Abstract: Rolling airframe projectile guidance and stability systems are disclosed. Flight control surfaces, such as canards and/or tail fins are attached to a projectile airframe that is designed to roll during flight. Stepper motors are attached to the flight control surfaces and move the flight control surfaces in discrete increments. A control system generates signals that control the flight control surfaces. The control system may include a neural network that is trained to generate control signals in response to received inputs.

Abstract: A control surface actuation system has the ability to move aerodynamic control surfaces using a rotational motion of a motor. In an arrangement, rotational motion of the motor enables the aerodynamic control surfaces of a rotating projectile to oscillate and thus vary the angle of the control surfaces as the projectile spins. The rotation of a motor in one direction in combination with a gear and a link and a crank arm attached to a shaft of the aerodynamic control surfaces allows the control surfaces to move in fluttering motion to induce the maneuvering of a projectile in the desired direction. A controller takes information regarding the current condition of the projectile and drives the motor to move the aerodynamic devices to maneuver the projectile.

Abstract: A system, device and method provide an exhaust assembly adapted for use with a mass ejection drive system to produce rotational torque about the principle axis of the drive system. Representative features generally include a vane suitably configured to at least partially engage a mass ejecta stream to apply a net rotational torque about the principal axis of the drive system, and a tailfin coupled to the at least one vane. The tail fin is configured to selectively deploy from an at least partially stowed position in order to decrease the application of net rotational torque about the principal axis of the drive system.

Abstract: A locking assembly has a base and a rotary shaft which is capable of rotating relative to the base. The rotary shaft has a shaft body and a set of capture portions supported by the shaft body. The locking assembly further includes a set of detention mechanisms supported by the base. The set of detention mechanisms is arranged to (i) initially apply retention force to the set of capture portions to provide resistance against rotation of the rotary shaft from an initial angular position, and (ii) remove application of the retention force from the set of capture portions in response to an amount of rotational torque on the rotary shaft. The amount of rotational torque on the rotary shaft exceeds a predetermined threshold and is sufficient to substantially rotate the rotary shaft from the initial angular position.

Abstract: An apparatus for launching projectiles may incorporate a hermetically sealed launch tube, projectile or projectiles within the launch tube with their payload inside or connected via meaning of socket to projectile from outside. The space between the outer surface of the projectile inside the launch tube and the inner surface of the launch tube is filled with compressed gas and hermetically sealed with a fast removable lid. If outside payload is used, then it will be attached to inside projectile via a socket where inside projectile is located inside the launch tube and outside payload connected to the protruded via fast acting valve, portion of projectile and connected to it via the socket. Projectile may incorporate another meaning of control via controllable surfaces or propulsion or constant acting engines. The exhaust gas would be in addition to use for projectile stabilization or additional propulsion, by incorporation a exhaust gas organizers.

Abstract: A fuze guidance system is configurable by an end user, allowing the end user to select between different configurations of canards of the system. The different configurations of canards may include canards with different surface areas, optimized for providing appropriate control with different sizes of munitions. The different configurations may be accomplished by having canards with separable portions which may be broken off or otherwise removed by the end user, to reduce canard surface area and/or span. Alternatively the fuze guidance system may come in a kit with multiple sets of canards having different sizes or otherwise having different configurations for providing different aerodynamic characteristics. The end user may select a canard set based on the munition size or type that the fuze guidance system is to be used with.

Abstract: A launchable unit including a warhead for generating non-nuclear electro magnetic pulses and a thermobaric warhead without dangerous fragments. The warheads in combination are arranged to operate in different modes dependent on target types and/or objectives with engagement controlled by the aiming and setting of the weapon by a gunner.

Abstract: A spin-stabilized correctible-trajectory artillery shell has a generator in the rotation-decoupled engagement region between a canard guidance unit and its munition body. The generator can be switched over to avoid load fluctuations between an adjusting motor and a substitute load. In order to avoid an additional heat source in the interior of the guidance unit the substitute load is in the form of an electrical resistance on, at or in canard surfaces behind the afflux flow edges. The canard surfaces are preferably formed on anti-spin canards which are not adjustably mounted.

