Actuated Personally TRIZ Cases

Directional haptic seat cues reduce pilot tuning-out of visual and audio alerts while improving awareness of object location.

Variable force profiles let pilots feel inceptor mode transitions, reducing confusion and visual checking in fly-by-wire aircraft.

Distributed aircraft components add position- or velocity-based supplemental attitude to counter drift and avoid single-point fly-by-wire failure.

A single eVTOL inceptor replaces multiple cockpit controls, cutting weight and footprint while maintaining control through hover, transition, and forward flight.

Normalizing and prioritizing pilot, autopilot, voice, and remote inputs helps eVTOL flight controls stay operable with dissimilar command sources.

Consistent input mapping lets tilt-thrust aircraft transition between hover and airplane flight with lower pilot workload and fewer control errors.

Viscoelastic material inside the side stick gear cuts freeplay through axial compression, improving linear force feedback for pilots.

Shared 3D maps, obstacle data, and no-fly zone inputs let UAVs navigate without onboard sensors, cutting weight, volume, cost, and power use.

Rotating handlebars command synchronized yaw and roll, making aerial vehicle turns more intuitive while keeping momentum aligned with orientation.

Landing-phase load and blade pitch data are reused to auto-adjust rotor pitch for balanced vertical takeoff from sloping ground.

Supplemental attitude blending helps distributed flight controls counter drift from wind or sensor noise while avoiding single-point failures.

A single hand controller combines multi-axis flight control with vibration and visual obstacle alerts to simplify piloting and reduce collision risk.

Distributed aircraft components combine attitude with position or velocity supplements to resist drift and avoid single-point control failure.

Floor-mounted rocker pedals use vertical foot motion for rotorcraft yaw control, reducing lumbar loading while preserving precise response.

Consistent input-to-effector mapping across hover and airplane regimes cuts pilot workload and modal confusion in tilt-thrust aircraft.

A homokinetic universal-joint chain lets aircraft rudder pedals adapt to pilot size while preserving reliable yaw and braking control.

Pedal-driven tail rotor RPM control lets helicopters boost anti-torque speed beyond main rotor RPM for better stability and maneuverability at altitude.

Dual rudder shaft assemblies keep trim feedback and pedal resistance after a pedal link failure, reducing unwanted rudder changes and pilot workload.

A controller coordinates rotor thrust and control surfaces by speed and input orientation to smooth VTOL transitions and maintain balance.

An armrest-based cockpit inceptor separates yaw, pitch, and roll inputs to reduce axis coupling while removing rudder pedals.

Lateral armrest displacement separates yaw from wrist-driven pitch and roll, reducing axis coupling and removing pedal hardware.

A movable side or front element adds graduated input to one aircraft stick, simplifying yaw, pitch, and roll control.

Separate yaw, pitch, roll, and braking controls add cockpit complexity; an integrated stick consolidates these inputs and reduces installation weight.

Multi-axis actuator adjustment and ball-joint rolling motion adapt the armrest to users, reducing fatigue while improving control precision.

A movable bracket and guide rail reposition mission equipment on an aircraft console, reducing visual and physical obstacles during use.

This case uses two universal joints in the rudder bar drive train to transmit pedal motion while supporting reliable yaw control.

Selector lever pivots on a shaft unit guided through redundant optoelectronic sensor units for precise position detection.

Torque sensors and evaluation units detect jamming or misalignment in aircraft high-lift systems, replacing heavy mechanical limiters.

Dynamic priority switching resolves conflicting rudder pedal and handle commands, ensuring reliable emergency maneuver execution.

A panel-mounted control stick uses bellcranks and spool bearings to translate pilot inputs into aircraft pitch and roll movements.

Flight control logic manages pilot and co-pilot sidestick inputs to establish sole command authority through priority arbitration mechanisms.

Ball ramp assembly multiplies pilot brake triggering torque to engage the primary brake, delivering high capacity within a compact wing envelope.

Controller compares commanded and actual flap positions to detect discrepancies, enabling precise fault isolation without blind system shutdowns.

Flight controller initiates reverse torque commands to generate braking thrust, eliminating separate aerodynamic brakes and reducing aircraft weight.

A bank limit indicator displays safe maneuvering angles on flight instruments using real-time airspeed and sensor data.

An integrated electronic wall in a hybrid rotorcraft handle consolidates thrust controls, reducing cockpit clutter while maintaining precise pitch management.

A dual-section control yoke manages aircraft parachute and chassis functions through independent translational and rotational movements.

An alarm system monitors rudder bar position to detect extreme rotations and verify neutral return, alerting pilots to inappropriate maneuvers.

Intermediary spacers inserted into pedal housing slots prevent rearward movement, resolving safety risks from accidental pedal actuation.

A semi-permanent interface mount secures a mobile computer protective case to an aircraft yoke using an AMPS hole pattern plate.

Electronic controller processes touch signals from selector lever handle to prevent unintentional movement and display control surface positions.

A trim adjustment device converts designated values into minimum units using dynamic rate and click time for precise control.

Visual yaw feedback indicators guide pilot rudder inputs to correct deviations from the runway centerline during V1 cut maneuvers.

A static reference resolver circuit generates matching analog outputs using a transformer to replicate primary sensor signals.

A pivoting grip portion with a cam-actuated lock mechanism secures the control stick in a deployed position.

A sliding rudder bar assembly enables independent pedal positioning for rotary wing aircraft pilots.