• The Journal of Korean Institute of Communications and Information Sciences
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• v.35 no.11B
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• pp.1659-1666
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• 2010

The High maneuver missiles use various interfaces and high speed guidance and control loop. Hardware-in-the-Loop(HWIL) simulation control system, therefore, should have high performance computing power and hardware interface capabilities, and should be developed using IT technology with which real time operating system, embedded system, data communication technology, and real time hardware control are integrated. This paper suggests the control system design techniques, such as a system hardware configuration, a job distribution algorithm for high performance multi-processors, a real time calculation and control mechanism, inter-processor communication mechanism, and a real time data acquisition technique, to perform the HWIL simulation for high maneuver missile system.

• Proceedings of the KIEE Conference
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• 2002.07d
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• pp.2659-2661
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• 2002

The development of guided missile requires complex guidance schemes and hardware units because of high maneuver, delicate and variable missions. In this point of view, simulation systems and facilities which test missile hardwares and softwares are needed. This paper introduces the hardware-in-the loop simulation system and facilities which include the real-time computation systems and 3 Axis FMS(Flight Motion Simulator).

• 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.