Gaming Hatsunese Space Program in KSP with Real Solar System/Realism Overhaul

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mikusingularity
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[OUTDATED - new version here]

Recently, I have started to do a playthrough of Hatsunia's space development history in Kerbal Space Program.

This is basically going to be my personal VSA (virtual space program) with a structured career.

I used these mods in particular (but they are not the only ones, I also use mods like Procedural Parts and Kerbal Construction Time):

  • Real Solar System (which replaces the default tiny alien solar system with our own)
  • Realism Overhaul (which adds realistic propellants and engine behavior)
  • Realistic Progression 1 (which adds a career mode, a.k.a. RP-1)
However, RP-1's career progression seeks to emulate a "superpower" (US/USSR) space program, and the tech tree expects you to collect the science points from sending humans to the Moon in the 1960s. Since the Hatsunese Space Program is more like a "great power" space program, I might have to cheat with the science points just to unlock the parts representing later decades.

Negishima Space Center (I edited EarthHeight.dds and EarthSurface.dds):

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Launch of the Negi-A sounding rocket on 1956-08-31:

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(for in-game captions, I am using the "Kerbal Historian" mod)

Diameter: 339 mm
Height: 7.1 m
Wet mass: 958 kg (no payload)
Dry mass: 213 kg (no payload)
Propellant: Solid
Specific impulse: 220 s
Thrust: 28.2 kN
Burn time: 57 s

It reached a height of 307 km:

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The Negi-A was launched 9 times between 1956-08-31 and 1957-07-09, and carried a thermometer and barometer.

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Kerbal Construction Time simulates the time it takes to build and roll out a rocket. For Negi-A, it only takes 8 days to build, but I assumed 39 days between launches because a rocketry program like Japan or the UK at the time did not launch that often.

Sounding rocket mission contracts in RP-1 work like this: you send a specified amount of "sounding rocket payload" (SRP, which is treated as a resource loaded into pressurized tanks) to a certain altitude.

The 8th flight of Negi-A carried 345 SRP, which means that it carried 345 liters of sounding rocket payload. SRP always has a density of 0.5 kg per liter. I used a modular payload container system in which each segment contains 30 liters.

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The Negi-B sounding rocket was prepared for the International Geophysical Year.

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Diameter: 539 mm
Height: 9.7 m
Wet mass: 3191 kg (no payload)
Dry mass: 609 kg (no payload)
Propellant: Solid
Specific impulse: 220 s
Thrust: 93.9 kN
Burn time: 59.3 s

It launched five times between 1957-08-31 and 1958-04-11.

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Its first launch carried an Ion Mass Spectrometer to analyze the composition of the upper atmosphere.

IMS = Ion Mass Spectrometer, Bio = Biological payload, (R) = Payload recovered with parachutes

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The payload was recovered via parachutes.

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The second launch had a biological payload: several mice with life support equipment.

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The third launch sent 275 kg of payload over 100 km.

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Negi-C was a two-stage sounding rocket, first launched on 1958-05-17 with a Geiger-Müller Counter. It was essentially a Negi-A stacked on top of a Negi-B.

rBOCv4A.png


Total wet mass: 4137 kg (with no payload)
Height: 16.2 m (assuming three modular 100 L containers)

1st stage diameter: 539 mm
1st stage wet mass: 3141 kg
1st stage dry mass: 560 kg
1st stage thrust: 93.9 kN
1st stage burn time: 59.3 s
Propellant: Solid
Specific impulse: 220 s

2nd stage diameter: 339 mm
2nd stage wet mass: 996 kg
2nd stage dry mass: 251 kg
2nd stage thrust: 28.2 kN
2nd stage burn time: 57.0 s
Propellant: Solid
Specific impulse: 220 s

The second launch (and all subsequent launches) used 100 L modular containers.

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Negi-C launched twenty times from 1958-05-17 to 1958-12-10 (GMC = Geiger-Müller Counter)

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Negi-D had a new upper stage with the same diameter as the lower stage and a vacuum-optimized nozzle. It was first launched on 1960-01-13.

