Abstract: A dog toy includes a projectile and a slingshot. The projectile is configured to fly through the air while resembling a dog bone. Accordingly, the projectile has a first and second visual pair of bulbous portions disposed at the leading and trailing ends. The trailing end is also shaped as fins for stability in flight, whereas the leading end is heavier in mass. A pair of hooks are at the leading end. A finger grip is attached near, to or formed as part of the trailing end and allows a user to grip the projectile with a user's fingers. The slingshot includes a handle configured to be gripped by the user. A pair of prongs extend from a handle top and form an opening. An elastic band is connected to each prong. A hand guard protects a portion of the user's hand during use.

Abstract: Techniques are provided for guiding a projectile. A methodology implementing the techniques according to an embodiment includes generating a roll command based on a roll angle obtained from a steering map that causes a change in range and cross range of the projectile that results in a ground motion closest to a desired ground motion. The method also includes calculating a remaining maximum maneuver distance for the projectile, over a time period extending from the current time of flight to the end of flight. The calculation is based on integration a series of maximum maneuvers, obtained from the steering map, at time intervals within the time period. The method further includes generating a lift command for the projectile based on: distance between the target location and an impact point prediction (IPP) calculated at the current time of flight; an error estimate of the IPP; and the remaining maximum maneuver distance.

Abstract: The present disclosure provides generally for a system and method for planting flora, fauna, and dispersing various organisms through drone delivery. The system may comprise of a drone with seedling box that may hold and drop the pods containing flora or fauna. The seedling box may hold the pods with the flora or fauna in them and at specific intervals drop the pod with the flora or fauna. The seedling box may also hold various organisms or other materials and drop these organisms or materials when directed. A seedling box may comprise loading mechanism and deploying mechanism to facilitate accurate, timely deployment of the pods containing the seedlings. A pod may comprise a weighted tip with hollow cavity for seedling placement and a vertical rod for securing seedling during deployment. Where the system comprises uneven number of seedlings, seedling box may include counterweights to provide stability in configured flight patterns for duration of seedling deployment.

Abstract: In one embodiment, a less lethal munition including a ring airfoil projectile. The flight trajectory of the projectile has increased accuracy resulting from the aerodynamic stabilization of the projectile. In some embodiments, the projectile is both aerodynamically stabilized and spin stabilized.

Abstract: A fin retention system having a plurality of fin retention units and in which each unit is associated with one deployable fin of the projectile. Each retention unit has an alignment device and a pair of span arms extending outwardly from opposite sides of the alignment device. An attachment device attaches the free ends of the span arms of adjacent fin retention units together. In doing so, the alignment device engages and holds each fin in its undeployed position.

Abstract: A multi-caliber fuze kit includes a fuze housing configured for coupling with multiple projectiles. One or more canards are moveably coupled with the fuze housing. The one or more canards are adjustable between two or more canard configurations. In a first canard configuration, the one or more canards are at a first canard angle relative to a bore sight of the fuze housing, and the first canard angle is configured for use with a first projectile. In a second canard configuration, the one or more canards are at a second canard angle relative to the bore sight of the fuze housing, and the second canard angle is configured for use with a second projectile. The first and second canard angles are different. In another example, in the first canard configuration the one or more canards include a first canard shape configured to provide a first specified trajectory with the first projectile.

Abstract: A projectile is provided for delivering a payload from a smoothbore launcher to a target. The projectile includes an aerodynamic stabilizer, an extender along which the stabilizer can longitudinally translate, and a chamber connected to the extender to contain the payload. The chamber can include a plastic bag for containing a liquid that represents the payload, and a plurality of holes that radially extend through its wall. The stabilizer enhances post-launch directional stability of the projectile by longitudinally translating rearward along the extender to shift center of pressure of the projectile aft of center of gravity of the projectile. The bag ruptures upon contact with the target, thereby disbursing the liquid through the holes. The bag can include malodorant or paint. The projectile can be contained within a gunpowder-loaded shotgun shell for launch.

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: The present invention relates to a fin-stabilized artillery shell (1) comprising a body part (8, 26, 36) which can be axially displaced rearwards, in the direction of flight of the shell, once the latter has left the barrel from which it has been fired, and which in the original position is fully retracted in the shell (1), and in which a number of deployable fins (18, 24, 29-30, 42-47) are in turn secured, and from which the fins are automatically deployed as soon as the body part has reached its rear position in which it is locked relative to the rest of the shell. One of the advantages of the invention is that in the flight position it gives the shell a greater length than is permitted by the charging position of the artillery piece launching the shell. This gives the shell considerably better stability in its trajectory towards the target.

