Rotocraft TRIZ Cases

A vibration controller adapts control parameters via real-time avionics data, reducing structural impact during transient flight conditions.

High lock-number blades with flexures enable in-plane lead-lag motion, eliminating dampers while reducing rotor mass and vibration.

Dynamic transmission tilt adjusts rotor mast orientation to reduce component wear and eliminate ballast requirements.

Electromagnetic induction actuates individual rotor blade pitch to resolve low thrust change rates at variable speeds.

Segmented cutting edges in an aircraft cable severing jaw distribute mechanical tension across multiple zones.

Friction press-fit connection secures fairing to hub body, preventing rotation and blow-off while reducing weight.

Extracting yaw control from the main lift system via rear ducted fans reduces vibratory loads and simplifies operation.

A flexure-type twist-shank yoke enables blade pitch and flapping motion through elastic deformation.

Segmented rotor blades reduce inboard size and weight by separating aerodynamic shell from load-bearing flexbeam.

A counter rotating torque rotor generates drag torque opposite to the lifting rotor direction.

Segmented elastic hinge members diverge at a predetermined angle to lower bending stiffness, reducing peak stresses on rotor blade connectors.

A rigid swashplate and direct linear actuators eliminate mechanical slack to achieve flight speeds exceeding 200 mph.

Fiber-reinforced polymer plates form an integrated lead-lag hinge to provide low lead-lag stiffness and high flapping stiffness.

Segmented primary and secondary tail rotors resolve reliability complexity trade-offs by enabling independent backup operation.

A lift offset management system dynamically adjusts blade pitch angles to optimize rotor performance.

Mechanical flap positioning creates air drag to reduce rotor speed, enabling stable transition from helicopter to airplane mode.

A locking element prevents rotation of a fixed swashplate ring while allowing tilt.

Counter-rotating turbine stages extract energy from a central lenticular chamber to cancel rotational torque and reduce noise.

A foldable protective cage shields propellers and cargo, resolving the trade-off between user safety and drone transport volume.

Variable torsion composite paddles resolve root stall conflicts in tilt rotor craft by dynamically adjusting twist angles across flight modes.

A passively tiltable rotor group redirects lift to generate horizontal thrust without extra motors.

A rotor hub assembly uses a universal joint and elastomeric member to transmit forces while absorbing vibrations.

Independent cyclic and collective actuators reduce flight criticality by eliminating interdependent control mechanisms.

Resilient members in UAV rotor mounts provide elastic force to minimize mating surface wear and improve reliability.

A segmented autogyro rotor blade applies varying cross-sectional profiles along its span to optimize aerodynamic lift generation.

Spherical magnet surfaces maintain constant gaps during rotation, preventing magnetic field weakening and ensuring reliable torque generation.

A rotating thrust director redirects mixed airflow through a fixed nozzle assembly to generate propulsive and anti-torque vectors, eliminating the tail rotor.

Segmented rotor blades pivot via a transitional brace, reducing structural envelope without increasing drag.

Segmented components with variable shims resolve the contradiction between manufacturing precision and adaptability, reducing reinstallation time.

An airfoil-shaped tail boom counters fuselage torque via pressure differences, eliminating heavy tail rotors and reducing power consumption.

Rearward propeller placement and stabilizing surfaces remove the tail boom, resolving vibration and noise contradictions in hybrid helicopters.

Gas generator and pipe rotate with blades to eject gas through an orifice, eliminating complex tail rotors.

A rotorcraft rotor stop mechanism uses a pivoting lever and hook to constrain blade flapping movement.

A dual inertia anti-torque tail fan uses separate high and low inertia assemblies to deliver responsive yaw control.

An inwardly facing centrifugal force bearing manages rotor blade forces within an articulated hub assembly.

A limited-angle electric motor adjusts rotor blade pitch through a shared shaft to provide precise cyclic control.

Trajectory-based algorithms drive electronic actuators to precisely track blade pitch positions, resolving vibration reduction limits in swashplate systems.

Automated controller sets rotor neutral positions using speed data, reducing pilot workload during start-up and take-off sequences.

A parking tail rotor system stops rotating at high speeds to minimize parasitic drag on compound aircraft.

Segmented stub spars and thickened skins distribute structural loads to reduce manufacturing complexity.

Annular ridge and seat configuration engages during bearing failure to maintain anti-torque rotor controllability via redundant mechanical path.

Damping assemblies connect radially non-adjacent blades to selectively dampen center-of-mass movements, reducing component stress and maintenance frequency.

Elastomeric bearings and pneumatic dampers isolate rotor oscillations from the airframe, enabling efficient low-RPM operation during high-speed cruise.

Segmented helicopter rotor blades reduce vortex interaction noise while preserving power savings during high-speed flight.

Non-equidistributed blades shift acoustic energy away from bothersome frequencies, reducing annoyance while maintaining compact rotor diameter integration.

Variable channel depth between 14% and 20.5% of inner diameter lowers form drag while maintaining thrust efficiency.

A quiet mode controller adjusts tail rotor speed to reduce noise emissions.

A hybrid helicopter rotor stop and positioning system halts main blade rotation during cruise flight.

A hybrid helicopter yaw control device modifies propeller blade pitches differentially to adjust thrust distribution for directional changes.