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Flight Control System Simulation Platform for UAV Based on Integrating Simulink With Stateflow  [cached]
Gao Yanhui,Xiao Qiangui,Hu Shousong,Ju Xiao
TELKOMNIKA : Indonesian Journal of Electrical Engineering , 2012, DOI: 10.11591/telkomnika.v10i5.1345
Abstract: Aiming at rapidly analyzing and validating control strategy, control law and flight mode of the Unmanned Aerial Vehicle (UAV), a digital simulation test platform for flight control system (FCS) of UAV is presented in this paper. The platform is built on principles of hierarchy and modularity, its core is composed of flight mode management and control module, and the two components are implemented by using Matlab/Stateflow and embedded Simulink Function respectively. Simulation test for a certain type of UAV with a variety of flight mode, including remote control and autonomic flight, is achieved. Compared with actual flight test, the results of the simulation validate the rationality and validity of the modeling theories and method. Practices show that developing new type or modified FCS of UAV through this platform, similarity between simulation model and real aircraft can be improved, and this is useful to minimize the risk and increase flexibility for design changes.
The New Evolution for SIA Rotorcraft UAV Project  [PDF]
Juntong Qi,Dalei Song,Lei Dai,Jianda Han,Yuechao Wang
Journal of Robotics , 2010, DOI: 10.1155/2010/743010
Abstract: This paper describes recent research on the design, implement, and testing of a new small-scaled rotorcraft Unmanned Aerial Vehicle (RUAV) system—ServoHeli-40. A turbine-powered UAV weighted less than 15?kg was designed, and its major components were tested at the Shenyang Institute of Automation, Chinese Academy of Sciences in Shenyang, China. The aircraft was designed to reach a top speed of more than 20?mps, flying a distance of more than 10 kilometers, and it is going to be used as a test-bed for experimentally evaluating advanced control methodologies dedicated on improving the maneuverability, reliability, as well as autonomy of RUAV. Sensors and controller are all onboard. The full system has been tested successfully in the autonomous mode using the multichannel active modeling controller. The results show that in a real windy environment the rotorcraft UAV can follow the trajectory which was assigned by the ground control station exactly, and the new control method is obviously more effective than the one in the past year's research. 1. Introduction Unmanned aerial vehicles (UAVs) are useful for many applications where human intervention is considered difficult or dangerous. Traditionally, the fixed-wing UAV has been served as the unit for these dangerous tasks because the control is easy. Rotary-wing UAV, on the other hand, can be used in many different tasks where the fixed-wing one is unable to achieve, such as vertical take-off/landing, hovering, lateral flight, pirouette, and bank-to-turn. Due to the versatility in maneuverability, helicopters are capable to fly in and out of restricted areas and hover efficiently for long periods of time. These characteristics make RUAV applicable for many military and civil applications. However, the control of RUAV is difficult. Although some control algorithms have been proposed [1–6], most of them were verified by simulation instead of real experiments. One reason for this is due to the complicate, nonlinear, and inherently unstable dynamics, which has cross coupling between main and tail rotor, and lots of time-varying aerodynamic parameters. Another reason is that the flight test is in high risk. If an RUAV lost its control, it would never be stabilized again. Based on our UAV research in [7], this paper details the development of a new unmanned helicopter (UAV) test bed—ServoHeli-40 (Figure 1) and the advanced control experiments performed toward achieving full autonomous flight. The experimental platform which has 40 kilograms takeoff weight is designed and finished by our research group in
Mathematical Modeling of Aerodynamic Space -to - Surface Flight with Trajectory for Avoid Intercepting Process  [PDF]
Serge Gornev
Computer Science , 2006,
Abstract: Modeling has been created for a Space-to-Surface system defined for an optimal trajectory for targeting in terminal phase with avoids an intercepting process. The modeling includes models for simulation atmosphere, speed of sound, aerodynamic flight and navigation by an infrared system. The modeling and simulation includes statistical analysis of the modeling results.
Modeling of aerodynamic Space-to-Surface flight with optimal trajectory for targeting  [PDF]
Serge Gornev
Computer Science , 2003,
Abstract: Modeling has been created for a Space-to-Surface system defined for an optimal trajectory for targeting in terminal phase. The modeling includes models for simulation atmosphere, speed of sound, aerodynamic flight and navigation by an infrared system. The modeling simulation includes statistical analysis of the modeling results.
