• Title/Summary/Keyword: Flight Dynamics Modeling

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Flight Dynamics Modeling Using Quaternions (쿼터니언을 이용한 비행운동 모델링)

  • 황명신;박욱제
    • 제어로봇시스템학회:학술대회논문집
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    • 2000.10a
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    • pp.187-187
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    • 2000
  • This paper presents the comparison of Euler-Rodrigues quaternion and Euler Angles using attitude kinematics for aircraft flight simulation. It is hard for PC-Level to accomplish real-time simulation. The purpose of this paper is to accomplish real-time simulation of the aircraft dynamics modeling parts and the graphics parts. The computation time is more reduced in case of applying quaternions than Euler Angles. This paper provides a quaternions algorithm and it's applications for the real-time simulation.

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Flight Dynamics Analyses of a Propeller-Driven Airplane (I): Aerodynamic and Inertial Modeling of the Propeller

  • Kim, Chang-Joo;Kim, Sang Ho;Park, TaeSan;Park, Soo Hyung;Lee, Jae Woo;Ko, Joon Soo
    • International Journal of Aeronautical and Space Sciences
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    • v.15 no.4
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    • pp.345-355
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    • 2014
  • This paper focuses on aerodynamic and inertial modeling of the propeller for its applications in flight dynamics analyses of a propeller-driven airplane. Unsteady aerodynamic and inertial loads generated by the propeller are formulated using the blade element method, where the local velocity and acceleration vectors for each blade element are obtained from exact kinematic relations for general maneuvering conditions. Vortex theory is applied to obtain the flow velocities induced by the propeller wake, which are used in the computation of the aerodynamic forces and moments generated by the propeller and other aerodynamic surfaces. The vortex lattice method is adopted to obtain the induced velocity over the wing and empennage components and the related influence coefficients are computed, taking into account the propeller induced velocities by tracing the wake trajectory trailing from each of the propeller blades. Aerodynamic forces and moments of the fuselage and other aerodynamic surfaces are computed by using the wind tunnel database and applying strip theory to incorporate viscous flow effects. The propeller models proposed in this paper are applied to predict isolated propeller performances under steady flight conditions. Trimmed level forward and turn flights are analyzed to investigate the effects of the propeller on the flight characteristics of a propeller-driven light-sports airplane. Flight test results for a series of maneuvering flights using a scaled model are employed to run the flight dynamic analysis program for the proposed propeller models. The simulations are compared with the flight test results to validate the usefulness of the approach. The resultant good correlations between the two data sets shows the propeller models proposed in this paper can predict flight characteristics with good accuracy.

Parameter Estimation of a Small-Scale Unmanned Helicopter by Automated Flight Test Method (자동화 비행시험기법에 의한 소형 무인헬리콥터의 파라메터 추정)

  • Bang, Keuk-Hee;Kim, Nak-Wan;Hong, Chang-Ho;Suk, Jin-Young
    • Journal of Institute of Control, Robotics and Systems
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    • v.14 no.9
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    • pp.916-924
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    • 2008
  • In this paper dynamic modeling parameters were estimated using a frequency domain estimation method. A systematic flight test method was employed using preprogrammed multistep excitation of the swashplate control input. In addition when one axis is excited, the autopilot is engaged in the other axis, thereby obtaining high-quality flight data. A dynamic model was derived for a small scale unmanned helicopter (CNUHELI-020, developed by Chungnam National University) equipped with a Bell-Hiller stabilizer bar. Six degree of freedom equations of motion were derived using the total forces and moments acting on the small scale helicopter. The dynamics of the main rotor is simplified by the first order tip-path plane, and the aerodynamic effects of fuselage, tail rotor, engine, and horizontal/vertical stabilizer were considered. Trim analysis and linearized model were used as a basic model for the parameter estimation. Doublet and multistep inputs are used to excite dynamic motions of the helicopter. The system and input matrices were estimated in the frequency domain using the equation error method in order to match the data of flight test with those of the dynamic modeling. The dynamic modeling and the flight test show similar time responses, which validates the consequence of analytic modeling and the procedures of parameter estimation.

