Rotocraft TRIZ Cases

Upper secondary wing houses drive shafts to provide additional lift, resolving horizontal flight speed limits caused by retreating blade stall.

Rotatable electric fans on a helicopter tail boom adjust cant angles to resolve the trade-off between anti-torque thrust and lift capability.

A feed-forward control system adjusts cyclic pitch commands to counteract gyroscopic moments in coaxial rotor helicopters.

Electromechanical actuators drive a swash-ring via a ball joint coupling mechanism for precise pitch adjustment.

Offset propellers on rotor blades generate thrust to rotate the shaft and twist the blade pitch, eliminating heavy swashplate mechanisms.

Specific thickness and camber distributions lower pitching moment coefficients, increasing maximum speed and flying range.

Active vibration control system detects gunfire events to modify force generator commands, maintaining propulsion vibration cancellation during weapon firing.

A coaxial rotor helicopter uses ailerons for translational movement control, eliminating cyclic pitch mechanisms to reduce mechanical stress and vibration.

Electromagnetic motor integration enables precise yaw control for aviation devices without tail rotors.

Pitch horn assembly rotates relative to rotor blade to adjust pitch angle, eliminating external control rods that generate parasitic drag.

Segmented composite construction reduces aerodynamic resistance and weight while maintaining structural integrity for efficient damping.

A dual ducted tail rotor system combines mechanical and electric power sources for reliable anti-torque force generation.

Segmented scissor links enable in-flight tracking adjustments without adding separate mechanisms, reducing weight and drag.

Zero to five degree twist angles and rearward sweep reduce non-linear behavior, while rolling bearings minimize clearance and wear.

A twisted flexbeam unit integrates torsion and flapping functions into a single helical structure.

A negative hinge offset rotor head positions the driveshaft between the hinge axis and blade tip to rotate blades orthogonally.

Segmenting the swashplate into rotating and non-rotating parts reduces weight and minimizes aerodynamic drag.

Non-linear hole perimeters minimize stress concentration while maximizing usable opening area, enhancing fatigue life and structural integrity.

Articulating rotary wing modules rotate around hinge shafts to reduce volume while maintaining flight stability.

Integrates upper rotor hub members with a hollow shaft to reduce structural weight while maintaining maintenance access through an open center design.

Compression-loaded elastic bushings in the teeter bearing prevent catastrophic wear and extend fatigue life.

An internal fan redirects airflow for yaw control while an external propulsor generates thrust, eliminating drag from conventional tail rotors.

Elastomeric bearing housing integrates an anti-rotation member to centralize attachment points and reduce shear forces on helicopter rotor systems.

Asymmetric contours between the coupling section and tie section distribute forces evenly, preventing tension peaks to extend service life.

Segmented landing gear units in a joined-wing configuration maintain propeller ground clearance while reducing overall weight.

Dynamic nozzle structures modulate downwash to enhance lift and reduce power consumption without adding battery weight.

Actuator moves weighted mass along rotor blade to adjust moment, eliminating costly scrapping from manufacturing weight variations.

Paddle clamps pivot rotor blades to reduce aircraft volume, resolving the trade-off between transport size and part complexity.

Radial actuators displace the yoke relative to the mast to attenuate oscillatory vibrations, eliminating weight penalties from passive dampers.

Segmented high Lock-number blades lower rotor inertia and fuselage weight while maintaining lift, eliminating heavy lead-lag dampers.

Asymmetric fasteners in the blade root junction transmit centrifugal loads while the fairing reduces structural height for easier folding.

Flexible elastomer spacers distribute impact forces to prevent local delamination of composite material hubs during rotor operation.

A propulsive anti-torque system uses a rotating sleeve valve to direct mixed airflow through thrust nozzles.

Variable chord and twist gradients along the span reduce noise generation during approach flights while maintaining high lift efficiency.

A movable structural element immobilizes a single-blade rotor against the fuselage to minimize aerodynamic drag during cruising flight.

Curved leader hole adjacent to main holes distributes stress and minimizes fatigue in carbon-fiber composite rotor blades.