148 results about "Weapon system" patented technology

Unmanned systems, and primarily vehicles, and in most embodiments unmanned aerial systems (UAS), as well as novel guided and unguided munitions are presented herein. to the two combine to present unmanned weaponized systems that not only carry weapons functionality, but allow for advanced observation and reconnaissance. These unmanned systems are largely directed toward military applications where the weaponized unmanned system may be forward deployed to allow human warfighters to remain at long range distances from the potential targets, and to provide surveillance, target identification and tracking, general reconnaissance information, and the like, while also providing weaponized attack capabilities. The unmanned systems may, in some embodiments, include advanced command and control capabilities for communication between the system and the remote, rear-positioned warfighter, and between separate elements of the unmanned system. Many embodiments also include weapons systems, munitions, or rounds with guidance and real-time maneuverability capabilities as well.

The method and apparatus for a remote weapon station or incorporated into manually-aimed weapons. The methodology requires use of a muzzle velocity sensor that refines the aiming of the second and subsequent fires or volleys fired from weapon systems. When firing the first volley a weapon uses an estimated velocity and, at firing, the muzzle velocity of a projectile is measured. When firing the second volley a weapon's fire control calculates an aiming point using the measured velocity of the first volley.

A riser mount system includes a housing having a lower surface configured to engage a weapon accessory interface and an upper surface opposite the lower surface configured to engage a fire control system. A peripheral wall extends between the lower surface and the upper surface, wherein the housing defines an interior compartment. A forward-facing camera assembly is disposed within the interior compartment and is operatively coupled to a riser circuit assembly also disposed within the interior compartment. The interior compartment is configured to receive one or more batteries for electrical coupling to the riser circuit assembly.

A riser mount system includes a housing having a lower surface configured to engage a weapon accessory interface and an upper surface opposite the lower surface configured to engage a fire control system. A peripheral wall extending between the lower surface and the upper surface, wherein the housing defines an interior compartment. A riser circuit assembly disposed with the interior compartment, which is configured to receive one or more batteries for electrical coupling to the riser circuit assembly. A first electrical connector is disposed on the first surface and is structured and operable to electrically couple the one or more batteries to a fire control system. A second electrical connector disposed on the second surface and is structured and operable to electrically couple the one or more batteries to one or more devices on the weapon accessory interface.

Systems, devices, and methods are disclosed to correct aimpoint of a system of a weapon and affixed digital weapon sight. The method employs the components of a digital weapon sight configured together for a process of sensing of a ballistic event, storing of digital imagery data before and after a shot or series of shots, and then the performing of an image registration algorithm, via a cross-correlation type function. The image registration determines the misalignment between the images as a Cartesian shift, and aimpoint of subsequent shooting is corrected through application of adjusted reticle symbology or adjusted image sensor windowing. Preprocessing methods for enhancing image registration algorithm accuracy are presented.

The invention relates to a bending moment-torque composite loading device for testing the load capacity of a steering engine, and belongs to the technical field of ammunition weapon system testing. In the device, the pressure head, the pressurizing rod and the composite loading slip ring synchronously rotate along with the rotation of the rudder wing, so that the applied pressure can be ensured to be always perpendicular to the rudder surface and is closer to the real wind resistance working condition during flight. The bending moment output device and the torque output device are coupled together through the composite loading slip ring, so that the bending moment and the torque can be loaded at the same time and are closer to the actual flight condition.

A weapon system has an optical sight mounted to a weapon and a frame with a sight window that is configured to superimpose a reticle that is visible through the sight window in a first focal plane. An optoelectronic device is mounted to the weapon and includes an imager with a sensor array and a display device. An image processor is configured to receive image data captured by the sensor array and process the image data to generate a subset image that is received from a select region of the sensor array. The select region of the sensor array defines a second focal plane. A controller is configured to receive an input from an operator, and in response to the input, to select the select region of the sensor array for aligning the second focal plane with the first focal plane.

