UAV Automatic Landing Control Law

2011 ◽  
Vol 383-390 ◽  
pp. 1452-1457 ◽  
Author(s):  
Mao Han Liu ◽  
Chun Tao Li ◽  
Yi Wang
Keyword(s):  
Control Structure ◽  
Digital Simulation ◽  
Cascade Control ◽  
Control Law ◽  
Matlab Simulink ◽  
Automatic Landing ◽  
Engineering Significance ◽  
Landing Control ◽  
Approach Phase ◽  
Landing Trajectory

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.

scholarly journals Dynamic Matrix Control for the Thermal Power of MHTGR-Based Nuclear Steam Supply System

Energies ◽  
2018 ◽  
Vol 11 (10) ◽  
pp. 2651 ◽  
Author(s):  
Di Jiang ◽  
Zhe Dong ◽  
Miao Liu ◽  
Xiaojin Huang
Keyword(s):  
Control Structure ◽  
Thermal Power ◽  
Coordinated Control ◽  
Cascade Control ◽  
Step Response ◽  
Control Law ◽  
Dynamic Matrix Control ◽  
Dynamic Matrix ◽  
Matrix Control ◽  
Power Response

The modular high temperature gas-cooled reactor (MHTGR) based nuclear steam supplying system (NSSS) is constituted by an MHTGR, a once-through steam generator (OTSG) and can generate superheated steam for industrial heat or electric power generation. The wide range closed-loop stability is achieved by the recently proposed coordinated control law, in which the neutron flux and the temperatures of both main steam and primary coolant are chosen as controlled variables, and the flowrates of both primary and secondary loop and the control rod speed are chosen as manipulated variables. However, the thermal power is only controlled in open loop manner and hence could be further optimized through feedback. Motivated by this, a dynamic matrix control (DMC) is proposed for optimizing the thermal power of MHTGR based NSSS. A simple step-response model with the thermal power response data is utilized in designing the DMC. The design objective of DMC is to optimize the deviation of the thermal power from its reference under its rate constraint. Then, by the virtue of strong stability of existing control law and optimization ability of DMC, a cascade control structure is implemented for the thermal power optimization, with the coordinated control law in the inner loop and DMC in the outer loop. Numerical simulation results show the satisfactory improvement of thermal power response. This cascade control structure inherits the advantages of both proportional-integral-differential (PID) control and DMC, by which the zeros offset and the short settling time of thermal power are realized.

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

2015 ◽  
Vol 138 (2) ◽  
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.

Variable Cascade Control Structure for Tubular Reactors

2015 ◽  
Vol 38 (3) ◽  
pp. 521-529
Author(s):  
Galo R. Urrea-García ◽  
Sergio Reséndiz-Camacho ◽  
José Álvarez-Ramírez ◽  
Guadalupe Luna-Solano
Keyword(s):  
Control Structure ◽  
Cascade Control ◽  
Tubular Reactors

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

2012 ◽  
Vol 452-453 ◽  
pp. 548-552 ◽  
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.

Wind Shear Encountered Landing Control Based on CMACs

2013 ◽  
Vol 284-287 ◽  
pp. 2351-2355 ◽  
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.

Sign in / Sign up

Export Citation Format

Share Document