Flexible Fuel Containers and Androgynous Coupling for Spacecraft Refueling
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Solution Overview
Problem
Existing space systems face limitations in fuel capacity due to size and cost constraints, leading to restricted mission lifetimes and capabilities, and refueling satellites is challenging due to complex and incompatible docking systems.
Innovation Solution
The development of spacecraft configured to transport, deliver, store, and process materials in space, including flexible container systems and androgynous coupling structures, enables efficient fuel management and refueling capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If spacecraft are launched with limited fuel capacity due to size and cost restrictions, then launch vehicle mass capacity is optimized, but mission lifetime and utility are reduced
Solution Approach 1:
The fuel supply system is segmented into multiple independent components: a launch vehicle with initial fuel, a space station with storage tanks, and flexible bladders for fuel transfer. This segmentation allows fuel to be supplied in stages rather than requiring all fuel to be launched at once, extending mission lifetime without proportionally increasing initial launch mass.
Solution Approach 2:
Fuel is preliminarily stored in the space station's storage tanks before the spacecraft needs it. The station receives and stores fuel in advance, then dispenses it to visiting spacecraft as needed. This preliminary action eliminates the need for each spacecraft to carry full mission-duration fuel supplies.
2Adaptability or versatility
If spacecraft are launched with full fuel capacity for entire mission lifetime, then mission utility is maximized, but launch cost and vehicle mass capacity are compromised
Solution Approach 1:
The space station serves multiple functions: it acts as a fuel storage depot, a refueling station for visiting spacecraft, and potentially a processing facility. This multi-functionality allows the system to support multiple missions and spacecraft types without requiring each to be independently fueled, reducing overall launch mass requirements.
Solution Approach 2:
The space station with its fuel storage tanks and dispensing systems acts as an intermediary between the launch vehicle and visiting spacecraft. Instead of direct fuel transfer from launch vehicle to spacecraft, the station mediates the fuel supply, allowing flexible refueling operations without compromising launch vehicle mass capacity.
3Ease of operation
If existing docking systems are used for refueling satellites, then refueling operations can be performed, but system complexity and incompatibility between satellites increase
Solution Approach 1:
The coupling structure is designed as a universal interface that can accommodate multiple spacecraft types and refueling operations. The standardized design with complementary docking elements allows different satellites to dock with the space station using the same interface, simplifying operations and reducing the need for multiple specialized docking systems.
Solution Approach 2:
The docking system uses asymmetric complementary elements (male and female coupling components) that provide unique, non-interchangeable connections. This asymmetry ensures proper alignment and connection while preventing incompatible dockings, simplifying the refueling operation by eliminating the need for complex compatibility checks between different satellite types.
Data Source
AI summary
Systems and methods for transferring, storing, and/or processing materials, such as fuel or propellant, in space, are disclosed. A representative system includes a flexible container that is changeable between a stowed configuration in which the flexible container is contained within a satellite, and a deployed configuration in which the flexible container extends away from the satellite. The system can include a tanker with a storage container to dock with and refuel a satellite. Another representative system includes a controller programmed with instructions that position a spacecraft with a storage container in a first orbit, transfer the spacecraft to a second orbit, dock the spacecraft with a satellite in the second orbit, transfer material between the storage container and the satellite, undock the spacecraft from the satellite, and, optionally, return the spacecraft to the first orbit. An androgynous coupling system with mechanical and fluid connectors facilitates docking and material transfer.