Abstract: A finless projectile provides improved ease of use, aerodynamics, muzzle velocity, drag, target, and excursion accuracy, structural integrity, terminal effectiveness and safety, at lower cost. The finless projectile includes a slug, a forward projectile body, an aft projectile body, an obturator, and a pad. The finless projectile is a full bore projectile that defines a hollow core, but does not include a sabot nor does it carry explosives. The finless projectile functions by kinetic energy transfer from the projectile to the target by deforming the target. The center of gravity of the finless projectile is forward of the center of pressure to provide static stability to the finless projectile.

Abstract: An optically guided mortar comprising a three axis canard assembly, an optical seeker, a guidance and control processor, and a fuze mechanism. The optical seeker is a direct replacement for existing standard mortar fuzes. The resulting system significantly improves current mortar circular error probability (CEP) and results in overall reduction of cost of target prosecution, reduction in collateral damage, improved crew survivability, and adds compatibility against limited non-stationary targets. The optical seeker detects an optical illuminator located at a target and supplies signals to the guidance and control processor which through a guidance algorithm supplies steering commands to drive motors of the three axis canard assembly which move a plurality of guidance canards to accurately direct the munition toward a target.

Abstract: A modular electromechanical actuation system assembly is provided that includes an electronic control unit housing having a plurality of motor receptacles and a plurality of battery receptacles formed in an outer surface thereof. Each of the motor receptacles has an associated motor electrical interface, and each of the battery receptacles has an associated battery electrical interface. An electronic control unit is disposed within the electronic control unit housing and is electrically coupled to each of the motor electrical interfaces and each of the battery electrical interfaces. A plurality of motors are supported, one each, within one of the motor receptacles, and a plurality of batteries are supported, one each, within one of the battery receptacles.

Abstract: An electromagnetic railgun projectile is disclosed which includes an aeroshell having a substantially flat surface extending along the length thereof. The substantially flat surface is configured to increase the lift-to-drag ratio of the projectile during reentry. The projectile also includes an armature integrated into the aeroshell substantially near the center-of-gravity of the projectile, and a plurality of extendable flaps attached to the aeroshell. The flaps are capable of stabilizing the projectile during an unguided portion of its flight and maneuvering the projectile during a guided portion of its flight.

Abstract: A locking assembly has a base and a rotary shaft which is capable of rotating relative to the base. The rotary shaft has a shaft body and a set of capture portions supported by the shaft body. The locking assembly further includes a set of detention mechanisms supported by the base. The set of detention mechanisms is arranged to (i) initially apply retention force to the set of capture portions to provide resistance against rotation of the rotary shaft from an initial angular position, and (ii) remove application of the retention force from the set of capture portions in response to an amount of rotational torque on the rotary shaft. The amount of rotational torque on the rotary shaft exceeds a predetermined threshold and is sufficient to substantially rotate the rotary shaft from the initial angular position.

Abstract: A terminal guidance and/or steering process for a projectile towards a target, process in which the orientation of a velocity vector {right arrow over (Vp)} is determined then a guidance law is applied and finally a steering algorithm enabling the projectile to be reoriented towards its target, process wherein the three components of the terrestrial magnetic field {right arrow over (H)} are measured in a projectile-linked reference marker (OxmYmZm) and these measurements are used in the guidance law and/or steering algorithm as a fixed reference marker enabling the orientation at least partially of the projectile-linked reference marker with respect to the terrestrial reference marker (GXfYfZf).

Abstract: A guidable projectile has a central shaft, a projectile body, and a surface control assembly. The projectile body is arranged to rotate around at least a portion of the central shaft during flight of the guidable projectile to provide stabilization. The surface control assembly is supported by the central shaft. The surface control assembly includes a movable member arranged to control a trajectory of the guidable projectile during flight of the guidable projectile, and an electromagnetic actuator interconnected between the central shaft and the movable member. The electromagnetic actuator is arranged to control movement of the movable member relative to the central shaft.

Abstract: A projectile has the ability to generate and provide power to components located in two sections of the projectile which have relative rotation to each other. The projectile has a pair of generators allowing the powering of components in two sections. The projectile has a force-producing device for altering the direction of the projectile as the projectile moves along the longitudinal axis of the projectile and the relative rotational position of the force-producing device on the projectile is controlled by a generator.

