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Common Frame Dynamics for Conically-Constrained Spacecraft Attitude Control.

Arnold Christopher Cruz1, Ahmad Bani Younes1

  • 1Department of Aerospace Engineering, San Diego State University, San Diego, CA 92182-1308, USA.

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PubMed
Summary
This summary is machine-generated.

This study introduces a common frame dynamics approach for spacecraft attitude control with pointing constraints. This method reduces control effort for spacecraft rotation, enhancing mission capabilities.

Keywords:
attitude controlcommon frame dynamicsconstrained controllyapunov control

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Area of Science:

  • Spacecraft dynamics and control
  • Robotics and autonomous systems
  • Astrodynamics

Background:

  • Spacecraft missions require precise attitude control to avoid damage to sensitive equipment (exclusion zones) and maintain communication/power (inclusion zones).
  • Existing constrained attitude control techniques often operate in non-intuitive reference frames.
  • Modified Rodrigues Parameters (MRPs) are a common representation for spacecraft attitude.

Purpose of the Study:

  • To derive and implement common frame dynamics for spacecraft attitude control under static and dynamic conic pointing constraints.
  • To improve the efficiency and reduce the control effort of constrained attitude control systems.
  • To validate the proposed method using Lyapunov stability analysis and numerical simulations.

Main Methods:

  • Derivation of common frame dynamics using Modified Rodrigues Parameters.
  • Application of Lyapunov methods to redevelop kinematic steering laws and servo subsystems.
  • Implementation of a novel constrained attitude control technique in the common frame.
  • Numerical simulations and Monte Carlo analysis to assess performance and convergence.

Main Results:

  • The common frame dynamics approach successfully handles both static and dynamic conic constraints.
  • A significant decrease in control effort (torque) was observed compared to the original frame dynamics.
  • Monte Carlo simulations confirmed the convergence and robustness of the control system under perturbations.
  • The method demonstrated effective tracking for both static and dynamic constrained problems.

Conclusions:

  • Common frame dynamics offer a more efficient approach to spacecraft attitude control with pointing constraints.
  • The developed technique enhances mission reliability by minimizing control effort and improving pointing accuracy.
  • This work provides a valuable framework for designing future spacecraft attitude control systems with complex constraints.