9-DOF Modeling and Turning Flight Simulation Evaluation for Parachute (9-DOF 낙하산 모델링 및 선회비행 시뮬레이션 검증)

  • Lee, Sang-Jong;Min, Byoung-Mun
    • Journal of the Korea Academia-Industrial cooperation Society
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    • v.17 no.9
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    • pp.688-693
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    • 2016
  • This paper describes the parachute dynamics modeling and simulation results for the development of training simulator of a HALO (High Altitude Low Opening) parachute, which is currently in use for military purposes. The target parachute is a rectangular shaped parafoil and its dynamic model is derived based on the real geometry data as the 9-DOF nonlinear equations of dynamics. The simulation was conducted through the moment of inertia and its aerodynamic derivatives to reflect the real characteristics based on the MATLAB/Simulink. In particular, its modeling includes the typical characteristics of the added mass and moment of inertia, which is shown in the strong effects in Lighter-Than-Air(LTA) flight vehicle. The proposed dynamic modeling was evaluated through the simulation under the spiral turning flight conditions of the asymmetric control inputs and compared with the performance index in the target parachute manual.

Flight Dynamics Analyses of a Propeller-Driven Airplane (II): Building a High-Fidelity Mathematical Model and Applications

  • Kim, Chang-Joo;Kim, Sang Ho;Park, TaeSan;Park, Soo Hyung;Lee, Jae Woo;Ko, Joon Soo
    • International Journal of Aeronautical and Space Sciences
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    • v.15 no.4
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    • pp.356-365
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    • 2014
  • This paper is the second in a series and aims to build a high-fidelity mathematical model for a propeller-driven airplane using the propeller's aerodynamics and inertial models, as developed in the first paper. It focuses on aerodynamic models for the fuselage, the main wing, and the stabilizers under the influence of the wake trailed from the propeller. For this, application of the vortex lattice method is proposed to reflect the propeller's wake effect on those aerodynamic surfaces. By considering the maneuvering flight states and the flow field generated by the propeller wake, the induced velocity at any point on the aerodynamic surfaces can be computed for general flight conditions. Thus, strip theory is well suited to predict the distribution of air loads over wing components and the viscous flow effect can be duly considered using the 2D aerodynamic coefficients for the airfoils used in each wing. These approaches are implemented in building a high-fidelity mathematical model for a propeller-driven airplane. Flight dynamic analysis modules for the trim, linearization, and simulation analyses were developed using the proposed techniques. The flight test results for a series of maneuvering flights with a scaled model were used for comparison with those obtained using the flight dynamics analysis modules to validate the usefulness of the present approaches. The resulting good correlations between the two data sets demonstrate that the flight characteristics of the propeller-driven airplane can be analyzed effectively through the integrated framework with the propeller and airframe aerodynamic models proposed in this study.

Longitudinal Flight Dynamic Modeling and Stability Analysis of Flapping-wing Micro Air Vehicles (날갯짓 비행 로봇의 세로방향 비행 동역학 모델링 및 안정성 해석)

  • Kim, Joong-Kwan;Han, Jong-Seob;Kim, Ho-Young;Han, Jae-Hung
    • Journal of Institute of Control, Robotics and Systems
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    • v.21 no.1
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    • pp.1-6
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    • 2015
  • This paper investigates the longitudinal flight dynamics and stability of flapping-wing micro air vehicles. Periodic external forces and moments due to the flapping motion characterize the dynamics of this system as NLTP (Non Linear Time Periodic). However, the averaging theorem can be applied to an NLTP system to obtain an NLTI (Non Linear Time Invariant) system which allows us to use a standard eigen value analysis to assess the stability of the system with linearization around a reference point. In this paper, we investigate the dynamics and stability of a hawkmoth-scale flapping-wing air vehicle by establishing an LTI (Linear Time Invariant) system model around a hovering condition. Also, a direct time integration of full nonlinear equations of motion of the flapping-wing micro air vehicle is conducted to see how the longitudinal flight dynamics appear in the time domain beyond the reference point, i.e. hovering condition. In the study, the flapping-wing air vehicle exhibited three distinct dynamic modes of motion in the longitudinal plane of motion: two stable subsidence modes and one unstable oscillatory mode. The unstable oscillatory mode is found to be a combination of a pitching velocity state and a forward/backward velocity state.