Abstract: The disclosed system and method for improving aerodynamic stability of aeronautic vehicles generally includes an ejectable grid fin adapted for releasable engagement with aeronautic vehicles. The grid fin is generally configured to optimize the flight performance characteristics of the aeronautic vehicle taken in engaged combination with the grid fin as compared with the flight performance of the aeronautic vehicle taken alone. Disclosed features and specifications may be controlled, adapted or otherwise optionally modified to improve the aerodynamic stability and/or control of a variety of deployed aeronautic vehicles. Exemplary embodiments of the present invention generally provide ejectable grid fins that may be used in conjunction with missiles mounted on an eject rail of an aircraft.

Abstract: A reconnaissance system that comprises a projectile (10) that has an opening (17) through which images of a target area can be acquired. The projectile (10) is launched from a portable launcher (30) towards the target area, and comprises image acquiring means (13, 14) for acquiring images of the target area through the opening (17) and for transmitting the images to a remote station (70); means for stabilizing the projectile (10) and/or the image acquiring means (13, 14) while flying in a nearly-parabolic trajectory above the target area; and a remote station (70), for receiving and displaying the transmitted images that comprises a monitor (71) for displaying the transmitted images.

Abstract: Control surface assemblies having a torque tube base are disclosed. In one embodiment, a control surface assembly includes a control surface portion and a base portion. The base portion has a hollow, shell-like base portion coupled to a first end portion of the control surface portion, and is adapted to be coupled to a supporting structure such that the control surface portion projects outwardly from the supporting structure. In one aspect, the base portion includes an elongated, closed section portion adapted to be coupled to the supporting structure. In a further aspect, the base portion includes an elongated, closed section portion adapted to be coupled to the supporting structure, and a pair of tapered end portions formed at opposing ends of the closed section portion.

Abstract: A guided projectile has a deployment system for deploying a deployable structure, such as a fin, another type of control surface, or an antenna. The deployment system includes a single-piece body that has a hub body and a resilient tab. The resilient tab presses against a stepped surface of a guided projectile body. As the deployable structure is extended, the deployable structure body rotates about a shaft in a central hole or aperture in the hub body. The resilient tab presses against the stepped surface on one side of an edge of the stepped surface during a first (relatively stowed) part of this deployment. At a certain point, as the contact between the tab and the stepped surfaces reaches the edge (the step of the stepped surface), the resilient tab changes position. The change in position of the resilient tab keeps the deployable structure from retracting again.

Abstract: A folding control surface assembly includes a torsion shaft, a base, and a control surface hingedly attached to the base via the torsion shaft, such that the torsion shaft biases the control surface toward an unfolded configuration with respect to the base. A vehicle includes a body and at least one folding control surface assembly. The at least one folding control surface assembly includes a torsion shaft, a base attached to the body, and a control surface hingedly attached to the base via the torsion shaft, such that the torsion shaft biases the control surface toward an unfolded configuration with respect to the base.

Abstract: A control surface system for a marine vehicle is provided. The control surface system includes a control member having at least two control portions fixedly connected at a predetermined spacing from each other. The control portions each have opposed surfaces, with the control portions being rotatable about an axis.

Abstract: An air-launched aircraft includes deployable wings, elevons, and vertical fins that deploy from a fuselage during flight. The aircraft may include a control system for operating the elevons, a communication system, and batteries for powering the systems. In addition, the aircraft may include a payload module that mates with an interface in the fuselage. The payload module may include any of a variety of payloads, including cameras, sensors, and/or radar emitters. The aircraft may be powered or unpowered, and may be very small, for example, less than on the order of 10 kg (22 pounds). The aircraft may be employed at a low cost for any of a wide variety of functions, such as surveillance, or as a decoy. The deployable surfaces of the aircraft may be configured to deploy in a pre-determined order, allowing the aircraft automatically to enter controlled flight after being launched in a tumbling mode.

