Without Power Ampliication TRIZ Cases

Switchable couplings replace complex differential gears in the drive system, eliminating mechanical redundancy while preserving independent flap adjustment.

Multi-slice rotary actuator design mitigates wing bending stress by allowing arm slices to flex, preventing jamming in aircraft flight-control systems.

Actuators change strut tension to control wing deflection and twisting, reducing drag while maintaining structural stability.

A distributed electromechanical actuation system uses induction motors controlled via a common bus to drive flight control surfaces.

Electric pedal control device replaces complex mechanical linkages with motor-driven systems to reduce volume, weight, and jamming risks.

Selective drive engagement ensures reliable operation and seamless transition during failure.

A telescopic rod deployment mechanism extends auxiliary wing surfaces using a ball screw actuator and nested inner and outer rods.

An offset gearbox assembly couples nonparallel input and output shafts through integrated gear mechanisms to transmit torque efficiently.

A frangible fuse pin shears under ground contact load, releasing a coupler link into a carrier beam channel to protect wing structure from damage.

A scissor arrangement actuates a leading-edge flap through variable motion patterns.

Rocking lever linkage moves tab with main surface to overcome aerodynamic constraints and improve lateral control.

A suspended rudder bar architecture uses primary and secondary hinges to mount control pedals above the flight deck floor.

Relocating the actuator housing into the flight control panel resolves thin-wing space constraints while a connecting rod transmits force to the wing structure.

Segmented locking elements and a solenoid prevent rebound issues while the stress limiter absorbs jerks during operation.

Parallel drive combinations with primary and secondary swivel joints allow streamwise movement without swing-link rods, reducing part count and weight.

Deployable cruise mini flap increases lift coefficient to 0.7-0.8 while maintaining low drag, reducing fuel consumption.

Dual prime movers drive a shared screw-nut interface to prevent complete jamming during emergency conditions, maintaining actuator reliability.

A bearing assembly combines a laminated section with a spherical section to manage angular displacement.

Redundant actuators and dynamic cam couplers isolate failures to prevent skew conditions and ensure complete flap deployment.

Dual-motor actuators with vibration isolators reduce pilot fatigue while maintaining manual override authority.

An asymmetric hydraulic control system routes fluid through lines of varying diameters to supply multiple aircraft actuators.

A spindle drive uses a torsion bar to provide redundant actuation when the primary path fails.

Spheroid bearing surfaces guide swiveling motion to compensate for torsional moments in lightweight frameworks.

Check valves seal against a piston head to form a hydraulic lock, eliminating kick loads from misaligned U-joints during high-speed flight.

Rolling elements replace sliding friction between the input shaft and sliding collar to enable precise axial movement.

Axial retraction of the motor drive shaft disengages the jammed primary system, allowing the backup control to operate without resistance.

An integrated rub block reduces contact loads and eliminates complex linkage systems to minimize maintenance costs on aircraft wings.

Pivoting deflector panels on an airfoil create asymmetrical profiles that generate lift to counteract torque, reducing engine power requirements.

A distributed wing flap system uses a hydromechanical clutch to switch between hydraulic and electric actuators.

Aircraft artificial force feel device monitors shear pin fatigue to reconfigure tactile cue forces.

A pivotally mounted lever arm applies controlled tensile and compressive forces to a flight control actuator secondary channel.

Segmenting actuation into deployment and pitch motions eliminates ailerons, reducing aircraft weight while enabling independent lift and drag control.

Sub-turn transmission lines synchronize multiple flight surfaces within one revolution, reducing assembly complexity and system weight.

Nesting a first planetary gear stage inside a second reduces overall volume while maintaining high reduction ratios.

A magnetic reluctance position sensor detects angular displacement via geometric variations on an actuator output arm.

A rotationally mounted connector member moves upper and lower skin structures simultaneously to change trailing edge camber.

Translation and rotation mechanism folds wing segments parallel to the fuselage, reducing aircraft width for constrained spaces.

Segmented mechanical and electrical units generate independent feedback, resolving power loss reliability issues while reducing structural loads.

An asymmetry sensor calculates correction values to detect actuator skew in aircraft movable components.

An integrated tensioning tool measures and applies cable force directly via a load cell, eliminating complex hydraulic systems and multiple assembly stations.

A solid-state motor uses a shape-memory alloy belt driven by thermal regulation to rotate without mechanical gears.

A spring mechanism with a blocking element corrects excessive rope lengthenings while accommodating thermal fluctuations to prevent high reversal tensions.

Counterweights attached to the power transmission mechanism absorb load fluctuations from air resistance, stabilizing flight attitude.

Extracting actuators from wing interior into control surfaces eliminates drop hinges, reducing drag while optimizing internal wing volume.

A horizontal control column uses a transfer assembly to translate pilot forces into pitch output link motion.

A flight control actuator uses a sacrificial sensing element between spherical shapes to detect load transfer during primary path failure.

A planetary drive servo actuator uses a clutch to constrain an outer cylinder while allowing an inner cylinder to rotate the output shaft.