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

2018 ◽  
Author(s):  
Xi Chen
Keyword(s):  
Formal Verification ◽  
Control Algorithm ◽  
Theorem Prover ◽  
Automatic Landing ◽  
Landing Control

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.

Automatic Landing Control of a Very Flexible Flying Wing

2018 ◽  
Author(s):  
Pengyuan Qi ◽  
Xiaowei Zhao ◽  
Yinan Wang ◽  
Rafael Palacios ◽  
Andrew Wynn
Keyword(s):  
Automatic Landing ◽  
Landing Control

Energy-Saving Algorithm of Automatic Control of Compulsory Passenger Carrier Landing. Part II

2018 ◽  
Vol 19 (12) ◽  
pp. 788-796 ◽  
Author(s):  
V. F. Petrishchev
Keyword(s):  
Automatic Control ◽  
Energy Saving ◽  
Linear Model ◽  
Pitch Angle ◽  
Control Algorithm ◽  
Automatic Landing ◽  
Motion Parameters ◽  
Energy Saving Control ◽  
Saving Algorithm ◽  
Landing Mode

The task was to develop an automatic landing system (ALS) for a passenger carrier that can be externally activated and excludes the possibility of the crew’s interference into the landing process, for example, when a carrier alters its nominal course or there is no contact with the crew. The air crush history saw a lot of cases that could have been prevented if the planes had had an ALS system and airports had had possibilities to activate that system and suspend the crew from flight control. One of such unforgettable examples is the New-York tragedy of September 11, 2001. State-of-the-art technology allows solving the problem of automatic carrier landing. The most remarkable example demonstrating solution of this problem is the automatic landing of the Buran orbiter 30 years ago on November 15, 1988. The article consists of two sections. The first section of the article deals with conditions of effective solution of autoland problem. It describes in short, the flight modes during automatic landing control. To solve the problem of automatic longitudinal control in the most crucial final landing mode, the author proposes an energy-saving control algorithm that provides control in the mode of negative feedback. The system status vector comprises six parameters: range, altitude, pitch angle, and their first-order derivatives. The control algorithm is developed for the Tupolev TU-154M airliner. In development of the algorithm, the following assumptions were used: a) a linear model of dependence of aerodynamic data on the angle of attack; b) a linear model of programmed switch of engine thrust to the idle mode on the interval of 3 seconds from the beginning of the flareout; c) a pitch angular acceleration, occurring at elevator rate reversal, as a control signal; d) the frequency of the control algorithm operation equal to 200 Hz.The second section further analyzes characteristics of the energy-saving algorithm of automatic control of compulsory passenger carrier landing during the final landing phase, which was developed in the first section. The author developed a model program of control and mathematically modeled the carrier landing phases. When switching from one phase to another, the motion parameters were concatenated so that the final motion parameters of the previous phase became the initial motion parameters of the next phase. The author also studied the influence of errors in aerodynamic data on the landing conditions. The modeling revealed that if a pitch deflection direction is used for the determination of phases, then in a general case, the landing mode consists not of two traditionally determined phases, but of the following three: pitch angle increase (flareout), pitch angle decrease (float), and again, pitch angle increase (this phase is called ‘maintenance’). The necessity to introduce the third phase is determined by the presence of errors in the aerodynamic data of the airplane. On the whole, it is confirmed that the energy saving control algorithm provides successful solution of the problem of automatic landing of a passenger carrier at its final flight phase. At that, it is determined that the landing mode does not exceed 5 s.

EFFECTIVE FINITE HORIZON LINEAR-QUADRATIC CONTINUOUS TERMINAL CONTROL

2013 ◽  
Vol 10 (06) ◽  
pp. 1350038 ◽  
Author(s):  
X. XIA ◽  
Z. XU
Keyword(s):  
Matrix Method ◽  
Optimization Problem ◽  
Computation Time ◽  
Finite Horizon ◽  
Terminal Control ◽  
Linear Quadratic ◽  
Sweep Method ◽  
Crucial Point ◽  
Automatic Landing ◽  
Landing Control

An effective algorithm for the finite-horizon linear quadratic continuous terminal control is proposed. It is the combination of existing continuous soft and hard terminal control. We apply the algorithm to the automatic landing control of OH-6A helicopters. Numerical demonstration shows that, whether noise exists or not, the algorithm has less computation time and less feedback gains than existing hard terminal control while generally achieving the same terminal accuracy. The optimization problem which represents the hard terminal control can be addressed by sweep method and transit matrix method. It is also discovered that transit matrix method is a crucial point for improving terminal accuracy.

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