• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.137-143
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• 2013

In recent years, the interest in a various energy sources is increasing. Among these energies, there are many kinds of researches for the kite which can generate the energy from high-altitude wind power. There are many attempts to apply the kite to the wind power generation and ship salvage, and it must require the flight control of the kite for this applications. In this paper, we suggest this flight controller based on the flight technique of sport kite. For this controller based on the human controller, we design the simple fuzzy controller with simple fuzzy rules.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.426-432
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• 2017

An experimental and numerical study on shock attenuation in a solid by a subminiature flyer impact was conducted to determine the performance of a subminiature exploding foil initiator such as, flyer velocity and impulse loading. The obtained attenuation pattern shows the possibility to determine the critical flyer velocity for initiating the miniaturized pyrotechnic unit by figuring out shock intensity and duration according to flight characteristics.

• Journal of Advanced Navigation Technology
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• v.14 no.5
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• pp.596-603
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• 2010

This paper presents a homing guidance law of anti-ship missiles using flight path angle to achieve an impact time constraint as well as an impact angle constraint. the independent variable in the nonlinear engagement model is change d from the flight time to the heading angle of the missile. The proposed guidance law can home a missile to the target with zero miss distance as well as satisfying both of the impact angle and time constraints. The performance of the proposed guidance law is evaluated by the computer simulations.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.12
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• pp.981-988
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• 2021

This paper presents a decentralized guidance algorithm for swarm flight of fixed-wing UAVs (Unmanned Aerial Vehicles). Considering swarm flight missions, we assume four representative swarm tasks: gathering, loitering, waypoint/path following, and individual task. Those tasks require several distinct maneuvers such as path following, flocking, and collision avoidance. In order to deal with the required maneuvers, this paper proposes an integrated guidance algorithm based on vector field, augmented Cucker-Smale model, and potential field methods. Integrated guidance command is synthesized with heuristic weights designed for each guidance method. The proposed algorithm is verified through flight tests using up to 19 small fixed-wing UAVs.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.5
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• pp.386-392
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• 2017

This paper considers the analysis of the flight performance reserve, which is required propellant to compensate various launch vehicle performance deviations, to inject the payload of a 3-staged launch vehicle to a circular sun synchronous orbit at a height of 700 km. The various error sources, which affect the orbit injection accuracy, and their uncertainty are defined first. Then the sensitivity analysis, which has the advantage that each error source effect can be investigated independently, is performed for the extreme ${\pm}3{\sigma}$ conditions of the launch vehicle performance errors. Monte carlo simulations are also conducted to compute the propellant reserve, which can consider the combined effects of each error source. Finally the obtained flight performance reserves by the two approaches are compared and it is confirmed that they show similar results.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.7-14
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• 2005

This paper describes development of automatic flight control system for an unmanned target drone. Current target drone is operated by pilot control of on-board servo motor via remote control system. Automatic flight control system for the target drone greatly reduces work load of ground pilot and can increase application area of the drone. Most UAVs being operated nowdays use high-priced sensors as AHRS and IMU to measure the attitude, but those are costly. This paper introduces the development of low-cost automatic flight control system with low-cost sensors. The integrated automatic flight control system has been developed. The performance of automatic flight control system is verified by flight test.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2012.05a
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• pp.539-540
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• 2012

최근까지 무인 항공기는 군사적인 목적으로 활용하기 위해 활발하게 연구 되어 왔다. 근래에 들어 레저용, 또는 상업용으로 활용도가 급격히 증대되고 있다. 이에 국내외의 대학 및 연구기간에서 무인항공기의 자동비행 제어시스템을 위한 연구를 활발히 진행되고 있다. 최근 들어 무인항공기로 제어하기가 쉽고 활용도가 높은 쿼드로터 비행체가 각광을 받고 있는데 이미 많은 연구가 진행되어 왔다. 이러한 쿼드로터는 4개의 로터의 속도 제어로 비행체의 위치제어가 가능하다. 쿼드로터의 구조적인 이점으로 제어가 쉬운 반면 바람과 같은 외란에 매우 취약하다는 단점이 있어 실제 위치 제어가 쉽지가 않다. 본 논문에서는 외란(disturbance)에 취약한 쿼드로터의 위치제어를 안정하게 제어하기 위해 비행체의 자세 측정 센서인 관성측정장치(Inertial Measurement Unit)를 만들어 비행체의 자세를 측정 할 수 있도록 하였다. IMU는 자이로(Gyro)와 가속도(Accelerometer) 센서를 융합하여 비행체의 Roll, Pitch, Yaw 자세를 계측할 수 있도록 하였다. 본 논문에서는 일반적인 PID 제어기법을 적용하여 기존의 쿼드로터의 비행체에 대한 제어 성능을 실험을 제시하고자 한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.9
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• pp.907-913
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• 2010

In this paper, we have described a development of the external instrumentation system of a fighter aircraft for flight test. The external instrumentation system consists of the instrumentation pod and the image pod. The instrumentation pod measures a flight data(attitude, velocity, altitude, etc) of the fighter aircraft by using GPS/AHRS sensor. The image pod takes high-speed images for the separation trajectory of a smart bomb with 2 high-speed cameras and video signal for it with one general camera. We have verified the performance of the external instrumentation system through the ground test, the environment test and the flight test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.7
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• pp.633-639
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• 2007

This paper presents a new homing guidance law based on well-known BPN to achieve an impact time constraint as well as an impact angle constraint. The guidance commands are synthesized by introducing an additional command to control impact-time. The structure of the additional command has a BPN-based loop multiplied by time-varying gains being proportional to the time difference between the required time-to-go and the estimated time-to-go by BPN. Moreover, the proposed homing loop converges to BPN as the time-to-go error is reduced. The performance of the proposed guidance law is evaluated by the computer simulations.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.6
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• pp.31-38
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• 2002

This paper presents the analysis of the flight test data measured by the sensors installed on a four-seat canard aircraft. The inherent stall proof characteristics of canard aircraft was verified from the stall test. The dihedral effect, adverse yaw and roll control power were examined and the neutral point that determines the longitudinal stability of the aircraft was investigated. The dynamic characteristics such as dutch roll mode were also examined. Without relying on the parameter identification method, the aerodynamic derivatives or the relations between the aerodynamic derivatives were obtained by analyzing the steady state flight data.