AVS1230_Lab 2 Fall 2023

Problem You are tasked with  analyzing the frame of a bubble fuselage. The frame is 3D printed using PLA material and must be capable of supporting a 22.05 lb load placed within the cabin space, with the direction of the load indicating the direction of deformation. You will need to perform a series of calculations and analyses to ensure that the design meets strength and safety requirements. Data: Frame Dimensions: A blueprint is provided specifying the dimensions and geometry of the bubble fuselage frame. The thickness of the frame its 0.5 inch. Material: The frame will be 3D printed in PLA material. The material properties of PLA are as follows: Young's Modulus (E): 595669.99 Psi. Yield Strength (σy): 9094.01119 Psi. Density (ρ): 10.04515912 lb/in³ Load: A 22.05 lb load will be applied within the cabin space, with the load direction indicating the direction of deformation Tasks to Perform:( Remmember present the solution process with equations, procedure and results; use…

Write down a proper material for each structures given below. A pipe for water Material: Reason: exchange The nose section of an Material: aircraft fuselage Reason: The spar of an aircraft Material: wing Reason: Turbine blades of a Material: turbojet engine Reason: The skin of an aircraft Material: fuselage Reason: The structure of interior Material: furniture in aircraft cabins Reason: Material: The gearbox of a helicopter Reason: The front tips of a space Material: shuttle surface Reason:

Problem You are tasked with  analyzing the frame of a bubble fuselage. The frame is 3D printed using PLA material and must be capable of supporting a 22.05 lb load placed within the cabin space, with the direction of the load indicating the direction of deformation. You will need to perform a series of calculations and analyses to ensure that the design meets strength and safety requirements. Data: Frame Dimensions: A blueprint is provided specifying the dimensions and geometry of the bubble fuselage frame. The thickness of the frame its 0.5 inch. Material: The frame will be 3D printed in PLA material. The material properties of PLA are as follows: Young's Modulus (E): 595669.99 Psi. Yield Strength (σy): 9094.01119 Psi. Density (ρ): 10.04515912 lb/in³ Load: A 22.05 lb load will be applied within the cabin space, with the load direction indicating the direction of deformation Tasks to Perform:( Remmember present the solution process with equations, procedure and results; use…

Explain the most critical loading condition for fuselage central part structure of airliner aircraft. Draw figures of structure elements to resist this loading.

Q2: A fiberglass composite consists of a matrix of vinyl ester and reinforcing fibers of E-glass. The volume fraction of E-glass is 30%. The density of the vinyl estiser 0.882 g/cm³, and its modulus of elasticity is 3.6 GPa. The density of E-glass is 2.6 g/cm³, and its modulus of elasticity is 76 GPa. A section of composite 1 cm by 25 cm by 2 m is fabricated with the E-glass fibers running longitudinally in the 2000 mm direction. Determine: (a) The masses of vinyl ester and E-glass fibers. (b) The density of the composite. (c) The composite modulus of elasticity in the longitudinal and the perpendicular directions of the glass fibers. (d) If the tensile strength of the glass fibers, is 1 GPA and the tensile strength of the epoxy matrix is 60 MPa, find the tensile strength of the composite in the longitudinal direction.

d) A number of [0]s and [0,90]s CFRP test specimens were made from prepreg material with the following properties: Fibre strength, of = 3250 MPa Fibre modulus, E₁ = 195 GPa Matrix strength, m = 35 MPa Matrix modulus, Em = 3.8 GPa Volume fraction of fibres, Vf = 0.65 Calculate the tensile strength, oc, and the tensile modulus, Ec, in the 0° and 90° directions, using the simple "rule of mixtures" approach for both the [0]s and [0,90]s specimens.

70 docs.google.com/forms/d/e, w/l O w O W w+l O 4/4 How do point loads and uniform distributed load be represented in ?SFD Curved lines and inclined lines O Horizontal lines and inclined lines Horizontal lines and curved lines O Cant represent any more 4/4 A cantilever is a beam whose Both ends are fixed One end is fixed and other end is free +

Arrangement of your solution:   The following section should be underlined and  numbered in your solution   Problem statement   Given   Required   Drawing/ sketch / free body diagram  V. Solution with explanation

Which properties are the most helpful in identifyingminerals. Are these properties helpful in the field of engineering? *400 to 500 words FORMAT: i. Introductionii. First body paragraphiii. Second body paragraph... and so oniv. Conclusion

Topic: Mechanics of Deformable Bodies: Analysis on Trusses

Please explain ths graph from Materials Science and EngineeringAn Introduction

Provide at least three (3) advantages and disadvantages each of the following fuselage constructions: truss type/framework monocoque semi-monocoque Also, identify a five (5) aircrafts each that uses these types of fuselage construction and indicate their specifications

