Heaven Piercer I
Shipbucket's One Small Step Challenge work in progress
Heaven Piercer I
Mission Type: Crewed Lap landing and orbital maneuver exercises
Operator: Victorious Flock
Mission duration: 5 days
Spacecraft: 08E1-Z Alliance Space Use Suit
Manufacturer: VF Hoowu X. Tziehu’s Machine Shop – Naval Station Khal Kharran
Launch mass: 860 metric tons
Landing mass: 743 metric tons
Crew: 1 (Vyzógeo, still known as Teirokan)
Members: Junis of Paselei
Callsign: Starstreak
Launch date: 5208
Launch vehicle: Teirokan Launch System 98A1-08H 2-stage Titan-class vehicle
Launch site: South Paseleia Sea
Recovered by: Walked out
Landing date: 5208
Landing site: Ben Paselei lake
Mission requirements:
Launch from Vyzóg’s (Still known as Teirokos III) southern Paseleia, into a trans-Lap injection trajectory. Land on Lap. Perform specified mission activities in Lap. Launch from Lap into a mobile anchorage intercept trajectory. Refuel and perform specified mission activities on mobile anchorage. Land on Paseleia, lake next to Ben Paselei.
Mission’s Purpose:
Demonstrate to the vyzógeo population that their species can reach space and operate in it. Claim sovereignty of the system for Vyzóg and its inhabitants. Demonstrate to Koya that this new species is not only able and willing to join the Republic, but also represent a useful addition to the cause. Generate popular support both in Vyzóg and out in the greater Republic for the integration of this new species.
Vyzóg:
Inclination: 2.4° to star’s (“Var”) equator
Satellites: 1 natural satellite “Lap”
Mean radius: 6401km
Equatorial radius: 6405,22km
Circumference: 40245,27km
Surface area: 514894102km2
Mass: 5,07651×1024kg
Surface gravity: 8,33565 m/s2 = 0,85G
Axial tilt: 12°25” to orbital plane
Surface temperature: minimum -75,1°C mean 12°C maximum 45,9°C
Lap: Still not defined.
Constraints:
Resources available are limited to the Mobile Anchorage VF Hoowu X. Tziehu
On board fabricator – licensed to produce additional fabricators.
On board mineral processing facility.
Organic mining drone gang.
On board electrolysis plant.
Fuel and pellet processing facility.
Naval Station Khal Kharran deployed on surface, has 65% of capabilities of Mobile Anchorage.
Facilities include a small spaceport for aerodyne dropships (marston matting) and small launch pads for personnel shuttles.
None of the facilities can handle superheavies, a superheavy cooled pad would have to be built.
Heavy dropships are landing in the ocean.
Air Launch does too little of the work fraction, no vehicle available immediately.
Available fuels are
LH/LOX from hydrolysis (AVAILABLE IMMEDIATELY).
Metalox. Methane from harvesting nearby planets or Sabatier reaction (AVAILABLE IMMEDIATELY).
Kerosene from synthetic production.
98A1-08H 2-stage Titan-class vehicle
An update to an older water launched superheavy lifter provided by the Naval Design Library. Chosen for its payload capacity and ease of construction, very few modifications were needed to adapt it to its new mission. Once assembled, it would be towed out to sea, the crew loaded from another ship, and its ballast tanks filled to reach launch position, where it would be fuelled and readied for launch.
Specifications:
Function: Superheavy reusable launch vehicle
Manufacturer: VF Hoowu X. Tziehu’s Machine Shop – Naval Station Khal Kharran
Origin: Chikol Republic
Production cost: 40,000 work hours
Height: 166.8 m
Diameter: 28 m
GTOW: 16,040,214 kg
Defuelled: 1,983,316 kg
Empty: 1,095,316 kg
Stages: 2
Payload to LVO: 888,000 kg
Altitude: 310 km
Orbital inclination: 15°
Mass: 888,000 kg theoretical, 860,000 kg practical.
First Stage – 98A1-A1
Height: 68.64 m
Diameter: 28 m
Empty mass: 721,887 kg
Gross mass: 9,335,447 kg
Powered by: 11 97AH1-08F Tiuku
Maximum thrust: 363,000 kN at 1 atm.
Specific impulse: 378 s
Burn time: 240 s
Propellant: Methalox
Second Stage – 98A1-B1
Height: 84.16 m
Diameter: 28 m
Empty mass: 275,387 kg
Loaded defuelled mass: 1,163,387 kg
Gross mass: 3,711,205 kg
Powered by: 1 1AJ1-08R Traka Ring aerospike
Maximum thrust: 57,600 kN at 0 atm.