Abstract: Disclosed are antenna embodiments and air vehicles so equipped that include a first antenna component, and a second antenna component, separated by a free space gap, where the antenna embodiments are adapted to capacitively couple the first antenna component and the second antenna component across one or more portions of the free space gap and where the first antenna component member has a degree or axis of rotation, relative to the second antenna component.

Abstract: At very low apparatus expenditure, namely with a canard system which is adjustable in a single-axis mode, it is possible to achieve a spatially two-dimensional trajectory correction in respect of the artillery ammunition which in itself is unguided, with the additional degree of freedom in respect of trajectory extension and thus an extraordinary increase in the precision of delivery in relation to the predetermined target point.

Abstract: A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.

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: An apparatus for actuating a control surface includes a first spur gear; a first drive assembly engaged with the first spur gear; a second spur gear; and a second drive assembly engaged with the second spur gear. The apparatus further includes a gear assembly engaged with the first spur gear and the second spur gear and adapted to be coupled with the control surface.

Abstract: An apparatus for actuating a control surface includes a first spur gear, a first drive assembly engaged with the first spur gear, a second spur gear, a second drive assembly engaged with the second spur gear, and a gear assembly capable of being coupled with the control surface and engaged with the spur gears. The gear assembly includes a first screw, a first gear engaged with the first spur gear, a thrust nut mounted to the first gear and threadedly engaged with the first screw, a second gear engaged with the second spur gear, a second screw mounted to the second gear and mechanically coupled with the thrust nut and a translation nut threadedly engaged with the second screw and capable of being coupled with the control surface. The second screw and the thrust nut rotate independently and translations of the thrust nut are transmitted to the second screw.

Abstract: A deployment and orientation device for projectile control surfaces, the deployment being carried out by means of springs between a loading position in which the control surfaces are folded inside the projectile and held against the action of the spring means using blocking means, and a deployed position in which the control surfaces may be oriented with respect to the projectile, device wherein it incorporates motors ensuring firstly the deployment of the control surfaces and secondly their orientation, the blocking means for the control surfaces being single means ensuring the immobilization of all the control surface and enabling them to be released simultaneously, the blocking means being immobilized by first locking means released by the pivoting of the bodies of the motors.

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiralling motion without the aircraft rolling. Two fins 6 and 17 are attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The fins 6, 17 are able to rotate in a pivoting manner on the rotatable tube 3 with respect to the rotatable tube 3, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 3. Fin 6 is larger than fin 17. The difference in sizes between the fins makes the larger fin 6 exert a greater force on the rotatable tube 3 than the smaller fin 17 when the fins are pitched in unison. The aerodynamic imbalance between the fins thus causes the rotatable tube 3 to rotate. When pitched at an angle to the longitudinal axis in unison, both fins 6, 17 would exert a lateral force on the rotatable tube 3. Thus, as well as forcing the rotatable tube 3 to rotate, the fins 6, 17 would also push the rotatable tube sideways.

Abstract: A finless cone-nosed, ogival-nosed, or combination ogive-cone nosed training projectile is statically stable, yet has adequate spin rate to compensate for aerodynamic or mass asymmetries. In addition, the training projectile can be fired from smooth bore or rifled cannons of various calibers, including 120 mm and 105 mm. Spin torque and stability augmentation are provided by a radially angled slotted tail flange attached to the rear of the training projectile, providing high performance and improved accuracy at low cost for use in training exercises. The training projectile has a higher static margin than conventional devices, and provides the ability to train personnel with a training projectile that achieves flight ranges similar to its matching tactical projectile, and has improved accuracy.

Abstract: A penetrator includes a fore body comprising a pin and having a center of aerodynamic pressure forward of a center of gravity and a stabilizing portion comprising a material of lower density than that of the fore body and a plurality of outwardly extending fins for improving an aerodynamic stability of the projectile and defining a bore in which the pin is received for removably attaching the fore body thereto such that, when attached to the fore body, a center of gravity for the penetrator is forward of a center of aerodynamic pressure for the penetrator.

