Fuselage Frames TRIZ Cases

Flexible frame members bend to expand the fuselage for wing storage, resolving contradictions between road usability and flight aerodynamics.

A composite stringer base flange merges skin flanges and webs into a continuous structural connection.

Segmented fuselage segments with protrusions enable LD-3 container placement without increasing aircraft weight or degrading aerodynamic efficiency.

A splice assembly replaces the defective aft portion of a Cessna tail-cone reinforcement angle to restore structural integrity.

Tailored mandrel geometry accommodates in-plane changes to eliminate ply wrinkling and maintain structural integrity during fabrication.

Directional stiffness in the isolation device reduces vibration transmission by five orders of magnitude, preventing imaging blur and equipment malfunction.

Pivoting the tail section vertically enables horizontal centering of the dome bulkhead, resolving tolerance compensation challenges during assembly.

Segmented modular cells with nested profiles enable in-field reconfiguration, reducing internal load demands and manufacturing complexity.

A co-curing method uses rigid mandrels on one side and flexible mandrels on the other to support composite stiffeners during manufacturing.

A pneumatic fastening mechanism elevates aircraft panels via fluid pressure changes to enable tool-free removal.

Multi-directional chopped carbon fiber gap filler matches thermal expansion rates to relieve stress at aircraft stringer interfaces.

Tension bars stiffen composite T-profile junctions to prevent delamination from out-of-plane stresses.

Reinforcing beads on the aircraft wing rib prevent deformation during drilling, maintaining precision without extra jigs.

Modular end rings and internal spoke supports maintain composite barrel geometry, reducing rework from shape deformation.

Elastic coupling isolates sensor frame from propulsion vibrations, preserving measurement precision while maintaining structural integrity.

Replacing vacuum bags, the caul plate creates a rigid vacuum seal with a mandrel to apply consolidation pressure, reducing material waste and labor costs.

Integrates bulkhead outer caps into aircraft skin, reducing fastener count by 30-50% while maintaining structural stiffness.

Prefabricated moisture diverting device captures condensate on aircraft support members, eliminating cabin dripping through preassembly.

Permeable fuselage walls reduce pressure drag and fuel consumption by allowing air flow through the central wing region during forward flight.

Robotic tape placement automates construction of layered composites, reducing labor and damage while filling voids.

Interstitial stiffeners introduce predefined buckling modes in vehicle beams, dissipating landing loads while maintaining lightweight structural integrity.

A detachable sealant mold attaches to an elongated aircraft structural part, forming a cavity that receives wet sealant for in-situ curing into a protective liner.

Channel-like main formers increase spacing between structural elements to resolve the trade-off between fuselage stiffness and window width.

A condensation-controlling insulation system uses an exterior absorption layer to retain moisture and release it as vapor.

A cable release mechanism detaches at a predetermined load, allowing the curtain to drop and equalize pressure without heavy structural members.

Segmented vacuum phases remove gas before melting, preventing porosity in thick thermoplastic composite panels without autoclave equipment.

Three-dimensional sound absorbing panels utilize additive manufacturing to create custom acoustic geometries.

An open-channel stiffener aligns its shear center with the bondline edge to reduce delamination risks in composite structures.

A convertible aircraft system uses lockable rotation mechanisms to transition between helicopter, airplane, and gyroplane configurations.

Monolithic compliant panel absorbs bird strike energy via deformation, reducing weight by 27 kg and simplifying manufacturing.

Concentric rail routing clusters forming stations to boost production rate while reducing factory floor space.

A composite ramp employs a triangular prism to transition between steep and gentle gradients, enabling automated tape lay-up without weight penalties.

A Modular Isotropic Lattice Extruder System assembles discrete cellular lattices through interlocking elements.

Clevis and lug fastening system with hinge unit transfers wing loads while maintaining aerodynamic efficiency.

A flexible cable connects aircraft floor and hull structures to withstand 9 g forward acceleration loads.

A CFRP fuselage connector arrangement uses a slidable underlay device within a guide groove to absorb mechanical energy through controlled hole-bearing failure.

Fiber-reinforced plastic aircraft shell segments use hybrid bonding with inclined reinforcement elements to secure stiffening structures.

Open frames paired with closed stringers increase buckling strength while simplifying composite manufacturing.

Converging non-parallel faceplanes tilt the rear fuselage upward, preventing ground strikes during takeoff without adding weight or modifying landing gear.

Concave reinforcement lines on a domed fuselage body achieve high stability and low weight by optimizing load distribution.

A composite splice bridges fuselage sections using an H-shaped fitting and shear tie to reduce assembly time.

Orienting reinforcing fibers at specific angles within composite stringers increases stiffness while suppressing ply splitting.

Asymmetric tendon placement prevents resonant oscillations in aircraft wing spars, extending service life.

Segmented end caps seal open composite stringers to prevent moisture ingress while eliminating costly precise bevel manufacturing.

Dual shafts with gear form couplings enable spherical rotation, resolving misalignment issues in traditional face gear designs.

Bar on insulating blanket supports systems to avoid structural holes.

Internal open spaces enable uniform thermal expansion of an elastic mandrel, preventing cavity shape distortion and uneven pressure on composite layups.

Co-infused fiber preforms create unitized composite structures with smoothly transitioned stiffener runouts.

A composite tube assembly uses a locking collar nut and jam nut to secure metallic end fittings without bonding.