Fuselage Frames TRIZ Cases

A non-cylindrical blended wing body uses stiffeners, skin, and bulkheads to resist cabin pressure while cutting drag, weight, and volume loss.

Selective vacuum on covered movable pallets supports composite stringer layup while exposed pallets stay at ambient pressure to cut leakage.

Circumferential flanges and force-fit fasteners let fuselage sections open for tank installation while maintaining continuous load transfer.

Circumferential flange joints replace heavy tank doors, enabling continuous load transfer and faster hydrogen tank installation in aircraft fuselages.

Airtight layers and a porous insulating core route cabin air without riser pipes, cutting aircraft insulation weight, cost, and installation complexity.

A movable door in an anti-sloshing tank wall suppresses liquid hydrogen sloshing while preserving large access for aircraft tank inspection.

Separated aircraft sections enable parallel boarding, maintenance, and remote hydrogen refueling while guided docking preserves coupling integrity.

Expandable inserts and external hollow stringers help composite space structures resist compression and debris impact without adding weight.

Angled and rounded stringer edges improve load transfer, seal skin joints, and reduce moisture-driven delamination in composite structures.

Humidity sensors and openable drainage ports keep aircraft insulation blankets dry, limiting weight gain and preserving thermal and acoustic comfort.

Thin carbon plies and a stiffening framework let an aircraft panel work reliably in the post-buckling regime while cutting weight.

Thin carbon plies and a stiffening framework let aircraft panels operate reliably in post-buckling while cutting weight up to 30%.

Adjusted tow tension and lower compaction pressure let AFP lay composite skin over unsupported stringer or frame slots without mandrels.

Parallel charge forming stations and conveyors cut composite stringer manufacturing time and floor space while improving contour consistency.

Linear composite frame members are joined along a curved path to support panels with less wrinkling, waste, and manufacturing cost.

Spaced web sections and chord members enlarge center wing box access while limiting corner strain and preserving load-bearing strength.

A flexible lumen-based collector drains ceiling condensation from aircraft cabin modules, reducing custom parts, weight, and installation complexity.

Corrugated C-channels and stanchion fittings enable progressive collapse in fuselage sub-floor columns, improving crash energy absorption stability.

A dual-mounted cover bridges the lining-monument gap, preserves sealant function, and allows millimeter-level monument placement flexibility.

A belly-mounted pneumatic speed brake uses stored air, springs, and a magnet to improve low-speed control and rapid airspeed deceleration.

A tapered wing rib interface smooths wing-to-fuselage transitions, cutting eccentric loading, drag, and reinforcing weight.

Segmented composite charges and normal-force compaction on a curved layup tool speed stiffener forming at ±45° and 90° orientations.

3D-printed temperature-resistant bases cut die weight, cost, and heat loss while heated forming plates speed vehicle cabin panel forming.

Slit regions in continuous composite fibers enable press forming of complex aircraft parts without autoclaves, cutting time and labor.

AFP-placed filler plies form and heat-consolidate radius gap fillers, improving stiffener positioning while reducing handling and tooling.

Deformable additional frames and corrugated absorbers smooth crash loads in a fuselage section to protect structure, occupants, and fuel tanks.

A removable top fuselage panel with anchor points lets aircraft fuel tanks be hoisted out efficiently while preserving structural continuity.

Paired dies and a tool lid create one curing chamber for composite blade stringers, reducing tool transfers, cycle time, and formation inconsistency.