620 results about "Artillery" patented technology

The invention discloses an unmanned aerial vehicle system and a method for dynamically positioning a ground moving target, belonging to the fields of unmanned aerial vehicle system application and the like. The unmanned aerial vehicle system comprises an unmanned aerial vehicle body, a vehicle-mounted photoelectric rotating tower and a ground control terminal, wherein the unmanned aerial vehicle body comprises an acquisition device, the vehicle-mounted photoelectric rotating tower comprises a photoelectric sensor and a sight-stabilizing platform, and the ground control terminal comprises a determining device, a trace command generating device, a resolving device and a predicting device. According to the technical scheme provided by the invention, geographical coordinate information including latitude, longitude and the like of a tracked ground moving target can be output in real time, the original geographical coordinate information can be accurately and quickly fitted, the moving trend of the ground moving target can be predicted and evaluated, and the original geographical coordinate information can be screened to realize display and prediction of the track of the moving target; the positioning accuracy acquired by the unmanned aerial vehicle system and the method approaches that of static positioning and can meet requirements for initial alignment of weapons including artilleries and the like, and the probability of fusion processing of an unmanned aerial vehicle intelligence system and an entire-army intelligence gathering network is provided.

The multi-target tracking and discrimination system (MOST) fuses with and augments existing BMDS sensor systems. Integrated devices include early warning radars, X-band radars, Lidar, DSP, and MOST which coordinates all the data received from all sources through a command center and deploys the GBI for successful interception of an object detected anywhere in space, for example, warheads. The MOST system integrates the optics for rapid detection and with the optical sensor array delivers high-speed, high accuracy positional information to radar systems and also identifies decoys. MOST incorporates space situational awareness, aero-optics, adaptive optics, and Lidar technologies. The components include telescopes or other optical systems, focal plane arrays including high-speed wavefront sensors or other focal plane detector arrays, wavefront sensor technology developed to mitigate aero-optic effects, distributed network of optical sensors, high-accuracy positional metrics, data fusion, and tracking mounts. Field applications include space monitoring, battlefield artillery, battlefield management, ground defense, air defense, space protection, missile defense, gunfire detection, and the like.

A handheld controller allows a human operator to control various aspects of a vehicle's operation. The operator's fingers are used to manipulate various devices (e.g., buttons, switches, joysticks, levers, triggers, trackballs and the like) disposed on the handheld controller to control aspects of the vehicle's operation associated with these devices. The handheld controller may provide control signals to the vehicle by a cable, or by a wireless connection. The handheld controller allows the operator to freely move about the vehicle's compartment or to move outside the compartment, while still being able to control the various aspects of vehicle operation. Furthermore, the handheld controller allows the operator to control the various aspects of vehicle operation from a location away from potentially hazardous surfaces within the compartment, which helps to prevent the operator from contacting these surfaces in the event that the vehicle is struck by an object (e.g., enemy artillery, another vehicle, etc.) or otherwise jarred.

A dual condition fire / smoke detector system includes a housing and a sensor comprising at least two of a photoelectric sensor, a heat sensor, an ionization sensor or a carbon monoxide sensor disposed within the housing. A wireless communication system associated with the sensor enables communication of the detector with a remote device via a wireless receiver and a wireless transmitter. A light source associated with the housing may be positioned to illuminate an exit in response to a hazard detected by any of the aforementioned sensors.

A dynamically-reconfigurable multiband multiprotocol communications jamming system and method is provided that are particularly suited for the generation of effective radio-frequency waveforms / noise output that successively translates up and down the RF spectrum. The system and method are particularly suited for strategically targeting specific frequencies in order to disrupt a communications network or networks, and can be rapidly deployed via delivery platforms, such as artillery and other projectile mechanisms, remote operated vehicles (unmanned aerial, sea or land systems) or targeted air or land delivery via manned assets or automated or robotic support means, or manual delivery by personnel.

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.

A modular reconnaissance capsule or reconnaissance pod is provided that is suitable for deployment by means of an artillery launching platform, such as a conventional 40 mm grenade launcher or 155 mm cannon wherein a parachute is deployed at a pre-calculated observation altitude, the parachute being designed to yield a sufficiently slow rate of descent to permit live video capture and transmission of images as forward observation information. Alternatively, pods according to the invention may also be air dropped from an aircraft, either piloted or pilotless, thus allowing the aircraft to operate at a safe distance and yet provide close reconnaissance even under a cloud cover. Accurate information about targeting dynamics is made available to the user through commercially available products. The invention complements other reconnaissance methods and provides easy-to-use real-time visual information for a desired area of interest.

