Aircraft Navigation Control TRIZ Cases

Fluid jet propulsion replaces mechanical actuators to reduce power consumption during orbital changes.

Pivotable panels on an omnidirectional thrust mechanism redirect compressed gas to generate multi-directional forces.

Segmenting a single central airflow into multiple jet streams via lateral guiding outlets reduces vehicle weight while maintaining flight stability.

Strategic flow channels modify shock formations and separation regions, eliminating vibration and buffet on transonic aerospace vehicles.

Segmented pivotable vanes in the divergent nozzle section redirect exhaust flow for enhanced aircraft maneuverability while reducing system complexity.

Radial protrusion on the rotation shaft guides combustion gases away from the gas seal member to reduce direct thermal exposure.

An operating map guides air vehicles through low Reynolds number regimes by controlling angle of attack and speed.

Collapsible lift propellers reduce electrical power consumption and drag by dynamically adjusting blade orientation via torsion springs.

Dual-temperature planar jets direct airflow over a wing to generate vertical lift for low thrust-to-weight ratio aircraft.

Segmented rectangular nacelles with rotatable inlet slats and exhaust flaps resolve drag and yawing moment trade-offs while reducing air turbulence.

A hybrid air transport vehicle integrates side rotors and a rear rotor with a retractable fixed wing to enable autonomous vertical takeoff and horizontal flight.

Segmented access doors open in opposite directions to bypass rotor assemblies, resolving vehicle size versus loading access trade-offs.

Aircraft use swiveling jet engines to generate pitch and yaw torques via thrust vectoring.

A blended-wing-body aircraft houses turbofan engines within the fuselage to reduce aerodynamic drag and improve fuel efficiency.

Orifice-based active flow control shifts shock waves via aerodynamic imbalance, reducing mechanical weight and complexity in flight systems.

Counter-rotating coaxial rotors transition between vertical lift and forward flight via gimbal tilt, eliminating downwash inefficiencies during VTOL operations.

Segmenting the gas generator from propulsion reduces engine size while maintaining even lift distribution.

Rotating ducted fans transition between vertical lift and horizontal thrust, enabling door-to-door operations from driveways without airport infrastructure.

An internal rotor nested in an anechoic chamber within a ducted body eliminates external propellers, reducing noise and improving safety.

Blowing slots modify wing pressure distribution to maintain directional control at high angles of attack without vertical tails.

Body-movement control replaces complex steering mechanisms while counter-rotating propulsion systems cancel gyroscopic stresses for stable spatial orientation.

Segmented flow guiding assemblies rotate along non-parallel axes to reduce energy consumption required for flight maneuvering.

Self-calibration detects mechanical stops to replace manual adaptation, reducing calibration time and improving thrust reverser precision.

Aircraft stabilization system detects component failures and commands automatic autorotation actions to maintain flight control.

A propeller system uses electromagnetic blade attachment apparatuses to rotate individual blades about their spanwise axes for independent pitch control.

Removable pyrotechnic booster thrusters attach to the helicopter frame to generate independent vertical thrust.

Dynamically reconfigurable pivot wings resolve the trade-off between versatile vertical takeoff capability and stable horizontal cruise performance.

Integrating a translating panel with cascade guide vanes varies nacelle nozzle area to reduce aircraft weight while maintaining noise reduction capabilities.

Segmented dual-engine design distributes mass to lower launch weight while nested components maintain flight duration.

Cabin blower supplies pressurized fluid to aircraft active flow control, reducing weight and complexity.

An articulatable tail section rotates about two perpendicular axes to reorient thrust and stabilizers.

A circulation control airfoil directs vectored airflow through internal ducts to generate precise roll moments.

A fluidic propulsion system uses variable geometry nozzles to transition between thrust augmentation and cruise modes.

A flight control surface uses secondary fluid flow to influence the primary exhaust boundary layer and generate non-axial forces.

A monitoring device calculates available thrust margin for a rotorcraft anti-torque member based on power and air density ratios.

Merged pitch and yaw cylinders restrict roll motion, eliminating separate links to simplify assembly.

Mechanical control surfaces deflect within propeller slipstreams to enable low-speed turning without high airspeed requirements.

A straddling flying cycle uses downward jet exhaust ports for vertical lift and forward thrust via a pilot-controlled control panel.

Spatially separated thrusters eliminate airflow interference, resolving nonlinear relationships between individual thrust and total vector accuracy.

Separating core and bypass streams prevents exhaust disruption, maintaining cruise efficiency while lowering surface temperatures during lift operations.

A valve-less pulsejet helmet uses a flow-turning device to redirect exhaust thrust along the axial line.

Segmented nozzle throat directs pressurized flow through geometric inflections to generate vectored thrust while minimizing parasitic drag.

Auxiliary propulsion groups compensate for flight control malfunctions, enabling trajectory control without heavy redundant actuators.

Segmenting exhaust flow through a bypass mechanism reduces system losses and drag while maintaining thrust.

Contra-rotating rings with articulating airfoils exploit ambient currents to reduce energy consumption while maintaining lift capability.

Modular nozzle units vector thrust independently to maintain three-dimensional stability without generating vibrations or increasing energy consumption.

Segmented seals on interfitting flaps constrain gap formation between adjacent assemblies, maintaining a continuous surface to reduce leakage.

A hybrid unmanned aerial and submersible vehicle uses a wing tilting mechanism to resolve the complexity trade-off during seamless air-water transitions.

Rotating ducted fans enable smooth VTOL-to-forward flight transitions, eliminating runway requirements while maintaining high-speed efficiency.

Engine suction pulls air through internal channels to create pressure differences, reducing drag and energy consumption.