Accession Number:

AD0875403

Title:

Synthesis of a Suboptimal Guidance Law to Minimize the Terminal Error of an Entry Vehicle

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING

Report Date:

1970-06-01

Pagination or Media Count:

184.0

Abstract:

The purpose of this thesis is to use the concept of minimizing position sensitivity coefficients to minimize the terminal position error of an entry vehicle. Modern control theory is applied to the problem with a lumped parameter control which includes vehicle design parameters. A simulation including a Kalman filter is used to validate the feedback scheme obtained. The minimum sensitivity coefficient trajectory obtained is one which is dominated by lift such that it levels out to nearly horizontal flight and then dives to the desired terminal conditions. The simulation results, using both observation noise and initial condition errors, confirm the concept of minimizing sensitivity coefficients since the terminal position error is the least susceptible to initial condition errors.

Subject Categories:

  • Guided Missile Dynamics, Configurations and Control Surfaces
  • Spacecraft Trajectories and Reentry

Distribution Statement:

APPROVED FOR PUBLIC RELEASE