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.

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.

The invention provides a self-propelled mobile system that is characterized by a lightweight space frame chasis on which is mounted a large caliber artillery piece. The weight of the system is preferably less than 8.000 kg and the artillery piece preferably has a calibre of up to a 155 mm 52 caliber gun. The artillery piece may include a lightweight elevating and traversing mass and gun chasis mounted on a space frame vehicle, such vehicle having a weight which does not exceed 3,800 kg.

A simple RF system tracks a missile, bullet or artillery round and determines the instantaneous attitude of the spinning projectile while in flight. The system is particularly useful in command-guided weapons systems where line-of-sight is maintained from the launch platform to the target. The system includes a first pair of linearly polarized transmit antennas spaced apart on the projectile for transmitting a signal and a harmonic of that signal. A receiver on the launch platform determines the roll angle and either the yaw or pitch angle from the received signals. To determine the remaining angle, either the receiver samples the received signals ninety degrees out of phase or a second pair of transmit antennas are mounted on the projectile, preferably ninety degrees from the first pair, for transmitting another pair of harmonic signals.

In one aspect, an artillery projectile apparatus is provided that includes a carrier projectile containing a payload, and a fuze disposed at an ogive of the projectile and which is configured to eject the payload when the fuze is detonated. The fuze includes a receiver configured to receive location information from a radionavigation source and a processor configured to acquire position data from the receiver. The processor is also configured to estimate a projectile flight path using the position data, to determine intercept parameters of the artillery projectile relative to an ejection plane of its payload cargo, and to adjust an ejection event initiation command time of the payload in accordance with the determined intercept parameters. In some configurations, the present invention dramatically decreases range errors typically associated with delivering artillery payloads to specific targets.

A dynamically-reconfigurable multiband multiprotocol communications jamming system and method is provided that are particularly suited for the generation of effective radio-frequency waveforms / noise output that successively translates up and down the RF spectrum. The system and method are particularly suited for strategically targeting specific frequencies in order to disrupt a communications network or networks, and can be rapidly deployed via delivery platforms, such as artillery and other projectile mechanisms, remote operated vehicles (unmanned aerial, sea or land systems) or targeted air or land delivery via manned assets or automated or robotic support means, or manual delivery by personnel.

A Reconfigurable Nose Control System (RNCS) is designed to adjust the flight path of spin-stabilized artillery projectiles. The RNCS uses the surface of a projectile nose cone as a trim tab. The nose cone may be despun by the action of aerodynamic surfaces, to zero spin relative to earth fixed coordinates using local air flow, and deflected by a simple rotary motion of a Divert Motor about the longitudinal axis of the projectile. A forward section of the nose cone having an ogive is mounted at an angle to the longitudinal axis of the projectile, forming an axial offset of an axis of the forward section with respect to the longitudinal axis of the projectile. Another section of the nose cone includes another motor, the Roll Generator Motor, that is rotationally decoupled from the forward section and rotates the deflected forward section so that its axis may be pointed in any direction within its range of motion. Accordingly, deflection and direction of the forward section may be modulated by combined action of the motors during flight of the projectile.

The invention relates to a generalized-morphology-based automatic filling system fault diagnosis method. The method includes that aiming at high-speed motion of each mechanism when an automatic filling system works, measuring points are arranged at each angle motion component position, a driving motor and a power source portion to measure vibration acceleration, angle motion parameters and load current response signal for data analysis and fault classification recognition; experiment testing, signal processing, feature extracting and fault diagnosis are integrated, and automatic diagnosis, alarming and predicting can be realized. Aiming at different fault types of the automatic filling system, a generalized-morphology-based early fault diagnosis method is developed, convenience and quickness in fault diagnosis and prediction of the automatic filling system are realized, the problem that a medium-large-caliber artillery automatic filling system is backward in maintenance means and needs to be demounted greatly for inspection is solved, and the fault diagnosis method is high in intelligence level, low in maintenance cost, short in period, less prone to misdiagnosis and missed diagnosis and adaptable to needs of equipment and weapon development.

