A5032546374- Adaptive Control of Nonlinear Systems
- Aerospace and Aviation Technology
- Guidance and Control Systems
- Robotic Path Planning Algorithms
- Aerospace Engineering and Control Systems
- Inertial Sensor and Navigation
- Distributed Control Multi-Agent Systems
- Dynamics and Control of Mechanical Systems
- UAV Applications and Optimization
- Biomimetic flight and propulsion mechanisms
- Space Satellite Systems and Control
- Advanced Control Systems Optimization
- Aeroelasticity and Vibration Control
- Spacecraft Dynamics and Control
- Robotics and Sensor-Based Localization
- Control Systems and Identification
- GNSS positioning and interference
- Aerospace Engineering and Energy Systems
- Control and Dynamics of Mobile Robots
- Underwater Vehicles and Communication Systems
- Vehicle Dynamics and Control Systems
- Adaptive Dynamic Programming Control
- Internet of Things and Social Network Interactions
- Fault Detection and Control Systems
- Target Tracking and Data Fusion in Sensor Networks
Chungnam National University
2016-2025
New Generation University College
2024
National University College
2024
Agency for Defense Development
2014
University of Surrey
2014
Korea Aerospace Research Institute
2012
Seoul National University
1995-1998
Daewoo Pharma (South Korea)
1998
A guidance and control system is proposed for automatic carrier landing of an unmanned aerial vehicle (UAV). To this end, the position attitude predicted by considering sea state so that UAV loop can be compensated during final approach phase. The kinematics reference trajectory are determined using touchdown position. Nonlinear laws designed based on a sliding-mode scheme to make robustly follow trajectory.
Abstract This paper describes the tailless control system design of a flapping-wing micro air vehicle in four-winged configuration, which can provide high authority to be stable and agile flight conditions from hovering maneuvering flights. The consists variable flapping frequency wing twist modulation. creates rolling moments through differential vertical force mechanisms that independently driven on left right sides. modulation changes tension, resulting horizontal variations during one...
This paper investigates a model predictive automatic carrier landing system considering the motion of carrier. With medium-altitude long-endurance UAV and models, guidance control for safe shipboard use relative geometry between deck into account. The is operated by two types systems. One linear quadratic tracker with integral designed to track desired glide slope. other which finds optimizing input sequences over certain time horizon predicting future motions deck. Numerical simulations are...
This paper discusses the design of fault-tolerant guidance law based on incremental nonlinear dynamic inversion (INDI). The INDI method is robust against model uncertainty, unlike (NDI), by converting NDI into an form taking a Taylor series. Also, disturbances using sensor measurement feedback at high frequency. robustness has led to growing body research controllers. In most studies, control derived dynamics force or moment equations. However, contain information about airframe and actuator...
In this paper, a new 3D-PDD (Position Determination Device) is developed based on PSD Sensitive Detector) sensor. Vision sensor uses camera modules, and relative position distance from target point to sensors are calculated via stereo vision. A LED driver module at consists of IR LEDs chip, emits Infrared Ray proportional the distance. DSP processes analog signal band pass filter. Camera calibration implemented by way high order polynomial in compensate lens distortion. Effectiveness...
This study proposes an Extended Kalman Filter (EKF) that considers dynamics to diagnose thrust faults in lift-cruise type UAVs. A diagnostic logic, based on the residuals of roll and pitch rates calculated using EKF-estimated values, is devised determine location faults. The EKF also provides real-time estimates health values for each rotor. Numerical simulations validate efficiency proposed fault diagnosis method, demonstrating its ability rapidly identify locations.
A single tilt-wing UAV has a new-concept hybrid configuration for adopting the advantages of both fixed-wing and rotary-wing aircraft. This paper presents dynamic modeling analysis which is composed tilted main wing, fuselage, tail variable pitch propeller. The wing can be divided into fixed section. section located at outer an electric propulsive system each side. used improving control performance during vertical flight. derived by forces moments UAV. Momentum theory blade element are...
Given a cooperative mission consisting of multiple tasks spatially distributed, an aerial robotic swarm’s decision-making issues include team formation, team-to-task assignment, agent-to-work-position assignment and trajectory optimisation with collision avoidance. The problem becomes even more complicated when involving heterogeneous agents, tasks’ minimum requirements fair allocation. This paper formulates all the combined as then proposes integrated framework that addresses in...
Tracking control system based on linear quadratic (LQ) tracker is designed for a ducted-fan unmanned aerial vehicle (UAV) under full flight envelope including hover, transition, and cruise modes. To design the LQ tracker, matrix augmented with tracking error term. Then input can be calculated to solve single Riccati equation, but steady-state errors might still remain in this system. In order reduce errors, integrator (LQTI) add an integral term of state vector. performance proposed...