://www.pearce.uk.com
 
D

Dirk Bruere at Neopax

Jan 1, 1970
0
Don said:
Neither of those figures is particularly substantial. Certainly 500mph
is next to nothing in terms of velocity, and 40,000 ft, although
reasonably attenuated, still has a lot of air.

What % of the orginal fuel load of a rocket is required to get the whole thing
to 500mph?

--
Dirk

The Consensus:-
The political party for the new millenium
http://www.theconsensus.org
 
D

Dirk Bruere at Neopax

Jan 1, 1970
0
Don said:
Absolutely - without multi-stage rockets, the space race would never
even have got started. As for mass ratio, it is not payload to fuel
that matters, but payload plus vehicle to fuel. Not a pretty
calculation.

And for multistage the effective mass ratio is a multiplication of the mass
ratios of the individual stages.

--
Dirk

The Consensus:-
The political party for the new millenium
http://www.theconsensus.org
 
R

Rich Grise

Jan 1, 1970
0
Do you mean a two-stage rocket? However you do it, you still have to
carry the fuel up from the ground; there is no such thing as "launch
from there".
Your "first stage" is just a high-performance heavy-lift air-breather.
I don't know if we'd have to invent something new - maybe something like
the B1, but cheaper. ;-)

And, of course, a good mass driver up K2 would get you to 30,000' or so at
an arbitrary speed, depending how much oomph you want to put into it. :)

Cheers!
Rich
 
R

Rolavine

Jan 1, 1970
0
Thanks to all of you, we have some really smart people here, and your
instruction on rocket effiency was great.

Can anyone explain how SpaceShipOne's feather works? I think this the
reconfiguration of the ship for reentry, and something about that prevents it
from buring up?

Thanks in advance.

Rocky
 
J

John Woodgate

Jan 1, 1970
0
I read in sci.electronics.design that Don Pearce <[email protected]>
Absolutely - without multi-stage rockets, the space race would never
even have got started. As for mass ratio, it is not payload to fuel that
matters, but payload plus vehicle to fuel. Not a pretty calculation.

If private space-flight proves economically impracticable, we'll have to
wait for the Space Elevator. This is so important that governments will
not really be able to refuse to underwrite it (or rather them; we need a
minimum of three).
 
D

Don Pearce

Jan 1, 1970
0
I read in sci.electronics.design that Don Pearce <[email protected]>


If private space-flight proves economically impracticable, we'll have to
wait for the Space Elevator. This is so important that governments will
not really be able to refuse to underwrite it (or rather them; we need a
minimum of three).

Well, that depends on the guys in the materials labs. Having read
Arthur C. Clarke's "The fountains of paradise" it is clear that even
this is not the only problem. All that orbiting junk is a serious
hazard.

d
Pearce Consulting
http://www.pearce.uk.com
 
R

Rich Grise

Jan 1, 1970
0
Thanks to all of you, we have some really smart people here, and your
instruction on rocket effiency was great.

Can anyone explain how SpaceShipOne's feather works? I think this the
reconfiguration of the ship for reentry, and something about that prevents
it from buring up?

The thing about reentry that prevents it from burning up is that when
it starts reentry, it's going at approximately zero miles an hour. ;-)

This has been explained to me in great detail, by a couple of generous
folks, whom I might not have thanked properly. Thanks!

Well, it's going maybe 100 or so MPH - that's within three significant
digits of zero percent of orbital velocity, anyway. ;-)

Now, if it'd been shot up there with a proper mass driver -

I've been doing some fantasizing about a 15,000 foot LIM up the side
of some handy mountain, with enough power to it to maintain 1G all
the way to the end.

s = (a/2) * t^2
t^2 = s / (a/2) = 2 * s / a, which is associative.

So, if I assign 32 ft./sec/sec as a, and 15,000 feet as s, then
t is 21 seconds? And you're only going 472 MPH? Hmmmm.... how about
1.5G....

But the only limit on how much gets to that height and speed is
engineering. Remember, it's going 472 MPH at 30,000 or so feet. Cargo
could handle, say, 4G .... it looks like it'd make 15Kft in just under
11 sec, with a final speed of 944.75 MPH.

Of course, the whole mass driver would have to be enclosed in an
evacuated tube.

Thanks!
Rich
Of course, if my math is from planet Neptune, please enlighten me, thanks.
 
C

Clifford Heath

Jan 1, 1970
0
Rich said:
I've been doing some fantasizing about a 15,000 foot LIM up the side
of some handy mountain,
Of course, if my math is from planet Neptune, please enlighten me, thanks.

Work out how to fire a BB gun pellet through fifteen metres of honey,
and you'll have an idea how to get things to penetrate the atmosphere
in the way you're proposing.
 
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