This project proposes to synthesize a high-lift mechanism (HLM) of a transportation aircraft, which is very important mechanism to generate addition lift to the wing of aircraft in take-off and landing condition. The crucial design problem is a minimization of error between the motions of a four-bar mechanism for controlling a flap to the target point. The optimum target points are positions and angles of flap at the take-off and landing condition, which design based on aerodynamic to maximize lift/drag and it is found from the review of literature. Design constraints include the possibility of four-bar mechanism to work well, limiting position and includes workplace of mechanism. The optimizer is used in this study, is in a group of Metaheuristics (MHs). The results show the optimum mechanism can generate flap motion meet with the design targets causes the proposed technique can increase the performance of HLM.
To observe the kinematics and accuracy of the four-bar linkage mechanism, the authors designed wing model with single-slotted fowler flap in solid work program to simulate the kinematics, which refer to the length parameters that obtain from numerical experiment. Then, the demonstration set of the single-slotted fowler flap is to test and compare the desire position and angular of HLM at a take-off condition. From the experimental results show the result is meet with the numerical result.
Although most aircraft gains its power using the gas engine as turbojet, turbofan or as rocket engine there is a kind of device used to produce thrust which is “propeller”, the first thrust producing device in the world used until nowadays, along with Science theories and today’s technologies were used for development in airplane propeller for greater efficiency.
To provide the knowledge for an individual who interested in this field, the purpose of this research is to study the basic knowledge of airplane propeller and the creation of an apparatus that is capable to be used in the propeller characteristics measurement and the experiment result comparison are included.
Turbojet engines are the first and simplest type of gas turbine engines. A basic of jet engines consist of air inlet, air compressor, combustion chamber, turbine, and exhaust nozzle.
The jet engines as part of an aviation engineering program which the objectives of this project were to (1) rebuild and repair for the jet engine demonstration laboratory; (2) to design the inlet attach to the SWIWIN SW60B turbojet engine; (3) to install new pressure sensor to measure the total pressure at the new inlet; (4) to measure actual thrust of engine and compare to the previous and calculation thrust; and (5) to measure, calibrate data from sensors by using LabVIEW program.
This experiment, the researchers decided to study on the effective of the inlet shape by create three design inlet consist of 95 millimeters diameter inlet, 100 millimeters diameter inlet, and 120 millimeter diameter inlet attach to the SWIWIN SW60B turbojet engine. From the previous senior project, the engine was installed seven sensors to measured air properties, thrust, and engine RPM. This project the new sensor to measure the pressure at the design inlet was installed and re-calibrate all the sensors. When experimenting, the measured data from sensors were sent to data acquisition system. After that the output data is sent to the personal computer with the LabVIEW program and showed on the ECU display. After the experiment finished, the data is recorded and then compared to the data of OEM inlet and plot the graphs, the different is shown the effectiveness of the air inlet shape.
The thrust produce from the jet engine depend on engine RPM and the inlet. It was found that in the range low RPM up to 30 percent throttle, 100 millimeter diameter inlet can produce the most measured thrust. For the higher RPM, 40-70 percent throttle is produce the most measured thrust with 95 millimeter diameter inlet and 80-100 percent throttle OEM inlet can produce the most measured thrust. The calculated thrust of inlet 100 millimeter diameter inlet is the best and also generate the least amount of additive drag. Even though no inlet has the highest value of thrust but it has no inlet, So the additive drag can not be calculated and mass flow rate is not reasonable.
This project provides to understanding about the fundamental knowledge, the method to increase the thrust of the jet engine by a focus on inlet shape and also opportunities to apply in an aircraft power plant.
This thesis aims to redesign the impeller in Centrifugal Pump. The impeller is a rotor like machinery use to move fluid. That are drive by either engine or electric motor. There is three type of rotor design. The open, semi open and closed impeller. Each type have there own advantage and disadvantage. And considering the blade design there are three main type of blade arrangement. The forward, radial and backward blade arrangement. Which we will further studies in this project.
