• 대한전기학회논문지
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• 제37권3호
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• pp.171-179
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• 1988

본 논문은 MRAC방식을 이용하여 비행체 조종장치의 제어기 설께에 관하여 다루었다. 적응제어 시스템의 구성은 NARENDRA와 VALAVANI가 제안한 구조를 토대로 하여 프랜트의 상대차수가 $n^{*}=2$인 경우에 대하여 고찰하였다. 비행체 조종장치는 단일 입.출력을 갖는 제어시스템으로 근사화하였고, 제어입력은 기준모델과 프랜트의 입.출력관계로부터 얻는다. 설계된 제어시스템의 타당성을 검토하기 위하여 프랜트가 애널로그 모델인 경우롸 비행자세를 나타내줄 수 있는 비행운동테이블을 포함하는 각각의 경우에 대하여 시뮬레이션하였고, 그 결과 검토하였다.

• Advances in aircraft and spacecraft science
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• 제6권5호
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• pp.349-369
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• 2019

In the design of flight control systems there are issues that deserve special consideration and attention such as external perturbations or systems failures. A Simple Adaptive Controller (SAC) that does not require a-priori knowledge of the faults is proposed in this paper with the aim of realizing a fault tolerant flight control system capable of leading the pitch motion of an aircraft. The main condition for obtaining a stable adaptive controller is the passivity of the plant; however, since real systems generally do not satisfy such requirement, a properly defined Parallel Feedforward Compensator (PFC) is used to let the augmented system meet the passivity condition. The design approach used in this paper to synthesize the PFC and to tune the invariant gains of the SAC is the Population Decline Swarm Optimization ($P_DSO$). It is a modification of the Particle Swarm Optimization (PSO) technique that takes into account a decline demographic model to speed up the optimization procedure. Tuning and flight mechanics results are presented to show both the effectiveness of the proposed $P_DSO$ and the fault tolerant capability of the proposed scheme to control the aircraft pitch motion even in presence of elevator failures.

• 한국게임학회 논문지
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• 제19권5호
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• pp.53-62
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• 2019

드론 시장이 확산되고 있는데 비하여, 가장 기본적인 드론의 기초 운항법을 위한 트레이닝 콘텐츠 개발은 상대적으로 미비한 편이다. 이에, 본 연구에서는 실제 드론 트레이닝에 사용되고 있는 다양한 드론 운항법에 대한 문헌들과 관련 콘텐츠 등을 분석하여, 조작능력 향상을 위한, 게임 환경에서의 트레이닝 콘텐츠를 기획하였다. 그리고 실제 드론 조작에 사용되는 컨트롤러를 XBOX 게임 콘트롤러에 키 맵핑하여, 게임을 통해 실제 드론 트레이닝이 가능하도록 콘텐츠를 구현하였다. 추후 연구에서는 본 연구를 기반으로 개발된 기초 운항법 트레이닝 콘텐츠를 기초로 둔 특수목적용 드론 콘텐츠 제작을 진행하고자 한다.

• 로봇학회논문지
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• 제16권3호
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• pp.245-249
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• 2021

In this paper, we present novel simulation contents for drone racing and autonomous flight of drone. With Depth camera and SLAM, we conducted mapping 3 dimensional environment through RTAB-map. The 3 dimensional map is represented by point cloud data. After that we recovered this data in Unreal Engine. This recovered raw data reflects real data that includes noise and outlier. Also we built drone racing contents like gate and obstacles for evaluating drone flight in Unreal Engine. Then we implemented both HITL and SITL by using AirSim which offers flight controller and ROS api. Finally we show autonomous flight of drone with ROS and AirSim. Drone can fly in real place and sensor property so drone experiences real flight even in the simulation world. Our simulation framework increases practicality than other common simulation that ignore real environment and sensor.

• 한국군사과학기술학회지
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• 제14권2호
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• pp.213-221
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• 2011

Avionics system tends to be designed to have the integrated architecture, and it is getting difficult and complex to verify the flight-critical function because of sophisticated structure. In Korean Utility Helicopter, mission computer acts as the MUX Bus Controller to handle the data from both communication, identification, mission/display and survivability equipment inside Mission Equipment Package and aircraft subsystems such as fuel system and electrical system while it is interfacing with Automatic Flight Control System and Full-Authority Digital Engine Control via ARINC-429 bus. The Flight Displays which is classified as flight-critical function in aircraft is implemented on Primary Flight Display after mission computer processes data from AFCS in order to generate graphics. This paper defines the flight-critical function implemented in mission computer for KUH, and presents the static and dynamic test procedures which is performed on System Integration Laboratory along with Playback Recorder prior to flight test.

