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) (ii) POWER SCHEW JACK CARRIAGE (iii) -FLAPERON BALL NUT FLAP NOSE ROLLER -Flap actuator. Figure 1 At a point on the shaft surface, determine the value of the, (1) compressive stress, shear stress. BEAM FITTING CARRIAGE ROLLER bending stress, and -COLLAPSIBLE DOCK Indicate on a representative element in 2-D Cartesian Coordinates the stresses calculated in (a). Determine the principal stresses at the point.

Shown below is a horizontal beam that is fixed at the left end and is cyclically operated at the right end by a vertical actuator that deflects it 3 mm up and 10 mm down, both from the horizontal position. The frequency of cycling is 2 Hz. The beam is 250 mm long and has a rectangular cross section of 20 mm width. The beam's material is a steel with Sut = 440 MPa, Syt = 370 MPa, and a fully modified Se = 250 MPa. %3D %3D (a) Using a factor of safety of 1.5, determine the thickness of the beam (h) for a life of 1,000 hours. (b) Suppose a small hole of 4 mm diameter is drilled at the mid-width of the beam at a distance 150 mm from the left end. The beam thickness is the same as that determined in Part (a). Can the beam survive 1,000 cycles of cyclic operation now? Justify your answer with calculations. h 250 mm Actuator

A (25 kW, 500 rpm) motor has a mild steel shaft of (30 mm) diameter and (8 cm) length. There are two parallel keys available A (w = 12 mm, t = 10 mm) and B (w = 10 mm, t = 8 mm), suggest one of them to connect the shaft with a pulley. use torsional shear stress = 160 MPa, tensile strength = 400 MPa, compression strength=280 MPa, bending strength= 380, factor of safety=3. Hello, I need an accurate handwritten answer in 15 minutes, please

Solve part C