scholarly journals Development of Mobile Ground Control System and GPS Base Auto Tracking Antenna

2018 ◽  
Vol 16 (1) ◽  
pp. 83 ◽  
Author(s):  
Herma Yudhi Irwanto
Keyword(s):  
Control System ◽  
Monitoring System ◽  
Unmanned Aerial Vehicle ◽  
High Speed ◽  
Flight Test ◽  
Simulation System ◽  
Ground Control ◽  
Hardware In The Loop ◽  
Automatic Tracking ◽  
Aerial Vehicle

Flight test of both rocket and high speed Unmanned Aerial Vehicle (UAV), which is currently developed by LAPAN, can not be separated from the need for a monitoring system of all the attitude of the vehicles. Utilizing and combining some of the available equipment components into a ground control system (GCS) equipped with GPS based auto tracking antenna, makes it easy in previous flight test activities that only do tracking antenna manually. This ground control system is equipped with automatic tracking antenna that always leads to the vehicle, so that the data attitude of flying the vehicle will be maximally monitored and analyzed directly with ease. This system has been tested on a laboratory scale related to testing using hardware in the loop simulation system

scholarly journals Control and flight test of a tilt-rotor unmanned aerial vehicle

2017 ◽  
Vol 14 (1) ◽  
pp. 172988141667814 ◽  
Author(s):  
Chao Chen ◽  
Jiyang Zhang ◽  
Daibing Zhang ◽  
Lincheng Shen
Keyword(s):  
Unmanned Aerial Vehicle ◽  
High Speed ◽  
Cross Coupling ◽  
Flight Test ◽  
Control Allocation ◽  
Tilt Rotor ◽  
Satisfactory Performance ◽  
Allocation Method ◽  
Aerial Vehicle ◽  
The Cost

Tilt-rotor unmanned aerial vehicles have attracted increasing attention due to their ability to perform vertical take-off and landing and their high-speed cruising abilities, thereby presenting broad application prospects. Considering portability and applications in tasks characterized by constrained or small scope areas, this article presents a compact tricopter configuration tilt-rotor unmanned aerial vehicle with full modes of flight from the rotor mode to the fixed-wing mode and vice versa. The unique multiple modes make the tilt-rotor unmanned aerial vehicle a multi-input multi-output, non-affine, multi-channel cross coupling, and nonlinear system. Considering these characteristics, a control allocation method is designed to make the controller adaptive to the full modes of flight. To reduce the cost, the accurate dynamic model of the tilt-rotor unmanned aerial vehicle is not obtained, so a full-mode flight strategy is designed in view of this situation. An autonomous flight test was conducted, and the results indicate the satisfactory performance of the control allocation method and flight strategy.

scholarly journals The UNMANNED AERIAL VEHICLE (UAV) AIRCRAFT DESIGN GALAK-24 WITH AUTONOMOUS METHOD

2021 ◽  
Vol 2 (Oktober) ◽  
pp. 66-74
Author(s):  
Argo Surono ◽  
Imam Ashar ◽  
Muhamat Maariful Huda
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicle ◽  
Hydraulic System ◽  
Aircraft Design ◽  
Flight Test ◽  
Radio Waves ◽  
Remote Control System ◽  
Aerial Vehicle ◽  
Unmanned System ◽  
Very High

Abstract: Unmanned Aerial Vehicle is a type of aircraft that is controlled by a remote-control system via radio waves. UAV is an unmanned system (Unmanned System), which is an electro-mechanical-based system that can carry out programmed missions with the characteristics of a UAV that is able to fly without a pilot capable of controlling automatically and can run again by carrying several weapons or other tools. An autopilot is a mechanical, electrical, or hydraulic system that guides a vehicle without human intervention. The application of the Autonomous control system on the UAV is carried out by using Autonomous equipment in the form of components such as Flight Controller, GPS, Mission Planner Software and Telemetry. The number of parameters set by the observations made on the movement of the UAV when in Auto mode. The flight test used a square waypoint with a distance of 500 meters on each side. The UAV is able to fly in an Autonomous manner stably using a predetermined Waypoint. This is a pure experiment by means of tool testing and data collection that requires very high attention from the crew and results in fatigue.

scholarly journals Using Fuzzy Logic to Stabilize the Position of a Multi Rotor

2019 ◽  
Vol 49 (4) ◽  
pp. 441-461
Author(s):  
Karol Bęben ◽  
Norbert Grzesik ◽  
Konrad Kuźma
Keyword(s):  
Fuzzy Logic ◽  
Control System ◽  
Unmanned Aerial Vehicle ◽  
Stabilization System ◽  
Hardware In The Loop ◽  
Vertical Takeoff And Landing ◽  
Aerial Vehicle ◽  
Arduino Microcontroller ◽  
Rotor Model ◽  
Vertical Takeoff

Abstract The article is a continuation of research into a stabilization system for the Unmanned Aerial Vehicle of vertical takeoff and landing. The stabilization system was designed on the basis of a fuzzy logic Mamdani type controller. In the framework of the research, the authors built a test stand with a Multi Rotor model, which allows “Hardware In The Loop” testing in real time. The control system was written in the Matlab/Simulink software and implemented to the Arduino microcontroller.

