Automatic Braking Sequence TRIZ Cases

Automatic reverse idle arming uses landing-condition detection to trigger thrust reversers faster and reduce runway excursion risk.

Automatic touchdown detection triggers thrust reversers from reverse idle, cutting pilot reaction delay and braking distance on wet or short runways.

Conservative runway assumptions can distort landing indicators; this case uses runway and retardation data to improve distance estimates.

A brake system determines stack closure pressure using pressure transducers and a control valve to modulate fluid flow.

A brake de-selection controller calculates energy input from torque and wheel speed to selectively disable brakes.

Replacing mechanical interlocks with a digital graphical interface frees instrument panel space while reducing aircraft weight and maintenance complexity.

Automated processing circuit reduces pilot decision time by 2-4 seconds, preventing runway overrun accidents after engine failures.

Electro-hydraulic valves enable remote emergency park braking while reducing system weight through segmented power sources.

Electronic sensors replace qualitative verbal reports with quantitative braking data, eliminating traffic halts while providing accurate traction estimates.

A predictive braking method estimates taxiing brake temperatures to optimize path selection and reduce component wear.

An aircraft control module calculates deceleration distances for brake and thrust reverser configurations to identify the lowest total cost equipment setting.

Automated control module adjusts nose gear steering angle and braking force to prevent loss of adhesion during ground operations.

Automated control system manages aircraft taxi speed using real-time engine thrust adjustments to eliminate jerky deceleration and reduce brake wear.

Autobraking system maintains aircraft course stability by applying differential braking forces based on yaw error feedback.

Dynamic braking control reduces runway occupancy time and thermal energy generation by optimizing deceleration profiles against exit targets.

Dynamic braking force distribution manages individual brake temperatures to minimize aircraft turn-around time.

Brake control system sensors collect wheel speed and pressure data to generate objective runway condition reports for landing aircraft.

Normalized braking performance measurements replace subjective pilot perception, resolving accuracy inconsistencies in adverse weather.

Brake controller selects accurate deceleration rates from avionics and wheel sensors to resolve reliability versus measurement precision contradictions.

Real-time acceleration feedback dynamically modulates brake pressure to maintain optimal friction levels and prevent skidding on slippery surfaces.

An automatic rejected takeoff system monitors aircraft sensors to initiate stopping procedures.

Cross-connected IMA computers manage dual anti-skid units, maintaining braking reliability despite single computer failures.

Automated lateral control system distributes yaw moment across engines and brakes to maintain directional stability when nose wheel steering fails.

Antiskid valve modulation controls wheel deceleration to prevent structural fatigue and rebound collisions during landing gear retraction.

Pedal balance controller counters wind and thruster imbalance by dynamically adjusting brake commands to maintain desired course.

Asymmetric braking force application among actuators reduces mechanical oscillation without increasing structural complexity or weight.

Processing onboard flight data recorder metrics eliminates ground-based measurement delays and equipment variability for accurate runway friction assessment.

A mode controller adjusts brake command rise rates based on energy supply configurations to optimize antiskid performance.

An onboard braking alerting system calculates remaining runway distance and deceleration rates to issue timely alerts when current braking is insufficient.

Dynamic brake force distribution adjusts unit braking setpoints based on real-time thermal states to optimize energy dissipation across aircraft friction elements.

Electronic switches and logic gates open brake valves for emergency braking, eliminating heavy cables and simplifying assembly.

Simplified aircraft brake distance estimation replaces iterative geodesic calculations with a modified Haversine formula for efficient real-time control.

Staggering brake actuation timing reduces peak dynamic loads on the nose gear, allowing lighter aircraft structural designs.

A shutoff valve control system manages brake fluid communication using binary hardware logic inputs and weight-on-wheels status signals.

Braking force applied during landing delays wheel spin-up, decoupling vertical and horizontal load peaks to reduce maximum total stress.

Joule heating boils liquid in a sealed chamber to dissipate infrequent electric braking energy without overheating components.

Nose-up elevator commands shift weight to main wheels, resolving reduced traction caused by dynamic loading during heavy braking.

Feedback control adjusts brake force based on actual deceleration rate to maintain steady course despite varying environmental friction conditions.

An automatic system detects engine failure during takeoff and initiates an autonomous abort sequence.

System calculates kinetic energy discrepancies to reduce pressure and prevent wheel lockup while maintaining braking authority.

Braking assistance system determines local runway state from deceleration measurements to update braking data items and correct stopping distance predictions.

Brake control unit calculates axle reference speeds from wheel sensors to identify runway surface conditions.

Brake controller analyzes wheel speed during retract phase to identify dormant mechanical faults that existing monitoring misses.

Adaptive deceleration control adjusts switching time based on real-time aircraft speed and position to generate valid braking commands.

Computing deceleration set points from virtual runway states allows aircraft braking verification on adverse conditions without physical relocation.

Flight control computer calculates minimum deceleration using high-integrity inertial data to verify braking commands before transmission.

A universal controller unit identifies connected aircraft assemblies and selects corresponding program code to manage multiple subsystems.