• Journal of the Korea Institute of Military Science and Technology
• /
• v.5 no.1
• /
• pp.96-106
• /
• 2002

Many modern guided weapon systems employ sophisticated target sensors as well as powerful computing systems. Due to such advanced features, they are required to achieve better guidance accuracy, and at the same time other guidance objectives for better weapon effectiveness and survivability. In this paper, we overview some of the technical considerations in such advanced guidance algorithm development, and briefly look at some related research works. More specifically, we discuss impact angle control, time-varying nature of the guidance system, time-to-go estimation, guidance loop stability, effect of autopilot lag and physical limitations in control variables, parasitic paths in guidance loops, etc. We also briefly look at some advanced concepts such as integrated guidance and control loop design, target adaptive guidance, guidance law development based on dual control concept, and terminal evasive maneuver.

• 제어로봇시스템학회:학술대회논문집
• /
• 1992.10a
• /
• pp.590-595
• /
• 1992

An integrated guidance scheme for guided weapon system is described in this paper. Against conventional guidance methods, this method combines an autopilot and a guidance law. The controller is designed using LQ regulator whose performance index is different from other optimal guidance laws. Since dynamics of the system is considered in the derivation, the controller performance is improved. By simulation, the suggested method shows better performance in minimum distance sense than conventional guidance schemes such as Bang Bang guidance or Pursuit Guidance. Since the suggested method provides smooth rudder deflection in contrast to the conventional method, the load on a energy source of the system can be greatly lessened.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.13 no.4
• /
• pp.642-649
• /
• 2010

LOS analysis is used for optimal deployment of mid-range guided weapon system or system engagement effectiveness simulation. Comparing to real-world, LOS analysis includes error sources such as coarse terrain data resolution, refraction of radio waves, and several ideal assumptions. In this research, exact LOS algorithm under assumption of constant earth curvature and error analysis of that is investigated. It proved that LOS algorithm under assumption of constant earth curvature has negligible error in mid-range guidance weapon system's scope.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.19 no.5
• /
• pp.606-612
• /
• 2016

A Captive Flight Test(CFT) is used to verify the performance of missile component such as seeker and guiding algorithm of missile. Recently most of surface to air missile adapts multi-mode guidance method which include command guidance and active/passive guidance. A CFT system for missile system adapting multi-mode guidance method consists of pod equipment, command transmitting system and measuring system. In this paper, we proposed CFT system and testing method for missile which adapt multi-mode guidance, and system integration procedure by using distributed missile system integration method and procedure. The proposed CFT system and system integration method was applied to CFT of surface to air missile, and brought successful result.

• Korean Journal of Artificial Intelligence
• /
• v.12 no.2
• /
• pp.17-23
• /
• 2024

Various methods have been developed to predict the flight path of an air-launched weapon to intercept a fast-moving target in the air. However, it is also getting more challenging to predict the optimal firing zone and provide it to a pilot in real-time during engagements for advanced weapons having new complicated guidance and thrust control. In this study, a method is proposed to develop an optimized weapon engagement zone by the SCG (Scaled Conjugate Gradient) algorithm to achieve both accurate and fast estimates and provide an optimized launch display to a pilot during combat engagement. SCG algorithm is fully automated, includes no critical user-dependent parameters, and avoids an exhaustive search used repeatedly to determine the appropriate stage and size of machine learning. Compared with real data, this study showed that the development of a machine learning-based weapon aiming algorithm can provide proper output for optimum weapon launch zones that can be used for operational fighters. This study also established a process to develop one of the critical aircraft-weapon integration software, which can be commonly used for aircraft integration of air-launched weapons.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.50 no.4
• /
• pp.233-240
• /
• 2022

The smart weapon system is a new weapon system of the future battlefield environment as a miniature guided weapon that performs precision strike missions through terminal phase guidance. However, it has small coverage to guide due to its low maneuverability because the smart weapon is controlled by using actuator of piezoelectric drive type due to the structural limitations. In this paper, we propose a firing data calculation algorithm under non-standard conditions to increase the effectiveness of the smart weapon. The proposed algorithm calculates firing data under non-standard conditions by calibrating firing data under standard conditions using information acquired in battlefield environments. The performance of the proposed algorithm is verified by numerical simulations under various conditions.

• Journal of the Korea Society for Simulation
• /
• v.31 no.4
• /
• pp.1-10
• /
• 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 Korea Institute of Military Science and Technology
• /
• v.27 no.2
• /
• pp.277-284
• /
• 2024

For the high reliability of guidance weapon, it is important to maintain the stable supply voltage for guidance system while the bomb is gliding. However, the DC motor drive for guidance control in the low temperature can lead to the critical voltage drop due to a large inrush current. In this paper, we propose the wing deployment logic design to enhance the guidance system stability. To derive the stable drive logic based on PWM, we controlled the duty cycles for input voltage of DC motor in low temperature. The initial duty cycle was set to 40 % to relieve the inrush current. Moreover, the proper time, which is less than 1 second for controlling duty cycles, was determined by the iterative wing deployments of guidance kit. Finally, the validity of proposed logic was confirmed from the result the maximum voltage drop for the wing deployment was decreased by 23 %.

• 제어로봇시스템학회:학술대회논문집
• /
• 1993.10a
• /
• pp.466-470
• /
• 1993

A HILS(Hardware-In-the-Loop Simulation) technique for an IR guided weapon is proposed. The IR HILS facility functions as a testing unit for a missile guidance and control system to evaluate target acquisition, tracking, and countermeasure performance. The configuration of IR HILS facility, modeling technique of an IR environment including target, background and countermeasure, and test and evaluation procedure are included.

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