Design variables, design parameters, component technology factors, constraints and weight breakdown in the main sheet
| Design variables | Constraints | Current value | Feasibility criterion | ||
|---|---|---|---|---|---|
| Wing span | 32.86 | m | Power margin | 0.000000 | >0 |
| Aspect ratio | 24.00 | – | Energy margin | 0.622854 | >0 |
| Wing area | 45.00 | m2 | Night time energy margin | 0.000000 | >0 |
| Power available | 0.87 | kW | Cruise CL margin | 0.641136 | >0 |
| Fuel cell energy available | 10.64 | kWh | |||
| Cruise speed | 10.66 | m/s | |||
| Empty weight | 76.2 | kg | |||
| Design parameters | Design parameters | ||||
| Total weight | 165.06 | kg | Solar cells | 22.4 | kg |
| Solar cell fill factor(Sff) | 0.828 | Motor + propeller | 3.9 | kg | |
| Payload power (Ppl) | 360 | W | RFC system | 22.6 | kg |
| Payload mass | 40 | kg | Avionics | 0.0 | kg |
| Avionics system mass | 0 | kg | Payload | 40.0 | kg |
| Maximum allowable CL @ Cruise | 1.5 | – | |||
| Component technology factor | |||||
| Solar cell efficiency | 0.19 | – | RFC specific energy | 470 | Wh/kg |
| Solar cell-specific mass | 0.6 | kg/m2 | Fuel cell efficiency | 0.6 | – |
| Propeller efficiency @ Cruise | 0.83 | – | Electrolyzer efficiency | 0.7 | – |
| Electric motor/prop specific power | 0.0443 | Round trip efficiency | 0.42 | ||
| Electric motor efficiency | 0.9 | Airframe weight adjustment factor | 1 | ||
| Design variables | Constraints | Current value | Feasibility criterion | ||
|---|---|---|---|---|---|
| 32.86 | m | Power margin | 0.000000 | >0 | |
| 24.00 | – | Energy margin | 0.622854 | >0 | |
| 45.00 | Night time energy margin | 0.000000 | >0 | ||
| 0.87 | kW | Cruise CL margin | 0.641136 | >0 | |
| 10.64 | kWh | ||||
| 10.66 | m/s | ||||
| 76.2 | kg | ||||
| Design parameters | |||||
| 165.06 | kg | Solar cells | 22.4 | kg | |
| 0.828 | Motor + propeller | 3.9 | kg | ||
| 360 | W | RFC system | 22.6 | kg | |
| 40 | kg | Avionics | 0.0 | kg | |
| 0 | kg | Payload | 40.0 | kg | |
| 1.5 | – | ||||
| 0.19 | – | RFC specific energy | 470 | ||
| 0.6 | Fuel cell efficiency | 0.6 | – | ||
| 0.83 | – | Electrolyzer efficiency | 0.7 | – | |
| 0.0443 | Round trip efficiency | 0.42 | |||
| 0.9 | Airframe weight adjustment factor | 1 | |||
Notes:
Airframe weight calculation method 1: Heliplat; 2: Calibrated regression; 3: HPA (Human powered aircraft); 4: Regression method 2; and 5: Stender
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