Accession Number : AD0770082

Title :   Maximum Launch Range For an Air-to-Air Missile Employing Proportional Navigation for Guidance.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING

Personal Author(s) : Graves,Timothy J.

Report Date : JUN 1973

Pagination or Media Count : 66

Abstract : Optimal control theory is used to find the necessary conditions for maximizing the launch range of an air-to-air missile employing proportional navigation for guidance. Use of the first-order gradient technique provides an optimal solution for one- and two-dimensional intercept trajectories where thrust magnitude is the only control. A near-optimal, empirical method is developed and used for comparison. Results indicate that the launch range of the class of missiles considered is nearly insensitive to the thrusting schedule employed, suggesting that the low gain in launch range over present constant thrust methods may not warrant the increased complexity of an optimal design. Further, the results of the easier empirical method agree closely enough with the optimal method to suggest use of the empirical method in lieu of the gradient technique. (Author)

Descriptors :   (*Air to air missiles, Thrust), (*Aerial warfare, *Antiaircraft missiles), Control theory, Proportional navigation, Intercept trajectories, Guided missile trajectories, Optimization, Mathematical models, Theses

Subject Categories : Guided Missile Traj, Accuracy and Ballistics
      Air- and Space-launched Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE