615 results about "Artillery" patented technology

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.

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.

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.

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.

Disclosed is a Powered Wing Aircraft. A generalized stabilizer/directional vent is used for providing a standard range of aeronautical control. It controls cross winds, directional velocity, directional control, and torque balancing in one simple easy to control device. It is attached to the axles. These improvements can apply to both military and civilian applications.

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 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.