In this paper, a design method of the simulation program for HILS(Hardware-In-the-Loop Simulation) system is proposed. The present method consists of definition of requirements for HILS, development of specifications, and implementation of the program to satisfy the specifications. In the implementation of the program, the application of hardware interface and the concept of structural modularization are proposed to satisfy the specifications. The concepts of CSCI(Computer Software Configuration Item) and encapsulation are used for structural modularization.The proposed method was practically applied to the development of the simulation program for the efficient operation in HILS of an anti-ship missile system.

Estimation of a full set of aerodynamic coefficients for a flight vehicle is performed processing the actual flight test data. Extended Kalman filter algorithm is utilized. Dynamic plant modeling is set up including aerodynamic forces, thrust, and mass characteristics. The pre-processed test data are used as measurement inputs for the above filtering algorithm. Six component aerodynamic coefficient structure is modeled in a polynomial form. It contains a set of 30 independent coefficients which consist of static and dynamic derivatives in the longitudinal plane as well a s in the lateral-directional one. The derivatives are determined by the multidimensional algebraic polynomial approximation from the wind tunnel look-up tables. The effect of parameter identification has been proved to be useful by comparing some state variable trajectoties one another which are constructed from the identified parameters, the original wind tunnel data, and the telemetered flight test data.