The system provides predictive error-checking and conflict resolution by comparing data contained in cognitive artifacts such as orders / instructions and reports against one another and against existing domain-specific databases, procedural and conceptual models, reasoning schemes, (in military domain specific applications, that would be terrain, weather, equipment, artillery, logistics, rules of engagement, field manuals, military doctrine, models of war games, etc) to determine their validity and effectiveness. Possible situations, states, or conditions arising from inferred actors' intent are recognized through expert systems analysis and trigger information exchanges. The system further advance Intention Awareness by enabling users to view information corresponding to the applicable environment obtained from external application systems across interoperability bridge. Through its graphical user interface the system allow users to graphically visualize and communicate their intent. The system also provides the management of information exchanges, where decisions to exchange a specific item of information are based on a set of metrics within a particular application-specific domain knowledge (such as importance, scope, time window of relevance as well as doctrine and rules of engagement in a military domain knowledge. Such metrics are evaluated while making information exchange decisions.

A full-insurance rain bomb fuze relates to an artificial hail-suppressing rain bomb fuze for antiaircraft guns. The present invention mainly includes a fuze body, an upper drug tray, a lower drug tray, a rotary body, a bracket, a pressure screw, and a detonator tube. There is a 134-136° circular groove on the bottom surface of the medicine tray and the top surface of the medicine tray respectively. The gunpowder column is installed on the side, and the gyratory body is installed in the medicine feeding tray. The left and right sides of the medicine feeding tray and the gyratory body are respectively equipped with centrifugal safety screw plugs, centrifugal springs, centrifugal pins and safety pins, and gunpowder safety screw plugs. The dimensions of the booster tube have also been improved. The invention has the advantages of small fragments, sufficient explosion, safe use, good delay reliability and more complete detonation.

The invention discloses a high-speed target tracking control method applied to a photoelectric tracker, and belongs to the technical field of servo control. Relevant parameters outputted from the photoelectric tracker, artillery, a carrier inertial navigation system, a video tracker and a laser range finder are utilized, calculation of tracking feedforward compensating parameters of an orientation speed ring and a pitching speed ring below an aiming line coordinate system is completed through a series of coordinate transformation, recursive iteration and coordinate inverse transformation, and the parameters are respectively superimposed to an orientation and pitching tracking control loop to participate in tracking control. By the adoption of the photoelectric tracker, the high-speed target tracking control method has the advantages of being high in response speed, little in dynamic lag, high in tracking precision and good in tracking stability when the method is used for tracking an incoming high-speed moving target, is suitable for tracking high-speed moving targets such as incoming guided missiles and aircrafts by vehicle-mounted and ship-based photoelectric tracking systems, and has great significance in improvement of target resolving precision of fire control systems and operational effectiveness of the whole weapon system.

The invention automatic fire artillery and its control method, is composed by the artillery body and the control system, its characteristic is the system is composed by the water supply installment, the flame picture locator, the decoding as well as the computer; The computer control artillery body movement, accepts the fire alarm through the hypothesis procedure, gains the artillery body position and the flame picture information through the angle potentiometer and the flame picture locator, promptly adjusts the artillery body position and the nozzle angle, after aims the artillery body nozzle at the flame surface vanguard, automatically turns on the water pump and the motorized valve,sprays water to the fire point,fights the fire, until the flame extinguishes, this road alarm has already eliminated.The invention automatic fire artillery can linkage with the fire prevention alarm system,the computer automatic control fire prevention artillery to carry on the flame recognition in spatial scope of the hypothesis monitoring, the flame space localization and automatically open the valve spraying of water, suppresses the flame, specially suits to the big space and nobody value defends the situation the fire safe monitoring and save goal, may raise the automated level of the early fire saves goal.

A fuze setting circuit in an artillery or tank shell having a case with a press-fitted head assembly is provided with an electromechanical fuze-wiring link that is completed electrically by mechanical assembly of a tracer-carrying projectile on the shell casing, and by the rotational attachment of a programmable fuze onto the projectile.

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.

