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Posted By: sai yeshwanth Member Level: Bronze Posted Date: 11 Jun 2008
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2007 Jawaharlal Nehru Technological University B.Tech B.Tech II Semester Supplimentary Examinations, Aug/Sep 2007 AIRCRAFT STRUCTURES-II (Aeronautical Engineering) Question paper
Code No: RR322102
Set No. 1
III B.Tech II Semester Supplimentary Examinations, Aug/Sep 2007 AIRCRAFT STRUCTURES-II (Aeronautical Engineering) Time: 3 hours Max Marks: 80 Answer any FIVE Questions All Questions carry equal marks ????? 1. Derive the Equation for principle moment of inertia for unsymmetrical section about both axes. If Ix ,Iy are M.I. about the centroidal axes and Ixy is product of inertia. [16] 2. A channel section is subjected to a shear of 20kN. Determine the shear ?ow at points B,C,D and plot the shear ?ow variation throughout the cross-section. Also calculate the resultant force in each region of the cross-section. Shown in ?gure 2. [16]
Figure 2 3. Locate Shear Centre. Assume uniform thickness. Shown in ?gure 3. [16]
Figure 3 4. Derive the Bredt- Batho formula related to torsion. What are the assumptions made? [16]
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Code No: RR322102
Set No. 1
5. Thickness uniform locate the Shear Centre for the two compartment box beam t = 10mm, b = 500mm. Also draw the shear ?ow variation. Shown in ?gure 5. [16]
Figure 5 6. The sheet stringer panel 250 x 300 x 1 mm, shown in ?gure 6. is loaded in compression on the 300 mm side by means of rigid members. The sheet is assumed to be simply supported at the loaded ends and at the rivet lines and to be free at the sides. Each stringer has an area of 65mm2 . Find total compressive load P for the following conditions. (a) When the sheet ?rst buckles. (b) When the structure stress FC is 7000N/cm2 . [16]
Figure 6 7. What are the various functions of structural components? 8. Write short notes on the following: (a) Types of riveted joints (b) Rivet failures. ????? [16] [16]
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Code No: RR322102
Set No. 2
III B.Tech II Semester Supplimentary Examinations, Aug/Sep 2007 AIRCRAFT STRUCTURES-II (Aeronautical Engineering) Time: 3 hours Max Marks: 80 Answer any FIVE Questions All Questions carry equal marks ????? 1. For the z-sectia Determine Iz , Iy , Ixy . Determine the principal M.I and locate the orientation of the NA. thickness uniform t =12mm as Shown in Figure1. [16]
Figure 1 2. A steel-wide ?ange beam is subjected to a shear of F = 80kN. Plot the shear stress distribution acting over the beams cross-sectional area. Also Determine the shear force resisted by the web. The thickness, t = 20mm uniform. Shown in ?gure 6. [16]
Figure 6 3. A cross-section in the shape of a circular arc of uniform thickness is subtending an angle ß from either side of the symmetrical axis. Shown in ?gure 3 That Shear [16] Centre e = 2R(sin ß-B cos ß) . B-sin ß cos ß
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Code No: RR322102
Set No. 2
Figure 3 4. (a) Explain Bredth Batho theory (b) A thin tube is made from 5mm thick A- 36 steel plates such that it has crosssection of equilateral triangle of side 90mm.
