- A Simplified Aircraft Model Relating Airspeed V T M S With Thrust T T Nat Cruising Altitude Is Mi F V T Where M 1 (571.6 KiB) Viewed 56 times
- A Simplified Aircraft Model Relating Airspeed V T M S With Thrust T T Nat Cruising Altitude Is Mi F V T Where M 2 (91.21 KiB) Viewed 56 times
A simplified aircraft model relating airspeed v (t) m/s with thrust T (t) Nat cruising altitude is mi + F(v) = T where m is the mass of the aircraft, and the aerodynamic drag experienced by the aircraft at this altitude is F(v) = 0.45v². UCAV US AIR FORCE SP-X Suppose m = 27000 kg, vo - 250 m/s. Then we may find an appropriate value To for the thrust T under which we may linearise the aircraft model in the form of mô, + αδ. = δτ. Here d = v vo and dT = T - To. Provide the integer part of the coefficient a. a = a
In your hand written working, include the following explanations and steps: (1) Show how the value of To is calculated, and explain the reasoning behind your calculation. (2) Show the key working in deriving the value of a that you provided. (3) Suppose there is disturbance and the actual linearised model of the system dynamics is md₂ + ad₂ = ST + d. If you design a controller that should be able to have , tracking any constant reference r with zero steady-state error, what controller would you choose? Present a controller and explain why zero steady-state error is achieved.