CLLARE Hardware Configurations
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This page lists all the standard configurations of the CLLARE Core Hardware. Each configuration is suited to a different flight type.
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[edit] Suborbital Configuration
The suborbital configuration is the simplest hardware configuration and consists of a lone Command Module (CM). This configuration is denoted by CM.
The CM configuration can be used only for suborbital flights and has an estimated empty mass of not more than 1250 kg.
[edit] Low apogee orbital configuration
The low apogee orbital configuration is the simplest non-trivial hardware configuration and consists of a Command Module mated to an Orbital Support Module. The configuration is denoted by OSM-CM.
The OSM-CM configuration can be used for orbital flights with sufficiently low apogees that the configuration can be inserted directly by its launch vehicle (around 200 km above the Earth's surface). Depending on whether or not the OSM is filled with extra consumables, this configuration can have an endurance of 24 hours (relying on CM consumables alone) or around 7 days (using OSM extra consumables).
[edit] High apogee orbital and circumlunar configuration
The high apogee orbital and circumlunar configuration consists of a Command Module mated to an Orbital Support Module, mated to a Propulsion Module of the Light variety. The configuration is denoted by PML-OSM-CM.
The PML-OSM-CM configuration can be used for orbital flights with very high apogees, including flights which travel far enough from Earth (around 300,000 km) to engage in circumlunar flights. Such flights are achieved by having a launch vehicle place the configuration into a LEO parking orbit (around 200 km above the Earth's surface), and then using the Propulsion Module to increase the apogee. This configuration has an endurance of around 7 days (using OSM extra consumables).
[edit] Lunar landing configuration
The lunar landing configuration is identical to the high apogee orbital and circumlunar configuration with the Light Propulsion Module replaced by a Heavy Propulsion Module, and with a Lunar Lander mated to the front of the CM. The configuration is denoted by PMH-OSM-CM-LL.
The PMH-OSM-CM-LL configuration can be used for manned lunar landing flights. The configuration is placed into a LEO parking orbit (around 200 km above the Earth's surface) by its launch vehicle. The PMH is then used to place the configuration on a free-return translunar trajectory, and then used again to insert the configuration into a lunar orbit. The LL detaches from the CM, descends to the lunar surface and then ascends, using its own engine. The PMH then carries the PMH-OSM-CM sub-configuration out of lunar orbit and on a trajectory back to Earth, the LL being left in lunar orbit.
[edit] Unmanned Lunar landing configuration
For missions that will not be carrying a human to the surface of the moon a simpler version of the stack may be used that permits the lower launch mass. In this configuration the stack would consist of the PHM-LL. The amount of propellant and the mass of the lander's payload depend on weather it is a sample return mission or not.
