Control of Spinning Symmetric Airframes

Abstract

Several missiles and projectiles have periods during their flight where the body is spinning and must be controlled. It has been stated that a roll stabilized autopilot may be more appropriate during this phase of the flight. This paper first examines the full nonlinear equations of motion in both the roll stabilized frame and the body axis system assuming a rigid axially symmetric body. Two and three loop autopilots are developed using an optimal control approach for a non-rolling airframe. These autopilots are examined to determine how well they are able to follow inertial commands. An extremely simplified example is presented so that the basic characteristics of the closed loop system can be examined. The results are presented and conclusions drawn. Effects of different acceleration levels, including the axial moment of inertia and very high roll rates are examined.

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Document Details

Document Type
Technical Report
Publication Date
Nov 14, 2006
Accession Number
ADA466818

Entities

People

  • Curtis P. Mracek
  • Max Stafford
  • Mike Unger

Organizations

  • Raytheon Missiles & Defense

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Airframes
  • Angular Momentum
  • Automatic Pilots
  • Bandwidth
  • Closed Loop Systems
  • Coordinate Systems
  • Deflection
  • Equations
  • Equations Of Motion
  • Frequency
  • Inertial Measurement Units
  • Linear Momentum
  • Moment Of Inertia
  • Momentum
  • Nonlinear Dynamics
  • Simulations
  • Transfer Functions

Fields of Study

  • Physics

Readers

  • Control Systems Engineering.