Q3 Q4 In an aircraft hydraulic system, the actuation of a…

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Question Answered step-by-step Q3 Q4 In an aircraft hydraulic system, the actuation of a… Q3Image transcription textQuestion 3 (12 marks) The following are the general specifications foran Airbus A340-600 commercial jet aircraft, powered by four RollsRoyce Trent 556 engines: Wing area, S: 439.4 m Span, b:… Show more… Show more    Q4  In an aircraft hydraulic system, the actuation of a retract/extend actuator requires 5 litres of hydraulic fluid. Since this is a rapid process, an adiabatic change of state can be assumed. The gas pre-charge is to be 0.9 times the min working pressure.  Image transcription textPo Vo AV… Show moreA summary of the working parameters are provided below: Max working pressure: P2=201 bar Min working pressure: P1=101 bar Effective volume (Working Volume): ?V=5 litres Max working temp: Tmax= 45 deg C Min working temp: Tmin=25 deg C  i.Determine the gas precharge pressure at maximum ambient temperature.           ii.Determine the gas precharge pressure at minimum ambient temperature.           iii.Determine the ideal gas volume.                                                                      iv.Determine the adiabatic correction factor.                                                       v.Determine the real gas volume and state a suitable accumulator size by rounding up to the nearest whole number.      vi.Draw the P-V diagram, showing the three important stages of charge of an accumulator. Also indicate the working volume as well as V0 (Vreal), p1, p2 & p3 on the diagram.    Q5 The general specifications an executive jet transport aircraft itted with upgraded Pratt & Whitney PW 545 B] engines are as stated below:     Wing span, b                            = 17.2 m Wing area, S                            = 370 ft2 (33.75 m2) Height of wing above ground, h = 1.75 m Aircraft weight, W                   = 90 kN Power plants,  T(Available)                = 2 x 17.75 kN [PW 545 B] Reserve thrust                          = 20% of maximum available Fuel capacity                            = 4,000 litres Fuel density                             = 0.75 kg/litre Specific fuel consumption       = 0.06 kg of fuel/N (thrust)/hour Parasite drag coefficient, Cdp = 0.02 Oswald efficiency factor, ?      = 0.85 Friction coefficient, ?r            = 0.018 Aircraft Climbing at Mach Number  = M0.3 Using the above given data and based on Sea-Level Condition  Identify and calculate the following:  Aircraft Speed during Climb Lift Force during Climb Total Drag Force and Power required Rate of Climb Climb Angle Load Factor during the Climb  Engineering & Technology Mechanical Engineering EAS 105 Share QuestionEmailCopy link Comments (0)