Development Of Missile System Research Articles

A preliminary multidisciplinary design procedure for tactical missiles

During missile system development, multidisciplinary design procedure is iteratively implemented based on the missile objective and target nature including internal ballistic, warhead function, and airframe configuration. By applying missile preliminary design, a good estimation for different design parameters can be obtained which will be useful through further detail design process. The aim of this paper is to build a preliminary design procedure for an unguided tactical missile that uses single-stage solid propellant motor to deliver a defined payload mass to a desired ground range. Based on data of available similar mature missile systems, two empirical formulas are developed to serve in the initial sizing of the missile with consideration of slenderness ratio, warhead mass, and desired ground range. Two different design concepts are implemented for tubular and star grains with different propellant compositions and chamber filling coefficients while the body-alone airframe configuration is adopted. The results demonstrate the capability of the proposed design procedure in defining the detailed design parameters. The impact of changing the propellant compositions and chamber filling coefficients on the obtained ground range is also explored.

Evaluation of Critical Geometrical Parameters and Alignment Corrections of Large Size Aerospace Systems

Metrological assessment of geometrical, form parameters plays an important role in development of quality hardware of aerospace systems such as missiles. These parameters are critical for mission performance and system evaluation studies. High precision CNC Coordinate Measuring Machines (CMMs) are extensively used for evaluating geometrical, form parameters in alignment checks of large missile subsystems, assemblies and tooling. These high precision metrological tools can also be used for geometrical and alignment corrections of critical missile subsystems. Alignment check of integrated missile is an important activity carried out during development of missile system. The critical aerodynamic parameters viz. nose tip deviation, cant angle and orthogonality of wings & fins and propulsion parameters such as thrust axis misalignment are evaluated using geometrical features available on integrated missile. These aerodynamic and propulsion parameters are used for aerodynamic studies and predicting missile trajectory during pre-flight simulation analysis. The deviation in these values directly affects the missile performance during flight. In case of high deviations, the above parameters are corrected mechanically in order to meet the design requirements. This paper brings out the applications and methodologies developed for evaluation and correction of geometrical and form parameters in alignment checks of integrated missiles

Knowledge management in long gestation projects

When compared to short term, dynamic, profit-driven projects like those in IT, fashion, infotainment and the service industries, long gestation complex high-technology projects pose different kinds of challenges in Knowledge Management. Typical of such programs are defence programmes, infrastructure projects and drug development. These projects run for more than a decade and there is a frequent turnover of specialists. In this paper, issues related to Knowledge Management throughout the various activities of such long gestation programs has been addressed so that the project is brought to successful completion irrespective of the continued non-availability of the specialists throughout the programme. An example of a surface-to-air missile system development project has been taken where the tools and techniques of Knowledge Management have been applied to ensure the success of this long gestation project.