Open Loop Flight Control System

1968 ◽  
Author(s):  
J. R. Younkin
Keyword(s):  
Control System ◽  
Flight Control ◽  
Open Loop ◽  
Flight Control System

IMPROVEMENT OF QUADROTOR PERFORMANCE WITH FLIGHT CONTROL SYSTEM USING PARTICLE SWARM PROPORTIONAL-INTEGRAL-DERIVATIVE (PS-PID)

2017 ◽  
Vol 79 (6) ◽  
Author(s):  
Andi Adriansyah ◽  
Shamsudin H. M. Amin ◽  
Anwar Minarso ◽  
Eko Ihsanto
Keyword(s):  
Control System ◽  
Flight Control ◽  
Pid Controller ◽  
Rapid Development ◽  
Particle Swarm ◽  
Open Loop ◽  
Control Performance ◽  
Proportional Integral Derivative ◽  
Flight Control System ◽  
Advanced Control

The rapid development of microprocessor, electrical, sensors and advanced control technology make a quadrotor fast expansion. Unfortunately, a quadrotor is unstable and impossible to fly in fully open loop system. PID controller is one of methodology that has been proposed to control the flight control system. Unfortunately, adjustment of PID parameters for robust control performance is not easy and still problems. The paper proposed a flight controller system based on a PID controller. The PID parameters are tuned automatically using Particle Swarm Optimization (PSO). Objective of this method is to improve the flight control system performance. Several experiments have been performed. According to these experiments the proposed system able to generate optimal and reliable PID parameters for robust flight controller. The system also has 41.57 % improvement in settling time response.

scholarly journals Multistrand, Fast Reaction, Shape Memory Alloy System for Uninhabited Aerial Vehicle Flight Control

2012 ◽  
Vol 2012 ◽  
pp. 1-8
Author(s):  
M. Brennison ◽  
R. M. Barrett ◽  
L. Kerth
Keyword(s):  
Control System ◽  
Shape Memory Alloy ◽  
Shape Memory ◽  
Flight Control ◽  
Alloy System ◽  
Open Loop ◽  
Flight Control System ◽  
Loop Design ◽  
Aerial Vehicle ◽  
Sma Actuator

This paper details an investigation of shape memory alloy (SMA) filaments which are used to drive a flight control system with precision control in a real flight environment. An antagonistic SMA actuator was developed with an integrated demodulator circuit from a JR NES 911 subscale UAV actuator. Most SMA actuator studies concentrate on modeling the open-loop characteristics of such a system with full actuator performance modeling. This paper is a bit different in that it is very practically oriented and centered on development of a flight-capable system which solves the most tricky, practical problems associated with using SMA filaments for aircraft flight control. By using well-tuned feedback loops, it is shown that intermediate SMA performance prediction is not appropriate for flight control system (FCS) design. Rather, capturing the peak behavior is far more important, along with appropriate feedback loop design. To prove the system, an SMA actuator was designed and installed in the fuselage of a 2 m uninhabited aerial vehicle (UAV) and used to control the rudder through slips and coordinated turns. The actuator was capable of 20 degrees of positive and negative deflection and was capable of 7.5 in-oz (5.29 N cm) of torque at a bandwidth of 2.8 Hz.

scholarly journals Preliminary Validation of the Wind Tunnel Based Flight Control System Evaluation Method

2018 ◽  
Vol 179 ◽  
pp. 03021
Author(s):  
Min Huang ◽  
Zhong-wei Wang ◽  
Xing-Bao Yang ◽  
Zhen-yun Guo ◽  
Yao-bin Niu
Keyword(s):  
Control System ◽  
Wind Tunnel ◽  
Flight Control ◽  
Pitch Angle ◽  
Evaluation Method ◽  
Open Loop ◽  
Control Performance ◽  
Flight Control System ◽  
Pitch Control ◽  
Preliminary Validation

As mathematical models of aircraft aerodynamics and rudder loadings always have to be built in the hardware-in-the-loop simulation, wind tunnel based flight control system (FCS) evaluation methods were proposed in order to test and evaluate the flight control systems under real aerodynamic and rudder loading environment. To validate the evaluation method, a wind tunnel based flight control system test was performed in a hypersonic wind tunnel facility. As the aircraft support rig in the wind tunnel is static, the aircraft angle of attack cannot be changed in this test. During the test, the elevator response, the lift force and the pitching moment were measured. By analysing the measured data, the elevator control performance of the pitch control system was determined, and the pitch angle was successfully predicted, but the open-loop pitch control performance was not determined. These results validate the feasibility of evaluating the elevator control performance and predicting the pitch angle of a FCS by the wind tunnel based FCS evaluation method.

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