Height control based on model identification for a small-scale unmanned helicopter

2017 ◽  
Author(s):  
Hu Yongqiang
Keyword(s):  
Model Identification ◽  
Small Scale ◽  
Unmanned Helicopter ◽  
Height Control

scholarly journals Dynamical Model Identification for a Small-Scale Unmanned Helicopter Using an Integrated Approach

2019 ◽  
Vol 2019 ◽  
pp. 1-11 ◽  
Author(s):  
Rui Ma ◽  
Li Ding ◽  
Kailei Liu ◽  
Hongtao Wu
Keyword(s):  
Model Identification ◽  
Wind Tunnel Test ◽  
Integrated Approach ◽  
Dynamical Model ◽  
Small Scale ◽  
Unmanned Helicopter ◽  
Bee Colony ◽  
Chaotic Operator ◽  
Dynamical Parameters ◽  
Search Speed

This article presents an integrated approach for the parameter identification of a small-scale unmanned helicopter. With the flight experiment data collection and preprocessing, a hybrid identified algorithm combining the improved artificial bee colony algorithm and prediction error method is proposed to obtain the unknown dynamical parameters of the linear model. The proposed algorithm is valid to use thanks to an adaptive search equation, a novel probability-scaling method, and a chaotic operator and has a good performance in search speed and quality. Afterwards, we design a wind tunnel test to modify the main rotor time constant of the identified model. The identified accuracy and feasibility of the proposed approach are verified by making a time-domain comparison with three other algorithms. Results show that the dynamical characteristics of the helicopter can be determined accurately by the identified model. And the proposed approach is propitious to enhance the reliability and availability of the identified dynamical model.

Flight Control System Design and Autonomous Flight Control of Small-Scale Unmanned Helicopter Based on Nanosensors

2021 ◽  
Vol 16 (4) ◽  
pp. 675-688
Author(s):  
Xinfan Yin ◽  
Xianmin Peng ◽  
Guichuan Zhang ◽  
Binghui Che ◽  
Chang Wang
Keyword(s):  
Control System ◽  
Flight Control ◽  
Control Algorithm ◽  
Installation Space ◽  
Small Scale ◽  
Unmanned Helicopter ◽  
Flight Control System ◽  
Autonomous Flight ◽  
Position Controller ◽  
Attitude Controller

Due to the limitation of the size and power, micro unmanned aerial vehicle (MUAV) usually has a small load capacity. Aiming at the problems of limited installation space and easy being interfered in flight attitude measurement of the small-scale unmanned helicopter (SUH), a low-cost and lightweight flight control system of the SUH based on ARM Cortex-M4 core microcontroller and Micro-Electro-Mechanical Systems (MEMS) sensors is developed in this paper. On this basis, in order to realize the autonomous flight control of SUH, firstly, the mathematical model of the SUH is given by using the Newton-Euler formulation. Secondly, a cascade flight controller consisting of the attitude controller and the position controller is developed based on linear active disturbance rejection control (LADRC) and proportional-integral-derivative (PID) control. Furthermore, simulations are conducted to validate the performance of the attitude controller and the position controller in MATLAB/SIMULINK simulation environment. Finally, based on the Align T-REX 470L SUH experimental platform, the hovering experiment and the route flight experiment are also carried out to validate the performance of the designed flight control system hardware and the proposed control algorithm. The results show that the flight control system designed in this paper has high reliability and strong anti-interference ability, and the control algorithm can effectively and reliably realize the attitude stabilization control and route control of the SUH, with high control accuracy and small error.

SYSTEM DESIGNING FOR A SMALL-SCALE AUTONOMOUS HELICOPTER

2006 ◽  
Vol 03 (04) ◽  
pp. 359-367 ◽  
Author(s):  
WENBING CHEN ◽  
MING LIU ◽  
YUNJIAN GE
Keyword(s):  
Pid Controller ◽  
Low Cost ◽  
Model Identification ◽  
Small Scale ◽  
Fuzzy Pid ◽  
Camera System ◽  
Fuzzy Pid Controller ◽  
Binocular Stereo ◽  
Model Helicopter ◽  
Autonomous Helicopter

This paper presents the design of a relative low-cost and more compatible autonomous helicopter system using HIROBO 50 scale as an experimental platform. Because of the limit of helicopter payload, we choose the MP2128 Autopilot and a number of sensors to build the system and the weight of instrumentation is about 500 g, much less than the payload capability of model helicopter. Thus it is feasible to design the binocular stereo-camera system to achieve full autonomous flight and the whole weight (include power) of instrumentation is about 1500 g. After getting the model of the helicopter using the subspace model identification (SMI) algorithms, we present the structure of fuzzy PID controller.

scholarly journals A Novel Comprehensive Kinematic and Inverse Dynamic Model for the Flybar-Less Swashplate Mechanism: Application on a Small-Scale Unmanned Helicopter

Symmetry ◽  
2020 ◽  
Vol 12 (11) ◽  
pp. 1849
Author(s):  
Jianbo Liu ◽  
Rongqiang Guan ◽  
Yongming Yao ◽  
Hui Wang ◽  
Linqiang Hu
Keyword(s):  
Dynamic Model ◽  
Flight Control ◽  
Virtual Work ◽  
Influence Factors ◽  
Parallel Manipulators ◽  
Small Scale ◽  
Unmanned Helicopter ◽  
Inverse Dynamic ◽  
Inverse Dynamic Model ◽  
Helicopter Flight

In this paper, we propose a novel kinematic and inverse dynamic model for the flybar-less (FBL) swashplate mechanism of a small-scale unmanned helicopter. The swashplate mechanism is an essential configuration of helicopter flight control systems. It is a complex, multi-loop chain mechanism that controls the main rotor. In recent years, the demand for compact swashplate designs has increased owing to the development of small-scale helicopters. The swashplate mechanism proposed in this paper is the latest architectures used for hingeless rotors without a Bell-Hiller mixer. Firstly, the kinematic analysis is derived from the parallel manipulators concepts. Then, based on the principle of virtual work, a methodology for deriving a closed-form dynamic equation of the FBL swashplate mechanism is developed. Finally, the correctness and efficiency of the presented analytical model are demonstrated by numerical examples and the influence factors of the loads acted on actuators are discussed.

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