Rocket Engine Plants TRIZ Cases

A pintle injector with a retractable concentric igniter provides radial hot gas ignition for propellant mixing.

A suction base removes recirculating fluid from an exhaust duct, enabling efficient heat exchange without increasing component mass.

A fuel conversion system transforms kerosene propellants into a supercritical state, eliminating pressure oscillations and incomplete burning in gas generators.

Buffer tank vaporizes liquid propellant via upstream heater to supply pressurization gas, eliminating slow continuous valve regulation.

A throttleable solid propellant system uses an embedded shape-altering structure to expand the burning surface area for thrust control.

Separate turbopumps eliminate dynamic seals to resolve reliability risks from fuel-oxidant mixing while maintaining high thrust efficiency.

A rocket motor thrust adjustment device diverts propellant gas flow to modify net forward thrust output.

A resin transfer molded rocket nozzle uses alternating material layers to erode at controlled rates, passively shifting throat geometry during fuel burn.

An integrated shaft merges the actuator and drive pinion to rotate a jet vane, reducing part count while maintaining thermal protection.

A rocket engine uses movable thermal chokes to adjust effective throat area during ascent.

A decompressive extinguishing plug nozzle enables multiple ignitions in solid rocket motors by rapidly altering combustion chamber pressure.

Detachable inner housing shields outer body from thermal damage during continuous high-temperature combustion.

A secondary propellant layer with a lower autoignition temperature manages heat transfer near the motor casing.

Segmented open and closed loops reduce onboard computing burden while maintaining thrust regulation precision.

A universal EPDM insulation composition cures into a single layer providing mechanical and ablative protection across rocket motor sections.

Segmented dual-outlet impellers supply distinct pressure fluids directly, eliminating energy waste from bleeding and repressurizing high pressure streams.

A room temperature curing rocket propellant formulation using low molecular weight HTPB and high molecular weight isocyanate.

A universal delay manipulation tool customizes rocket motor timing through direct access to pyrotechnic components.

Segmented propellant design reduces case weight while enabling dynamic thrust management.

A 2-pulse gas generator uses ultrasonic waves to detect the solid propellant combustion surface position for real-time consumption estimation.

Series gas generators feed exhaust into a second unit to vaporize propellants for tank pressurization during ballistic stages.

An insulated accumulator stores hot gas for multiple restarts, eliminating separate cold-start systems.

A liquid rocket combustor fuel manifold channels propellant through vertical downward and upward cooling channels.

Segmented combustion chambers with burst disks enable precise thrust control by isolating propellant charges and preventing sympathetic ignition.

A heavy inert gas insulating layer within blast tube walls reduces overall diameter and weight while maintaining thermal protection.

A missile propulsion system merges the exhaust engine into the flight engine pressure tube to generate starting thrust without ejection.

Heated helium infusion lowers exhaust molecular mass to boost specific impulse while eliminating hydrogen dissociation risks.

An ignition device fixed to a barrier membrane ruptures the film using pelletized explosive.

Segmented turbines power pumps while an expander cycle increases chamber pressure, reducing propellant loss in gas generator systems.

A mechanical locking device secures a rocket nozzle closure body using elastic elements and a rocker arm.

Segmented combustion chambers with a common nozzle eliminate complex piping and valves, reducing divert system complexity while improving navigation accuracy.

Axial control module blocks ramjet air intake to terminate propulsion, enabling precise trajectory correction via deployed canard surfaces.

A selectable ramjet propulsion system uses a frangible diaphragm to control fuel flow between the gas generator and booster.

A monopropellant continuous detonation engine utilizes a porous injector insert to suppress upstream shock waves and prevent flashback.

A propulsion system with axial and divert thrusters shares a common propellant manifold to provide independent thrust vectors.

Refractory metallic screens and flexible heat shields protect the deployment mechanism from high thermal radiation in extendable rocket engine nozzles.

A hybrid rocket engine combines solid propellant blocks with fluid oxidizer injection to enable self-sustaining combustion and precise thrust regulation.

Receptacle support transfers combustion loads to reduce casing strength, enabling higher thruster density on flight vehicles.

Neutral fluid pressure blocks liquid oxygen from entering the heater, eliminating dedicated anti-flood valves and reducing propulsion assembly mass.

Intersecting bores in a single-piece injection element create a manifold that ensures uniform fuel distribution while reducing manufacturing defects.

A dismantleable mandrel assembly segments into base and core components to form large transverse grain cavities within monolithic casing openings.

A rotatable exhaust nozzle assembly directs thrust vectors to enhance air vehicle agility.

Segmented manifold plenums with independent initiators selectively ignite motor groups, resolving thrust balancing complexity in non-centerline installations.

Multi-time ignition apparatus for rocket engines uses a turbopump assembly and gas generator to enable repeated starts while reducing weight and complexity.

A flexible silica membrane seals the gap between fixed and moving rocket nozzle parts.

A two-pulse gas generator uses a barrier membrane to isolate nested inner and outer propellants for sequential ignition.

Nesting the engine inside the oxidizer tank reduces structural mass while a cooling device protects the nozzle from erosion, extending burn time.

A solid propellant booster merges a cylindrical body and conical front end into one continuous casing structure.

Segmented airfoil fins distribute exhaust flow to resolve heating and producibility constraints in tactical missile designs.