| 摘要 |
The invention provides a variable length mission-configurable module (30) that can be readily reconfigured to meet the specific pressurized space and payload requirements for a wide variety of Earth orbit missions. The module system includes a plurality of truncated body portions (34), a substantially flat forward bulkhead (32), and a substantially flat aft bulkhead (40). The plurality of truncated body portions (34) and bulkheads (32 and 40) are coupled together, wherein the forward bulkhead (32) is located at a front end of a line of coupled truncated body portions (34), and the aft bulkhead (40) is located at an aft end of the coupled truncated body portions. The number of truncated body portions (34), employed can be readily varied to adjust the overall length, pressurized volume and payload capabilities of the module system to specific mission requirements.
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