scholarly journals DEVELOPMENT OF NUMERICAL PLATFORM FOR AIRCRAFT SYSTEMS SIMULATION

INSIST ◽  
2019 ◽  
Vol 2 (2) ◽  
pp. 97
Author(s):  
Rianto A Sasongko ◽  
Yorgi A. Ndaomanu ◽  
Yazdi I. Jenie ◽  
M. Luthfi I. Nurhakin ◽  
M. Rafi Hadytama ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Control System ◽  
System Analysis ◽  
System Development ◽  
Landing Gear ◽  
Control Surface ◽  
System Control ◽  
Aircraft Systems ◽  
And Performance ◽  
Aircraft System

This paper discusses the development of a numerical simulation platform that can be used for representing the principal works of aircraft systems. The platform consists of some parts each of which is intended to replicate the operation of a system implemented in a modern aircraft, such as hydraulic line, electrical system, landing gear system, control system, etc. The platform is intended to be a tool for modeling and analyzing the operation and performance of certain systems configuration. To some extend the platform can be viewed as a virtual Iron Bird System. Iron Bird is a term representing a platform for simulating the works of aircraft systems using real components, which is very important for aircraft system development. At this stage, the numerical platform will only involve some sub-systems, namely main hydraulic line, control surface actuation, landing gear, and control system. These sub-systems are chosen to be the basis for further development where other sub-systems will be added and integrated to the platform.Keywords—Aircraft System, Numerical Simulation, System Analysis

Modeling, control design, and influence analysis of catapult-assisted take-off process for carrier-based aircrafts

2017 ◽  
Vol 232 (13) ◽  
pp. 2527-2540 ◽  
Author(s):  
Ziyang Zhen ◽  
Ju Jiang ◽  
Xinhua Wang ◽  
Kangwei Li
Keyword(s):  
Control System ◽  
Flight Control ◽  
Control Design ◽  
Control Surface ◽  
Flight Control System ◽  
Influence Analysis ◽  
Surface Ship ◽  
Lateral Channel ◽  
And Performance ◽  
Longitudinal Channel

This paper addresses the problems of modeling, control design, and influence analysis of the steam catapult-assisted take-off process of the carrier-based aircrafts. The mathematical models of the carrier-based aircraft, steam catapult, landing gears, and the environmental factors including deck motion and bow airflow have been established to express the aircraft dynamics in the take-off process. An engineering method based automatic flight control system has been designed, which is divided into the longitudinal channel and lateral channel. The influences of the preset control surface, ship deck motion, ship bow airflow, and automatic flight control system system are tested by a series of simulations. The simulation results show that the elevator angle preset is necessary in the stage of accelerated running on the ship deck and the deck motion is the most important factor for safe take-off, while the ship bow airflow is beneficial for climbing up of the aircraft. The automatic flight control system gives the guarantee of safety and performance in the take-off process of the carrier-based aircraft.

Waukesha 275GL Series NOx Control System Development and Performance Testing

2010 ◽  
Author(s):  
Jared J. Wentz
Keyword(s):  
Control System ◽  
System Development ◽  
Fuel Efficiency ◽  
Performance Testing ◽  
Peak Performance ◽  
Engine Control System ◽  
Engine Wear ◽  
Nox Control ◽  
And Performance ◽  
And Control

Dresser Waukesha’s 275GL engine series, released in 2009, included an Engine System Manager (ESM) to manage and control critical engine operations. These engines are typically used in mechanical drive applications for natural gas compression as well as power generation at 2500 to 3300 kWb (3400–4500 bhp). The 275GL is now being offered in a low NOx configuration designated the 275GL+, that features a NOx based Air/Fuel Ratio (AFR) control. Market analysis determined that an engine with lower NOx output emissions while maintaining peak performance is of high importance. Utilizing a traditional oxygen based AFR system has limitations when controlling emissions at extreme low NOx values. In order to meet these needs and maintain a consistent low NOx level, development of a control system that allows an engine to achieve these requirements was essential. A NOx sensor based control system was developed to control extremely low NOx values while accounting for engine wear, humidity and fuel changes. An oxygen based AFR system has limitations that make it difficult, if not impossible, to use this approach for extremely low NOx levels. Some of these limitations can be attributed to sensor signal masking due to exhaust gases and having to correlate O2 to NOx for the specific application. This new NOx sensing functionality enables robust control of specific NOx emissions at varying engine and environmental conditions, yielding a powerful addition to the ESM engine control system applied on the 275GL engine. The NOx control running with ESM allows for the engine to achieve 0.5 g/bhp-hr NOx levels while maintaining fuel efficiency, fuel tolerance, and turndown range. This paper discusses the key testing, results and performance of this development when implemented on the 275GL+ engine.

