Cosmonautic Power Supply Systems TRIZ Cases

A laser-equipped satellite constellation splits wireless power delivery to keep space targets powered through eclipse periods and low-solar regions.

Rotatable coaxial waveguide relays steer and phase-correct wireless power beams, enabling flexible long-range transfer without kilometre-scale SBSP structures.

A staged leadscrew boom deploys nested sections in compact spacecraft structures while enabling fault recovery, ratchet locking, and frequency tuning.

Differential-expansion fiber layers and heating wires help an extensible mast deploy after storage while limiting added weight and roll volume.

Centrifugal force and controlled solar radiation pressure shape a lightweight film space structure for faster deployment and stable large reflectors.

A frame cutout and perimeter attachment let flexible solar-cell substrates radiate heat directly while reducing mass and delamination risk.

Back-to-back TTC antennas spaced within one wavelength cut signal oscillations and preserve omnidirectional coverage in flat satellites.

Magnetic or electrostatic levitation lets a spherical gimbal steer satellite optical beams precisely without added mass or vibration transfer.

Combining light sources with mapped landmarks keeps moving-object positioning accurate when sunlight blocks visible reference lights.

A rotated, tightly nested satellite stack uses shared support housings to cut mass while maintaining strength against launch forces.

A backbone with standardized power, data, and thermal interfaces enables robotic module assembly and scalable spacecraft reconfiguration.

Multi-orbit LEO, MEO, and GEO satellites balance signal strength, coverage, and latency for more accurate navigation and atmospheric data.

Identical flat modules distribute payload, power, and radiators to scale space platforms while improving attitude control and thermal dissipation.

Identical self-sufficient modules and a movable mass enable scalable space platform deployment with attitude control and lower propellant use.

Multi-layer oxidant-resistant cover materials integrate light reflection to tailor space hardware protection while reducing temperature and mass.

Frame-mounted spring elements create load paths between stacked spacecraft, reducing bowing and supporting deployment.

Multiple aspect ratio modules optimize antenna reflector and thermal radiator placement within standard launch vehicle fairings.

Rotary seals maintain pressurization between a rotating hub and stationary structure in an artificial gravity habitation module.

Modular units slide along a circular track to bring items near the hatch, resolving fixed locker access bottlenecks.

Deployable phased array antennas on CubeSats increase data transmission capacity while reducing operational costs compared to large satellites.

Robots inscribe data onto celestial surfaces to preserve information against environmental degradation.

Flattened Card-Sat design merges structural covers with solar cells, resolving volume constraints while maximizing energy collection.

A 6U CubeSat bus integrates magnetometer, mass spectrometer, and particle telescope sensors for Heliophysics missions.

Modular strut-and-node design enables robotic assembly with brazing to minimize thermal distortion, reducing complexity while maintaining high precision.

Cyclical electric propulsion reduces solar array size by matching power generation patterns.

Winding flexible solar panels around the satellite body resolves the contradiction between compact stowed volume and high power generation capacity.

Hinged composite panels fold into a compact stowed configuration for launch and unfold to expand the deployed surface area.

Composite plastic modules merge mechanical strength and electromagnetic shielding, reducing mass while maintaining structural integrity.

Embedded command modules allow manual ground control of thrusters and solar wings to de-orbit spacecraft after dual processor failures.

Beam-hopping in LEO satellite constellations reduces capital expenses while maintaining broad internet coverage for remote areas.

Rotating a satellite around its speed axis points the optical instrument while keeping orbit and nadir angles fixed.

Electrostatic collection devices neutralize abrasive regolith to prevent component wear and enable efficient sample capture.

Integrating the antenna dish into the adapter ring eliminates separate deployment mechanisms, reducing launch stack volume and increasing payload capacity.

A payload interposer board standardizes power and communication links, reducing development time and cost while maintaining reliability across diverse missions.

A deorbiting drag device reduces satellite orbit lifespan and space debris accumulation by deploying when health sensors detect end-of-life conditions.

A deployer system attaches to the International Space Station robotic arm for rapid cube satellite orbital insertion.

Segmented support posts and removable panels allow accurate component placement while preventing adhesive air bubbles from expanding in space.

An orbital assembly line constructs space station segments using external manipulators and conveyor systems.

A hybrid spacecraft communications assembly integrates laser terminals and radio frequency antennas on a shared base.

Segmenting large satellites into a coordinated nanosatellite constellation reduces launch costs while maintaining ground visibility.

Segmented solar panels deploy dynamically in space to resolve launcher volume constraints while maintaining reliable energy supply.

Constellation power sharing via laser or microwave beams augments electric propulsion thrust, reducing orbital transfer time and propellant mass.

Selective laser melting creates a monolithic frame that resolves manufacturing flexibility versus structural integrity trade-offs in nano-satellite buses.

A reconfigurable solar array manages power output through dynamic string activation and deactivation.

Polygonal modular satellite buses self-mate to maximize payload space while reducing manufacturing costs and production time.

Folding mechanisms deploy control systems from optical cavities, reducing launch volume while maintaining high-resolution imagery.

A rotating mass attitude control system uses electric motors to spin circular masses for precise spacecraft orientation adjustments.