Determine the best rocket propulsion designs for one stage of a rocket, given a set of constraints and preferences (Kerbal Space Program).
kspalculator is a tool which determines the best rocket propulsion designs for one stage of a rocket, given a set of constraints and preferences.
Constraints are properties of the spacecraft which have to be fulfilled. These are the possible payload and the Delta-v as well as the minimum acceleration which is reached in an environment with given air pressure. Preferences are further properties a propulsion design might fulfil in order to be preferred. Examples for preferences are the thrust vectoring angle, the radial size, whether the engine is able to generate electric power, etc.
Which is the best design depends heavily on the specific application. A design might be better than another one, if it is cheaper or has a lower mass, but it might also be considered better if it is buildable using less technology or if it better fulfills some of the given preferences. Obviously, it is impossible to sort all propulsion designs by their “goodness”, so there might be more than one which is the best at least by some criteria. This tool presents exactly all best designs.
There is an official web frontend for kspalculator at: https://kspalculator.appspot.com/.
kspalculator evaluates all possible designs, checks whether they fulfil the user’s requirements, and then checks whether it is the best design using the relation “A is better than B iff A is better than B by any of the user’s criteria”. Only the best designs are then presented to the user. This way, the user has maximum flexibility to use the type of propulsion which serves best his needs, still without being spammed by non-optimal solutions.
The stage might have different requirements for minimum acceleration for different *flight phases* through different air pressures and different Delta-v requirements. For example you might require the vessel accelerating by 1000 m/s with an acceleration of 3 m/s², and later 500 m/s with an acceleration of 7 m/s².
Besides considering the classic liquid fuel engines as well as solid fuel boosters, kspalculator also considers using the LV-N Nerv Atomic Rocket Motor, the IX-6315 Dawn Electric Propulsion and the O-10 Puff MonoPropellant Engine.
Considered criteria to decide whether a design is better than another one are
Even though calculating this sounds highly sophisticated, the best designs are presented to the user usually within less than a second. The information shown about each design includes a detailed listing of the performance characteristics, i.e. the actually reachable Delta-v (which might be slightly more than required, because of rounding to tank sizes), the acceleration at full thrust as well as the mass at beginning and end of each flight phase.
(By the way, we are talking about Kerbal Space Program, version 1.2.1)
There is an official web frontend for kspalculator at: https://kspalculator.appspot.com/.
Here we explain how to use the kspalculator command line tool, but the basic concepts don’t vary.
Make sure you have Python, at least version 3.4 installed.
If you have pip installed, you may install kspalculator using
pip3 install kspalculator
Alternatively, fetch the most recent version of kspalculator at https://github.com/aandergr/kspalculator/releases. Installation is then done by unzipping the archive and calling
python3 setup.py install
kspalculator is invoked on the command line. Syntax is
kspalculator [--boosters] [--cost] [preferences] <payload> <Delta-v[:acceleration[:pressure]] [...]>
where payload is the payload in kg and Delta-v[:acceleration[:pressure]] are tuples of required Delta-v in m/s, acceleration in m/s² and environment pressure in ATM (0.0 = vacuum, 1.0 = kerbin sea level pressure) for each flight phase. You have to specify at least one of these tuples. Acceleration and pressure are optional and default to zero.
If you add --bosters, kspalculator will consider adding solid fuel boosters. This is very useful for launcher stages.
Options for preferences are:
In contrast to the constraints, preferences aren’t hard requirements for a design suggestion to be shown up. Adding preferences only adds criteria under which designs may be considered better than others. This means, specifying more preferences, more designs will be suggested.
If you specify --cost, results will be sorted by their cost instead of their mass.
For a brief reference for options, call kspalculator --help. To display the version of the tool as well as the corresponding version of Kerbal Space Program, call kspalculator --version.
Note that kspalculator calculates optimal designs for one stage only (or two if you allow boosters, where the first is a stage only utilizing solid fuel boosters). It will never split up your design into multiple stages.
Imagine we build a light Mun lander, having a payload of 1320 kg. That is a Mk1 Command Pod, four LT-05 Landing Struts, a Parachute, a Heat Shield, a Stack Decoupler and Solar Panels. We want to have two stages: the upper one flying from Low Kerbin Orbit to Mun, landing there, and then flying back to Kerbin; and the lower one launching the lander stage from Kerbin Space Center to Low Kerbin Orbit.
After having determined the payload of the stage, we need to figure out Delta-v requirements, acceleration requirements and air pressure at the different flight phases.
In this case air pressure is easy: As the Mun does not have any atmosphere and the stage starts its way already being in orbit, it is clear that the lander will be designed to fly through vacuum only.
Needed Delta-v can be easily read at Delta-v maps or calculated by calculation tools found in the internet (see links section later in this document). We find out, that we need 1170 m/s from Low Kerbin Orbit to Low Mun Orbit, then 580 m/s for landing at Mun, 580 m/s for starting at Mun and later 310 m/s for returning to Kerbin. Additionally, in this example we want to have 700 m/s Delta-v as a reserve.
Now let’s think about acceleration. As we land and start on Mun, we indeed have constraints regarding minimum acceleration, because we need to counteract Mun’s gravity. In this example, we want to have at least 2g = 3.3 m/s² acceleration when starting to land at Mun (i.e. when having reached Low Mun Orbit), and 3g = 5.0 m/s² to launch at Mun, g being Mun’s surface gravity, which is about 1.65 m/s² as can be found out in the in-game knowledge base.
