Accession Number : ADA183062

Title :   Nonlinear Control Theory for Missile Autopilot Design.

Descriptive Note : Final technical rept. 15 Aug 86-14 Feb 87,

Corporate Author : SCIENTIFIC SYSTEMS INC CAMBRIDGE MA

Personal Author(s) : Gustafson,Donald E ; Baillieul,John ; Levi,Mark

PDF Url : ADA183062

Report Date : 24 Apr 1987

Pagination or Media Count : 68

Abstract : Bank-to-turn steering is attractive in terms of potential performance improvements over skid-to-turn steering. In order to fully realize this performance, attitude maneuvers in response to guidance system commands will sometimes take place at high body rates and angle-of-attack, where the dynamics are nonlinear. The problem is further complicated by constraints on angle of attack, control surface deflections and body rates. It appears that linear control methods may be inadequate in these cases. In this paper we consider several nonlinear control approaches. A decoupling controller is derived and shown to be well-defined (nonsingular). Conditions for constraint avoidance are derived. Stability is analyzed in the presence of estimation errors. A minimium-time control law which takes constraints into account is derived, resulting in a bang-bang controller. Keywords: equations of motion; short range air to air weapons.

Descriptors :   *AUTOMATIC PILOTS, *GUIDED MISSILE TRAJECTORIES, *CONTROL THEORY, AIRBORNE, ATTITUDE(INCLINATION), MANEUVERS, STEERING, DEFLECTION, DYNAMICS, ERRORS, ESTIMATES, CONTROL, LINEAR SYSTEMS, ANGLE OF ATTACK, PULSE MODULATION, RATES, DECOUPLING, EQUATIONS OF MOTION, HIGH RATE, GUIDED MISSILE COMPONENTS, ATTITUDE CONTROL SYSTEMS, FLIGHT MANEUVERS, NONLINEAR SYSTEMS, AIR TO AIR MISSILES, SHORT RANGE(DISTANCE)

Subject Categories : Guided Missile Dynam, Config & Cntrl Surfaces
      Cybernetics
      Air- and Space-launched Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE