• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.6
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• pp.505-516
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• 2011

The concept of the IGC(Integrated Guidance and Control) has been introduced to overcome the performance limit of the SGC(Separated Guidance and Control) loop. A new type of IGC with impact angle constraint has been proposed in this paper. Angle of attack, pitch angle rate, pitch angle and line of sight angle are considered as state variables. A controllability analysis and equilibrium point analysis have been carried out to investigate the control characteristic of the prposed IGC. The LQR(Linear Quadratic Regulator) has been adopted for the control law and detailed explanations about the adoption has been provided. The performance comparison between the IGC and the SGC has been carried out. The result of numerical simulations shows that the IGC guarantees better guidance performance than the SGC when the agile maneuver is needed for a specific guidance geometry.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.12
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• pp.857-866
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• 2022

Fixed-wing UAVs have long endurance and range capabilities compared to other aerial platforms. These advantages led fixed-wing UAVs to become a popular platform for reconnaissance missions in the military. In this research, we modeled fixed-wing UAVs, including the landing gear model and developed a guidance and control system for flight control computers to construct a HILS environment. We also developed an autopilot system that includes automated take-off, cruise, and landing control for UAVs. We also retrived the Aerodynamic coefficients an UAV using Datcom and AVL software and used them for 6 degrees of freedom modeling. The Flight control computer calculates guidance commands using the Carrot chasing guidance law after distinguishing the condition of the UAV based on 16 pre-defined flight modes and calculates control inputs using Nonlinear Dynamic Inversion (NDI) control scheme. We used RTNngine to integrate the Simulink model and flight control computer for HILS environment formulation.

• Journal of the Korea Society for Simulation
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• v.31 no.4
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• pp.1-10
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• 2022

This paper describes the development of a modular simulation environment to analyze the performance of guided weapons. For the reusability of the simulation environment, components of the guided weapon simulation are modularized based on MATLAB Simulink. And the module management system is implemented based on Excel and MATLAB GUI for simulation interface and module management. In addition, a method of integration for modules with different interface and a method to set up the guidance and control phase for designing a guided flight scenario are suggested. Finally, to verify the performance of the implemented simulation environment, it was compared with the existing simulation results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.7
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• pp.610-617
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• 2017

In the recent weapon system trend, it is required to develop small and low cost guidance missile to track and strike the enemy target effectively. Controling the such small drone typed weapon demands a integrated electronic device that equipped with not only a wireless network interface, a high resolution camera, various sensors for target tracking, and position and attitude control but also a high performance processor that integrates and processes those sensor outputs in real-time. In this paper, we propose the android smartphone as a solution for that and implement the guidance and control application of the missile. Furthermore, the performance of the implemented guidance and control application is analyzed through the simulation.

• Journal of the Korea Institute of Military Science and Technology
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• v.16 no.6
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• pp.733-738
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• 2013

A guidance kit transforming a general purpose bomb into an air-to-surface gliding bomb was developed. This guidance kit consists of a flight kit and a tail kit. Flight kit contains deployable wing, GPS/INS integrated navigation system, guidance and control system. Also this guidance kit was designed to use neither electrical nor mechanical interface with aircraft, and to increase dramatically the survivabilities of pilot and aircraft with the high accuracy and the mid-range non-powered gliding capability.