Common problems faced in centrifugal pump are cavitation, vibration, noise, heat generated and leakage. This Project focused mainly on the design of the pump impeller. To improve overall efficiency and pump performance. The best efficiency point is the point of highest efficiency of the pump. Because there are partially energy loss to the fluid and external factors. To redesign and considerate new design of the pump impeller.
The calculation Is intended to determine the best type of impeller design and configuration. That provide the best efficiency of flow rate relative to the work input. which will determine the best type suitable for the industries and application.
This research studies about Electric Power engine UAV design for the intelligence surveillance and reconnaissance(ISR) and summarization the performance to present the principle that constitute the fundamental of flight and basic flight control, starting from conceptual design define requirement and calculation critical performance of aircraft to find the constrain diagram. The constrain diagram indicates the design point on graph between power and wing loading to layout design. In Preliminary design includes wind tunnel testing. Wind tunnel testing will find aerodynamic performance such as coefficient of lift, coefficient of drag, angle of attack. Use Solid work and XFLR. They are computer program simulate airflow on the wing and empennage. Detail design includes flight testing. The flight testing proves the aircraft that accord to requirement. The knowledge was studied to be user-friendly and to be the source of knowledge to interested people and next generation students.
This study’s purpose is to be able to construct a wind tunnel, to be used as a learning tool for Aeronautical Students, as well as any interested individuals. Wind tunnel instruments are hard to come by, furthermore, it is an expensive piece of equipment, our problem is to construct a low-cost wind tunnel that is capable of learning purposes.
This study will allow us to understand the instrument used in the aviation industry. We learn from the experiences in solving problems during conducting this project. The instruments which we produce will be one of the most useful equipment in the department of aeronautical engineering laboratory for learning and researching. We hope our instrument could be of any assistance to education in aeronautical engineering.
The unmanned aerial vehicles (UAV) are one of the technological advancements that develop to satisfy human’s requirements such as area observation and goods delivery. It is known as drones, which are the unmanned piloted aircraft. Generally, the UAV requires taking-off area to produce sufficient lift and velocity for launching into the sky. Moreover, with hands launching, this results in difference of work that is input to the UAV. Consequently, the horizontal distances and time are inaccurate and unreliable. This project aims to design and assemble the glider launcher for achieving the solution on launching operations and study the aerodynamic of gliders. The launcher allows the users to exceed the limit of taking-off area with constant work exerted on the gliders.
To observe the performance of the launcher, the researchers designed and built gliders to test the assembled launcher. The experiment applied on four different conditions of gliders, which were varied on the aspect ratio, wing characteristic, and dihedral angle. The drawing of complete dimensions to both launcher and gliders was complete in Google Sketchup. After the launcher was modified, the gliders were used to inspect the efficiency of the launcher. In addition, the tests were observed on the horizontal distances varying with time including the performance of each glider. Likewise, the calculation and experimental results would enhance the determination of the launcher capability.
After the experiment were done, the researchers found out that there are several deviations occurred during the trials. The model SII and SIII seems to achieve the results with the percentage error less than 10% and can be considered as acceptable results. However, with the model SI and SIV, they experienced with the percentage error more than 10%, which they are exceeding the error that the authors predict in the hypothesis. The deviation might cause by the effect from environmental such as winds and launcher friction.
The results suggested that the launcher was designed as expected which has suitable size and force generating enough to drive the glider up to 8kg. In further research, the launcher can still have improvement such as adding new structure or change the force generating system. Likewise, the study can still be performed to increase the performance of the system.
A beam is a part of a structure that receives the bending moment and shear, which is caused by external forces exerted on or loaded on that beam. When the beam receives weight or external force, it deflects and causes damage to the structure. The purpose of this study is to design and manufacture a simple experimental apparatus to measure the deflection distances of beams under various loads carried on small beams and for use in the laboratory of Aeronautical Engineering and Commercial Pilot Department to enhance the understanding about the fundamental knowledge of the mechanics of material and aircraft structure. Various materials are considered in terms of suitability and strength for building apparatus, stainless steel and steel are chosen for the construction of the frame and clamp. The dimensions of the apparatus were calculated to see whether it could support the maximum weight and strength. Solid Works was used for design’s and sketch’s the overall shape of the apparatus and a three-dimensional image for the factory to build the apparatus. Since the percentage error from the apparatus is need to be as small as possible, we choose to have a factory with expertise as a manufacturer of equipment, instead of producing the equipment ourselves. Lab sheet was designed to be used as an experimental document, collecting data and writing experiment reports for use in the laboratory of the department.
