Classical guidance and control laws have been used for aerospace vehicles, which are aerodynamically unstable and non-linear, with varying degrees of performance, complexity and seeker/sensor requirements. Accuracy requirements with dynamic tactics of modern warfare demand performance improvement, which is a trade-off between costly sophisticated hardware and computationally intensive software. Flight motion simulator (FMS) is a high-bandwidth angular motion system for the simulation of missile dynamics. This paper describes the initial laboratory integration of the hardware-in-loop Simulation (HILS) for homing guided missile system. HILS facilities and methodology form an integrated system for transforming a preliminary guidance and control system design to flight software and hardware from initial launching till impact. FMS will be driven by the output of deterministic simulations and will replicate the time history of the command signals. This paper describes the motivation, the servo system, mechanical, and electronic subsystems, and control software and algorithms. Moreover, the software user interfaces for the FMS. Six-degrees-of- freedom (6-DOF) flying body model is utilized in association with graphical user interface (GUI) for FMS.