Performance improvement of PID-controller for integrating systems with time delay


Integrating systems with time delay are found in modeling of liquid level systems, liquid storage tanks, boilers, batch chemical reactors and bottom level control of a distillation column. There also exist Processes such as aerospace control system, vertical take-off air place (Filatov et al, 1996), DC motors
and high speed disk drives (Liu et al., 2004). Oxygen control in fed batch fragmental fungal fermentation reactors (Bodizs et a1.2007) whose dynamics show the characteristics of double integrating types.
There are number of methods available in the literature for designing PID controllers for pure integrating with time delay. They are: methods based on stability criteria (Ziegler Nichols, 1942; Tyreus and Luyben, 1992; Chidambaram, 1994; Poulin and Pomerleau, 1999; Luyben, 1996; Wang and Cluette, 1997; Kookos et al., 1999; Wang and Cai, 2002 ;), optimization method (Visioli, 2001; Zhang et al., 1999), IMC method (Rivera et al., 1986; Chien and Fruehauf, 1990; Skogestad, 2003), two degree Freedom Controller (Sung and Lee, 1996), modified smith predictor method for large time delay (Matausek and Micic, 1999; Majhi and Atherton, 1999) and direct synthesis method (Seshagiri Rao and  Chidambaram, 2008).
            Generally when a PID Controller is designed for a process, it is designed to give best performance for the regulatory problem. The same PID is used for a servo problem which leads to a large overshoot for integrating and unstable systems. The overshoot is reduced by set point weighted PID controller. Many of the commercial PID controllers have the set point weighted PID action. However, the method for the Selection of set point weighting parameter is not given for integrating and unstable systems.
Therefore, the present work is intended to calculate set point weighting parameter for integrating Systems, double integrating systems and unstable/stable FOPTD(First   Order Plus Time Delay) systems with an integrator using numerical optimization of ISE (Integral Square Error), IAE (Integral Absolute Error), ITAE (Integral Time weighted Absolute Error) using MATLAB and simulink
It is also proposed to extend the equating coefficient method (Padma Sree and Chidambaram, 2004) for the calculation of set point weighting parameter for unstable systems to the above mentioned systems and Compare the servo performance with numerical optimization methods.
Simulations on various transfer function models of integrating system with time delay, double integrating system with time delay and stable/unstable FOPTD system with an integrator show that both the methods give improved performance  with less ISE, IAE and ITAE values when compared with the conventional PID controller and the conventional PID controller with a set point filter (Lee et al., 1999).


Here is List Of Aeronautical Engineering Seminar Topics :


Aircraft Lighting Systems : Download File 

HAI Public Aircraft Forum : Download File

Aircraft Instruments : Download File

Aircraft Fuel Systems : Download File

Aircraft Inspections : Download File

Aeronautical PowerPoint Presentation : Download File

AIRCRAFT GROUND DEICING/ANTI-ICING : Download File

Airworthiness of Aircraft : Download File

Eaton Aerospace : Download File

Aeronautical Learning Outcome : Download File

SAE Aircraft Seat Committee Magnesium Working : Download File

Aircraft Stability and Control AE 1350 : Download File

Aircraft Encounters : Download File

Open Systems Architecture for Legacy Aircraft (OSALA): Download File

AIRCRAFT REPAIR and SUPPLY CENTER : Download File

Aircraft PowerPoint Presentation : Download File

Airport Operations : Download File

Aircraft Performance : Download File

Correlation of Accelerometer and Microphone Data :

List Of Aicraft And Aeronautical PPTs And Seminar Topics


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Improving the Safety Culture in Aircraft Maintenance : Download File

OEM Drivers and Replacement Options for Aircraft : Download File

Aircraft Vertical Navigation Planning Information : Download File

Aircraft and Mechanical Engineering : Download File

PPT On Piper Aircraft Jet :Download File

Designing Advanced Fighter Aircraft : Download File

Operations Consulting Skills & Business Process Re-engineering :  
Download File

PPT on Kein Folientitel Aircraft: Download File

Engineering as a Profession PPT : Download File

PowerPoint Presentation on IGDS Concurrent Engineering Module : 