Моделювання композиц йного та розпод леного керування висотою польоту пов тряного судна SIMULATION RESULTS OF COMPOSITED AND INTEGRATED AIRCRAFT FLIGHT ALTITUDE CONTROL SYSTEM Моделирование композиционного и распределённого управления высотой полёта воздушного судна  [cached]
Kateryna Kopytova
Proceedings of National Aviation University , 2013,
Abstract: Розглянуто результати моделювання схеми системи керування висотою польоту в дхиленням руля висоти та комплексно схеми системи керування висотою польоту з розпод леною аеродинам чною схемою поверхонь керування. The article deals with simulation results of the structure of flight altitude control system by means of elevator rudder controlling and integrated the structure of flight altitude control system by means of composited control over aerodynamic configuration of control surfaces. Рассмотрены результаты моделирования схемы системы управления высотой полёта отклонением руля высоты и комплексной схемы системы управления высотой полёта с распределённой аэродинамической схемой поверхностей управления
Research of UAV Flight Planning Parameters  [PDF]
Jing He, Yongshu Li, Keke Zhang
Positioning (POS) , 2012, DOI: 10.4236/pos.2012.34006
Abstract: UAV remote sensing as a digital aerial photography, not only has some basic photogrammetry features, but also has some other features. In this paper, aim at the characteristics of UAV remote sensing, begin with image data acquisition, the various parameter setting in the route planning were introduced, some of the principle was analyzed, the design of control points was described, and some of the considerations when laid control points were summarized.
Mathematical Modeling of Aerodynamic Space -to - Surface Flight with Trajectory for Avoid Intercepting Process for Safety and Security Issues  [PDF]
Serge Gorneff
Computer Science , 2009,
Abstract: The research project has been made for mathematical modeling of aerospace system Space-to-Surface for avoid intercepting process by flight objects Surface-to-Air. The research has been completed and created mathematical models which used for research and statistical analysis. In mathematical modeling has been including a few models: Model of atmosphere, Model of speed of sound, Model of flight head in space, Model of flight in atmosphere, Models of navigation and guidance, Model and statistical analysis of approximation of aerodynamic characteristics. Modeling has been created for a Space-to-Surface system defined for an optimal trajectory in terminal phase. The modeling includes models for simulation atmosphere, aerodynamic flight and navigation by an infrared system. The modeling simulation includes statistical analysis of the modeling results.
Effect of an external vortex on the uav aerodynamic performances  [cached]
Boudaoud Warda,Yahiaoui Tayeb,Imine Bachir,Imine Omar
EPJ Web of Conferences , 2012, DOI: 10.1051/epjconf/20122501104
Abstract: In this present work, the CFD and wind tunnel are used to investigate the effect of an external vortex around an UAV in order to obtain initial estimates of lift and drag coefficients with flow velocity of 30 meters per second for various angles of attack. The model of Spalart- Allmaras turbulence is used for the investigation of the complex flow around the UAV. The wind tunnel and CFD results are compared and appropriate error bands placed on the data.
Hardware In The Loop Simulator in UAV Rapid Development Life Cycle  [PDF]
Widyawardana Adiprawita,Adang Suwandi Ahmad,Jaka Semibiring
Computer Science , 2008,
Abstract: Field trial is very critical and high risk in autonomous UAV development life cycle. Hardware in the loop (HIL) simulation is a computer simulation that has the ability to simulate UAV flight characteristic, sensor modeling and actuator modeling while communicating in real time with the UAV autopilot hardware. HIL simulation can be used to test the UAV autopilot hardware reliability, test the closed loop performance of the overall system and tuning the control parameter. By rigorous testing in the HIL simulator, the risk in the field trial can be minimized.
In-flight collision avoidance controller based only on OS4 embedded sensors
Becker, Marcelo;Sampaio, Rafael Coronel B.;Bouabdallah, Samir;Perrot, Vincent de;Siegwart, Roland;
Journal of the Brazilian Society of Mechanical Sciences and Engineering , 2012, DOI: 10.1590/S1678-58782012000300010
Abstract: the major goal of this research was the development and implementation of a control system able to avoid collisions during the flight for a mini-quadrotor helicopter, based only on its embedded sensors without changing the environment. however, it is important to highlight that the design aspects must be seriously considered in order to overcome hardware limitations and achieve control simplification. the controllers of a uav (unmanned aerial vehicle) robot deal with highly unstable dynamics and strong axes coupling. furthermore, any additional embedded sensor increases the robot total weight and therefore, decreases its operating time. the best balance between embedded electronics and robot operating time is desired. this paper focuses not only on the development and implementation of a collision avoidance controller for a mini-robotic helicopter using only its embedded sensors, but also on the mathematical model that was essential for the controller developing phases. based on this model we carried out the development of a simulation tool based on matlab/simulink that was fundamental for setting the controllers' parameters. this tool allowed us to simulate and improve the os4 controllers in different modeled environments and test different approaches. after that, the controllers were embedded in the real robot and the results proved to be very robust and feasible. in addition to this, the controller has the advantage of being compatible with future path planners that we are developing.
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