J0205-1-6 Study on the Stable Flight COntrol System of the Micro Air Vehicles in the Low Speed Wind Tunnel

2010 ◽  
Vol 2010.6 (0) ◽  
pp. 37-38
Author(s):  
Kiyotaka YAMAMOTO ◽  
Hiroki SHIBATA ◽  
Yoshiyuki KAWAMURA ◽  
Teruo TSUJI
Keyword(s):  
Control System ◽  
Wind Tunnel ◽  
Flight Control ◽  
Micro Air Vehicles ◽  
Flight Control System ◽  
Low Speed ◽  
Low Speed Wind Tunnel ◽  
Air Vehicles

1A2-F01 Development of the Stable Flight Experimental System in the Low Speed Wind Tunnel for Biomimetic Micro Air Vehicles

2009 ◽  
Vol 2009 (0) ◽  
pp. _1A2-F01_1-_1A2-F01_4
Author(s):  
Hiroki SHIBATA ◽  
Atsushi KONDO ◽  
Yoshihiro NAGAHUCHI ◽  
Tomohiro YOSHIDA ◽  
Kazumi OGAWA ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Experimental System ◽  
Micro Air Vehicles ◽  
Low Speed ◽  
Low Speed Wind Tunnel ◽  
Air Vehicles

Divergence Speed Prediction for Practical Slung Load Shapes

2015 ◽  
Author(s):  
Brandon Liberi ◽  
Chau Ton ◽  
Narayanan Komerath
Keyword(s):  
Control System ◽  
Robust Control ◽  
Wind Tunnel ◽  
Flight Control ◽  
Flight Control System ◽  
Wind Tunnel Experiments ◽  
Flight Testing ◽  
Flight Vehicles ◽  
Analytical Functions ◽  
Speed Prediction

Given the innumerable combinations of flight vehicles, loads and flight conditions, alternatives are sought to flight testing, to certify the safe flight speed with slung loads. With well-resolved airload maps now feasible for arbitrary shapes as analytical functions, dynamic simulation predicts divergence speeds, regardless of the symmetry of the object. Likely modes of amplification are found using wind tunnel experiments with free-swinging objects. A robust control formulation enables safe flight close to divergence speed where the flight control system can prevent disturbance amplification.

Design of the wind tunnel based virtual flight testing evaluation method for flight control systems

2016 ◽  
Vol 232 (1) ◽  
pp. 17-29
Author(s):  
Min Huang ◽  
Zhong-wei Wang ◽  
Zhen-yun Guo ◽  
Yao-bin Niu
Keyword(s):  
Control System ◽  
Wind Tunnel ◽  
Control Systems ◽  
Flight Control ◽  
Evaluation Method ◽  
Simulation Models ◽  
Hardware In The Loop ◽  
Flight Control System ◽  
Flight Testing ◽  
Simulation Evaluation

In order to provide a method for evaluating flight control systems with the wind tunnel based virtual flight testing and provide a guide for building virtual flight testing systems, the virtual flight testing evaluation method was researched. The virtual flight testing evaluation method consisted of three parts: virtual flight testing method, virtual flight testing data processing method, and flight control system performance determination method, which were respectively designed for a pitching control system. Then, the hardware-in-the-loop simulation evaluation method was presented, and comparisons between the virtual flight testing and hardware-in-the-loop simulation evaluation method were conducted to highlight the characteristics of virtual flight testing evaluation method. Finally, virtual flight testing simulation models of a sample air vehicle were built and virtual flight testing were simulated to demonstrate the virtual flight testing evaluation method, which is helpful for the understanding of the virtual flight testing evaluation method with more sensibility. The evaluation results show that the virtual flight testing evaluation method designed can be used for flight control system evaluation.

Video Tracking Control Algorithms for Unmanned Air Vehicles

2008 ◽  
Author(s):  
Ricardo Bencatel ◽  
Joa˜o Correia ◽  
Joa˜o Borges Sousa ◽  
Gil M. Gonc¸alves ◽  
Elo´i Pereira
Keyword(s):  
Control System ◽  
Flight Control ◽  
Tracking Control ◽  
Video Tracking ◽  
Control Algorithms ◽  
Unmanned Air Vehicles ◽  
Hybrid Automata ◽  
Simulation Environment ◽  
Flight Control System ◽  
Air Vehicles

We present and discuss a modular flight control system suitable for video tracking natural structures with Unmanned Air Vehicles (UAVs), like rivers, roads or canals. The control system is modeled in the framework of hybrid automata, where each state corresponds to different control algorithms. We implemented four nonlinear turn-rate control algorithms and compared them in a simulation environment to assess tracking performance.

Design of the Flight Control System for a Small-Scale Helicopter

2013 ◽  
Vol 380-384 ◽  
pp. 459-462
Author(s):  
Yu Hu Du ◽  
Jian Cheng Fang
Keyword(s):  
Control System ◽  
Flight Control ◽  
Small Scale ◽  
Unmanned Helicopter ◽  
Flight Control System ◽  
Low Speed ◽  
Ground Station ◽  
Aerial Vehicles ◽  
Small Scale Helicopter

Compared with the fixed-wing aerial vehicles, small-scale unmanned helicopter (SUH) has the advantages of taking off and landing vertically, cruising under ultra low speed, and sustained hovering in the air. SUH has properties of nonlinear, unstable, strongly coupling, and applying control system for SUH is considered as a challenging task. This paper presents the design of the flight control system for a SUH. This flight control system consists of two parts, namely, ground station and onboard part. Various experiments have been conducted to test the performance of this flight control system, and some of the results are presented at the end.

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.

scholarly journals An Auto-Tuning PI Control System for an Open-Circuit Low-Speed Wind Tunnel Designed for Greenhouse Technology

Sensors ◽  
2015 ◽  
Vol 15 (8) ◽  
pp. 19723-19749 ◽  
Author(s):  
Karlos Espinoza ◽  
Diego Valera ◽  
José Torres ◽  
Alejandro López ◽  
Francisco Molina-Aiz
Keyword(s):  
Control System ◽  
Wind Tunnel ◽  
Open Circuit ◽  
Pi Control ◽  
Low Speed ◽  
Auto Tuning ◽  
Low Speed Wind Tunnel
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