Rotocraft TRIZ Cases

An internal weight tray with guide rods adjusts rotor blade balance through the tip, eliminating stress concentrations from external components.

A computing device establishes differential cyclic values to create net yaw moments in coaxial rotor aircraft.

Separable junction between helicopter airfoil blade and flexbeam control cuff uses asymmetric bolts for structural connection.

Dual transmission shafts synchronize tandem helicopter rotors to prevent blade collisions and ensure civil certification compliance.

A balancing flyweight device generates a horizontal centrifugal force to oppose the resultant of lift and drag forces, reducing vibrations and bearing wear.

Central and outboard fan assemblies balance high thrust inertia against rapid angular acceleration for responsive control.

Segmented trim tab head fits cavity to resolve maintenance difficulty from permanent bonding.

Asymmetric rotor blades generate non-planar vortices that break up harmonic reinforcement, reducing noise and vibration in aircraft propulsion systems.

A rotor blade uses spherical magnets to maintain a constant gap during pitch adjustments.

Composite angled leg mounting assembly distributes rotor loads to the airframe, reducing weight and manufacturing complexity.

Segmented plates with mounting arms create a central access opening while distributing centrifugal loads to preserve structural strength.

Variable pitch tail rotors reduce noise emissions by dynamically adjusting rotational speed and blade angle based on flight phase.

A non-rotary damper unit converts rotary blade motion into translational movement to modify resonant frequencies.

A stiff in-plane rotorhead design uses a lag restraint star to manage blade motions without lead/lag dampers.

A helicopter rotor assembly uses magnetic fields to actuate blade pitch directly, eliminating mechanical transmission components.

Tilting tail rotor segments propulsion to reduce component stress, improving speed and service life.

Segmented airfoil profiles on tail rotor blades increase thrust generation in high-altitude, low-pressure conditions where conventional designs fail.

Eliminates heavy metallic fittings and bolted joints by merging the yoke fitting into the rotor blade structure, reducing weight and complexity.

Segmented axial springs constrain flapping bearing movement, preventing wear while preserving radial and torsional spring rates.

A flight instrument displays main rotor rotational speed using a stationary setpoint indicator and movable limit markers to simplify cockpit visualization.

Inner bearing stiffness tuning resolves vibrational mode sensitivity limits without increasing structural complexity.

Segmenting tail rotor hydraulics eliminates shared failure modes, reducing weight and hysteresis while improving ballistic tolerance and control precision.

A centrifugal force bearing uses a conical shear boss and elastomeric member to transmit mechanical loads between rotor components.

Rotor blade reflectors redirect radar pulses to create a synthetic aperture image from a hovering helicopter platform.

Integrated spar spacers eliminate shim complexity and reduce assembly time.

Segmented elastomeric bearings replace friction systems to eliminate moisture leakage and simplify failure detection in high-thrust rotor hubs.

A hybrid helicopter uses a mechanical interconnection system to link the main rotor and propeller drive.

Curved balancing tubes filled with weighted fluid adjust mass distribution during rotation, countering unbalanced forces that fixed weights cannot address.

A helicopter rotor head uses a sequence of angular contact, thrust roller, and deep groove ball bearings to manage radial and axial loads.

A computing device manages tail rotor transitions between flight modes based on speed thresholds.

A method establishes thrust ratios to generate rotor blade profile parameters.

Rotating the bearing within the cartridge redistributes stress to extend service life beyond two hundred flight hours.

Intersecting rotor assemblies use synchronized beveled gears to balance torque loads, eliminating swashplate wear and vibration.

Liquid Inertia Vibration Eliminator units in pylon links isolate counter-rotating rotor harmonics, reducing crew fatigue and structural instability.

A dual frequency damper combines a liquid inertia vibration eliminator with a fluid damper to treat oscillatory forces across multiple frequencies.

Positioning the pusher propeller forward of the anti-torque system extends the lever arm for torque while maintaining structural stability against debris.

A tiltable tail rotor pivots to provide forward thrust alongside the main rotor.

A contra-rotating coaxial rotor assembly uses a singular preloaded central member to enhance structural rigidity and stability.

Segmented flexure and shear portions reduce virtual hinge offset, improving blade movement efficiency and load distribution.

A ducted cross-flow fan replaces tail rotors to eliminate foreign object damage risks while generating anti-torque and lift.

Segmented spokes and curved segments balance thrust forces to reduce aircraft weight while maintaining structural integrity.

Merging blade pitch control via shared links lowers system weight and complexity while maintaining flap-lag stability.

A single cylindrical abutment pivots on a rotor hub to manage blade flapping motion during operation.

Hybrid metal-composite swashplates resolve weight-stiffness contradictions by nesting tubular composites in metal cavities for rotary wing aircraft.

A mono-wing aerial device uses a tangential thrust unit to control altitude and trajectory.

Aligning the connecting rod with the elastic ball joint's preferred axis reduces stress in non-preferred directions, improving rotor stability.

Tapered graphite epoxy yoke and lag spring stabilize rotor lag mode while reducing Coriolis forces at the blade root.

Variable elasticity spacer tube compensates for rotor mast ovalization, reducing bearing wear and extending service life in rotary-wing aircraft.

A helicopter anti-torque rotor coupling mechanism uses a high-friction ring to manage torque transmission between control rods.

Alternating rubber and metal shim layers in end bearings prevent resonance from axial oscillatory loads, extending elastomeric bearing service life.