Abstract: An inexpensive artillery munition of great range and acquisition accuracy for universal use while maintaining the external-ballistic coefficients is afforded when inserted between a standardized tail section (12) and also standardized tip section (13) is a load section (14) which connects the two contours of said sections together and which can be equipped with very different warheads which in particular are optimized against hard targets. For launch into an aerodynamically stabilized ballistic trajectory the tail section (12) is provided with super-calibre stabilization fins (17).

Abstract: The present invention relates to a long-range artillery shell (1) that is fin-stabilised in its trajectory and which is designed to be fired in a rifled gun barrel and thus has a slipping driving band (8) as main contact surface with the inside of the barrel, and has a so-called base-bleed unit (3) with a number of stabilization fins (9-14) that are deployable after the shell has left the barrel.

Abstract: A device for reducing base drag on cylindrical rear truncated objects moving in a fluid, caused by the shedding of vortices at the base of the object. The device consists of ring shaped winglets attached to the rear of the object which may be sub-divided into a plurality of hinged partial winglets. The parameters of distance of winglet from cylinder shaped object, winglet circumference, angle, profile and chord length may be varied automatically for optimum drag-reducing capability.

Abstract: A tail piece for a projectile includes at least three fins connected to either the projectile itself or a bracket connected to the projectile. Each fin is linked to the projectile/bracket by at least one fastening foot that cooperates with at least one recess of the projectile/bracket.

Abstract: An artillery rocket including a motor for the launching thereof into a ballistic trajectory across a specified target area over which a payload is to be released. The rocket is equipped with a flight controller or autopilot for the control over a rudder or control surface-setting or control system which is actuatable from a navigational receiver with actual positional coordinates. The flight controller operates on a control or setting system which is disposed in front of the warhead in the forward region of the nose cone without noticeably restricting the usable volume for the warhead.

Abstract: Infrared decoy flare having box fins which deploy upon firing of the flare from an aircraft to stabilize flare trajectory and flight path, and an aerodynamic nose to also enhance flight stability, as well as plume formation and subsequent decoying.

Abstract: A vehicle steering device is disclosed that can be joined to any air-drop, free-falling component and steers that component directly down to a pre-determined location on the earth's surface. The device is comprised of an aerodynamically-shaped housing that is joined to the front of the component, and which carries orientation means in a nose portion, high-density gravity-reaction means, and steering fins rotatably joined thereto. After the combination is dropped, at a pre-determined altitude and airspeed, the orientation means causes it to assume the most efficient aerodynamic position and then the gravity-reaction means forces the nose, which is joined to and leads the component, to dive into the earth. The reaction means are connected to the fins and force a controlled and predictable descent.

Abstract: The disclosed projectile has a tube forming a mortar, a munition contained in the tube, at least three deployable fins, solidly joined to the tube, and firing means triggering the ejection of the munition. During operation, when the projectile, released from an aircraft, lands on the ground for example, the fins form a pedestal in the mortar tube and, upon the command of the firing means, the munition is ejected to a certain distance from the tube.

Abstract: A pivoting guidance mechanism for small-calibered projectiles, missiles or small bombs with fins, which are form-fittingly fixed and axially oriented within a housing, are pivotable transverse to the longitudinal axis and guided in longitudinal slots in the housing, and which include a slider for extending the fins which is actuatable through a pretensioned, central coil spring.

Abstract: Apparatus for stabilizing a weapon launched from an aircraft. The weapon is rovided with a plurality of concentric rings mounted on the nose of the weapon for reducing nose lift. The tail of the weapon is provided with a plurality of wedge shaped fins positioned on a decreasing tail diameter which increases the tail stability while minimizing tail lift. The outer faces of the fins are of a multi-tiered construction with angled portions connecting the tiers.

Abstract: Stabilized ballistic projectiles of the explosive type (e.g. artillery and mortar shells, bombs) are described including a plurality of stabilizing fins symmetrically arranged around the nose of the projectile well forward of its center of mass and pivotable on axes at right angles to the projectile axis, the leading edge of each fin, and the pivot axis of each fin, being located with respect to the foremost point of the projectile, inclusive of its stabilizing fins, a distance which is substantially less than the length of the fin.

Abstract: An aerodynamic housing is disclosed for stabilizing the free-fall descent an article, particularly a sonobuoy, launched from an aircraft. The housing is cylindrically-configured and includes a tail section wherein a plurality of symmetrical channels are formed obliquely to the cylindrical surface of the housing about the circumference thereof, each channel having a leading edge in the shape of a truncated ellipse. A tailring mounted at the rear of the tail section partially covers the channels thereby forming contoured air ducts through which air flows during the free-fall to orient the housing vertically and stabilize the descent.