Without Power Ampliication TRIZ Cases

Slat control system extends leading edge devices from sealed to gapped positions, reducing approach noise and aerodynamic drag during aircraft landing.

Movable disk couples and decouples actuator torque transmission via retaining part rupture to prevent seizure damage.

Integrated sensor units compare actuator outputs to detect skew conditions and malfunctions, reducing system weight while maintaining measurement precision.

A piston assembly with a pressure relief valve holds an aircraft wing trailing edge in neutral position under constant supply pressure.

Pivoted linkages in a spar assembly warp the wing, reducing actuator weight and stress penalties.

Lateral moving mechanism reduces wing thickness, lowering air resistance and drag.

Spring-loaded bistable mechanism deploys slats to spoil airflow and reduce wing loading when gust thresholds are exceeded, avoiding structural weight penalties.

Elastically deformable interconnection portions maintain slat pitch angle while accommodating skewing forces between tracks.

A selectively self-locking actuator uses a split nut and ball screw to reduce motor current during static holding.

Cross-axis flexure pivots create negative stiffness that counteracts centrifugal forces, reducing actuator weight and power requirements.

A detection device uses a deflector to skew the support frame, identifying actuator faults through mechanical displacement.

Segmented flaperon linkage uses fusable joints to shear under obstruction loads.

A hybrid gear arrangement uses a friction drive to transmit torque between axles without mechanical play.

Planetary gear assembly with irreversible gears prevents back-driving to maintain continuous operation after single motor failure.

A flight control cable sensor uses a magnetic connector to decouple measurement from actuation forces.

An adjustment device moves conduit and cable segments independently to modify assembly length.

Fluid piston maintains drive position to recover from screw jams.

Calculating efficiency ratios from current and axial stress detects gradual seizure in rotary-linear actuators without adding external sensors.

Segmented high lift drive units use secondary brakes to arrest motion, eliminating duplicate synchronized drives and reducing maintenance complexity.

A dual door stall correction mechanism opens a flap slot via a coupler linkage to restore wing airflow, eliminating sensor-based response lag.

Hinged slat track and link element avoid front spar penetration, eliminating track can construction.

Rotatable sync shaft links dual connection elements to prevent slat skew during extension, ensuring reliable positioning via a unified drive mechanism.

Segmented control surfaces adjust camber via single actuators to increase low-speed authority while minimizing high-speed drag.

Inverted link plates align hinge points along a movable aircraft flow body axis, resolving outboard space constraints for slimmer designs.

Segmenting the wave generator with radial grooves reduces mass and inertia, enabling faster directional changes without compromising structural strength.

Segmented track members form independent load paths to meet FAA redundancy requirements without excessive weight.

An eccentric crankshaft assembly drives a coupler link through 360° over-center rotation, resolving clearance issues and reducing motor torque requirements.

Nested outer tracks guide rollers within wing volume to articulate slats, eliminating spar penetrations that compromise structural strength.

Deflecting lower surface spoilers away from the wing reduces structural loads on upper control surfaces.

A pivot-mounted link with a spring biases the support structure to an upright position, clearing routings and preventing spoiler over-travel damage.

Activatable links decouple SMA actuators from aircraft airfoils, reducing power consumption while maintaining structural integrity during deployment.

A flap actuation mechanism uses an eccentric coupler rod to translate rotary motion into linear displacement for wing surface deployment.

Differential distributes torque between opposing flap drive links to prevent skewed deployment during abnormal actuation.

Segmented rack members eliminate front spar openings, preserving structural integrity while enabling complex wing slat profiles.

A self-locking actuator uses a swivel assembly to engage a cage, preventing creep under vibration.

Helically coiled cables retract within a telescopic strut, eliminating external housing weight while maintaining electrical connectivity.

Segmented upper and lower flaps pivot to create an airflow passage that increases lift coefficient and stall angle while reducing device complexity.

A flight control combiner adjusts yaw gain via a variable geometry parallelogram linkage.

Independent motor paths in a dual planetary gear actuator maintain output rotation during jamming without mechanical separation delays.

Planetary gearbox assembly drives position transducer via resolver drive arm for compact electric actuation.

Non-linear torsional elements limit peak torque loads during skew events by adapting stiffness, protecting the drive system from damage.

A biasing roller unit elastically urges slat rollers against guide rails, eliminating play caused by manufacturing tolerances and load variations.

Segmented no-back devices and backup brakes prevent flight control surface asymmetry by blocking air load back-driving without adding full system weight.

A leading edge rib assembly houses a gear train to transmit torque for high lift device actuation.

A rotary actuator pivots flight control surfaces using a crowned spline and spherical bearing joint to maintain structural integrity during wing flexion.

A wing assembly uses a drive unit and carriage to actuate high-lift devices.

A secondary actuation mechanism arrests control surface movement using a pyrotechnic actuator and drive link to retain the default position.

Actuator assembly pivots control surfaces via a linear actuator and multi-axis joint, reducing weight and complexity.

A sync shaft couples spaced drive unit output sections to prevent slat skewing during deployment.

A vibration-based detection assembly monitors frequency response changes in aircraft flight control actuator attachments to identify secondary channel energization.