Mathematical Modelling of the Royal Aircraft Establishment (RAE) Lightweight Flexible Solar Array

Abstract

The paper describes the development of a mathematical model for the attitude dynamics of a spacecraft equipped with a lightweight flexible solar array. The theory has been developed using a continuous mechanics approach and a computer program prepared to generate the lateral bending modes of a spacecraft comprising a rigid central structure carrying a pair of solar arrays symmetrically situated about the central body. Furthermore, the program will generate the effective inertia and mass as a function of the forcing frequency. These are then formulated in the form of transfer functions which are more convenient for control problem analysis.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1974
Accession Number
ADA005265

Entities

People

  • R. N. A. Plimmer

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Artificial Satellites
  • Attitude Control Systems
  • Computer Programs
  • Computers
  • Control Systems
  • Coordinate Systems
  • Differential Equations
  • Equations
  • Frequency
  • Mechanics
  • Modulus Of Elasticity
  • Partial Differential Equations
  • Resonant Frequency
  • Scientific Satellites
  • Solar Panels
  • Spacecraft
  • Vibration

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Aerodynamics/Aeronautics.
  • Robotics and Automation.

Technology Areas

  • Space
  • Space - Spacecraft Maneuvers