With Power Amplification TRIZ Cases

Shared consolidation of flight parameters lets redundant flight control computers compute one flight order for both command and monitor roles.

Buffered detent-state sensing uses trim data to detect pilot override in rotorcraft FBW control and prevent rapid state cycling.

Redundant inner and outer control loops with electromechanical braking stabilize helicopter flight and reduce pilot workload without hydraulics.

A stick-mounted attitude hold button and fine tracking quickener help large aircraft capture trim quickly and track tanker drogues more precisely.

Automatic lift device positioning replaces manual flap lever operation, reducing pilot workload while keeping target position visible.

Automatic lift device positioning reduces pilot flap-handling workload during takeoff and landing while maintaining accurate control.

A rotatable leading edge surface retracts into the wing to dump lift or protrudes to raise camber, cutting control-surface complexity and wing space use.

See how a two-way transmission and clutch assembly route torque in either direction while reducing aircraft control-system components.

A geared handwind overcomes engaged holding-brake torque, enabling manual actuator operation without a separate brake-release mechanism.

A rotating leading edge device switches between lift generation and lift dumping, while reducing wing space and bending moments.

An accumulator and controller route backup pressure to landing gear and brakes, reducing duplicate components while preserving reliability.

An FCC error monitor compares detent slip and trim rates, adapting flight management when collective or cyclic stick sensors fail.

A variable-displacement hydraulic motor uses swash-angle feedback to control tilt transitions, limit peak loads, and prevent stalling.

A bent optical fiber produces a measurable phase shift, enabling precise slat and flap control without airgap drift.

Fly-by-wire trim assemblies adjust pilot controls to maintain rotorcraft power settings, reducing pilot workload during flight transitions.

Segmenting redundant calculation channels allows a supervisor to isolate failures, maintaining safety compliance while reducing system mass.

Aircraft fly-by-wire systems detect pilot input force anomalies to generate control commands based on applied effort rather than controller position.

Constraining actuator movement parameters during ground operations prevents fatigue loads and force mismatches in redundant systems.

Replacing mechanical push-pull rods with direct drive electro motors reduces control system weight while maintaining load-bearing capacity.

Integrated failure protection system isolates faulty channels to maintain flight control surface functionality despite electromechanical actuator jamming risks.

Ground lock mechanism decouples active drive to maintain tactile feedback during system failures.

An electrically powered actuator limits motor speed via auxiliary setpoints to prevent overheating.

A partial authority mixing unit allocates control commands to trim and stability augmentation servomechanisms.

Segmenting the rudder bar into a single detachable main module reduces disassembly difficulty and maintenance time in compact aircraft cockpits.

Dynamic gain scaling and neutral position adjustment maintain control surface stability during large stick inputs.

Estimates aircraft speed using hydraulic actuator pressure differences and neural networks without total pressure sensors.

Speed-adaptive flight control decouples roll and yaw channels to eliminate limit cycles caused by wind gusts at varying speeds.

A mechanical balancing device equalizes differential pressures between independent hydraulic networks using pressure-actuated valves and locking assemblies.

Accelerometer-based surface contact detection enables fly-by-wire systems to transition to ground operation without weight-on-wheel switches.

Camber control actuator rotates drive arm linkage to adjust flap angle, maintaining wing seal and reducing drag coefficient during cruise flight.

A low-speed mixing algorithm decouples rolling and pitching moments to eliminate asymmetric lift-induced rolling during low-speed forward flight.

Segmented primary and secondary control architectures prevent inadvertent actuation while maintaining deployment reliability without increasing aircraft weight.

A passenger discomfort-aware control unit modulates actuator commands based on sensor data to reduce kinetosis and mechanical vibrations during flight.

Arcuate pistons and segmented chambers minimize internal leakage, enabling precise load holding without external fluid power.

Segmented hydraulic lines with automatic couplings isolate pressurized fluids upon impact, eliminating fire risks from ruptured tubes in eVTOL aircraft.

A trim actuator generates resistive force on a rotorcraft flight control member to alert the pilot.

Air/ground contact logic prevents actuator wind-up during flight transitions by dynamically regulating control authority based on landing gear states.

An electrical yaw control system replaces mechanical linkages with actuators to stabilize rotation rates and reduce pilot fatigue.

Universal control units drive local and remote motors to reduce weight, power consumption, and complexity in single axis active inceptors.

Fly-by-wire lateral shuffle filter attenuates tail section vibrations using bandpass or notch signal processing, avoiding structural weight penalties.

Dynamic inceptor profiles shift resistive force using real-time acceleration data to restore pilot situational awareness lost in passive fly-by-wire systems.

Coupling two independently operable actuators end-to-end eliminates clutch delays and mechanical fuses, ensuring continuous operation when one unit fails.

Flight control computer monitors tail rotor actuator extension to provide pilot warnings when approaching maximum limits.

A vehicle control system uses a decoupling device to mechanically isolate force generators, enabling seamless transition between manned and unmanned operation modes.

A pneumatic decoupling device integrates a pressure accumulator to release compressed gas and separate drive components in electromechanical actuators.

A direct contact heat exchanger mixes heated substance and liquid coolant in a single chamber to maximize thermal dissipation.