Abstract: A tail boom having a structure and a protuberance, the protuberance being secure with the structure. In each section of the tail boom, the protuberance extends in elevation over an extension height (Hext) and it extends laterally over an extension thickness (EPext), the extension height (Hext) lying in the range 0.05 times the maximum thickness (EPmax) of the structure, included, to 0.5 times the maximum thickness (EPmax), included, of the section, the extension thickness (EPext) lying in the range 0 to 0.4 times the maximum thickness (EPmax), included, of the section.

Abstract: A method and system for separating and releasing component parts of a payload of a floating platform in response to a high collision probability is disclosed. The method includes, determining if an in-flight aircraft is within at least a safety zone associated with a floating platform, wherein the floating platform comprises releasably-coupled component parts; and activating, responsive to a determination that the in-flight aircraft is within at least the safety zone, a release mechanism, wherein the release mechanism is configured to uncouple the component parts.

Abstract: A ballistic parachute associated with an aircraft is deployed where the aircraft includes a first part and a second part, the two parts are detachably coupled to each other when the ballistic parachute is deployed, and the ballistic parachute is coupled to the first part of the aircraft. A landing zone associated with the second part of the aircraft is determined and it is decided whether to decouple the two parts, including by deciding whether the landing zone associated with the second part of the aircraft is inhabited. If it is decided to decouple the two parts from each other, they are decoupled from each other.

Abstract: A method and system for separating and releasing component parts of a payload of a floating platform in response to a high collision probability is disclosed. The method includes, determining if an in-flight aircraft is within at least a safety zone associated with a floating platform, wherein the floating platform comprises releasably-coupled component parts; and activating, responsive to a determination that the in-flight aircraft is within at least the safety zone, a release mechanism, wherein the release mechanism is configured to uncouple the component parts.

Abstract: A device may determine that a charge of a capacitor of the device, powered by solar energy, satisfies a threshold. The device may power on a first set of components of the device based on determining that the charge of the capacitor satisfies the threshold. The device may obtain ephemeris data based on powering on the first set of components. The device may power on a second set of components of the device based on obtaining the ephemeris data. The device may obtain GPS data using the ephemeris data and based on powering on the second set of components. The device may transmit the GPS data. The device may power off at least one component, of the first set of components or the second set of components, after transmitting the GPS data.

Abstract: Apparatus and methods determine the rotational position of a spinning object. A satellite positioning system can be used to determine the spatial position of an object, which in turn can be used to guide the object. An adaptive sideband filter is used to provide increased robustness against interference. However, when the object is spinning, such as an artillery shell, then the rotational orientation should be known in order to properly actuate the control surfaces, such as fins, which will also be spinning.

Abstract: A ballistic parachute is released to slow descent of a cabin and an airframe where the airframe supports a plurality of rotors and the cabin removably attaches to the airframe. A ground condition is detected and it is decided whether to detach the airframe from the cabin. The airframe is detached from the cabin in response to the decision.

Abstract: An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.

Abstract: Disclosed is a method for delivering a load on-board an aircraft to a target. The method comprises: acquiring a position of the target; acquiring parameter values relating to aircraft maneuverability; acquiring load properties; acquiring parameter values relating to environmental conditions; using the acquired information, determining a position and a velocity value; performing, by the aircraft, the procedure; and, at a point in the procedure that the aircraft has the determined position and its travelling at a velocity equal to the determined velocity value, releasing the load. The determined position and velocity value are such that, were the aircraft to release the load while having the determined position and velocity, the load would travel to be within a predetermined distance of the target. The procedure is such that the aircraft would have the determined position and velocity at some time-step.

