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• Q1: What is the volume of a sphere whose radius is 15.41?See Answer
• Q2:doing research on the F-35 fighter program to discuss the design, logistics, and maintenance features of the new F-35 fighter. With the new design requirement approach, what kind of advantage(s) & disadvantage(s) do the F-35 fighter program gain in future logistics and maintenance operations (compared to current available fighter programs)? Why the program is significantly over budget now and what should be done from logistics point of view to improve the situation? Also discuss the potential influence of COVID-19 pandemic situation to the F-35 supply chain.See Answer
• Q3:In House Assessment- Mechanica Figure 1: AC-101 Aircraft Design The AC-101 aircraft has been developed as a multi-purpose aircraft with the following specifications: Cruise Altitude Maximum Altitude Empty Weight Maximum Take-Off Weight Range Maximum Take-off Roll Maximum Deceleration under Braking Minimum Landing Roll Cruise Velocity Maximum Velocity Maximum Structural Loading i. Wheel locations ii. Wheel installation and fixation arrangement iii. Suitable bearing arrangement RESTRICTED 700m AMSL 1500m AMSL Revision: 1 40 kg 50 kg 150km 200 m 0.8g 1. Problem 1 aircraft consists of a standard tricycle landing gear arrangement for which the front landing gear needs to be detailed. on the layout given in Figure 2, determine: a. The maximum load on the front landing gear module. b. A suitable diameter and material for the Front Landing Gear Axle. C. Given the Wheels specified in Figure 3, propose a suitable design for the axle. Include at least the following: 10 m. 140km/h 160 km/h Vertical: -3g/+5g Lateral: -1.5g/+1.5g Axial: -1g/+1.5g/nMo 62mm 70mm KAGRISD 550mm 35mm 64mm Figure 2: AC-101 Landing Gear Arrangement Aluminium hub rubber wheels 735mm New Aluminium hub rubber wheel SIZE 5.00 - AL 1050mm CNC Aluminium hub rubber wheels Dis Dimm 127 RESTRICTED Figure 3: Front Wheel Specification 02 REMARKSee Answer
• Q4:2. Problem 2 For the Front Landing Gear Module, it is specified that a spring is required to soften the wheel forces transmitted to the aircraft. The only location for this spring has been identified as indicated in green in Figure 4 with the following restriction and conditions: SEE DETAIL A- Static Length (L) Minimum Length (L_min) 80mm 30 mm 20 DETAIL A SCALE 1:1 Figure 4: Front Landing Gear Module Spring Position a. Design a suitable spring which is able to cater for all loading conditions.See Answer
• Q5:Need to make a Report in 2 pages APA format + PPT of two slides Topic is: The International Civil Aviation Organization Explanation of the following Annexes (6,8,13,16) related to airworthiness - u can refer to the ICAO website and the chapter 3.1 of the book - U can add pictures tables diagrams The ppt is related to the report so the same thing but just in short form in the pptSee Answer
• Q6: An aircraft climbs at an angle of 15°. The weight of the aircraft is 108 kN and its wing area is 75m². The aircraft's drag equation is given by Cp = 0.035 + 0.025 C2. If the engines of the aircraft produce 45 kN of thrust during the climb what is the fastest equivalent airspeed the aircraft could be climbing at? The answer should have units of ms ¹.See Answer
• Q7: A glider weighs 47 kN and has a drag equation of CD = 0.026 +0.024 C2. What is the minimum glide angle of the glider? Your answer should be in degrees.See Answer
• Q8: The thrust required for a cargo aircraft to fly straight, level and steady was measured. In each measurement the speed and altitude of the aircraft was the same but the weight changed. When the weight was 130 kN, empty weight with no cargo and little fuel, the thrust required was T =18.7 kN. When the weight was 30 kN above the empty weight the thrust required increased by dT0.50 kN (Total thrust in this case is T+ dT kN). What (total) thrust would be required to fly at the same speed and altitude if the weight was 50 kN above the empty weight? The answer should have units of kN.See Answer

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