The invention refers to a counter countermeasures device, for use in an anti-aircraft combat. In one embodiment the CCM device together with an anti-aircraft weapon system forms an air defense system. The counter countermeasures device is configured for generating and emitting electromagnetic radiation of appropriate wavelengths and is capable of operating in spoof and jam mode and switching between both modes. The mode of operation is dependent on the selection of the output power of the EM source unit and the distance to the target. The selection of the output power may be done with a mechanical cover or with an electronic solution, decreasing driving current of the EM sources. With the CCM device the anti-aircraft missile launch warning and detection system installed on aircrafts are deceived and the countermeasures are released. With the use of the CCM device the efficiency of the anti-aircraft combat is highly improved, i.e. the probability of the target hit is highly improved.

A suppressor for a multi-barrel weapon system includes an aft end configured to receive a muzzle of each barrel of the plurality of barrels, a forward end defining a plurality of projectile apertures configured to align with the plurality of barrels when the muzzle of each barrel is received in the aft end, and a sidewall extending from the aft end to the forward end, the sidewall at least partially defining a single continuous interior chamber in which propellant gases emitted from the muzzle of each barrel comingle and circulate. The suppressor can include a plurality of baffles. A plurality of projectile apertures in each baffle can align with the muzzles to define a plurality of parallel bullet paths. Each projectile aperture is in fluid communication with each other projectile aperture.

The invention discloses a low-cost injection type seeker semi-physical simulation test method which is suitable for semi-physical simulation of all weapon systems adopting image guidance. According to the method, a simulation mode of a traditional image guided weapon system based on a five-axis turntable is abandoned, three inner axes of the five-axis turntable are used for simulating guide machine motion, two outer axes of the five-axis turntable are used for simulating target motion, and a ground image is directly injected into a seeker image information processing card. The defects that a traditional weapon system simulation method is not comprehensive in tracking algorithm assessment, and the motion angle of a rotary table is limited are overcome. According to the method, the actual working process of a seeker tracking algorithm and an image seeker can be comprehensively assessed, the whole simulation process does not depend on a high-performance five-axis turntable and an image simulator, the purpose of assessing the working performance of the seeker in a low-cost and multi-dimensional mode is achieved, and the simulation system and method are simple in design, effective, practical and suitable for popularization and application. Good popularization and application space is realized.

Certain aspects of a novel weapon sight system combine a direct view, a visible light video view, and an infrared (IR) video view mode. Each of the view modes may be viewed individually or simultaneously with one or more of the other view modes through a single viewing aperture. Further, the one or more view-modes may be provided while providing a bore-sighted reticle superimposed on the selected view. Further, the reticle may be powered separately from the video view electronics enabling use of the reticle regardless of the power status video view electronics.

The invention discloses an unmanned vehicle-unmanned aerial vehicle cooperative reconnaissance and strike system which comprises an unmanned vehicle system, an unmanned aerial vehicle system, a central control system and a remote command system. The unmanned vehicle system and the unmanned aerial vehicle system directly communicate through the data link communication module; the unmanned vehicle system communicates with the remote command system through a satellite communication module; the unmanned vehicle system performs comprehensive perception and data acquisition on the surrounding environment through the multi-mode sensor assembly; the central control system is configured to integrate information of an unmanned vehicle, an unmanned aerial vehicle and a weapon system. The cooperative control module is used for optimizing task allocation and a cooperative process; the situation awareness module and the target recognition module are used for fusing and analyzing multi-modal sensor data in real time to construct a unified battlefield situation map; and the resource optimization module is used for managing system resources. The advantages of all the systems are exerted, and the overall combat ability is improved.

The invention discloses a heterogeneous spacecraft cluster target allocation method based on a multi-agent reinforcement learning algorithm, and mainly relates to a heterogeneous weapon system model design and a hierarchical hybrid collaborative decision framework design based on multi-agent reinforcement learning. According to the method, the problem of heterogeneous target allocation of the spacecraft cluster in the technical field of spacecraft cooperative control is solved. The spacecraft cluster heterogeneous target allocation method based on multi-agent reinforcement learning comprises the following steps: 1, establishing a heterogeneous weapon target allocation model for a spacecraft cluster heterogeneous target allocation problem; 2, constructing a'global-local-monomer 'hierarchical decision model based on a multi-agent depth deterministic policy gradient (MADDPG) algorithm framework, wherein a global task allocation layer agent adopts centralized training to learn a heterogeneous weapon task allocation and cluster hierarchical strategy; and intelligent agents of the local collaboration layer and the single execution layer adopt distributed training and local observation to carry out collaborative decision making and target distribution. And 3, designing a composite reward function fusing the target value, the intelligent agent capability matching degree and multiple constraints to guide the intelligent agent to maximize the overall task income and generate an optimal allocation strategy on the premise of meeting the complex constraints, thereby effectively improving the heterogeneous target allocation efficiency under the spacecraft large-scale cluster. The method can be applied to the aerospace field and in-orbit autonomous decision-making scenes.

