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A novel multi-aperture based sun sensor based on a fast multi-point MEANSHIFT (FMMS) algorithm.

Zheng You1, Jian Sun, Fei Xing

  • 1State Key Laboratory of Precision Measurement Technology and Instruments, Department of Precision Instruments and Mechanology, Tsinghua University, Beijing 100084, China. yz-dpi@mail.tsinghua.edu.cn

Sensors (Basel, Switzerland)
|December 14, 2011
PubMed
Summary
This summary is machine-generated.

A new multi-aperture sun sensor for micro/nanosatellites offers high accuracy and reliability. Its novel algorithm achieves 0.01 pixel centroid accuracy, outperforming conventional methods for small satellite attitude determination.

Keywords:
APS sun sensormulti-aperturemulti-point MEANSHIFT algorithm

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Area of Science:

  • Spacecraft engineering
  • Attitude determination and control systems
  • Micro/nanosatellite technology

Background:

  • Star trackers are unsuitable for micro/nanosatellites due to size and weight.
  • Conventional sun sensors lack the accuracy required for micro/nanosatellite attitude determination.
  • There is a significant need for small, high-accuracy, and reliable sun sensors for small satellites.

Purpose of the Study:

  • To develop a small, high-accuracy, and reliable sun sensor for micro/nanosatellites.
  • To introduce a novel algorithm for improving sun sensor performance.
  • To address the limitations of existing attitude determination systems in small spacecraft.

Main Methods:

  • Design of a multi-aperture sun sensor using a MEMS mask with 36 apertures and an APS CMOS detector.
  • Development and application of a novel fast multi-point MEANSHIFT (FMMS) algorithm for analyzing sun spot array images.
  • Derivation of sun angles by analyzing aperture image locations on the detector.

Main Results:

  • Achieved a centroid accuracy of 0.01 pixels for the sun image, a significant improvement over conventional methods (0.05 pixels).
  • Demonstrated high reliability and accuracy even with missing apertures or bad pixels.
  • Maintained performance without increasing weight or power consumption.

Conclusions:

  • The multi-aperture sun sensor with the FMMS algorithm meets the demanding requirements of micro/nanosatellite attitude determination.
  • This technology provides a viable and superior alternative to traditional attitude sensors for small spacecraft.
  • The sensor's robustness ensures reliable operation in harsh space environments.