Figure 4b Determine the Max. torque T to which it can be subjected, if the allowable shear stress is 90MPa and the tube is restricted to twist no more than 2 x 10-3 radians. The length of the tube is 3m. G = 75 x 109 N/m2 . Shown in ?gure 4b. [16] 5. Box beam of uniform thickness t = 3mm is subjected to a shear force of 20kN. Determine the variation of shear ?ow through out the cross-section. Shown in ?gure 7. [16]
Figure 7 6. The sheet stringer panel 250 x 300 x 1 mm, shown in ?gure 6. is loaded in compression on the 300 mm side by means of rigid members. The sheet is assumed to be simply supported at the loaded ends and at the rivet lines and to be free at the 2 of 3
Code No: RR322102
Set No. 2
sides. Each stringer has an area of 65mm2 . Find total compressive load P for the following conditions. (a) When the sheet ?rst buckles. (b) When the structure stress FC is 7000N/cm2 . [16]
Figure 6 7. The beam shown in the Figure 7. Is assumed to have a pure tension ?eld web. Plot the axial loads in the sti?eners and ?anges. Assume angle of tension diagonal a = 45. [16]
Figure 7 8. Write short notes on the following: (a) E?ective walls and ine?ective walls (b) Sheet wrinkling. ????? [16]
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Code No: RR322102
Set No. 3
III B.Tech II Semester Supplimentary Examinations, Aug/Sep 2007 AIRCRAFT STRUCTURES-II (Aeronautical Engineering) Time: 3 hours Max Marks: 80 Answer any FIVE Questions All Questions carry equal marks ????? 1. An axial compressive load P is acting at pt A ? Lr to yz plane. Derive the Equation for bending stress at the four perpendicular. Corners and specify the nature of stresses. Identify the location for Max. tensile and compressive stresses. Shown in ?gure 1. [16]
Figure 1 2. Explain the concept of Shear Stresses in thick beams with the help of neat sketch and draw the shear stress Variation (a) Rectangular section (b) Circular section. 3. Locate the Shear Centre. The thickness is uniform. Shown in ?gure 3. [8+8] [16]
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Code No: RR322102
Set No. 3
Figure 3 4. A Torque of T = 3 kNm is applied to the torsion member whose cross-sectia in shown in ?gure 4. With uniform thickness t = 5 mm. Determine the, maximum Shear Stress in the member and the angle of twist per unit length. calculate the total strain energy stored. [16]
Figure 4 5. A thin walled Box beam is use in the support structure of an aeroplane wing. Locate its shear centre. Shown in ?gure 5. [16]
Figure 5 2 of 4
Code No: RR322102
Set No. 3
6. Find crippling stress for the two channel shown in ?gure 6a and Figure 6b when formed of following material using Gerard’s method. (All dimensions are in mm). (a) AISI 4130 Stel Heat treated to Ftu=120N/mm2 (b) 7075-T6 Aluminum alloy. [16]
Figure 6a
Figure 6b 7. The fuselage of light weight passenger carrying aircraft has the circular cross section shown. The cross-sectional area of each stringer is 100 mm2 and is subjected to transverse shear load of 100 KN. Calculate the distribution of shear ?ow in the section and sketch the shear ?ow distribution? Shown in ?gure 7. [16]
Figure 7 8. Write short notes on the following:
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Code No: RR322102 (a) Moment of inertia (b) Product of inertia. ?????
Set No. 3
[16]
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Code No: RR322102
Set No. 4
III B.Tech II Semester Supplimentary Examinations, Aug/Sep 2007 AIRCRAFT STRUCTURES-II (Aeronautical Engineering) Time: 3 hours Max Marks: 80 Answer any FIVE Questions All Questions carry equal marks ????? 1. An axial compressive load P is acting at pt A ? Lr to yz plane. Derive the Equation for bending stress at the four perpendicular. Corners and specify the nature of stresses. Identify the location for Max. tensile and compressive stresses. Shown in ?gure 1. [16]
Figure 1 2. Derive the equation for shear ?ow in the ?ange and web of thin walled I-section. Plot the shear ?ow variation. [16] 3. Explain what do you mean by e?ective wall and ine?ective wall related to beams. De?ne boom show composite beams with boom, ?anges and webs. [16] 4. A hexagonal tube is subjected to a torque of 150 N-m. Determine the mean dimension ‘a’ of its sides. If the allowable Shear Stress is talla = 60MPa. Each side is having uniform thickness t = 3mm. Determine the Max. angle of twist possible, if it is made of Aluminum, G = 26 Gpa. Shown in ?gure 4. [16]
Figure 4 5. Explain the procedure of ?nding shear ?ow in symmetric closed section, and location of shear centre for both single and multicell sections. [16]
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Code No: RR322102
Set No. 4
6. The sheet stringer panel 250 x 300 x 1 mm, shown in ?gure 6. is loaded in compression on the 300 mm side by means of rigid members. The sheet is assumed to be simply supported at the loaded ends and at the rivet lines and to be free at the sides. Each stringer has an area of 65mm2 . Find total compressive load P for the following conditions. (a) When the sheet ?rst buckles. (b) When the structure stress FC is 7000N/cm2 . [16]
Figure 6 7. Explain in detail the stresses in the fuselage components due to air loads? 8. Write short notes on the following: (a) stringers (b) bulk heads (c) ?oor beams (d) spar webs. ????? [16] [16]
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