The invention relates to a CAD model generation system and method based on natural language modeling. The CAD model generation system comprises a data layer, an application layer and a middle layer. The application layer is used for acquiring request information of a user; the middle layer is used for analyzing the request information through a natural language processing method to obtain parameters corresponding to the design intention of the user; mapping the corresponding parameters of the user design intention to a predefined structure template, and associating a standard; according to the structure template and the constraint condition, generating an automatic script for constructing a two-dimensional / three-dimensional model through a depth model generation method; based on the automatic script, adopting Siemens NX software to generate a CAD (Computer Aided Design) model; the data layer is used for querying corresponding standard terms in a knowledge base according to the association standard; and based on the standard terms, extracting constraint conditions corresponding to the association standards. The method is suitable for rapid modeling and design verification of complex parts in a weapon system.

The present invention relates to a pointing drive (10) for receiving and aligning a weapon system (102), characterized by a coupling gear (12) for pointing in elevation, wherein the coupling gear (12) has a crank (14), a rocker (16) and a coupler (18), wherein the crank (14) is mounted at one end on a first bearing (22) so as to be pivotable about a first pivot axis (20), wherein the rocker (16) is mounted at one end on a second bearing (26) so as to be pivotable about a second pivot axis (24), wherein the crank (14) and the rocker (16) are each connected in an articulated manner to the coupler (18) at their other end, wherein the first bearing (22) and the second bearing (26) are each connected to a base element (28), wherein the base element (28) defines a reference plane (30), wherein the coupler (18) is mounted at its end facing away from the base element (28) top side has a receiving surface (32) for receiving and fastening the weapon system (102),wherein the crank (14) is pivotable about the first pivot axis (20) by driving a crank drive (36), so that an elevation angle (α) which the receiving surface (32) and the reference plane (30) enclose with each other can be adjusted. A weapon system (100) with such a targeting drive (10) is specified.

Unmanned systems, and primarily vehicles, and in most embodiments unmanned aerial systems (UAS), as well as novel guided and unguided munitions are presented herein. to the two combine to present unmanned weaponized systems that not only carry weapons functionality, but allow for advanced observation and reconnaissance. These unmanned systems are largely directed toward military applications where the weaponized unmanned system may be forward deployed to allow human warfighters to remain at long range distances from the potential targets, and to provide surveillance, target identification and tracking, general reconnaissance information, and the like, while also providing weaponized attack capabilities. The unmanned systems may, in some embodiments, include advanced command and control capabilities for communication between the system and the remote, rear-positioned warfighter, and between separate elements of the unmanned system. Many embodiments also include weapons systems, munitions, or rounds with guidance and real-time maneuverability capabilities as well.

A system for securing two-way communications using a radio frequency wireless network between N weapons systems to be remotely operated, with N≥1, and a control station, includes: a remote-control station accommodating at least one operator, with a first field data bus to which a first controller is connected with at least a first transceiver system as a client; and N conventional weapons systems, each with a second field data bus and at least one client, the system including an additional client provided with a second transceiver system to be connected to each of the N weapons systems, permanently or removably, for operation in remote operation mode, the first controller with the first transceiver thereof receiving data from and / or sending commands to the client via the radio frequency wireless network.

