How to define the mass ratio of a multi-stage rocket?

In summary, the mass ratio of a multistage rocket is the product of the individual vehicle stage mass ratios, does this mean the expression below holds?$$MR=\prod_{i} \frac{m_{f,i}}{m_{0,i}}$$Yes.
  • #1
Leo Liu
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Screen Shot 2021-10-15 at 1.23.53 PM.png

Sutton writes that the mass ratio of a multistage rocket is the product of the individual vehicle stage mass ratios, does it mean the expression below?
$$MR=\prod_{i} \frac{m_{f,i}}{m_{0,i}}$$
 
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  • #2
Yes.
 
  • #3
It a bit obvious but just to make sure please note that "individual stage" here don't refer to each stage in isolation but to the rocket stack after each individual staging such that the final mass of a stage is the initial mass of next stage, i.e. ##m_{0,i+1} = m_{f,i}##.
 
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  • #4
Filip Larsen said:
the final mass of a stage is the initial mass of next stage...
I don't think that would be correct. The final mass of a stage contains plenty of mass which you drop before the next stage ignited. That's the very point of having multiple stages.
 
  • #5
Rive said:
I don't think that would be correct.
For the payload ratio, the structural mass of the i-th stage is included in ##m_{0,i}##. Its both described on Multistage rocket (Wikipedia) and e.g. by Wiesel in "Spaceflight Dynamics" (using the symbols from this thread):

W.E. Wiesel said:
... the initial mass ##m_{0,k}## of the ##k##th stage is the mass of everything above the separation plane for that stage. The final mass of the ##k##th stage, ##m_{f,k}##, is the structural mass of that stage, plus the mass of stages still remaining. The ##(n+1)##th stage in an ##n## stage rocket is the payload, mass ##m_*##.

Its also easy to see that for the total payload ratio to be equal to the product of the individual payload ratios, i.e. for $$\frac{m_*}{m_{0}} \equiv \frac{m_{f,n+1}}{m_{0,1}} = \prod_{i=1}^{n+1} \frac{m_{f,i}}{m_{0,i}}$$ to hold then it must follow that ##m_{0,i+1} = m_{f,i}##.
 
  • #6
My appologies.

I found my copy of Sutton's "Rocket Propulsion Elements" and can see why my statements may have caused confusion. Sutton's mass ratio (MR) is not the same as Weisel's payload ratio (##\pi##) even though both form a product and call it overall mass and payload ratio, respectively. The individual MR ratios are good for simple delta-V calculation (with ##\Delta v = -\sum_i v_{i} \ln MR_i##) while the overall payload ratio (and its associated stage structural factor) is good for optimization analysis that tries to separate "design" of each stage and the staging itself.

I can see that Sutton indeed mentions the overall mass ratio as the product shown in first post, but I do not recall any particular use for it. Anyone?
 
  • #7
The author has worded this definition awkwardly. I believe the mass ratio defined in the paragraph you cite is just the mass of all of the inert portions of the rocket (including payload) divided by the overall mass of the rocket on the launchpad, including propellant.

It's kind of a semantic at the end of the day, because all we care about is minimizing the mass of everything that isn't either payload or propellant (and even then, minimizing propellant mass), but assuming this question is geared toward a homework question, I believe the author is saying the mass of all inerts including payload, divided by the mass of everything on the launchpad. Double check this with your TAs- I've seen professors pull a quick one on students before.
 
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  • #8
Filip Larsen said:
but to the rocket stack after each individual staging
Sorry, nothing to add to the thread, just wanted to say that I love the phrase "Rocket Stack". It's both very high-tech and very low-tech sounding at the same time.
 
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  • #9
Filip Larsen said:
I can see that Sutton indeed mentions the overall mass ratio as the product shown in first post, but I do not recall any particular use for it. Anyone?
You can plug that ratio into the (single-stage) rocket equation as effective mass ratio. The mass ratio passed by each stage combined. Between stages you have to remove the inert mass that's dropped - otherwise this would be a telescopic product and you would simply get the initial to final mass ratio, which is incorrect.
 
  • #10
mfb said:
You can plug that ratio into the (single-stage) rocket equation as effective mass ratio.
The equivalent single-stage equation would then be $$\Delta v = -v_e \log MR,$$ with ##v_e## being the effective total ejection speed. If this has to match the multi-stage rocket equation $$\Delta v = - \sum_i v_{e,i} MR_i$$ with ##v_{e,i}## being the effective ejection speed for stage ##i##, then $$v_e = \frac{\sum_i v_{e,i}\log MR_i}{\sum_i \log MR_i}$$ which only reduce to something simple if ##v_{e,i}## is constant for all stages, i.e. if ##v_e = v_{e,i}##.

If its not (which I suspect is the general case for pretty much any launch stack due reduced ##v_{e,0}## from atmospheric pressure), then I can't quite see the benefit or analytic power of trying to express the multi-stage rocket equation as an equivalent single stage equation since you just hide the complexity in the calculation of ##v_e##. Or did I miss something?
 
  • #11
It only works with a constant exhaust velocity, sure. Same as the standard single-stage rocket equation, which doesn't vary the exhaust velocity either.

If you want a realistic mission profile of a launch you can't use the rocket equation anyway, you need to simulate the actual trajectory.
 
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Related to How to define the mass ratio of a multi-stage rocket?

1. What is the definition of mass ratio in a multi-stage rocket?

The mass ratio of a multi-stage rocket is the ratio of the initial mass of the rocket (including propellant) to the final mass of the rocket after all stages have been separated and the propellant has been expended.

2. How is the mass ratio of a multi-stage rocket calculated?

The mass ratio can be calculated by dividing the initial mass of the rocket by the final mass of the rocket. This can be expressed as a decimal or a percentage.

3. Why is the mass ratio important in rocket design?

The mass ratio is important in rocket design because it directly affects the performance and efficiency of the rocket. A higher mass ratio means that the rocket can carry more payload and travel farther, while a lower mass ratio results in a shorter range and less payload capacity.

4. What factors influence the mass ratio of a multi-stage rocket?

The mass ratio of a multi-stage rocket is influenced by several factors, including the efficiency of the rocket engines, the amount of propellant carried, the structural weight of the rocket, and the desired velocity and altitude of the rocket.

5. How can the mass ratio of a multi-stage rocket be optimized?

The mass ratio of a multi-stage rocket can be optimized by carefully designing and selecting rocket engines with high efficiency, minimizing the structural weight of the rocket, and determining the optimal amount of propellant needed for the desired velocity and altitude. Additionally, staging the rocket at the right time can also improve the mass ratio.

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