Self-Assembling Spacecraft Modules for Launch Optimization
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Solution Overview
Problem
The high cost and complexity of geosynchronous orbit (GEO) spacecraft, combined with the need for long-term operation and adaptability to changing market demands, pose challenges in maximizing revenue from limited orbital slots and maintaining compatibility with conventional launch vehicles.
Innovation Solution
A self-assembling spacecraft composed of deployable modules that can reconfigure from a launch to an on-orbit configuration using a robotic manipulator, allowing for interchangeable payload and bus service modules, enabling efficient use of launch vehicle fairing space and extending the operational life of the bus services module while allowing for payload module replacement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If spacecraft are made larger and more complex to maximize revenue from limited GEO slots, then payload throughput and power increase, but cost and difficulty of manufacture increase substantially
Solution Approach 1:
The spacecraft is divided into a bus module and multiple interchangeable payload modules that can be independently manufactured, tested, and deployed. This segmentation allows the bus services to be reused across multiple payload modules, reducing overall system complexity and cost while maintaining high payload throughput capability.
Solution Approach 2:
The bus module is designed with universal interfaces and standardized mounting mechanisms that can accommodate different types of payload modules. This multi-functionality allows a single bus platform to support multiple revenue-generating payloads, maximizing revenue from limited GEO slots without proportionally increasing complexity.
2Ease of manufacture
If spacecraft are configured for launch within fairing envelope constraints, then compatibility with conventional launch vehicles is maintained, but the spacecraft must be reconfigured from launch to on-orbit configuration
Solution Approach 1:
The modular architecture allows the spacecraft to be segmented into compact modules for launch, then reconfigured in orbit by assembling the modules into their operational configuration. This segmentation enables compatibility with conventional launch vehicle fairings while simplifying the reconfiguration process through standardized mechanical and electrical interfaces.
Solution Approach 2:
The payload modules are pre-configured and tested independently before integration with the bus module. This preliminary preparation reduces on-orbit reconfiguration complexity by eliminating the need for complex in-space manufacturing or debugging, allowing straightforward assembly once in orbit.
3Duration of action of stationary object
If payload modules are designed for long-term operation, then spacecraft can operate for 15 years or more, but payload technology may become obsolete before bus equipment reaches end-of-life
Solution Approach 1:
By segmenting the spacecraft into a long-lived bus module and replaceable payload modules, the system allows payload technology to be updated independently of the bus infrastructure. When payload technology becomes obsolete, only the payload module needs replacement, not the entire spacecraft, thus maintaining adaptability while achieving long-term operation.
Solution Approach 2:
The modular design enables the recovery and reuse of the bus module and its services after a payload module completes its mission. The bus infrastructure can be retained and reused with new payload modules, maximizing the value of long-term investments while staying current with evolving payload technology.
Data Source
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AI summary
A spacecraft (100) includes a plurality of deployable module elements (110), at least one of the deployable module elements including a robotic manipulator (150), the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.