Cosmonautic Vehicles TRIZ Cases

A dual stage vehicle attitude control system coordinates reaction wheels and momentum platforms for precise orientation.

A stored pressure driven cycle uses a pressurant tank to drive a turbopump for sustained propellant flow.

A spacecraft control system calculates gimbal movements for collinear control moment gyroscopes using momentum offsets to maintain attitude stability.

Magnetic levitation maintains sphere orientation without mechanical friction, isolating experiments from residual gravity disturbances.

A satellite attitude control system determines thruster on-time values using star tracker data and quaternion processing.

Segmented optical components project a reference grid to measure range and attitude, reducing system weight while maintaining precision in harsh environments.

Mechanical locking pin and lever system separates launcher refueling module portions during vertical movement, eliminating pre-ignition drainage requirements.

Electrodes concentrate electrical charges to arc and ignite solid fuel, enabling multiple restarts without pyrotechnic safety hazards.

Centrifugal confinement fusion stabilizes plasma using radial electric fields to induce high-velocity azimuthal rotation.

Triangulated tape measure configuration prevents uncontrolled deployment and instability in space deployable structures.

A Hall effect thruster varies its annular channel cross-section via a movable wall to resolve the thrust versus specific impulse trade-off.

Averaging forward and backward Kalman filter states estimates spacecraft body rates without gyros, reducing estimation errors by a factor of three to five.

A rotary locking mechanism uses a spring-loaded rod to maintain pre-tension and enable rapid payload separation.

An oblique metallic waveguide array rejects incoming celestial radiation while emitting waste heat directionally, preventing unwanted thermal absorption.

An intermediate buffer layer accommodates thermal expansion mismatch between the substrate and outer protective coating to prevent debonding.

Offset secondary tape-springs deploy reinforcing structures opposite the membrane face, preventing violent unfolding of large solar generators.

A node-synchronous eccentricity control method manages orbital vectors to maintain precise satellite positioning.

Inlet valve modulates core and bypass flow to enable multi-mode operation, avoiding cycle penalties at supersonic speeds.

A control system state limiter calculates a modulation parameter based on actual and limited dynamics to modify system behavior smoothly.

A spacecraft tank wall heating method detects the liquid-gas interface position using rapid temperature measurements during high-thrust phases.

Deploying tethers creates friction forces that reduce thermal and acceleration loads on spacecraft during atmospheric entry.

Extendable boom mechanisms deploy solar arrays to distribute mass, enabling passive attitude stabilization via gravity gradient forces.

A staring sensor system uses co-collimated telescopes to illuminate sparsely populated focal plane arrays for simultaneous imaging.

Segmented combustion chambers with axial injectors prevent suboptimal mixing in large-scale hybrid propulsion units, ensuring maximum energy release.

A Guideless Resilient Androgynous Serial Port interface provides selectable preload structural connections between spacecraft modules.

A charge segregation assembly captures beta-minus particles and electrons from solar wind to generate electric energy for spacecraft.

Ball bearings mechanically isolate the rigid ball from launch vibrations and magnetic interference, ensuring precise attitude control.

Three axially aligned flywheels manipulate phase differences to counteract imbalance forces, minimizing attitude jitter at its source.

An autonomous system estimates remaining propellant mass using heating devices and temperature sensors to drive a reduced order model.

Medium Earth Orbit satellites generate focused spot beams to deliver high-speed internet access via efficient spectrum reuse.

Segmenting satellite power networks into modular distribution boxes eliminates centralized wiring complexity and reduces production costs.

A precision control system calculates disturbance parameter vectors from telemetry data to cancel gimbal errors.

Outer perimeter fiber optic gyroscope and control moment gyroscope arrangement maximizes diameter for high precision inertial guidance.

A triangular rollable and collapsible boom uses two curved flanges to form an open cross-section for structural deployment.

Multi-layer radiation reflector emitter scatters solar wavelengths and reflects infrared energy to maintain spacecraft temperatures below 75 K.

Elevated transmission power enables deep atmospheric penetration for precise monitoring while periodic action limits energy consumption.

Segmented parallel switching reduces control delays and bus voltage instability while lowering thermal load.

An annular booster rocket nests around a jet nozzle to deliver additional thrust without expanding the vehicle envelope.

Direct solar array coupling to Hall effect thrusters eliminates heavy power management systems, maintaining peak output as panels age.

Integrates manoeuvre data into filtering processes to resolve GNSS anomalies, ensuring accurate SAR imaging.

A thermally integrated pressurization system uses supercritical bottles and thermal switches to regulate tank pressure.

Segmented links with contact sensors adapt to arbitrary debris shapes, resolving the trade-off between grasping reliability and system complexity.

Spray injection destratifies bulk fluid and reduces pressure, preventing boil-off loss during low-gravity venting operations.

Epoxidized polybutadiene resins minimize volatile compound release to prevent environmental pollution in space.

Perimeter bus bars drive current through a transparent resistive coating to heat large optical membranes uniformly without obstructing the aperture.

Suction-held plates maintain connection between ground and on-board modules, preventing irreversible separation during launch aborts.

A passive despin damper uses magnetic torque to dissipate rotational energy and slow orbital object spin rates.