# How Space Works

This is a collection of calculators, animations, and mini-apps that illustrate the physics of space. There are also tutorials on core concepts. This is being expanded over time to get across a feel for space and space travel in an intuitive way.

Click and drag!

## Lunar Elevator

Start distance: (From the centre of the Moon towards Earth)

use lunar surface

End distance:

use EML1

Material strength:

use Zylon I want the mass of the elevator too!

Parameters required to calculate elevator mass:

Safety factor:

## The Rocket Equation

Mass ratio:

Exhaust velocity: (m/s)

## A quick introduction to orbital mechanics

Orbital motion? That is just what happens when gravity is the only force that applies. In space, which mostly consists of space, things are seldom touching each other. As gravity is the only way objects then interact, orbital mechanics becomes the tool of choice to analyse what is going on.

##### The following terms are important when describing an orbit:
• Periapsis: The point where the orbiting craft is closest to the object it orbits.
• Apoapsis: The point where the orbiting craft is farthest from the object it orbits.
• Semi-major axis: The largest central radius of an ellipse. This is half the distance between the periapsis and apoapsis. Often shortened to $a$.

##### Let us then get started with the math!

We have a spacecraft orbiting in a circular orbit. What is its velocity? $$v=\sqrt{\frac{\mu}{r}}$$ $v$ is of course the velocity. $\mu$ is the gravitational parameter. You would often see that as $GM$, which is the same thing. That is the mass of the object you are orbiting ($M$) multiplied with the gravitational constant ($G=6.674 \cdot 10^{-11} \frac{m^3}{kg s^2}$).

To save you some time:

• $\mu _{Earth}=3.98600441 \cdot 10^{14} \frac{m^3}{s^2}$
• $\mu _{Moon}=4.9048695 \cdot 10^{12} \frac{m^3}{s^2}$
• $\mu _{Sun}=1.32712440018 \cdot 10^{20} \frac{m^3}{s^2}$

Using that information, we can calculate things like the orbital velocity in low Earth orbit: $\sqrt{\frac{\mu _{Earth}}{r_{LEO}}}=\sqrt{\frac{3.986 \cdot 10^{14} \frac{m^3}{s^2}}{6600000m}}=7771 \frac{m}{s}$

But wait a minute, not all orbits are circles! How can be calculate the orbital velocity in an elliptical orbit? Well, first of all, the velocity varies depending on where in the orbit you are, having a larger velocity at the periapsis than at the apoapsis. But there is an equation here to: $$v=\sqrt{\mu \left(\frac{2}{r}-\frac{1}{a}\right)}$$ $r$ is here your current distance to the centre of the object you are orbiting, and $a$ is the semi-major axis that we just talked about. Notice that in the case of a circular orbit, $r=a$ so this equation simplifies back to $v=\sqrt{\frac{\mu}{r}}$

### Transfer Orbits

We can already start to put the things we have learned together. Take a look at the figure below. Imagine you are orbiting in the blue orbit, and want to change to the red orbit:

What do you do? Well, take a look at the point where the orbits touch each other. Why are we in the blue orbit there, and not in the red one? After all, you can be in that location if you where in the red orbit too. Not everything is the same. What matters here is that you would have a different velocity, depending on which of the orbits you are in. Let us calculate that. We say $\mu = 1$ for simplicity: $$v_{blue}=\sqrt{\frac{1}{1}}=1$$ $$v_{red}=\sqrt{1\left(\frac{2}{1}-\frac{1}{2}\right)}=1.225$$ Below is an illustration of the velocity vectors. The pink part is the $\Delta v$ we have to spend. Note that the difference is smallest when the vectors point in the same direction.

##### Hohmann transfer orbits

A very common type of orbital transfer is between two circular orbits with different radius. The most efficient transfer is almost always an elliptical orbit touching both cirles. Below is an illustration. Click "start" to view an animation.

The $\Delta v$ cost would be the elliptical velocity at periapsis minus the velocity of the smaller circle, plus the velocity of the greater circle minus the elliptical velocity at apoapsis.

