Airbus Cargo Drone Challenge Frame Sheet














[Insert Participant Name(s) here]

Version .............................................................................................................................................................................................................. V 1.00







Last Update ................................................................................................................................................................................................ 01.04.2016
















Green cells are calculated by formulars or are given (not changeable) requirement values












White cells are specific to the design entry; mandatory to be filled out by the participant as delivery item












Blue cells are optional delivery items












Aircraft Data:
















Aircraft name : Air Nurse




















General Requierements
















Description

Symbol Value Unit Comment










Maximum Take-Off Mass

mMTOM = 25,0 kg Shall stay below 25 kg

Air Density

r= 0,954 kg/m @ 2000m MSL and ISA+20C




























Geometry Data:
















Description

Symbol Value Unit Comment










Wing Span

b = 2,75 m


Aspect Ratio

AR = 10,5769230769 -


Wing Area

Sref = 0,715 m


Wing Loading (fixed wing mode)

m/Sref = 33 kg/m 10 - 30 kg/m recommendation

Disc Loading (rotor disc)

m/Sprop Lift = 31,25 kg/m 10 - 50 kg/m recommendation

Lift Propeller Area per Lift Propeller

Sprop Lift = 0,200 m


Lift Propeller Diameter

Dprop Lift = 0,505 m


Cruise Propeller Diameter

Dprop Cruise = 0,3 m


Cruise Propeller Area per Cruise Propeller

Sprop Cruise = 0,07 m


Number of Propeller for Hover

npropeller,hover = 4 -


Number of Propeller for Cruise

npropeller,cruise = 1 -


Fuselage Length

Lfuselage= 1,8 m


Fuselage Diameter (max. Diameter)

Dfuselage= 0,3 m











Vertical Tail Surface

Svertical tail = 0,0385 m


Vertical Tail Leaver Arm to CoG

lvertical tail = 1,1 m


Horizontal Tail/Canard Surface

Shorizontal tail = 0,0385 m


Horizontal Tail/Canard Leaver Arm to CoG

lhorizontal tail = 1,1 m


Control Curface Area for Pitch

Scontrol,pitch = 0,01925 m


Control Surface Leaver Arm to CoG for Pitch

lcontrol,pitch = 1,1 m


Control Surface Area for Roll

Scontrol,roll = 0,052 m


Control Surface Leaver Arm to CoG for Roll

lcontrol,roll = 0,55 m


Control Surface Area for Yaw

Scontrol,yaw = 0,01925 m


Control Surface Leaver Arm to CoG for Yaw

lcontrol,yaw = 1,1 m




















Mass and Balance Data:
















Description

Symbol Value Unit Comment










Structural Mass (wing, fuselage, empenage, nacelles, )

mstruct = 5 kg


Avionics Mass (see ignition kit)

mavionics = 3,4 kg


Flight Control Actuation

mactuation = 0,55 kg


Electric Motors and Controllers Mass (for hover)

mmotors,hover = 1,7 kg


Electric Motors and Controllers Mass (for cruise)

mmotors,cruise = 0,3 kg


Propellers Mass (for hover)

mpropeller,hover = 0,5 kg


Propellers Mass (for cruise)

mpropeller,cruise = 0,1 kg


Battery Mass

mbattery = 6,420 kg


Additional Mass for Installations

minstalltions = 1 kg mass for wiring, installations, etc.

Empty Mass
mempty = 18,970 kg











Payload Mass

mPayload = mMTOM - mempty = 6,03 kg











Center of gravity location
















x-location

xCoG = 0,73 m


y-location

yCoG = 0 m


z-location

zCoG = 0,3 m




















Efficiencies:
















Description

Symbol Value Unit Comment










Efficiencies for Hover Flight
















Electrical Motor Efficiency (incl. Motor controller efficiency)

helect. motor = 88%



Figure of Merit

FOM = 0,6 -


Battery Efficiency

hbattery = 97%



Power Management and Distribution Efficiency

hPMAD = 99%












Efficiencies for Cruise Flight
















Electrical Motor Efficiency (incl. Motor controller efficiency)

helect. motor = 88%



Propeller Efficiency

hpropeller = 82%



Battery Efficiency

hbattery = 97%



Power Management and Distribution Efficiency

hPMAD = 99%





















Aerodynamics:
















Description

Symbol Value Unit Comment










Oswald Factor

e = 0,88 -


Zero Lift Drag Coefficient

CD0= 0,03 -


Cruise Lift Coefficient

CL Cruise= 0,92 -


Induced Drag Coefficient

CDi Cruise= 0,03 -


Lift to Drag Ratio

L/DCruise = 15,61 -


Static Margin

SM = 10%





















Component specific Energy:
















Description

Symbol Value Unit Comment










Battery Specific Energy

wbattery = 140,0 Wh/kg




















Aircraft Range Performance Estimation:
















Description

Symbol Value Unit Comment










Required Cruise Thrust

Tcruise = 15,7 N


Cruise Speed

vcruise = 28,0 m/s


Range

drange = 60,0 km


Required Cruise Power

Pcruise = 633,5 W


Hover nz

nz= 1,1 -


Required Hover Power

Phover = 6730,3 W


Required Power for Avionics

PAvionics = 91,0 W


Cruise Time

tcruise = 40,7 min including 5 min reserve

Hover Time

thover = 2,0 min 2 min Hover time is required

Battery Energy

Ebattery = 719,0 Wh