Project Planning for Design of Aircraft Undercarriage - Report Example

Project Planning for design of Aircraft Undercarriage Name Institution Affiliation Project Planning for Design of Aircraft Undercarriage Project background The aim of the project is design and simulate an aircraft landing gear which is a critical component of the aircraft. The purpose of landing gear on an aircraft is to maneuver the ground operations. Landing requires a lot of energy thus the landing gear must be properly designed for stability. The design and modeling should takes into account that a landing gear can withstand various conditions during it use such as riding performance, crash survivability, stroke length weight and height(Dobrzynski et.al 2010). The landing gear proposed is should in the diagram below The design and simulation of the landing gear will aim at behavior during touch down impact as well as performance excitation induced by track roughness during takeoff and landing. The available landing gears are costly thus this design will take into account the cost reduction(Thota, Krauskopf, & Lowenberg,(2011). Purpose of the project The main objective of this project is to do design and simulate landing gear. Therefore the main is to develop landing gear model for simulation. The other aim is to use Lagrangian formulation as well as momentum energy methods to formulate equations of motion. Dynamic Modelling This model will require accuracy in computing the variables of the landing gear. The following is the specification of the LANDING GEAthat will be modeled using autocad’s software.  In the equation x0-x represents deformation during the collision while x≥x0 represents a contact force when there is no collision. Collision occurs when x>x0. The dumping co-efficient is represented by C while D represents penetration debt. This equation has an S which is written as follows: S =  where , ,  In this case change in d =  and is deformation of the body that is contact with the broken tooth. Stiffness is presented by K and is calculated by using the following follows; The materials for the pinions and gears of the landing gear are alloy steel and cast steel respectively, and the values for the Poisson ratio and the Young’s Modulus are listed below. Through calculation, the stiffness values for the three gear pairs in the drive line of the landing gear. LAGRANGE'S EQUATIONS OF MOTION There are various parts of that require different elements, forces and moments that will help in deriving of Newton's equations. In this model the following equations of motion will be used in deriving modeling equation. The equation that governs the movement It can as well be written as Where pi is linear momentum and t is time, mi is mass, ai is acceleration and F is force. Where T is kinetic energy and can be calculated as The momentum is written as Then this expressed as Then if we apply Newton’s second law of motion then Then adding up Langrange’s equation Project Methodology The project will be done in phases so as to ensure that each stage is undertaken to perfection. Some of the phases will include confirmation from the department professors to give guidelines for the next course of action. The 1st step of this project will include identification of the specific area of study for the project. In this case, we have already identified undercarriage design. Further, we engaged in the identification of a topic for the project. The topic was then refined so as to set the stage for working on the proposal. The next step for this project is the development of the proposal and its presentation to the professor for verification and corrections. This stage is also accompanied by drawings and design on Solidworks. The stage also involves simulations of the same project on SolidWorks as well. The next stage of the project will involve actualization of the project by the actual assembly. Basically, the project will involve a lot of work in the mechanical engineering workshops. Here, we will need welding machines and rods, metal rods amongst other materials. Further, we will also require a lathe machine for a number of machining operations. In some instances, specialized machining from experts will be required. During such instances, the technologists in the workshop will be called in to assist accordingly. In an instance that a specific part may not be manufactured at the workshop, there will be freedom to outsource services of a more skilled person. Standard parts will be outsourced from dealers as a time for manufacturing them may be limited. Action Plan Milestone Description Duration 1 Stage 1: Area of interest identified 3 days   2 Stage 2: Specific topic selected 2 days 3 Stage 3: Topic refined to develop Dissertation Proposal 4 days 4 Stage 4: Proposal writing, designs , simulations and submission 10 days 5 Stage 5: Collection of data and information 3 days   6 Stage 6: Data analysis and interpretation 3 days   7 Stage 7: Compiling the information 3 days  8 Stage 8: Final draft prepared—submission of dissertation  1 day Gantt chart Ethical issues Consideration of ethical issues that surround a project comes in handy. In this design, we are faced with a number of ethical issues that will need to be discussed with the department before the actual construction of the project begins. Researchers and engineers have been able to come up with strong high fiber content materials that are lighter and stronger (Torenbeek, 2013). The newly founded composites are also deemed safer than steel alloy frames in earlier versions of the aircraft. There is, however, a hurdle that arises and further leads a contravention of one of our design objectives. Newer fiber composites are more expensive to procure for this project. As a matter of fact, we may not be able to purchase the fiber composites. This leaves us with lesser options. It also means that we will use steel alloys for this construction hence compromising current safety directives. This matter will, however, be considered and given maximum attention by the team. Pursuant to Aircraft safety directive of 2012, engineers are continously requested to consider the positioning of the fuel tanks in relation to the landing gear (Currey, 2008).  