Supplier Diversity Programs : Download File

Open Systems Architecture for Legacy Aircraft (OSALA): Download File

PPT on Aircraft Training (Major Repairs and Alterations ): Download File

PowerPoint Presentation on Hurricane Imaging Radiometer (HIRAD):Download File

Changing The Engineering Culture(Shell Aircraft) : Download File

PPT On Control and Systems Engineering : Download File

PPT On Aircraft Mechanical Engineering : Download File

Application of Compound Compressible Flow to Hypersonic Three-Dimensional Inlets


Abstract: A method for correcting flow non-uniformities and incorporating multiple oblique shocks waves into compound compressible flow is presented. This method has several applications and is specifically presented for the problem of creating a streamline-traced hypersonic three-dimensional inlet. This method uses compound compressible flow theory to solve for the freestream flow entering a pre-defined duct with a desired downstream profile. This method allows for multiple iterations of the design space and is computational inexpensive. A method is also presented for modeling a laminar or turbulent boundary layer to compare inlet designs and to determine the viscous correction to the inlet. Two different Mach 6 designs were evaluated, with a rectangular capture area and circular combustor with a uniform temperature, pressure, and Mach number profile. Comparison with other three-dimensional inlets indicates those designed with this method demonstrate good inviscid performance. These inlets also have the ability to correct incoming flow non-uniformities.

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Architecture for the Autonomous Generation of Preference-Based Trajectories


Abstract: Numerous techniques exist to optimize aircraft and spacecraft trajectories over cost functions that include terms such as fuel, time, and separation from obstacles. Relative weighting factors can dramatically alter solution characteristics, and engineers often must manually adjust either cost weights or the trajectory itself to obtain desirable solutions. Further, when humans and robots work together, or when humans task robots, they may express their performance expectations in a "fuzzy" natural language fashion, or else as an uncertain range of more or less acceptable values. This work describes a software architecture which accepts both fuzzy linguistic and hard numeric constraints on trajectory performance and, using a trajectory generator provided by the user, automatically constructs trajectories to meet these specifications as closely as possible. The system respects hard constraints imposed by system dynamics or by the user, and will not let the user's preferences interfere with the system and user needs. The architecture's evaluation agent translates these requirements into cost functional weights expected to produce the desired motion characteristics. The quality of the resulting full-state trajectory is then evaluated based on a set of computed trajectory features compared to the specified constraints. If constraints are not met, the cost functional weights are adjusted according to precomputed heuristic equations. Heuristics are not generated in an ad hoc fashion, but are instead the result of a systematic testing of the simulated system under a range of simple conditions. The system is tested in a 2DOF linear and a 6DOF nonlinear domain with a variety of constraints and in the presence of obstacles. Results show that the system consistently meets all hard numeric constraints placed on the trajectory. Desired characteristics are often attainable or else, in those cases where they are discounted in favor of the hard constraints, failed by small margins. Results are discussed as a function of obstacles and of constraints.

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Aerospace Project


This is a Aerospace Project On Bending Of Selectively Reinforced Beams is good project report and experiment for students which aims to investigate the flexural behavior of structural beam elements through experimentation and analysis. Additionally, the goal of the experiment is to assess the utility of composite materials as reinforcement components. In this 3 beams will be tested viz. an aluminum beam, an aluminum with aluminum caps, and an aluminum with graphite/epoxy caps.The beam with the thin aluminum top and bottom pieces will theoretically deflect more than the beam with the extra aluminum caps.
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Report On Sensors And Actuator System Of Special Hyper Redundant Robot


Abstract: This is a M.Tech seminar report on Sensors And Actuator System Of Special Hyper Redundant Robot and submitted to Department of Aerospace Engineering. Spatial Hyper Redundant Robot (SHR) is an all terrain robot and sometimes has special features like climbing ladder or a pole or climbing through a vertical duct, it requires special arrangement of sensors throughout its body. The whole report tells about different type of sensor, actuators, joint designing,  etc. through chapters. 

The above image shows a actuated universal joint discussed in this seminar report. In this report, the roll of sensors and actuators in SHR and their implementation in various type of design philosophy has been reviewed. Different types of joint architectures has been also discussed here and it has been found that modern researches on actuator implementation is evolved around the necessity of a perfect joint mechanism, which can give an uniform performance in versatile conditions.

