• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1997.11a
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• pp.3-3
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• 1997

미사일 수직발사 시스템은 공간을 작게 차지하고 간편하여 각국이 선호하고 있다. 그러나 수직발사 초기에는 매우 낮은 속도로 상승하므로 Fin의 공력이 발생하지 않기 때문에 추력방향을 직접제어하지 않으면 안된다. 추력방향 제어장치는 Gimbal, Jet Vane, Jet Tab, Secondary Injection 등 여러 방식이 있으나 Jet Vane Type의 추력 방향 제어장치는 응답이 빠르고 경량화가 가능하며 후방 Fin과의 연동 및 작동 후 분리가 가능하다는 장점으로 인해 수직발사 미사일의 초기 방향제어에 주로 사용한다. 이 장치는 Vane이 화염 속에서 직접 구동되므로 고내열성 재료의 기술이 필요하며 미사일의 전체 System에 요구되는 Side Force를 발생시키기 위한 Vane의 최대 받음각 및 회전속도를 결정해야 한다. 따라서 초음속 유동해석을 통해서 Vane의 받음각에 대한 Side Force와 Torque를 계산하며, 구조해석을 통해 Side Force가 가해지는 동안의 Housing의 굽힘, 비틀림 하중 등을 계산하였다. 또한 Controller는 기존의 유압방식보다도 소형이며 복잡하지 않고 가격이 싼 DC Motor와 감속기를 이용하여 빠른 응답성에 부합토록 설계하였다. 본론에서는 성능과 관련된 초기 요구조건에 대한 최적설계의 변수들을 해석하고. 그에 따른 개발사양, 개발 과정, 구조, 시험방법 등에 대해 고찰하고자 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1112-1114
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• 2017

The liquid rocket engine determines the routing of the component placement and layout by adapted the cycle method, the hardware configuration, the gimbal type on the functional implementation, and so on. In this paper, the conceptual routing of major pneumatic lines such as helium (He) supply pneumatic line for driving, many purge pneumatic line and main ignition line based on the main components installed in the liquid rocket engine was performed.

• 제어로봇시스템학회:학술대회논문집
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• 2001.10a
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• pp.85.6-85
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• 2001

This paper describes a 3-DOF attitude control of a small model helicopter in hover through explicit decoupling and adaptive control scheme. A model helicopter mounted on gimbal-stand is considered as a system that has 3 independent SISO systems representing motions about roll, pitch and yaw axis and these subsystems are identified from the test flight data. In this consideration, the contribution of others to yaw channel is neglected since it is relatively small. Two PID controllers based on Ziegler-Nichols method are designed for roll pitch channels independently. Also, adaptive fuzzy tuner is designed and applied to those PID controllers to cope with coupling effects between each channel and system uncertainties due to variation of engine RPM. The experimental results show that the attitude control ...

• Journal of Institute of Control, Robotics and Systems
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• v.20 no.10
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• pp.1014-1022
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• 2014

In mechatronic systems using electric signals to drive control systems, driving signals including the frequency band of the unwanted signals, such as resonant frequencies and noise frequencies, can affect the accuracy of the controlled system and can cause serious damage to the system due to the resonance phenomenon of the mechatronic system. An LOS (Line of Sight) control unit is used to automatically rotate the gimbal system with a video imaging system generally mounted on modern aerial vehicles. However, it still suffers from natural frequency variation problems due to variations of operational temperature. To prevent degradation in performance, this paper proposes an adaptive filtering technique based on real-time noise analysis and adaptive notch-filtering for LOS control systems, and verifies how our proposed method maintains the LOS stabilization performance. Additionally, this filtering technique can be applied to the image noise filtering of the video imaging system. It is designed to reduce image noises generated by switching circuits or power sources. The details of design procedures of the proposed filtering technique and the experiments for the performance verification are described in this paper.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.5 no.5
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• pp.1025-1030
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• 2001

As the pre-stage of making 3D stabilizing systems, at this paper designed 2D stabilizing system. This is composed of two axes stabilizing platform to preserve targeted direction while vehicle is moving. The system maintains stabilization by recovering error using the rate gyro with DSP TMS320F240 as controller, vibratory rate gyro (Tokimec co. TFG -l60D) as gyro scope, SD1015B52-1·SD1004C04-l/DM1015B DM1004C as direct drive driver/motor, PI control as control algorithm. This paper got a comparably good stabilization.

