Aircraft Power Plants TRIZ Cases

A UAV controller rotates rotors at a preset speed lower than hover velocity to initiate stable flight.

Dynamic fuel scheduling dampens thermo-acoustic instabilities without adding structural weight.

A gas-generating substrate produces buoyancy by reacting with liquid to capture on-demand gas.

Distributed arbitration in electronic speed controllers eliminates single-point arbiter failures, maintaining system reliability and reducing design costs.

Flight control system synchronizes propeller pitch transition to prevent thrust asymmetry and reduce yaw moments during landing.

A control unit calculates velocity to never exceed using actual aircraft weight and altitude data.

Image recognition systems overlay configuration instructions on displays to resolve manual checklist bottlenecks and reduce setup errors.

Aircraft cabin blower system uses a toroidal continuously variable transmission to drive the compressor.

A control unit generates a variable speed setpoint for a rotorcraft main rotor based on ambient air density.

A multirotor control system dynamically reconfigures rotor inputs using a real-time control effect matrix.

A disable processor monitors throttle levers to prevent auto throttle disengagement during uncommanded movements.

Aircraft engine control channels broadcast data simultaneously across two independent buses to increase communication throughput.

Dynamic speed adjustments based on holding time analysis reduce fuel consumption and delays during airport approach operations.

Segmenting control logic into remote modules reduces wiring harness weight and assembly time while maintaining real-time processing reliability.

Parallel propellers on linear supports improve reliability and endurance by maintaining flight capability after individual motor failures.

Aircraft engine exhaust gas temperature margin monitoring uses signal smoothing to isolate wear trends from servicing noise.

Dual-loop feedback control system combines airspeed and inertial velocity signals to minimize longitudinal accelerations caused by turbulence.

Anticipatory shroud expansion prevents blade rubs during throttle changes, reducing fuel burn and enhancing engine efficiency.

Varying motor RPM around a target value reduces tonal noise annoyance while maintaining flight stability through dynamic feedback.

An icing detector monitors the time rate of change in helicopter rotor RPM trim signals to identify ice accumulation on blades.

A dynamic equivalent circuit model adjusts parameters based on operational data to resolve prediction accuracy issues under high discharge rates.

Replacing heavy synchro-trigonometers with digital sensors reduces device weight and complexity while maintaining measurement precision.

Dynamic engine rating selection adapts aircraft power output to current flight conditions.

Barometric altimeter data verifies radio altitude against ground elevation, preventing premature throttle retardation from sensor errors.

An assisted piloting mode maintains engine parameters below predetermined thresholds when the primary limit indicator fails.

Aircraft drive motor control system adjusts torque levels based on power and rotation speed signals to ensure smooth wheel movement.

A rotorcraft control unit adjusts drive speed based on ambient temperature to manage blade surface conditions.

Motor-driven lever replaces mechanical friction with electronic torque control, eliminating wear while maintaining traditional feel.

Detects engine control lever position anomalies during aircraft landing, triggering warnings for thrust dissymmetry that prevents runway deviations.

Dynamic thrust ramping adapts to crosswind thresholds, reducing engine wear and enabling heavier payloads on shorter runways.

A controller adjusts rotor tilt and pitch using pad-mounted force sensors to stabilize lift during ground transition.

An avionics controller circuit compares expected flight performance parameters with current sensor values to adjust ownship operation settings.

A multi-engine bay control system evaluates engine damage to adjust functional limits and maintain thrust.

A multi-rotor UAV uses coaxial contra-rotating propellers on one arm to maintain stability and yaw control after a single arm failure.

Dynamic fuel adjustment tracks rapid rotor speed changes during aggressive maneuvering by modifying supply based on real-time measurements.