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Because linear increases in delta-v require exponential increases in mass, small changes to the assumptions you make about fuel tank structural mass and engine thrust-to-weight ratio start to make very large changes in the final size of the rocket.

For example, if you’re getting off a 3.6g planet with a 7-stage rocket, the difference between 88% fuel fraction and 92% fuel fraction yields about a 10:1 difference in the total mass of the rocket.

So I don’t think it’s really reasonable to talk about ultimate theoretical limits; too many engineering factors are involved.

Locking down a lot of variables, I can tell you what kind of rocket you’d need for a given surface g, though. Let’s make these assumptions:

- We are placing 1 ton of payload into low planetary orbit.
- Required delta-v to reach orbit, including atmospheric and gravity losses, is 10,000m/s per surface g. Seems to hold for Earth, Mars, and the “Earthtoo” which was discussed in another Q/A.
- We can build rocket stages of arbitrary size, with a tankage propellant fraction of 90%; the rocket stage mass is the tank mass plus the engine mass — ullage rockets, interstage, etc. is all handwaved out.
- We have an infinite supply of Apollo-era rocket engines: RL-10, J-2, M-1, H-1, and F-1.
- First-stage TWR at ignition must be at least 1.2 (relative to local gravity)
- Middle-stage TWR at ignition must be at least 0.8
- Final-stage TWR at ignition must be at least 0.5

Given those assumptions, here is a table of surface gravity, stage count, first-stage engines, and total rocket mass.

```
Surface First Total Saturn V
Gravity Stages Stage Mass, t Equivalent
0.5 2 1x RL-10 4.5
1.0 3 1x H-1 49.4 0.02
1.5 3 1x F-1 249.2 0.1
2.0 4 5x F-1 1329.0 0.5
2.5 5 40x F-1 8500.9 3
3.0 6 274x F-1 50722.2 17
3.5 7 2069x F-1 331430.9 100
4.0 8 20422x F-1 2836598.4 950
4.5 8 392098x F-1 47 million 15000
5.0 9 3.5 million F-1 391 million 130000
6.0 11 400 million F-1 38 billion millions
10.0 18 2.88e19 F-1 1.65e21 quadrillions
```

Up above 10g, something really interesting happens that is kind of a theoretical limit. The mass of the rocket reaches *a measurable fraction of the mass of the entire planet* it’s launching from.

At 10.3g, rocket mass is 0.035 of the mass of the planet.

10.4g, rocket mass is one fifth of the mass of the planet. This doesn’t actually alter the ∆v requirement — we’re going into orbit around the rocket/planet barycenter!

At 10.47g, the rocket *is* the planet, and we’re… just… chewing it up entirely, pulverizing it in a dust cloud expanding at 4km/s.

These extreme conclusions appear to be corroborated by this independently derived paper, which explores some other related aspects of super-Earth-based chemical rockets.

Another consideration recently brought up by user @uhoh is that as the linear scale of a given rocket stage increases, its mass, and thus the required thrust force to lift it, goes up by the cube of the scale, but the area available at the base of the rocket to mount engines goes up only by the square of the scale; this problem is made even worse here by the increasing surface gravity. The Saturn V was just about at the point where this relation starts to become problematic; the outboard engines on its first stage are mounted at the very edge of the stage in order to make room for their nozzles to gimbal.

Solid rockets don’t have the same dimensional constraints, and have very good thrust-to-weight and thrust-to-cost ratios, so they’re probably more likely to be used in lower stages for these very large rockets.

Stages much larger than the Saturn V first stage would need to address this with some combination of being shorter and squatter, or compromising engine gimbal range, or mounting engines in pods surrounding the tankage, and there might be fairly hard engineering limits at some point for those reasons. At the 3g mark, for example, the 274 first-stage engines would require a stage about 90 meters in diameter and 9 meters tall, at which point the engineering inefficiencies associated with the fuel tank proportions will be becoming serious.

