Abstract: A gun sight for use with a weapon configured for super elevation is disclosed herein. The gun sight includes, but is not limited to, an imaging system that is configured for rotation. The gun sight further includes a drive mechanism that associated with the imaging system and that is configured to rotate the imaging system. The gun sight further includes a gyroscope associated with one of the weapon and the imaging system. The gun sight still further includes a processor that is communicatively coupled with the drive mechanism and the gyroscope. The processor is configured to control the drive mechanism to rotate the imaging system in a manner that causes the imaging system to maintain an initial angular orientation based on information provided by the gyroscope when the weapon is superelevated.

Abstract: An apparatus and system for controlling the trajectory of a projectile having two rotationally decoupled sections, wherein the first section is rotationally decoupled from the second section. The first section of the projectile contains a navigation system. The first section also contains an actuator by which aero-control surfaces on the second section are actuated. The second section may have external aero-spin surfaces which provide a torque counter to the rotation of the base projectile. The apparatus and system also includes embodiments having applications for nose sections of projectiles.

Abstract: A gun sight for use with a weapon configured for super elevation is disclosed herein. The gun sight includes, but is not limited to, an imaging system that is configured for rotation. The gun sight further includes a drive mechanism that associated with the imaging system and that is configured to rotate the imaging system. The gun sight further includes a gyroscope associated with one of the weapon and the imaging system. The gun sight still further includes a processor that is communicatively coupled with the drive mechanism and the gyroscope. The processor is configured to control the drive mechanism to rotate the imaging system in a manner that causes the imaging system to maintain an initial angular orientation based on information provided by the gyroscope when the weapon is superelevated.

Abstract: The invention is a projectile, device and system having a roll control device which may be fixed or deployable, for providing torque counter to the spin of the projectile and providing drag on the projectile. The roll control device includes a guidance collar rotatably attached to the projectile located near a front end of the projectile wherein the guidance collar includes one or more guidance collar aero-surfaces shaped to provide torque counter to the spin on the projectile. The guidance collar aero-surfaces may be controlled by a brake and guidance electronics on the projectile. The invention also includes a body collar fixedly attached to the projectile aft of the guidance collar, wherein the body collar includes one or more body collar aero-surfaces and fixed or deployable drag devices. Another embodiment use only a guidance collar aero-surfaces to orient a fixed drag device relative to an Earth inertial reference frame to create asymmetrical drag on the projectile and thereby altering its trajectory.

Abstract: A loading machine for feeding a receiver includes, but is not limited to, a drum cam that is configured to rotate. The drum cam includes, but is not limited to, a first cam path, and a second cam path. A rammer subassembly is positioned proximate the drum cam. The rammer subassembly includes, but is not limited to, a first member that is configured to engage the first cam path and to move longitudinally with respect to the drum cam upon a rotation of the drum cam, and a second member that is configured to telescopically engage the first member and further configured to engage the second cam path and telescopically move with respect to the first member upon the rotation of the drum cam.

Abstract: A system for controlling an object traveling through exoatmospheric space is disclosed herein. The system includes, but is not limited to, a pressure vessel, a pair of solid propellant grains associated with the pressure vessel that is configured to direct a gas into the pressure vessel during combustion, an exhaust nozzle that is in fluid communication with the pressure vessel, and a valve that is coupled with the exhaust nozzle and that is configured to selectively obstruct the gas from venting through the exhaust nozzle.

Abstract: The invention is a projectile, device and system having a roll control device which may be fixed or deployable, for providing torque counter to the spin of the projectile and providing drag on the projectile. The roll control device includes a guidance collar rotatably attached to the projectile located near a front end of the projectile wherein the guidance collar includes one or more guidance collar aero-surfaces shaped to provide torque counter to the spin on the projectile. The guidance collar aero-surfaces may be controlled by a brake and guidance electronics on the projectile. The invention also includes a body collar fixedly attached to the projectile aft of the guidance collar, wherein the body collar includes one or more body collar aero-surfaces and fixed or deployable drag devices. Another embodiment use only a guidance collar aero-surfaces to orient a fixed drag device relative to an Earth inertial reference frame to create asymmetrical drag on the projectile and thereby altering its trajectory.

Abstract: A method for preparing a stabilized nitrocellulose article includes providing a nitrocellulose-containing mat of fibers. The nitrocellulose-containing mat of fibers is treated with a solution that comprises a solvent and a stabilizer to produce the article. The stabilizer is soluble in the solvent. The solvent dissolves the stabilizer and the nitrocellulose in the nitrocellulose-containing mat of fibers is substantially insoluble in the solvent at ambient pressure and temperature. An inflatable bag comprises a shell and the stabilized nitrocellulose article. The shell is formed from a foldable material and has an outer surface and an inner surface. The inner surface defines an interior cavity of the inflatable bag. The stabilized nitrocellulose article is disposed upon the inner surface of the shell in the interior cavity and is foldable in conformity with at least one fold of the shell.

Abstract: A fin retention and deployment mechanism that has the advantage of providing for the deployment of aerodynamic control surfaces on command without the need for an additional actuation device or control circuitry separate from the actuator that controls the angle of the fins during flight. The actuator that is already required for operation of the control surfaces after deployment initiates the deployment of the fins, as well. A latch mechanism comprises a retaining member and a lath, which engages the retaining member enabling a biasing mechanism to force the fins from a stowed position to a fully deployed position.

