Power Installations TRIZ Cases

An electric taxi system drives the fan assembly via a low pressure shaft to enable controlled aircraft movement during ground operations.

A multi-configuration transformer adapts voltage levels across permanent magnet generators using selectable primary windings.

A variable cycle compensation system coordinates actuation and electric components to adjust engine thrust profiles.

An auxiliary power unit uses an excess air duct to route compressor outlet flow directly to the turbine section inlet.

A power converter monitor uses comparators and logic gates to detect voltage faults and generate inhibit pulses.

Selective connection mechanisms route power from hybrid generators to taxiing or aircraft networks, eliminating heavy ATRU modules and reducing onboard weight.

Non-conductive ventilation conduit vents hot gases while preventing electrical conduction and thermal damage to aircraft composite skin.

A harmonic regulator adds loop delay to stabilize power system control.

A hydraulic damping device uses a rotating blocking member to progressively cover damping holes within a plate.

An integrated energy-load assembly combines power and load components within a single accommodating box for unmanned aerial vehicles.

Suction-blow molding forms hollow three-dimensional thermoplastic ducts using reinforced PEEK, PPS, or PEI materials.

A fuel cell system uses an electrically drivable hydraulic pump to generate oxygen-depleted air and water.

Segregating primary electrical networks from cabin loads via dynamic conversion interfaces to maintain avionic certification standards.

Aircraft hydrogen propulsion system using a fuel cell and supercritical CO2 bottoming cycle to generate electrical power.

Integrated dihydrogen generator combines storage and conveyor compartments within a single enclosure to produce hydrogen gas efficiently.

Segmenting power via a flywheel battery supplies inertial acceleration current without increasing main unit weight.

Segmented fuel cell modules match local load demand, reducing energy transmission losses and improving overall system efficiency.

Electric tail rotor control replaces fixed mechanical linkages to optimize performance across flight phases while reducing setpoint overrun.

A capacitive sensing system detects fluid levels using a conductive plate and insulator.

A mount yoke assembly distributes forces across a larger area to secure auxiliary power units.

Segmented brackets and intermediary links distribute blade disengagement loads to smaller rubber bushes, reducing accessory gear box size.

Segmenting the control circuit board into an external casing protects it from vibration and impact while maintaining structural simplicity.

Segmented controller modules determine power allocation through local feedback signals, eliminating complex central coordination.

Solenoids pivot legs to clear a blocking pin, overcoming spring bias and frictional forces for reliable emergency power generation.

Cross-wing electrical drive lines balance torque during engine failure, eliminating yaw instability and reducing rudder authority requirements.

A conditioning system uses a pressure accumulator to manage hydrogen fuel volume variations and damping transient pressures.

A folded battery core uses nanocellulose fibers to create a lightweight cellular structure.