Aircraft Stabilisation TRIZ Cases

A carbon nanotube surface film replaces metal mesh to dissipate lightning energy on composite aircraft parts with lower weight and less microcracking.

Dual power signal lines and independent switches keep remote brake engagement working when ECU-controlled solenoids fail.

Adjustable torque limiting lets an EMA permit droop movement after power loss while reducing stop damage and spurious extension.

Adaptive torque limiting in an EMA lowers stop-zone loads and releases anti-extension when needed to protect the actuator and allow spoiler movement.

Pin-in-slot joints create a virtual pivot so a material layer keeps constant length through motion, enabling flat storage without in-plane strain.

Axial flux motor direct drive replaces geared radial motors in a trimmable horizontal stabilizer actuator to cut weight, size, and maintenance.

A pin-in-slot virtual pivot lets a reconfigurable linkage keep its material layer at constant length, reducing in-plane strain during shape change.

Embedding an antenna in a segmented non-metallic airfoil cuts drag and signal interference while simplifying fin assembly.

A segmented dielectric airfoil embeds antennas to cut drag and signal interference while avoiding metallic fasteners.

Interlocking composite airfoil segments eliminate metal fasteners to protect embedded electronics from interference while simplifying manufacture.

A removable hollow dorsal fin hides aircraft antennas and sensors inside a radome enclosure while preserving access, aerodynamics, and stability.

A removable hollow dorsal fin hides antennae and sensors in a sealed radome compartment, preserving fuselage space and aerodynamics.

An axial flux motor directly drives the screw shaft to cut stabilizer actuator weight, footprint, and gear-driven complexity.

A shock-absorbing tail structure and cushioned circuit plug help composite-wing UAVs withstand landing impact and maintain electrical connectivity.

An antenna recessed into an aircraft leading edge preserves radio transmission while cutting drag, weight, and assembly time.

A symmetric 2N tilting rotor layout reduces empennage airflow interference and stabilizes pitch during VTOL and transition flight.

A double eccentric bush and spigot joint enables two-axis aircraft component alignment, cutting assembly time while preserving aerodynamic shape.

A double eccentric bush adjusts a spigot in two orthogonal directions, speeding aircraft assembly while keeping steps, gaps, and alignment in tolerance.

A symmetric 2N tilting rotor layout shifts thrust moments to offset empennage airflow interference and improve pitch stability in VTOL transition.

Automatic fly-by-wire trim adjustment moves the stabilizer during takeoff rotation to avoid mistrim and maintain safe rotation timing.

Tilting fan assemblies switch thrust between vertical lift and forward flight, improving VTOL transition control and cruise capability.

A passive breather tube and dual passageway layout balances pressure between aircraft reservoirs in any orientation without valves or pumps.

Electronic gearing synchronizes elevator and stabilizer motion to cut stabilizer weight and drag while preserving flexible pitch control.

A cam-controlled anti-extension mechanism disables at set rod positions, removing the torque limiter and protecting the motor from torque feedback.

Tilting fan assemblies and lift fans coordinate thrust direction to smooth VTOL hover, takeoff, landing, and forward flight transitions.

A non-parallel boom layout and spatial control system stabilize a towed refueling unit for safe simultaneous refueling of multiple aircraft.

A ratchet-pawl anti-extension mechanism uses rod-driven cam disengagement to block feedback torque without a separate torque limiter.

Electric ducted fans counteract wind-driven swing and rotation of suspended loads, improving hoist safety without aircraft-specific hardware.

Redundant lift motors and real-time power rebalancing help a UAV stay stable and controllable after a motor failure.

A radially biased load detent interlocks with spaced engagement surfaces to stop actuator creep and back-driving in aircraft flight controls.

Consistent input-to-effector mapping cuts pilot workload and modal confusion during tilt-thrust aircraft hover-to-airplane transitions.

Bank angle and filtered dynamic estimates replace missing temperature or pressure sensor data to maintain accurate heading reference navigation.

Symmetric empennage surface deflection adds drag for landing and rejected takeoff while preserving aircraft controllability on short runways.

Real-time lateral center of gravity indicators use fuel tank distribution and thresholds to flag imbalance and support timely rebalancing.

Ground wind stations detect incoming gusts and feed flight controls early, improving VTOL takeoff and landing stability at gusty sites.

Relative displacement between primary and secondary load paths lets an LVDT detect actuator jams early and stop excessive stabilizer loads.

Laser rangefinders and plot-line processing replace visual rigging to align aircraft control surfaces more precisely while reducing hazard exposure.

A shrunk-fit translation guide keeps lock and actuator axes aligned, reducing gland wear and actuator fluid leakage in latch systems.

Nanowire thermal anemometry captures small turbulent airflow fluctuations, enabling more precise airspeed vectors and steadier aircraft control.

Precision-guided UAV water drops improve wildfire coverage in hard terrain while reducing pilot risk, dispersion, and recovery cost.

Sensors and actuators coordinate wing flexing and fuselage rotation to improve UAV mission adaptability without relying on rigid-wing control alone.

A spherical removal and reaming kit replaces Black Hawk stabilator bushings in place, cutting downtime and avoiding full stabilator removal.

Sensor feedback and actuator control keep a refueling device synchronized with tanker roll, improving alignment and safer in-flight engagement.

Active roll and yaw control keeps an airborne refueling nozzle aligned with tanker roll, reducing hose-driven oscillations during engagement.

An asymmetric five-arm coaxial multirotor uses autopilot throttle redistribution to stay stable after one arm fails.

A pivoting rear fuselage and tail-mounted lift impeller enable simple, reliable transitions between VTOL, hover, and forward flight.

Pitching moments from configuration changes are shifted to the horizontal stabilizer, freeing elevators for aircraft maneuvering.

Hydraulic shutoff and directional rate valves lock the trim actuator when idle, minimizing un-commanded stabilizer movement and weight.

Variable electronic gearing between elevator and stabilizer reduces stabilizer size, weight, and drag while preserving aircraft pitch control.

Automated longitudinal and lateral takeoff control cuts pilot workload, shortens takeoff distance, and improves climb efficiency.

Paired tilting fans and lift fans coordinate vertical and forward thrust to keep VTOL aircraft stable through hover, transition, and cruise.

Partitioning the leading edge plenum into pressure zones cuts side-section blowing pressure, reducing aircraft weight, space needs, and drag.

Inclined lower arm pivot shaft axes prevent wheel toe-in, enhancing steering stability without increasing vibration transmission.