Undercarriages TRIZ Cases

Pivoting support aligns landing gear rollers to resolve assembly tolerance issues.

A retractable landing gear uplock uses reversible electromagnets and permanent magnets to secure the stowed position.

Replacing hydraulic pipework with an electric motor reduces weight and eliminates fluid leakage risks in aircraft landing gear systems.

Segmented rear door uses independent drive mechanism to open orifice for air escape, preventing flooding during front door operation.

Inboard sidestay assembly with shear web transfers landing gear loads via multiple paths to reduce wing attachment forces and simplify retraction.

Nested cylinder structures switch a flight vehicle landing gear between stowed and released states, eliminating frequent replacement costs from deformation.

Integrating a single linear actuator into the breaker strut eliminates multiple actuators, reducing device complexity and weight while stabilizing the gear.

Unlock actuator anchors to stay element for single-direction load, eliminating sequential control and additional hard points.

Aperture guides rod pivot beyond non-aligned position, eliminating overtravel and complex sensor logic during landing gear retraction.

A hydraulic transfer device compresses the strut independently of the retract actuator.

Coupling lever with preloaded spring absorbs force feedback stress during deployment while transmitting lifting forces.

A hook member and actuator lock landing gear in a stowed state without an energized latch.

Directional frangible connections enable tailored detachment forces based on impact direction, protecting the fuselage and wing from damage.

Pivoting landing gear leg deploys away from housing during emergency impact to absorb energy and prevent cabin intrusion.

A hydraulic shrink landing gear uses a transfer cylinder to exchange pressurized gas and fluid for controlled retraction.

Transverse strut mechanism with universal joints retracts aircraft landing gear laterally, reducing box height and weight.

A landing gear assembly shifts spring anchor points via a lost motion mechanism, reducing down locking spring extension and weight.

Torsion spring in aircraft landing gear absorbs loads and maintains deployed position, replacing oleo-pneumatic shock absorbers to reduce maintenance needs.

A decentralized electrohydraulic drive unit controls landing gear functions using a single electric motor and hydraulic pump.

An articulated brace retracts into the compartment to resolve the contradiction between leg rigidity and available aircraft interior volume.

Plunger-clevis locking mechanism prevents wheel jamming in shrunk landing gear configuration.

Landing gear control system rotates wheels to match ground speed, reducing tire impact damage and debris dispersion during aircraft landing.

An extendable tailwheel strut retracts a ventral fin portion to reduce aerodynamic drag while maintaining rotor clearance.

Repositioning the brace joint near the wheel lowers bending moments and eliminates torque arms.

An external spring support prevents broken down-locking springs from entering critical spaces and jamming the mechanism without adding significant weight.

An intermediate fastening device transfers landing gear loads to the aircraft fuselage via a central box structure.

Facing webs in landing gear structural parts transmit forces while reducing mass through optimized material distribution.

Reordering avionics side changeovers after gear movement minimizes deployment time, reducing drag and fuel consumption.

A pivotally coupled fairing shields landing gear components from airflow while deflecting debris propelled by wheels.

Nose landing gear integrates lifting fulcrum and steering means on a rotating tube to reduce volume and mass.

Strategic two-force member coupling redirects non-normal loads into normal forces, preventing lug displacement in lightweight composite strut tubes.

Positioning a streamlined torque arm forward of the shock strut diverts airflow and reduces turbulence, lowering noise generation during aircraft landing.

Strut gas pressure isolation valve bleeds off internal gas to reduce high load forces and prevent inadvertent extension.

Anticipatory hatch opening reduces apparent maneuver time by executing initial steps before manual activation.

Sliding bearing redirects strut loads to the fuselage, eliminating wing spar reinforcement and reducing structural mass.

Curved stress relieving portions on landing gear trunnion arms manage stress concentration to minimize weight and enhance durability.

Replacing hydraulic actuators with an electromechanical system reduces weight and noise while eliminating fluid leakage risks.

Mounting obstacle detectors on landing gear struts provides 360-degree detection coverage, resolving visibility blind spots during aircraft ground operations.

Lateral folding linkage minimizes nose landing gear bay volume while maintaining structural restraint.

An electrically activated landing gear control system uses proximity sensors and command signals to manage valve actuation.

A rotary actuator pivots a stabilizer rod to unlock the locking member and lift the undercarriage.

A cam plate, hook, and follower mechanism locks landing gear in a stowed position.

Articulated lock mechanism with upper and lower links locks landing gear in extended or retracted positions, reducing component count.

A non-jamming shrink latch mechanism uses rocker arms and a detent to secure the strut piston during retraction.

Dynamic attachment resolves indeterminate load distribution by switching between three-point and four-point configurations.

Spring blades buckle under axial compression to maintain alignment, reducing actuator force and weight compared to coil springs.

Segmented movable panels follow a predetermined kinematic law to avoid wheel interference while maintaining aerodynamic continuity.

An attachment system connects landing gear to aircraft bays using pre-aligned elements inserted from a single direction.

Non-parallel rotation axes fold the landing gear laterally within fuselage boundaries, eliminating protruding enclosures that increase aerodynamic drag.