• Journal of Aerospace System Engineering
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• v.10 no.3
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• pp.15-22
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• 2016

The on-board appendages of satellites with mechanical moving parts such as the fly-wheel, the control-moment gyro, the cryocooler, and the gimbal-type directional antenna can generate an undesirable micro-vibration disturbance, which is one of the main causes of the image-quality degradation that affects high-resolution observation satellites. Consequently, the isolation of the micro-vibration issue has always been considered as salient, and the micro-vibration is therefore the focus of this study wherein a complex system that can provide the dual functions of a guaranteed vibration-isolation performance and electrical energy harvesting is proposed. The vibration-isolation and energy-harvesting performances of the complex system are predicted through a numerical analysis based on the characteristics that are obtained from component-level tests. In addition, the effectiveness of the complex system that is proposed in this study is verified through an assembly-level functional-performance test.

• International Journal of Aeronautical and Space Sciences
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• v.14 no.4
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• pp.369-378
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• 2013

This paper presents a vision/LiDAR integrated navigation system that provides accurate relative navigation performance on a general ground surface, in GNSS-denied environments. The considered ground surface during flight is approximated as a piecewise continuous model, with flat and slope surface profiles. In its implementation, the presented system consists of a strapdown IMU, and an aided sensor block, consisting of a vision sensor and a LiDAR on a stabilized gimbal platform. Thus, two-dimensional optical flow vectors from the vision sensor, and range information from LiDAR to ground are used to overcome the performance limit of the tactical grade inertial navigation solution without GNSS signal. In filter realization, the INS error model is employed, with measurement vectors containing two-dimensional velocity errors, and one differenced altitude in the navigation frame. In computing the altitude difference, the ground slope angle is estimated in a novel way, through two bisectional LiDAR signals, with a practical assumption representing a general ground profile. Finally, the overall integrated system is implemented, based on the extended Kalman filter framework, and the performance is demonstrated through a simulation study, with an aircraft flight trajectory scenario.

• 제어로봇시스템학회:학술대회논문집
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• 2004.08a
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• pp.1747-1753
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• 2004

CMG(Control Momentum Gyro) is a control device being used for spacecraft attitude control constructing relatively large amount of torque compared to conventional body-fixed reaction wheels. The CMG produces gyroscopic control torque by continuously varying the angular momentum vector direction with respect to the spacecraft body. The VSCMG(Variable Speed Control Momentum Gyro) has favorable advantages with variable speed to lead to better control authority as well as singularity avoidance capability. Attitude dynamics with a VSCMG mounted on a two-axis gimbal system are derived in this study. The dynamic equation may be considered as an extension of the single-axis counterpart. Also, a feedback control law design is addressed in conjunction with the dynamic equations of motion.

• Proceedings of the KIEE Conference
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• 2004.11c
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• pp.110-113
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• 2004

A delay dependent fuzzy $H_{\infty}$ controller design method for delayed nonlinear systems with parameter uncertainty is considered. Using delay-dependent Lyapunov function the asymptotical stability and $H_{\infty}$n performance problem :are discussed. A sufficient condition for the existence of fuzzy controller is presented in terms of linear matrix inequalities(LMIs). A simulation example through radar gimbal system is given to illustrate the design procedures and performances of the prosed methods.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.115-123
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• 2003

In this paper, in order to guarantee successful operation of KSR-III TVC actuator in the presence of excessive external disturbances, a relief valve is designed as a key component of the actuator. It is shown that the relief valve can resolve the stability problems which occur due to actuator failure in the presence of excessive disturbance torques on the actuator. Six degree-of-freedom simulation shows that relief valves with low operating pressure and low LOHM parameter may be better is stability and performance of the TVC actuator system.