Spacecraft Docking Connector with Thruster Piston
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current structural, fluid, and electrical connectors for spacecraft modules are inflexible and costly, requiring significant rework for design changes and lacking the ability to function as both a docking interface and propulsion thruster.
Innovation Solution
A connector interface featuring male and female valve assemblies with retractable pistons and O-rings for fluid and electrical connections, capable of forming a structural connection and functioning as a propulsion thruster when not mated, utilizing a combination of mechanical, pneumatic, and electromagnetic actuation for extension and retraction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If custom designed spacecraft with box-like modules and complex wiring harnesses are used, then single spacecraft function is provided, but design flexibility and adaptability are lost requiring significant rework for design changes
Solution Approach 1:
The patent applies universality by designing a standardized interface connector that can serve multiple functions: structural connection, fluid transfer, and electrical connection. This single multi-functional interface replaces the need for separate connectors and complex wiring harnesses, enabling the same hardware platform to be adapted for different missions by simply changing the modules connected through the universal interface.
Solution Approach 2:
The patent segments the spacecraft into modular components (propulsion module, payload module, etc.) that can be independently designed, manufactured, and connected through standardized interfaces. This segmentation allows individual modules to be replaced or reconfigured without affecting the entire system, providing design flexibility while maintaining system reliability.
2Ease of manufacture
If modular spacecraft with standard interfaces are used, then multi-use designs and mass production are enabled reducing cost, but interface connector complexity increases to handle structural, fluid, and electrical connections
Solution Approach 1:
The patent merges structural connection, fluid transfer, and electrical connection functions into a single integrated interface connector. This consolidation reduces the total number of components and connection points needed, simplifying the overall system while maintaining all necessary functions. The unified interface is easier to manufacture and assemble compared to multiple separate connectors.
Solution Approach 2:
The interface connector is designed as a universal multi-functional component that handles structural loads, fluid transfer, and electrical connections simultaneously. This universal design enables mass production of standardized modules that can be assembled into different spacecraft configurations, reducing development costs while managing complexity through standardization.
3Productivity
If homogeneous cells with all spacecraft sub-system capabilities are combined, then mass production savings and rapid assembly are achieved, but substantial redundancy increases costs
Solution Approach 1:
The patent segments spacecraft functions into standardized homogeneous cells that can be rapidly assembled through common interfaces. Each cell contains necessary sub-systems and connects to others via universal connectors, enabling quick assembly of different spacecraft configurations from the same modular building blocks, thus improving productivity.
Solution Approach 2:
The modular homogeneous cell design allows for easy replacement of individual cells if they fail or need upgrading. Instead of redesigning the entire spacecraft, individual cells can be discarded and replaced with new or upgraded modules, reducing long-term costs despite initial redundancy.
4Force
If pyrotechnically actuated clamp bands and separation bolts are used for structural connection, then load transfer capability is provided, but separation reliability and precision are compromised
Solution Approach 1:
The patent replaces pyrotechnic separation mechanisms with a mechanically actuated piston system. The piston can be precisely controlled to push the male connector away from the female connector for separation, or pushed in to form a rigid structural connection. This mechanical substitution provides both strong load transfer capability and reliable, precise separation control without the unpredictability of pyrotechnics.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
Enables flexible and cost-effective interconnection of spacecraft modules with improved structural integrity, allowing for easy docking and separation in space, and providing both fluid and electrical connectivity while functioning as a propulsion thruster when needed.
Implementation Method 1
one or more O-rings positioned around the piston for forming a fluid tight seal within the central bore's cylindrical surface
Implementation Method 2
the distal end of the piston's central conduit projects distally from the central bore's distal end. Further, the piston conduit's distal end is preferably formed to provide a divergent nozzle
Implementation Method 3
the position of the piston is controlled by a helical spring, pneumatic extension and electromagnetic retraction
Data Source
Figure 1
Figure 2~3
Figure 4~5
AI summary
An interface connector is provided for connecting homogenous spacecraft cells. The interface connector includes at least one male valve assembly and at least one female valve assembly. The male valve assembly includes an extendable and retractable piston having a central conduit. The female valve assembly has a central bore closed by a ball valve. Preferably, the male and female valves are positioned so that extension of the piston engages the ball valve so as to create a fluid pathway. Various components in the male and female valve assemblies are electrically conductive to allow the transmission of power and data. Further, the male valve assembly is constructed to function as a propulsion thruster when not mated to a female valve assembly.