scholarly journals Design and Simulation of Air to Air Missile Homing System

INSIST ◽  
2019 ◽  
Vol 2 (2) ◽  
pp. 75
Author(s):  
Rahmat Alfi Duhri ◽  
Rianto Adhy Sasongko ◽  
Yayom Dwi Laksmana
Keyword(s):  
Control System ◽  
General Purpose ◽  
Guidance System ◽  
Control Surface ◽  
System Control ◽  
Missile Guidance ◽  
Proportional Navigation ◽  
Simulink Model ◽  
Non Linear Equation ◽  
And Control

This paper will talk about AIM 120 AMRAAM missile guidance for pursuing a moving target. The missile guidance system itself consists of missile dynamics, control system, seeker, and guidance methods. For general purpose, the missile dynamics approach will use non-linear equation of motions. The control surface that will be discussed follow the rule BTT (Bank-to-Turn) and control system that will be used is PID control system that widely used for control design. Lastly, the guidance method that will be studied here is proportional navigation and constant bearing course approach. The simulation will be conducted using MATLAB Simulink. The Simulink model consist of target dynamics, and guidance system. From the result of simulation, it will be shown that the missile can pursue its target quite well. Hence, the simulation system can be used well for preliminary design purpose.Keywords—Homing System, Control System, Proportional Navigation, Missile Dynamics, Seeker, Bank-to-Turn, Constant Bearing Course.

Electronic differential for tramcar bogies: system development and performance evaluation by means of numerical simulation

2014 ◽  
Vol 52 (sup1) ◽  
pp. 405-420
Author(s):  
Andrea N. Barbera ◽  
Giuseppe Bucca ◽  
Roberto Corradi ◽  
Alan Facchinetti ◽  
Ferdinando Mapelli
Keyword(s):  
Numerical Simulation ◽  
Performance Evaluation ◽  
System Development ◽  
And Performance

scholarly journals Controlling the PVTOL Aircraft System with an Inverted Pendular Load by means of Nested Saturation Functions and GPI Controller

2021 ◽  
Vol 2021 ◽  
pp. 1-19
Author(s):  
Cesar Alejandro Villaseñor Rios ◽  
Octavio Gutiérrez-Frías ◽  
Carlos Aguilar-Ibanez ◽  
Miguel S. Suarez-Castanon
Keyword(s):  
Numerical Simulation ◽  
Linear Transformations ◽  
Control Approach ◽  
Performance Indexes ◽  
Input Control ◽  
Unknown Disturbances ◽  
Position Regulation ◽  
And Performance ◽  
Aircraft System ◽  
The Stability

This paper presents a control scheme that allows height position regulation and stabilization for an unmanned planar vertical takeoff and landing aircraft system with an inverted pendular load. The proposed controller consists of nested saturations and a generalized proportional integral (GPI). The GPI controls the aircraft height and the roll attitude; the latter is used as the fictitious input control. Next, the system is reduced through linear transformations, expressing it as an integrator chain with a nonlinear perturbation. Finally, the nested saturation function-based controller stabilizes the aircraft’s horizontal position and the pendulum’s angle. Obtaining the control approach was a challenging task due to the underactuated nature of the aircraft, particularly ensuring the pendulum’s upright position. The stability analysis was based on the second method of Lyapunov using a simple candidate function. The numerical simulation confirmed the control strategy’s effectiveness and performance. Additionally, the numerical simulation included a comparison against a PD controller, where its corresponding performance indexes were estimated, revealing that our controller had a better response in the presence of unknown disturbances.