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Aerospace Project On Composite Construction of an Unmanned Aerial Vehicle


This is a Aerospace Project Report on Composite Construction of an Unmanned Aerial Vehicle. The purpose of this thesis is to develop an understanding of composite construction while building a systematic manufacturing and assembly process for the construction of an all-composite Unmanned Aerial Vehicle. Use this thesis only for your reference and study.

This thesis in intended for both beginners and advanced composite builders and documents the entire construction of a molded composite aircraft from CAD to Runway. Several processes are discussed including CNC Plug Milling and Foam Cutting, Wet Lay-up, Tooling Manufacturing and Vacuum Assisted Resin Transfer Molding (VARTM - Infusion).

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Aircraft Mechanical Seminar Project Report On Stealth Technology In Aircraft's


Intro: This is a Aircraft Mechanical Seminar Project Report On Stealth Technology In Aircraft's done for third year Mechanical Seminar work report. Stealth aircraft are aircraft that use stealth technology to make it harder to be detected by radar and other means than conventional aircraft by employing a combination of features to reduce visibility in the visual, audio, infrared and radio frequency (RF) spectrum and the project report focus on other different aspects.

The report also tells about principles of radar reflectivity and how they can be exploited when one starts thinking about aiming for stealth in earnest and RCS minimization techniques.

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AirCraft Hydraulic System


AirCraft Hydraulic System is a Mechanical Seminar project Report and will tell about hydraulic and then gives the definition of Aircraft Hydraulic as a system where liquid under pressure is used to transmit this energy. Hydraulic systems take engine power and convert it to hydraulic power by means of a hydraulic pump. It also tell about Some Hydraulic Systems in Aircraft's such as Primary control boosters, retraction and extension of landing gear, Automatic pilot and gun turrets etc. 

The report also gives the function of the hydraulic system power pump is to change mechanical horsepower to hydraulic horsepower and types of Power Pumps.

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High Altitude Aeronautical Platform Stations (HAAPS)


This is High Altitude Aeronautical Platform Stations (HAAPS) Seminar Report made by Aeronautical, Electronics and Telecommunication Engineers and is the name of a technology for providing wireless narrow band and broad-band telecommunication services as well as broadcasting services with either airships or aircraft's.A high altitude telecommunication system comprises an airborne platform typically at high atmospheric or stratospheric altitudes – with a telecommunications payload, and associated ground station telecommunications equipment.

The High Altitude Long Operation (HALO) Network is a broadband wireless metropolitan area network (MAN) consisting of HALO aircraft operating at high altitude and carrying an airborne communications network hub and network elements on the ground.

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Augmented Reality for Space Applications


Abstract On Project: The Future space exploration will inevitably require astronauts to have a higher degree of autonomy in decision-making and contingency identification and resolution. Space robotics will eventually become a major aspect of this new challenge, therefore the ability to access digital information will become crucial for mission success. In order to give suited astronauts the ability to operate robots and access all necessary information for nominal operations and contingencies, this thesis proposes the introduction of In-Field-Of-View Head Mounted Display Systems in current Extravehicular Activity Spacesuits. The system will be capable of feeding task specific information on request, and through Augmented Reality technology, recognize and overlay information on the real world for error checking and status purposes The system will increase the astronaut's overall situational awareness and nominal task accuracy, reducing execution time and human error risk.

The aim of this system is to relieve astronauts of trivial cognitive workload, by guiding and checking on them in their operations. Secondary objectives of the system will be the introduction of electronic checklists, and the ability to display the status of the suit and surrounding systems as well as interaction capabilities. Features which could be introduced are endless due the nature of the system, allowing extreme flexibility and future evolution without major design changes. This work will focus on the preliminary design of an experimental Head Mounted Display and its testing for initial evaluation and comparison with existing information feed methods. The system will also be integrated and tested in the University of Maryland Space Systems Laboratory MX-2 experimental spacesuit analogue.

Keywords: Engineering, Aerospace Engineering, Aerospace Augmented Reality; Virtual Reality; Head Mounted Display; Vision Sensing


Bio-Inspired Information Extraction In 3-D Environments Using Wide-Field Integration Of Optic Flow


Abstract on Project: A control theoretic framework is introduced to analyze an information extraction approach from patterns of optic flow based on analogues to wide-field motion-sensitive interneurons in the insect visuomotor system. An algebraic model of optic flow is developed, based on a parameterization of simple 3-D environments. It is shown that estimates of proximity and speed, relative to these environments, can be extracted using weighted summations of the instantaneous patterns of optic flow. Small perturbation techniques are utilized to link weighting patterns to outputs, which are applied as feedback to facilitate stability augmentation and perform local obstacle avoidance and terrain following.

