Self-Propelled Projectiles TRIZ Cases

A pyrotechnically released tail flap stays stowed in cruise, then deploys for high-G terminal steering with added aerodynamic lift.

An autonomous deployable camera captures clear external rocket and crew-capsule footage in flight, then lands by parachute for recovery.

A pyrotechnically released front cap shields a missile optronic sensor from rain erosion, then ejects in flight to preserve detection and drag.

A detachable rocket assist extends into the shell payload cavity to vary propellant mass and range without changing shell aerodynamics.

Bearings between the motor sleeve and payload adapter decouple axial spin while keeping the rocket payload securely attached.

An autonomous deployable camera captures clear in-flight rocket and crew imagery, then lands by parachute for recovery and data download.

A leading-edge TEG harvests hypersonic flow heat to power sensor packages, extending operation while reducing battery weight and power-system complexity.

Engine gas pressure breaks a circumferential clamp at defined overload, enabling reliable rocket stage separation without pyrotechnic triggers.

An articulating wing serves as a propulsion inlet and post-burnout lift surface, extending projectile range while addressing inlet drag.

Movable wings provide ramjet air intake during powered flight, then deploy as lift surfaces to reduce drag after fuel exhaustion.

A coarse, multi-start thread joins the ogive and casing, reducing machining effort while resisting spin-induced thread failure.

Selective radial motor ejection maintains center of gravity balance during trajectory adjustments, eliminating the need for additional ballast mass.

A pyrotechnic latch mechanism moves a missile component from a locked to a released position using gas pressure.

Thermal insulation isolates the pyrotechnic charge from heat, preventing degradation and sensor damage while maintaining rapid ejection speed.

A rotatable partial fin engages a support structure to form a complete aerodynamic edge, reducing drag while a leaf spring locks the assembly against vibration.

Actuator releases slot covers to deploy fins, shielding guidance systems from aerodynamic forces and contamination.

Flexible tension element converts translational drive motion into shaft rotation, eliminating backlash and hysteresis during high-force steering maneuvers.

Interchangeable guidance and flight control modules reduce manufacturing costs by eliminating the need for multiple specialized systems per configuration.

A projectile body with a propellant cavity and openable nozzle manages thrust for stable high velocity flight.

Passive aileron adjustment via dynamic pressure steers spinning projectiles, avoiding shock from propulsive outlets and reducing energy expenditure.

Slot thrust motor cavities expel gas streams through chamfered openings to reduce missile weight and volume while maintaining maneuverability.

An integral resilient tab shifts position over a stepped surface to prevent fin retraction, reducing part count and machining complexity.

Integrated actuator latch deploys projectile fins, eliminating separate deployment actuators and reducing system complexity.

Lateral thrusters expand pressurized gas to generate perpendicular thrust, resolving the steerability versus drag trade-off across mission profiles.

Two-piece adapter transfers steering loads and maintains fuze preloading, enabling guided rocket retrofitting.

GPS feedback guides steerable fins to correct trajectory deviations, reducing circular error probability from 500m to under 50m at extended ranges.

A sleeve and nut coupler mechanically decouples control surfaces to weather vane, reducing captive flight drag.

Independent fixing means decouple fuse positioning from section alignment, enabling reversible operation and consistent cutting performance in any direction.

A projectile places a launch motor at the aft end and a propulsion system at the fore end to rotate and deploy an aerospike after ejection.

Asymmetric offset attachment systems prevent mobile plate rocking during clamping by counteracting end connector stiffness.

Electromagnetic coils apply torque to maintain PGK spin rate, preventing navigation loss when canard torque is insufficient at high altitudes.

A wing deployment mechanism uses orthogonal rotational motion to drive simultaneous wing extension via linked arms.

Arithmetic unit adjusts control parameters based on ablation material shape changes to suppress deterioration of aerodynamic characteristics stability.

Cone positioning mechanism steers projectile control surfaces via toothed wheel rotation, resolving imperfect movement transmission from spherical forms.

A telescoping air inlet mechanism transitions from closed to open positions on a missile body.

An internally coupleable joint uses axial protrusions and internal securing members to mate missile sections.

A pivoting deflector strip manages propulsive jet particles to protect the guidance link wire.

A predictive guidance system divides interceptor flight into distinct phases to position the vehicle on a zero effort miss trajectory.