Module 5
Mission Definition
Configuration: Quadrotor VTOL
Payload mass W = 1.2 kg
Hover time t = 25 min = 0.417 hr
Design safety margin
Sea-level operation
Battery type: Li-Po
Hover T/W = 2.0 (safe VTOL design)
Initial MTOW Assumption
MTOW = Wpayload + Wbattery+avionics + Wstructural
MTOW ≈ Wpayload /[1 − (βbattery+avionics + βstructural)]
Where represents the weight fraction of those components (typically 0.3 for battery and 0.25 for structure in Li-Po VTOLs).
VTOL MTOW Calculator
VTOL MTOW Calculator
Estimated MTOW:
8.50 kg
Drone Aerodynamic Calculator and Live Graphs
Lift Calculator
Drag Calculator
Typical Mission Parameters
Payload mass (e.g., camera, sensors): 0.4–2 kg
Endurance: 1–6 hours
Range: 20–300 km
Cruise speed: 15–35 m/s
Operating altitude: 300–3000 m
Take-off & landing: Hand-launch / Runway / Catapult
Environment: Day/Night, Wind tolerance
Conceptual Design
Initial configuration selection.
High-wing → Stability, surveillance missions
Low-wing → High speed, aerobatic UAVs
T-tail / Conventional tail / V-tail
Tractor vs Pusher propulsion
Recommended for surveillance: High-wing, tractor propeller, conventional tail
Weight Estimation
The total take-off weight of a fixed-wing UAV is determined through an iterative estimation process, as several components depend on each other during the design phase. The overall weight (MTOW) is expressed as the sum of the structural weight, propulsion system weight, avionics weight, payload weight, and battery weight.
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Materials and Structural Design
The selection of materials for the fixed-wing UAV is based on achieving an optimal balance between strength, stiffness, weight, and manufacturability. The wing structure is typically constructed using balsa wood reinforced with a carbon fiber spar, providing adequate bending strength while maintaining low weight. The fuselage is commonly fabricated from EPO foam or fiberglass, which offers good impact resistance and ease of integration for onboard components. A carbon fiber tube is used as the primary spar due to its high strength-to-weight ratio and excellent fatigue resistance. The outer skin of the aircraft is covered using Oracover film or foam, which enhances aerodynamic smoothness and provides environmental protection.