##### More math!

Let us take another look at the equation for velocity in an elliptical orbit: $$v=\sqrt{\mu \left(\frac{2}{r}-\frac{1}{a}\right)}$$ What happens if we tries to travel "to infinity"? We start at distance $r$, and travels to $a=\infty$: $$v=\sqrt{\mu \left(\frac{2}{r}-\frac{1}{\infty}\right)}$$ That simplifies to $$v=\sqrt{\mu \left(\frac{2}{r}-0\right)}$$ and that is equal to $$v_e=\sqrt{\frac{2\mu}{r}}$$ "$v_e$" is here short for "escape velocity". It turns out that travelling as far away as you would like has a limited cost. Of course, reaching infinity takes an ehm... infinite time... From this point, when I say infinity, I mean sufficiently far away.

You can also notice that the escape velocity at a given distance is $\sqrt{2}$ times larger than the orbital velocity of a circular orbit. $v_e = \sqrt{2}v_c$.

### Escape Velocity: Beyond Infinity

You have now seen 3 of the 4 different shapes an orbit can have, circular, elliptical and parabolic. The parabolic orbit is the one where we reach infinity. The remaining orbit is the one shaped like a hyperbola. This one also reach infinity, like the parabola, but with a mayor difference: In a parabolic orbit, we only "just reach infinity", that is, we are slowed down all the time by gravity, and the velocity is approaching zero as we get farther away. That is not always what we want. For instance, if we only "just escape Earth", our relative velocity to it is zero, and that means we have the same orbit around the Sun as Earth! In many cases, we want to have some extra velocity once we have escaped, for example for heading towards Mars, Jupiter, or for escaping the solar system entirely. An example closer to home is when we escape the Moon for a return trip. We do not want to end up in the same orbit as the Moon, instead, we want to head back home.

How can we achieve that? The answer is naturally to get a velocity higher than the escape velocity. But how exactly does that relate to the final velocity we end up with once we have escaped? Behold. The Pythagoras formula of orbital mechanics:

Example: Say we are in an orbit again around a mass with a $\mu$ of 1. Our distance is also 1. The escape velocity at this distance is then $\sqrt{2}$. Say then that we have an actual velocity larger than that, for instance $v=2$. In that case, we are going to escape. However, we are still going to be slowed down by gravity, so our final velocity when we have travelled far away is going to be lower than 2 for sure. $$v^2 = v_{\infty}^2 + v_{e}^2$$ We have some of the numbers to plug in to this equation. $$2^2 = v_{\infty}^2 + \sqrt{2}^2$$ We can rearrange that to get: $$v_{\infty}^2 = 2^2 - \sqrt{2}^2$$ And then get our velocity "at infinity": $$v_{\infty}=\sqrt{2}$$

## Delta-v: The core idea of rockets

We have seen that the way of controlling our trajectory through space is to change the spacecraft's velocity. How is that done? Rocket propulsion depends upon conservation of momentum. At first, this looks troubeling. Surely, if our momentum is going to stay the same, so is our velocity as momentum is simply velocity multiplied by mass. But velocity is a vector quantity. If two equal masses are going with the same speed in opposite direction of each other, their momentum are together still zero. So as a first working model, we can imagine two spacecraft starting together, then pushing of from each other. One goes in the direction we want, the other one... wherever stuff ends up while drifting through space. Sacrificing a second spacecraft for every maneuver would be quite wastefull. Indeed, this way of 'propulsion' does not depend upon the other vehicle being a spacecraft, it just has to be something with mass. That allows us to pick something that is for example convenient to store onboard. Another concern of efficiency is the speed the reaction mass is ejected. Low speeds give us only a little momentum, so in order to get the most out of our propellant we wish the 'exhaust velocity' to be as high as possible. One more thing to consider is that while the last bit of ejected mass only has to push our empty spacecraft, all the mass ejected before it has to push more or less of the propellant along with the vehicle. This means a velocity change costs exponential amounts of propellant. There is a straight forward formula to find the total velocity change from what we know about the propulsion system: $$\Delta v=\ln{\frac{m_0}{m_1}}v_e$$ Change in velocity equals the natural logarithm of start mass divided by end mass, multiplied by the exhaust velocity.
The inverse equation is also conventient when we wish to find the required mass ratio for a given velocity change: $$\frac{m_0}{m_1} = e^{\frac{\Delta v}{v_e}}$$