Rotocraft TRIZ Cases

Segmented rotor groups use asymmetrical balance to shape sound pressure levels and frequency spectrums, reducing component stress from vibration.

A separable helicopter rotor blade attachment uses a bolted junction and stiffened link to transfer centrifugal loads between the airfoil blade and flexbeam.

A rotorcraft generates an updraft by rotating blades at a negative pitch angle to supplement lift during vertical take-off.

Serially stacked swashplate assemblies enable independent pitch control of rotorcraft blades through concentric ring sections and sliding mechanisms.

A passive pitch adjustment apparatus uses levers and rods to rotate rotor blades via aerodynamic torsion moments.

Sliding connection between retaining arm and antirotation bracket eliminates hinge slack, reducing weight and maintenance needs.

Azimuth offset in the servo-control generates consistent torque to reduce axial shocks and wear on the non-rotating compass.

Epicyclic gear train transmits motion from mast to hub at differential speeds, driving accessories without increasing rotor weight.

A semi-levered landing gear system uses a universal joint and radius rod to guide the tire along an arcing path during shock strut compression.

A rotor blade fold assembly uses a loose linkage to support the second section only when rotated, reducing structural envelope.

A reconfigurable rotorcraft blade tip adjusts its sweep angle during flight to optimize aerodynamic performance across varying speeds.

Horizontal spar distribution on rotorcraft blade surfaces secures the main structure via horizontal fixing sockets.

Adjusting damper spring rate via real-time fluid pressure changes reduces vibratory forces on the hub assembly across varying flight conditions.

A rotor blade attachment assembly uses a hub extender and tension torsion strap to enable rapid folding.

Integrated weight cartridge in the rotor blade tip block reduces assembly burden and loose weight handling while maintaining aerodynamic stability.

A rotorcraft power optimization device disconnects drive shafts to redirect engine torque to rotors.

Integral stabilizer arrangement in a box configuration mounted to the shroud of a ducted tail rotor system.

Pivotable tail boom fans redirect thrust vectors to resolve power utilization inefficiencies during forward flight.

Dynamic actuators shift bearings on an annular track to undulate a swashplate, adjusting rotor blade pitch at specific azimuths to counteract hub shear loads.

A drone guard uses support members and a flexible member to surround aerial vehicle rotors while maintaining portability.

A magnetic de-rotation system stabilizes a shaft fairing using eddy currents and magnet attraction forces.

A detection device measures vertical and true airspeed to predict rotorcraft approach into a vortex domain.

Orthogonal actuators in the fairing produce adjustable anti-vibration moments that neutralize rotor rotation vibrations despite compact gearbox dimensions.

Axially symmetrical trailing edge sections on rotor blade profiles maintain consistent aerodynamic performance across varying airflow directions.

A mechanical control combiner uses a parallelogram linkage to transmit cyclic and collective pitch commands without interference.

A control system adjusts cyclic pitch via servos to counteract opposing rotor moments in dual rotor helicopters.

A control method adjusts propulsion propeller blade pitch to regulate hybrid helicopter speed.

A rotor yoke uses distinct attachment devices to allow transverse chord-axis movement while maintaining pitch-change axis rotation.

Torque splitter devices rotate dual-plane rotor hubs to stack blades in one horizontal plane, reducing storage footprint while maintaining flight stability.

Twisting the wing reduces rotor wake drag, decreasing yaw and roll maneuver time for tilt wing aircraft.

Emergency collective actuator lowers rotor pitch via motor force to prevent stall during engine failure, bypassing pilot reaction delays.

A spring-integrated rotor pivots about a second axis to decouple vibratory loads from the motor, extending operational life.

A hinge mechanism pivots coaxial helicopter blades from parallel to perpendicular positions for compact storage and automatic deployment.

Spherical lead stop surfaces engage the hub arm to maintain elastomeric bearing compression during braking, preventing tension-induced rupture.

Inverted anti-drive links resolve conventional inefficiencies by enabling full collective stroke extension across the mast.

A pitch horn joint uses a spherical bearing and slider sleeve to distribute stress across a wider contact area.

Linkage assembly with adjustable spacer controls rotor blade fold angle, reducing structural envelope for rapid stowage.

Segmented steel keys with tungsten carbide coatings improve durability while minimizing weight addition in rotary aircraft anti-drive mechanisms.

Lateral actuators with sliding joints reduce control system height by eliminating anti-rotation mechanisms.

Friction pads in a lag damper housing dissipate heat via cooling fins, reducing weight and manufacturing costs of vertical lift aircraft.

Replacing metal components with carbon fiber composites resolves the weight-strength trade-off while minimizing pivot bearing loads and corrosion risks.

Segmented pin bonding replaces drilled holes in flexbeams, preserving rigidity while reducing rotor blade weight.

Variable pitch tail rotors transition between yaw control and lift generation to maintain flight stability while reducing fuel consumption during heavy loads.

Centralized swashplate mechanism adjusts rotor blade pitch angles, resolving the contradiction between active lift balancing and system complexity.

A bearing restraint keeps elastomeric rotor bearings compressed during low-speed operations, preventing column instability caused by transverse forces.

Replacing complex fibre strand positioning with unidirectional flat fibre strips simplifies spar manufacturing while maintaining structural strength.

Segmenting drag damping from thrust bearings reduces laminated bearing mass and vibration in gyroplane rotors.

A coaxial helicopter pitch control mechanism uses four servomechanisms to drive uniformity cyclic and differential collective adjustments.

Hinged lids enclose rotors inside pods to minimize aerodynamic drag, enabling higher cruise speeds without adding complex actuation mechanisms.

Harmonic analysis of strain data predicts rotor blade tip displacement, preventing collisions in coaxial rotorcraft.