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Apollo 11 liftoff acceleration function

by leehufford
Tags: acceleration, apollo, function, liftoff
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leehufford
#1
Dec17-13, 04:31 PM
P: 63
Hello,

Recently I saw a youtube video of the Apollo 11 launch with time and velocity data. I took data in 5 second increments and put the data in my graphing calculator. I used a quadratic regression to come up with a velocity time function.

I then differentiated this function to come up with an acceleration time function, and for the first 22 seconds I have a negative acceleration. Where did I go wrong?

My velocity function from quadratic regression:

v(t) = 0.1368t^2 - 5.9846t + 102.863

Then differentiating for a(t):

a(t) = 0.2736t - 5.9846

I tried removing the point (0,0) so I could do an exponential regression, but this fits the data worse and gives a nonzero acceleration at t=0...

So either I am using the wrong regression type or the data was bad. Is the launch simply too complex to fit into a nice differentiable function like this? I just thought it would be cool to have a handle on the types of acceleration experienced during this historic achievement. If you'd like me to post the data I would be happy to. Thanks in advance,

Lee
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A.T.
#2
Dec17-13, 04:38 PM
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Quote Quote by leehufford View Post
Recently I saw a youtube video ...
Link?
leehufford
#3
Dec17-13, 04:45 PM
P: 63
Quote Quote by A.T. View Post
Link?
Sorry about that. The video is found at http://www.youtube.com/watch?v=F0Yd-GxJ_QM.

A.T.
#4
Dec17-13, 04:59 PM
P: 3,914
Apollo 11 liftoff acceleration function

Quote Quote by leehufford View Post
v(t) = 0.1368x^2 - 5.9846x + 102.863
That intercept of 102.863 doesn't make any sense. v(0) must be 0.
leehufford
#5
Dec17-13, 05:18 PM
P: 63
Quote Quote by A.T. View Post
That intercept of 102.863 doesn't make any sense. v(0) must be 0.
I agree. Do you think the data is bad? I've tried exponential and power regressions to no success. Not sure how to force the regression to go through the point (0,0). I double checked my numbers and they agree with the numbers in the video. Do you think the velocity function should be quadratic? Thanks for your help.

-Lee
rcgldr
#6
Dec17-13, 05:42 PM
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I recall something like 7 million pounds of thrust on a 6 million pound Saturn V rocket full of fuel. The initial launch acceleration would be fairly slow, 1/6 g upwards.
SteamKing
#7
Dec17-13, 08:08 PM
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You give formulas for v(t) and a(t), but the independent variable is 'x'. Shouldn't 'x' be 't'?
leehufford
#8
Dec17-13, 09:16 PM
P: 63
Quote Quote by SteamKing View Post
You give formulas for v(t) and a(t), but the independent variable is 'x'. Shouldn't 'x' be 't'?
Yea I don't know why I mixed those up, I went ahead and edited that so t is the independant variable.

I wonder if the actual function itself was changing during the launch, making the concept of a single function invalid. My data went from t=0 until t=160 seconds because at that point the first stage rocket is jettisoned and there is an abrupt change in the velocity.

I wonder if shortening the timespan would improve the function. I know usually the more data the better, but if it does, it might indicate that the data should not be considered as one function, but several.

-Lee
SteamKing
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Dec17-13, 11:44 PM
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During stage separations, the rockets in the jettisoned stage have been cut off and the rockets in the next stage have not ignited, so the rocket is not accelerating during these intervals, at least due to thrust. There is a change in mass though from the loss of the stage being jettisoned.

By not including any data points during the first stage burn, you have necessarily lost accuracy in crafting your velocity and acceleration functions.
leehufford
#10
Dec18-13, 12:36 AM
P: 63
Quote Quote by SteamKing View Post
During stage separations, the rockets in the jettisoned stage have been cut off and the rockets in the next stage have not ignited, so the rocket is not accelerating during these intervals, at least due to thrust. There is a change in mass though from the loss of the stage being jettisoned.

By not including any data points during the first stage burn, you have necessarily lost accuracy in crafting your velocity and acceleration functions.
I'm a little confused now. I thought the time interval from t=0 to t=160 was the first stage burn, which is the only time I considered. I excluded time after that because I thought the velocity change would mess up the regression for the first part of the launch. Thanks for the relpy.

-Lee
harkkam
#11
Dec18-13, 12:46 AM
P: 26
From what I understand, the equation that was created cannot be the right equation simply because of the y intercept first of all being more than 0.

So either the data was entered incorrectly or the regression function is not working properly. Perhaps run the regression in an excel spreadsheet vs a graphing calculator and try again.

I would think that a rocket is just a simple object accelerating upwards, like those ball toss problems that physics 101 text books use.

Here the ball is the rocket.

However there might be something to consider, since the rocket is consuming fuel very quickly the change in mass is taking place, its getting lighter and the accelerating forces on a changing mass might cause the function to approx incorrectly, as the force acted upon the rocket remains the same.

