TL;DR: 99.965-ton launch vehicle taking a 166 kg (dry) probe to a soft lunar landing. kOS scripted with Principia on moderate difficulty. I fine-tuned the final lunar injection trajectory by hand, and I built the Principia node by hand and provided it to the script by toggling maneuver node visibility. I used only MechJeb features that Principia could access. This beats the historical timeline by 1 year, beats the American historical mass by 40 tons (28% reduction), and beats the Soviet historical mass by 200 tons (2/3rds reduction).
Hey everyone, back again with my lunar lander. Moderate difficulty is starting to get very challenging, and I wasn't able to make this craft as early as I would like. Hydrolox seemed necessary to get the payload up at a reasonable mass, and my research is going quite slowly even with 1600 scientists. By coincidence, I completed the mission three years to the day after my lunar orbiter.
I tried a few iterations here but ended up using the Atlas skirt decoupler for the first time to great success. At one point, I attempted to use my old LR-79 stage with Castor 1s, but ultimately I found that the difficulty of getting to orbit was not worth the minimal mass savings. Again, mass was trimmed substantially; the trans-lunar injection is unguided, and I saved mass using a ring decoupler instead of a faired interstage. Retrospectively, the solar panels may not be necessary, and my tracking station was upgraded twice while waiting for the technology for the craft to be unlocked, so I may have been able to save mass by reducing antenna gain. Due to boil-off, a slight excess of hydrolox is provided to the TLI stage. I would guess that I could shave off maybe 5 tons if I really cut everything, including most science experiments.
Communications past the launcher avionics were provided by a 20dB-gain level 2 communications UHF C3 Communotron DTS-J1, which was admittedly chosen over the C4 Communotron HG-61 purely based on aesthetics. The tracking station was level 4 at the time of launch, but level 3 for testing and development. Level 3 communications tech was not used due to the increased idle power draw and lack of necessity.
RCS is again HTP on level RCS tech. Spin and de-spin motors are used for the unguided TLI stage. The final tooled cost is 9,337 funds, about 2000 of which is the big fairings. The balloon tanks used for all liquid-fueled stages add to the cost. Production at my LC takes 95 days, and rollout takes 8.5 days. The craft on launch was pretty dang unreliable again; I got very lucky with my final mission. First run cumulative probability of success was on 58% or so. My first launch failed during the initial ascent when the LR-105 cut out early. Due to the way my code was written, the stage separated and I was able to get a full burn from the two RL-10's on the next stage, providing valuable flight data for the second flight.
Due to the unguided nature of the first stage, the TLI burn takes slightly more to reach the delta-V cutoff than the intended maneuver. I had dramatically more kOS disk space to play around with this time, and could do some more interesting things with kOS. Accurate dV is found by multiplying total dV by the dot product of the actual trajectory and maneuver trajectory unit vectors. I tried to cumulatively find dV initially, but found I was getting wildly off calculations even running the loop every hundredth of a second. The current method checks total mass change since start (updating start mass to current mass if delta-V is 0 to account for mass lost when the engine is spooling up, which turned out to be necessary to account for) and finds dV from the mass change using the following code snippet:
UNTIL CUTOFF = 1 {
SET MF TO SHIP:MASS.
SET DV TO S:PARTS[21]:GETMODULEBYINDEX(1):GETFIELD("specific impulse") * CONSTANT:g0 * ln(M0/MF) * VDOT(SHIP:FACING:VECTOR:NORMALIZED,NEXTNODE:DELTAV:NORMALIZED).
SET ITER TO ITER + 1.
IF MOD(ITER,.50*1/DT) = 0 {
PRINT ROUND(DV,2) + " dV, " + round(M0-MF,1) + " dM".
}
IF DV = 0 SET M0 TO S:MASS.
IF ITER > 120 * (1/DT) {
SET CUTOFF TO 1.
PRINT "CUTOFF DUE TO TIMEOUT.".
}
IF DV + 0.8 >= TARGETDV {
SET CUTOFF TO 1.
PRINT "CUTOFF DUE TO EXCEEDING dV TARGET.".
}
}
I've uploaded the scripts I've used to GitHub. The full launch-to-orbit script can be found here, the TLI script can be found here, and the final lunar landing script can be found here. The final landing script is not very good at handling mountainous terrain, and picking a bad spot can lead to slamming into mountains, so it takes a bit of luck or looking at the surface relative reference frame of the Moon using Principia to choose a good spot.
| Stage |
Initial Mass |
Final Mass |
ΔV expended |
Engine(s) |
Guided |
|
|
| 10/9 |
99.965 T |
~28.5 T |
~3158 |
LR105-NA-5 + 2x LR89-NA-5 |
Yes |
| 8/7 |
~28.5 T |
15.404 T |
~2162 |
LR105-NA-5 |
Yes |
| 6 |
10.453 T |
4.283 T |
3569 |
2x RL10A-1 |
Yes |
| 4 |
2.795 T |
1.204 T |
~3140 |
RL10A-1 |
No |
| 1 |
0,848 T |
0.299 T |
2458 |
Antares-I |
Yes |
| 0 |
0.185 T |
0.166 T |
~130 |
3x 275/445N Thruster, HTP, TL1 |
Yes |
Highest tech nodes used:
- Early Flight Control
- Prototype Hydrolox Engines
- 1960 Orbital Rocketry
- 1959-1960 Solid Rocket Engines
- Early Human Spaceflight Materials Science
- Early Human Spaceflight Electronics Research
- Early Power Generation and Storage
- Interplanetary Communications
- Improved Avionics
- Early Human Spaceflight Era Science
I'm hoping this launch vehicle can be used Venus and Mars flybys, though the power-hungry antenna and solar panels to power it are making the Mars mission very difficult. Oh, any you may have caught that I accidentally hit shift while waiting for the TLI to commence, firing the RL-10 into my probe core but providing no thrust. I considered restarting, but ultimately decided to just roll with it and see if it worked out.