This paper exhibits a comparative the time response specification performance between PID and fuzzy logic controller of pitch control of an aircraft system. The dynamic modeling of pitch control system is considered on the PID and fuzzy logic controller, they are used to control the pitch angle, and we start with a mathematical model to describe the dynamics of an aircraft. The performances of pitch control systems are investigated and analyzed based by using step’s response in order to identify which control strategy delivers better performance with respect to the desired pitch angle. Finial we produced simulation models for pitch control system using matlab Simulink compared the performance of fuzzy and PID controller. to They are three
Robust Control for Helicopter Model D.Supriya1, P.S.Manoharan2, Asst.professor, P.T.R. College of Engineering and Technology, Madurai Associate professor, Thiagarajar College of Engineering, Madurai. email@example.com, firstname.lastname@example.org Abstract— A paper discusses the problem of designing the robust control for a helicopter model, which is a nonlinear system with two degrees of freedom and cross couplings. The objective of this work is to stabilize the helicopter model, to attain a particular position and to make it to track a reference trajectory using robust µ-synthesis. The control scheme is implemented for the uncertainty and disturbances present in the system.
AIRFOIL DESIGN 3 Modern Airfoil Design Flight has been the biggest desire since humanity had started. A lot of aircraft have been designed in the last two centuries. Sailplanes, helicopters and airplanes are just a few prototype. Moreover, aircraft have four forces of flight which are thrust, drag, weight and lift. Lift is the major force acting on an aircraft.
3. Results 3.1. Optimization of the thruster geometry In this section, the thruster geometry optimization is based on a numerical model "PCLLT" based on Prandtl’s classic lifting line theory. 3.1.1. Validation of the numerical model "PCLLT" We varied the angle of incidence of a rectangular thruster having an aspect ratio of between 0° and 14°, and we made a comparison with a lift experimental results  (Figure 1).
he airspring bellow, which are here considered, consist of two cross wound fabric layers, which are embedded into rubber matrix. The bellow was tested by the life duration tests and benchmarking tests in the experimental workshop. In the benchmarking results, there were various breakages observed in the case of failed airspring bellow. Here the figure shows the result of the benchmarking tests and the failure mode of the airspring bellow from the rolling lobe area and the second figure shows the results which are computed analytically by the finite element method. Here, an Abaqus based simulation tool is also available for the airspring bellow considering both macro and micro mechanical analysis.
CHAPTER THREE RESEARCH METHODOLOGY 3.0 INTRODUCTION The purpose of the current study was to examine communication in aviation discourse, to identify the type of miscommunication that occurred in pilot-controller communication and repair strategies taken by pilots and controllers to rectify the problem. In addition, this research attempt to investigate intercultural communication factors in aviation discourse focusing at English as lingua franca setting. Chapter 3 describes the methods and procedures employed to conduct the research, this chapter includes: research design of the study, research sample and site, access and permissions, research procedure and data analysis. 3.1 Research Design This research used case study approach by
Introduction to Boeing: An Airplane is an Aircraft that has wings and is powered by propellers or jets. The first time the world ever saw manned flights in the sky was in 1903 when the Wright brothers created an Airplane and flew in it. They achieved to gain an altitude of 12 feet and travel a distance of 120 feet. Ever since Aircrafts have been of great importance and there is a very high demand for them. Airplanes are put to many uses such, as they are a very important means of transportation for people and for goods, all the armies in the world use them as well.
This aspect should be drilled by flying instructor as these are life saver limitations. (d) Knowledge. Flying instructor must always check his student if his knowledge standard is not up to the mark. Flying knowledge must not only include aircraft system knowledge or emergency procedures, but also general aviation topic that can help him in making good decisions. Trend of morning session, mission briefs, de-briefs are fundamental element for improving knowledge of new pilots, which will definitely enhance his safety in
B. Angle of attack Angle of attack is the angle between the reference line of airfoil and the directional vector of incoming wing flow. Angle of attack influence the lift and drag co-efficient consistently. C. NACA airfoil The NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). The shape of the NACA airfoils is described using a series of digits following the word "NACA".
Airbus Helicopters Southeast Asia (AHSA) design organisation (DO) also holds the Design Organisation Approval (DOA) as part of CAAS Singapore Airworthiness Requirements (SAR) 21. This allows for the company to certify Singapore registered rotorcrafts that have undergone minor modifications to be airworthy. The proposed scope of approvals includes Type Certificates (TC), Supplemental Type Certificates (STC) and modification/repair or Singapore Technical Standard Order (STSO) certificate of approval. For AHSA DO, they are authorized to do modification and repair of helicopters related to structures, cabin interior and furnishings, and integration of avionics and electrical systems. For major modifications done to a rotorcraft, a Supplemental