In other words I think since the rocket is producing I would assume consistent thrust per time unit, but accelerating a changing mass, that might be a problem.
leehufford
#12
Dec18-13, 01:02 AM
P: 63
Quote Quote by harkkam View Post
From what I understand, the equation that was created cannot be the right equation simply because of the y intercept first of all being more than 0.

So either the data was entered incorrectly or the regression function is not working properly. Perhaps run the regression in an excel spreadsheet vs a graphing calculator and try again.

I would think that a rocket is just a simple object accelerating upwards, like those ball toss problems that physics 101 text books use.

Here the ball is the rocket.

However there might be something to consider, since the rocket is consuming fuel very quickly the change in mass is taking place, its getting lighter and the accelerating forces on a changing mass might cause the function to approx incorrectly, as the force acted upon the rocket remains the same.

In other words I think since the rocket is producing I would assume consistent thrust per time unit, but accelerating a changing mass, that might be a problem.
That was essentially my idea behind shortening the timespan, which would reduce some of the mass-loss effect. Not sure about the ball/rocket comparision though... one has an upward thrust combatting gravity while the other is just combatting gravity right?

-Lee
harkkam
#13
Dec18-13, 02:30 AM
P: 26
Quote Quote by leehufford View Post
That was essentially my idea behind shortening the timespan, which would reduce some of the mass-loss effect. Not sure about the ball/rocket comparision though... one has an upward thrust combatting gravity while the other is just combatting gravity right?

-Lee
Yes, the ball has a negative acceleration, i guess what I was trying to say was that my first thought was that this problem is a simple motion problem, negative and positive acceleration are in my opinion the same type of force but in different directions and you can "plug and chug".

But then I realized that the rockets acceleration is not constant unlike the ball, which is 9.8/ms^2,

so yeah they are different, but I think that the derivative of acceleration of the right eq, would give us how fast the acceleration changes, but still not sure how to help solve the problem.
harkkam
#14
Dec18-13, 02:36 AM
P: 26
perhaps, Im not sure but maybe a group of functions needs to be created, each unique function for maybe i dont 1 sec time intervals and plot each function on a graph and then approx one function from that, not sure if that makes sense, just something i came up with
K^2
#15
Dec18-13, 03:20 AM
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Quote Quote by rcgldr View Post
I recall something like 7 million pounds of thrust on a 6 million pound Saturn V rocket full of fuel. The initial launch acceleration would be fairly slow, 1/6 g upwards.
That seems very unlikely. TWR only slightly above 1 is extremely wasteful. Optimal for vertical ascent portion is 2, but since the whole thing gets lighter as it burns fuel, you'd typically start a touch low, and end up a touch high. Still, anything bellow 1.6-1.7 would be just a waste of fuel. You are almost better off to just pour out the fuel that's holding you back and start with higher acceleration.

Edit: And yet, that seems to be what they have gone with. I'm getting TWR of 1.23 from data on Wiki. I'll have to take a look at how that changes as fuel is burnt off, but this just doesn't seem like smart engineering, which really shouldn't be the case. Unless, increase in payload requirements came in late, and they had to increase the size of first stage tanks to compensate. But even then, some boosters would do a much better job of it... Weird.

Edit 2: Curiouser and curiouser. I just plugged in some numbers.

At the listed thrust of 34MN and ISP of 263s, in the 150s that the first stage was firing, it'd burn through just under 2,000T of fuel. Which is consistent with masses listed. Plugging that into the rocket formula, I get total [itex]\Delta V[/itex] of 3,160m/s. But hanging out in Earth gravity for 150 seconds brings it down to 1,690m/s.

Now, suppose I just poured out 600T of fuel. I really want that higher TWR on liftoff. No modifications to the rocket. We just reduce initial mass of the rocket, keeping final mass, after stage burns through, unchanged. Naturally, we get much less [itex]\Delta V[/itex]. Just 2,540m/s, in fact. But we also burned through all this fuel in just under 105 seconds instead of 150. After we take gravity's toll out, we're down to 1,515m/s.

I don't know about you, but 175m/s for almost a third of your fuel seems a bit wasteful. And that's without taking into account any savings you can make by reducing tank size.

Now, without taking drag into effect, this does buy you about 20km of extra altitude. That's significant on the ascent stage. Difference between 60km and 80km when you fire second stage would be huge. Of course, rocket would be far into rotation by then. But I have a feeling that once I add even a simple atmospheric model, I'm going to lose even that advantage. I'm going to go check that now.

