AEROSIM / OVERVIEW

Flight systems overview

MODEL CHECKS PASS
ACTIVE AIRCRAFTAquila U-8Lift + Cruise · 8 motors · model 0.2
PROFILE RANGE
379KM
MISSION DISTANCE
48.1KM
MISSION ENERGY
15.7KWH
END SOC
86.9%
LIVE MODELMODEL 0.2
Y↑X
FLIGHT TIME
29.5MIN
ENERGY / DISTANCE
0.326KWH/KM
HOVER BATTERY POWER
110.4KW
THRUST / WEIGHT
1.29RATIO
PHASE-DERIVED TELEMETRY

Mission timeline

AltitudeBattery SOC
Preparing phase telemetry…
VTOLCLIMBCRUISEDESCENTLAND
CONCEPTUAL CONSTRAINTS

Model checks

0constraints exceeded
Hover shaft powerPASS91.3 / 440.0 kW
Hover battery powerPASS110.4 / 400.0 kW
Required hover thrustPASS5,886.0 / 7,600.0 N
Calculated takeoff massPASS600.0 / 600.0 kg
Mission energyPASS15.7 / 96.0 kWh

Battery pack specific energy exceeds 400 Wh/kg; verify this user-defined assumption.

Conceptual simulation result. Passing model checks does not establish real-world feasibility or safety.

How was this calculated?Trace every displayed result to model inputs, equations, and assumptions.
MODEL VERSION0.2
INPUT HASHfnv1a-72441c47
SIMULATED9/8/2026, 4:53:25 PM
ASSUMPTIONS10
EMPTY MASS420 kg
CALCULATED MTOW600 kg
CRUISE BATTERY POWER26.2 kW
RESERVE MARGIN66.9%
Hover battery power110.4 kW
P_ideal = T^(3/2) / sqrt(2ρA)P_shaft = P_ideal / FMP_bus = P_shaft / (η_motor × η_inverter) + P_auxP_battery = P_bus / η_battery
Reference cruise power26.2 kW
CL = W / (qS)CD = CD0 + CL² / (πeAR)D = qSCDP_bus = P_shaft / (η_motor × η_inverter) + P_auxP_battery = P_bus / η_battery
Mission energy15.69 kWh
E = P_battery × tSOC_end = SOC_start - E / E_nameplate × 100
Profile range379.5 km
R = d_noncruise + (E_budget - E_noncruise) / (E_cruise / d_cruise)

Phase energy breakdown

PhaseTimeDistanceBattery powerEnergyEnd SOC
VTOL1.00 min0.00 km110.4 kW1.84 kWh98.5%
CLIMB1.67 min2.44 km61.9 kW1.72 kWh97.0%
CRUISE23.33 min42.00 km26.2 kW10.18 kWh88.6%
DESCENT2.50 min3.67 km2.6 kW0.11 kWh88.5%
LAND1.00 min0.00 km110.4 kW1.84 kWh86.9%

Active assumptions

  1. v02.environment.user-densityAir density is supplied by the aircraft environment and remains constant for the mission.
  2. v02.phase.steady-stateEach mission phase is treated as a steady operating condition; transitions are omitted.
  3. v02.hover.uniform-inflowHover induced power uses uniform actuator-disk momentum theory.
  4. v02.hover.figure-of-meritA user-supplied figure of merit corrects ideal induced power to rotor shaft power.
  5. v02.hover.profile-power-implicitRotor profile and installation losses are represented only through figure of merit.
  6. v02.aero.parabolic-polarWing-borne flight uses CD = CD0 + CL²/(πeAR).
  7. v02.climb.excess-powerClimb adds m × g × vertical rate to drag power.
  8. v02.descent.no-regenerationDescent propulsive power cannot be negative; regenerative energy is not credited.
  9. v02.battery.no-thermal-modelBattery voltage sag, temperature, C-rate derating and thermal behavior are omitted.
  10. v02.range.fixed-profileRange extends the simulated cruise profile after reserving energy for non-cruise phases.
DESIGN LIBRARY

Concept fleet

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Engineering snapshot readyInputs, assumptions, model 0.2, phase results and limitations.