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.

Linear actuators pseudo-sinusoidally adjust blade pitch for rapid thrust vectoring, resolving the trade-off between control speed and device complexity.

A flow director varies exhaust stream attachment to the fuselage, resolving directional control limitations during short take-off and landing maneuvers.

Replacing hydraulic dampers, electro-mechanical actuators enable active lead-lag control to enhance rotor stability and cut maintenance.

Flexible drive tapes transmit motion from linear actuators to flap mechanisms, eliminating mechanical backlash and reducing vibration in rotor blades.

Distributed magnetostrictive pumps eliminate swash plates, reducing vibration and noise while increasing stroke precision.

Individual blade control systems eliminate heavy swashplates, reducing weight and complexity while improving reliability.

A swashplateless rotor hub uses a mast-anchored delta-3 restraint to maintain blade pitch-flap coupling.

A locking mechanism secures the rotor-wing at an oblique angle to the fuselage for fixed-wing flight.

Inflatable diaphragms actuate trim tabs via centrifugal pressure, reducing vibration and maintenance time.

A rotor blade control system generates independent pitch signals using azimuthal position sine and cosine values.

A pitch horn assembly uses a moveable arm and extendable member to adjust the pitch horn radius relative to the rotor blade.

A rotor blade actuation system uses flexible drive tapes and linear actuators to move trailing edge flaps with high precision.

An expandable member shifts a rotor blade fluid flow altering surface between positions, resolving adaptability trade-offs across flight regimes.

Stowable high-lift propellers direct airflow past a leading-edge assembly to increase lift force during low-speed operations.

A rotor blade uses a solid flexure joint and pneumatic actuator to deform its geometry for flight adaptation.

A direct-drive rotor head design integrates motor coupling with swashplate synchronization to reduce actuator count.

Segmenting the control architecture into independent channels resolves the trade-off between device complexity and vibration reduction performance.

Segmented blade control resolves yaw degradation during forward flight and descent by applying distinct pitch commands to up-flow versus down-flow zones.

An inclined parting line on a movable leading edge slat reduces drag and maintains laminar flow by preventing turbulence caused by assembly steps.

Embeds shape memory alloy wires in thermoplastic layers to form adaptive composite structures, eliminating separate actuation mechanisms and reducing weight.

Splices wing spars into the aircraft super frame to eliminate heavy structural wing boxes and reduce overall aircraft weight.

A rotary actuator uses a preload mechanism and radial load path to manage internal forces.

Serrated trailing edges on a wing leading element generate vortices to suppress flow separation, eliminating discrete vortex generators and reducing drag.

Blade controllers query historical positions to validate commands, preventing catastrophic failure from lost blade command position.

Controllable surface adjusts inboard blade angle of attack independently to prevent retreating rotor blade stall and increase forward speed.