Edit 3: Alright, so even with atmosphere in place, it looks like this extra fuel is buying altitude. None of the above takes into account the fact that ISP of the engines improves dramatically up there, but the idea is the same either way. Get as much fuel to thin atmo as you can, and let it all burn there. The whole thing could still be more efficient with a bit more thrust at the liftoff, but I'm guessing it comes down to working with what you have. I'm glad I got that sorted. Maybe it will be interesting to someone else.
sophiecentaur
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Dec18-13, 08:06 AM
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Rockets are hugely inefficient in the initial stages (zero efficiency for the first second or so). You just have to put up with virtually chucking away most of your fuel during and just after liftoff. Space engineers are constantly looking for better ways of launching but nothing viable has yet turned up. I am really surprised that aircraft launching is not yet the thing to use.
SteamKing
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Dec18-13, 08:57 AM
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Quote Quote by sophiecentaur View Post
Rockets are hugely inefficient in the initial stages (zero efficiency for the first second or so). You just have to put up with virtually chucking away most of your fuel during and just after liftoff. Space engineers are constantly looking for better ways of launching but nothing viable has yet turned up. I am really surprised that aircraft launching is not yet the thing to use.
It shouldn't be that surprising that A/C launch is not used. Rockets are still pretty sizable objects to fly around with. Granted, later systems use solid propellant instead of liquid fuel, but I think the desire is to increase the amount of payload which can be put into orbit. Even a Saturn V type rocket with the first stage omitted is a big critter.

http://en.wikipedia.org/wiki/Delta_IV

http://en.wikipedia.org/wiki/Antonov_An-225_Mriya

From the articles, you can see that the Delta IV launch system weight can easily exceed the maximum payload capacity of the An-225 aircraft.

Now the Russians have lately become interested in using the An-225 in an air launch project:

http://en.wikipedia.org/wiki/Air_launch_to_orbit

Who knows what will happen?
cjl
#18
Dec18-13, 10:48 AM
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Quote Quote by K^2 View Post
That seems very unlikely. TWR only slightly above 1 is extremely wasteful. Optimal for vertical ascent portion is 2, but since the whole thing gets lighter as it burns fuel, you'd typically start a touch low, and end up a touch high. Still, anything bellow 1.6-1.7 would be just a waste of fuel. You are almost better off to just pour out the fuel that's holding you back and start with higher acceleration.

Edit: And yet, that seems to be what they have gone with. I'm getting TWR of 1.23 from data on Wiki. I'll have to take a look at how that changes as fuel is burnt off, but this just doesn't seem like smart engineering, which really shouldn't be the case. Unless, increase in payload requirements came in late, and they had to increase the size of first stage tanks to compensate. But even then, some boosters would do a much better job of it... Weird.

Edit 2: Curiouser and curiouser. I just plugged in some numbers.

At the listed thrust of 34MN and ISP of 263s, in the 150s that the first stage was firing, it'd burn through just under 2,000T of fuel. Which is consistent with masses listed. Plugging that into the rocket formula, I get total [itex]\Delta V[/itex] of 3,160m/s. But hanging out in Earth gravity for 150 seconds brings it down to 1,690m/s.

Now, suppose I just poured out 600T of fuel. I really want that higher TWR on liftoff. No modifications to the rocket. We just reduce initial mass of the rocket, keeping final mass, after stage burns through, unchanged. Naturally, we get much less [itex]\Delta V[/itex]. Just 2,540m/s, in fact. But we also burned through all this fuel in just under 105 seconds instead of 150. After we take gravity's toll out, we're down to 1,515m/s.

I don't know about you, but 175m/s for almost a third of your fuel seems a bit wasteful. And that's without taking into account any savings you can make by reducing tank size.

Now, without taking drag into effect, this does buy you about 20km of extra altitude. That's significant on the ascent stage. Difference between 60km and 80km when you fire second stage would be huge. Of course, rocket would be far into rotation by then. But I have a feeling that once I add even a simple atmospheric model, I'm going to lose even that advantage. I'm going to go check that now.

Edit 3: Alright, so even with atmosphere in place, it looks like this extra fuel is buying altitude. None of the above takes into account the fact that ISP of the engines improves dramatically up there, but the idea is the same either way. Get as much fuel to thin atmo as you can, and let it all burn there. The whole thing could still be more efficient with a bit more thrust at the liftoff, but I'm guessing it comes down to working with what you have. I'm glad I got that sorted. Maybe it will be interesting to someone else.
Another thing that the lower TWR buys you is lower dynamic pressure. If you look at your velocity vs altitude profile, you'll find that the one with the higher TWR at liftoff will have a significantly higher velocity through the lower atmosphere, which increases aerodynamic loads on the vehicle structure. You can somewhat compensate for this by throttling down shortly after liftoff, and then throttling back up after you are through the thickest part of the atmosphere, but that increases gravity loss. You also tend to want to throttle down near the end of the stage burn to limit peak acceleration, and at this point, since you're throttling down for dynamic pressure at the beginning of the burn, and throttling down to limit acceleration at the end of the burn, you really start to get to the point where it's worth downsizing the engines and living with the low TWR at liftoff.

Also, another thing that you might not be considering here is the relative cost - rocket engines are very expensive, but rocket fuel is (relative to the cost of a launch) cheap. The fuel cost is a tiny percentage of the overall cost of a modern launch vehicle, so if you can gain any benefit by increasing fuel load without increasing engine count or thrust, even if it is hugely wasteful, it is probably worthwhile. This is especially true with liquid fuel rockets - if you look at the liftoff TWR of rockets powered only by liquid fuel, they tend to be pretty slow off the pad, while ones with solid rocket boosters tend to jump off the pad much faster (though still not typically above 1.5 or 1.6:1 or so)


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