Abstract: Wing deployment mechanism for deploying a pair of wings from an airborne body, wherein their deployment in motion, each one around an axis, defines the wings' deployment plane relative to the airborne body, and wherein the mechanism is characterized by that it comprises a propelable assembly mounted in the airborne body and suited to a rotational motion around an axis that is substantially orthogonal in its direction to the wings' deployment plane, a pair of arms that are linked, each one, on its one side to the assembly and at distance from the assembly's rotation axis, and on its other side to an end of one of the wings and at a distance from the axis around which the rotational motion of the wing in the wings' deployment plane is enabled, and wherein the link of each one of the arms is performed in a manner that enables angular motion of each of the arms relative to the assembly and to the end of the wing unto which it is linked, and wherein propelling the assembly to rotational motion and actuating a mome

Abstract: A method of actuating a control surface in a munition. The method including: coupling a pair of fins to an actuation device; generating pressurized gas to selectively actuate the actuation device; and converting the actuation of the actuation device to rotation of the pair of fins. The converting can convert a linear output of the actuation device to the rotation of the pair of fins or a rotary output of the actuation device to the rotation of the pair of fins. The generated gas can be directly provided to the actuation device or the generated gas can be stored in a storage device before being provided to the actuation device. The method can further include repeating the coupling, generating and converting for a second pair of fins.

Abstract: A self-controlled device maintains a frame of reference about an x-, y- and z-axis. The self-controlled device processes an input to control the self-propelled device, the input being based on the x- and y-axis. The self-propelled device is controlled in its movement, including about each of the x-, y- and z-axis, based on the input.

Abstract: A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead having an outer casing. The warhead includes a frangible container within the outer casing of the warhead and a destructive element within the frangible container. The destructive element is formed with a non-explosive material. The weapon may also include a guidance section configured to direct the weapon to a target.

Abstract: A flying bomb includes a standardized bomb casing formed of steel and having a nose opening and a tail opening. A thin penetrator is disposed in the bomb casing in order to achieve high effectiveness with little collateral damage when the flying bomb strikes a target. A distance between the tip of the penetrator and the nose opening is greater than 100 mm.

Abstract: Methods and apparatus for varying a trim of a vehicle are provided. A nose cone assembly for a vehicle includes an angle cone portion and a nose cone portion rotatably coupled to the angle cone portion. The angle cone portion and the nose cone portion are arranged such that a plane of rotation between the angle cone portion and the nose cone portion is slanted at an angle relative to a plane perpendicular to a long axis of the vehicle. The angle cone portion rotates relative to the vehicle body about the long axis. The nose cone portion rotates relative to the angle cone portion about an axis normal to the plane of rotation. A tip of the nose cone portion varies in position relative to the long axis of the vehicle based on the rotation of the angle cone portion and the rotation of the nose cone portion.

Abstract: An optically guided munition and control system has a replacement fuse assembly mounted on the front of a munition body or shell casing. An optical seeker subsystem detects an illuminated target and supplies signals to a processor. The processor develops steering commands sent to a flight control subsystem having a plurality of guidance canards which are actuated by drive motors through gear assemblies. The roll of the munition is established and left/right and up/down steering commands are sent to the canard drive motors based upon the optical seeker subsystem detection of the target illuminator. Range adjustment is based upon bore sight lockdown angle and cross range control is based upon left/right centering error. A code is contained in the optical radiation received from the illuminated target which must be validated by a preset code in the system processor to arm the munition.

Abstract: A flying bomb includes a standardized bomb casing formed of steel and having a nose opening and a tail opening. A thin penetrator is disposed in the bomb casing in order to achieve high effectiveness with little collateral damage when the flying bomb strikes a target. A distance between the tip of the penetrator and the nose opening is greater than 100 mm.

Abstract: A kit for upgrading a non-guided shell to an airborne guided shell includes a device to couple the kit to the body of the non-guided shell. A fastener provides for fastening the resulting airborne shell to an aircraft and for detaching it there from. The kit also provides for causing the trajectory of the shell to change once detached from the aircraft according to instructions received in the kit; for determining the position of the shell; and for transferring data from the carrying platform to the guidance kit.

Abstract: A spin rate tracking system comprising a guidance system suitable for adjusting a flight path of a vehicle based on a spin rate of the vehicle, a signal reception system configured for receiving signal information from a global navigation system wherein a spin rate of the vehicle is derived from a substantially harmonic pattern produced amongst a global navigation signal.

