The essential element is a shuttle to transport the crew during the various stages of the travel. In this project, the crew of 6 astronauts takes their seats in the multi-purpose manned vehicle (MMV) for each transfer. The MMV is made up of 3 sub-parts:

– The inhabited compartment sized for 6 astronauts in comfort optimized for a week (several months in a crisis).

– The propulsion block, with tanks for 8 tons of hydrolox plus 500 kg of hydrogen recovery intended to inflate lift balloons. The propulsion is made up of two small-diameter engines.

– The recovery system is consisting of a ventral heat shield inspired by the re-entry demonstrator European atmospheric IVX, for a re-entry from a hyperbolic (if necessary with successive air-bratings) and a system of hydrogen lift recovery sized for earth return or Venusian.

VHP in Earth orbit
Item Mass kg
Computer Com, Nav 250
Power 100
Propulsion Atmospheric 50
Thermal 100
ECLS (including closed-circuit water) 200
Crew 800
Freight (including food for a week) 100
Engines[1] 350
Rcs 200
Structure Tanks 1 150
Balloons 200
Shield 650
Hydrogen recovery 500
Reserve Design 350
Empty mass 5 000
Propellant 8 000
   
Isp (s) 444
Delta-V (m/s) 4 166

[1] data from these engines are taken from HM7B.

With a Delta-V 4.17 km/s, the MMV can be mounted on a first stage to place itself on its own. in a low Earth orbit. It can also reach a lunar orbit and return, if it is placed with full in a medium orbit, or be used for a launch to Venus as presented here.

A MMV can be launched to Venus in three different ways:

– With the Venusian launch system .

– With only a first stage, the MMV serves as the second stage to be placed in low Earth orbit, be refuelled and then head for Venus. This method involving a transfer of propellants into orbit will not be developed here.

– In payload with ergols, scenario developed below. In this case, the MMV and a cargo module are placed in orbit by an Ariane 6 qualified for flight Lived.

For the calculations, we consider that a contribution of 9300 m/s is needed to place a payload in low orbit. To reach Venus, we add 3700 m/s for a total delta-V of 13,000 m/s.

Both versions of Ariane 6 can be used according to the desired mass for the Cargo.

Ariane 6.4 M stage (t) Initial M (t) M ergols (t) Isp (Ns/kg) Delta-V (m/s)
Cargo   5,15      
MMV 13,0 18,15 8,00 4 355,64 2 531,48
2nd stage 28,6 46,75 24,28 4 560,00 3 340,81
1st stage 191,0 237,75 171,90 3 551,00 4 558,92
4 boosters 520,0 757,75 481,72 2 550,00 2 575,10
Delta-V total 13 006,31
Ariane 6.2 M stage (t) Initial M (t) M ergols (t) Isp (Ns/kg) Delta-V (m/s)
Cargo   2,85      
MMV 13,0 15,85 8,00 4 355,64 3 060,52
2nd stage 28,6 44,45 24,28 4 560,00 3 603,17
1st stage 191,0 235,45 171,90 3 551,00 4 650,64
2 boosters 260,0 495,45 240,86 2 550,00 1 697,82
Delta-V total 13 012,15
MMV with its cargo after it is launched into orbit by Ariane 6

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