Automatic Landing Control Law for Unmanned Helicopter using Lyapunov Approach

Landing is the most important stage of the Flight of UAV, the study of automatic landing of UAVs has important engineering significance. In this paper, the UAV landing trajectory is divided into approach phase, steep glide phase and flare phase; a cascade control structure controller of height tracking was applied and the landing control law was designed. The digital simulation was done in the MATLAB / simulink environment. The results of simulation indicated that UAV can track the designed landing trajectory very well under the control law of automatic landing and safe landing can be achieved.

Download Full-text

Formal Verification of Helicopter Automatic Landing Control Algorithm in Theorem Prover Coq

10.23940/ijpe.18.09.p2.19471957 ◽

2018 ◽

Cited By ~ 1

Author(s):

Xi Chen

Keyword(s):

Formal Verification ◽

Control Algorithm ◽

Theorem Prover ◽

Automatic Landing ◽

Landing Control

Download Full-text

Simultaneous Optimal Design of the Lyapunov-Based Semi-Active Control and the Semi-Active Vibration Control Device: Inverse Lyapunov Approach

ASME 2010 Pressure Vessels and Piping Conference: Volume 8 ◽

10.1115/pvp2010-25883 ◽

2010 ◽

Author(s):

Kazuhiko Hiramoto ◽

Taichi Matsuoka ◽

Akira Fukukita ◽

Katsuaki Sunakoda

Keyword(s):

Optimal Design ◽

Lyapunov Function ◽

Vibration Control ◽

Active Control ◽

Control Device ◽

Ball Screw ◽

Design Parameters ◽

Resistance Force ◽

Control Law ◽

Lyapunov Approach

We address a simultaneous optimal design problem of a semi-active control law and design parameters in a vibration control device for civil structures. The Vibration Control Device (VCD) that is being developed by authors is used as the semi-active control device in the present paper. The VCD is composed of a mechanism of a ball screw with a flywheel for the inertial resistance force and an electric motor with an electric circuit for the damping resistance force. A new bang-bang type semi-active control law referred to as Inverse Lyapunov Approach is proposed as the semi-active control law. In the Inverse Lyapunov Approach the Lyapunov function is searched so that performance measures in structural vibration control are optimized in the premise of the bang-bang type semi-active control based on the Lyapunov function. The design parameters to determine the Lyapunov function and the design parameters of the VCD are optimized for the good performance of the semi-active control system. The Genetic Algorithm is employed for the optimal design.

Download Full-text

Design of Automatic Landing Systems Using the H-inf Control and the Dynamic Inversion

Journal of Dynamic Systems Measurement and Control ◽

10.1115/1.4032028 ◽

2015 ◽

Vol 138 (2) ◽

Cited By ~ 12

Author(s):

Romulus Lungu ◽

Mihai Lungu

Keyword(s):

Federal Aviation Administration ◽

Dynamic Inversion ◽

Control Law ◽

Reference Models ◽

Low Intensity ◽

Automatic Landing ◽

Sensor Measurement ◽

Wind Shears ◽

Sensor Errors ◽

Theoretical Results

This paper focuses on the automatic control of aircraft in the longitudinal plane, during landing, by using the linearized dynamics of aircraft, taking into consideration the wind shears and the errors of the sensors. A new robust automatic landing system (ALS) is obtained by means of the H-inf control, the dynamic inversion, an optimal observer, and two reference models providing the aircraft desired velocity and altitude. The theoretical results are validated by numerical simulations for a Boeing 747 landing; the simulation results are very good (Federal Aviation Administration (FAA) accuracy requirements for Category III are met) and show the robustness of the system even in the presence of wind shears and sensor errors. Moreover, the designed control law has the ability to reject the sensor measurement noises and wind shears with low intensity.

Download Full-text

CAT III Autoland Control Laws Design Based on Multi-Objective Optimization

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.452-453.548 ◽

2012 ◽

Vol 452-453 ◽

pp. 548-552 ◽

Cited By ~ 1

Author(s):

Hui Jie Li ◽

Ling Yu Yang ◽

Gong Zhang Shen

Keyword(s):

Monte Carlo Simulation ◽

Monte Carlo ◽

Multi Objective Optimization ◽

Control Laws ◽

Multi Objective ◽

Automatic Landing ◽

Simulation Results ◽

Free Parameters ◽

Structure Measurement ◽

Landing Control

The CAT III longitudinal automatic landing control laws based on multi-objective optimization is discussed. Firstly summarized the CAT III airworthiness criteria and transformed into the specifications of control system. The configuration of the longitudinal automatic landing controllers is proposed secondly and multi-objective optimization is used to tradeoff free parameters of the controllers. The Monte Carlo simulation results show the designed control laws fulfill the CAT III requirements, when there are uncertainties of structure, measurement error and disturbances.

Download Full-text

Wind Shear Encountered Landing Control Based on CMACs

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.284-287.2351 ◽

2013 ◽

Vol 284-287 ◽

pp. 2351-2355 ◽

Cited By ~ 1

Author(s):

Jih Gau Juang ◽

Chung Ju Cheng ◽

Teng Chieh Yang

Keyword(s):

Intelligent Control ◽

Adaptive Learning ◽

Wind Shear ◽

Learning Rule ◽

Lyapunov Theory ◽

Intelligent Control System ◽

Automatic Landing ◽

Control Scheme ◽

Shear Condition ◽

Landing Control

This paper presents an intelligent control scheme that uses different cerebellar model articulation controllers (CMACs) in aircraft automatic landing control. The proposed intelligent control system can act as an experienced pilot and guide the aircraft landed safely in wind shear condition. Lyapunov theory is applied to obtain adaptive learning rule and stability analysis is also provided. Furthermore, the proposed controllers are implemented in a DSP. The simulations by MatLab are demonstrated.

Download Full-text