Cosmonautic Vehicles TRIZ Cases

Elastomeric end pieces enable isostatic flexible pivots that resist launch stresses while active control attenuates low-frequency disturbances.

Canted incidence angle sensor enables conical scanning to align spacecraft axis with the Sun, reducing sensor complexity and cost.

Selective solar cell section deactivation generates differential radiation pressure torque, unloading reaction wheel momentum without thruster fuel consumption.

A miniature release mechanism secures nanosatellite deployables using a threaded interface and retracting pins.

A spacecraft docking system uses linear actuators and elastic means to deploy a stowed assembly for orbital missions.

An electronic regulator maintains hypersonic fuel tank pressure within ±1.5% of the set point by replacing mechanical springs with solenoid actuation.

A flexible strip link device replaces entangled cables with a wound strip mechanism, enabling stable harpooning of space debris without trajectory interference.

Metallo-thermal composition generates heat to destroy spacecraft elements, resolving demisability trade-offs in reaction wheels.

Doppler-GPS orbital determination fits Kepler elements to single-signal frequency trends, maintaining accuracy when fewer than four satellites are visible.

Spherical displacement of electromagnets compensates for misalignment, enabling reliable capture without complex external guidance systems.

Autonomous orbit estimation uses onboard cameras and visual odometry to determine satellite position without relying on ground-based tracking systems.

A randomized spring array creates a redundant electrical interface using compressible wire mats to maintain contact integrity.

A method for controlling an ion thruster adjusts emission current and speed via applied potentials to enable efficient propulsion.

Anisotropic weighted gradient method generates dynamic input-output gains to control spacecraft attitude.

A microcavity discharge thruster accelerates propellant plasma through a supersonic nozzle to generate thrust.

Particle swarm optimization reduces deorbit duration and collision risks by dynamically adjusting thruster parameters via augmented Lagrangian constraints.

A solar cell array system uses a bow spring compression member and tensile force members to deploy panels without carrying loads through the cells.

Navigation system calculates expected celestial directions to determine body position using star tracking sensors and inertial sensors.

Low-temperature catalytic cracking of branched alkanes enables endothermic fuel to absorb aircraft waste heat without high reaction temperatures.

Segmented bed partitions and a compliant shell prevent uneven thermal expansion from causing cold shell failure during repeated cycling.

Synchronous display of satellite orbit position and time information simplifies complex orbital mechanics, enabling ordinary users to plan imaging tasks easily.

Merging the thrust reverser with the fan nozzle reduces engine weight and complexity while maintaining performance envelopes across flight conditions.

An integral actuation device merges structural support and torsion spring functions into a single additively manufactured component.

Displacing a single electric thruster generates arbitrary axial moments to desaturate reaction wheels, reducing propellant consumption.

Elastic ribs wind around a hub and deploy into a parabolic shape using restoring force, eliminating complex mechanisms.

A conical shell mount transfers launch loads directly from the propellant tank to the interface ring.

Single-piece mixer center body routes fan exhaust through interstitial ducts to lower core exhaust temperature and reduce infrared signature.

An anticipator module calculates pitch and roll compensation amounts using measured rates to correct attitude signals before they reach the autopilot.

Two-step calibration program compensates for installation errors by substituting rotator data into an integrated model to improve attitude measurement accuracy.

Linked latch assemblies secured by a notched bolt rotate out of the way via shape memory alloy actuators, enabling controlled spring-loaded payload deployment.

Multi-station correlation processing calculates satellite distance using reception time differences between ground antennas.

Calculates estimated valve opening from acting and fluid force balance to correct target positions, reducing trajectory errors caused by valve transformation.

Timing-controlled braking force reduces orbital speed of large debris for atmospheric reentry without inducing rotation.

A plane mirror fixed to a star finder reflects a collimated beam to a detector, establishing the telescope line of sight direction.

Non-contact laser patterning creates microstructures on vehicle surfaces using photopolymer curing depth profiles.

A pre-stressed connecting element surrounds launcher stages to transmit mechanical loads via cured adhesive bonds.

Thermal expansion generates a secondary rim interference fit, maintaining weld joints in compression to prevent fatigue and enable higher rotational speeds.

Segmented feed chimneys surrounded by coaxial sheaths stabilize flow and maintain uniform injection despite propellant takeoff from the chamber.

Inductive plasma torches and magnetic cylinders stabilize materials to extract pure metals despite deep space vacuum challenges.

High-temperature silicone coating on inorganic insulation cable prevents micrometeorite damage to stationary plasma thruster field coils.

Adjusting injector placement creates a 100-degree phase shift that reduces thermo-acoustic coupling and fatigue damage.

A space propulsion module mounts an electric thruster on a solid-fuel chemical thruster main body for combined thrust generation.

Deployable radiators rotate from east-west stowed positions to north-south facing orientations for spacecraft thermal control.

Ultra-thin emitter wires in an ion propulsion assembly lift power source weight against gravity using segmented wire structures.

A single high-voltage generator supplies multiple spacecraft drive units, reducing weight and cost while enabling independent thrust vector control.

A self-pressurization system uses operative gas to increase raw fluid pressure without mechanical pumps.

Orbit propagation models estimate motion vectors for virtual debris pieces, eliminating trial-and-error searches and reducing processing time.

Virtual reference station corrections resolve atmospheric delays and orbital perturbations to achieve sub-meter accuracy for low earth orbit satellites.

Liquid crystal electro-optic panels replace thrusters to eliminate fuel consumption and transient disturbances during orbital maintenance.