Do we have any preferences? Yes we do. We’re building a lander utilizing LT-05 Micro Landing Struts, which are quite bad, so it would be nice to prefer engines which have a short length. Thus, we add --length flag to kspalculator invocation. Additionally, our Payload has radial size small, so it would be cool if the propulsion system also had this radius. We add -R small. Note that adding preferences does not prevent the listing of solutions which do not meet these preferences, i.e. adding preferences always leads to more output.
Doing so, we get:
$ kspalculator 1320 -R small --length 1170 580:3.3 580:5.0 310 700 48-7S Spark Total Mass: 6145 kg (including payload and full tanks) Cost: 1670 Liquid fuel: 840 units (4725 kg full tank mass) Requires: PropulsionSystems Radial size: Tiny Gimbal: 3.0 ° Engine is short enough to be used with LT-05 Micro Landing Struts Performance: [...] LV-909 Terrier Total Mass: 6320 kg (including payload and full tanks) Cost: 1190 Liquid fuel: 800 units (4500 kg full tank mass) Requires: AdvancedRocketry Radial size: Small Gimbal: 4.0 ° Engine is short enough to be used with LT-05 Micro Landing Struts Performance: 1: 1170 m/s @ vacuum 9.49 m/s² - 13.42 m/s² 6.3 t - 4.5 t 2: 580 m/s @ vacuum 13.42 m/s² - 15.92 m/s² 4.5 t - 3.8 t 3: 580 m/s @ vacuum 15.92 m/s² - 18.90 m/s² 3.8 t - 3.2 t 4: 310 m/s @ vacuum 18.90 m/s² - 20.72 m/s² 3.2 t - 2.9 t 5: 700 m/s @ vacuum 20.72 m/s² - 25.48 m/s² 2.9 t - 2.4 t 6: 51 m/s @ vacuum 25.48 m/s² - 25.86 m/s² 2.4 t - 2.3 t [...] LV-T30 Reliant Total Mass: 11008 kg (including payload and full tanks) Cost: 2825 Liquid fuel: 1500 units (8438 kg full tank mass) Requires: GeneralRocketry Radial size: Small Engine generates electricity Engine is short enough to be used with LT-2 Landing Struts Performance: [...] [...]
(Output was shortened)
Of the suggested designs, all are the best by some criteria. The first one, using Spark engine, is the one having the lowest total mass, but in this example we do not want to use it, for example because we did not research “Propulsion Systems” yet. We choose the Terrier design as we think it serves best our needs. Note that the tool also suggests the Reliant because of lower technology requirements, as well as some other nice designs which we skipped in this document to save space.
Now build the stage adding the 800 Unit Fuel Tank and the Terrier engine under your payload. Then add a stack decoupler (which weights 50 kg) as we’re building the launcher stage.
The payload for the launcher stage is 6370 kg (i.e. the lander stage plus 50 kg stack decoupler). Safe Delta-v and acceleration requirements for a launch to Low Kerbin Orbit have been found out to be 905 m/s with 13 m/s² at 1 ATM and then 3650 m/s with 13 m/s² at 0.18 ATM.
We want to use solid fuel boosters for the launch, so we add --boosters. Additionally, we prefer engines with thrust vectoring as it may be helpful to counteract turbulences during launch, so we add --gimbal. Small is still our preferred radial size. Now we determine best launcher designs:
$ kspalculator 6370 --boosters --gimbal -R small 905:13:1 3650:13:0.18 RE-I5 Skipper Total Mass: 89320 kg (including payload and full tanks) Cost: 18258 Liquid fuel: 5600 units (31500 kg full tank mass) Requires: HeavyRocketry Radial size: Large Gimbal: 2.0 ° Engine generates electricity Radially attached 2 * S1 Kickback SFB SFBs mounted on TT-70 Radial Decoupler, Advanced Nose Cone, 2 * EAS-4 Strut Connector each Performance: *1: 905 m/s @ 1.00 atm 13.30 m/s² - 21.35 m/s² 89.3 t - 55.6 t *2: 213 m/s @ 0.18 atm 23.59 m/s² - 26.08 m/s² 55.6 t - 50.3 t 3: 3437 m/s @ 0.18 atm 15.55 m/s² - 47.68 m/s² 40.9 t - 13.3 t 4: 107 m/s @ 0.18 atm 47.68 m/s² - 49.37 m/s² 13.3 t - 12.9 t 4 * Mk-55 Thud, radially mounted Total Mass: 108520 kg (including payload and full tanks) Cost: 19467 Liquid fuel: 4600 units (25875 kg full tank mass) Requires: HeavyRocketry Radial size: Small Gimbal: 8.0 ° Engine is short enough to be used with LT-05 Micro Landing Struts Radially attached 3 * S1 Kickback SFB SFBs mounted on TT-70 Radial Decoupler, Advanced Nose Cone, 2 * EAS-4 Strut Connector each You might limit SFB thrust to 79.5 % Performance: *1: 905 m/s @ 1.00 atm 16.42 m/s² - 26.35 m/s² 108.5 t - 67.6 t *2: 637 m/s @ 0.18 atm 29.12 m/s² - 39.36 m/s² 67.6 t - 50.0 t 3: 3013 m/s @ 0.18 atm 13.15 m/s² - 36.68 m/s² 35.8 t - 12.9 t 4: 2 m/s @ 0.18 atm 36.68 m/s² - 36.71 m/s² 12.9 t - 12.8 t [...]
(Output was shortened)
The asterisks in the performance tables indicate that the phase of flight is done by solid fuel boosters. The SFB thrust limit suggestion is the minimum thrust required to fulfil your acceleration constraints.
Now build one of the launchers being suggested by kspalculator and we’re ready to do a giant leap for kerbinkind.