Weighting patterns that provide direct linear mappings between the sensor array and actuator commands can be derived by casting the problem as a combined static state estimation and linear feedback control problem. Additive noise and environment uncertainties are incorporated into an offline procedure for determination of optimal weighting patterns. Several applications of the method are provided, with differing spatial measurement domains. Non-linear stability analysis and experimental demonstration is presented for a wheeled robot measuring optic flow in a planar ring. Local stability analysis and simulation is used to show robustness over a range of urban-like environments for a fixed-wing UAV measuring in orthogonal rings and a micro helicopter measuring over the full spherical viewing arena. Finally, the framework is used to analyze insect tangential cells with respect to the information they encode and to demonstrate how cell outputs can be appropriately amplified and combined to generate motor commands to achieve reflexive navigation behavior.

Keywords: Engineering, Aerospace, Engineering, Robotics, Bio-inspired Navigation, Insect Vision, Obstacle Avoidance, Optic Flow, Tangential Cells, Wide-Field Integration.

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Axisymmetric Inlet Design for Combined Cycle Engines


Abstract of Project: This project Report is all about the Performance considerations for a turbine-based combined-cycle engine inlet are presented using the inlet of the Lockheed SR-71 as a baseline. A numerical model is developed using the axisymmetric method of characteristics to perform full inviscid flow analysis, including any internal shock reflections. Self-starting characteristics are quantified based upon the Kantrowitz limit. The original SR-71 inlet is analyzed throughout the designed self-starting regime, beginning at Mach 1.7 and ending with the shock-on-lip condition at Mach 3.2.

The characteristics model is validated using computational fluid dynamics. A series of modifications are then considered for their ability to extend the range of the inlet into the hypersonic flight regime. Self-starting characteristics of these new designs are also characterized; results indicate that two new designs can maintain self-starting capability into the Mach 6-7 range. Full external and internal flow properties of the new designs are determined using the characteristics model. Mach number, total pressure ratio, temperature, pressure and mass flow properties (and their levels of distortion) are quantified at the inlet exit plane for all cases considered.

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Keywords: Engineering, Aerospace inlet; combined cycle; propulsion; aerodynamics;

Autonomous Target Recognition and Localization for Manipulator Sampling Tasks


This is a Aeronautical Engineering Theses

Abstract on Project: Future exploration missions will require autonomous robotic operations to minimize overhead on human operators. Autonomous manipulation in unknown environments requires target identification and tracking from initial discovery through grasp and stow sequences. Even with a supervisor in the loop, automating target identification and localization processes significantly lowers operator workload and data throughput requirements. This thesis introduces the Autonomous Vision Application for Target Acquisition and Ranging (AVATAR), a software system capable of recognizing appropriate targets and determining their locations for manipulator retrieval tasks. 

AVATAR utilizes an RGB color filter to segment possible sampling or tracking targets, applies geometric-based matching constraints, and performs stereo triangulation to determine absolute 3-D target position. Neutral buoyancy and 1-G tests verify AVATAR capabilities over a diverse matrix of targets and visual environments as well as camera and manipulator configurations. AVATAR repeatably and reliably recognizes targets and provides real-time position data sufficiently accurate for autonomous sampling.

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Keywords: Engineering, Aerospace


APPLICATION OF REDUCED ORDER MODELING TECHNIQUES TO PROBLEMS IN HEATCONDUCTION, ISOELECTRIC FOCUSING AND DIFFERENTIAL ALGEBRAIC EQUATIONS


Abstract: This thesis focuses on applying and augmenting `Reduced Order Modeling' (ROM) techniques to large scale problems. ROM refers to the set of mathematical techniques that are used to reduce the computational expense of conventional modeling techniques, like finite element and finite difference methods, while minimizing the loss of accuracy that typically accompanies such a reduction. The first problem that we address pertains to the prediction of the level of heat dissipation in electronic and MEMS devices. With the ever decreasing feature sizes in electronic devices, and the accompanied rise in Joule heating, the electronics industry has, since the 1990s, identified a clear need for computationally cheap heat transfer modeling techniques that can be incorporated along with the electronic design process. We demonstrate how one can create reduced order models for simulating heat conduction in individual components that constitute an idealized electronic device. The reduced order models are created using Krylov Subspace Techniques (KST). We introduce a novel `plug and play' approach, based on the small gain theorem in control theory, to interconnect these component reduced order models (according to the device architecture) to reliably and cheaply replicate whole device behavior.