To test the strength and overall performance of the apparatus and to verify the suitability of the designed lab sheet, the experiment was therefore carried out following the design steps. First, we found that the size and strength of the equipment are as designed. Second, the structure can support the weight without any deviations that affect the experiment. Third, the designed experiment procedures can be done promptly. The experimental results were compared with theoretical calculations, with an error of 10% for the simply supported beam which is acceptable and 40% for the cantilever beam which is greater than the value that we set in hypothesis. The fact that the device and the constants value used in the calculations may not match the properties of the specimen might result in the unexpecting discrepancy.
The structure of the apparatus was designed to be large and suitable for the installation of different types of beams. But the main limitation of this deflection tester is the clamp, which can be used for holding a simply supported beam and cantilever beams with square cross-sectional areas only. Further research on this deflection tester is required to design a new clamp to support beam deflection measurements to cover all types of beams. Including changing the conventional dial gauge type to a digital dial gauge to increase accuracy in the experiment.
Presently, the average of greenhouse gases and fuel prices are continuously rising higher due to ground vehicle usage. The main causes of this problem are an aerodynamic drag, it is generated by the separation of flow near the rear end of the vehicle which caused the car to drive slower and loss more fuel. In aerodynamics, drag is defined as the force that resists forward motion through air and parallel to the direction of the free-stream velocity of the airflow. The Vortex generator is the device that already being used in the aeronautical industry to delay the flow and improve aerodynamics. As their potential, the automotive industry rather uses this device applied on the trailing edge of the car to decrease the wake region and overall drag. In this study, SolidWorks and Blender were used to model the automotive van and Vortex generator presented in 3D. FCS (Facility control system) was used to simulate the flow situation and collect data. This paper presents the optimization result, drag reduction by use of vortex generators in the flow field which these effects take place. Finally, this research, found that the coefficient of drag was reduced by 11.30% at the velocity of 30 m/s of vortex generator at 10 degrees is the most effective in achieving the drag reduction.
A this thesis is “safety workshop”, the researchers have to consider various methods that will ensure safe access to the workshop and aside from safety, the researchers must consider the accidents that can occur in workshop and find solutions, including finding ways to prevent accidents, including the placement of machinery or equipment. In order to do so, the researchers need to use the rules and regulations that are necessary for the workshop, as well as relying on the international standards or the authorities to make it our standard and safety for those who use the workshop. In this project, safety in the workshop was created to make a workshop that has industry standards. By using rules and regulations set forth for use in building a workshop. After conducting the workshop, a few problems were discovered which may affect the standards. The rules and regulations that define this workshop standard will show that when creating a workshop, you will encounter some problems and limitations in the designated area. Also, it shows how we can solve problems with the workshop. This workshop will become a part of aeronautical engineering’s laboratory at the International Academy of Aviation Industry, King Mongkut’s Institute of Technology Ladkrabang. The workshop was created to be the source of knowledge for next-generation students.
The spacecraft docking operation needs an accurate, reliable, and robust object detection algorithm. Typically, the exact mathematical expression of the spacecraft motion is unknown. Therefore, the advanced computational algorithm is widely applied to the spacecraft position and attitude determination system. This research aims to construct the vision-based position and attitude estimation model with the employment of the image processing through the convolutional neural network. The pose estimation model was constructed by repurposing the modified GoogLeNet, a convolutional pre-trained model with the available Unreal Engine 4 rendered dataset of the spacecraft, Soyuz. In the implementation, the convolutional neural network learned from the data samples to create the correlation between the images and six degrees of freedom parameters. Furthermore, the complete pose estimation model has achieved moderately high performance. The position accuracy is 92.53 percent with an error of about 1.2 meters, while the accuracy in attitude prediction is 87.93 percent with errors in three Euler angles do not exceed 7.6 degrees. The demonstration in this research can be a contribution to the spacecraft tracking and detection problems.