Table of Contents
The Journeys of the Saturn : Spacecraft Data
Information on spacecraft in the The Journeys of the Saturn timeline.
Apollo Command and Service Model Specifications
Manufacturer - North American Aviation - Merged with Rockwell in March 1967 and now known as Rockwell International
Block I
Early model of the Apollo Command Module. Lacked the ability to dock with the planned Lunar Module. Only used for Apollo 1 and 2 test flights.
Block II
Apollo spacecraft designed for Lunar missions. Also used for Skylab missions and ASTP-I mission.
Block III
Apollo spacecraft that was designed for low Earth Orbit. The Service Module was significantly shortened with reduced fuel capacity. The Fuel cell power generation system was replaced by batteries and Solarpanels. This module was canceled in favor of the Big Gemini spacecraft.
Block IV
Apollo lunar spacecraft designed to seat 4 astronauts. Also featured a separate Mission Module. The CSM docks with the MM after launch. The Fuel cell power generation system was replaced by batteries and Solarpanels.
| Model Name | First Manned Flight | Last Flight | Crew Capacity | CSM Mass | MM Mass | Cargo Mass | Fuel Capacity | Habitable Volume |
|---|---|---|---|---|---|---|---|---|
| Apollo Block I | August 1967 | December 1967 | 3 | 12,200 kg | N/A | ?? | max 18,124 kg | 6.2 m3 |
| Apollo Block II | Oct 1968 | July 1974 | 3 | 12,200 kg | N/A | ?? | max 18,124 kg | 6.2 m3 |
| Apollo Block III | Canceled | Canceled | 5 | 12,200 kg | 5,000 kg | 3,000 kg | 1,600 kg | 6.2 m3 |
| Apollo Block IV | September 1974 | ?? | 4 | 12,200 kg | 5,000 kg | 3,000 kg | max 18,124 kg | 6.2 m3 |
Big Gemini Spacecraft Specifications
Manufacturer - McDonnel Douglas
Big Gemini is a re-usable spacecraft designed by McDonnel Douglas. Based on the Gemini spacecraft design. Designed for Earth Orbit missions and features the ability to land using a parawing and skid landing gear. Has a down capacity of over twice as much as the Apollo Command Module.
The Big Gemini featured the following modules.
Launch Escape tower- Used the same system as the Apollo CSM
Big Gemini re-entry Module- This module was configured with 2-pilots in the Gemini Cockpit. The passenger compartment was accessible through a hatch in the Gemini bulkhead. The crew compartment could hold up to 10 passengers but standard NASA configuration only has 4 passengers to allow substantial cargo return capability. Underneath the floor is the environmental control system, communication system and backup power system.
Retrograde Module- This module was attached to the back of the re-entry module. This housed the solid fuel de-orbit rockets.
Maneuvering and Cargo Module- This module included the maneuvering rockets, electrical power system. A pressurized pass through tunnel through this allowed access to a pressurized cargo module. The cargo module included a control station to allow docking. The Big Gemini docked with it's aft end to the space station.
| Model Name | Crew Size | Length | Passenger Capacity | Mass | Cargo Mass | Habitable Volume |
|---|---|---|---|---|---|---|
| Big Gemini-Block-I | 2 | 11.5 Meters | 6 | 32,000 kg | 12,000 kg | 18.7 m3 |
| Big Gemini-Block-II | 2 | 11.5 Meters | 6 | 32,000 kg | 13,000 kg | 18.7 m3 |
Block-II module used the knowledge gained in building the Block-I modules to allow the vehicle to be 1,000 kg lighter which allows more cargo capability.
