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# (Solved): 1) Calculate the unreliability Q_(D1) of the servo controller at 400 flying hours, and thus find th ...

1) Calculate the unreliability

`Q_(D1)`

of the servo controller at 400 flying hours, and thus find the reliability

`R_(comp )`

of the parallel servo controller subsystem of Mod 2 at 400 hours. 2) please calculate the reliability

`R_(S)`

of the ACTS for each option, Mod 1, Mod 2, and Mod 3 at 10 hours and 400 hours. Additionally, please explain why it is not possible to convert the falue for Mod 2 to time-independent values of MTBF for the system. 3) if the servo controller can be improved by

`80%`

in MTBF, will the resulting increase in the reliability of the Mod 1 system be enough to eliminate the need for redundant elements at either 10 hours or 400 hours? (i.e. do you think the reliability of the Mod 1 system with the improved compensator will be significantly higher than that of the Mod 2 or Mod 3 systems with the standard servo controller, to the point where the disadvantages of using redundant elements can be overcome?) You need to identify and consider the drawbacks of using redundant elements, not just the numbers produced in the calculation. 4) choosing Mod2 modification of the ACTS, complete a detailed Fault Tree Analysis of the ACTS. 5)discuss the advantages and disadvantages of incorporating redundant elements in the above component of a combat aircraft. Please compare this approach with the benefits, drawbacks, and costs of creating a mature product that enhances the reliability of components to an extent that eliminates the need for redundancy. Component and Failure rate per million flying hours : Power supply =217.04 HUD Interface Unit = 97.45 Servo Controller =554.53 Elevation Servo Actuator = 60.06 Azimuth Servo Actuator =130.83 Amunition Feed System =86.61 ECU =11.62 Recoil System =212.22 Temperature Sensor =80.94 Airspeed Sensor =94.55 Balistic Load Sensor =140.44

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