Title: A 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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The Following Are some of the Seminar Topics and Project Titles For Aerospace Engineering:

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 vehicles

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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.

Title: 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.

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Keywords: Engineering, Aerospace, Impedance, Admittance, Control, Robotic Manipulator
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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

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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;

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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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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

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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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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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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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