Operator and organizational maintenance manual for guided missile system, surface attack M47; training equipment consisting of, monitoring set, guided missile system, training, AN/TSQ-T1; trainer handling, GM launcher, M57; trainer, launch effects, guided missile M54; transmitting set, infrared, M89E1 (Dragon medium antitank/assault weapon system).

"September 1979."

Operator and organizational maintenance manual for TOW Weapon System guided missile system M220A1 (1440-00-169-1764) : TOW heavy antitank/assault weapon system.

"January 1980."

Operator's manual for 66mm light antitank weapon system M72A1, M72A2 with coupler, M72A3 and practice rocket launcher M190 with M73 practice rocket.

"January 1986."

Demilitarization procedures for DRAGON medium antitank/assault weapon system.

"March 1976."

Operators manual : DRAGON weapon system, M47 /

"15 April 1974"--p. i.

Hand receipt covering contents of Components of End Item (COEI), Basic Issued Items (BII), and Additional Authorization List (AAL) for combat vehicle, anti-tank : improved tow vehicle, M901 (2350-01-045-1123).

"April 1983."

Operator and organizational maintenance manual for TOW weapon system training set, guided missile system M70 (6920-00-179-7320) and TOW weapon system training set, guided missile system XM-145 (P/N 13060929) : (TOW heavy antitank assault weapon system).

"January 1980."

Operator's manual for DRAGON weapon guided missile system, surface attack : M47 (medium antitank/assault weapon system).

"July 1979."

DS and GS maintenance manual : surveillance of guided missile and launcher, surface attack, M222 and guided missile and launcher, surface attack, practice, M223, including repair parts and special tools list (dragon medium antitank/assault weapon system)

"April 1974."

Operator and organizational maintenance manual for TOW 2 Weapon System, guided missile system M220E4 (1440-01-104-9834), (TOW 2 Heavy Antitank Assault Weapon System).

"May 1983."

Operator, organizational, DS and GS maintenance manual : differential multimeter, 6625-489-8908 (TOW heavy antitank/assault weapon system).

Includes bibliographical references.

Operator and organizational maintenance manual for TOW 2 Weapon System training set, guided missile system M70E2, (TOW 2 Heavy Antitank Assault Weapon System).

"May 1983."

Impact-Angle-Constrained Suboptimal Model Predictive Static Programming Guidance of Air-to-Ground Missiles

A nonlinear suboptimal guidance law is presented in this paper for successful interception of ground targets by air-launched missiles and guided munitions. The main feature of this guidance law is that it accurately satisfies terminal impact angle constraints in both azimuth as well as elevation simultaneously. In addition, it is capable of hitting the target with high accuracy as well as minimizing the lateral acceleration demand. The guidance law is synthesized using recently developed model predictive static programming (MPSP). Performance of the proposed MPSP guidance is demonstrated using three-dimensional (3-D) nonlinear engagement dynamics by considering stationary, moving, and maneuvering targets. Effectiveness of the proposed guidance has also been verified by considering first. order autopilot lag as well as assuming inaccurate information about target maneuvers. Multiple munitions engagement results are presented as well. Moreover, comparison studies with respect to an augmented proportional navigation guidance (which does not impose impact angle constraints) as well as an explicit linear optimal guidance (which imposes the same impact angle constraints in 3-D) lead to the conclusion that the proposed MPSP guidance is superior to both. A large number of randomized simulation studies show that it also has a larger capture region.

Generalized model predictive static programming and its application to 3D impact angle constrained guidance of air-to-surface missiles

A new `generalized model predictive static programming (G-MPSP)' technique is presented in this paper in the continuous time framework for rapidly solving a class of finite-horizon nonlinear optimal control problems with hard terminal constraints. A key feature of the technique is backward propagation of a small-dimensional weight matrix dynamics, using which the control history gets updated. This feature, as well as the fact that it leads to a static optimization problem, are the reasons for its high computational efficiency. It has been shown that under Euler integration, it is equivalent to the existing model predictive static programming technique, which operates on a discrete-time approximation of the problem. Performance of the proposed technique is demonstrated by solving a challenging three-dimensional impact angle constrained missile guidance problem. The problem demands that the missile must meet constraints on both azimuth and elevation angles in addition to achieving near zero miss distance, while minimizing the lateral acceleration demand throughout its flight path. Both stationary and maneuvering ground targets are considered in the simulation studies. Effectiveness of the proposed guidance has been verified by considering first order autopilot lag as well as various target maneuvers.

Generalized Model Predictive Static Programming and Angle-Constrained Guidance of Air-to-Ground Missiles

A new generalized model predictive static programming technique is presented for rapidly solving a class of finite-horizon nonlinear optimal control problems with hard terminal constraints. Two key features for its high computational efficiency include one-time backward integration of a small-dimensional weighting matrix dynamics, followed bya static optimization formulation that requires only a static Lagrange multiplier to update the control history. It turns out that under Euler integration and rectangular approximation of finite integrals it is equivalent to the existing model predictive static programming technique. In addition to the benchmark double integrator problem, usefulness of the proposed technique is demonstrated by solving a three-dimensional angle-constrained guidance problem for an air-to-ground missile, which demands that the missile must meet constraints on both azimuth and elevation angles at the impact point in addition to achieving near-zero miss distance, while minimizing the lateral acceleration demand throughout its flight path. Simulation studies include maneuvering ground targets along with a first-order autopilot lag. Comparison studies with classical augmented proportional navigation guidance and modern general explicit guidance lead to the conclusion that the proposed guidance is superior to both and has a larger capture region as well.