Specific impulse: 449 s
Burn time: 540 s
Propellant: Hydrolox
Math
Boosting from surface to low orbit: Δvo = √[ (G * Pm) / Pr ]
where:
Δvo = deltaV to lift off into orbit or land on a planet from orbit (m/s)
G = 0.00000000006673 or 6.673e-11 (gravitational constant, don't ask)
Pm = planet's mass (kg)
Pr = planet's radius (m)
√ [x] = square root of x
So for Vyzóg: Δvo = √[ ( 0.00000000006673 * 5.07651×1024) / 6.40522×106 ] = 7909 m/s
(( 0.00000000006673 * 5.07651*10^24) / (6405.22*10^3)^(1/2)) = 7,909.0217
Net ∆v for LVO = 7909 to orbit + 1500 gravity + 300 drag + 100 backpressure for 1st stage + 150 correction + 30 water launch – 395 equatorial launch = 9,594 m/s
LVO to Gtransfer: 2440 m/s + Lap transfer: 679 + escape/capture: 145 + 100km orbit: 676 + 1721 launch/land
Net ∆v from LVO to Lap landing: 5661 m/s All done with spaceship so in a brachistochrone trajectory.
Titan 2nd stage
Tankage: 483,381 kg 107,008 kg
Skirts, lines and structure: 134,584 kg 119,000 kg
Engine system: 133,379kg 20,992 kg
Misc: inc ballute 68,585 kg 28,387 kg
subtotal 819,929kg 275,387 kg
payload 3,711,205 kg 888,000 kg
subtotal 2 4,531,134 kg 1,163,387 kg
Fuel S: 11,509,080 kg 2,547,818 kg
MassFull 16,040,214 kg 3,711,205 kg
GTOW: 16,040,214 kg
A = F / Mc
where A = spacecraft's acceleration (m/s), divide by 9.81 for Gs
F = spacecraft's thrust (newtons)
Mc = spacecraft's current mass (kg)
By rearranging the equation for acceleration, given the ship's thrust we can calculate the maximum mass of the ship with full propellant tanks (the mass of the ship with full tanks is often called Gross Lift Off Weight or GLOW).
GLOW(kg) = Thrust(newtons) / accel(m/s) Thrust 1st stage: 372600000
372,600,000 / 16,040,214 kg = 23.2 ( 2.4 G initial)
372,600,000 / 4531134 kg = 82.2 ( 8.4 G final, obvs throttled down)
Underwater launch payload penalty of 3.2%: Nominal Payload is now 888 metric tonnes
Δv equation:
Δv = Ve * ln[ M / Me ]
Δv = Ve * ln[R]
3700 * ln( 16,040,214 / 4,531,134) = 4,667 m/s = 4.67 km/s for 1st Stage. Which is more than the anticipated 4.43 km/s
4400 * ln( 3,711,205 / 1,163,387) = 5104 m/s = 5.1 km/s for 2nd Stage. Which is about on the mark for the anticipated 5.16 km/s
Sum is 9.77 km/s for LVO mission. More than 9.59 km/s needed to reach LVO.
Rockets:
Launch vehicle only has to go up to low orbit, suit will use Z-pinch + afterburner for orbit transfer.
1st stage to 250,000ft, Methalox 363 MN sum 10217 kg per engine, 112387kg total
11 short nozzle engines with 3 nozzles each with 2 turbopumps per engine. 11 MN per nozzle 33 MN per engine. 10217 kg TWR (3,300,000 / 10217) 323 sea level. 1560Kg turbomach.
Engines run at close to stoichiometric mixture thanks to materials.
Reusable, splashes on its own with little aerobraking and retroburn+ballute.
Gas generator is monopropellant charge with reloads. Isopropyl nitrate? Std VF charge.
Can this work as igniter too?
Peak q of 1600lb/ft2 on ascent.
1st stage parallel, Hydrolox 9.6 MN sum 4440kg total
Three medium single expanding nozzle to maintain attitude while launching from the sea. 3.2 MN each 1480 kg TWR 216 sea level. 520Kg turbomach.
Around 2nd stage to provide authority soon after ignition. Stay attached to 2nd stage.
Two turbopumps per engine, gas generator uses monopropellant charge.
Can this work as igniter too?
Throttle off to provide control to 2nd stage too, ability to vastly increase expansion ratio.
2nd stage to LVO, Hydrolox, Built in orbit and descends as on mission. 57.6 MN 16552kg total
Multinozzle ring aerospike engine with expanding nozzles. 57.6 MN for assembly, 4820kg turbomach., 16552kg total. TWR 348 in space.
Two turbopumps for assembly, gas generator uses monopropellant charge.
Reusable, has to reenter with heat shield.
Opens up aeroshell frontally. No hard edges, only curves.
Igniter is small spark igniter that is fed fuel and ox.
3rd stage is spaceship boosters, two 19.5m LH/LOX large nozzle boosters+organic engines.
Two single Falcon 1e 1st stage size. 40 tonnes each, 80 tonnes total.
Reusable but dock on anchorage.
Bootstrap startup.
Igniter is small spark igniter that is fed fuel and ox.13
Mass ratio
If you happen to have the rocket's delta V (or you are designing for a target delta V) and exhaust velocity, there is an equation that will allow you to calculate the required mass ratio:
R = e(Δv/Ve)
Net ∆v for LVO = 7909 to orbit + 1500 gravity + 300 drag + 100 backpressure for 1st stage + 150 correction + 30 water launch – 395 equatorial launch = 9,594 m/s
1st stage ∆v 4430 e(4430/3400) = 3.54
2nd stage ∆v 5164 e(5164/4400) = 3.19
Liquid Oxygen: 1141kg/m3
Fuselage has limit of 27 m inside
Hydrolox: 2,547,818 kg 1 atm 0 atm
r Mixture ratio (mass): 4.13 4.07 rich 4.83 4.75 rich ~4.41
Liquid Hydrogen: 80kg/m3
LH Load: 470,946 kg
Volume: 5,886.83 m3
Height: 12.34 m
LOX Load: 2,076,872 kg
Volume: 1,820 m3
Height: 3.82 m
Methalox: 11,509,080 kg 1 atm 0 atm
r Mixture ratio (mass): 3.21 3.15 rich 3.45 3.39 rich ~3.27
Liquid Methane: 420kg/m3
LCH4 Load: 2,695,335 kg
Volume: 6,417 m3
Height: 13.44 m
LOX Load: 8,813,745 kg
Volume: 7,725 m3
Height: 16.2 m
2nd stage housing: 45 m
LH tank: 12,34 m
LOX tank: 3,82 m
engine control 8 m
engine ring m 15 m
2nd stage: 84.16 m
Interface: 5m
CH4 tank: 13.44 m
LOX tank: 16.2 m
engine 1st stg: 34m
Stack: 152.8 m
Ballast: 14m
Total height: 166.8 m
Spacecraft: 08E1-Z Alliance Space Use Suit
93 tonnes empty. 860 tonnes GTOW.
∆v 111.65 km/s on 27t of fuel.
∆v ~ 4135 m/s per hour for the 27t tank.
Flow Stabilized Z-pinch Propulsion D-He3 fuel
Current: 5 MA
Mass flow: 0.095 kg/s
Fusion power: 3.3x1012W
Exhaust velocity: 3.5x106 m/s
Specific impulse: 356,800 s
Thrust: 3.3x105 N
14.5 hours of burn on 5 tonnes of fuel. Less than 1 TWR for 0.039G, 0.38 m/s2 (38 milligee) full load, 0.045G, 0.44 m/s2 (44 milligee) empty.
79 hours on 27 tonnes of fuel. ∆v 111.65 km/s on 27t of fuel.
Has to spiral out of planets nonetheless, unless using afterburner since it doesn’t achieve 0.1 G.
This is actually torchship performance. If barely. Actually firmly on low end torchship territory. “Classical” torchships are about 1000x more powerful.
Lunar mission ∆v: 5661 m/s ~ 4 hrs. 1390 kg of fuel expended one way.
Need to do the same for return + 7909 m/s to go back to Vyzóg?
Min 380 m/s to deorbit.
Do aggressive deorbit of 3800 m/s then deploy ballute.
Total spaceship mission ∆v: 15122 m/s Idealized newtonian case, 63% of ∆v means an exhaust velocity of: 0.6275 * 15122 = 9489 m/s, far below 3500000 m/s of the drive. This justifies using the water afterburner for the majority of the mission’s duration.
This is all work in progress and I appreciate your feedback.
A shipbucket scale drawing has been completed and submitted to the One Small Step challenge in shipbucket’s forums.
