• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.3
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• pp.221-228
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• 2014

In this paper, the operational concept and the navigation algorithms for the gliding guided artillery munition are studied. The gliding guided artillery munition has wings for gliding; therefore spin of the munition should be eliminated. The previous navigation algorithms assumed a spinning munition with constant angular velocity; hence, they cannot be applied for the gliding munition. Moreover, lateral stability becomes worse due to decrease of angular momentum. Therefore, side force should be controlled to improve the stability, and the munition should maneuver, then the previous navigation algorithms for typical fixed-wing aircraft cannot be applied. In this paper, we apply the previous navigation algorithms for the spinning munition. Spin is eliminated and wings are deployed based on the estimation results, and the advanced navigation algorithm for the non-spinning munition is introduced.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.3
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• pp.229-236
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• 2014

In this paper, the guidance laws and controllers for the gliding guided artillery munition is studied. The gliding guided artillery munition has wings for gliding to increase a range; therefore previous guidance laws and controllers for the guided munition could not be applied. Concepts of vector field guidance and proportional navigation guidance are applied for mid-term and terminal guidance, respectively. The gliding guided artillery munition is operated within wide altitude and speed areas; therefore, the controllers are designed for each area, and gain-scheduling and the linear interpolation technique is applied to compute the appropriate gains.

• Proceedings of the KIPE Conference
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• 2015.07a
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• pp.133-134
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• 2015

본 논문에서는 유도형 활공 탄약의 방향과 자세 제어를 위한 4축 조종 날개의 위치 제어용 Sensorless BLDC 전동기 구동 시스템을 개발하였다. HILS(Hardware in the loop system)를 이용하여 유도형 탄약의 발사 조건과 비행 환경을 시뮬레이션하면서 비행 시 발생하는 공력 부하를 기구부로 재현하였고 이러한 조건하에서 4축 조종 날개의 위치 제어 특성을 확인함으로써 개발된 구동 시스템의 성능을 검증하였다.

• Journal of the Korea Society for Simulation
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• v.28 no.1
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• pp.49-56
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• 2019

In this study aerodynamic characteristics of guided gliding type ammunition were investigated by using a computational analysis and wind tunnel test. Missile DATCOM, a semi-empirical method, and a FLUENT, a computational fluid dynamics analysis program, were used for computational analysis. For a guided gliding type ammunition, aerodynamic characteristics were investigated by calculating lift force, drag force, pitching moment and etc. Aerodynamic characteristics of guided gliding type ammunition are completely different from those of conventional ammunition. The results obtained from the computer analysis are similar to those obtained from the wind tunnel test. Although the pitch moment values obtained by the semi-empirical method were slightly different from the wind tunnel test results, the overall computer analysis results showed trends and values similar to the test results. In this study, aerodynamic characteristics of guided gliding type ammunition were identified and it found that semi-empirical method can be applied to analyze the aerodynamic characteristic in the initial design of guided gliding ammunition.

• Proceedings of the KIPE Conference
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• 2014.07a
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• pp.49-50
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• 2014

본 논문에서는 유도형 활공 탄약의 비행경로 제어와 자세유지를 위해 장착된 꼬리 날개 구동을 위한 BLDC 전동기 제어시스템을 개발하였다. 이 시스템에서는 높은 고도에서의 비행 시 압력에 취약한 홀(Hall) 센서와 같은 회전자의 위치 검출 센서를 사용하지 않는 센서리스(Sensorless) 구동 방식을 적용하였다. 측정된 극전압으로부터 상전환 신호를 추출하여 BLDC 전동기의 센서리스 구동을 실현하였으며, 또한 상전환 신호로부터 추정된 속도를 사용하여 속도 제어를 통해 꼬리날개의 변위 명령 추종을 위한 위치 제어를 수행하였다. 실제 구현된 시스템에서의 실험을 통해 개발된 센서리스 제어 알고리즘을 적용하여 위치 제어의 성능이 우수함을 확인하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.9
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• pp.681-689
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• 2020

This paper presents methods and results of both flight test examining roll angle estimation performance of slowly rolling munition forced to spin in the air, and fabricating a replica of guided munition. Guided munition was deployed from multi rotor type UAV mother ship whose altitude and velocity was conveyed to it as initial state. Flight test scenario is composed of a sequence of munition drop(deployment), munition spin, roll angle estimation and stabilization. Munition was deployed from mother ship at around 200m high with horizontal velocity of 15m/s, and was made spun using internal reaction wheel. Performance analysis on roll angle estimation is provided in comparison with commercial aerospace graded GPS/INS. Moreover, several mechanisms that rotates munition using reaction wheel, and actual product that realizes one of them are introduced.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.5
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• pp.373-381
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• 2021

This paper details the result of flight experiment that examines performance of roll angle estimation algorithm of slowly rolling munition taking time delay of measurement into account when measurement comes in delayed fashion. As the measurement is passed through low pass filter for numerical stabilization and de-noising purpose which induces time delay, we design augmented state Kalman filter that incorporates distribution models of stochastic delay over time. Flight experiment was conducted to verify the algorithm at around 250m high AGL(Above Ground Level) conveying velocity of 28m/s from fixed-wing mother plane to the munition. Munition was made spun with respect to its roll axis using internal reaction wheel afterward. Numerical comparison of proposing method's roll estimation performance with that of commercial aerospace graded GPS/INS shows that proposed filter design can effectively compensate time delay of measurement.

• Journal of the Korea Institute of Military Science and Technology
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• v.27 no.4
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• pp.457-465
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• 2024

The Remote Control Munition System is a anti-personnel munitions system to replace land mines that are hard to retrieve and can inflict damage on friendly forces and civilians. As operating environments and methods change, quality improvement is necessary to ensure appropriate durability. Therefore, corrosion resistance evaluation was performed according to the surface treatment of ALDC12, the main assembly material. We conduct the potentiodynamic polarization, cyclic corrosion test to perform analysis on corrosion behavior. Additionally, we try to observe the pitting on the surface through SEM analysis. In conclusion, among the three surface treatments, Anodizing surface treatment is judged to be the most suitable for corrosion durability in a field environment.

• Journal of Industrial Technology
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• v.35
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• pp.9-13
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• 2015

In this paper, a new excitation scheme is developed to increase the output torque of the sensorless BLDC(Brushless DC) motor(BLDCM), which drives fins to control the flight attitude of a guided artillery munition. The proposed scheme is based on a 12-step excitation strategy combining two-phase and three-phase excitations. The proposed 12-step excitation scheme can produce more torque than a typical 6-step scheme for the start-up and synchronous operation in the sensorless BLDCM drive. The simulation and experimental results on the sensorless BLDCM drive system to control the fin were verified the validity of the proposed scheme.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.11
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• pp.965-972
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• 2016

This paper presents results of flight experiments on a navigation algorithm including multiplicative extended Kalman filter for estimating attitude of the guided munition. The filter describes orientation of aircraft by data fusion with low-cost sensors where measurement update is done by multiplication, rather than addition, which is suitable for quaternion representation. In determining attitude from vector observations, the existing approach utilizes a 3-axis accelerometer as a 2-axis inclinometer by measuring gravity to estimate pitch and roll angles, while GNSS velocity is used to derive heading of the vehicle. However, during accelerated maneuvers such as coordinated flight, the accelerometer provides inadequate inclinometer measurements. In this paper, the measurement update process is newly defined to complement the vulnerability by using different vector observations. The acceleration measurement is considered as a result of a centrifugal force and gravity during turning maneuvers and used to estimate roll angle. The effectiveness of the proposed method is verified through flight experiments.