(Some of the technical details, as well as a neural network approach are detailed here.)
I loosely followed a discussion on how SpaceX land their first stage rocket boosters, and thought I
would try to understand how the boosters are controlled to land so accurately.
There are lots of different aspects to this question:
How do they build something like this?
How do they rotate the engines in flight?
How do they work out exactly where the boosters are?
I'm just going to discuss how they work out what to wiggle and when, during flight, in order to get their rocket to land on its bottom.
I'm not affiliated with SpaceX, and my information is based on a handful of papers on the subject in the public domain.
My aim is to explain the method in a way that does work, at least in my simulations, and is hopefully understandable.
Image from SpaceX, with copyright waived.
SpaceX make rockets that go to orbit. As far as we're concerned, these rockets have three bits:
The main body that continues upwards into the sky.
A booster (or two for the falcon heavy) that helps accelerate the main body, but only for the first two or three minutes.
The side booster(s) detach from the main body of the rocket, and with a small amount of fuel remaining, make a controlled landing either
near the launch site, or on barges out at sea. Like this:
The booster
The booster is a 42m long cylinder with fuel inside, and nine engines on the bottom.
It also has grid fins on the top and thrusters on the top.
The booster is controlled in four ways:
The nine engines can have their thrust level adjusted.
The nine engines are gimballed: their angle can be adjusted quickly in flight. If the engines are firing, then this produces a torque, rotating the vehicle.
There are cold gas thrusters at the top of the vehicle. These are not very powerful, but are useful for rotating the vehicle in space.
There are grid fins at the top of the vehicle. These can be rotated in flight to steer the vehicle.
The Task
The task here starts when the boosters detach from the main body of the rocket. They then become separate vehicles, which need to
turn around,
accelerate in such a way that they end up on a trajectory ending at a suitable landing site,
steer themselves through the atmosphere, so they stay on the right trajectory,
decelerate at the end so that they are pretty much stopped when they hit the landing site,
be more-or-less upright at the end of the flight so they don't fall over and explode.
The way to solve this task, from the onboard computer's point of view, is to send signals continuously to the engines, thrusters and grid fins,
to make sure this happens.
How to solve it.
There are several ways to solve this, for instance:
Make a neural network and optimise it using a genetic algorithm: The neural networks that get closest to landing the thing replicate with mutation, whereas the neural networks that do worse get replaced.
Use Pontryagin's maximum principle. There is a differential equation that consists of the dynamics of the rocket and also some costate equations.
If you can find a solution to the differential equation, it tells you the optimal controls throughout the trajectory. I believe that this is, in theory, an elegant if somewhat complicated way to solve the problem, and involves simply
optimising or searching for the correct boundary conditions, which here may be a 5-Dimensional space. This is a widely-known way to solve control problems, but I haven't personally used it.
Convex optimisation: You formulate the problem in such a way that it can be solved using a convex optimiser. This is apparently the in-favour approach and is discussed below. Compared to Pontragin's maximum principle, this is simple.
Train a neural network to predict the convex optimisation's output. Like here.
Convex optimisers
An optimiser is a simple beast. It takes a list of statements about a problem, and spits out the solution to the problem.
My aim here is to convince you that convex optimisers are not complicated to use or understand, and so this G-FOLD algorithm isn't actually all that difficult.
For instance, you may tell it to find a series of 3 numbers, separated by 2 or less from the previous, with the first not more than 0, and and the last number as large as possible. It should then output 0,2,4 as the solution.
All you have to do to use the optimiser is choose what to optimise, and write down two things: A scoring system, and a list of constraints.
In this article, I'm going to set up the problem as follows:
The trajectory, in real life, is a continuous path. In this problem, I'm going to approximate it by positions, velocities, etc., at N equally spaced times. For instance, at t=0 seconds (now), at t=1 seconds, t=2, ...
I'm going to choose that the thing I'm optimising is the velocities at each timepoint. This actually is equivalent to optimising the positions or the thrusts at each time, because given one of position, velocity, thrust, I can always work out the other two. It doesn't matter which I choose, but velocity, to me, seems simpler.
