Aircraft Control TRIZ Cases

Connecting device between adjacent leading edge lifting bodies absorbs impact shocks and transfers external forces to maintain structural integrity.

Segmented architecture reduces hardware complexity while maintaining reliability through distributed command verification.

A load testing apparatus applies torque and tensile forces to a flight control surface using segmented vertical and fore/aft structures.

Flap and plug seals close wing slat apertures, eliminating aerodynamic drag from exposed openings.

A non-linear filter adapts its parameters to match control order speeds, eliminating pilot induced oscillations in aircraft.

A deployable gurney flap arrangement uses a flexible seal to retract into an airfoil surface, preventing debris ingress that causes component degradation.

A three-steering gear direct-drive coaxial rotor system actuates upper and lower swashplates to control cyclic pitch angles.

Independent control valves in dual-stage actuators balance hydraulic pressure via cross-controller feedback links, resolving fault detection limits.

A distributed neural network segments processing between a base station and a vehicle front end to enable real-time object identification.

Dual linear modules drive a common non-rotating output, maintaining landing gear position without complex locking mechanisms.

Double hinge mechanism articulates droop nose to reduce air leakage and wear while maintaining aerodynamic efficiency.

Applying asymmetric deflection and rate limits to roll control surfaces overcomes symmetric constraint bottlenecks that restrict aircraft roll quickness.

A torque transmission device uses a flexible earth ring to transmit rotational force via friction.

Adaptive LQG and MPC controllers balance load sharing between hybrid actuators, reducing structural damage from unequal dynamic responses.

A flight control interpreter replicates unmanned aircraft system profiles on an optionally piloted vehicle.

Flexible leading edge skin transitions curvature profiles without arc length change, eliminating steps that disrupt laminar flow and generate noise.

A supplemental thrust system integrates a turbocharger unit and heat exchanger into an aircraft propulsion duct to increase engine power.

Torsion springs deploy articulated flaps for airflow guidance while retracting them to minimize nacelle diameter and reduce aerodynamic drag.

Rotatable tube support with connection element fixes movable control surface orientation, distributing vibrational stress to enhance stability.

A mode-selecting processor executes a fast Fourier transform on sensor data to identify the helicopter operation mode for inertial reference system leveling.

A power demand anticipation system uses cyclic control and flight sensors to proactively adjust rotorcraft engine output.

Local comparison of positional data by smart sensor pairs detects flap skew, reducing wiring complexity and software integration in aircraft high lift systems.

Replacing linear actuators with a central rotary unit reduces volume and weight while maintaining torque for faster flight.

A trailing edge device coupling uses a cam track and offset cam to support the wing-mounted component during normal operation.

Segmented coupling units with specific bolt axis orientations compensate for manufacturing tolerances, reducing constraint forces during assembly.

A control valve circulates hydraulic fluid through a constriction to maintain consistent viscosity in electrohydrostatic actuators.

Elastic sealing panels adapt to flap movements, resolving the trade-off between reliable gap closure and aerodynamic drag reduction.