With Power Amplification TRIZ Cases

A fly-by-wire control system processes pilot inputs through feed-forward crossfeeds and washout mechanisms to generate decoupling commands.

Detects uncontrolled aircraft control surface movement by comparing theoretical servo current against measured feedback values.

Calculates accurate hydraulic fluid levels during stable flight segments to eliminate movement-induced measurement errors and enable predictive maintenance.

A sealed heat transfer device couples two hydraulic systems to move thermal energy without fluid mixing, resolving temperature control complexity.

Real-time gain adaptation reduces performance dispersion in aircraft actuators, resolving the trade-off between control law robustness and gain value.

Multiple smaller servo-actuators operate in a ganged configuration to increase torque output while maintaining high speed characteristics.

Electromagnetic speed conversion replaces gear trains to reduce aircraft actuator weight and complexity.

Electronic actuators in the control grip press fingertips to convey aircraft attitude data, reducing pilot distraction from visual instruments.

Ground-flight sensor deviation analysis detects aircraft high lift component states using standard accuracy sensors.

Dynamic coupling pivots and translates the device to reduce peak actuator loads, cutting weight and power consumption.

Electronic rudder bias system calculates thrust estimates to generate engage commands, eliminating mechanical weight and pilot force measurement requirements.

Real-time angle monitoring detects pylon differences and applies braking force to prevent asymmetric conditions from escalating beyond safe limits.

Replacing complex mechanical linkages with a kinesthetic control system reduces device complexity while maintaining aircraft control reliability.

Paired actuators switch operation upon failure to prevent loss of control and airframe breakup in aircraft.

Feed-forward control cross-feeds anticipate coupled motions in rotorcraft, reducing pilot workload while maintaining stability during perturbations.

Force sensors detect pilot input to adjust actuator torque, eliminating complex mechanical springs and reducing device complexity.

Weighted mean position feedback synchronizes multiple electro-mechanical actuators, preventing uneven loading and unexpected aircraft roll or yaw.

A hybrid actuation system moves aircraft control surfaces using electric and hydraulic actuators to optimize power usage.

Rotatable and slidable ribs twist a wing element to adjust aerodynamic configuration, overcoming flow separation issues from conventional control surfaces.

A dual channel rudder system architecture utilizes electromechanical actuators with independent control circuits and passive damping mechanisms.

A processor estimates sideslip angle from flight parameters and scales maximum yaw rate to constrain aircraft rotation within structural limits.

An electromechanical actuator replaces hydraulic systems in helicopter controls, providing manual override capability during power failures.

Electric flight control system transmits auxiliary stick position to protection module during autopilot engagement.

Switching wing tip camber between positive and negative states uses aerodynamic torque to reduce actuator force requirements.

Sensor feedback adjusts independent drive stations to prevent aerodynamic asymmetry from asynchronous flap movement.

A redundant current-sum feedback control system measures total coil currents to manage actuator movement.

Automatic arming logic reduces pilot workload and procedural errors by deploying spoilers only during ground operations.

Aircraft flight control system manages transition between load factor and longitudinal attitude modes.

A biasing member moves between compressed and expanded states to reduce high-pressure hydraulic cycles, lowering energy consumption and heat generation.

Segmented flight controllers enable safe landing by allowing actuators to receive direct pilot inputs during primary system failures.

LED lighting components on sidestick controllers provide visual feedback that resolves pilot awareness gaps in automated flight systems.

A backup hydraulic pump supplies high discharge pressure to drive aircraft control surfaces during central system failure.

Exponential piloting law parameters compensate for control chain time delays and asynchronisms in flexible aircraft flight systems.

Automatic fly-by-wire pitch trim system converts multi-parameter settings to equivalent center of gravity, reducing miscalculations and enhancing safety.

A feed-forward rotor speed command system adjusts aircraft rotor speeds based on flight commands.

Electronic monitoring module detects backdrive failures and maintains autopilot continuity without redundant actuators.

Control method alternates pilot authority over aerodynamic means to prevent simultaneous inputs.

A fluidic oscillator adjusts flow frequency by changing chamber volume without altering input pressure.

Merging the stability augmentation and main rotor actuators into one assembly reduces system weight while maintaining control precision.

Automated flight mode indicators on rotorcraft instrument panels display active control states to pilots.

A gas turbine engine thermal management system recovers waste heat from exhaust gases using a low spool driven pump.

Servo device manages force feedback through adjustable saturation values for piloting members.

Non-linear scheduled translational rate feedback adjusts acceleration commands to resolve pilot augmentation limits and prevent target overshooting.

A recursive autoregressive model estimates servo loop dynamics to detect blockages early, reducing structural loads and improving reliability.

A rotor moment control system establishes blade pitch angles to counteract external forces.

Adjustable deadband mechanism in aircraft control sticks enables smooth transitions between distinct operational modes.