Design and Implementation of Digital Missile Trajectory Controller

Document Type : Original Article

Authors

1 M.Sc. student, Dpt. Of Guidance, Military Technical College, Cairo, Egypt.

2 Ph.D. Defense Systems Studies Center, Cairo, Egypt.

3 Associated Prof., Guidance Dep., Military Technical College, Cairo, Egypt.

4 Ph.D., Lecturer, Guidance Dep., Military Technical College, Cairo, Egypt.

Abstract

The missile mission success depends on robust guidance techniques in which the missile is to be guided to fulfill a correct trajectory up to hit point. This paper is devoted to discuss the design, implementation and verification of a digital trajectory generator (DTG) and its application for guided vehicles. The DTG is fed with target position and environmental parameters. The suitable trajectory missile attitude angles are generated as a function of time and are transmitted from the launcher to the missile via the four standard control wire dispended from the missile during flight. For the simulation
purposes, an adaptation is developed to interface the DTG with the software based missile simulator through the standard USB port. A synchronizer is embedded in the DTG hardware design to synchronize and simulate the missile leave launch event. The design is verified by comparing the results of the basic stand alone flight simulator and those with the DTG hardware in the loop simulations in various operating points. Promising results showed potential for an on-going research and development for the system of concern. Developed DTG is a must step on upgrading the guided vehicles via using a goniometer in the launcher or via integrated onboard with homing head.

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