I'm not going to model the rotation of the vehicle. It's assumed that it can jump from one angle to another instantly. This is a horrible approximation, but it seems to be what the other papers do too. This assumption is probably required for keeping the problem solvable by cone optimisers (which is what we're going to use).
So the variables I'm going to optimise are:
vx_{0}
The x-velocity at time 0 seconds
vy_{0}
The y-velocity at time 0 seconds
vz_{0}
The z-velocity at time 0 seconds
thrust_{0}
The absolute thrust at time 0 seconds
vx_{1}
The x-velocity at time 1 seconds
vy_{1}
The y-velocity at time 1 seconds
vz_{1}
The z-velocity at time 1 seconds
thrust_{1}
The absolute thrust at time 1 seconds
vx_{2}
The x-velocity at time 2 seconds
vy_{2}
The y-velocity at time 2 seconds
vz_{2}
The z-velocity at time 2 seconds
thrust_{2}
The absolute thrust at time 2 seconds
...
...
vx_{N-1}
The x-velocity at time N-1 seconds --- at the end of the flight
vy_{N-1}
The y-velocity at time N-1 seconds --- at the end of the flight
vz_{N-1}
The z-velocity at time N-1 seconds --- at the end of the flight
thrust_{N-1}
The absolute thrust at time N-1 seconds
Now we have to tell the optimiser what the scoring system is. There are several scores that make sense: You could try to minimise
the fuel used, or you could minimise the distance from the last position in the trajectory to the target, or perhaps minimise the velocity at the end.
In this article, we're going to minimise fuel used. It's an arbitrary choice, and other choices may work better in real life. We tell the optimiser:
Note that this isn't complicated yet: We're just minimising the total sum of the thrust we're going to use.
Next we have to write down a list of constraints. These are rules that the optimiser has to obey.
Rule 1: The initial velocity
Let's say we're on the booster, and we're moving downwards at 100 metres per second. The optimal useful trajectory has to have, at time t=0 (now), that vy = -100.
Otherwise we can't use the trajectory: it's not our trajectory, it's just a trajectory.
vx_{0} = our actual x velocity.
vy_{0} = our actual y velocity.
vz_{0} = our actual z velocity.
Rule 2: The final velocity
We want to be stopped at the end of the trajectory.
vx_{N-1} = 0.
vy_{N-1} = 0.
vz_{N-1} = 0.
Rule 3: Position
During the first second, our average x velocity is (vx_{0} + vx_{1})*0.5 ---
the average of the two velocities at either side of the second.
We also know that the distance, in the x direction, that we'll move is going
to be equal to this (because we have 1 second timesteps).
We can add these 1-second steps up, and get the total distance we'll move over the trajectory:
Let us imagine now that we are at a known current height, and that the landing site is
100m in the x direction away, and level in the z direction. This gives us the following constraints:
distance x is between 95m and 105m.
distance y is equal to our current height.
distance z is between -5m and +5m.
Rule 4: Acceleration
At the moment, the optimiser could pick basically any trajectory it wanted: It could start here, move to the finish line, and stop there,
and also declare that the total fuel is zero: We haven't told it anything about thrust or acceleration.
We can tell the optimiser to be aware of how thrust works as follows. Let's pick the first timestep as an example:
Note that this is just Pythagoras' theorem applied to the velocity difference. The constant, g, is gravity.
This constraint is for the first timestep. We add one constraint per timestep, except for the last, resulting in N new constraints here.
The main effect of this is that the optimiser now has to keep track of what the thrust magnitudes are: It can
no longer take an arbitrary
path to the destination and declare that the total thrust is zero.
Rule 5: Max thrust
We have to limit the thrust to what the rocket can actually do.
thrust_{i} <= MAX_THRUST
This is a set of N constraints: we tell the optimiser that at every second, the total thrust for that second
must be below an upper bound.
Note that this constraint isn't exactly what SpaceX, or the other papers use, since they model the vehicle getting lighter, and
therefore the acceleration caused by thrust getting stronger as time goes on.
Let's see how this all works
Ok, so we have a way to calculate a trajectory. There are several things to look at: What is the trajectory, and more importantly,
does a vehicle using this trajectory actually land?
If we take an example test problem, and run it through the optimiser, we get one complete trajectory.