Abstract: Apparatus and methods provide a kit for converting a conventional mortar round into a glide bomb. Mortar rounds are readily available to combat personnel and are small and light enough to be carried by relatively small unmanned aerial vehicles (UAVs) such as the RQ-7 Shadow. Advantageously, the kit provides both guidance and relatively good standoff range for the UAV such that the kit-equipped mortar round can be dropped a safe distance away from the intended target so that the UAV is not easily observed near the intended target.

Abstract: A system for launching, controlling and delivering in a preselected target pattern a plurality of low-cost, guided fire-retardant-containing vehicles, i.e., “smart water bombs” equipped with control surfaces sufficient to provide limited lift and maneuverability to respond to guidance command to place it at a selected GPS coordinate within a large footprint in time and space and to discharge its payload of fire retardant at a preselectable altitude in a very precise manner and dispersion pattern. A controller determines bombing patterns and timing for all bombs and trajectories for each guided bomb. Dynamic differential equations are used to determine location and time of release of the guided bombs to achieve the target while avoiding collisions among guided bombs and aircraft.

Abstract: The present invention is a multi-element anti-jamming (A/J) antenna array. The antenna array includes a first multi-band GPS edge-slot antenna and a second multi-band GPS edge-slot antenna. The first edge-slot antenna and the second edge-slot antenna are configured for implementation within at least one of an artillery shell and a munition. The first edge-slot antenna and the second edge-slot antenna are each further configured for supporting L-band frequencies.

Abstract: A pneumatic launch system includes a manifold that stores pressurized gas and releases the pressurized gas on command to sequentially open the store retention hooks and eject the store. The manifold includes an eject valve whose main chamber is part of the high pressure gas storage. A hook release valve is controlled by the eject valve for sequential operation of hook opening and store ejection. A manually selectable pitch valve provides pitch setting to proportion the gas delivered to the ejector cylinders. The manifold minimizes flow path restrictions and provides a fast actuation response with minimum variability to unlock the hooks and quickly eject the store.

Abstract: A guidance system according to various aspects of the present invention operates in conjunction with a suite of different ordnance delivery devices. In one embodiment, the guidance system comprises an interface configured to attach to the ordnance delivery devices in the suite, such as via the fuze well. The guidance system may further include a control system adapted to attempt to establish communications with a subsystem of the ordnance delivery device and operate the guidance system as a standalone guidance system if the attempt fails. The guidance system may further include a control surface interchangeably attachable, for example via an interchangeable control surface module.

Abstract: Methods and apparatus for a fast action impulse thruster according to various aspects of the present invention may comprise a projectile comprising an impulse thruster system. The impulse thruster system may comprise a guidance system and a fast action impulse thruster system. The guidance system may control the trajectory of the projectile, for example by activating the fast action impulse thruster system to adjust the projectile's trajectory. The fast action impulse thruster system may be configured such that it may provide an impulse force to guide the projectile with a reaction time that is not affected by the rotational velocity of the projectile. The impulse force may be achieved by ejecting at least one mass from the projectile at high velocity such that a resulting momentum exchange may alter the trajectory of the projectile.

Abstract: A spin-stabilized projectile is steered by taking air from an air intake at the front of the projectile, and expelling the air along an outer surface of the projectile to alter its trajectory toward the desired impact location. Air taken in through the air intake is directed toward a rotor that is able to rotate relative to the rest of the projectile. The rotor has an outlet that may direct the air taken in at the air inlet out in a direction having both radial and circumferential components. The force produced in the radial direction provides a steering force substantially normal to the projectile axis, used to steer the projectile. The force produced in the circumferential direction is used to provide impetus to spin the rotor. A brake is used to control the rotational speed of the rotor, to control the direction that the air is expelled from the projectile.

Abstract: The present invention is a folded monopole antenna assembly. The folded monopole antenna assembly includes a dielectric substrate, the dielectric substrate being configured for receiving at least one input. The folded monopole antenna assembly further includes a folded monopole antenna. The folded monopole antenna is configured for being connected with the dielectric substrate. Further, the folded monopole antenna includes at least one reactive circuit. The folded monopole antenna is further configured for receiving a signal via a received input included in the at least one received input. The antenna assembly is configured for implementation within an artillery shell and/or a munition.