                                                         The final aim is to have this technique available commercially as a computationally cheap and reliable option that enables a designer to optimize for heat dissipation among competing VLSI architectures. Another place where model reduction is crucial to better design is Isoelectric Focusing (IEF) - the second problem in this thesis - which is a popular technique that is used to separate minute amounts of proteins from the other constituents that are present in a typical biological tissue sample. Fundamental questions about how to design IEF experiments still remain because of the high dimensional and highly nonlinear nature of the differential equations that describe the IEF process as well as the uncertainty in the parameters of the differential equations. There is a clear need to design better experiments for IEF without the current overhead of expensive chemicals and labor. We show how with a simpler modeling of the underlying chemistry, we can still achieve the accuracy that has been achieved in existing literature for modeling small ranges of pH (hydrogen ion concentration) in IEF, but with far less computational time. We investigate a further reduction of time by modeling the IEF problem using the Proper Orthogonal Decomposition (POD) technique and show why POD may not be sufficient due to the underlying constraints. The final problem that we address in this thesis addresses a certain class of dynamics with high stiffness - in particular, differential algebraic equations. With the help of simple examples, we show how the traditional POD procedure will fail to model certain high stiffness problems due to a particular behavior of the vector field which we will denote as twist. We further show how a novel augmentation to the traditional POD algorithm can model-reduce problems with twist in a computationally cheap manner without any additional data requirements. Keywords: Engineering, Aerospace Mathematics, Chemistry, Biochemistry, Differential Algebraic Equations, Heat dissipation electronic devices, Isoelectric Focusing, Krylov Subspace Theory, Proper Orthogonal Decomposition, Reduced Order modeling.

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Categorizing Admittance Control Parameters for the Ranger 8-DOF Tele-operated Space Manipulator

Abstract: Position-based admittance control of a robotic manipulator is a strategy that allows the manipulator to achieve compliance without sacrificing positional accuracy or modifying the underlying position controller. Desired manipulator stiffness and damping can be specified so that the tool tip behaves as a spring-dashpot system. This work characterizes the range of parameters that allows stable task execution in contact with an environment of varying stiffness for the Ranger dexterous manipulator. A classical stability analysis and simulation of the controller is conducted to predict its response in contact. The manipulator's behavior is then observed during a series of simple tasks involving contact in one and two degrees of freedom. Suitable gains are chosen such that interaction forces at the tool tip are kept low. A compliant peg-in-hole insertion task is successfully accomplished. The work also outlines the implementation of an algorithm that removes unwanted gravity forces measured at the tool tip.

Aeronautical training centers in INDIA


Aeronautics and aerospace are fast growing industries and many companies wish to hire fresh graduates to provide them training in such a way that the fresh graduates are perfectly molded to meet their requirements. This will enable the company to grow well since the fresh graduates are perfectly trained.

Training is normally given by these companies while working. On-the-job training is provided since this is a fast-moving industry and the engineers need to keep themselves updated about the latest development in the industry. Training differs from one organization to another, but most of these companies offer structured training and encourages the trainees to perform well.

The training schemes of some companies are accredited by professional bodies. Even some companies work with universities for developing perfect training programs for staff with different specialization and different levels. Some companies even provide training in other fields like project management, leadership qualities and information technology.

Some of the organizations providing training in India are given below:

Aeronautical Engineering Training Academy:
Aeronautical Engineering Training Academy is an exclusive training institution, established under the instruction of professionals in the field of aviation industry. The aim of this academy is to provide perfect training to the aeronautical engineering students in the specialized field of aviation. For more information the students can visit their web site http://www.iitmpune.com/

Alpine Institute of Aeronautics:
Alpine Institute of Aeronautics institute is run by the National Institute of Aeronautical Engineering. The institute effectively prepares the students for the field of aeronautical engineering by giving them exclusive training with the state of art lab equipment and facilities. For more information the students can visit their web site http://www.alpineddn.com/

Bharat Institute of Aeronautics:
Bharat Institute of Aeronautics is one of the few aeronautical training institutes providing excellent training to the students located within the boundaries of airport in Patna. This institute possesses its own maintenance hangar for providing full maintenance facilities. You can also Subscribe to AeronauticalProjects by Email for more such projects and seminar.