This isn't the path that the rocket would take, it's just what the optimiser *thinks* will happen in its dreams: Just a plan.
Next we need to see if it works in practice. Rather than build a 42m rocket, which planning
laws prohibit, we can run a simulation.
What we do is run a simulation with short timesteps (eg., 50 ms), and re-run the entire optimisation every second or so.
The optimiser says something like "In the first second, accelerate along the (1.0,0.5,0.3) vector",
and you can take that advice and use it for the first 20 or so timesteps.
Note that the optimiser's useful output is just the thrust vector, it doesn't say how to fire the RCS thrusters to spin the vehicle.
I've implemented a basic PD controller that won't allow the vehicle to tilt more than 45' that tries to orient the
vehicle with future planned
thrust directions.
If we do that, we get the path the (simulated) rocket actually does take --- not just the optimisers plan:
Note that the black line, in the video, is the plan that the rocket intends to take. Even the best-laid plans
often go amiss, though, and these ones are no different: The optimiser isn't fed exactly the same physics
as in real life: for instance, it doesn't know that the rocket tilt is unlikely to go outside 45', and it doesn't
know that the thrust direction can't change instantly.
As a result, the plan does change a fair bit during the flight. This is something that any real rocket will face
in real life. Consequently, plans always do need to be re-optimised periodically.
This does ok, but it's not upright when it hits its target, and when it hits the target, it doesn't really know it, so it keeps
buzzing around re-planning how to get back to the target. We can improve this by adding a few more common-sense rules
to the problem the optimiser solves each second.
Other rules
You could add other rules, such as that the thrust has to be accelerating the vehicle roughly upwards: This prevents
the rocket from wasting
fuel by accelerating towards the target more than it should. This would happen if the number of timesteps is minimised.
Another rule might be that the
thrust direction shouldn't change too much from one second to the next (which I haven't implemented, but it wouldn't be difficult).
Another quite extreme rule that I've added is that in the last second or two, the vehicle has to
be travelling downwards (with almost no side-ways motion) at a certain speed.
When you do these, and use that in the same old simulation as before, with the usual PD controller for the rocket RCS thrusters, you get this:
Comparison with SpaceX
The way I solved this differs from SpaceX in several ways. Firstly, I am trying to illustrate how convex optimisers are used
to generate trajectory plans, and hopefully you can see how flexible the approach is. It is certain that the actual constraints
used by spaceX are quite different to the ones I've chosen. For instance, some of the papers discuss constraining the trajectory
to finish off inside a landing cone --- rather than a narrow landing cuboid that I have used --- which probably saves fuel.
There are, however, a number of things that I've brushed over which will be quite a bit more complicated for SpaceX than for me:
Their engines can't be set to any level: They have to be either off, or going at a significant thrust, never just a tiny bit of thrust. This makes the problem more complicated.
Their vehicle gets lighter as it uses fuel, meaning that the vehicle is more responsive at the end of the flight.
The grid fins SpaceX use are probably harder to use than my RCS thrusters, and their RCS thrusters are less powerful than mine. This will make it harder to track the optimal trajectory.
Their physics has uncertainty in it.
They have to do the calculation in real time.
About the last point: My optimisation typically takes around a second, maybe half a second, on my laptop. I also run it several times to search for the smallest number of timesteps that produces a feasible result --- although this could be done in parallel with just 10 cores quite easily in the same time. Either way, I couldn't easily get an optimal trajectory recalculated in under a second.
It may be that the trajectory should be re-optimised more often than that: Basically
this works as a reaction time, and it seems possible that you need reaction times faster than 1 second in order to guarantee landing the thing.
I think that there are a suite of tricks that SpaceX use to speed up getting this optimal trajectory, and I can imagine that it would be things like storing bits and pieces off line, or re-using old trajectories as starting points for future trajectories, but to be honest, I don't know.
One thing I also think is that even if 1-second optimisation times are ok for a 42-meter long rocket, they wouldnt' be ok for a 1-meter long model rocket: Scaling laws mean that it's probably easier to optimise real-time trajectories for large objects than small.
Some of the technical details, as well as a neural network approach are detailed here.