Fuselage Frames TRIZ Cases

Combines translational fixing and elastic contacts to eliminate separate plug connections in difficult-to-access areas.

Outward-facing flanges allow external skin attachment, eliminating interior access needs and reducing assembly complexity.

Flat and wavy prepreg portions transform into bent sections via forming die pressure, eliminating complex auxiliary yarns to lower production costs.

Suspended mounting mechanism with structure and component holders creates a rear gap for aircraft interior components.

Surface treatment forms liquid flow paths on aircraft panels to divert moisture, eliminating heavy separate devices that lose effectiveness under compression.

A wedge-shaped plug shatters hollow UAV structural members upon impact to disperse kinetic energy.

Through-fuselage columns transfer wing downward loads to the main landing gear, resolving the contradiction between structural strength and aircraft weight.

An asymmetric Y-shaped composite stringer resolves buckling resistance and torsional behavior trade-offs by maximizing moment of inertia per unit weight.

A flexible carbon fibre composite packer conforms to airframe surfaces to define a precise inner mould line, resolving Outer Mould Line tolerance challenges.

A particulate forming aid deposits spatially varying shear and tack on prepreg plies to enable controlled interlaminar slippage during composite draping.

Rod and ring stiffeners between skins eliminate adhesives, resolving weight and production complexity trade-offs.

A bidirectional electronic unit compartment enables symmetric module insertion via parallel connection faces and magnetic couplers.

An integration module attaches aircraft equipment and lines outside the fuselage before insertion into the technical bay.

Rotatable support members adjust roller axes to form variable curvature gap fillers, eliminating abrupt surface changes in aircraft stringer applications.

A hat-shaped stringer incorporates a recessed cap portion to position internal composite walls that reinforce the structure.

Transverse flaps join intersecting structural members to transmit loads, eliminating extra parts that increase weight and complexity.

A mandrel package manufacturing apparatus consolidates composite layups using vacuum pressure and radius fillers.

Segmenting the housing into distinct chambers allows independent maintenance of stacked circuit boards while improving heat dissipation.

A composite attachment ring segment connects a helicopter tail boom to the fuselage via longitudinal tension members distributed around its perimeter.

An inflatable bladder constrains the cap of a contoured composite hat stringer during forming, eliminating buckling and wrinkling defects.

Vertical stiffeners in a cellular core maintain structural integrity while resonating chambers attenuate low frequency noise without increasing panel thickness.

Spring-loaded fixing devices join transverse edges of plastic composite ceiling panels to prevent vertical offset between adjacent sections.

Automated continuous fiber placement eliminates manual splicing to prevent wrinkling and defects while boosting production rates for aerospace components.

A sheet entity joins carbon fiber and aluminum laminates via an insulating adhesive bond to form a stepped overlap joint.

Segmented sensor modules with standardized interfaces allow quick replacement of malfunctioning units, reducing aircraft downtime and fleet size requirements.

Three-dimensional woven composite preforms at fuselage cusps counter pressure loads and reduce weight without increasing structural complexity.

A movable gate adjusts the extrusion nozzle opening to shape polymer beads, eliminating voids in complex channels.

Mass elements in a sandwich structure slow shear waves to reduce noise radiation without adding weight.

Segmented rubber seals adapt to wing bending, blocking longitudinal airflow and reducing structural vibrations.

Merging discrete components into an integral bowl hull eliminates stress concentrations from kinked joints while reducing structural weight.

Angled component carrier reduces volume by tilting relative to the aircraft base plane, resolving space constraints without adding fastening complexity.

A composite stringer end trim uses curved radii to reduce bending and axial stiffness at the free edge.

Spanwise tapered stringer bases with web cutouts redistribute loads at the aircraft side of body joint.

An aircraft hatch ejection device uses a reversible articulated arm to mechanically separate the panel from the fuselage structure.

Automated optical scanning and feedback control adjust fuselage shapes, reducing manual labor and improving fit accuracy.

Co-cured perimetral and longitudinal reinforcing elements integrate with composite aircraft skin to maintain structural integrity around large openings.

Segmented aircraft wing structure with integrated spoiler and vent system reduces hub-and-spoke travel time by enabling direct point-to-point flights.

Integrated C-shape composite forms segregate hydraulic systems within multispar cells, reducing assembly complexity and manufacturing costs.

Segmenting composite spars into simpler curvatures reduces fabrication equipment complexity and cost while maintaining structural strength.

Segmented flexible members with visual indicators detect edge disbond locations while restricting crack propagation without autoclave curing.

Folding a beveled flat composite charge into a mandrel enables co-curing BVID treatments, eliminating post-cure trim operations.

Replacing internal rods with integrated stiffeners eliminates complex fitting while maintaining structural strength.

An air-cooling channel integrated into the airfoil mount dissipates heat through direct airflow passage.

Failure-initiating element applies lateral force to aircraft fuselage struts during impact to induce controlled buckling.

Man portable aircraft system uses modular wings and pylons for rapid in-situ assembly.

Thermal expansion of insertable pellets applies uniform pressure against cavity walls during curing, eliminating heavy removable tooling.

Segmented base body positions energy storage devices centrally within structural walls, resolving the trade-off between rotor clearance and maintenance access.

Segmenting the fuselage with local composite floors provides four-minute burnthrough resistance without adding weight or insulation mats.

Segmented ceiling panel with universal mounting elements resolves complexity-versatility trade-offs in aircraft cabin partitioning.