An optimization approach for DAL assignments

2018 ◽  
Vol 90 (2) ◽  
pp. 328-335
Author(s):  
Xianan Li ◽  
Zhong Lu ◽  
Jingyi Wang
Keyword(s):  
Mathematical Model ◽  
Hybrid Algorithm ◽  
Optimization Problem ◽  
System Development ◽  
Optimization Method ◽  
Optimization Approach ◽  
Development Cost ◽  
Content Type ◽  
Aircraft Systems ◽  
Aircraft System

Purpose Development assurance level (DAL) is the measurement of the rigor of development assurance tasks performed to functions or items. The DAL assignment is an important process of aircraft system development that can make the reliability and safety of the system stay at acceptable levels. This paper aims to propose an optimization approach for the DAL assignments to minimize the development cost of aircraft systems. Design/methodology/approach The mathematical model for the DAL assignment optimization has been developed on the basis of the given expressions of objective function and constraints. In addition, a hybrid algorithm model synthesizing the advantages of genetic algorithm (GA) and Tabu search (TS) has been proposed to solve the optimization problem of the DAL assignment. Findings The results of the case study show that the proposed hybrid algorithm is more efficient and effective than the exhaustive method as well as the pure GA. Practical implications The proposed approach can be applied in the development of aircraft systems, and it has great significance in minimizing the development cost as well as keeping the system reliability and safety at an acceptable level. Originality/value The constrained optimization method has been applied in the DAL assignments, the corresponding mathematical model has been built and a hybrid evolutionary algorithm has been proposed to solve the optimization problem.

DESIGN, SIMULATION AND IMPLEMENTATION MONITORING SYSTEM FOR SYSTEM CONTROL C4 FEEDING PUMP FOR FEED VAPORIZATION IN THE BUTADIENE PLANT

2020 ◽  
Vol 1 (1) ◽  
pp. 31-35
Author(s):  
Fahmi Yunistyawan ◽  
Yunistyawan J Berchmans ◽  
Gembong Baskoro
Keyword(s):  
Motor Control ◽  
Control System ◽  
Field Operator ◽  
System Control ◽  
Variable Speed ◽  
Variable Speed Drive ◽  
Software And Hardware ◽  
Discharge Pressure ◽  
Selection Of

This study implements the auto start control system on an electric motor 3 phase C4Feeding pump when the discharge pressure is low-low (4.3 kg /cm²). The C4 feeding pumpmotor was initially manually operated from the local control station, this was very ineffectiveand inefficient because it still relied on the field operator to operate the pump motor and whenthe plant was in normal operating it is very risk if the field operator late to operate motor then itwill impact to quality of the product, and if the delay time to operate motor is too long then planthave to shut down, therefore improvement is needed in the C4 feeding pump motor controlsystem. In this paper, various types of 3-phase motor control are explained which allow it to beapplied to the C4 feeding pump motor that are on-off, inverter, and variable speed drive andefficient selection of the three systems control of the motor. Software and hardware used in thisthesis work are DCS CENTUM VP Yokogawa.

Determinants of Control System Design in Divisionalized Firms

2004 ◽  
Vol 79 (3) ◽  
pp. 545-570 ◽  
Author(s):  
Margaret A. Abernethy ◽  
Jan Bouwens ◽  
Laurence van Lent
Keyword(s):  
Control System ◽  
System Design ◽  
Performance Measures ◽  
Simultaneous Equation ◽  
Equation Model ◽  
Control System Design ◽  
Information Asymmetries ◽  
Endogenous Variables ◽  
And Performance ◽  
Using Data

We investigate two determinants of two choices in the control system of divisionalized firms, namely decentralization and use of performance measures. The two determinants are those identified in the literature as important to control system design: (1) information asymmetries between corporate and divisional managers and (2) division interdependencies. We treat decentralization and performance measurement choices as endogenous variables and examine the interrelation among these choices using a simultaneous equation model. Using data from 78 divisions, our results indicate that decentralization is positively related to the level of information asymmetries and negatively to intrafirm interdependencies, while the use of performance measures is affected by the level of interdependencies among divisions within the firm, but not by information asymmetries. We find some evidence that decentralization choice and use of performance measures are complementary.

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