Cosmonautic Vehicles TRIZ Cases

Coordinated gimbal and fin steering maintains horizontal rocket motion during landing without attitude change or added thrusters.

An asymmetrical enclosure and rotating electromagnetic field generate directional thrust while reducing momentum loss in propellant-less propulsion.

A viscoelastic hub structure enables lightweight, tunable damping in strut end fittings to reduce vibration and shock loads.

A layered high- and low-density secondary explosive bolt enables controlled separation while containing fragments and avoiding primary explosive risks.

A satellite SAR cluster captures multi-angle echoes in one pass, cutting 3D mapping time and cost while preserving scene reconstruction accuracy.

A rocket-deployed net and ballast pattern captures slow high-altitude aerial objects intact, enabling controlled descent and recovery.

A dry spring-elastomer isolator switches stiffness between launch and orbit to limit deflection, damp micro-vibrations, and avoid fluid leaks.

A shape-memory wire moves a blocking body to release equipment with high force in a compact, lightweight module that can be reset and retested.

Virtual-point MPC with inner and outer polytope boundaries lets each spacecraft maneuver autonomously while cutting fuel use and control complexity.

Electromagnetic attraction and repulsion help modular couplings self-align, distribute forces, and enable secure connection with easier release.

A sliding counterbalance keeps the combined center of mass nearly fixed, cutting exercise forces and residual vibration in spacecraft.

A delayed-contact damping element absorbs release-ring shock after nut release, improving reusable satellite separation reliability.

A coupled solid-fluid model estimates fuel shape and center of mass to issue control commands that stabilize sloshing-sensitive spacecraft.

A dual-port baffle and beam splitter let a star tracker image the sun and stars at once while avoiding solar washout and filter-wheel complexity.

Slew bearings reorient and support the gyroscope rotor to cut module size and mass while preserving high torque in tight spaces.

Spatial and temporospatial filters cut orbital screening workload while preserving accurate close-approach warnings for large object catalogs.

A sealed ultrasonic pump feeds pressurized gas to a reaction wheel bearing, cutting friction, vibration, and lubrication needs for longer life.

Discontinuous thrust sub-maneuvers improve satellite three-axis desaturation while lowering fuel use and articulated-arm stress.

A flanged carrier lets panel inserts be replaced without panel damage while boosting pullout strength and mounting flexibility.

Paired shells and integrated hinges let a spacecraft boom flatten for compact rolling, then self-deploy with maintained strength and torsional stiffness.

Space-time grids and dynamic satellite-group matching cut latency and simplify autonomous mission forwarding in large LEO constellations.

A movable pivot arm and fastener layout creates all-direction clearance so spacecraft isolators can damp vibration while maintaining launch restraint.

A proportional valve with pressure feedback stabilizes xenon flow for spacecraft propulsion and preserves regulation if a valve fails.

A variable-thickness spiral ribbon improves stress distribution, thermal-cycle resistance, and synchronized quick release in fastening assemblies.

Radial spokes and flexible attachments expand pivot rotation while preserving axial stiffness, reducing center shift and micro-vibration transfer.

Bearing elements and nut indentations redirect release forces radially to cut shock peaks, avoid jamming, and protect spacecraft structures.

Precomputed dual candidates and active sets replace iterative LP convergence, enabling optimal constraint-safe control within each cycle.

A moving active sleeve creates fluid transfer without axial connector motion, cutting hose-related weight, interference, and failure risk.

Projected alternate vectors smooth satellite attitude commands near vector collinearity, preventing infinite-rate rotations and instability.

High-pressure fluid actuates a segmented locking housing to release spacecraft components with lower shock and more even load distribution.

A monolithic 3D rolling diaphragm tank uses additive manufacturing and isotropic metal structure to reduce buckling and stabilize fluid expulsion.

Actuator-driven sliding wedges enable spacecraft hold-down release with near-zero shock and repeated reset without consumable parts.

A polygonal two-bracket coupler uses distributed isolators to cut shock and vibration loads while meeting tight space and weight limits.

A pre-loaded shape memory alloy wire replaces sliding hinge surfaces to prevent cold welding and galling during satellite solar panel deployment.

Chopped carbon fiber thermoplastic and ribbed bridge-leg geometry cut mount weight while preserving strength and vibration isolation.

Poppet, piston, and venting features balance high-pressure forces to prevent leaks and pressure blow-off during connector coupling.

Optimized cone angle, strut length, and quaternion PID control keep a pyramid deorbit sail stable while maintaining high drag for faster deorbiting.

By steering spacecraft states into non-expanding STM modes, this case cuts thruster use while keeping bounded motion near unstable halo orbits.

An inverted U-shaped elastic support frame absorbs motor vibration, cuts flywheel support weight, and simplifies manufacturing.

An ideal momentum wheel model is compared with real wheel motion to correct delay and friction errors for more accurate spacecraft stabilization.

Retaining the severed bolt parts keeps explosive-gas energy in the release path, helping a two-part Marman clamp separate more reliably.

Standardized frangible joints with interchangeable mounting elements cut custom redesign, lowering manufacturing cost while preserving separation integrity.

Electrically shortened memory alloy wires replace pyrotechnics to deliver fast, reusable separation with lower impact and no gas pollution.