Flight Control Test of Quadrotor-Plane with Hybrid Flight Mode of VTOL and Fast Maneuverability (Hybrid 비행 모드를 갖는 Quadrotor-Plane의 비행제어실험)

  • Kim, Dong-Gyun;Lee, Byoungjin;Lee, Young Jae;Sung, Sangkyung
    • Journal of Institute of Control, Robotics and Systems
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    • v.22 no.9
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    • pp.759-765
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    • 2016
  • This paper presents the principle, dynamics modeling and control, hardware implementation, and flight test result of a hybrid-type unmanned aerial vehicle (UAV). The proposed UAV was designed to provide both hovering and fixed-wing type aerodynamic flight modes. The UAV's flight mode transition was achieved through the attitude transformation in pitch axis, which avoids a complex rotor tilt mechanism from a structural and control viewpoint. To achieve this, a different navigation coordinate was introduced that avoids the gimbal lock in pitch singularity point. Attitude and guidance control algorithms were developed for the flight control system. For flight test purposes, a quadrotor attached with a tailless fixed-wing structure was manufactured. An onboard flight control computer was designed to realize the navigation and control algorithms and the UAV's performance was verified through the outdoor flight tests.

Study on Dynamics Modeling and Depth Control for a Supercavitating Underwater Vehicle in Transition Phase (초공동 수중운동체의 천이구간 특성을 고려한 동역학 모델링 및 심도제어 연구)

  • Kim, Seon Hong;Kim, Nakwan
    • Journal of the Society of Naval Architects of Korea
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    • v.51 no.1
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    • pp.88-98
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    • 2014
  • A supercavitation is modern technology that can be used to reduce the frictional resistance of the underwater vehicle. In the process of reaching the supercavity condition which cavity envelops whole vehicle body, a vehicle passes through transition phase from fully-wetted to supercaviting operation. During this phase of flight, unsteady hydrodynamic forces and moments are created by partial cavity. In this paper, analytical and numerical investigations into the dynamics of supercavitating vehicle in transition phase are presented. The ventilated cavity model is used to lead rapid supercavity condition, when the cavitation number is relatively high. Immersion depth of fins and body, which is decided by the cavity profile, is calculated to determine hydrodynamical effects on the body. Additionally, the frictional drag reduction associated by the downstream flow is considered. Numerical simulation for depth tracking control is performed to verify modeling quality using PID controller. Depth command is transformed to attitude control using double loop control structure.

Nonlinear Adaptive Flight Control Using Neural Networks and Backstepping (신경회로망 및 Backstepping 기법을 이용한 비선형 적응 비행제어)

  • Lee, Taeyoung;Kim, Youdan
    • Journal of Institute of Control, Robotics and Systems
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    • v.6 no.12
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    • pp.1070-1078
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    • 2000
  • A nonlinear adaptive flight control system is proposed using a backstepping controller with neural network controller. The backstepping controller is used to stabilize all state variables simultaneously without the two-timescale assumption that separates the fast dynamics, involving the angular rates of the aircraft, from the slow dynamics which includes angle of attack, sideslip angle, and bank angle. It is assumed that the aerodynamic coefficients include uncertainty, and an adaptive controller based on neural networks is used to compensate for the effect of the aerodynamic modeling error. It is shown by the Lyapunov stability theorem that the tracking errors and the weights of neural networks exponentially converge to a compact set. Finally, nonlinear six-degree-of-freedom simulation results for an F-16 aircraft model are presented to demonstrate the effectiveness of the proposed control law.

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Establishment of Flight Simulation Environment for Evaluation of Helicopter Flying Quality (헬리콥터 비행성 평가를 위한 모의비행시험 환경의 구현)

  • Han, Dong-Ju;Lee, Sang-Haeng
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.9
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    • pp.783-791
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    • 2007
  • For an access to specified helicopter simulator qualification's level C or FTD(Flight Training Device) level 5 of FAA(Federal Aviation Administration) AC(Advisory Circular) 120-63, the mathematical model of a single rotor helicopter flight dynamics is investigated. From the rotorcraft simulation model validated by evaluation of its flight performance, the feasibility of the flight dynamic model that is selected for its effectiveness has been proved. Thereby the simulation environment for evaluation of helicopter flying quality is established with the development of FTD for training and testing the flight performance.