Abstract: The present invention is a device which includes an antenna and circuitry. The antenna may receive a circularly-polarized signal as first and second linearly-polarized signals. The circuitry is connected to the antenna and is configured for combining the first and second linearly-polarized signals to produce at least two reception patterns. The reception patterns are created by summing the first and second linearly-polarized signals via phase shifting. The reception patterns are optimized for at least two substantially different directional orientations. Further, the antenna may simultaneously allow/provide spec-compliant Global Positioning System operation and spec compliant Height of Burst operation.

Abstract: According to one embodiment, a system of powered bomb guidance includes a munition and a guidance system operable to detect a relative position of a target. The guidance system determines course corrections to direct the munition to the target and generates a control signal reflective of the course corrections. One or more explosive guidance units are disposed at one or more control surfaces disposed along an outer surface of the munition. Each explosive guidance unit is mechanically coupled to one of a plurality of control surfaces and in electrical communication with the guidance system. Each explosive guidance unit is configured to detonate in response to receiving the control signal from the guidance system and is further configured to apply force upon detonation to the control surface to which it is coupled.

Abstract: A method and system for guiding and controlling an ordinance body having a trajectory and a bore sight angle including making corrections to the trajectory based on bore sight angle vs. time history. The system is incorporated with existing fuse components in a replacement kit for existing munitions. The method determines nominal time values of the ballistic trajectory of the munition in relation to launch time and determines deviation from the nominal time values by an algorithm by analyzing signals received from a source of radiation located at the target. A processor determines lateral (left/right) and range errors and provides commands to a plurality of flight control surfaces mounted on the munition.

Abstract: A guided missile or projectile and associated guidance control are provided to control a path to a point of intersection with a potentially moving target. A new path is repetitively recomputed and acceleration orthogonal to the path is applied to minimize heading error and thereby to converge on the target. The gain of the control function is partly proportional to heading error, but the gain is reduced approaching the point of convergence. In this way, the guidance control is more responsive to actual variance of the true heading error and is less responsive to random error in sensing the target heading, which random error would otherwise increase in its contribution to corrective guidance movements approaching the point of intersection.

Abstract: A non-spinning projectile that is self-guided to a laser designated target and is configured to be fired from a small caliber smooth bore gun barrel has an optical sensor mounted in the nose of the projectile, a counterbalancing mass portion near the fore end of the projectile and a hollow tapered body mounted aft of the counterbalancing mass. Stabilizing strakes are mounted to and extend outward from the tapered body with control fins located at the aft end of the strakes. Guidance and control electronics and electromagnetic actuators for operating the control fins are located within the tapered body section. Output from the optical sensor is processed by the guidance and control electronics to produce command signals for the electromagnetic actuators. A guidance control algorithm incorporating non-proportional, “bang-bang” control is used to steer the projectile to the target.

Abstract: A method of assembling an external telemetry unit for a projectile comprising the steps of providing a shell whose inside is formed to match the contour of the projectile body, encircling the front of the shell with a flexible battery and flexible electronic circuitry, and covering the flexible battery and flexible electronic circuitry with a plurality of contoured antennas. Also disclosed is a method of using an external telemetry unit comprising the steps of removing the fuze from a projectile having a projectile body and a fuze, sliding the unit over the front of the projectile body; reinstalling the fuze, firing the projectile, and observing the projectile data transmitted by the unit.

Abstract: The present invention provides an unpowered low-cost “smart” micromunition unit for a weapon system for defense against an asymmetric attack upon ships and sea or land based facilities. A plurality of air dropped micromunition units are each capable of detecting and tracking a plurality of maneuvering targets and of establishing a fast acting local area wireless communication network among themselves to create a distributed database stored in each deployed micromunition unit for sharing target and micromunition unit data. Each micromunition unit autonomously applies stored algorithms to data from the distributed database to select a single target for intercept and to follow an intercept trajectory to the selected target. It is emphasized that this abstract is provided to comply with the rules requiring an abstract that will allow a searcher or other reader to quickly ascertain the subject matter of the technical disclosure.

