Motorized Marman Ring Clamp for Satellite Retrofitting
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Solution Overview
Problem
Satellite operations and design are costly and labor-intensive, leading to outdated technology in orbit due to long lifespans and high asset costs, hindering technological advancement and new business models, with traditional satellite designs being one-off or series-specific and lacking easy upgrade capabilities.
Innovation Solution
A clamp mechanism with a baseplate, motor, and drive assembly that translates linear motion axes to contract tooth assemblies onto a Marman ring, providing secure attachment for components like enhancement modules, enabling retrofitting and life extension of satellites.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional satellite design methods are used with one-off or series-specific designs, then satellites can serve specific mission objectives, but they cannot be easily upgraded with other components and technology lags behind terrestrial capabilities
Solution Approach 1:
The clamp mechanism is designed with a universal interface that can attach to standard satellite structures (such as Marman rings) and accommodate various components including enhancement modules, sensors, and other payloads. This universal design enables a single satellite platform to serve multiple mission objectives through component interchangeability, resolving the contradiction between adaptability and design complexity.
Solution Approach 2:
The satellite system is segmented into a core platform and interchangeable component modules. The clamp mechanism serves as a standardized interface that separates the permanent satellite structure from upgradeable components, allowing independent development and testing of components before integration. This segmentation enables easier upgrades without redesigning the entire satellite system.
2Duration of action of stationary object
If satellites are designed with long lifespans to amortize high asset and launch costs, then return on investment is improved, but technology in orbit significantly lags terrestrial capabilities
Solution Approach 1:
The satellite system transitions from a static, fixed-configuration design to a dynamic, reconfigurable platform. The clamp mechanism enables components to be added, removed, or replaced during the satellite's operational lifetime, allowing the system to adapt to evolving technological requirements while maintaining the long lifespan needed for economic viability.
Solution Approach 2:
Standardized clamp interfaces and mounting structures are pre-integrated into the satellite design at the outset. This preliminary preparation of attachment infrastructure enables future component upgrades without requiring structural modifications, thus maintaining both long lifespan and technological currency throughout the satellite's operational life.
3Ease of manufacture
If satellites are launched with fixed hardware technology capability, then asset costs are controlled, but new innovative business models become economically infeasible
Solution Approach 1:
The satellite system is divided into a core platform with standardized attachment interfaces and interchangeable functional components. This segmentation allows the core platform to be manufactured once at controlled cost, while different component combinations can be configured for various business applications, enabling multiple revenue streams without proportionally increasing manufacturing costs.
Solution Approach 2:
The standardized clamp mechanism creates a universal platform that can support multiple business models and applications. A single satellite platform can be configured for different missions by swapping components, allowing operators to maximize asset utilization and generate revenue from diverse services, thus making innovative business models economically feasible.
4Ease of operation
If traditional satellite operations are used without independent attachment interfaces, then satellite design is simplified, but components cannot be easily attached or upgraded on-orbit
Solution Approach 1:
The clamp mechanism is designed to be self-contained with integrated actuation and locking features that automatically secure components to the satellite structure. The mechanism includes self-aligning features and automated fastening that reduce the need for complex external attachment systems or manual intervention, thus improving ease of operation while controlling complexity.
Data Source
AI summary
A clamp for attachment to a satellite, wherein the satellite is without an independent attachment interface for receiving the clamp, comprising a baseplate for attachment to the component, a motor and a drive assembly, a linear motion axis, a stop, a first tooth assembly and a second tooth assembly, and wherein, actuation of the motor and the drive assembly translates the linear motion axis such that at least one of the first tooth assembly and second tooth assembly contract to clamp on to a Marman ring on the satellite. The tooth assemblies may be combinations of rigid teeth and camming teeth which pivot to secure and pull the clamp orthogonal to the contracting direction and towards the Marman ring.