Attitude Control TRIZ Cases

Handheld attitude input and head-mounted directional marks make UAV control more intuitive while helping users anticipate flight path and collisions.

Automatic trim scheduling uses airspeed-based angle of attack and actuator commands to simplify tiltrotor conversion and improve power efficiency.

Electromagnets and floor metal plates stabilize autonomous container-handling vehicles during loading, preventing tipping without bulky mechanics.

Adjustable hydrofoil wings and onboard control electronics help beginners gain stability while fitting different watercrafts at lower cost.

Injecting the test signal inside the UAV autopilot loop enables Bode plots, gain margins, and phase margins without destabilizing flight.

Multiple binocular cameras divide UAV blind zones into sectors, improving obstacle distance detection and avoidance decisions during flight.

Mode sensors decompose rotorcraft structural vibrations into fundamental modes so flight controls can adjust actuators for steadier flight.

Past location and attitude estimates guide scan-to-map matching, keeping vehicle localization reliable during wheel slip and high-speed motion.

Predicted pitch attitude and propulsor blade trim reduce pilot workload while maintaining precise compound aircraft flight-state control.

A single recoupling input automatically sequences trim, attitude retention, and autopilot layers to stabilize rotorcraft in emergencies.

Automatic collective and trim control helps rotorcraft enter autorotation quickly, preserve rotor speed, and reduce pilot workload after engine loss.

Pre-checking position and nearby vocal or display equipment helps a mobile robot choose a safe recovery motion and avoid collisions or falls.

A split UAV autopilot uses a real-time main processor and delayed co-processor commands to keep stable control with low power use.

A decoupled control model lets vectored multicopter thrusters be adjusted independently, improving stability and maneuverability in constrained flight.

Spar-mounted sensors and onboard path planning help UAVs avoid obstacles and hold stable flight in tight spaces for precise delivery.

A single recoupling input restores trim, attitude retention, and autopilot layers in sequence to cut pilot workload during emergencies.

Onboard sensors generate a virtual runway centerline so aircraft can align and track heading during takeoff in low or no visibility.

Dynamic roll rate limits preserve rudder margin during engine-out maneuvers, preventing excessive sideslip without reducing roll authority unnecessarily.

A moment-ratio corrective command stabilizes autopilot roll control after nonlinear spoiler deployment without disabling existing spoilers.

Aircraft navigation system adjusts flight paths using real-time thermal and ridge lift data from fine-grained weather models.

Automated differential lateral control system maintains tip clearance by adjusting cyclic inputs based on flight conditions.

A flight control system computes automatic elevator commands to stabilize the aircraft during low speed or high attitude conditions.

Sensors detect ground contact to suspend inversion control, preventing torque interference and stabilizing acceleration for coaxial vehicles.

Reversing a multicopter rotor direction creates compensating torque, preserving lift and maneuverability after a motor failure.

Partial Least Squares regression calculates flight vectors to improve reliability while reducing monitoring complexity.

Flight control system calculates heading error to generate lateral and longitudinal movement error values.

Automatic heading control system adjusts rotorcraft orientation to reduce lateral forces.

Processing blade bending moments reduces horizontal stabilizer weight while maintaining stability.

Real-time pitch compensation using lift and weight data reduces altitude deviations during high roll angle turns.

Integrating antennas into a control fin reduces hydrodynamic drag, while movable batteries enable precise trim adjustments without external masts.

A control unit for inverted pendulum vehicles computes superimposed tilt commands to notify operators of impending balance loss.

An autopilot device maintains a reference aerodynamic angle of attack by automatically controlling collective pitch.

A control allocation method uses virtual effectors to modify commands and predict vehicle accelerations.

Iterative target speed calculation balances torque and rotational acceleration to maintain stabilized lift when one engine fails.

A vehicle uses tiltable propellers to generate thrust forces that press support components against surfaces.

An optical sensing device detects distant laser displacement to characterize line-of-sight variations for real-time image stabilization.

Vehicle-mounted beam emitters project optical patterns captured by onboard cameras to determine landing status without relying on external platform devices.

Onboard cameras identify mobile targets and calculate optimal positioning to minimize coordinate uncertainty without external radio control.

An auxiliary command value calculation mechanism adjusts servo-control parameters to reduce phase shift between pilot input and aircraft response.

Lift offset management system optimizes coaxial rotor performance through dynamic blade pitching adjustments.

Autopilot reverses coaxial propeller rotation to counteract surplus thrust and torque from rotor failure, maintaining yaw, roll, and pitch stability.

Flight control computer automates independent speed and attitude control using a translational thrust system.

Segmented dual rotor blades with variable chord and twist balance lift distribution to resolve forward speed stability trade-offs.

A droop protection loop commands collective pitch adjustments to maintain rotor speed within safe limits.

A guidance law computes set points using vertical and longitudinal speed components to determine an avoidance trajectory.

A projectile control system executes coning maneuvers to enhance roll authority during flight.