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiralling motion without the aircraft rolling. Two fins 6 and 17 are attached to a tube 3a that is able to rotate around the encircled part of the fuselage. The fins 6, 17 are able to rotate in a pivoting manner on the rotatable tube 3a with respect to the rotatable tube 3a, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 3a. Rotation of the rotatable tube is achieved by using an electric motor 3b turning a wheel 3c. The wheel 3c makes contact with the rotatable tube. When pitched at an angle to the longitudinal axis in unison, both fins 6, 17 would exert a lateral force on the rotatable tube 3a. But as the rotatable tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiralling motion of the aircraft when in flight. The rotation of one fin causes the rotation of another fin.

Abstract: A method and structure for a full-bore artillery projectile fin deployment device comprising a projectile stabilization fin comprising an aperture and a movable pawl; a rod comprising a head portion and a shaft portion terminating with a beveled tip configured for engaging the pawl; a tailboom configured for housing the fin, wherein the tailboom comprises a hollow bore configured for receiving the rod; a pin slotted through the aperture and attached to the tailboom; and a bias member adjacent to the head portion of the rod. The rod is slotted to simultaneously engage a plurality of fins. The tailboom comprises a forward end and a rearward end and a slot configured for permitting the fin to articulate out of the tailboom, and wherein the tailboom connects to a projectile. Additionally, the power source for the device is the naturally occurring launch accelerations.

Abstract: There is provided a ground sensor assembly adapted for deployment from air to a selected ground location. The ground sensor assembly comprises an aerially deployable sensor housing which has upper and lower housing ends defining a longitudinally elongated aperture therebetween. A plurality of connected sensor modules are longitudinally inserted into the aperture between the upper and lower housing ends. Furthermore, an aerodynamic module is connected to the sensor modules and is disposed adjacent the upper housing end outside the aperture. This aerodynamic module has a plurality of stabilizers which radially extend outward therefrom and form a generally parallel relationship with the upper housing end. Such stabilizers provide aerodynamic stability during the deployment of the ground sensor assembly from the air to the selected ground location.

Abstract: A variable drag projectile stabilizer is utilized by a training projectile to match the trajectory of a tactical projectile for up to 3 km while having a range limitation of 8 km. The stabilizer applies supersonic flow phenomena to alter the aerodynamic characteristics of a training projectile while in free flight to fulfill this requirement. The stabilizer uses a cowling supported by struts to provide tail lift and ensure a stable flight path. Supersonic flow is established through ducts formed by the cowling and struts when launched from a weapon. The flow remains supersonic until the projectile reaches the desired range but then quickly becomes subsonic (choked) due to shock waves emanating from interior angles in the ducts. The geometry of the ducts can be designed to create different shock wave patterns within the ducts.

Abstract: Applicants have invented a guidance system for guiding a projectile, the projectile having a body portion capable of being spun in a first direction and a nose portion connected to the body portion by a spin control coupling, the nose portion being capable of being spun in a second direction. The nose portion including first and second aerodynamic surfaces fixedly attached to the nose portion and configured and arranged to cause the nose portion to spin in a second direction during projectile flight. The nose portion including third and fourth aerodynamic surfaces fixedly attached to the nose portion, which are configured and arranged such that when the nose portion is spinning the third and fourth aerodynamic surfaces have no net effect on projectile flight, but when the nose portion is despun using the spin control coupling, the third and fourth aerodynamic surfaces induce both a moment and a lateral force to the nose, causing the projectile flight path to change.

Abstract: A fin deployment system for missiles and munitions that deploys and activates straight flat fins for roll control authority. The fin deployment system employs numerous design features, among which are the following: A wrap-around fin concept generates space-savings within a projectile body whereby the fins are arranged in a wrapped configuration around a boomtail structure. The fins may be constructed of a super-elastic material; the system eliminates mechanical means of deploying the wrapped fins, eliminating the need for springs to deploy the fins. The fin deployment achieves substantial space savings for increasing the onboard towing capacity of electronic packaging or lethality in the missiles and munitions systems, while at the same time providing a good roll control authority during flight by enabling a straight fin deployment resulting from the use of super-elastic materials.

