Dynamic Optimization Genetic Algorithms for Flight Control Laws Design

2013 ◽  
Vol 278-280 ◽  
pp. 1581-1584
Author(s):  
Xiao Xiong Liu ◽  
Yan Wu ◽  
Peng Hui Li ◽  
Heng Xu
Keyword(s):  
Genetic Algorithms ◽  
Dynamic Optimization ◽  
Flight Control ◽  
Control Parameters ◽  
Longitudinal Control ◽  
Control Laws ◽  
Longitudinal Function ◽  
Adaptive Capability ◽  
Dynamic Optimization Model ◽  
Set Up

The general flight control laws are designed by static designs and dynamic fits. To improve the adaptive capability, the method of control laws design was introduced by using dynamic optimization genetic algorithms. The control parameters were adjusted online in the flight envelope. The dynamic optimization model was built for aircraft longitudinal function. The fitness was set up by applying order track. And then the control parameters were regulated by dynamic optimization genetic algorithms. Finally an example of a longitudinal control augmented stability system of an aircraft is used with a simulation.

Research on the Simulation Model for Longitudinal Control Channel of FCS Based on PC

2013 ◽  
Vol 756-759 ◽  
pp. 564-568
Author(s):  
Qing Li ◽  
Wei Yang ◽  
Zhao Xie Huang
Keyword(s):  
Control System ◽  
Simulation Model ◽  
Flight Control ◽  
Control Channel ◽  
Control Parameters ◽  
Flight Control System ◽  
Longitudinal Control ◽  
Control Structures ◽  
Control Rules ◽  
Classical Control

According to the analysis of control structures of the two typical control modes-pitch control and height control, the simplified control rules for the two special control systems are presented. Under the condition of enduring the real-time property and fidelity, the classical control theory is applied to study the control parameters selecting of the flight control system (FCS) based on PC modeling traits. The selecting process of control parameters of longitudinal control channel is analyzed and the simulation resources are simplified. The simulation model is achieved. The steps are summarized for the simulation modeling of longitudinal control channel of the flight control system, and the corresponding flow chart based on PC is also given.

scholarly journals Flight Control Laws Verification Using Continuous Genetic Algorithms

ISRN Robotics ◽  
2013 ◽  
Vol 2013 ◽  
pp. 1-20 ◽  
Author(s):  
A. Al-Asasfeh ◽  
N. Hamdan ◽  
Z. Abo-Hammour
Keyword(s):  
Genetic Algorithm ◽  
Genetic Algorithms ◽  
Flight Control ◽  
Optimization Problem ◽  
Controller Design ◽  
Load Factor ◽  
Significant Information ◽  
Control Laws ◽  
Convergence Performance ◽  
Command Signals

This work is concerned with the application of a continuous genetic algorithm (CGA) to solve the nonlinear optimization problem that results from the clearance process of nonlinear flight control laws. The CGA is used to generate a pilot command signal that governs the aircraft performance around certain points in the flight envelope about which the aircraft dynamics were trimmed. The performance of the aircraft model due to pitch and roll pilot commands is analyzed to find the worst combination that leads to a nonallowable load factor. The motivations for using the CGA to solve this type of optimization problem are due to the fact that the pilot command signals are smooth and correlated, which are difficult to generate using the conventional genetic algorithm (GA). Also the CGA has the advantage over the conventional GA method in being able to generate smooth solutions without the loss of significant information in the presence of a rate limiter in the controller design and the time delay in response to the actuators. Simulation results are presented which show superior convergence performance using the CGA compared with conventional genetic algorithms.

DYNAMIC OPTIMIZATION USING NEURAL NETWORKS AND GENETIC ALGORITHMS FOR TOMATO COOL STORAGE TO MINIMIZE WATER LOSS

2003 ◽  
Vol 46 (4) ◽  
Author(s):  
T. Morimoto ◽  
K. Tu ◽  
K. Hatou ◽  
Y. Hashimoto
Keyword(s):  
Neural Networks ◽  
Genetic Algorithms ◽  
Dynamic Optimization ◽  
Water Loss ◽  
Cool Storage

String Instabilities in Formation Flight: Limitations Due to Integral Constraints

2004 ◽  
Vol 126 (4) ◽  
pp. 873-879 ◽  
Author(s):  
P. Seiler ◽  
A. Pant ◽  
J. K. Hedrick
Keyword(s):  
Flight Control ◽  
Formation Control ◽  
Energy Savings ◽  
Feedback Loops ◽  
Formation Flight ◽  
Control Laws ◽  
Aerodynamic Efficiency ◽  
Preceding Vehicle ◽  
Specific Control ◽  
Theoretical Results

Flying in formation improves aerodynamic efficiency and, consequently, leads to an energy savings. One strategy for formation control is to follow the preceding vehicle. Many researchers have shown through simulation results and analysis of specific control laws that this strategy leads to amplification of disturbances as they propagate through the formation. This effect is known as string instability. In this paper, we show that string instability is due to a fundamental constraint on coupled feedback loops. The tradeoffs imposed by this constraint imply that predecessor following is an inherently poor strategy for formation flight control. Finally, we present two examples that demonstrate the theoretical results.

A DYNAMIC OPTIMIZATION MODEL FOR PLANNING IN A MULTI-PRODUCT ENVIRONMENT

1975 ◽  
Vol 6 (2) ◽  
pp. 274-283 ◽  
Author(s):  
Donald E. Ricketts ◽  
Robert K. Zimmer
Keyword(s):  
Dynamic Optimization ◽  
Optimization Model ◽  
Dynamic Optimization Model

Automatic Flight Control of Unmanned Helicopter Based on Nonlinear Model

2012 ◽  
Vol 472-475 ◽  
pp. 1492-1499
Author(s):  
Run Xia Guo
Keyword(s):  
Nonlinear Model ◽  
Flight Control ◽  
Attitude Control ◽  
Lyapunov Stability Theory ◽  
Test Results ◽  
Unmanned Helicopter ◽  
Control Laws ◽  
Control Approach ◽  
State Dependent ◽  
Compensation Technique

The Unmanned helicopter (UMH) movement was divided into two parts, namely, attitude and trajectory motion. And then a two-timescale nonlinear model was established. The paper improved and expanded state dependent riccati equation (SDRE) control approach, deriving analytical conditions for achieving global asymptotic stability with lyapunov stability theory. Proof was given. By combining improved SDRE control with nonlinear feed-forward compensation technique, the full envelop flight attitude control laws could be designed. On the basis of attitude control, trajectory controller was developed. Actual flight tests were carried out. Test results show that the control strategy is highly effective.

Energy dynamic optimization model research for off-grid run micro grid

2014 ◽  
Author(s):  
Qing Ai ◽  
Dongshan Geng ◽  
Shaowu Li ◽  
Yongchao Yang ◽  
Kunyi Chen
Keyword(s):  
Dynamic Optimization ◽  
Optimization Model ◽  
Model Research ◽  
Dynamic Optimization Model ◽  
Micro Grid
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