Spars/Stringers TRIZ Cases

A composite torque box sleeve forms a continuous airfoil surface to reduce structural weight in aircraft wing assemblies.

Real-time distance detection allows a robotic peening device to adjust nozzle orientation, ensuring accurate shot placement on deforming aircraft parts.

Unbalanced composite skin couples twist and bending to alleviate root bending moments, reducing weight without active systems.

Release film resists shear forces on multi-lane tows, preventing fiber distortion and reducing material waste.

Applying variable tension along the web height prevents wrinkling during fabrication, allowing tighter curvature without compressive stress.

Co-cured sacrificial members on composite spar flanges eliminate manual shimming to resolve assembly time and fit contradictions.

Aligning fastener holes with the web center plane reduces the number of required fasteners and lowers aircraft weight.

An inclined spar joint configuration enables direct assembly of aerodynamic boxes without solid shims.

Titanium alloy pi chord securement member joins graphite fiber epoxy laminate composite layers for aircraft structural attachment.

Co-cured hat-shaped core structure reduces warpage and noodle cracking in composite wing panels.

Inserting a tapered rib into a composite cavity eliminates mechanical fastening, reducing weight and fabrication time while maintaining structural integrity.

Transition spars link staggered wing spars in a virtually spanned plane, eliminating structural kinks and reducing constructional complexity.

Segmented end rib assembly directs airflow to absorb noise, resolving the trade-off between structural complexity and acoustic performance.

An injection molded wing structure encases a pre-assembled frame with an air-filled matrix material to provide torsional rigidity.

A caul plate groove accepts a tool to slide the plate laterally, avoiding delamination from forceful prying.

A variable radius assembly uses a spindle and guide member to drive non-linear tension changes in structural struts.

Mandrel expansion presses flanges against webs during co-infusion, reducing manufacturing costs while preventing wrinkling in aircraft fuel system vents.

Rigid lateral forming tools shape outer spars during curing, eliminating inner tool extraction and achieving ±0.1 mm tolerance.

Welded thermoplastic fasteners secure wing covers without protruding rivets, preserving aerodynamic tolerances and enabling modular maintenance.

Aluminum stiffeners on carbon fiber rib webs resolve thermal mismatch with wing boxes while reducing weight.

Segmented CFRP planked stringers with aligned fiber orientations reduce wing weight while avoiding design complexity from metallic paradigms.

Embedded fluidic networks create asymmetric deformation fields within elastic structures to counteract external forces.

Stepped lower skin surfaces eliminate rib shimming gaps while thick-walled bases secure stringer connections for improved manufacturing precision.

Bonded splice joints replace heavy mechanical fasteners with adhesive connections, reducing weight while maintaining load distribution across the fuselage.

Co-cured sacrificial flanges on composite spars provide conformal contact surfaces for aircraft skin panels.

Flexible shear ties eliminate shims in wing box assembly, reducing weight and production costs while maintaining structural stability.

A monolithic wing spar integrates a distinct strut to enhance structural rigidity and stress distribution within the aircraft wing assembly.

A lifting structure deforms elastically to adapt its profile passively in response to fluid flow orientation changes.

Segmented jury struts distribute buckling loads along the wing strut member, reducing vulnerability to engine rotor bursts and bird strikes.

Aircraft wing configuration member divides into regions using high strength and high elasticity composite materials to optimize structural rigidity.

Overlapping pi preforms secure aircraft skins and spars, reducing assembly sensitivity while maintaining structural rigidity.

Backup fitting assembly transfers drag loads in-plane via intercostal members, reducing out-of-plane forces on composite rear spars.

A rotor blade closeout structure integrates fluid channels to supply differential pressure for actuating trailing edge devices.

Struts transfer transverse bending forces from a pivoting oblique wing to the fuselage, resolving strength-versus-adaptability trade-offs.

Curved tie elements in aircraft flow body torsion boxes reduce interface loads at corner regions by providing resilient deformation along the connection line.

An assembly line shuttle uses adjustable pogos to enforce wing panel contours during structural component installation.

Adjustable tooling shapes composite wing laminates, resolving the trade-off between structural strength and manufacturing ease.

A pre-cured laminate rib assembly integrates honeycomb panels and skin flanges to simplify aircraft wing construction.

Extracting resilient inserts from cured composite junctions eliminates filler defects and reduces weight while simplifying non-destructive testing.

Linear alignment of spar front and strut rear surfaces increases engine ground clearance while maintaining structural load paths.

Continuous composite fiber winding creates truss ribs with integrated gusseting plates, reducing assembly time and improving load transfer capability.

Optimized zinc-magnesium-copper alloy composition resolves the trade-off between compressive strength and fracture toughness in thick wing spar components.

Continuous curvature eliminates kinks and fasteners, reducing weight and lightning risks while distributing loads evenly across wing structures.

Segmented planked stringers merge with skins via co-curing to resolve weight versus manufacturing complexity trade-offs.

A manual wing-fold mechanism uses shear pins and an extension tube to decouple outboard wing sections for storage.

A swing wing tip device pivots rearward using a receiving portion to nest the fixed wing skins and reduce aircraft span.

Adjustable connection members compensate for dimensional variations during airfoil assembly, eliminating time-consuming post-assembly rectification.

Integrated monolithic torsion box eliminates assembly complexity and fasteners while enhancing torsional rigidity for aircraft lifting surfaces.