Aircraft Control TRIZ Cases

An acceleration limiter constrains actuator displacement during initial deployment to synchronize movement across redundant flight control actuators.

Active loading control prevents structural damage by dynamically adjusting actuation order when current loads exceed predetermined setpoints.

Stiffener reacts loads through spar flanges to eliminate custom manufacturing variability and reduce thermal strain in wing ribs.

A variable-sweep wing aerial vehicle uses a box-wing structure and blown flaps to generate lift for vertical takeoff and landing operations.

Extracting the inboard-most flap support from the fuselage interior and mounting it to a landing gear beam simplifies the assembly complexity.

Merging drive shaft and fairing supports reduces cross-sectional area and weight, lowering drag and manufacturing costs.

Door member blocks torque tube slot during flap extension, preventing airflow that reduces lift and causes vibration.

Internal carrier beam linkage reduces actuation forces and aerodynamic drag from underwing protrusion.

Integrated C-channel spar design reduces fastener count and manufacturing complexity while maintaining structural integrity.

A linear actuator driven flap mechanism positions drive components between rib frame webs within a wing support structure.

Aircraft control surface regulating device uses a laser tracker to measure flap position relative to wing reference features.

A small unmanned aerial system mounts a radio frequency repeater using spatial power combining and beam forming to establish high data rate links.

A single rotational sensor coupled with differentials measures multiple aircraft control surfaces via a common driveline, reducing system complexity and cost.

Spring-loaded pawl opposes rotation without motor power, preventing flutter and structural damage during aircraft power loss.

Segmenting descent profiles into idle and geometric sub-segments positions the deceleration point lower, resolving insufficient deceleration in steep segments.

Distributed pneumatic bladders replace mechanical linkages to actuate split flaps, eliminating flutter risks and reducing structural weight.

A flexible tip spoiler uses a rub block to maintain precise gap positioning between wing components.

Arc-shaped deployment reduces load on Krueger flap, allowing larger curvature for increased lift.

Multi-degree-of-freedom gimbal compensation keeps radar direction and elevation angle consistent during vehicle orientation changes.

Segmented inboard and outboard ailerons reduce wing deformation while maintaining roll authority through coordinated lever movement.

Integrated standby instrument combines inertial and pressure sensors with calculation means to display critical flight data.

Variable curvature rollers align with non-parallel tracks to eliminate stress concentrations and extend bearing lifespan.