StayOnTarget

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answered Jul 30, 2016 at 20: 53

Russell BorogoveRussell Borogove

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First, let us look at the rocket equation:

$$Delta v=ln left(frac{m_0}{m_f}right)v_e$$

That tells how much a rocket can change its velocity (the $Delta v$). The requirements for reaching a higher velocity for a minimal orbit would increase on your heavier Earth. (For constant density it is proportional to the radius.)

How can we increase the $Delta v$ of the rocket to keep up? We can increase the exhaust velocity, $v_e$, of the engine, but that cut-off is around 5000 m/s for chemical engines. The other thing we could do is increasing the mass ratio of the rocket $left(frac{m_0}{m_f}right)$. That is problematic too, as we can not really make the fuel tanks out of soap bubbles. Staging is the option left, you could place a big rocket under a small rocket to get a little more change in velocity. Then you are getting a linear benefit for an exponential expense.

As an example, the Saturn V rocket got into LEO (~9000 m/s), sent a payload towards the Moon (3120 m/s), the service module slowed the stack into LMO (820 m/s), and finally the LM landed and took off again (2*1720 m/s). There are still some unused fuel left in the service module then, so let us just call the total $Delta v$ of the Saturn V/Apollo 17 km/s. That is less than the requirements for a 2x radius Earth. The Apollo program was pretty expensive [citation needed], so it may take a while before a nation of a 2x Earth world attempts to go into orbit. The limit is, as you state, the ridiculously low payload ratio.

Another consideration is the increased surface gravity. (That scales linearly with diameter at constant density). That requires the rocket to have a higher thrust to weight ratio, and that will increase the dry mass, reducing the possible $Delta v$. (It also increases gravity losses, but that is mostly compensated by the lower scale height of the planet, reducing drag losses).

Eventually, the gravity is so high that even the most powerful engine can not lift itself from the ground. That at least is a definitive limit.

**A more theoretical consideration, is $Delta v$ requirements actually a finite limit?**

Surprisingly, it is not. Remember what I said about staging earlier: “you are getting a linear benefit for an exponential expense”. But there is not limit to what we can expend! Consider the following scenario: We add more and more stages at the bottom of the rocket, each of them has the same mass as all the stages on top of it. Then burning each of them gives the same mass ratio between before and after, therefore each of them are supplying

the same amount of $Delta v$. To add 10 times that amount, you need 10 stages each doubling the mass. To add 100 times that amount, you need to double a hundred times. The mass grows ridiculously fast, even doubling 10 times are over a thousand times more. But why should we stop 🙂

**But can we really continue to add exponentially larger stages for ever?**

After a while, other problems show up. For instance: Rockets are long and thin, to minimize drag. That shape can not be kept for very large rockets. The reason not is the square cube law. Conserving the same dimensional proportions, a rocket twice the height has 8 times more mass. But the base area of the rocket has only increased 4 times. That means that each unit of area has to support more mass. Sooner or later, even the strongest materials must give up, and you must give up the traditional rocket shape in favour of a wider base. That adds a lot to the drag! Problems like that are going to continue to show up:

“More mass means more problems, exponentially more mass means exponentially more problems.”

**Summarized: **

A modern design, larger rocket than the Saturn V, with modifications to increase the T/W ratio could probably make it to orbit on a 2x radius, 8x mass Earth. That is a feasibility limit, rockets that are ridiculously much larger may have a few km/s extra $Delta v$, but that does not alter the numbers a lot. In theory though, rockets can grow until the drag stops them, or the engines can no longer lift even themselves.

Or perhaps you at some point want to use the available resources of the planet to launch a single rocket to orbit.

answered Mar 9, 2016 at 8: 48

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**note: ** I’ve accepted an answer 2.5 years ago. This paper was published recently so I thought I would add this *supplemental answer* since it may be an interesting reference for future readers.

The Space.com article No Way Out?