Diagnostic Method for a Landing Gear and Doors Actuation System Based on a State Machine Control Algorithm

2016 ◽  
Author(s):  
Neno Novakovic
Keyword(s):  
Control Algorithm ◽  
Diagnostic Method ◽  
State Machine ◽  
Landing Gear ◽  
Actuation System ◽  
Machine Control

An unconventional adaptive flutter suppression actuation system: From modeling to experimentation

2016 ◽  
Vol 28 (8) ◽  
pp. 1089-1101
Author(s):  
Mario Cassaro ◽  
Manuela Battipede ◽  
Piero Gili ◽  
Pier Marzocca
Keyword(s):  
Adaptive Control ◽  
Control Algorithm ◽  
Leading Edge ◽  
Force Balance ◽  
Structural Stiffness ◽  
Flutter Suppression ◽  
Flutter Speed ◽  
Actuation System ◽  
Wide Range ◽  
Adaptive Control Algorithm

This article contributes to the definition of an unconventional actuation system coupled with an adaptive control algorithm, it is intended specifically for slender/highly flexible wings flutter suppression. The design and validation process of the novel actuation architecture is presented together with the performance analysis of the post-flutter dynamics control. Robustness of the overall control architecture is verified with respect to the uncertainties deriving from the unpredictable degradation of the structural properties. The proposed actuation system is based on a row of multiple mini-spoilers, located in proximity of the leading edge and coordinated by a modified model reference adaptive control algorithm. The spoiler configuration is optimized by computational fluid dynamics numerical simulation, whereas the aerodynamic database is derived by wind tunnel tests on the prototype by means of a six-axes force balance. The resulting aeroelastic mathematical model is then used to implement and validate the adaptive control algorithm for a wide range of conditions, from on-design flutter speed and nominal structural stiffness to post-flutter speed and reduced structural stiffness. The two degree of freedom aeroelastic model is successfully controlled in all conditions. This article aims at defining a robust procedure for aeroelastic phenomena control system design, which employs a synergy of modeling, simulation, and experimental approaches. Pertinent conclusions are discussed in the final section of the article.

scholarly journals Aeroload Simulation of Interceptor Missile using Fin Load Simulator

2021 ◽  
Vol 71 (1) ◽  
pp. 102-107
Author(s):  
M.V.K.S. Prasad ◽  
Patri Sreehari Rao ◽  
Jagannath Nayak
Keyword(s):  
Control Algorithm ◽  
Navigation Algorithm ◽  
Actuation System ◽  
Control Command ◽  
Load Simulator ◽  
The Difference ◽  
Miss Distance ◽  
Hardware In Loop ◽  
Hardware In Loop Simulation ◽  
Mission Objective

Interceptor missiles are designed to destroy enemy targets in air. Targets can be destroyed either in atmosphere or out of atmosphere. So for Air Defence scenario, a two layer protection system is required with one taking care of exo atmosphere and another endo atmosphere. In this Air Defence scenario, irrespective of target trajectory interceptor should neutralise it. So the control, guidance are to be designed and validated thoroughly with various scenarios of interceptor and target. These interceptors sense the rates from rate gyroscopes and accelerations from accelerometers which are fitted on board the interceptor. The navigation algorithm calculates the interceptor’s position and velocity from these rates and accelerations from time to time. Using these interceptor data and target information received from ground RADAR or on board seeker, guidance calculates accelerations demand and subsequently rate demand. The control algorithm runs in on board mission computer along with guidance. The control algorithm calculates the commanded rate and eventually commanded deflections to the control fins to move towards the target. The fins have to move as per commanded deflections to meet the mission objective of hitting the target. But the load known as aeroload which comes on the control fins during mission, causes control fins not to move as per command. Due to the difference between control command and physical movement of fin, the expected path towards target deviates. This increases the miss distance and also misses the target hit. This aeroload scenario is to be simulated on ground and some feature is to be designed to take care of it during mission. By studying the control system behaviour due to load, the control autopilot is to be automatically tuned to compensate for the loss in commanded deflections. This scenario can be carried out in Hardware-in-Loop simulation (HILS) setup. Mission load conditions can be applied on hardware actuation system in HILS setup and mission performance can be seen and also with different loads and different autopilot tunings.

scholarly journals Finite State Machine Based Modelling of Discrete Control Algorithm in LAD Diagram Language With Use of New Generation Engineering Software

2019 ◽  
Vol 159 ◽  
pp. 2560-2569 ◽  
Author(s):  
Wojciech Zając ◽  
Grzegorz Andrzejewski ◽  
Kazimierz Krzywicki ◽  
Tomasz Królikowski
Keyword(s):  
Control Algorithm ◽  
Finite State Machine ◽  
State Machine ◽  
Discrete Control ◽  
Engineering Software ◽  
Finite State ◽  
New Generation

