Aircraft Stabilisation TRIZ Cases

A coupling assembly with rotatable balls connects a flexible drive shaft to an actuator assembly.

Design procedure shapes fairing to minimize gap with fuselage during elevator movement, reducing parasitic aerodynamic resistance.

Segmented hydraulic architecture reduces line complexity while the roller clutch maintains flap position under aerodynamic forces.

Integrating an adaptable section into the stabilizer structure eliminates tail skids, reducing drag and weight while maintaining energy absorption capability.

A clevis system attaches a vertical stabilizer to an aircraft fuselage through composite skin apertures.

Auto-guidance system regulates aircraft taxi speed via direct commands to the electric controller.

Trailing edge control surfaces dynamically adjust lift distribution to delay flow separation and eliminate buffeting without increasing cruise drag.

Nested secondary ball nut transitions to majority control upon primary failure, maintaining aircraft stability.

An aircraft control surface employs an arced nose profile with offset curvature centers to delay boundary layer separation at high deflection angles.

A hybrid flight control system merges mechanical linkages with electronic actuators to manage aircraft surfaces.

Fuselage-mounted plates and thrust fans provide counter torque to reduce tail rotor power demand, enabling stable lateral movement in crosswinds.

Nested translating body retracts to eliminate external bumps, reducing cruise drag while maintaining effective gap creation during deployment.

Inflating flexible lifting envelope extends wingspan to reduce induced drag while deflating maintains airport gate compatibility.

An automatic yaw axis control system manages aircraft orientation using sensor data and actuator feedback.

Variable tilt motor assemblies reorient propellers to transition between flight modes, reducing propulsion system complexity.

Downward tail boom protuberances control air stream flow to reduce negative lift, resolving the trade-off between structural strength and aerodynamic drag.

Dual-axis articulated horizontal tail units replace vertical stabilizers, reducing drag and weight while maintaining yaw control.

Modular flight control subsystems enable variable manning modes, reducing operational costs while managing automation complexity.

Resilient tail mounts establish a nodding axis to decouple dynamic fuselage responses, avoiding weight penalties from stiffening airframe structures.

A supplemental wing rotates between hover and forward flight positions using adjustable pitch surfaces to generate lift.

A cross pin in a longitudinal slot converts linear ram motion to rotational deflection, reducing backlash and improving flight control precision.

A fixed-structure vertical takeoff and landing aircraft uses two independent flight control systems to switch between multi-rotor and fixed-wing modes.

Cambered airfoil structures eliminate anti-icing systems by using concave top surfaces to prevent ice accumulation, reducing weight and complexity.

Hollow fiber-reinforced plastic reaction links suppress buckling deformation while maintaining tensile strength for lighter aircraft actuators.

Segmented pivot systems with bearings separate stationary engines from rotating wings, resolving fluid management complexity in tiltwing aircraft.

Inlet and exhaust ports in the wing structure channel airflow to cool the hydraulic apparatus, suppressing temperature increases during continuous operation.

Segmented wing chambers isolate wiring from landing gear interference, enabling dedicated fuel storage volume.

Integrating electronics into sandwich structures reduces production time while maintaining secure component installation.

Aircraft elevator variable feel unit uses a single cam and roller mechanism to adjust control column resistance.

Single-part composite skin spans aircraft mid-box lifting surfaces from tip to tip, eliminating central joints and reducing weight.

An intermediary spacer maintains accurate spacing between hinge ribs during installation, reducing structural complexity and enabling in-situ maintenance.

An air vehicle uses a movable wing control surface and additional actuator to optimize lift and drag while minimizing system weight.

Sliding wing structure adjusts center of gravity to reduce horizontal stabilizer size and minimize aerodynamic drag.

Mechanical linkage between high-lift devices and tilting HTP increases lift coefficient, reducing aircraft weight and drag.

Auto throttle computer computes second derivative of pitch angle to anticipate mountain wave disturbances and stabilize aircraft speed.

Merging three electric stages into one integrated unit reduces throttle lever space while preventing runaway extensions through computer verification.

Single autoclave curing joins structural components via adhesive bonding, reducing rivet weight and assembly time compared to traditional multi-step methods.

A rotor assembly with collective pitch control generates variable thrust output at constant rotational speed.

Rearward wing intakes ingest boundary layer air via distributed electric fans, resolving fuel consumption complexity trade-offs.

Repositioning tail control surfaces in wake-free zones resolves interference from lift components that reduces reliability and control effectiveness.

Separate ground latch device holds foldable wing tip in place, reducing actuation unit complexity while ensuring reliable positioning.

Centralized differential locks and redundant brakes detect position deviations to stop unwanted flap movement without wing-end hardware.

A carbon fibre-reinforced plastic intermediate part joins lateral stabiliser boxes via riveted flaps and integrated fitting plates.

Heat shielding member blocks radiant fire wall energy while guide member channels rising air to maintain pivot bulkhead temperature within allowable limits.

Lug and clevis connections replace confined space joints in the horizontal stabilizer assembly, simplifying manufacturing and improving scalability.

A counterweighted aerodynamic control surface passively deflects to oppose wind gust loads on aircraft panels.

Electronic strain gauges replace bulky mechanical jamming mechanisms to detect load path failures without increasing actuator weight or volume.

A fuel jettison system manages independent tank discharge to maintain aircraft balance.

A control device translates pilot commands into acceleration setpoints for hybrid aircraft propulsion and rotary wing systems.