Aircraft Navigation Control TRIZ Cases

A duplex tab exhaust nozzle generates streamwise vortices to attenuate engine noise.

Electromagnetic propulsion eliminates combustion pollution in saucer aircraft, maintaining high-speed flight without atmospheric emissions.

Drag link maintains concentric alignment between primary and secondary exhaust ducts during engine movement.

Variable arm mechanisms adapt moment of inertia and center of gravity to resolve stability trade-offs during engine failure or payload shifts.

A rotor blade assembly with tip jets provides independent thrust control at the blade tips.

Integrating inlet leading edges with wing shockwaves improves engine performance without compromising waverider aerodynamic efficiency.

An annular exhaust duct inner case features an axial end portion that bends radially and inwardly to provide structural reinforcement.

Relocating cylinder mounting to the upstream diaphragm edge eliminates rear frame penetration, reducing radial thickness and aerodynamic losses.

A gimbaled thruster configuration aligns thrust lines with servo hinge points to enable large tilting motion ranges.

Onboard pressure vessels eliminate tether weight, improving mobility and positioning accuracy for aerial paint spraying.

Rotatable louver-vanes retard descent speed, resolving safety and complexity trade-offs in VTOL personal flying vehicles.

A spherical unmanned aerial vehicle uses reversible propellers and a wheeled exoskeleton to enable hover, forward flight, and ground mobility.

Coaxial wheel hub motors provide independent aircraft taxi propulsion, preserving brake capacity and structural strength while reducing fuel consumption.

Multi-camera schlieren imaging detects transonic shock positions to generate actuator commands that reduce aerodynamic drag.

Positioning jet engines above the fuselage leverages structural components as acoustic shields, reducing ground noise without increasing engine complexity.

A vectoring exhaust nozzle pivots three vanes via a mechanical linkage to adjust throat area and maintain flow convergence during 63-degree thrust vectoring.

Tandem divert thrusters overcome aero torques by generating larger yaw control moments while reducing system complexity and mass.

Segmented fairings adjust airfoil contours on rotating wings to mitigate retreating blade stall and drag, enabling speeds exceeding 200 mph.

Shifting a movable mass alters the center-of-mass to generate torque, compensating for thrust misalignment in small rocket-propelled vehicles.

Internal structure redirects incoming air through venturi tubes to emit contraflow streams that generate reactive thrust.

A rotating pylon assembly directs thrust by swinging a rotor about a boom axis.

A movable sleeve system adjusts fan nozzle exit area to optimize thrust and fuel economy across flight conditions.

Segmented face sheets and cores deflect bird strikes, reducing structural weight penalties.

Liquid jet propulsion devices emit pressurized fluid to decelerate vehicles, preventing collisions without relying on post-impact airbag deployment.

A variable geometry nozzle adjusts its exit aperture shape to modify the exhaust flowfield near the wing assembly.

Segmented turbines maximize thrust output while the rotating engine redirects propulsive thrust for rapid directional changes.

A distributed cross-flow fan wing design rotates a rotor about a perpendicular axis to capture and exhaust airflow along parallel longitudinal axes.

Foldable wings on modular aerial vehicles resolve the trade-off between horizontal flight efficiency and compact storage volume.

An external rotor actuator encircles a rocket nozzle to translate rotary motion into linear pintle movement.

Propulsion assemblies reorient between vertical and horizontal axes to resolve downwash inefficiencies during vertical takeoff.

A tiltrotor aircraft positions a reversibly tiltable aft rotor below the fuselage to generate vertical lift and forward thrust.

Spherical joints in a structural hoop connect control vanes, resolving complexity trade-offs during helicopter-to-airplane mode transitions.

Fixed ducted rotors and segmented flaperons direct airflow to reduce drag during forward flight while maintaining vertical take-off capability.

Intermeshing drive and driven tiles shift to vary the nozzle orifice, reducing noise while optimizing propulsion performance.

Coanda and fluidic injectors manipulate exhaust flow direction in gas turbine nozzles.

Single actuation controls tiltable rotor booms, enabling smooth transition from thrust borne to wing borne flight while reducing energy requirements.

Fixed horizontal and vertical propulsors contribute to lift during hovering, eliminating inactive units and improving propulsion efficiency.

Segmented spacers line the perimeter of a spherical bearing within a drive link hub, reducing fracture risk under high load misalignment.

An aircraft lift transducer uses an LC circuit to measure wing vane position changes for precise flight parameter detection.

External actuation manipulates the exhaust plume to vector thrust, resolving the trade-off between nozzle weight and peak performance.

Dynamic passage constriction maintains high thrust efficiency at low flow rates where fixed designs degrade.

A propeller-enclosed airlifting air tube apparatus uses multi-air-tube structures to generate stable lift while protecting rotating components.

Pivoting the rear fuselage engine pylon via a worm gear actuator optimizes thrust vectoring, reducing horizontal stabilizer size and weight.

Flexible driveshaft accommodates misalignment between electric motor and power gearbox, reducing vibration impact on aircraft propulsion system.

Segmented chevron lobes generate multiple rotational flows, resolving the trade-off between mixing efficiency and engine weight.

Liquid rocket booster carries UAV payload to threshold altitude, reducing launch forces on the airframe.

Differential motor rotation controls orientation in a tailless aerial vehicle, eliminating complex mechanical articulation for vertical and horizontal flight.

A six-propulsion VTOL aircraft uses rotatable units to generate distributed thrust for vertical takeoff and landing.

Articulated electrical motors direct thrust vectors to control pitch, roll, and yaw in modular miniature unmanned aircraft.

Distributed elevons manage control faults while coaxial rotors eliminate downwash inefficiencies during vertical takeoff.