83results about "Fall bombs" patented technology

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. It is submitted with the understanding that it will not be used to interpret or limit the scope of the claims.

The present invention comprises a warhead designed to provide a number of spiraling tendrils composed of segmented rods that move in an increasing radial arc in order to defeat a target. The warhead comprises a substantially cylindrical explosive charge having a plurality of rod segments arranged circumferentially around the explosive charge in a plurality of horizontal layers. As the horizontal layers descend down the explosive charge, the rod segments are offset from those directly above and below them to create a pattern that appears to be twisted columns. The number of columns is equivalent to the number of rod segments in each horizontal layer.

A fire-extinguishing bomb that can be pre-programmed to explode 2-200 feet above the ground or tree line. The bomb employs a laser or barometric altitude sensor in combination with a GPS-altitude sensor for failsafe detonation with extreme accuracy at the proper altitude. The redundant failsafe altitude-dependent detonation system ruptures a container carrying a payload of wet or dry fire retardant / suppressant, preferably dry environmentally-friendly fire-retardant powder having no toxicity and having fertilizer properties. Upon detonation the device coats the ground below with a uniform fire extinguishing coating. The core components of the bomb can be biodegradable, or alternatively can be readily retrieved and reused after each activation, thereby increasing both economy and reducing environmental concerns.

A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead having destructive elements. The weapon also includes a folding lug switch assembly that provides a mechanism to attach the weapon to a delivery vehicle and is configured to close after launching from the delivery vehicle, thereby satisfying a criterion to arm the warhead. The weapon still further includes a guidance section including an antenna configured to receive mission data before launching from the delivery vehicle and further configured to receive instructions after launching from the delivery vehicle to guide the weapon to a target.

An aerial surveillance device is provided, comprising an image capturing device capable of being supported by an airframe structure above the ground. The airframe structure includes a body portion defining a longitudinal axis and configured to support the image-capturing device. A tail portion having control surfaces is operably engaged with the body portion along the axis. Transversely-extending wing portions are directly engaged with the body portion. Each wing portion is defined by longitudinally-opposed spars extending from a spaced-apart disposition at the body portion to a common connection distally from the body portion. The spars have a fabric extending therebetween to provide a wing surface. A support member extends along an aerodynamic center, transversely to the body portion, of each wing portion, to tension and rigidify the wing portions so as to provide a positive camber for the wing portions and to form an airfoil.

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.

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.

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 steering commands to a plurality of flight control surfaces mounted on the munition.

A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead including destructive elements and a guidance section with a target sensor configured to guide the weapon to a target. The target sensor includes a front lens configured to provide a cover to protect the target sensor from an environment and a fast fresnel lens behind the front lens to provide a multi-lens focusing system for the target sensor. In a related embodiment, the weapon includes an aft section including a tail fin having a modifiable control surface area thereby changing an aspect ratio thereof.

A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead including destructive elements and a guidance section with a seeker configured to guide the weapon to a target. The seeker includes a detector configured to receive a distorted signal impinging on an objective lens from the target, memory configured to store target criteria and a correction map, and a processor configured to provide a correction signal based on the distorted signal, the target criteria and the correction map to guide the weapon to the target.

Methods and devices for differentiating an actual air drop of a gravity dropped weapon from an accidental drop of the weapon onto a surface. The method including: connecting a first end of at least one lanyard to an airframe; releasably connecting a second end of the at least one lanyard to a power generation device such that release of the second end with the power generation device initiates power generation by the power generation device; and releasably connecting a third end of the at least one lanyard to at least a portion of an air velocity sensor such that release of the third end one of activates or exposes the air velocity sensor to an air stream; and differentiating the actual air drop from the accidental drop based at least on a detection of an air velocity by the air velocity sensor.

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. The fast action impulse thruster system may also be configured in such a way so as to provide a significant improvement to the overall safety during the production, assembly, and handling of the projectile.

A water pod for assisting a user in extinguishing forest fires includes a hollow shell constructed with a biodegradable plastic that ruptures upon impact when dropped from an aircraft. The shell includes a fill port allowing it to be filled with water or another flame retardant material. The shell may include a detonation device allowing the pod to be ruptured prior to impact, if desired.

A mounting set for use in mounting an external stores to a mounting station of an aerospace vehicle includes a mounting bracket arrangement and a strap arrangement. The bracket arrangement is configured for selective reversible engagement with respect to the mounting station and for cooperating with the strap arrangement. The strap arrangement is configured for securing the bracket arrangement to the stores in load bearing abutment therewith to enable transfer of loads between the stores and the mounting station via said bracket arrangement, in operation of said mounting set. A mounting system is also provided for mounting an external stores to an aerospace vehicle having two or more mounting stations, including a mounting set for each mounting station. Mounting methods are also provided.