A rifle platform weapon system dry firing device which allows the user to dry fire a rifle platform weapon system and still experience the trigger pull and cycling of the weapon system without breaking the shooter's positioning and sight alignment. The dry firing device includes a bolt carrier group configured to replace the standard bolt carrier group of the rifle platform weapons system. The dry firing device includes a magazine with a reset finger configured to reset a hammer of the weapons system. The dry firing device includes at least one of i) a charging rod engaging with a charging handle of the rifle platform or ii) an integrated laser within the bore of the weapons system.

Disclosed is a simulator and simulation method with increased precision, in particular a weapon system simulator, and weapon system provided with such a simulator. —The simulator (1) comprises a unit for generating a virtual image (I1) which is defined according to an orientation reference and a sighting reference, a unit for generating a so-called captured image from angle-error and telemetry measurements relating to one or more real actors (R1 to R4) each of which is equipped with a retroreflector (10), the angle-error and telemetry measurements being performed using a rangefinder, a comparison unit for comparing the current virtual image (I1) and the captured image so as to determine an error value representative of an orientation and / or sighting error, and a resetting unit for resetting the orientation reference and / or the sighting reference in order to correct said error value so as to create an optimised virtual image which is displayed on the vision element (2) in place of the current virtual image.

A laser weapon system is described. Particularly, embodiments describe subsystems of a laser weapon system including those necessary for laser generation, operational control, optical emission, and heat dissipation configured to provide a lightweight unit of reduced dimensions.

A laser weapon system is described. Particularly, embodiments describe subsystems of a laser weapon system including those necessary for laser generation, operational control, optical emission, and heat dissipation configured to provide a lightweight unit of reduced dimensions.

The invention discloses an air-water cross-medium shell whole-course trajectory firing table compiling method, and belongs to the technical field of outer ballistic cross-medium trajectory correction theories, cross-medium fluid dynamics and artillery firing table compiling. The method comprises numerical simulation of an air trajectory, a water entry trajectory and a water trajectory and a whole-course trajectory shot table fast interpolation algorithm. Wherein the air trajectory is solved based on a six-degree-of-freedom trajectory model; the water entry trajectory and the underwater trajectory are obtained by solving a fluid control equation by adopting a fluid volume (VOF) multiphase flow model, a turbulence model, a cavitation model and a dynamic grid technology; the full-ballistic shot table fast interpolation algorithm is realized based on a least square method and a linear interpolation algorithm. The method is suitable for the cannonball trajectory air-water cross-medium condition, the rapid and accurate calculation problem of firing elements of an artillery fire control system in the air-water cross-medium environment of the firing table is solved, the continuity of the cross-medium full-trajectory firing table is achieved, the blank of the cross-medium firing table is filled up, and the cross-domain combat ability of an artillery weapon system is effectively improved.

Provided is a blank firing adapter for a firearm that prevents a bullet or fragmentation from exiting a firearm barrel and traveling downrange. The device includes a body, a fore end, an aft end, a bore, a transverse exhaust hole, and a flange. The body is positioned within a muzzle end of the firearm barrel. The fore end includes a solid material to prevent bullet fragmentation from directly exiting the barrel in a direction coinciding with a point-of-aim direction when a live round is fired, and the transverse exhaust hole redirects gas traveling through the bore to a direction transverse to the muzzle end of the barrel. The device generates backpressure to permit automatic cycling of a weapon system, safely catches a fired bullet without any fragmentation to travel downrange, and is visually inconspicuous to the casual observer when installed, while allowing for the use of externally attached devices.

The invention relates to the field of searching and tracking integrated radars of a ground-to-air missile weapon system, in particular to an angle measurement method of a searching and tracking integrated radar. The method comprises the following steps of: scheduling a transmitting beam according to search information; carrying out amplitude comparison angle measurement on the received sum and difference beams; and the sum-difference beams have different amplitudes near the beam center. When the target is near the center of the beam, the angle of the target deviating from the center of the beam can be calculated according to the amplitude difference of the sum-difference beam receiving echoes, so that the function of measuring the angle in the beam is realized, and the angle measurement precision is improved.