Seminar Topics and Project Titles For Aeronautics Engineering


The Following Are some of the Seminar Topics and Project Titles For Aeronautics Engineering: 
  1. Role of Nano Technology in Aeronautical Engineering
  2. Aeronautical satellite comunications
  3. Nanocoating in Aeroplanes
  4. Magnetoplasmadynamic thruster
  5. Advanced Space Vision System
  6. High Altitude Aeronautical Platform Stations (HAAPS)
  7. Scram jet
  8. Aeroplane Propulsion System
  9. BlackBox, Cryogenics
  10. Blended Winged Aircraft
  11. Aeroelasticity
  12. Max Launch Abort System(MLAS)
  13. Lunar space elevator
  14. W-LAN and UMTS in aircraft cabins
  15. Fixed-wing aircraft
  16. Internet applications in aeronautics
PART  2


  1. Re-Entry Of Space
  2. Vehicle Ramjet, Scramjet Engines
  3. Aircraft navigation Systems 
  4. Space Shuttles And Its Advancements 
  5. Advances  in Rocket Propulsion 
  6. Quasi Turbine Engines 
  7. Low Cost Spacecraft Simulator 
  8. Clearance of Space Debris 
  9. Materials used in Space Re-entry Vehicles 
  10. Fuel Cells on Aerospace 
  11. Advanced flight technology 
  12. Magnetoplasmadynamic thruster 
  13. Advanced Space Vision System 
  14. Aeroelasticity 
  15. Lithobraking 
  16. Lunar space elevator 
  17. Fixed-wing aircraft 
  18. Space transport 
  19. Hohmann transfer orbit 
  20. Early Flying machines 
  21. Sigma Gamma Tau (aerospace engineering honor society) 
  22. Electrotechnology 
  23. Gas-generator cycle (rocket) 
  24. Antimatter rocket 
  25. Apsis HyShot 
  26. Atmospheric reentry issues 
  27. Avionics 
  28. Kessler Syndrome 
  29. Relativistic rocket 
  30. Nose cone design 
  31. Redshift rocket 
  32. Big dumb booster 
  33. Ablative laser propulsion
  34. High Altitude Technology 
  35. Safety in aerospace engineering 
  36. Landing and take-off of aerospace vehicles. 
  37. Advanced Fuels in aerospace engineering 
  38. Control system used in aerospace vehicle
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nanomaterials for aerospace applications.


Abstract : The technical challenges and the key research efforts in the field of nanomaterials for aerospace applications. Specifically, it focuses on carbon nanotube-reinforced polymers and materials produced by severe plastic deformation (SPD). Selected European projects and world conferences related to aerospace are included. The state of the art of polymer nanocomposite research is also reviewed. In the aerospace industry, there is a great need for new materials which exhibit improved mechanical properties. Materials possessing high strength at a reduced mass and size make lighter aircraft with lower fuel consumption. The development of new materials with tailored properties is a primary goal of today’s materials science and engineering. However, the possibility of obtaining improved mechanical properties by the conventional methods of cold working, solution hardening, precipitation hardening, etc., has been almost exhausted. We explicitly exclude any military R&D and applications, as this falls outside the mandate of Nanoforum. Our target audiences are twofold: non-experts of an academic level with a general interest in the potential of nanotechnology for aerospace applications, and experts involved in setting the strategic R&D agenda in this field. There are single wall and multi wall thicked carbon nanotubes(SWCNT and MWCNT). Mechanical features of CNT:Young's modulus: 1 TPa ',Tensile strength: 200GPa CNTs have been shown to provide desirable electrical properties for polymer matrix composites.The applications in aerospace industry are through thermal barrier and wear resistant coatings, sensors that can perform at high temperature and other physical and chemical sensors, sensors that can perform safety inspection cost effectively.
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Ceramic Damage Model for Analyses of Multi-Layered Ceramic-Core Sandwich Panels Under Blast Wave Pressure Loading