Design of Automated Catwalks Machine Control System for Offshore Drilling Platform

2014 ◽  
Vol 568-570 ◽  
pp. 1143-1146
Author(s):  
Shu Fen Qi ◽  
Shi Ping Cheng ◽  
Wen Long Wang ◽  
Kun Zhang
Keyword(s):  
Pid Control ◽  
Automatic System ◽  
Control Algorithm ◽  
Drill String ◽  
Efficient Production ◽  
Labor Intensity ◽  
Offshore Drilling ◽  
Whole Process ◽  
Automated Processing ◽  
Machine Control

In recent years, the use of drill string automated processing systems on offshore drilling platform has become more and more widespread, and it not only can improve the efficiency of workers, but also can reduce the labor intensity. In order to make the automatic system more intelligent and more efficient in the whole process, in this paper, we designed a set of adjustable speed drill delivery system, which is based on PID control algorithm. It can not only improve the efficiency of the automated catwalks machine conveying pipe, but also ensure the quick and efficient production.

scholarly journals Vibration Attenuation of Magnetorheological Landing Gear System with Human Simulated Intelligent Control

2013 ◽  
Vol 2013 ◽  
pp. 1-13 ◽  
Author(s):  
X. M. Dong ◽  
G. W. Xiong
Keyword(s):  
Intelligent Control ◽  
Control Algorithm ◽  
Impact Load ◽  
Landing Gear ◽  
Gear System ◽  
Control Parameters ◽  
Vibration Attenuation ◽  
Adaptive Ability ◽  
The Impact ◽  
Two Degree Of Freedom

Due to the short duration of impulsive impact of an aircraft during touchdown, a traditional landing gear can only achieve limited performance. In this study, a magnetorheological (MR) absorber is incorporated into a landing gear system; an intelligent control algorithm, a human simulated intelligent control (HSIC), is proposed to adaptively tune the MR absorber. First, a two degree-of-freedom (DOF) dynamic model of a landing gear system featuring an MR absorber is constructed. The control model of an MR damper is also developed. After analyzing the impact characteristic during touchdown, an HSIC is then formulated. A genetic algorithm is adopted to optimize the control parameters of HSIC. Finally, a numerical simulation is performed to validate the proposed damper and the controller considering the varieties of sink velocities and sprung masses. The simulations under different scenarios show that the landing gear system based on the MR absorber can greatly reduce the peak impact load of sprung mass within the stroke. The biggest improvement of the proposed controller is over 40% compared to that of skyhook controller. Furthermore, HSIC exhibits better adaptive ability and strong robustness than skyhook controller under various payloads and sink velocities.

Generalized predictive control of a robotic manipulator with hydraulic actuators

Robotica ◽  
1992 ◽  
Vol 10 (5) ◽  
pp. 447-459 ◽  
Author(s):  
A. Kotzev ◽  
D. B. Cherchas ◽  
P. D. Lawrence ◽  
N. Sepehri
Keyword(s):  
Adaptive Control ◽  
Predictive Control ◽  
Control Algorithm ◽  
Generalized Predictive Control ◽  
Maximum Output ◽  
Hydraulic Actuators ◽  
Actuation System ◽  
Hydraulically Actuated ◽  
On Line ◽  
Adaptive Control Algorithm

SUMMARYThis paper presents some aspects of the behavior of hydraulically actuated heavy duty manipulators. This category of manipulators is used extensively in large resource based industries and any improvement in efficiency may result in major financial benefits. In this paper an adaptive control algorithm is used for a two rigid link manipulator driven by hydraulic actuators. The dynamic model of the manipulator is derived as well as the models of the hydraulic actuators including compliance, dead time and full dynamics of the servo valves. An adaptive control algorithm is considered since changes occur on-line in the system's parameters. The adaptive algorithm used is Generalized Predictive Control (GPC). The GPC uses a controlled autoregressive integrated moving average (CARIMA) type model and a cost function that minimizes a predicted future output error and future weighted control inputs to the plant, resulting in a sequence of future control increments. The procedure, in this work, does not separate the hydraulic actuator and the link dynamics into separate sub-systems, but controls them as one system. The changes in the system's parameters due to the hydraulics or the link dynamics can be estimated and the coefficients of the model adjusted without the necessity of identifying the exact cause of the changes.It was found in this work that the variations of the GPC control horizon can lead to faster response during transients and significantly reduced overshoot in the nonlinear hydraulic actuation system. An on-line change of the maximum output horizon is also introduced.This work shows the analysis and results of a two link manipulator with hydraulic actuators. It can be implemented on any hydraulically actuated manipulator with any number of links and actuators.Numerical simulations are performed on a Vax 3200 computer and the results are presented.

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