| Big Gemini Vehicles | Name | Notes |
|---|---|---|
| BG-1 | Lexington | First Test Vehicle |
| BG-2 | Saratoga | Block-I |
| BG-3 | Enterprise | Block-I |
| BG-4 | Ranger | Block-I |
| BG-5 | Yorktown | Block-II |
| BG-6 | Franklin | Block-II |
Lunar Landing Vehicle Spacecraft Specifications
Manufacturer: Grumman Aerospace Corporation
Lunar Landing Vehicle (LLV) - LESA Base
The LLV LESA Base is launched un-manned by a Saturn-VB. When the LESA base nears the moon a Apollo-Centaur on the LLV burns to reduce the Delta-V by 900 m/s the Apollo-Centaur is then ejected to crash land on the lunar surface. The LLV Lander uses a computer to land the LESA Base on lunar surface, using four RL10A-3-1 engines. Once on the surface solar panels deploy and a 10kw Fuel Cell power system is activated. The fuel cell plant uses electrolysis to take the water generated by the fuel cell and separate it into Hydrogen and Oxygen Gas. Then a on-board Liquifier plant turns the Hydrogen and Oxygen gas into Cryogenic liquid for re-use in the Fuel Cell.
The LESA base will support a crew of 4 on the lunar surface for a 6+ month mission. The base features a 2-person airlock, small laboratory, crew living area.
The LLV LESA Base-LLV-LB
| Living Space - 6,000 cu ft |
|---|
| Mission Duration - 6-months+ |
| Crew- 4 |
| Total Wet Mass with Payload- 103,700 Kg |
| Propellant Mass - 36,000 Kg |
| Engines - Four RL10A-3-1 Engines |
| LLV Structure Mass - 11,000 Kg |
| Payload to Lunar Surface - 56,700 Kg |
| Power System 12kw Fuel Cell and PV Solar - 8,106 Kg |
| Emergency Battery Power 16×416 AmpHour Batteries - 1200 kg |
| Reactants for Fuel Cell - 2,000 kg |
| Basic Consumables-240 Days - Total - 10,560 kg |
| —-Oxygen(1kg Per Person Per Day) 240 Days 70% recycling - 288 kg |
| —-Dry Food (.5 kg Per Person Per Day) 240 Days - 480 kg |
| —-Whole Food (1kg per Person Per Day) 240 Days - 960 kg |
| —-Potable Water (4kg Per Person per Day) 240 Days - 3840 kg |
| —-Wash Water (26kg Per Person per Day) 240 Days 80% Recycling - 4992 kg |
| Emergency Consumables-60 Days - Total 1,520 kg |
| —-Oxygen(1kg Per Person Per Day) 60 Days - 240 kg |
| —-Emergency Food (.5 kg Per Person Per Day) 60 Days - 120 kg |
| —-Potable Water (4kg Per Person per Day) 60 Days - 960 kg |
| —-Emergency C02 Scrubbers- 200 kg |
| Oxygen Reserve - 600 kg |
| Communication Equipment - 2500 kg |
| Computer Systems and Imaging System - 500 kg |
| Medical Equipment - 250 kg |
| Crew Recreation - 800 kg |
| Additional Spacesuitsx4 (A8L Lunar Spacesuits) - 480 kg |
| Lunar Suit spares - 160 kg |
| Scientific Equipment - 5000 kg |
| Radiation Shielding - 2000 kg |
| AirLock - 2000 kg |
| Crew Equipment - 2000 Kg |
| Furniture and Interior Finishings - 1500 kg |
| Additional Water - 5000 kg |
| ECLSS (Environmental Control and Life Spport System) - 3000 kg |
| LESA Base Spares and tools - 1000 kg |
| Margin - 2000 kg |
| Living Space - 600 cu ft |
|---|
| Mission Duration - 6-months+ In Hibernation status |
| Crew- 4 |
| Descent Module |
| Total Wet Mass with Payload and Ascent Module - 70,000 Kg |
| Propellant Mass - 25,000 Kg |
| Engines - Four RL10A-3-1 Engines |
| LLV Structure Mass - 11,000 Kg |
| Power System PV Solar+Batteries - 2,000 Kg |
| Payload to Lunar Surface 33,000 (Not including Ascent Module) - Kg |
| Ascent Module |
|---|
| Crew- 4 |
| Total Wet Mass with Payload - 15,000 Kg |
| Structure Mass - 2,000 Kg |
| Propellant Mass - 7,500 Kg |
| Power System - Batteries - 300 kg |
| Return Payload 1600 Kg |