Spacecraft Appendage Identification via FPGA Texture Analysis
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Solution Overview
Problem
Current docking technologies for spacecraft face challenges in accurately differentiating between spacecraft appendages and the primary body, especially when dealing with unknown spacecraft structures, which can lead to catastrophic collisions during docking maneuvers.
Innovation Solution
The system employs a combination of cameras, a field programmable gate array (FPGA), and a processor to generate texture maps from image pixel streams, allowing for the detection and differentiation of spacecraft appendages from the primary body by determining the bus centroid of the spacecraft.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If fiducials, model libraries, or neural networks are used to identify spacecraft structure, then docking accuracy is improved, but the system requires a-priori knowledge of the subject spacecraft structure which limits adaptability to unknown spacecraft
Solution Approach 1:
The system performs self-identification of spacecraft structure by automatically analyzing image data to distinguish the spacecraft body from appendages without requiring pre-programmed knowledge or training data. The algorithm autonomously determines the bus centroid and structural configuration through real-time image processing, enabling the docking system to adapt to any spacecraft design independently.
Solution Approach 2:
The system changes the approach from using fixed structural models to dynamically analyzing image parameters such as texture, intensity, and geometric features. By processing image pixel streams and extracting structural parameters in real-time, the system adapts to different spacecraft configurations without requiring a-priori knowledge, resolving the contradiction between measurement precision and adaptability.
2Measurement precision
If complex image processing algorithms are used to distinguish appendages from spacecraft body, then identification accuracy is improved, but processing time and computational complexity increase
Solution Approach 1:
The image processing is segmented into distinct functional stages: initial image acquisition, dynamic range compression, texture map generation, thresholding, and centroid calculation. Each stage processes only the necessary data for its specific purpose, avoiding redundant computations and reducing overall processing time while maintaining high identification accuracy through focused analysis at each step.
Solution Approach 2:
The system performs partial processing by focusing computational resources on the most discriminative features for appendage detection, such as texture variations and intensity gradients near the spacecraft body. Rather than processing entire images at full resolution, the algorithm applies targeted processing only to regions containing potential appendages, significantly reducing computation time while preserving identification accuracy.
Data Source
AI summary
An apparatus for controlling docking with a spacecraft includes at least one camera for generating at least one image pixel stream of the spacecraft. A field programmable gate array (FPGA) receives the at least one image pixel stream from the at least one camera, compresses a dynamic range of the at least one image pixel stream and detects a sub-region from the at least one image pixel stream having a compressed dynamic range, processes the at least one image pixel stream to generate at least one texture map for the at least one image pixel stream. A processor receives the at least one texture map from the FPGA, generates thresholding results for each of the at least one image pixel stream responsive to the generated at least one texture map, clusters and downsamples the generated thresholding results, fuses each of the thresholding results for the at least one image pixel stream to create fused thresholding results, determines a bus centroid of the spacecraft responsive to the generated fused thresholding results and outputs the determined bus centroid of the spacecraft.