Satellite Stacking Interfaces for Launcher Weight Reduction
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Solution Overview
Problem
Current satellite launch systems face challenges in securely holding and stacking satellites due to excessive impacts and vibrations, with existing solutions being bulky, weight-intensive, and not optimized for space usage within launchers, limiting the number of satellites that can be launched and compromising mechanical strength and equipment protection.
Innovation Solution
A satellite design featuring a cylindrical main body with standard diameters for direct attachment to launchers, incorporating both internal and external equipment, and a clamp band system for stacking, optimizing space usage and mechanical strength while simplifying installation and manufacturing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If satellites are connected to a central dispenser structure with housings, then satellites are supported and protected during launch, but the structure becomes bulky and increases launcher weight
Solution Approach 1:
The patent removes the central dispenser structure and its housings entirely, extracting the satellite support function to the satellites themselves through stacking interfaces. This eliminates the bulky central structure and reduces launcher weight while maintaining satellite support during launch.
Solution Approach 2:
Satellites support each other through dedicated stacking interfaces built into their own structures. The top satellite supports itself and lower satellites through its interface, eliminating the need for an external dispenser structure. This self-service approach reduces overall system weight.
2Reliability
If a central dispenser structure with housings is used, then satellites are held securely, but the number of satellites that can be installed is limited by nosecone space
Solution Approach 1:
By removing the central dispenser structure, the patent frees up nosecone space that was previously occupied by the dispenser and its housings. This allows more satellites to be stacked vertically within the same nosecone volume, increasing productivity.
Solution Approach 2:
The patent transitions from a horizontal arrangement (satellites on shelves in a dispenser) to a vertical stacking arrangement. This dimensional change optimizes space utilization in the nosecone, allowing more satellites to be accommodated in the vertical dimension.
3Volume of moving object
If satellites are stacked one on top of another with dedicated interface structures, then space is optimized, but the interface structure diameter must be larger than standard launcher interface diameters
Solution Approach 1:
The patent introduces an adapter ring as an intermediary component between the satellite stacking interface and the launcher interface ring. This adapter enables compatibility between different diameter interfaces, allowing standard launcher interfaces to work with optimized satellite stacking structures.
4Strength
If the dedicated structure diameter is greater than standard launcher interface diameters, then satellite stacking is enabled, but an intermediate support must be placed between satellite and launcher ring
Solution Approach 1:
The adapter ring serves as a simple intermediary component that bridges the diameter mismatch between satellite stacking interfaces and launcher interface rings. This single component solution maintains mechanical strength while avoiding complex multi-component assemblies.
5Object-affected harmful factors
If satellites are supported by a dispenser structure, then impacts and vibrations are managed, but the structure is bulky and weight-intensive
Solution Approach 1:
The patent removes the bulky dispenser structure entirely and extracts the vibration and impact management function to the satellite stacking interfaces themselves. The stacked satellites support each other, managing forces without requiring heavy external structures.
Solution Approach 2:
The patent employs composite structures in the satellite stacking interfaces that provide high strength-to-weight ratios. These interfaces manage impacts and vibrations effectively while minimizing weight, replacing heavy metal dispenser structures with optimized composite materials.
Data Source
AI summary
Disclosed is a satellite including a cylindrical main body, the main body having an inner wall defining an inner space and an outer wall, and extending along a main axis between a lower end surface and an upper end surface, at least one of the lower end surface and the upper end surface including an interface mechanism intended for engaging with a complementary interface mechanism of another satellite or of a launcher, the satellite also including at least one external device attached to the outer wall of the main body, the outer device extending to project transversely from the outer wall relative to the main axis.