Propellers TRIZ Cases

Clamped cuff and bearing elements stiffen the rotor mast, limiting fan movement at tight duct tip gaps to preserve thrust and structural integrity.

A snap-fit locking member and elastic abutting sleeve keep the propeller secured under vibration and abrupt speed changes while enabling tool-free removal.

A hydraulic brake and control algorithm arrest rotor blades smoothly in wing-borne flight, avoiding peg-impact loads and reducing structural fatigue.

Shifting the blade tip leading edge increases local camber to delay shock waves, cut hover drag, and postpone stall in rotorcraft blades.

Resiliently mounted elevon surfaces and fuselage effectors improve UAV pitch, roll, and yaw control while keeping deployable airfoils compact.

During engine failure, airflow-driven pusher propeller torque feeds the drivetrain to support the main rotor and improve flare control.

An antifriction interface and redundant load path keep the anti-torque rotor controllable when bearing damage blocks normal control.

A pressure-regulated oil circuit diverts excess propeller control flow to the engine return line, limiting oil heating while preserving blade angle actuation.

Multi-stage movable guide shells redirect rotor downwash to a discharge port, shielding vertiport passengers during boarding and deboarding.

An integrated spindle assembly for dual ducted tiltrotors cuts separate parts and stressed joints while supporting efficient mode conversion.

A motor-driven rod and inner-rod actuator automates piston aircraft throttle, mixture, and propeller controls while preserving manual override.

A rotorcraft gearbox case showing how a relocated pitch bearing uses centrifugal and gravity-fed lubrication to improve wear debris detection.

A telescoping wing and deployable stabilizer layout lets a compact UAV expand for better aerodynamics, longer flight time, and higher payload.

A tilting propulsion unit lets a single-motor rotorcraft hover, steer, and follow a flight path without multi-rotor complexity.

An upstream-downstream thrust layout reshapes local flow to cut drag and power use while improving low-speed thrust or power extraction.

Suction outlets and injection inlets manage duct airflow to limit separation, boost thrust, and improve hover and forward-flight stability.

Pivoting engine modules switch from vertical lift to wing-supported flight, cutting VTOL power use, noise, and control-surface complexity.

A flanged tubular nut with an anti-rotation washer and retention ring secures a propeller shaft while cutting axial length and easing access.

Clamping a cuff between the mast nut and bearing boosts rotor mast stiffness, limiting fan movement and preserving ducted fan tip gap.

A backup bearing and thrust shoulder keep helicopter pitch change motion active after primary bearing failure while reducing skidding and false brinnelling.

A spring-biased locking mechanism uses chamber pressure control to prevent unwanted actuator movement while reducing blow-by and pressure peaks.

Automatic yaw-rate calculation from speed and roll angle lets a rider steer aircraft turns with handlebar-like inputs and precise control.

Spanwise airfoil shaping and pitch control reduce asymmetric rotor loading, cutting hover noise while preserving forward-flight efficiency.

A 3D-printed lattice support network replaces multi-part blade assembly to cut build time and cost while preserving dynamic load resistance.

Inclined serrations on a turbomachine splitter wall cut fan-wake broadband noise while preserving guide-vane aerodynamic behavior.

A dual-structure aircraft control link uses a sacrificial outer member and protected inner load path to resist impact and avoid single-point failure.

Distributed electric propulsors boost wing lift and drag for low-speed landing and takeoff on short or moving platforms in separated wake.

Curved leading-edge and overhang airfoil surfaces use the Coandă effect to keep flow attached, turn airflow sharply, and cut trailer drag.

Automatic propeller pitch reduction helps a hybrid helicopter sustain lift rotor speed during engine failure while limiting vibration and aerodynamic loads.

A dual epicyclic gearbox cuts turboprop reduction gearbox complexity, weight, and oil demand while matching turbine and rotor speeds.

Flexible blade tip extensions maintain tight duct clearance despite tolerances and loads, while absorbing contact energy and easing replacement.

Hydraulic synchronizer and locking elements match shaft speeds for smooth tiltrotor mode transitions and reliable torque transfer.

Telescoping wings, hinged ailerons, and modular payloads let a compact UAV expand for longer missions, better aerodynamics, and more carrying capacity.

Rotatable paired thrusters shift orientation between hover and forward flight to limit rotor downwash effects, manage torque, and improve control.

A derivative-based current rate limiter keeps electro-hydraulic servo-actuator speed within bounds during transients to avoid pressure drops.

A beam with uneven end masses uses bending and torsional modes to attenuate blade-pass vibration and harmonic frequencies in aircraft structures.

A sacrificial outer link and independent inner load path absorb impact damage and avoid single-point failure in aircraft flight controls.

Folding hollow-cell walls turn a 2D auxetic pattern into a 3D structure that absorbs impact energy and adapts to non-uniform shapes.

Yarn stitches join the blade shell around a thin trailing edge insert, preserving aerodynamic efficiency while improving bird-impact tolerance.

A removable coupling lets engineers rotate and extract the bearing cage in tight spaces while separating rolling bodies to reduce wear.

Progressive main rotor speed reduction cuts rotorcraft noise in flight while preserving lift margin and rapid recovery for emergencies.

A segmented cladding lets a composite fan blade tip separate at a set load, limiting rub damage while improving impact and delamination resistance.

A corrected propeller speed reference and torque adjustment keep turboprop engines near peak efficiency without changing pilot power input.

Mechanical rib coupling and bonded inner and outer covers reduce adhesive shear loading while improving rotor blade fatigue and impact resistance.

Using onboard batteries as oscillating masses with elastic mounts, this case attenuates rotor-induced airframe vibration without adding dead weight.

Axially engaged bearing and seal frames shrink seal areas in a hydraulic rotary feed-through, cutting leakage in large ventilator wheels.

Adjustable UAV propellers switch orientation, position, and blade geometry to preserve six-DOF control and safe landing after propulsion failures.

A compact elastomeric bearing assembly combines shear and centrifugal force bearings to cut rotorcraft weight and complexity.

A two-axis gimbaled fan redirects thrust through 360-degree motion to improve aircraft maneuvering and control in tight spaces.

Lag-compensated angular position estimation helps rotorcraft decouple coupled flight controls, stabilize handling across speed regimes, and cut pilot workload.