The invention discloses a method for diagnosing a fault of an automatic ammunition supply and transportation device, and aims to realize low maintenance cost and short period. The method comprises the following steps of: arranging measurement points on the large-aperture artillery automatic ammunition supply and transportation device, and selecting driving current of an ammunition supply motor and a hydraulic oil source motor as the measurement points according to a driving mode supplied by an automatic ammunition supply and transportation motion cyclic graph; simultaneously acquiring and recording angular displacement signals and angular speed signals of a rotary ammunition cabin, a coordination arm, a turning mechanism and an ammunition transportation mechanism as well as load current change signals of driving motors by a portable signal acquirer; performing signal data correction work of baseline drift correction and wild point removal on the acquired and recorded angular motion signals and current change signals; performing time domain analysis on an acquired acceleration impact signal and an acquired current impact signal, and making an amplitude probability density and probability distribution curve; and performing short-time-frequency characteristic extraction and small sample signal analysis on an impact response signal, analyzing a wavelet energy spectrum, and supplying peak values and frequencies in a frequency domain, and energy and entropy of each frequency band.

A muzzle brake has a rear end, a front end and a central axis. The muzzle brake includes a plurality of axially spaced turning vanes; each turning vane having an inside diameter that is substantially equal to or greater than an inside diameter of a rearmost turning vane, at least one turning vane having an inside diameter that is greater than the inside diameter of the rearmost turning vane; and each turning vane having a thickness that is substantially equal to or greater than a thickness of the rearmost turning vane.

A modular reconnaissance capsule or reconnaissance pod is provided that is suitable for deployment by means of an artillery launching platform, such as a conventional 40 mm grenade launcher or 155 mm cannon wherein a parachute is deployed at a pre-calculated observation altitude, the parachute being designed to yield a sufficiently slow rate of descent to permit live video capture and transmission of images as forward observation information. Alternatively, pods according to the invention may also be air dropped from an aircraft, either piloted or pilotless, thus allowing the aircraft to operate at a safe distance and yet provide close reconnaissance even under a cloud cover. Accurate information about targeting dynamics is made available to the user through commercially available products. The invention complements other reconnaissance methods and provides easy-to-use real-time visual information for a desired area of interest.

A Reconfigurable Nose Control System (RNCS) is designed to adjust the flight path of spin-stabilized artillery projectiles. The RNCS uses the surface of a projectile nose cone as a trim tab. The nose cone may be despun by the action of aerodynamic surfaces, to zero spin relative to earth fixed coordinates using local air flow, and deflected by a simple rotary motion of a Divert Motor about the longitudinal axis of the projectile. A forward section of the nose cone having an ogive is mounted at an angle to the longitudinal axis of the projectile, forming an axial offset of an axis of the forward section with respect to the longitudinal axis of the projectile. Another section of the nose cone includes another motor, the Roll Generator Motor, that is rotationally decoupled from the forward section and rotates the deflected forward section so that its axis may be pointed in any direction within its range of motion. Accordingly, deflection and direction of the forward section may be modulated by combined action of the motors during flight of the projectile.

A Kinetic Energy penetrator round is shown effective in neutralizing incoming air borne threat munitions such as rockets, artillery, or mortars for instance, without posing a threat in urban environments to harm bystanders on the ground. There are also no hazards or expense with this round of cleaning up unexploded ordnance, which might have occurred with other types of rounds due to unreliability of self destruct mechanisms. Shown herein is a kinetic energy penetrator for air defense that merely self destructs beyond its operational range into fragments that are not lethal to personnel on ground; no pyrotechnic or energetic materials means are used to activate this self destruct process. A full bore projectile structure is shown that is composed of plural axi-symmetric circular disks stacked on each other and tied by a shape memory metal wire of Nitinol. While operational as a joined group, the disks are a formidable round to kill an incoming air target. After the self destruct phase however, each disk is separated from adjacent disks on either side by a spring mechanism that enables separation after the process is initiated in flight when the Nitinol wire deforms due to heating from air drag. Each disk then proceeds alone with low enough terminal kinetic energy on the ground to be less than lethal.

The disclosed system, device and method for providing a multi-mode munition generally includes a modular projectile assembly having an aft module suitably configured for mechanical and electrical engagement with a forward module. The aft module generally provides a common assembly for engagement with a variety of forward modules as well as engagement with cartridge casings of various calibers. Disclosed features and specifications may be suitably controlled, adapted or otherwise optionally modified to improve optimization of artillery projectiles for a specific role. Exemplary embodiments of the present invention generally provide munition cartridges that may be augmented in the field with the utilization of specialized forward modules.