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Total wet mass: 4905 kg (with no payload)
Height: 14.5 m (assuming three modular 100 L containers)

1st stage diameter: 539 mm
1st stage wet mass: 3141 kg
1st stage dry mass: 560 kg
1st stage thrust: 93.9 kN
1st stage burn time: 59.3 s
Propellant: Solid
Specific impulse: 220 s

2nd stage diameter: 539 mm
2nd stage wet mass: 1764 kg
2nd stage dry mass: 402 kg
2nd stage thrust: 53.9 kN
2nd stage burn time: 57.2 s
Propellant: Solid
Specific impulse: 231 s

Negi-D launched sixteen times from 1960-01-13 to 1961-05-25.

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Size comparison with the Kronal Vessel Viewer mod:

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The Negi-E sounding rocket had twice the diameter of its predecessor. It would become the first stage of an orbital launch vehicle.

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Diameter: 1039 mm
Height: 14.6 m
Wet mass: 14661 kg (with no payload)
Dry mass: 2474 kg
Thrust: 539 kN
Burn time: 48.8 s
Propellant: Solid
Specific impulse: 220 s

All flights carried a recoverable payload with a camera.

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Negi-E launched four times from 1961-08-17 and 1962-04-26, carrying 1012.5 kg of payload with an additional 100 kg package containing a camera.

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Negi-F added a second stage, which approximately doubled the apogee.

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Total wet mass: 20725 kg (with no payload)
Height: 19.4 m

1st stage diameter: 1039 mm
1st stage wet mass: 14560 kg
1st stage dry mass: 2373 kg
1st stage thrust: 539 kN
1st stage burn time: 48.8 s
Propellant: Solid
Specific impulse: 220 s

2nd stage diameter: 1039 mm
2nd stage wet mass: 6165 kg
2nd stage dry mass: 1102 kg
2nd stage thrust: 239 kN
2nd stage burn time: 47.9 s
Propellant: Solid
Specific impulse: 231 s

Negi-F launched four times from 1962-07-17 and 1963-03-20.

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On 1962-10-01, the Rocket Development Promotion Headquarters of the Hatsunia Science and Technology Agency was converted into a dedicated space program: the Hatsunia Aerospace Science and Development Agency, or HASDA. The first satellite was planned to be launched in late 1964.

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Negi-G added a third stage, which didn't have as much of an effect on apogee as the second stage, but would serve as a crucial component in the upcoming orbital launcher.

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Total wet mass: 22646 kg (with avionics and no payload)
Height: 21.5 m

1st stage diameter: 1039 mm
1st stage wet mass: 14560 kg
1st stage dry mass: 2373 kg
1st stage thrust: 539 kN
1st stage burn time: 48.8 s
Propellant: Solid
Specific impulse: 220 s

2nd stage diameter: 1039 mm
2nd stage wet mass: 6065 kg
2nd stage dry mass: 1001 kg
2nd stage thrust: 239 kN
2nd stage burn time: 47.9 s
Propellant: Solid
Specific impulse: 231 s

3rd stage diameter: 1039 mm
3rd stage wet mass: 2021 kg
3rd stage dry mass: 539 kg
3rd stage thrust: 83.9 kN
3rd stage burn time: 40.0 s
Propellant: Solid
Specific impulse: 231 s

Negi-G launched five times from 1963-06-10 to 1964-05-23. The second launch (and all subsequent launches) implemented a guidance system, and was not spin-stabilized like previous sounding rockets. The extra mass of the avionics slightly lowered the maximum apogee.

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1964-08-31 01:39:00 UTC - The first orbital launch of HASDA, in the same year in which the "bullet train" was introduced. Instead of modular payload-carrying tanks, there was a jettisonable payload fairing with the satellite, which would also act as the fourth stage.

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Total wet mass: 22849 kg
Height: 19.4 m

1st stage diameter: 1039 mm
1st stage wet mass: 14560 kg
1st stage dry mass: 2373 kg
1st stage thrust: 539 kN
1st stage burn time: 48.8 s
Propellant: Solid
Specific impulse: 220 s

2nd stage diameter: 1039 mm
2nd stage wet mass: 6065 kg
2nd stage dry mass: 1001 kg
2nd stage thrust: 239 kN
2nd stage burn time: 47.9 s
Propellant: Solid
Specific impulse: 231 s

3rd stage diameter: 1039 mm
3rd stage wet mass: 2019 kg
3rd stage dry mass: 535 kg
3rd stage thrust: 83.9 kN
3rd stage burn time: 40.0 s
Propellant: Solid
Specific impulse: 231 s

4th stage diameter: 350 mm
4th stage height: 1580 mm
4th stage wet mass: 193 kg
4th stage dry mass: 42 kg
4th stage thrust: 13.9 kN
4th stage burn time: 24.6 s
Propellant: Solid
Specific impulse: 231 s

Fairing mass: 12 kg
_________________________

Second stage

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The third stage carried liquid propellant tanks along with small thrusters on the sides. They would be used after burnout of the solid rocket motor.