This invention discloses a method for correcting firing parameters in a closed-loop firing correction system suitable for conditions with very few satellite measurement points. It adds a rotational speed measuring device to the projectile system to measure the real-time rotational speed of the artillery projectile. Based on external ballistics theory, this invention utilizes muzzle rotation speed, ballistic speed, and measurement data (coordinates and velocities) from a limited number of ballistic points to propose a method for estimating the range and lateral deviations of a single projectile relative to the target point. This allows for the rapid determination of the launch angle and directional corrections, enabling artillery firing correction. This invention solves the key problem of how to quickly and accurately determine the firing parameter corrections of a closed-loop firing correction system when there are very few ballistic measurement points, greatly improving the adaptability and reliability of the closed-loop firing correction system under complex battlefield conditions and effectively enhancing the combat capability of the weapon system.

The present invention discloses a comprehensive control method for medium-frequency training of a complex weapon system, namely, when a close-in defense weapon system is in a medium-frequency training working mode, a medium-frequency simulator generates target data and sends it to a fire control device, which receives and processes the target data and sends target indication data to a tracking sensor, and receives target tracking data from the tracking sensor, performs various element calculations and various element extrapolations, performs filtering estimation and predicts gun deviation, corrects the various element extrapolation data in real time, obtains a gun servo position prediction value, and the medium-frequency simulator uses the gun servo position prediction data to perform coordinate transformation on the target data, drives the tracking sensor to complete target tracking, and realizes the medium-frequency training function of the system; the present invention solves the problem that a close-in defense weapon system cannot perform medium-frequency training because the gun servo position information data rate does not meet the requirements.

The present invention belongs to the technical field of tactical weapon system layout and engine structure design, and specifically relates to a solid fuel ramjet rotating detonation combined power system, comprising: an air inlet, an isolation section, a main charge, a pre-detonator tube, and a rotating detonation combustion chamber. To address the current difficulty in organizing mixed combustion in the afterburner, the present invention proposes using a rotating detonation combustion chamber instead of a traditional isobaric combustion chamber, thereby improving the engine cycle thermal efficiency and making the engine structure more compact. Theoretical calculations show that this invention can increase the engine specific impulse by more than 5%. Furthermore, the present invention provides a systematic design solution in conjunction with a solid fuel ramjet rotating detonation combined engine.

A reloading firearm featuring a mechanism to reduce the blowback of toxic propellant gasses towards the warfighter. The reloading assembly acts in plural segments to increase the firing chamber-closed dwell time, while limiting adverse impact to the overall nominal rate of fire. Greater dwell time corresponds with reduced exposure of the warfighter to propellant gasses. Moreover, increasing the dwell time without otherwise altering the firing cycle has the additional effect of delaying the breech opening after the cartridge is fired. This delay in breech opening permits gas pressure at the muzzle, which may be elevated and / or constrained by flash and / or sound suppression, to dissipate before the breech is opened. Accordingly, when the breech opens later in the firing cycle, there is a reduced pressure gradient across the combination of barrel and firing chamber, which reduces a driving force of propellant gasses towards the warfighter via the open breech.

A method for checking clearance to fire for a weapon system (6) of a vehicle (1A, 1B, 1C, 1D), in particular an armoured vehicle, comprising the following steps: a) acquiring (S1) vehicle sensor data (FSD) with the aid of a number NI of vehicle housing sensors (14) of the vehicle (1A, 1B, 1C, 1D), where NI > 1, b) evaluating (S2) the acquired vehicle sensor data (FSD) with the aid of an evaluation device (15), and c) checking (S3) with a checking device (17) that clearance to fire has been given on the basis of the evaluated vehicle sensor data (FSD).

This invention discloses a method for interceptor deployment and deorbiting decision-making in a space-based anti-missile scenario. It includes modeling the time interception window, establishing a model of the time window during the interception process; establishing a model of the space interception window, obtaining a space interception window model for the opposing ballistic missile; and calculating and analyzing the single-orbit distribution density of on-orbit interceptors. This enables the space-based interceptor weapon system to allocate the optimal number of on-orbit interceptors to intercept the opposing missile under different interception requirements. This invention provides a reference for solving the interceptor deployment and corresponding weapon deorbiting decisions in space-based anti-missile systems, enhancing the rationality and accuracy of space-based anti-missile interception systems, and has excellent application prospects in the aerospace field.