Abstract: Ceramics have been used as armor materials because of their high effectiveness in absorbing kinetic energy under extreme loading conditions such as ballistic impacts. This is possible because they have very high compressive strengths. Ceramics exhibit significant compressive strength even when pulverized by a ballistic projectile. In addition, ceramic armors are lightweight, compared to conventional steel armors that are much heavier and more cumbersome. However, the brittleness of ceramics under tension has limited their use to applications that require little deformation such as the torso of war fighters. 
                              A damage model for ceramic materials is developed and incorporated into the geometrically nonlinear solid shell element formulation for dynamic analyses of multi-layered ceramic armor panels under blast wave pressure loading. The damage model takes into account material behaviors observed from multi-axial dynamic tests on Aluminum Nitride (AlN) ceramic. The ceramic fails in a brittle or gradual fashion, depending upon the hydrostatic pressure and applied strain-rate. In the model, the gradual failure is represented by two states: the initial and final failure states. These states are described by two separate failure surfaces that are pressure-dependent and strain-rate-dependent. A scalar damage parameter is defined via using the two failure surfaces, based on the assumption that the local stress state determines material damage and its level. In addition, the damage model accounts for the effect of existing material damage on the new damage. The multi-layered armor panel of interest is comprised of an AlN-core sandwich with unidirectional composite skins and a woven composite back-plate. To accommodate the material damage effect of composite layers, a composite failure model in the open literature is adopted and modified into two separate failure models to address different failure mechanisms of the unidirectional and woven composites.
 Keywords: Engineering, Aerospace, Engineering, Mechanical, Applied Mechanics.
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Characterization and Modeling of the Magnetomechanical Behavior of Iron-Gallium Alloys


Department/Program Of Aerospace Engineering / Technology
Abstract: Magnetostrictive Iron-Gallium alloys (Galfenol) demonstrate moderate magnetostriction (~350 ppm) under very low magnetic fields (~100 Oe), have very low hysteresis, high tensile strength (~500 MPa), high Curie temperature (~675°C), are in general machinable, ductile and corrosion resistant. Therefore, they hold great promise in active vibration control, actuation, stress and torque sensing in helicopters, aircrafts and automobiles. To facilitate design of magnetostrictive actuators and sensors using this material, as well as to aid in making it commercially viable, it is necessary to perform a comprehensive characterization and modeling of its magnetomechanical behavior. This dissertation addresses some of these issues, focusing primarily on quasi-static characterization and modeling of the magnetomechanical behavior of single-crystal FeGa alloys with varying gallium content and along different crystallographic directions, and studying the effect of texture on the magnetomechanical behavior of polycrystals. Additionally, improved testing and modeling paradigms for magnetostrictive materials are developed to contribute to a better understanding and prediction of actuation and sensing behavior of FeGa alloys. In particular, the actuation behavior (λ-H and B-H curves) for 19, 24.7 and 29 at. % Ga <100> oriented single crystal FeGa samples are characterized and the strikingly different characteristics are simulated and explained using an energy based model. Actuation and sensing (B-σ and є-σ curves) behavior of <100> oriented 19 at. % Ga and <110> oriented 18 at. % Ga single crystal samples are characterized. It is demonstrated that the sensing behavior can be predicted by the model, using parameters obtained from the actuation behavior. The actuation and sensing behavior of 18.4 at. % Ga polycrystalline FeGa sample is predicted from the volume fraction of grains close to the [100], [110], [210], [310], [111], [211] and [311] orientations (obtained from cross-section texture analysis). The predictions are benchmarked against experimental actuator and sensor characteristics of the polycrystalline sample.
Project Intro: Smart materials display a large coupling of thermal, electrical or magnetic properties with mechanical properties enabling them to directly transduce energy from one form to another in an efficient manner. These properties have made them promising materials for actuation and sensing applications. Over the past two decades various smart materials, viz. shape memory alloys, piezo-electrics and magnetostrictive materials, which respectively transduce thermal, electrical and magnetic energy to mechanical energy, have been used as actuators and sensors in a wide range of fields: medicine, micro-positioning, atomic force microscopes, torque sensing and fuel injection systems in automobiles, sonar transducers for the Navy and control surfaces of helicopters and aircrafts.
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Keywords: Engineering, Aerospace Engineering, Materials Science, Applied Mechanics, Iron-Gallium, Magnetostrictive, energy-based model, magnetomechanical, characterization


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