1. Improved sizing (weight estimation) by using matlab code which was used in initial sizing
ye ppt me nahin aayega
Engine start, warm-up, taxi -
15 min at idle power,wf = (15/60 hr)*fuel consumption at ideal power,fuel cunsumtion at ideal power --- propulsion
Takeoff -1.devide takeoff in small segment and devide by the avg. velocity2. fuel burnt = CT(d/V)
Climb and accnprevious energy methods of emperical formulaUsing avg. D/T by propulsioncruise height,V,g
Cruise and loiter-Emperical formulaR=range(L/D)cruise= AerodynamicsDescentEmperical formula = Cd0,W/S,K,V,roh,T/W,
Landing wi/wi-1=0.997
Required Parameter
Fuel comsuption rate = C, D/T,
L/D, Cd0, W/S, K, roh, V, T/W, E(endurance time for loiter)
Avg velocity and distance during take off segments,(done in initial sizing)
Sizing matrix plot
vary w/s (plus and minus) 20%
vary T/W (plus and minus) 20%
Each combination will produce diff. aeroplane the one with min. w0 and satisfying all the requirement will be final design (cruise, takeoff, climb, missed approach)
(By RDS, software from net and matlab code)
Carpet Plot (By RDS
Same but another representation of sizing matrix
Trade studies
Requirement trade studies
Cruise is our deciding factor of w/s so change -
1. cruise speed,
2. fuselage diameter or (aisle width) because it is very large
3. Second stage climb is our deciding factor of T/w so what variation does it can have
4. No trade studies for tail.
Aerodynamics (wing)
5. t/c and lamda
6. Airfoil shape and camber
7. A and lambda
Structure
Materials - composite %
Payload
Sensitivity
aircraft operating cost and fuel price
aircraft operating cost and sfc