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1. A component in an aircraft flap actuator, shown in Figure 1, can be adequately modelled as a cylindrical bar subjected to a compressive axial force of 8 kN, a bending moment of 55 Nm and a torque of 30 Nm. It is to be manufactured of a 20 mm diameter solid bar of 7075-T6 aluminium alloy. FLAP ACTUATOR POWER SCREW JACK CARRIAGE (c) BALL NUT FLAP NOSE HOLLE (0) BEAN FITTING CARRIAGE ROLLER Figure 1: Aircraft Flap Actuator (a) At a critical point on the bar surface, determine the value of the, (1) compressive direct stress, (ii) tensile bending stress, and (iii) shear stress. COLLAPSIRE DOOK (b) Indicate on a representative element in 2-D cartesian coordinates the stresses calculated in (a). Determine the principal stresses and the maximum shear stress at the point. (d) Sketch the Mohr's stress circle representing the stress system and clearly mark on it the principal stress values calculated in (c) above and the direction (angle) of the maximum principal stress (0₁) with respect to axial (x) direction. (Note: Only a free hand sketch is required). Discuss how 'stress transformation leads to the identification of a material with suitable structural strength for the manufacture of the component modelled as a shaft; briefly explain the procedure that you would follow.

1. A component in an aircraft flap actuator, shown in Figure 1, can be adequately modelled as a cylindrical bar subjected to a compressive axial force of 8 kN, a bending moment of 55 Nm and a torque of 30 Nm. It is to be manufactured of a 20 mm diameter solid bar of 7075-T6 aluminium alloy. FLAP ACTUATOR POWER SCREW JACK CARRIAGE (c) BALL NUT FLAP NOSE HOLLE (0) BEAN FITTING CARRIAGE ROLLER Figure 1: Aircraft Flap Actuator (a) At a critical point on the bar surface, determine the value of the, (1) compressive direct stress, (ii) tensile bending stress, and (iii) shear stress. COLLAPSIRE DOOK (b) Indicate on a representative element in 2-D cartesian coordinates the stresses calculated in (a). Determine the principal stresses and the maximum shear stress at the point. (d) Sketch the Mohr's stress circle representing the stress system and clearly mark on it the principal stress values calculated in (c) above and the direction (angle) of the maximum principal stress (0₁) with respect to axial (x) direction. (Note: Only a free hand sketch is required). Discuss how 'stress transformation leads to the identification of a material with suitable structural strength for the manufacture of the component modelled as a shaft; briefly explain the procedure that you would follow.

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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1. A component in an aircraft flap actuator, shown in Figure 1, can be adequately modelled as a cylindrical bar subjected to a compressive axial force of 8 kN, a bending moment of 55 Nm and a torque of 30 Nm. It is to be manufactured of a 20 mm diameter solid bar of 7075-T6 aluminium alloy. FLAP ACTUATOR (a) (b) (c) (d) (e) POWER SCHEW JACK CARRIAGE -FAPERON BALL NUT FLAP NOSE ROLLER BEAM FITTING CARRIAGE ROLLER -COLLAPSIBLE DOOK Figure 1: Aircraft Flap Actuator At a critical point on the bar surface, determine the value of the, (1) compressive direct stress, (ii) (iii) tensile bending stress, and shear stress. Indicate on a representative element in 2-D cartesian coordinates the stresses calculated in (a). Determine the principal stresses and the maximum shear stress at the point. Sketch the Mohr's stress circle representing the stress system and clearly mark on it the principal stress values calculated in (c) above and the direction (angle) of the maximum principal stress (0₁) with respect to axial (x) direction. (Note: Only a free hand sketch is required). Discuss how 'stress transformation' leads to the identification of a material with suitable structural strength for the manufacture of the component modelled as a shaft; briefly explain the procedure that you would follow.
Transcribed Image Text:1. A component in an aircraft flap actuator, shown in Figure 1, can be adequately modelled as a cylindrical bar subjected to a compressive axial force of 8 kN, a bending moment of 55 Nm and a torque of 30 Nm. It is to be manufactured of a 20 mm diameter solid bar of 7075-T6 aluminium alloy. FLAP ACTUATOR (a) (b) (c) (d) (e) POWER SCHEW JACK CARRIAGE -FAPERON BALL NUT FLAP NOSE ROLLER BEAM FITTING CARRIAGE ROLLER -COLLAPSIBLE DOOK Figure 1: Aircraft Flap Actuator At a critical point on the bar surface, determine the value of the, (1) compressive direct stress, (ii) (iii) tensile bending stress, and shear stress. Indicate on a representative element in 2-D cartesian coordinates the stresses calculated in (a). Determine the principal stresses and the maximum shear stress at the point. Sketch the Mohr's stress circle representing the stress system and clearly mark on it the principal stress values calculated in (c) above and the direction (angle) of the maximum principal stress (0₁) with respect to axial (x) direction. (Note: Only a free hand sketch is required). Discuss how 'stress transformation' leads to the identification of a material with suitable structural strength for the manufacture of the component modelled as a shaft; briefly explain the procedure that you would follow.
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