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The small thrusters were fueled by hydrazine, and were used to spin-stabilize the fourth stage prior to ignition.

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The fourth stage ignited about 12 seconds before the apogee.

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The satellite was called "HATSUNE" (High Altitude Test Satellite Utilizing New Experiments), orbiting with a perigee of 339 km and an apogee of 2522 km. It had a dry mass of 42 kg and carried instruments to detect micrometeorites and gravitational perturbations, along with telemetry equipment and a thermometer.

[The probe core is a custom mesh. Later, I noticed that there was a bug in which the burning sound would play if I loaded a vessel with a procedural SRB from the tracking station. No thrust was produced, but the orbit changed very slightly.]

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Comparison of all the rockets so far. Hatsune Miku added for scale.

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The Negi-2 launch vehicle first lifted off on 1965-03-09. It had a maximum capacity of 300 kg to a 250 km low Earth orbit (but most launches would involve using up to half of the capacity, and launching into a higher inclination).

mCj6Ykz.png


Total wet mass: 52729 kg (assuming no payload)
Height: 22.9 m

1st stage diameter: 1.58 m
1st stage wet mass: 33634 kg
1st stage dry mass: 5451 kg
1st stage thrust: 1339 kN
1st stage burn time: 51.6 s
Propellant: Solid
Specific impulse: 250 s

2nd stage diameter: 1.58 m
2nd stage wet mass: 14550 kg
2nd stage dry mass: 2844 kg
2nd stage thrust: 539 kN
2nd stage burn time: 56 s
Propellant: Solid
Specific impulse: 263 s

3rd stage diameter: 1.58 m
3rd stage wet mass: 4329 kg
3rd stage dry mass: 542 kg
3rd stage thrust: 33.9 kN
3rd stage burn time: 4 m 58.5 s
Propellant: IRFNA/UDMH
Specific impulse: 272.5 s

(note: 3rd stage engine config is slightly modified from the AJ10-118-D)

4th stage diameter: 0.439 m
4th stage wet mass: 165 kg
4th stage dry mass: 81 kg
4th stage thrust: 13.9 kN
4th stage burn time: 15.6 s
Propellant: Solid
Specific impulse: 263 s

Fairing mass: 51 kg

Most of the stages used solid propellant...

TQM6qMJ.png


...except for the third stage, which used a LE-S1 engine ("Liquid Engine - Storable propellant"). It had a thrust of 33.9 kN and a specific impulse of 272.5 s. UDMH (unsymmetrical dimethylhydrazine) was the fuel, and IRFNA (inhibited red fuming nitric acid) was the oxidizer. (custom config based on AJ10-118D)

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Fairing separation

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Spin-stabilization prior to 4th stage ignition

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The fourth stage was small, and was used for getting that last bit of delta-v to put the satellite into orbit.

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The satellite was dubbed "Neginohana" (葱の花, green onion flower), and was an engineering test.
[analogous to "Kiku" (chrysanthemum), the imperial seal of Japan]

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More launches would follow.

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1965-10-12 - Tanryoku (淡緑, light green) was an engineering test satellite developed by students at the University of Miraito (light green being the school's official color)

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1966-05-15 - Shinsei (新星, nova) analyzed the ionosphere and cosmic rays.

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1966-12-07 - Ume (梅, plum) was another ionospheric analysis satellite.

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1967-07-08 - Ajisai (紫陽花, hydrangea) was a geodetic satellite, measuring the shape of the Earth and its gravitational field.

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List of HASDA's orbital launches so far. These would not be the only launches of Negi-2.
[I am making my own custom contract configs that better fit the launcher's capabilities]

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Orbital paths around Earth

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Negi-1 + 2 comparison

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