Without Power Ampliication TRIZ Cases

Detecting skew via a lanyard and hybrid actuator prevents structural damage from excessive loads while reducing supporting structure weight.

Separate drive member actuates the shutter panel to resolve sealing reliability versus complexity trade-offs.

Bonding elastomers between fingers on arcuate beams achieves high stiffness and damping without complex fluid mechanisms.

A quasi four-bar cable support unit uses a compensation link to maintain stable tension across varying temperatures.

A torque limiter uses a reference gear to detect output shaft load and engage a mechanical lockout mechanism.

A backstopping clutch prevents input device back-driving while an overrunning clutch enables direct load actuation.

Actuator design with nested arrangements and damping means for controlled extension.

An anti-jamming piston shifts within a hollow screw to prevent jamming during electrical or mechanical failures.

A titanium-containing transmission shaft provides torsional flexibility and bending rigidity for aircraft high-lift systems.

A control allocation matrix maps autopilot commands to actuator signals via feedback loops.

Angled crank shaft converts rotary motion into streamwise flap travel, reducing weight and complexity within thin wing profiles.

A slat support assembly uses a sliding joint to align the mounting lug along the rotation axis.

A gas generator wind-up apparatus retracts a brake cord to resolve insufficient response speed during emergency landing scenarios.

Continuously variable transmission adjusts drive-line speed to reduce power consumption and chatter in aircraft control surface systems.

An automatically locking linear actuator integrates a rotary lock mechanism directly into the drive screw assembly to eliminate separate control devices.

Negative air pressure on the wing surface deploys the spoiler hinged top flap, reducing actuator weight and structural deformation during gusts.

Discontinuous joints in aircraft gearbox assemblies prevent fracture propagation by isolating component failures within redundant load paths.

Bell crank mechanisms replace heavy cam tracks with four-bar linkages, reducing weight and jamming risks while maintaining robust flaperon movement.

Gas generator decouples actuator from release member, allowing emergency extension and locking without extra hardware.

Dual-shaft rotary actuator moves spoiler rods to reduce deflections and gaps that increase drag.

Integrating a primary lock into the drive cylinder simplifies the aircraft engine nacelle system while maintaining safety redundancy.

A rotary actuator drives an aircraft wing slat track via a groove and spigot engagement mechanism.

Crowned spline interfaces in a folding wing hinge form universal joints that isolate flight loads between fixed and folding wing portions.

A compact actuator transmits motor rotation to flight control surfaces through a pin and bush mechanism pivoting on orthogonal axes.

Nested curved guide rails reduce construction space and weight while maintaining reliable flap adjustment.

A common connection fitting merges two actuator rods into one slider crank mechanism, reducing stress on the flight control surface during redundant operation.

A dual-link high-lift device uses separate rotary shafts to independently drive flap extension and angle adjustment.

Concentric drive shafts enable redundant torque transmission to prevent loss of control in thin wing aircraft.

Dual laser distance sensors inside aircraft actuators measure linear translation displacement to provide real-time positional feedback.

A flap assembly uses dual drive units to perform aileron and landing functions.

Roller bearing slat track design reduces weight and complexity while maintaining load capacity.

A mechanical fuse with a flat rectangular profile and strategic channels distributes shear stress uniformly across the aviation actuator assembly.

Movable panel maintains continuous outer mold line shape to eliminate step surfaces that increase drag during cruising.

A coupling link uses a sliding intermediate member to connect an aircraft lift device to its track.

Redundant dual-motor load paths maintain commanded stroke positions without powered brakes, eliminating complex control circuitry and active power requirements.

Sync shaft prevents slat skewing by coupling spaced connection stations via spherical joints to avoid constraint forces.

Pivoting motor pods on a box wing structure adjust thrust vectors to reduce weight and enable operation on diverse surfaces.

An electromechanical drive unit moves a contact piece to establish friction force on a helicopter cyclic stick.

Segmented pitch and roll feel spring cartridges integrate into a single unit, reducing device complexity while maintaining reliable force feedback.

A retracting mechanism decouples a harmonic drive motor shaft from its flex gear to isolate the actuator assembly.

Coupling distinct hydraulic circuits through a shared heat exchanger to transfer thermal energy between fluids at different temperatures.

Protection arrangement interrupts drive to jammed actuator via sensors and locks, preventing shaft buckling from aerodynamic forces.

Linear actuator drives carriage along bearing rail to reduce mechanical complexity and wear in aircraft flap systems.

Nested track engagement assemblies guide aircraft flap motion to prevent structural deflection while preserving the wing loft profile.

Helical slat tracks align lateral surfaces with the line of flight, eliminating gaps that cause aerodynamic drag and noise.

Actuator reaction link pivots between cylinder units to create open manifold installation space.

Radial play and engaging elements arrest transmission shaft rotation upon misalignment, enabling detection without dedicated sensors.

A hydraulic actuator uses a roller screw mechanism to drive the piston, enabling precise load positioning.