Optimization of a Nutation Damper Attached to a Spin-Stabilized Satellite.

Abstract

This study uses linearized equations of motion for a rigid body with an attached spring-mass-damper to maximize the decay rate of a satellite's coning motion. An analysis of the numerical eigenvalues is presented which leads to an optimal relationship between relevant parameters: damper placement, spring constant, damping coefficient, system moments of inertia, and damper mass fraction. The coupled system's eigenvalues do not provide truly critical damping, thus the real eigenvalue parts are minimized in order to achieve damping which requires the minimum amount of time. A comparison between this optimal design method and a classical method concludes a noticeable improvement in damping performance for optimized systems.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1994
Accession Number
ADA289424

Entities

People

  • Brady P. Hauboldt

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Air Force
  • Angular Momentum
  • Artificial Satellites
  • Coefficients
  • Computer Programs
  • Control Systems
  • Eigenvalues
  • Equations
  • Equations Of Motion
  • Linear Momentum
  • Mathematical Analysis
  • Moment Of Inertia
  • Momentum
  • Numerical Analysis
  • Optimization
  • Payload
  • Resonant Frequency

Readers

  • Control Systems Engineering.

Technology Areas

  • Space
  • Space - Orbital Debris
  • Space - Spacecraft Maneuvers