Spacecraft Reprovisioning Subassembly for Life Extension
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Solution Overview
Problem
Current spacecraft operational lives are limited by fuel availability and propulsion system failures, leading to premature disposal, with existing refueling and life extension methods being technically risky and economically constrained.
Innovation Solution
A reprovisioning subassembly system for spacecraft, comprising a fuel tank, mating interface, control electronics, and thruster unit, allowing for robotic attachment and detachment, maintaining the spacecraft's center of mass and enabling fuel flow activation and control, thereby extending operational life without dedicated life extension vehicles.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If refueling is performed using robotic interfaces, then fuel can be replenished to extend operational life, but the process becomes technically risky due to potential leakage and attitude destabilization
Solution Approach 1:
The system divides the refueling operation into separate functional components: a servicing vehicle carrying fuel tanks and a client spacecraft with fuel receptacles. The fuel transfer is segmented into discrete operations through standardized interfaces, allowing the fueling process to be broken into manageable steps that reduce risk compared to continuous manual refueling operations.
Solution Approach 2:
The patent introduces a dedicated servicing vehicle as an intermediary between fuel storage and the client spacecraft. This vehicle acts as a mediator that safely handles fuel transfer operations, isolating the risks from the client spacecraft and providing a controlled interface for fuel replenishment without requiring direct robotic manipulation of the client's fuel system.
2Duration of action of moving object
If a parasitic repositioning vehicle is used to extend operational life, then fuel functionality is restored, but the system complexity increases due to the dedicated vehicle requirement
Solution Approach 1:
The servicing vehicle is designed with universal, standardized mating interfaces that can service multiple different client spacecraft types. This multi-functionality allows a single vehicle design to extend the operational life of various spacecraft without requiring custom parasitic attachments for each client, thereby reducing overall system complexity while maintaining the life extension capability.
Solution Approach 2:
The system employs dynamic attachment and detachment capabilities where the servicing vehicle can connect to and disconnect from client spacecraft as needed. This dynamic operation allows the vehicle to service multiple clients sequentially rather than remaining permanently attached to one spacecraft, reducing the complexity burden on any single client vehicle while maintaining extended operational capability.
3Extent of automation
If robotic attachment and detachment interfaces are implemented, then reprovisioning operations can be automated, but the manufacturing precision requirements increase
Solution Approach 1:
The patent employs parameter changes in the form of standardized interface specifications that define mechanical, electrical, and operational parameters for the mating interfaces. By establishing fixed parameter ranges and tolerances for these interfaces, the system enables automated robotic operations while managing manufacturing precision requirements through standardized design criteria rather than custom high-precision requirements for each interface.
Data Source
AI summary
A reprovisionable spacecraft and reprovisioning subassemblies for mating with a reprovisionable spacecraft are both described. The reprovisionable spacecraft has one or more mechanical, thermal, data, and or electrical mating interfaces for attaching, powering, and communicating with a reprovisioning subassembly, which for one embodiment is a self-contained thruster unit. The self-contained thruster unit preferably comprises a fuel tank, control electronics, and a thruster assembly. Alternately, a reprovisioning subassembly can comprise a fuel tank and control electronics, a fuel tank, or a thruster. Also, a reprovisionable spacecraft may be carried into orbit without reprovisioning subassemblies attached, and then deployed after reprovisioning subassemblies have been attached to their respective mating interfaces. Reprovisioning utilizing a self-contained thruster unit or tank eliminates the large risk associated with refueling satellites in space. Reprovisioning also eliminates the need for a dedicated attached life extension vehicle.