[Elastic Properties of Materials] There is a cylindrical bar of copper do in diameter is to be deformed elastically by application of a force along the bar axis. Using the data in Table given below, determine the normal force (F) that will produce an elastic reduction of Ad in the diameter. Use do 12.0 mm; Ad = d' - do = -3 × 10-³mm x = do 1 F d' l' Metal Alloy Aluminum Brass Copper Magnesium Nickel Steel Titanium Tungsten Modulus of Elasticity GPa 69 97 110 45 207 207 107 407 106 psi 10 14 16 6.5 30 30 15.5 59 Shear Modulus 106 psi GPa 25 37 46 17 76 83 45 160 3.6 5.4 6.7 2.5 11.0 12.0 6.5 23.2 Poisson's Ratio 0.33 0.34 0.34 0.29 0.31 0.30 0.34 0.28

The performance of a structural element is determined by the properties of the material the geometry functional requirements the microstructure

MIME2204–ENGINEERING MATERIALS

MIME2204– ENGINEERING MATERIALS

A wood composite was created to enhance the property of the common wood (control). Both samples underwent compression loading test. The result is shown in the accompanying figure. Which of the statement below is true? The elasticity of the wood composite is far better than the control The wood composite exhibit better resistance against deformation The wood composites showed a deformation behavior generally similar to that of untreated wood. After the yield point the composites showed an initially abrupt and then steady decrease in compressive stresS All of the above

During the selection of material, the availability of material is not an important factor. Select one: O True O False e ngineering Materials- Assignment Jump to..

Engng INT KO Ninun ADT Weg C 0.01 03 Densty, o Mo) From the chart above (also in notes) which materials would be the optimal choice for a helicopter blade Sic Steel Carbon Fibre Composite Titanium ungs Modulus E OPe

Not every recyclable material can be recycled efficiently. VWhich one below may not be one of the reasons for this? * In the case of widely distributed scrap, material contained in discarded products has to be collected, separated, and cleaned so that the economics is in the play. Some materials consist of large amount of impurities that the recycled materials cannot be used in place of a virgin material because of deterioration in material properties. Some materials cannot be separated from each other easily, i.e., fiber composites. The energy and emissions are higher for recycling processes of some materials than that of initial processes, and therefore, recycling may not be preferred depending on the material type.

For an application of high strength components including gears cams and rollers the desired properties in a plastic would be high tensile and impact strength, stability at high temperature, and machine ability. Potential materials which are suitable for these applications are nylon phenolics, TFE filled acetals, PET, and poly carbonate. True or false.

The design of an aircraft fuselage skin requires sufficient strength and stiffness in both the longitudinal and hoop direction. Based on this information alone, which of the following material options would be the best option? A) Aluminum 2024-T3  B) Unidirectional glass/epoxy laminate      Which of the statements below on the Euler buckling load is correct? A) If the axial load increases, the Euler buckling load will go up. B) If the axial load decreases, the Euler buckling load will go up. C) If the lateral load increases, the Euler buckling load will go up. D) If the lateral load decreases, the Euler buckling load will go up.   Is the following statement true or false: A structure does not need to break (ie: fracture) in order to fail.   Select whether the following statement is true or false: Structural safety is solely the responsibility of the aircraft manufacturer and the airworthiness authorities.   Select whether the following statement is true or false: Damage tolerance is…

a) A climber relies on a safety rope swing hung from a large cliff face. The diameter of the polyamide rope is 8.5 mm and the tensile strength of bulk polyamide is quoted as 138 MPa. Calculate the maximum size of person in kilograms that could utilise the rope, if a factor of safety of 6.2 is to be assumed. b) A ladder of length 5 m is resting against a smooth wall, its point of contact being just below a first floor window. The bottom of the ladder rests on the ground and the coefficient of friction between the ladder and the ground is 0.3. A person of mass 75 kg climbs the ladder, which has a mass of 4 kg. The bottom of the ladder is at the point of slipping, outward from the wallI, just as the person reaches the mid-point of the ladder's length.

Topic: Nonconcurrent, Nonparallel Forces

The tensile strength and number-average molecular weight for two poly(methyl methacrylate) materials are as follows: Tensile Strength (MPa) Number-Average Molecular Weight (g/mol) 66 30,000 160 50,000 Estimate the tensile strength (MPa) at a number-average molecular weight of 34,000 g/mol. Express your answer three significant figures. Answer:

Braced airplane in equilibrium (steady flight). There is distributed lift load on each wing. What method can be followed to calculate the height of the distributed load? Thank you in advance,