Spacecraft Panel Bracket Assembly for Repeatable AI&T Reinstallation
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Solution Overview
Problem
Existing spacecraft platforms made of aluminum honeycomb panels and embedded inserts are insufficiently durable for space operations, lacking consistency and reliability, and require improved structural stability and flexibility for Assembly, Integration, and Testing (AI&T) with easy access to internal units.
Innovation Solution
A spacecraft platform structure using panel interconnect (PIC) bracket assemblies with U-clip portions and flange plates, bonded to panel face sheets, and secured by fasteners, allowing for stress-free assembly, repeatable installation, and easy access to internal units through three-point support and expansion pins.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If aluminum honeycomb panels with embedded inserts are used for spacecraft platforms, then the structure provides basic mounting capability, but the durability and reliability are insufficient for rigorous space environmental demands
Solution Approach 1:
The patent employs a composite structure combining aluminum honeycomb panels with titanium inserts and stainless steel brackets. This multi-material approach leverages the lightweight properties of aluminum honeycomb while incorporating the superior strength and durability of titanium and stainless steel components, resolving the contradiction between basic mounting capability and insufficient durability for space environments.
Solution Approach 2:
The platform is divided into modular panels with standardized titanium inserts embedded at regular intervals. This segmentation allows for systematic reinforcement throughout the structure, enabling consistent durability across the entire platform while maintaining the lightweight honeycomb core structure.
2Reliability
If traditional embedded inserts and honeycomb panels are used, then the platform provides basic structural support, but the consistency and reliability under unique space conditions remain undefined
Solution Approach 1:
The patent establishes a universal platform architecture with standardized titanium inserts and bracket assemblies that can be consistently applied across all panels. This universality ensures repeatable assembly procedures and consistent structural performance under space conditions, addressing the need for defined reliability through standardized manufacturing and assembly processes.
Solution Approach 2:
The invention specifies precise geometric parameters for the titanium inserts (e.g., 0.250 inches by 0.250 inches cross-section, specific embedment depths) and bracket dimensions. These controlled parameters ensure manufacturing precision and assembly consistency, enabling reliable reproduction of the platform structure across multiple units while maintaining defined performance characteristics.
3Strength
If the platform structure is made strong and stable, then structural integrity is improved, but flexibility for accessing internal units during AI&T is reduced
Solution Approach 1:
The patent implements a dynamic assembly approach where panels are temporarily secured with brackets during AI&T operations, allowing easy access to internal units. Once testing is complete, the same brackets provide permanent structural reinforcement. This dynamic functionality resolves the contradiction between needing structural strength and requiring operational flexibility during different mission phases.
Solution Approach 2:
The titanium inserts serve as intermediary elements that facilitate both structural connection and operational access. During AI&T, panels can be accessed through the standardized insert locations without compromising overall structural integrity. The inserts mediate between the need for strong panel connections and the requirement for easy internal unit accessibility during testing operations.
Data Source
AI summary
Systems, methods, and bracket assemblies for a stable and repeatable spacecraft platform structure are provided. The method includes: providing a plurality of panel interconnect (PIC) bracket assemblies for connecting first and second adjacent platform panels; supporting and aligning the first and second platform panels in a vertical configuration using three points of support; installing the PIC bracket assemblies between the first and second platform panels; co-drilling a subset of the PIC bracket assemblies to establish co-drilled holes that traverse the first and second bracket; disassembling the bolted interfaces of PIC bracket assemblies to remove the first or second platform panel; and reinstalling the first or second panel using an expansion pin in the co-drilled holes to return the first or second platform panel to its quasi 0 G shape.