The Design and Simulation of Low-Cost and Super-Applicability Flight Control System of Super-Size UAV

2012 ◽  
Vol 466-467 ◽  
pp. 1156-1161
Author(s):  
Liu Rong ◽  
Yu Ping Lu
Keyword(s):  
Control System ◽  
Flight Control ◽  
Low Cost ◽  
Control Technique ◽  
Flight Control System ◽  
Flight Curve ◽  
Aerial Vehicle ◽  
The Stability ◽  
High Flexibility ◽  
The Cost

In this paper, considering the stability and robustness of the aircraft, the flight control system is designed following the aspect of high flexibility and low cost. Comparing with the flight control system of super-size high-subsonic Unmanned Aerial Vehicle (UAV) in the world, the system presented in this paper has adopted the inimitable control technique of flying-off course、low-cost combinatorial navigation strategy and the advanced safety scheme, which can guarantee the performance, degrade the cost and extend the airspace and groundspace of the aircraft.Through quite a few simulations, the results show that this system can guarantee the attitude and altitude stable. The error between the flight path and programming path is very small. Flight curve is prefect; and the system performances can be achieved completely.

Design and Implementation of a Detection Device for Flight Control System in Unmanned Aerial Vehicle

2011 ◽  
Vol 121-126 ◽  
pp. 764-767 ◽  
Author(s):  
Hong Jun Zhang ◽  
Lu Wen Jun ◽  
Li Biao Tong
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicle ◽  
Flight Control ◽  
Low Cost ◽  
Flight Control System ◽  
Angle Sensor ◽  
Calibration Table ◽  
Aerial Vehicle ◽  
Overall Performance ◽  
Command Center

Flight control system (FCS) is the command center for the unmanned aerial vehicle (UAV). A low-cost, high-precision micro-UAV attitude calibration table is designed by utilizing the structure of the vertical gyroscope of the flight attitude angle sensor. The detection device for the UAV FCS developed by loop-in-simulation achieves unmanned attitude calibration and overall performance detection of the FCS.

Study of Low Cost Micro Autopilot for Fixed-Wing UAV

2011 ◽  
Vol 317-319 ◽  
pp. 1672-1676
Author(s):  
Wei Xiong ◽  
Zhao Ying Zhou ◽  
Xiao Yan Liu
Keyword(s):  
Control System ◽  
Flight Control ◽  
Low Cost ◽  
Cost Effective ◽  
System Structure ◽  
Gps Receiver ◽  
Flight Control System ◽  
Sensor Configuration ◽  
The Cost ◽  
And Control

From the cost-effective viewpoint of low cost Bank-to-Turn (BTT) Unmanned Air Vehicles (UAV) and target drone, a low cost flight control system, with the fewest number of sensors, is studied in this paper for the fixed-wing UAV. The structure of the control system is described which is able to estimate necessary information to provide stabilization and guidance for a small fixed wing BTT UAV. The practical flight control system structure and control law for roll hold loop, altitude hold loop, trajectory tracking loop are designed based on the sensor configuration with only a MEMS rate gyro, a MEMS pressure sensor and global positioning system (GPS) receiver only. A prototype low cost autopilot is trial-produced to control a typical UAV. The Experimental results show the effectiveness of navigation and control methods of f the proposed methodology.

System identification and robust attitude control of an unmanned helicopter using novel low-cost flight control system

2019 ◽  
Vol 234 (5) ◽  
pp. 634-645
Author(s):  
Mohammad Hossein Khalesi ◽  
Hassan Salarieh ◽  
Mahmoud Saadat Foumani
Keyword(s):  
Control System ◽  
Robust Control ◽  
System Identification ◽  
Flight Control ◽  
Low Cost ◽  
Superior Performance ◽  
Raspberry Pi ◽  
Unmanned Helicopter ◽  
Flight Control System ◽  
Robust Control System

In recent years, unmanned aerial systems have attracted great attention due to the electronic systems technology advancements. Among these vehicles, unmanned helicopters are more important because of their special abilities and superior performance. The complex nonlinear dynamic system (caused by main rotor flapping dynamics coupled with the rigid body rotational motion) and considerable effects of ambient disturbance make their utilization hard in actual missions. Attitude dynamics have the main role in helicopter stabilization, so implementing proper control system for attitude is an important issue for unmanned helicopter hovering and trajectory tracking performance. Besides this, experimental utilization of low-cost flight control system for unmanned helicopters is still a challenging task. In this article, dynamic modeling, system identification, and robust control system implementation of roll and pitch dynamics of an unmanned helicopter is performed. A TRex-600E radio-controlled helicopter is equipped with a novel low-cost flight control system designed and constructed based on Raspberry Pi Linux-based microcomputer. Using Raspberry Pi makes this platform simpler to utilize and more time and cost-effective than similar platforms used before. The experiments are performed on a 5-degree-of-freedom testbed. The robust control system is designed based on [Formula: see text] method and is evaluated in real flight tests. The experiment results show that the proposed platform has the ability to successfully control the roll and pitch dynamics of the unmanned helicopter.

PID Control Based Missile Sub-Channel Simulation

2012 ◽  
Vol 433-440 ◽  
pp. 7011-7016 ◽  
Author(s):  
Chao Bo Chen ◽  
Bing Liu ◽  
Ning He ◽  
Song Gao ◽  
Quan Pan
Keyword(s):  
Control System ◽  
Real Time ◽  
Flight Control ◽  
Pid Control ◽  
Pid Controller ◽  
Channel Model ◽  
Control Method ◽  
Flight Control System ◽  
Aerodynamic Control ◽  
The Stability

The accuracy and real-time of modern missile flight control system of traditional aerodynamic can not be satisfied. In this paper a new method is presented to improve the accuracy and real-time of missiles under this condition. First of all, a missile sub-channel model of the dynamic equations and steering gear is established, then based on the established model, using PID controller to control steering gear and three channels of missile pitch, yaw, roll respectively which is called missile sub-channel PID control method, and finally making use of MATLAB/Simulink to complete the simulation. Simulation results show that compared with traditional aerodynamic control system, this method can reduce the response time of aerodynamic missile and enhance the stability of the control system obviously.

scholarly journals Robust dynamic inversion control of flight control system based on L1 adaptive structure

2021 ◽  
Vol 39 (5) ◽  
pp. 995-1004
Author(s):  
Yu LI ◽  
Xiaoxiong LIU ◽  
Ruichen MING ◽  
Shaoshan SUN ◽  
Weiguo ZHANG
Keyword(s):  
Control System ◽  
Flight Control ◽  
Dynamic Performance ◽  
Dynamic Inversion ◽  
Control Law ◽  
Flight Control System ◽  
Parameter Uncertainties ◽  
Strong Robustness ◽  
Adaptive Structure ◽  
The Stability

Nonlinear Dynamic Inversion(NDI) control has excellent rapidity and decoupling ability, unfortunately it lacks the essential robustness to disturbance. From the perspective of enhancing the robustness, an adaptive NDI method based on L1 adaptive structure is proposed. The L1 adaptive structure is introduced into the NDI control to enhance its robustness, which also guarantees the stability and expected dynamic performance of the system suffering from the disturbance influence. Secondly, the flight control law of the advanced aircraft is designed based on the present method to improve the robustness and fault tolerance of the flight control system. Finally, the effectiveness of the flight control law based on the present approach is verified under the fault disturbance. The results showed that the flight control law based on L1 adaptive NDI has excellent dynamic performance and strong robustness to parameter uncertainties and disturbances.

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