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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

ManufacturerGrumman 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.


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
Power System 10kw Fuel Cell and PV Solar - 5,000 Kg
Payload to Lunar Surface - 51,700 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
timelines/spacecraft_data.txt · Last modified: 2014/09/21 18:24 by brovane