Artificial Satellites TRIZ Cases

This case allocates propellant for full orbital operations and timely atmospheric reentry, limiting debris buildup and collision risk.

This engineering case shows how a tethered wheel-shaped landing structure dissipates orbital kinetic energy through lunar-surface friction.

This case optimizes satellite-station visibility combinations by adjusting feasible start and end times under constraints.

This case shows how cross-track scanning, TDI sensors, and onboard filtering expand high-resolution coverage while prioritizing data transmission.

Standardized interlocking cells support orbital reconfiguration, modular replacement, and larger structures without monolithic launches.

This case recalculates communication paths from orbital parameters to maintain reliable data transfer as interplanetary links change.

This case categorizes orbit forecasts by constellation, orbital plane, and satellite to streamline collision-risk analysis.

Magnetorquers provide satellite pointing control without reaction wheels or moving parts.

Orbit forecasts from multiple operators are standardized to detect constellation intrusions and support timely collision avoidance alerts.

The mission manager combines telemetry, user inputs, and ground-station visibility schedules to automate SAR tasking and orbit updates.

Uneven orbital spacing creates debris passage regions while preserving ground coverage.

A satellite control apparatus determines trackable targets and transmits acquisition commands to establish optical links.

Perpendicular ejection overcomes geometric constraints, enabling multiple small satellite deployments within a common berthing mechanism.

Processor detects commands embedded in telemetry data, restoring reliability when primary receivers fail.

A single rotary actuator drives a threaded rod to deploy and grasp satellites, eliminating multiple failure points in traditional multi-actuator arms.

A satellite system redirects solar plasma through the polar cusp to create a pressure wave that de-orbits small space debris.

Nested genetic algorithms compute and adjust trajectories for chaser spacecraft, resolving collision risks during dynamic swarm reconfiguration.

Segmenting pyrotechnic devices across multiple network buses with a bus interface circuit prevents logical address space limitations and reduces system weight.

Continuous three-axis stabilization eliminates propellant-based momentum dumping and reorientation during orbit transfer maneuvers.

Annular segments align daughter probes on a mother probe axis to eliminate trajectory corrections and reduce fuel consumption.

Avoidance strips obscure satellite paths, resolving security risks while maintaining operational response time.

Distinct orbital parameters maintain vertical separation at plane intersections, reducing endogenous collision risk without requiring active evasive maneuvers.

Thermal heating increases gas pressure in a transfer tank, eliminating mechanical pumps and reducing launch weight.

An electrostatic collector uses charged tendrils to attract and retain space debris particles in orbit.

A harpoon capture system uses a deployable mast to project projectiles at space debris, reducing collision risk while maintaining precise targeting.

A server controls an air vehicle to measure radio wave attenuation between the vehicle and a communication terminal.

Segmenting capture into two satellites aligns propulsion vectors with the debris center of gravity, eliminating complex positioning requirements.

A safe landing point search device generates terrain contour lines to identify optimal landing zones using largest empty circle algorithms.

Tilted guide members deflect ejection force from the horizontal plane, ensuring precise orbital placement and reducing collision risk.

Segmenting the rocket stage frame into gliding parts reduces engineering complexity and improves reliability through passive aerodynamic orientation.

Pre-installed capturing plate with surface treatment ensures reliable adhesive bonding on non-flat satellite surfaces.

A spacecraft attitude control system stops reaction wheels before observation phases to minimize mechanical disturbances during image capture.

Vertical stacking of networked panels dissipates heat from flat propellant tanks while maintaining payload compartment layout flexibility.

Segmented plate satellites with contact points distribute launch loads to maximize payload volume across multiple orbital planes.

Relocating time synchronization mechanisms to ground stations reduces satellite mass and extends orbital lifespan while maintaining high positioning accuracy.

A signal conditioner circuit with identical topology to a gimbal angle sensor output circuit generates a compensation signal for common mode errors.

Vertical stratification of LEO satellites into distinct altitude layers reduces horizontal collision probability while maintaining coverage area.

Kinematic and magnetic interfaces join modular reflector panels to form a self-supporting large aperture, bypassing launch fairing constraints.

Reprovisioning subassembly extends spacecraft operational life by enabling robotic fuel replenishment, eliminating dedicated life extension vehicles.

A satellite observation planning device generates temporary plans by combining specific observation scenes to optimize orbital efficiency.

Electromagnetic coils separate clustered picosatellites without mechanical contact, reducing launch costs and deployment complexity.

Segmenting satellites by type allows assigning tailored celestial mechanics models, reducing position errors caused by solar radiation pressure variations.

A lunar satellite system assigns positioning and communication functions based on two-dimensional projected relative positions to the Moon.

Onboard sensors detect co-orbital threats and compute optimal evasion maneuvers to eliminate intercept events, reducing fuel consumption by 30-50%.

Magnetic coils generate forces to assemble distributed structures, bypassing launch vehicle volume constraints.

A satellite management unit adjusts attitude control accuracy based on remaining battery levels to conserve power during imaging operations.

Retractable androgynous coupling mechanism allows robotic on-orbit servicing, extending satellite service life.

A satellite constellation forming unit adjusts orbital altitudes sinusoidally to maintain relative differences between adjacent planes.

A flexible boom stores strain energy to deploy satellite payloads from an attachment hub without complex mechanisms.