Accidents that have happened during landing have been associated with the landing kit either directly or indirectly. In our design, we have not considered this directive, however. This is due to the fact that current planes still have old configurations. Considering the fact that we are only a small scale designer, we opt to leave these drastic design changes to larger players in the industry. It would not be wise to create a part that will not be compatible with the currently available planes in the market. This ethical dilemma might remain as so due to technicalities surrounding it. Internal partners It is important to note that most parts involved in the project will be manufactured in the mechanical engineering workshop. As such, the mechanical engineering department automatically becomes a partner in this endeavor. Further, we will also use mechanical engineering laboratories for tests on some of the materials and parts. Aeronautical engineering department will thus require to write and seek approval from the mechanical engineering department. Further, we will require using the electrical engineering lab for a series of activities. Aeronautical engineering department will also seek approval as well from this department. External partners We also note that there will be a need for approvals and permits to access a hangar in the nearby airport to do our tests of the complete part with specialists and experienced engineers. As such, The University will need to seek approval from these external partners. There will be ethical issues that may arise from the use of airport facilities as the landing gear will be specifically tested on test planes and not any passage or cargo plane. Other external partners may include shops selling standard parts like nuts, tires, and bushes. We may not require any approvals for such. Expected outcome Simulation was done for duration of 0.5 seconds where the time interval was 0.01 seconds. The resistance force which was applied on the shaft of the landing gear was 8000N. The initial velocity that was used acted on the output shaft producing a maximum torque on the shaft. However, the supposed vibration is normally monitored as a way of determining the relative conditions regarding other motors so as to plan well certain preventive and maintenance procedures. The supposed vibration of the motor does occur over a moderately broad frequency band as opposed to the low when compared to the higher frequencies. There are different problems that may occur in a rotating motor especially when loaded. The problems that do occur arise from the distinct vibration types. For instance, there are rotor imbalances that do produce a particular significant rise when it comes to the spectrum that does emit the radial vibrators. When the bearing problems do occur, they normally create such an increase particularly when it deals with the high frequencies. This is due to the fact that the high frequencies normally make the motors to rotate approximately twelve times more therefore the speed is much faster. There is a major concern especially when the proactive maintenance method is undertaken to detect the rolling element of bearings. In addition, there is vibration that is related and conn3cted with the worn bearings which is usually created from the numerous impacts of the numerous metal parts. There have been accurate analyses meant to figure out very well the internal structure of a bearing so as to provide frequencies that is the appropriate one for each motor. This is meant to reduce the various problems that do arise from the rotating machine especially if they have been in use for a long time. During the calculation of the various frequencies used in the bearings, the calculations do require one to know some basic information that is typically known. For example, the typical information includes the race diameter: inner and outer size, particular number of balls and their sizes. However, there are some manufacturers that do change particular internal designs so as to complicate the specifications. Consequently, the specified bearings sizes are not changed. What the manufactures guarantee is that the typical information concerning parameters: size, speed or load deployed: is not easily known. As such, the vibration analysis to monitor the rotating speed of the machines is dependent on such factors. The machine must be able to generally use the properties regarding the vibration analysis especially when during the concept of proactive maintenance when it comes to rotating machines. Discussion It is obvious that a landing gear can be a source of major system failure if it is not measured and adequately analyzed and monitored. It is posted for this discussion that where extreme reliability is needed in the measurement and monitoring of the vibrations, then the permanent online monitoring system is most desired. Although this may be limited to a single component, it is notable for the ability to give sufficient information about the vibration that can be useful in determining the cause and source of a vibration in a machine. And as noted in the case of an engine in which reciprocating forces are applied, it is obvious that to train the dataset so as to enhance the extra body vibrations in the system will require a permanent online monitoring system to overlay such signals. References Austin, R. (2011). Unmanned aircraft systems: UAVS design, development and deployment (Vol. 54). John Wiley & Sons. Chai, S., & Mason, W. (2006). Landing gear integration in aircraft conceptual design. In 6th Symposium on Multidisciplinary Analysis and Optimization (p. 4038). Currey, N. S. (2008). Aircraft landing gear design: principles and practices. Aiaa. Dobrzynski, W., Chow, L. C., Smith, M., Boillot, A., Dereure, O., & Molin, N. (2010). Experimental assessment of low noise landing gear component design. International Journal of Aeroacoustics, 9(6), 763-786. Hahn, A. (2010, January). Vehicle sketch pad: a parametric geometry modeler for conceptual aircraft design. In 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition (p. 657). Sadraey, M. H. (2012). Aircraft design: A systems engineering approach. John Wiley & Sons. Thota, P., Krauskopf, B., & Lowenberg, M. (2011). Shimmy in a nonlinear model of an aircraft nose landing gear with non-zero rake angle. Torenbeek, E. (2013). Synthesis of subsonic airplane design: an introduction to the preliminary design of subsonic general aviation and transport aircraft, with emphasis on layout, aerodynamic design, propulsion, and performance. Springer Science & Business Media. Read More

