Cosmonautic Environmental Control Arrangement TRIZ Cases

A thermally conductive structure encircles a tubular resonator cavity filter while diametrically-opposed heat transfer legs couple the device to a mounting surface.

A thermal control device uses a pressure regulating valve to adjust hydraulic resistance in the fluid circuit.

Segmenting the gasket into a removable adhesive layer and structural CNT facesheets reduces cure time and prevents deck damage during rework.

Membrane separation removes liquid water from ionic liquid mixtures, reducing energy consumption and extending vacuum pump service life.

Segmented flexible pressurizable membrane walls enclose independent atmospheric pressure zones for structural stability.

A flexible solar array uses backside conductive coatings and structural ground extension harnesses to dissipate electrostatic charge.

L-shaped heat pipes externally attach to thermal radiator panels, transferring waste heat between north and south surfaces for balanced dissipation.

A movable thermal switch decouples a radiator from a temperature sensitive component to conserve satellite DC power.

Support bearings isolate the drive mechanism from the rotating gravity chamber, reducing noise and vibration while simulating artificial gravity.

A spacecraft chassis integrates a cellular grid fin structure to radiate heat directly into outer space.

Compliant thermal interface material eliminates precise manual alignment, preventing component bending while ensuring consistent thermal conduction.

Axially sliding heat pipes mounted via compliant brackets reduce thermal stress from differential expansion.

A 3-D exoskeleton truss structure mechanically couples interior equipment panels with external radiator panels.

A heat rejection radiator uses shape memory materials to dynamically adjust surface orientation and emissivity for thermal control.

Standardized APIs enable a decentralized space traffic management system to coordinate collision avoidance planning and reduce operational complexity.

Graphene paper thermal straps combine nanoplatelets with metal additives and binding materials to create flexible heat transfer components.

Nested housing with thermal insulating layer protects electronic apparatuses and batteries in space probing environments.

Segmented evaporator blocks with feedback-controlled pulsing adapt cooling capacity to irregular heat source geometries.

An articulable sunshield rotates to shade spacecraft components from solar radiation.

Foldable insulating sheets cover satellite radiator faces, reducing device complexity and electrical power consumption during transfer phases.

Flexible protective blanket uses carbon nanotube sheets as resistive heaters to regulate temperature and shield against debris.

An immiscible anti-icing fluid mixes with water vapor to prevent ice crystal blockages in space vehicle thermal loops.

Bending the overlapping solar array and thermal radiator increases mechanical stiffness, reducing unwanted resonances during launch.

A single-person spacecraft uses a direct-pressure hatch to connect the crew enclosure with space.

Segmented sensor mounting structure with thermal isolators reduces integration complexity while maintaining pointing accuracy for space optical systems.

A flexible heat pipe uses an axial wick insert and separator plate to divide the interior volume into distinct gas-phase and liquid-phase passages.

An electrohydrodynamic mixer moves dielectric liquid through a sealed housing, switching thermal conductance states to manage satellite temperatures.

Baffles in a helical flow filter create spiral airflow paths that extend residence time within compact spacecraft volumes.

A deployable photovoltaic generator integrates thermal radiator panels with solar arrays to reject heat via radiative surfaces.

Multi-network configuration connects panel satellites via data, thermal, and power links to maintain functionality after component failure.

Integrated heat pipes and sensors on satellite panels reduce wiring complexity while maintaining precise temperature control.

A capillary pumped diphasic fluid loop incorporates a thermal capacity using phase change materials to passively regulate temperature.

Embedding the thermoelectric module in a recess prevents peeling from external impacts and distributes loads to enhance reliability.

Inter-satlet propellant flow regulates temperature without heavy heat pipes, reducing spacecraft weight.

A gas removal station ejects greenhouse gas at escape velocity into space.

Adsorbent bed removes organic contaminants from feed water to prevent adherent monolayers on sublimator porous plate that impede heat transfer.

Replacing active cooling with a self-service thermal design eliminates vibration and weight while maintaining temperature stability.

East-west radiator assembly uses flexible heat pipes to stabilize temperature fluctuations and eliminate heater power requirements.

Perpendicular radiating elements on angled walls reduce parasitic reflections that degrade radiofrequency wave quality.

A tape spring device uses a U-shaped rotor to autonomously unwind and deploy flexible satellite structures.

Removable chassis panels enable independent module work, reducing maintenance time and component failure risk.

Shared vacuum vent duct merges CO2 removal and humidity control, reducing spacecraft life support complexity.

Parallel boards integrate RF antennas and amplifiers to reduce signal loss.

Dual porous wick structures enable high-capacity thermal management without increasing device weight or volume.

A modular satellite docking structure connects pre-assembled device carrier panels to standardize electrical interfaces and reduce manual wiring complexity.

Paraffin wax mixed with fatty acid ester expands into an ullage space during melting, preventing pressure damage to the heat sink structure.

A semi-interpenetrating polymer network material modulates infrared emissivity through electrochemical doping of a conductive polymer phase.

Nesting a wick-based heat pipe within a finned phase change material container improves heat transport efficiency while maintaining compact satellite mass.