Abstract: A projectile comprises an imaging seeker at a front of the projectile; a front warhead behind the imaging seeker; a power supply; an electronics unit connected to the power supply and comprising a microprocessor circuit board, a voltage regulator circuit board, an inertial measurement circuit board and a fuze and safe and arm circuit board, all electrically connected to each other, the microprocessor circuit board also being connected to the imaging seeker; a rear warhead, the front and rear warheads being electrically connected to the safe and arm circuit board; a rocket motor electrically connected to the electronics unit; foldable fins mounted at the rear of the projectile; a shell that encases the front warhead, the power supply, the electronics unit, the rear warhead and the rocket motor; and a maneuver mechanism disposed in the shell and electrically connected to the microprocessor circuit board.

Abstract: Method and arrangement for extending the range of fire of a fin-stabilized artillery missile. The fin-stabilized artillery missile (1), which is fired in a ballistic trajectory, has fins (3-6), which have been given a sawtooth-shaped leading wing edge (7) that has been found to give the missile (1) an extended range of fire and improved manoeuvrability.

Abstract: The present invention concerns a method for designing a deployment mechanism for a flight surface on an airborne body, including the steps of determining a stowed position of the flight surface, determining a deployed position of the flight surface, identifying a first rotation axis and respective rotation angle and a second rotation axis and respective rotation angle about and through which the flight surface is rotatable in sequence to move the flight surface from the stowed position to the deployed position, or vice versa, and using the identified first and second rotation axes and rotation angles to determine a single equivalent rotation axis and angle, about and through which the flight surface can be rotated from the stowed position to the deployed position, or vice versa.

Abstract: A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.

Abstract: A method of guiding a munition to a target transmitting one or more signals is described. The method includes configuring the munition with a radio frequency receiver, an antenna for the receiver mounted such that a main beam of the antenna pattern for the antenna is offset from a line of flight axis of the munition by an angle and configuring the munition to rotate along an axis substantially similar to the line of flight axis of the munition. The method also includes configuring the munition to process signals received at the antenna, wherein heading changes of the munition, the angle of the main beam of the antenna from the line of flight axis, and the rotation of the munition result in the received signals having amplitude variations. Directional corrections are generated for the munition to direct the munition towards the target based on amplitude variations in the received signals.

Abstract: The center of pressure of a projectile is caused to move upon the occurrence of an event that changes the static margin, such as the jettisoning of a body previously attached to the projectile, as noted above. In particular embodiments, this is achieved by a flare disposed toward the rear of the projectile. The flare has petals that deploy from a first, stowed position to a second, deployed position upon the occurrence of the event. In the stowed position, the petals are aligned with the air stream, in order to minimize drag. In the deployed position, the petals project into the air stream in such a way as to move the lift center rearward. A slide ring within the flare has sufficient inertia that it shifts aft in response to an acceleration that occurs when the attached body and the projectile are separated from one another. The slide ring is linked to the petals in such a way that the petals are deployed by the displacement of the slide ring.

Abstract: A method for protecting a second location against a first projectile fired from a first location at the second location. The method includes: firing at least one second projectile toward the first projectile; and deploying one or more projections from the second projectile to increase its footprint and increase the probability of destroying or changing the trajectory of the first projectile.

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 penetrator includes a fore body comprising a pin and having a center of aerodynamic pressure forward of a center of gravity and a stabilizing portion comprising a material of lower density than that of the fore body and a plurality of outwardly extending fins for improving an aerodynamic stability of the projectile and defining a bore in which the pin is received for removably attaching the fore body thereto such that, when attached to the fore body, a center of gravity for the penetrator is forward of a center of aerodynamic pressure for the penetrator.

Abstract: At very low apparatus expenditure, namely with a canard system which is adjustable in a single-axis mode, it is possible to achieve a spatially two-dimensional trajectory correction in respect of the artillery ammunition which in itself is unguided, with the additional degree of freedom in respect of trajectory extension and thus an extraordinary increase in the precision of delivery in relation to the predetermined target point.

Abstract: A fin actuator for a portable missile and a method of using the same. One aspect of the present invention includes a fin or wing actuator that meets very strict criteria to fit within a compact, portable missile while substantially limiting backlash. Another aspect of the present invention is a method of fin actuation in a portable missile while substantially limiting backlash.