Basically, the project will involve a lot of work in the mechanical engineering workshops. Here, we will need welding machines and rods, metal rods amongst other materials. Further, we will also require a lathe machine for a number of machining operations. In some instances, specialized machining from experts will be required. During such instances, the technologists in the workshop will be called in to assist accordingly. In an instance that a specific part may not be manufactured at the workshop, there will be freedom to outsource services of a more skilled person.

Standard parts will be outsourced from dealers as a time for manufacturing them may be limited. Action Plan Milestone Description Duration 1 Stage 1: Area of interest identified 3 days   2 Stage 2: Specific topic selected 2 days 3 Stage 3: Topic refined to develop Dissertation Proposal 4 days 4 Stage 4: Proposal writing, designs , simulations and submission 10 days 5 Stage 5: Collection of data and information 3 days   6 Stage 6: Data analysis and interpretation 3 days   7 Stage 7: Compiling the information 3 days  8 Stage 8: Final draft prepared—submission of dissertation  1 day Gantt chart Ethical issues Consideration of ethical issues that surround a project comes in handy.

In this design, we are faced with a number of ethical issues that will need to be discussed with the department before the actual construction of the project begins. Researchers and engineers have been able to come up with strong high fiber content materials that are lighter and stronger (Torenbeek, 2013). The newly founded composites are also deemed safer than steel alloy frames in earlier versions of the aircraft. There is, however, a hurdle that arises and further leads a contravention of one of our design objectives.

Newer fiber composites are more expensive to procure for this project. As a matter of fact, we may not be able to purchase the fiber composites. This leaves us with lesser options. It also means that we will use steel alloys for this construction hence compromising current safety directives. This matter will, however, be considered and given maximum attention by the team. Pursuant to Aircraft safety directive of 2012, engineers are continously requested to consider the positioning of the fuel tanks in relation to the landing gear (Currey, 2008).

  Accidents that have happened during landing have been associated with the landing kit either directly or indirectly. In our design, we have not considered this directive, however. This is due to the fact that current planes still have old configurations. Considering the fact that we are only a small scale designer, we opt to leave these drastic design changes to larger players in the industry. It would not be wise to create a part that will not be compatible with the currently available planes in the market.

This ethical dilemma might remain as so due to technicalities surrounding it. Internal partners It is important to note that most parts involved in the project will be manufactured in the mechanical engineering workshop. As such, the mechanical engineering department automatically becomes a partner in this endeavor. Further, we will also use mechanical engineering laboratories for tests on some of the materials and parts. Aeronautical engineering department will thus require to write and seek approval from the mechanical engineering department.

Further, we will require using the electrical engineering lab for a series of activities. Aeronautical engineering department will also seek approval as well from this department. External partners We also note that there will be a need for approvals and permits to access a hangar in the nearby airport to do our tests of the complete part with specialists and experienced engineers. As such, The University will need to seek approval from these external partners. There will be ethical issues that may arise from the use of airport facilities as the landing gear will be specifically tested on test planes and not any passage or cargo plane.

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