Wings TRIZ Cases

Solar-driven Stirling propulsion cuts aircraft CO2 emissions while thermal storage extends flight beyond daylight hours.

A protruding installation tool lets engineers position and secure aircraft bulkhead connectors from one side, avoiding fuel tank entry and damage.

Spherical-bearing joining members let the wing-fuselage joint pivot and translate, reducing bending moments while speeding assembly and disassembly.

Controlled Al-Cu-Li composition and hot-working conditions deliver low-density underwing stock with high strength, toughness, and fatigue stability.

Spherical-bearing wing-fuselage joints transfer shear loads while minimizing bending moments, simplifying fuselage structure and speeding assembly.

A sealed bag lets flowable shim material fill large joint gaps evenly, then cure with aligned fastener holes and less waste.

A rounded reinforcement conforms to concave laminated edges to spread loads, resist peel forces, and prevent delamination with smaller fasteners.

A profile-matched partial repair stringer reinforces damaged hat stringers while reducing weight, material use, and assembly complexity.

Controlled Al-Cu-Li composition and heat treatment raise wing-skin strength while preserving fracture toughness, fatigue resistance, and low density.

Flexible edges let an aircraft corner piece absorb wall geometry variation, removing machining and shims while maintaining a fluid-tight seal.

Sliding latches and strikes join composite panels without adhesive, cutting assembly time, waste, overflow, and panel bulging.

Freely pivoting thrust subunits balance opposing torque to maintain multirotor attitude under gusts without complex actuators.

A mechanical slide lock with latches and strikes joins composite panels without adhesive, reducing assembly time and preventing bulging.

Indexed wing-panel assembly stations guide robotic shim installation at rib interfaces, cutting setup, inspection, and movement time.

A sealed bag compresses flowable shim material to fill joint gaps evenly, then cures into a solid layer that avoids voids and manual sculpting.

Pivotable wheels, lifting arms, and sensor-guided cylinders let one carriage transport and precisely place aircraft wings without bridge cranes.

A rotatable cargo pod and distributed thrust array let a VTOL biplane aircraft deliver payloads quickly over long range and deploy them precisely.

Independent suction and pressure fans adjust wing pressure locally to increase lift without heavy flaps, slats, or hydraulics.

An air bladder and strap preload wing panels against the frame, replacing temporary fasteners to cut drilling, rework, and assembly time.

Chamfered hole edges in composite members spread fastener loads, reducing stress concentration, delamination, and tensile strength loss.

A curved CF fitting and aligned shear retainer create a stronger rotor yoke load path when inboard bearings must carry higher centrifugal loads.

Stiffening ribs lock a fastener strap into shell channels to transfer tensile and compressive loads with less weight and faster assembly.

Laser welding forms inflatable deicer boot tubes without sewn stress points, improving durability, ice removal, and weather resistance.

A rotating shaft with an internal cable path lets the wingtip tilt between horizontal and vertical positions without cable winding or separation.

A secondary de-icing layer and heating body offset splice plate heat loss, keeping the aircraft inlet lip temperature uniform.

A secondary heater at splice plates offsets thicker lip sections, restoring uniform aircraft inlet de-icing and temperature distribution.

A split-leg aft landing gear creates venting pathways and a compact stowed footprint, enabling rapid VTOL aircraft deployment in tight locations.

A covered external leading-edge joint uses negative pressure in the joining gap to preserve laminar flow and simplify aircraft maintenance.

Integrated protrusions and adhesive-filled recesses strengthen aerospace adhesive joints, cut stress concentrations, and limit bond failure propagation.

A hand-formed adhesive-bonded doubler and tape restore damaged composite wing leading edges quickly without fasteners or specialized tools.

Segmented composite panels with bonded titanium ends simplify large skin manufacturing, improve joint consistency, and allow one-sided maintenance access.

Horizontal wing-pylon fastening with aligned bores, screws, and shear pins cuts joint height and frees space for larger engines.

A bonded protection ply on fuselage skin avoids manual tank-area sealant work, cutting installation time, contamination risk, and access issues.

Varying stiffness between filler sections helps composite radius fillers match surrounding structures, reducing cure distortion and fit mismatch.

Same-material photogrammetry targets are formed with aircraft structural elements, avoiding temporary attachment and removal while improving assembly tracking.

A split trunnion assembly mounts across the wing spar, supporting pivoting landing gear without a main gear beam.

Ribless wing channels move batteries longitudinally, supporting aircraft structure while reducing weight, drag, and access-hole challenges.

This case shows how wings integrated into support beams adjust during flight to improve VTOL aerodynamics and maneuverability.

Half-arrowhead joining elements eliminate minimum core thickness constraints, enabling solid rivet installation while preserving aerodynamic continuity.

Removably attached pintle supports allow composite materials in landing gear ribs, resolving single-material forging constraints.

Bending exposed ceramic fibers parallel to facesheets increases the physical bond area in composite structures.

Modular indexing and clamping blocks position stiffeners on composite wing skins, reducing manual handling time and preventing surface damage.

Segmented housing with trunnion brace opening enables direct shrink link connection, reducing weight and extending service life.

Hinge clamps fold composite charges to maintain tension, preventing wrinkles while avoiding complex active control systems.

Pressure sensors measure liquid pressure differences within the wing to determine its bending state, enabling real-time fatigue analysis and load alleviation.

Merged spinnion structure manages high bending loads from hingeless roters, resolving moment capability limits without adding excessive weight.

Segmented broad goods and multi-head automated fiber placement resolve single-head bottlenecks to increase fabrication speed.