Cosmonautic Vehicles TRIZ Cases
- Dual Stage Vehicle Attitude Control System
A dual stage vehicle attitude control system coordinates reaction wheels and momentum platforms for precise orientation.
- Stored Pressure Driven Cycle for Rocket Propulsion
A stored pressure driven cycle uses a pressurant tank to drive a turbopump for sustained propellant flow.
- Collinear CMG Control System Singularity Avoidance
A spacecraft control system calculates gimbal movements for collinear control moment gyroscopes using momentum offsets to maintain attitude stability.
- Sphere Orientation Control via Magnetic Levitation and Thermal Isolation
Magnetic levitation maintains sphere orientation without mechanical friction, isolating experiments from residual gravity disturbances.
- Satellite Attitude Control Without Rate Sensors
A satellite attitude control system determines thruster on-time values using star tracker data and quaternion processing.
- Relative Navigation Grid Projection for Spacecraft Attitude Control
Segmented optical components project a reference grid to measure range and attitude, reducing system weight while maintaining precision in harsh environments.
- Launcher Refueling Module Separation Mechanism
Mechanical locking pin and lever system separates launcher refueling module portions during vertical movement, eliminating pre-ignition drainage requirements.
- Electrical Ignition for Hybrid Rocket Fuel
Electrodes concentrate electrical charges to arc and ignite solid fuel, enabling multiple restarts without pyrotechnic safety hazards.
- Centrifugal Confinement Fusion for In-Space Propulsion
Centrifugal confinement fusion stabilizes plasma using radial electric fields to induce high-velocity azimuthal rotation.
- Tape Measure Embedding for Deployable Structure Stability
Triangulated tape measure configuration prevents uncontrolled deployment and instability in space deployable structures.
- Hall Effect Thruster with Movable Wall for Variable Cross-Section
A Hall effect thruster varies its annular channel cross-section via a movable wall to resolve the thrust versus specific impulse trade-off.
- Star Tracker Rate Estimation with Kalman Filter
Averaging forward and backward Kalman filter states estimates spacecraft body rates without gyros, reducing estimation errors by a factor of three to five.
- Rotary Locking Mechanism for Low-Shock Payload Separation
A rotary locking mechanism uses a spring-loaded rod to maintain pre-tension and enable rapid payload separation.
- Metallic Waveguide Array for Directional Radiative Cooling
An oblique metallic waveguide array rejects incoming celestial radiation while emitting waste heat directionally, preventing unwanted thermal absorption.
- Multi-Layer Coating for Graphite Nuclear Fuel Elements
An intermediate buffer layer accommodates thermal expansion mismatch between the substrate and outer protective coating to prevent debonding.
- Offset Tape-Spring Deployment for Controlled Solar Generator Unfolding
Offset secondary tape-springs deploy reinforcing structures opposite the membrane face, preventing violent unfolding of large solar generators.
- Node-Synchronous Eccentricity Control for Inclined Synchronous Orbits
A node-synchronous eccentricity control method manages orbital vectors to maintain precise satellite positioning.