The invention, as embodied herein, comprises a variable yield warhead comprising an inner core of cylindrically-shaped, explosive material surrounded by an outer annulus of a different explosive material. The inner core explosive material has a heat of combustion comprising about 16 kcal / cc or higher and the outer annulus of explosive material has a heat of detonation comprising about 2.1 kcal / cc or higher. A warhead casing surrounds the outer annulus of material. The warhead has a dual initiation system. The first initiation system comprises a detonation cord that extends substantially through the inner core of explosive material and has an initiator at the tope side. The second initiation system comprises a booster explosive that contacts the bottom side of the outer annulus of explosive material and an initiator proximate to the booster.

An ordnance for air-borne delivery to a target under remotely controlled in-flight navigation. In one embodiment, self-powered aerial ordnance includes upper and lower cases. A plurality of co-axial, deployable blades is powered by a motor positioned in the upper case. When deployed, the blades are rotatable about the upper case to impart thrust and bring the vehicle to a first altitude above a target position. An explosive material and a camera are positioned in a lower case which is attached to the upper case. The camera generates a view along the ground plane and above the target when the ordinance is in flight. When the vehicle is deployed it is remotely controllable to deliver the vehicle to the target to detonate the explosive at the target. The ordnance may drop directly on a target as a bomb does.

A general purpose bomb having a shaped charge penetrator warhead mounted in the front of the bomb and facing forward, in which the caliber of the warhead is at least 90% of the caliber of the general purpose bomb.

The dynamically configurable controlled fragmentation insert mechanism of this invention includes an assembly of three or more sleeves with differing through hole patterns thereon, that fit inside the shell casing. The individual sleeves can move independently of one another and a simple pinning mechanism holds the parts in place for a selected configuration. The warfighter can realign the insert sleeves by to create different geometric patterns of holes, each designed to engage a different target set with optimally sized fragments. The aligned patterns of holes creates individual geometric shapes that focus high-velocity jets to cut into the steel shell casing to correlate to the through-holes in the aligned patterned sleeves. Realigning the insert sleeves changes the through-hole pattern to produce different fragment sizes and mass distributions. To defeat light armored vehicles for instance, a warfighter can deploy a sleeve hole pattern to produce larger fragments with greater penetrating power, while to engage enemy troops for instance, a warfighter can “dial in” another hole pattern through the fuze assembly to otherwise produce a much larger number of smaller, lighter fragments.

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.

An agent defeat bomb including a payload with at least one metal-based high thermal component, effective for producing high temperature, and a plurality of oxidizer components, such that the high thermal component and oxidizer are progressively stacked through the length of the projectile and react within the body of the bomb.

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.

The present invention relates to a kind of pneumatic cross rotary wing and ring tail wing for end-sensing ammunition, bomb, shell and flying vehicle of modern weapon system. It is characterized by that on a launching body or machine body a ring rollable mounting frame, a distance-increasing small-type rocret engine and a tail cone portion for adding tail cone and mounting tail cone cover are set, and an automatic control device is placed in its interior. It is an effective lift equipment which is simple in structure and has good aerodynamic characteristics for distance-increasing end-sensing ammunition and flying vehicle.

Multi-charge munition suitable for defeating a concrete target consists of a detonatable array of hollow primary charges (14) of explosive supported laterally of a line of target penetration on which is disposed a secondary explosive charge (48). Simultaneous detonation of the primary charges in the array causes jet penetrators to be projected together towards the target which produce wide boreholes in concrete suitable for the subsequent emplacement and detonation of the secondary charge. The munition may be an aerially-deliverable bomb or submunition.In one preferred embodiment, the primary charges (14) are positioned in a convergent configuration behind a forwardly-tapered secondary charge (48). Detonation of the primary charges projects penetrators forwardly passed the sides of the secondary charge and thrusts the secondary charge into the borehole produced in the target by the penetrators.

The invention has a guidance and control system (44) which includes an optical seeker subsystem (17), a processor subsystem (46), a three-axis guidance control subsystem (25). The processor subsystem (46) includes a 3-axis MEMs rate sensor (63), a roll algorithm device (65), a seeker detection algorithm device (51), and a guidance algorithm device (67). The flight control subsystem (25) include three canard axis drives (32).