Fluid-Pressure Actuator Safety TRIZ Cases

Captures fluid released during actuator reversal to prevent hydraulic lock, reduce shock, and reuse decompression energy in the next stroke.

Digital control opens high-load pressure compensation valves fully, then switches to mechanical backup if sensors fail to keep flow stable.

A single spool and one compression spring create four valve positions, cutting parts and simplifying manufacture without losing switching capability.

A pilot hydraulic line with check, solenoid, sealing, and relief valves stabilizes aircraft mode switching while cutting weight and power use.

Two smaller hydraulic power packs use a backup valve so one unit can drive both main landing gears after a failure, saving weight and space.

A preloaded check valve uses pilot leakage to hold return pressure, enabling stable main slider position control across varying supply pressures.

Switch-selectable logic and multiplexed routing let one hydraulic valve actuator circuit support multiple modes without rewiring.

Threshold-based valve energization sets multiple hydraulic relief pressures while cutting power use and preventing pre-leakage.

A shared redundant control path lets two hydraulic actuators switch modes, cutting aircraft actuator weight and complexity without losing backup control.

Cyclic valve actuation enables online air bleeding in redundant hydraulic servo control, cutting downtime and contaminant buildup.

Unequal piston areas and a power-off fluid path let this PRSOV hold a defined valve position, improving anti-ice shutoff reliability.

An embedded digital twin compares simulated and real valve behavior to identify faults early and estimate remaining component life.

A pivoting two-axis safety stop blocks cylinder retraction during hydraulic failure without interfering with ball-jointed rod movement.

By aligning hydraulic reaction and lock-nut support forces, this ram assembly improves burst disc sealing and fatigue life while reducing leakage.

Oil property sensing identifies mineral, biodegradable, or mixed hydraulic fluid so diagnosis thresholds can prevent hydraulic part damage.

Dual pistons and controlled fluid paths keep valves opening or closing despite sand blockage, supporting reliable flow and fluid adaptability.

Backup-battery-powered solenoid bleed valves let operators lower and retract an elevated boom within a safety envelope after primary power loss.

Individual motor test intervals and pressure thresholds verify backup hydraulic pump readiness without misleading combined-drive results.

Using one pressure sensor, this air circuit detects unsynchronized solenoid valves and quickly exhausts residual pressure from an air cylinder.

Two fluidically linked 4/2 safety valves block drive activation unless both switch together, preventing uncontrolled motion and aiding diagnosis.

An integral check and electro-proportional valve hold cylinder pressure after hose rupture, preventing boom or arm drop while allowing controlled lowering.

Monitors piston travel time and operation count to detect actuator faults in real time without device-specific threshold setting.

A biased diverter shunts fluid back to the reservoir until manual actuation, preventing accidental tool-head operation and reducing operator injury risk.

Sensor-driven logic adjusts pilot-valve coil current during hose rupture to prevent actuator speed doubling and keep valve flow controlled.

A metering spool redirects hydraulic lines during pressure or control loss, returning aircraft control surfaces to an adjustable neutral position.

Motor shaft angle and drive current are used to infer spool position and detect sticking without adding a separate spool sensor.

Pressure-based diagnostics detect steering isolation valve state in real time without wheel movement, improving startup safety and fault coverage.

Multi-stage gas-oil cavities and valve cores relieve impact pressure quickly, buffering heavy loads to protect hydraulic supports.

An isolation valve, unloader valve, and orifice cut PTU breakout friction, leakage, back pressure, and overheating in aircraft hydraulic circuits.

A compact hydraulic valve block replaces complex crane emergency piping and manual valves to prevent leaks and uncontrolled movement.

Multiple small waterproof covers protect manifold-mounted electromagnetic valves without cover distortion or reinforcing ribs under hot wash water and steam.

An isolation valve assembly and pilot-actuated poppet valves vent residual outlet pressure, reducing motor-boating and enabling true zero pressure.

Operation time statistics such as average, variance, and skewness rank high-risk cylinders for early inspection and replacement.

Pressure-profile monitoring in the actuator supply line detects leakage, seal wear, and rising friction before valve failure.

Two smaller hydraulic power packs and a passive backup valve let one unit drive both main landing gears after failure while cutting weight and space.

A pressure-switching valve lets either redundant solenoid control the actuator valve, cutting EHSV weight and size while preserving failure-mode control.

A pressure sensor enables motor current only when cylinder pressure rises, while a fixed orifice limits setup speed with lower valve cost.

An integrated floating shut-off valve blocks hydraulic fluid loss after a cylinder supply line break while allowing limited emergency operation.

A flow restrictor and pump keep pipeline pressure below ambient at sensitive crossings, so breaches draw material inward instead of spilling oil.

A gate lock valve and proportional pilot control flag operator input during lock state to prevent unintended excavator actuator movement.

Differential pump pressure between unloading and on-load states reveals unload circuit faults and helps suspend unsafe hydraulic operation.

Repeated air pressurization warms leaking clutch actuator seals in cold conditions, restoring clutch function faster before vehicle takeoff.

Blocked-flow checks on pump speed, flow rate, and pressure isolate hydraulic circuit faults from main machine issues during pressure holding.

A pilot-pressure logic valve and de-energized solenoid enable stable emergency shut-off while preventing pump overload and fluid reflux.

Locks hydraulic pressure in actuator cavities during power failure so aircraft actuators hold the last commanded position under load.

A selection valve switches between opposite-bias EHSVs to maintain propeller pitch control after valve failure and extend auxiliary pump operation.

Three 3-way solenoids and a multi-head piston replace heavier EHSV control, cutting actuator weight, leakage, and failure risk.

A threaded wear pad with spanner holes and retaining bolts speeds in-situ shield base lift replacement while protecting the cylinder rod.

A proportional brake valve also invalidates operation devices, cutting valve count while controlling slewing brake release and parking brake force.

Parallel SOVs, isolating valves, and redundant shuttle valves keep fluid delivery running during valve replacement and bypass failures.