ISS Robotic Airlock Interface for External Payload Deployment

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Solution Overview

Problem

The demand for external payload sites on the International Space Station (ISS) has exceeded available opportunities, and the end of the station's life poses a challenge for continued commercial investment, necessitating a solution to expand payload capacity and leverage resources for future low-Earth orbit operations.

Innovation Solution

A spacecraft airlock system that can be robotically attached to the ISS, utilizing Common Berthing Mechanisms (CBM) sites for enhanced power, thermal management, and data services, allowing robotic deployment and installation of payloads without astronaut spacewalks, and providing additional Flight Releasable Attachment Mechanism (FRAM) sites.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If additional FRAM sites are added to the ISS, then the capacity for external payload deployment is improved, but the device complexity and resource requirements increase

Engineering Contradiction:

Improvecapacity for external payload deploymentVSAvoiddevice complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The airlock mechanism is nested within the pressurized module structure, with the payload deployment system contained within the airlock volume. This nesting approach allows multiple functions (payload storage, depressurization, deployment) to be integrated in a compact configuration, adding payload capacity without proportionally increasing overall system complexity

Inventive Principle:

Principle #7Nested doll (Nesting)

Solution Approach 2:

The airlock mechanism serves multiple functions: it acts as a payload deployment system, a transfer chamber between pressurized and vacuum environments, and a platform for multiple FRAM sites. This multi-functionality allows a single added component to provide numerous payload deployment capabilities rather than requiring separate systems for each function

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Extent of automation

If a robotic airlock system is implemented, then crew time is reduced and automation is improved, but the device complexity increases

Engineering Contradiction:

Improverobotic operation capabilityVSAvoiddevice complexity

Core Design Contradiction:

Extent of automationVSDevice complexity

Solution Approach 1:

The airlock mechanism is designed with automated robotic interfaces that can perform payload installation, depressurization, and deployment operations autonomously. The system includes self-contained control systems, automated latching mechanisms, and integrated sensing that allow the airlock to service itself and deploy payloads without requiring extensive crew intervention, thereby reducing operational complexity despite added automation capabilities

Inventive Principle:

Principle #25Self-service

Solution Approach 2:

Manual mechanical operations previously requiring astronaut EVA are replaced with robotic manipulation systems. The robotic interface uses automated grapple fixtures, robotic arms, and programmable control systems to perform tasks that would otherwise require human manual operation, reducing crew time and risk while managing complexity through standardized robotic interfaces

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

3Quantity of substance

If the airlock is designed to accommodate larger satellites, then the payload capacity is improved, but the volume and mass of the airlock increase

Engineering Contradiction:

Improvepayload capacityVSAvoidairlock volume

Core Design Contradiction:

Quantity of substanceVSVolume of stationary object

Solution Approach 1:

The airlock mechanism incorporates deployable structures and expandable volume configurations that allow it to accommodate larger satellites when needed while maintaining a compact stowed configuration during normal operations. The system can dynamically adjust its internal volume through deployable panels, extendable arms, or reconfigurable internal structures, providing large payload capacity on demand without permanently increasing the airlock's baseline volume and mass

Inventive Principle:

Principle #15Dynamics

Data Source

PatentUS12630311B2Spacecraft systems airlock for international space station access and interface and methods of operation

Publication Date: 2026.05.19 NANORACKS LLC

AI summary

Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station. The spacecraft airlock system provides a defined volume of space payload to the international space station. The airlock further includes a means of attaching to a space station, a closed structure attached to said means, said means of attaching is capable of robotic manipulation, and a cooling system for cooling payload components within said closed structure.