Aircraft Power Plant Components TRIZ Cases

See how flexible hollow tubes of varying lengths attenuate ultra-low-frequency sound below 300

Curved wing diffusion members and distributed electric lift fans improve thrust control and reduce forward-flight inefficiency in VTOL aircraft.

A T-shaped chassis mounts the motor, fuel cell, tank, and cooling system externally to preserve strength while improving maintenance access.

A T-frame mounts the motor, fuel cell, tank, and cooling system for side access, reducing maintenance complexity in aircraft propulsion.

Movable engine placement and interconnection shafts cut drag and wing bending while preserving convertiplane redundancy and deployment flexibility.

A spring-loaded bell keeps the hook and pin in intimate contact, reducing manual adjustment and maintaining secure latching under vibration.

Laser-drilled perforations in a coated composite nacelle inlet deliver anti-ice liquid, avoiding bleed-air heating and reducing power use.

Skewed friction discs in a clutch and no-back unit tailor torque for cowl door loads, preventing runaway failure and easing actuator sizing.

A rotatable ferrule and stop mechanism locks telescopic cowls in the retracted position despite pressure and temperature variation.

A multi-pivot latch linkage secures aircraft cowls more reliably and still allows easy release under high aerodynamic loads.

Multiple die cavities and inert-gas vacuum forming shape nacelle bulkhead segments with more uniform thickness, less necking, and higher throughput.

A multi-pivot long-throw latch improves aircraft cowl closure by increasing hook travel for secure keeper engagement and easier handle release.

A ball housing and friction clutch limit motor shaft speed during power loss, allowing aircraft doors to close without uncontrolled retraction.

Femtosecond laser texturing creates a superhydrophobic aircraft composite surface that prevents downstream water adhesion, frost, and ice.

Corrugated ribbon cores with stamped reinforcements help thin acoustic panels attenuate low-frequency engine noise without losing rigidity.

Micron laser-drilled perforations in a CFRP-metal nacelle lipskin deliver anti-ice liquid without bleed-air power draw or pneumatic complexity.

A nacelle lock indicator uses key withdrawal to confirm cowl locking without software or signal-conveying systems, cutting mass and complexity.

Camera-scanned perforation patterns guide CNC drilling of nacelle repair patches to preserve acoustic alignment and noise attenuation.

Integrated composite plenums and suction perforations make active laminar flow control more manufacturable while reducing drag and panel weight.

Key removal mechanically switches the nacelle lock indicator, avoiding wiring and signal processing while improving pre-takeoff lock checks.

A guide ring and immobilized shaft enable one-sided aircraft cowl pivot assembly while avoiding radial stress on clevis branches.

A co-cured composite panel integrates plenums, perforations, and suction to remove boundary-layer air, cut drag, and reduce ALFC complexity.

A corrugated ribbon core with stamped reinforcements forms thin acoustic panels that attenuate low-frequency engine noise without losing strength.

Camera scanning and CNC drilling match replacement patch perforations to the original acoustic panel, preserving nacelle noise attenuation.

A mandrel and dozer-block stretch forming process creates double-curved thrust reverser skins with lower cost, weight, and assembly complexity.

A two-stage punch and die process forms angular droop nacelle leading edges while reducing tooling complexity, spring back, and cost.

Radial dies and vacuum superplastic forming shape multiple nacelle bulkhead segments with uniform thickness while avoiding necking and weak points.

Camera-guided CNC drilling matches replacement patch perforations to the original panel pattern, preserving nacelle acoustic performance after repair.

An offset-axis punch and die form nacelle leading edges with angular droop while reducing tooling complexity, spring back, and heat-treatment steps.

Double-walled metal plates are vacuum welded into a hermetic enclosure that cuts heat transfer while preserving long-term strength.

A guide ring, stops, and rotation lock secure an aircraft cowl pivot shaft from one side while avoiding radial stress in yoke branches.

An outward-angled pylon fairing reshapes flow at the wing-engine junction to cut interference drag and shock-induced separation at high speed.

A nested dual-handle latch improves nacelle cowl access and ergonomics while maintaining secure closure with lower complexity and drag.

A temperature-responsive shape-memory seal closes nacelle exhaust ports when de-icing is unnecessary, cutting drag and acoustic disturbance.

Pre-bonding the intermediate structure to the first skin raises compressive strength, enabling automated draping of oblique-cavity acoustic panels.

A spaced structural frame and porous resistive skin improve thrust reverser blocker door impact tolerance, acoustics, weight, and cost.

A remote drive rod, control handle, and lock collar make thrust reverser latches easier to access while keeping eye bolt engagement secure.

A variable-radius nacelle fillet stabilizes wing flow at high angles of attack, raising stall margin while avoiding strake drag and icing.

A spring-biased lever lock keeps an aircraft cowl latch closed under vibration, preventing unintended unlocking in severe flight conditions.

A fluidic ejector uses Coanda surfaces to entrain ambient air for efficient low-speed lift, cutting energy use and extending UAV and VTOL flight time.

A shape-memory shut-off closes nacelle exhaust orifices outside de-icing phases, cutting parasitic drag and acoustic noise.

Segmented nacelle inner sections use latches to preserve structural integrity while improving thrust reverser access, airflow continuity, and maintenance.

A weak secondary connector lets the engine cowl swing outward in a fan blade off event, absorbing impact loads without a heavier nacelle.

A fixed main wing and tilting auxiliary wing reduce transition energy, hinge strain, and control complexity in VTOL aircraft.

A drive-link and drag-link latch with built-in stops makes aircraft nacelle cowls easier to open while reducing complexity and over-rotation damage.

Infrared-transmitting lip walls let a nacelle de-icing source melt ice on inner and outer surfaces with lower energy use.

A Coanda-based fluidic propulsor entrains ambient air and prevents flow separation to boost VTOL lift efficiency and payload capacity.

A liquid ice protection plenum moves forward in the nacelle inlet, freeing space for a longer acoustic panel and lower noise.

A grooved flex zone in the nacelle junction flange absorbs fan blade off deformation energy without added brackets or harder assembly.

A pressure relief latch uses a spring-loaded roller and keeper to secure closure while allowing manual handle operation.