Wing Lift Eficiency TRIZ Cases

Sensor-driven actuators adjust drag, lift, or torsion to damp rotor blade vibration and stabilize motion during mode changes.

Automatic engine-failure detection adjusts collective and pitch attitude to preserve rotor RPM and speed rotorcraft autorotation entry.

Automatic fly-by-wire autorotation entry maintains target rotor RPM after engine failure, improving response for low-inertia main rotors.

By calculating a braking start point, the aircraft stops its vertical rotor blade-aligned to cut drag, noise, and power use in forward flight.

A non-linear spring between the rotor system and airframe changes natural frequency during relative motion, limiting resonance buildup and catastrophic oscillation.

HHC targets higher harmonics while AVC handles residual loads, reducing actuator weight and improving rotorcraft ride quality.

Individual electrical actuators rotate blade cuffs on the rotor hub to control pitch, eliminating bulky swashplates that increase drag and weight.

Pivoting the tail rotor swashplate cants the rotation plane, directing downward thrust to improve pilot visibility without compromising hover stability.

A fuel cell unmanned air system routes heated exhaust air through wing flaps to increase lift and reduce drag.

Air conveying openings harmonize airflow across wing leading edge interruptions, resolving inharmonic lift distribution and drag penalties near engine pylons.

A hydraulic pitch link uses cam-based actuation to control individual rotor blades without redundant electrical systems.

Adjustable blade pitch angles and tip jets overcome retreating blade stall to achieve speeds exceeding 200 mph.

A micro-perforated wing leading edge enables boundary layer suction without complex internal chambers.

Replacing sliding bearings with composite flexbeams eliminates lubrication needs and wear for high-frequency rotor blade control.

Dual actuators move and rotate wing flaps independently, eliminating complex selection mechanisms that increase drag and damage risk.

A linear motor drives a flexible bladder via hydraulic units to actuate rotorcraft blades with high power density.

Hub-mounted actuators drive blade root and tip rotation through linkages, resolving weight and voltage constraints without altering aerodynamic contours.

Segmenting the rotor blade flap distributes centrifugal loads across multiple actuators, preventing failure and extending service life.

Core-integrated actuators adjust trim tab angles to resolve the trade-off between manufacturing flexibility and dynamic adaptability in rotary wing aircraft.

Removing springs from the fairing drive assembly reduces moving weight and manufacturing cost while preventing over-travel damage.

Roller-driven door covers flap openings without rigid fairings, reducing drag and noise while accommodating variable camber.