Abstract: An external telemetry unit for a projectile. The external telemetry unit comprises a shell adapted to be inserted between the front of the projectile body and the fuze, a flexible battery and flexible electronic circuitry encircling the front of the shell, and a plurality of contoured antennas covering the flexible battery and flexible electronic circuitry. The inside of the shell is formed to match the contour of the projectile.

Abstract: The centroid of the discrete components forming the overall radar return from a target onto which a homing weapon is being guided may not coincide with a desired aimpoint on the target. Herein proposed is the discrimination and comparison of returns from different portions of the weapon sensor's field-of-view, i.e. different portions of the target and guidance of the weapon in dependence upon the relative values of the differences between those returns. As a result, the weapon can hit say the center of a tank turret roof rather than the probably heavily armored area forward of the turret roof.

Abstract: The centroid of the discrete components forming the overall radar return from a target onto which a homing weapon is being guided may not coincide with a desired aimpoint on the target. Herein proposed is the discrimination and comparison of returns from different portions of the weapon sensor's field-of-view, i.e. different portions of the target and guidance of the weapon in dependence upon the relative values of the differences between those returns. As a result, the weapon can hit say the centre of a tank turret roof rather than the probably heavily armoured area forward of the turret roof.

Abstract: Actuators already present as an integral part of the control systems of missiles and the like are used to activate and control the deployment of fins and the like without the need for separate explosively or mechanically driven fin deployment systems. Springs located in hinges on the fins accomplish the complete deployment of the fins after proper orientation by the actuators.

Abstract: A fuzing system for non-spinning or substantially non-spinning weapons is implemented by means of wide angle optics providing at least forward-hemisphere coverage, an array of infrared detectors and a microprocessor for image and data processing, aim-point selection, directional-warhead aiming and skewed-cone fuzing. The skewed-cone fuzing has a generatrix which is the vector sum of missile velocity, warhead velocity and the negative of target velocity.

Abstract: A projectile (12) to be fired from a rifled barrel (66) is described. At its tail (10) it has control surface vanes (14) which can be pivoted out from a sub-calibre launch position into an over-calibre functional position. To protect the inwardly folded vanes (14) and to protect further ballistic and sensor structures at the tail end of the projectile (12), a securing pot (18) is temporarily fixed to the tail (10) of the projectile (12), the securing pot having a pot peripheral portion (22) and a pot bottom (24). There is a pressure chamber (32) between the tail end face (26) of the projectile (12) and the pot bottom (24) of the securing pot (18). The pot bottom (24) has at least one propellent gas inlet (34) which opens into the pressure chamber (32). When the projectile (12) is fired from the barrel propellent gas flows through the propellent gas inlet (34) into the pressure chamber (32) so that a correspondingly high propellent gas pressure is produced in the pressure chamber (32).

Abstract: A weapon system comprising a mobile platform (1) e.g. an aircraft incorporating a first three-axis attitude reference sub-system (13), and a guidable vehicle (3) launchable from the platform (1) and incorporating a guidance sub-system (15) incorporating gyros (17) wherein correction of gyro parameters, i.e. scale factor and zero offset, of the vehicle attitude reference sub-system (15) is effected prior to launch of the vehicle (3) on the basis of repetitive comparisons of attitude data as measured by the platform and vehicle sub-systems (13, 15). The vehicle (3) may comprise a dispenser of a number of munitions (5) each itself incorporating a guidance sub-system (25) incorporating gyros (27), in which case corrections of gyro parameters of the missile guidance sub-system (25) may be effected prior to missile launch on the basis of repetitive comparisons of attitude data as measured by the dispenser and munition sub-systems (15, 25).

Abstract: A system and method for guiding an artillery shell in flight which includes a multi-element antenna having a large central access hole therein for receiving an airfoil actuator pin, the antenna array being switched during flight, as a function of the rotation of the shell, so that the upwardly directed portion of the radiation pattern predominates over a terrestrially directed segment of the radiation pattern.

Abstract: A fuzing system for non-spinning or substantially non-spinning weapons is implemented by means of wide angle optics providing at least forward-hemisphere coverage, an array of infrared detectors and a microprocessor for image and data processing, aim-point selection, directional-warhead aiming and skewed-cone fuzing. The skewed-cone fuzing has a generatrix which is the vector sum of missile velocity, warhead velocity and the negative of target velocity.

