sUAS Loading and Performance Flashcards

An sUAS is rated for a maximum structural load factor of 3G. During an aggressive banked turn, the effective load factor reaches 3.2G. What is the likely consequence?

Answer: Possible structural failure or component damage exceeding the design limit

Exceeding the rated structural load factor means forces on the airframe surpass the design limit, risking arm or frame failure, propeller separation, or other structural damage.

A remote pilot operates an sUAS on a cold winter day (temperature 10°F / -12°C). How does cold air density primarily affect rotor performance?

Answer: Increases lift efficiency because cold dense air provides better rotor thrust per unit of power

Cold air is denser than warm air, which improves rotor aerodynamic efficiency and thrust output; however, cold temperatures also reduce battery performance, which may offset the aerodynamic benefit.

When calculating density altitude at a field elevation of 2,000 ft MSL with temperature 15°F above standard, the pilot should expect the aircraft to perform as if it were at approximately:

Answer: Above 2,000 ft MSL because higher temperature increases density altitude

Temperature above standard increases density altitude above field elevation; the aircraft will perform as though it is at a higher altitude than the actual field elevation.

Which of the following best describes the relationship between sUAS payload weight and maximum flight time?

Answer: Flight time is inversely related to payload weight; heavier loads reduce endurance

Heavier payloads require more motor thrust to maintain altitude, consuming more battery power per unit time and reducing total flight endurance.

A remote pilot notices the sUAS drifts consistently to the left without control input. After checking for wind, the pilot suspects a loading issue. What is the most likely cause?

Answer: The left motors are spinning faster due to an asymmetric CG from off-center payload

Asymmetric payload placement shifts the CG laterally, forcing the flight controller to run motors on one side harder, which may manifest as a persistent drift and increased power consumption.

Under 14 CFR Part 107, an sUAS weighing more than 0.55 lbs must be registered. This weight is calculated as the aircraft's:

Answer: Total weight at takeoff, including battery and any installed payload

The 0.55-lb (250-gram) threshold is based on the total takeoff weight including the battery and any payload installed on the aircraft at the time of flight.

A remote pilot is planning a mission requiring maximum payload on a warm summer afternoon at a high-elevation site. What pre-mission action BEST ensures safe operations?

Answer: Calculate density altitude, verify the aircraft can hover with adequate power margin, and reduce payload if necessary

Calculating density altitude and verifying sufficient power margin (typically 20-30% motor headroom in hover) ensures the aircraft can safely operate before committing to flight with maximum payload.