Abstract: The invention relates generally to a roll damping apparatus for a spinning projectile having a first section and a second section rotatably attached about a roll axis. The roll damping apparatus comprises a first portion attached to the front section, and a second portion attached to the rear section. The first portion is adapted to cause a braking frictional force to act on the second portion, the braking force being effective to control the spin rate of the front section relative to the rear section. The invention further relates to a spinning projectile having a roll damping apparatus.

Abstract: Trajectory is controlled by a control system having fins that de-spin a section of the control system relative to a projectile or missile. The control system also includes aero-surfaces that produce a lift when brought to rotation speed of about 0 Hz relative to a reference fame and a brake that couples the guidance package to the rotational inertia of the projectile or missile. In one example, no electric motor is used in the trajectory control system, saving weight and increasing reliability.

Abstract: A fin retention and deployment mechanism that has the advantage of providing for the deployment of aerodynamic control surfaces on command without the need for an additional actuation device or control circuitry separate from the actuator that controls the angle of the fins during flight. The actuator that is already required for operation of the control surfaces after deployment initiates the deployment of the fins, as well. A latch mechanism comprises a retaining member and a lath, which engages the retaining member enabling a biasing mechanism to force the fins from a stowed position to a fully deployed position.

Abstract: The invention relates to an actuator system for a projectile having a first and second pair of opposing steering fins disposed in a transverse plane of the projectile. The first pair of opposing steering fins includes a first fin and second fin. The second pair of opposing steering fins includes a third fin and a fourth fin. The actuator system comprises a first motor assembly configured to control the position of the first pair of opposing steering fins, and a second motor assembly configured to control the position of the second pair of opposing steering fins. The first motor assembly and second motor assembly are mounted axially along an axis of the projectile such that a first portion of the first motor assembly is telescopically received within a second portion of the second motor assembly.

Abstract: A fin cover release and deployment system designed for high G forces of gun-launched missiles. In one embodiment, a pyrotechnic actuator drives actuator arms to first release and eject the fin slot covers, followed by deployment of the fins radially outward to the steering position. Following complete ejection of the covers, the fins are driven outwardly by cam surfaces along the latch arms, followed by a spring and wedge mechanism installed interiorly of the fin steering shaft to lock the fins in the fully deployed state. In another embodiment, a motor and rotating threaded shaft replace the pyrotechnic actuator.

Abstract: A primer assembly including an ignition element assembly, a primer head assembly and a tubular body, is presented. The primer head assembly has an exterior diameter and an internal chamber containing the ignition element assembly. The tubular body has an open head end, a closed tail end and a wall defining an internal chamber. The internal chamber of the tubular body contains an ignition charge and the head end includes an internal diameter for receiving the exterior diameter of the primer head assembly. When the primer assembly is assembled, the tubular body encloses the primer head assembly and the primer head assembly seals the internal chamber. In one embodiment, the tubular body is a one-piece, seamless metallic tube having a wall of a thickness of about 0.150 to 0.160 inch and, preferably, about 0.155 inch.

Abstract: Tracer visibility of APFSDS projectiles can be enhanced through a combination of increased steady state spin rate, reduced muzzle obscuration, and optimized airflow over the stabilizing fin geometry of the sub-projectile. The preferred means to increase steady state spin rates of the sub-projectile is to incline or deflect the fin blade tip portion, creating a larger, hotter burning, tracer plume.

Abstract: A guidance seeker system for a projectile includes a plurality of photoconductive sensing elements symmetrically disposed about a central axis of the projectile. When a target is illuminated with a light source, a lens transmits light reflected from the target to one or more of the photoconductive sensing elements. Dependent on which photoconductive sensing element is irradiated, a variance between the line of flight of the projectile and the target is determined. A voltage impulse resulting from irradiation of the photoconductive sensing element triggers actuation of a course corrector, such as a diverter, to nudge the line of flight of the projectile to increase the likelihood of the projectile reaching the desired target. This guidance seeking system is particularly effective when the target is designated with a pulsed laser.

Abstract: A guidance seeker system for a projectile includes a plurality of photoconductive sensing elements symmetrically disposed about a central axis of the projectile. When a target is illuminated with a light source, a lens transmits light reflected from the target to one or more of the photoconductive sensing elements. Dependent on which photoconductive sensing element is irradiated, a variance between the line of flight of the projectile and the target is determined. A voltage impulse resulting from irradiation of the photoconductive sensing element triggers actuation of a course corrector, such as a diverter, to nudge the line of flight of the projectile to increase the likelihood of the projectile reaching the desired target. This guidance seeking system is particularly effective when the target is designated with a pulsed laser.

Abstract: A subcaliber kinetic energy penetrator has first and second portions formed of dense material and secured to each other. The first portion, located ahead of the second portion preferably represents between 9% and 15% of the penetrator mass and a similar percentage of the combined lengths of the two portions. The first portion is formed of a material effective to produce a relatively large hole in an explosive reactive armor faceplate. The second portion is preferably formed from material selected to best perforate basal armor.

Abstract: Tracer visibility of APFSDS projectiles can be enhanced through a combination of increased steady state spin rate, reduced muzzle obscuration, and optimized airflow over the stabilizing fin geometry of the sub-projectile. The preferred means to increase steady state spin rates of the sub-projectile is to incline or deflect the fin blade tip portion, creating a larger, hotter burning, tracer plume.