Abstract: A target-penetrating aerial bomb includes a penetrator of hard steel or similar material that contains an explosive charge. A rocket motor is formed as an annular chamber and surrounds the penetrator. The bomb includes a guidance and control unit that guides the bomb on a glide path after release from the delivery aircraft, and steers the bomb onto a dive line. Once the bomb is aligned on the dive line, the guidance and control unit fires the rocket booster to accelerate the bomb to the target. A fuse ignites the explosive after target penetration.

Abstract: The disclosure relates to a low cost and highly accurate precision guided system suitable for use in conventional aircraft launched bombs. The system includes a kit mounted upon the nose of the conventional bomb which replaces the conventional fuse disposed in a fuse well, the kit including guidance electronics controlling a self-contained jet reaction device and GPS P-code receiver electronics. The bombs are readied for discharge by signals broadcast from the aircraft into the bomb bay which transfer initial GPS data and commence operation of a gas generator which powers the jet reaction device.

Abstract: A tail fin assembly for a munition having a housing configured for attachment to the munition, at least one flight control surface, an actuator for effecting movement of the flight control surface(s), so as to facilitate guiding of the munition, and a guidance system for controlling the actuator mechanism. The guidance system has a global positioning system (GPS) receiver for effecting control of the actuator mechanism.

Abstract: A guided bomb is provided with a central hardback section having a pair of extensible wings pivotally attached thereto. The hardback section is attached to the bomb by a saddle member. After launch of the bomb from the aircraft, the wings are extended by means of an electric motor and gear train to provide the lift necessary for gliding flight. One or more ailerons are provided on the trailing edges of the wings to enable control of the flight, these ailerons being controlled by the bomb's resident guidance system. The geometry of the wings, the hardback section and saddle member are designed so that the guided bomb units can be fitted within a restricted space on bomber aircraft rotary launchers.

Abstract: The recoverable airborne instrument platform accurately determines its present position and uses this data to execute a predetermined flight plan and ultimately guide its descent to a predetermined landing site. This is accomplished by installing the instrument package payload in the aerodynamic exterior housing of the recoverable airborne instrument platform, which has a plurality of moveable control surfaces thereon to autonomously control the altitude, attitude and flight path of the recoverable airborne instrument platform. A navigation circuit contained within the aerodynamic housing determines the geographic location of the recoverable airborne instrument platform as well as the location of at least one predetermined recovery site. The determined position data is used to dynamically calculate a flight path which allows the guidance control circuit to both execute a predetermined flight plan and controllably descend the recoverable instrument platform to a selected predetermined recovery site.

Abstract: An aerial cargo container system for transporting cargo from an aircraft to the ground having a cargo box with a continuous side wall with six rectangular side panels, and rotor blades having stowed positions against alternating box side panels and deployed positions extending outwardly from the box in a generally horizontal plane. Each blade may include a lower panel and an upper panel that has two triangular sections behind the leading edge that forms an aerodynamic camber. The blades are hinged to a rotor hub secured across the top of the box. The upward deployment of the blades is limited by tethers extending from the blades down to a tether attach frame secured across the bottom of the box. The box and blades are preferably formed of corrugated paper or plastic material. The entire unit rotates with the load to create aerodynamic braking and lower cargo to the ground with a minimum of energy being translated to the cargo on impact.

Abstract: Process for guiding an elongated missile, equipped with booster motor, sustainer, power source, control electronics, payload, and search head, from above, upon a target, such as a helicopter, where the missile, after ballistic flight, is braked before the target area by a drogue chute and is diverted into a position that is essentially perpendicular to the earth's surface over the target area so that the search head of the missile, which is suspended from the drogue chute, will be pointed downward, whereupon, after the search head has locked on the target, the drogue chute is separated and the missile is guided to the target by the sustainer, characterized in that, immediately prior to, before, or after the moment of drogue chute deployment, a lateral motor, located in the center of gravity of the missile, is turned on so that, first of all, in order to accelerate the tilt-off of the missile into the vertical, there is generated a force that is added vectorially to the force of gravity and that thereupon one