scholarly journals Hardware-in-the-loop simulation of high-speed maglev transportation five-segment propulsion system based on dSPACE

2018 ◽  
Vol 4 (2) ◽  
pp. 62-72
Author(s):  
Feng Qin ◽  
Ying Lin ◽  
Diqiang Lu
Keyword(s):  
Control System ◽  
Real Time ◽  
High Power ◽  
High Speed ◽  
Power Converter ◽  
Simulation System ◽  
Hardware In The Loop ◽  
Real Time Simulation ◽  
Time Simulation ◽  
Propulsion Control

Aim: For exploring and testing the key technology of high-speed maglev transportation propulsion control system, this paper designs and establishes a hardware-in-the-loop (HIL) real-time simulation system of the high-speed maglev transportation five-segment propulsion system. Materials and methods of the studies: According to the route conditions and propulsion segment division of Shanghai maglev demonstration and operation line, the real-time simulation platform based on dSPACE multiprocessor systems is implemented. The simulation system can achieve the functional simulation of all the high-power related equipment in the 5-segment area, including 8 sets of high-power converter units, 2 sets of medium-power converter units, 2 sets of low-power converter units, five-segment trackside switch stations and long-stator linear synchronous motors. The mathematical models of linear motors and converters are built in MATLAB/Simulink and System Generator, after compiling, they can be downloaded and executed in Field Programmable Logic Array (FPGA). All the interfaces connecting the simulation system to the propulsion control system physical equipment use real physical components as in the field, such as analog I/O, digital I/O, optical signals and Profibus. Results: By using CPU+FPGA hardware configuration, the simulation steps are greatly shortened and the response speed and accuracy of real-time simulation system are improved. The simulation system can simulate multiple operating modes such as multi-segment, multi-vehicle, double-track, double-feeding, step-by-step stator section changeover, and so on. The simulation results show that the maximum speed of the simulation system can reach 500 km/h. Conclusion: This HIL system can provide detailed real-time on-line test and verification of high speed maglev propulsion control system.

Pitch Attitude Control Design of Unmanned Aerial Vehicle via Hardware-in-the-Loop Simulation

2013 ◽  
Vol 284-287 ◽  
pp. 2271-2275
Author(s):  
Yun Ping Sun ◽  
Yen Chu Liang
Keyword(s):  
Control System ◽  
Data Acquisition ◽  
Real Time ◽  
Unmanned Aerial Vehicle ◽  
Pid Controller ◽  
Fuzzy Logic Controller ◽  
Hardware In The Loop ◽  
Real Time Control ◽  
Time Control ◽  
Aerial Vehicle

This paper describes an investigative hardware-in-the-loop simulation (HILS) effort through virtual instrumentation on longitudinal control of an unmanned aerial vehicle (UAV). The proportional-integral-differential (PID) controller and fuzzy logic controller (FLC) are designed for the pitch angle hold mode of autopilot; moreover, they are implemented by an embedded real-time control system as a prototype autopilot and tested by hardware-in-the-loop simulation. The hardware configuration of HILS is composed of a personal computer, an embedded real-time control system, several data acquisition devices, servo and sensor unit. The real-time control and data acquisition tasks in HILS is carried out by virtual instruments that is developed by graphical programming language LabVIEW. HILS provides a platform for researchers to correct and improve their design efficiently. The closed-loop performance between PID controller and FLC is evaluated in HILS. The results demonstrate that in the presence of unmodelled dynamics and nonlinear saturation the FLC has an excellent robust performance.

scholarly journals Conversion control of a tilt tri-rotor unmanned aerial vehicle with modeling uncertainty

2021 ◽  
Vol 18 (4) ◽  
pp. 172988142110270
Author(s):  
Chao Chen ◽  
Jiyang Zhang ◽  
Nuan Wang ◽  
Lincheng Shen ◽  
Yiyong Li
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicle ◽  
High Speed ◽  
Position Control ◽  
Velocity Control ◽  
Nonlinear Dynamic Model ◽  
Control Logic ◽  
Modeling Uncertainty ◽  
Conversion Mode ◽  
Aerial Vehicle

The tilt-rotor unmanned aerial vehicle (TRUAV) has vertical take-off and landing and high-speed flight capabilities through conversion and reconversion modes, thereby presenting wide application prospects. This article presents a compact tilt tri-rotor UAV. For flying in the conversion mode, the TRUAV needs to realize the transition of two control logic and two kinds of actuators in both of the rotor and fixed-wing modes, achieving the control of the multi-input multioutput, input nonaffine, and nonlinear multichannel cross-coupling UAV system. Furthermore, the lateral dynamics of a tilt tri-rotor UAV is more unstable for unpaired rotors. These system characteristics present a great challenge to conversion control. To solve these problems, the nonlinear dynamic model of the vehicle in the conversion mode is provided. Furthermore, a cascade control system consisting of position control, velocity control, angle control, angular velocity control, and control mixer is proposed. The simulation result of the control system shows steady flight and a fast transition in the conversion mode with modeling uncertainty in case of no wind.

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