Projectiles TRIZ Cases

Aerodynamic cone stabilizer with cylindrical bearing surface ensures supersonic projectile trajectory stability.

Spiracles in hinged fins vent trapped gases, preventing fin bending at the muzzle brake.

Dynamic trimmable rudders reduce drag from aggressive strakes by decoupling rotational control, extending effective range of gun-fired munitions.

A guidance unit motor rotates within a rigidly attached bearing to shield internal components from inertial loads.

Centrifugal and aerodynamic forces rotate rotatable fins from launch to flight position, eliminating springs or active drive elements.

Nested concentric motors and bearings articulate the nosecone through a central aperture, preserving aerodynamic integrity while transmitting control signals.

A rotatable lock mechanism uses a solenoid actuator to translate rings and bearing balls, locking fin shafts with high stiffness.

Centrifugal forces pump fluid from the stagnation area into the boundary layer, reducing drag and increasing range without additional propellant gas.

A lockable base bleed mechanism prevents breech residue disruption by maintaining internal pressure until the pyrotechnic gas generator ignites.

Movable grid fins on a detachable housing enable rapid pitch-over maneuvers, resolving low-speed guidance limitations without adding permanent weight.

Sealed housings for deployable projectile control surfaces prevent external fluid passage during flight.

A folding wing system uses a tongue and groove mechanism to lock the upper wing part against the root in the unfolded position.

A projectile brake uses a three-dimensional surface to increase air resistance and improve braking effectiveness.

Nested annular airfoils deploy radially to boost lift by 225% while minimizing stowed volume.

Concentric rear chambers increase propellant push area and fill vacuum zones to reduce drag while maintaining structural stability.

Deployable surfaces forward of the center of gravity induce resonance tumbling, terminating flight without explosives.

A torsional spring stores energy during control surface rotation to drive oscillation at the missile roll rate.

Single rotating latch with segmented sections locks all wings simultaneously, replacing complex strap systems prone to unintentional release.

Spiral spring loops deliver uniform pivoting torque to prevent fin asymmetry and rebound during deployment.

Axial play in a spin-stabilised projectile's detachable part reduces ball bearing contact pressure during thrust, preventing surface deformation.

A control surface actuator uses a pin and output gear to mechanically lock the shaft during deployment.

Helically-oriented hinge pin shaft guides fin members along a curved path for simultaneous axial and rotational movement during launch.

Elastic sheets fold around the ammunition body to deploy control surfaces, minimizing bulk and preserving payload volume.

A bendable projectile uses an articulating joint to separate forebody and rearbody units for independent flight control.

A centrifugal mechanism releases fins when rotational speed exceeds spring restraint, preventing launch interference without added complexity.

Pyrotechnic gas pressure rotates annular element to deploy fins, eliminating bulky motor drive systems and reducing internal missile volume.

Conical bearing surfaces redirect radial launch loads into axial motion while spring biasing re-centers the spindle for stable rotation.

A command mixing system coordinates canard deflections to generate simultaneous pitch and roll moments.

A steerable spin-stabilized projectile uses an internal counter-rotating mass to steer flight direction without external fins or thrust devices.

A projectile fin deployment mechanism uses a pressurized gas reservoir to actuate pistons that rotate and lock fins into position.

Redirecting generator loads to external canard surfaces manages thermal energy through convective air flow.

A single actuator rotates stowed fins parallel to the projectile axis, then pivots them using a spring biasing element.

Segmented divert and bowtie thrusters resolve inefficiency in course correction by reducing weight while maintaining precise roll, pitch, and yaw control.

A missile uses vectored thrust for steering when aerodynamic control surfaces lose effectiveness.

Detachable fairing and sleeve portions separate axially to reduce structural weight and minimize aerodynamic shocks during launch.

Retaining clip holds projectile fins in nondeployed state until launch clears obstructions, preventing structural damage during deployment.

Optimized boattail angle and meplat proportions reduce aerodynamic drag, resolving the trade-off between manufacturing precision and ballistic coefficient.

Ablatively erodible tangs constrain control fins during launch and release them via aerodynamic heating, eliminating debris hazards from pyrotechnic locks.

A body spin detection device uses a despun collar and perturbation signals to measure projectile rotation rates.

A projectile fin deployment mechanism rotates wings from a tangential position to a deployed state using synchronized toothed wheels.

Rotating control surfaces generate reaction torque for exo-atmospheric attitude adjustment, replacing separate thrusters to reduce vehicle weight.

Centrifugal forces deploy the canard by releasing the pawl, maximizing storage volume while resisting aerodynamic loads.

Centrifugal force deploys pivot-mounted air brake discs to increase drag, resolving launch path impediment and flight stability trade-offs.

An elastic spring element absorbs launch acceleration forces in a guided ammunition bearing unit, preventing brinelling damage while maintaining free rotation.

Curved air guiding recesses on the bullet tail direct airflow to the center, applying rotational force and stabilizing flight.

Rotating the front ogive relative to the aft section creates asymmetric lift, enabling finless steering that preserves internal volume for propellant.

Radially decoupled fin hub spins freely to eliminate fin-induced roll torque and preserve canard control authority.

Radial brake flaps unfold to increase drag, reducing longitudinal dispersion without adding internal weight or energy consumption.