• International Journal of Aeronautical and Space Sciences
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• 제9권1호
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• pp.162-168
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• 2008

A design objective for variable stability flight control system is to develop a controller of in-flight simulation capability that forces the aircraft being flown to follow the dynamics of other aircraft. This paper presents a model-following variable stability control system (VSS) for in-flight simulation which consists of feedforward and feedback control laws, the aircraft dynamic model to be simulated, and switching and fader logics to reduce the transient effect between two aircraft dynamics. The separate design techniques for feedforward and feedback control law proposals are based on model matching and augmented linear quadratic (LQ) techniques. The system allows pilots to select and engage VSS mode, and when deselected, the aircraft reverts to the baseline flight control system. Both the baseline flight control laws and VSS control laws are computed continuously during flight. Initialization of the state values are necessary to prevent instability, since VSS control laws have integrators and filters in longitudinal, and lateral/directional axes. This paper demonstrates and validates the effectiveness and quality of VSS with F-16 models embedded in T-50 in-flight simulation aircraft.

• Journal of Biosystems Engineering
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• 제36권6호
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• pp.467-475
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• 2011

Aerial spraying technology using a small unmanned helicopter is an efficient and practical tool to achieve stable agricultural production to improve the working condition. An attitude controller for the agricultural helicopter would be helpful to aerial application operator. In order to construct the flight controller, a state space model of the helicopter should be identified using a dynamic analysis program, such as CIFER$^{(R)}$. To obtain the state space a model of the helicopter, frequency-sweep flight tests were performed and time history data were acquired using a custom-built stick position transmitter. Four elements of stick commands were accessed for the collective pitch (heave), aileron (roll), elevator (pitch), rudder (yaw) maneuvers. The test results showed that rudder stick position signal was highly linear with rudder input channel signal of the receiver; however, collective pitch stick position signal was exponentially manipulated for the convenience of control stick handling. The acquired stick position and flight dynamic data during sweep tests would be analyzed in the followed study.

• International Journal of Aeronautical and Space Sciences
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• 제8권1호
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• pp.21-31
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• 2007

Relaxed Static Stability (RSS) concept has been applied to improve aerodynamic performance of modern version supersonic jet fighter aircraft. The T-50 advanced supersonic trainer employs the RSS concept in order to improve the aerodynamic performance. And the flight control system stabilizes the unstable aircraft and provides adequate handling qualities. The T-50 longitudinal control laws employ a proportional-plus-integral type controller based on a dynamic inversion method. The longitudinal dynamic modes consist of short period with high frequency and phugoid mode with low frequency. The design goal of longitudinal control law is optimization of short period damping ratio and frequency using Lower Order Equivalent System (LOES) complying the requirement of MIL-F-8785C. This paper addresses phugoid mode characteristics such as damping ratio and natural frequency that is affected by the nonlinear control laws such as angle of attack limiter, auto pitch attitude command system and autopilot of pitch attitude hold.

• International Journal of Aeronautical and Space Sciences
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• 제11권2호
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• pp.69-79
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• 2010

This paper describes the experimental framework for the control system design and validation of a rotorcraft unmanned aerial vehicle (UAV). Our approach follows the general procedure of nonlinear modeling, linear controller design, nonlinear simulation and flight test but uses an indoor-installed multi-camera system, which can provide full 6-degree of freedom (DOF) navigation information with high accuracy, to overcome the limitation of an outdoor flight experiment. In addition, a 3-DOF flying mill is used for the performance validation of the attitude control, which considers the characteristics of the multi-rotor type rotorcraft UAV. Our framework is applied to the design and mathematical modeling of the control system for a quad-rotor UAV, which was selected as the test-bed vehicle, and the controller design using the classical proportional-integral-derivative control method is explained. The experimental results showed that the proposed approach can be viewed as a successful tool in developing the controller of new rotorcraft UAVs with reduced cost and time.

• 한국정보통신학회:학술대회논문집
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• 한국정보통신학회 2022년도 추계학술대회
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• pp.583-584
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• 2022

드론의 발전으로 인해 드론의 임무는 다양한 분야에서 수행되며, 광범위한 영역에서 비가시권(BVLOS, Beyond Visual Line Of Sight) 비행한다. 대부분 드론은 무선 주파수(RF, Radio Frequency) 통신을 통해 운용되고 약 1-2 km의 제한된 반경에서만 비행이 가능하다. 이를 극복하기 위해 본 논문에서는 RF와 LTE (Long Term Evolution)를 활용하여 BVLOS에서 임무를 수행하는 드론을 조종하기 위한 다중 통신 프로토콜 기반 드론 조종 시스템을 제안한다. 제안한 시스템은 크게 조종부와 드론부로 이루어진다. 조종부는 조종기에서 발생한 하나의 조종 신호를 RF와 LTE를 통해 전송한다. 드론부는 RF와 LTE를 통해 이중으로 전송된 조종 신호를 통신 프로토콜의 우선순위에 따라 분류하여 FC (Flight Controller)로 전달한다. 제안한 조종 시스템을 통해 RF 통신 거리 한계를 극복하고 통신 연결 불능 상황을 방지할 수 있다.