105 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 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.

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.

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.

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 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.

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.

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.

This invention belongs to the technical field of integrated navigation and guidance weapon systems, specifically relating to a timing correction method for semi-physical simulation of satellite / inertial integrated navigation. The method includes: Step 1: Calculating the inertial navigation simulation link time; Step 2: Calculating the satellite simulation link time; Step 3: Calculating the time difference between the two links; Step 4: Aligning the timing of the two links; Step 5: Integrated navigation solution. This method calculates the execution time required for the inertial navigation simulation link and the satellite simulation link, eliminating timing differences during the execution of different links. It solves the drawbacks of traditional satellite / inertial integrated navigation semi-physical simulations, such as timing mismatch between the inertial navigation simulation link and the satellite simulation link, inaccurate navigation and positioning information solution, and low simulation accuracy. The advantages of this invention are that the simulation process is closer to the actual working process of the integrated navigation device, resulting in higher simulation accuracy. This simulation method is simple, effective, and practical, with great potential for widespread application.

The application provides a simulation method and device for simulating intercepting an airplane based on a ground-to-air missile weapon system, which comprises a data acquisition device, a data processing device, a communication integrated combination, a recording display control device and a communication lifting antenna; the communication lifting antenna transmits real airplane information data to the communication integrated combination; the communication integrated combination forwards the data to the data acquisition device for coordinate conversion processing, and the data acquisition device acquires weapon equipment data of the ground-to-air missile weapon system at the same time; the data processing device simulates the weapon equipment data of the ground-to-air missile weapon system and the data after coordinate conversion, and transmits the simulation result to the recording display control device for control and storage. The application trains the ground-to-air missile weapon system and the real airplane together, formulates a more reasonable command scheme, trains the user to use the ground-to-air missile weapon system and trains the pilot to operate the experience of avoiding the air defense missile, and achieves the effect of mutual training.

The uniqueness of the presented invention is a biofidelic, metamaterial structured, integrated with wireless sensors, modular, reusable, and anatomically accurate human surrogate (for both male and female) designed for testing and evaluation of personal protective equipment (PPE), and blast environments. Structured with metamaterials, the surrogate demonstrates a biofidelic response to blast overpressure. Metamaterials tailored for blast applications manipulate properties such as wave speed, acoustic impedance, and frequency response to match human tissues with minimized complexity. Incorporating technology from wearable blast sensors, the Blast Overpressure Body (BOB) provides high-resolution, high sampling rate, and time-synchronized simulated human blast data. Its modular design allows for easy replacement of damaged parts, alternative testing scenarios, and enhanced biofidelity, increasing flexibility and reusability. The BOB is a tool for testing, evaluating, and developing PPE and weapon systems, and for research, surveillance, and mitigation of blast exposure in military, industrial, civilian, and law enforcement contexts.

The invention discloses a millimeter wave large dynamic adaptive time-frequency modeling method based on deep learning. The method comprises the following steps: firstly, actually measuring baseband Doppler signal data by cleaning an external field radar, fitting an in-chamber projectile motion model, and constructing a simulation echo signal model superposed with noise; secondly, performing down-conversion processing on the echo signal, filtering noise by using an adaptive filter, and extracting a pure baseband Doppler signal; converting the signal into a projectile speed curve, and extracting input / output features to construct a data set containing a training set and a test set; and finally, through deep neural network training and testing, establishing an in-gun ballistic performance prediction model. According to the method, the analysis efficiency and prediction precision of the projectile velocity curve in a complex environment are remarkably improved, and reliable technical support is provided for ballistic performance evaluation in a weapon system.

The invention discloses a laser semi-active and long-wave infrared imaging composite simulator, which is suitable for generating a laser semi-active echo simulation signal, a long-wave infrared dynamic target background and other composite optical environments in a weapon system semi-physical simulation test, and is driven by a simulation control system in real time. Simulation of laser echo energy changes and long-wave dynamic targets and scenes under different distances, different time periods and different working conditions in the missile-target approaching process is achieved, and the system is mainly used for being matched with other systems to achieve the functions of laser semi-active and long-wave infrared imaging, composite guidance detector semi-physical simulation tests, anti-interference performance evaluation and the like. The simulator is mainly composed of a laser target simulation channel, a long-wave infrared scene simulation channel, a common-caliber coupler and the like. A laser target is output through the laser target simulation channel, and a long-wave infrared image is output through the long-wave infrared simulator and finally enters the detector after passing through the coupling device.

A high energy laser (HEL) weapon system for counter-UAS (C-UAS) use comprises a fully self-contained laser system including a power supply, thermal management, high-capacity batteries, and integrated radar and electronic warfare subsystems.

This invention belongs to the field of command and control technology for key area air defense, and relates to a method for deploying key area defense equipment systems oriented towards multiple air attack directions. The implementation steps of this invention are as follows: Step S101: Determine the relevant concepts and calculation methods of the protective capability of air defense weapons for key areas, and design a system model for air defense weapons defending a specific key area under multiple air attack directions; Step S102: Design an air defense weapon system deployment model. This invention designs an air defense weapon system model that comprehensively considers effective blocking width, cover angle, and effectiveness under multiple air attack directions; determines geographical constraints; designs an air defense weapon deployment model, and solves for the deployment positions of air defense weapons according to deployment principles. The advantages of this invention are: simple and effective implementation, beneficial for providing commanders with pre-battle air defense weapon deployment schemes that meet the needs of modern air defense operations, reducing time and weapon consumption, and improving the effectiveness of the key area defense system.

An automated human-transported weapon system is comprised of a barrel and munitions, sensing logic, selection logic, aim computational logic, trigger activation logic, a positioning subsystem, and firing logic. The barrel and munitions are utilized for propelling a munitions that are aimed towards a targeting area. The sensing logic senses which of from one to up to a plurality of targets are available targets that are within firing range of the weapon system. There are a plurality of the automated human transported weapons, each linked and providing communications with each other. An external drone is also linked to the plurality of the automated human transported weapons; and coupled to the sensing logic in order to assist in sensing. The external drone is an additional linked appliance that can communicate with the human transported weapon. The selection logic selects a selected target from the available targets in the targeting area that are within the firing range. Aim computational logic determines where to aim the barrel of the weapon, such that the munition will hit the selected target upon firing at a firing time. Trigger activation logic initiates firing of the munitions at the firing time, which is followed by a positioning subsystem that adjusts the aim of the munitions through the barrel, such that they can compensate as needed for where the selected target is at the firing time, which is responsive to derived data. Finally, firing logic fires the munitions responsive to the positioning subsystem and the trigger activation logic.

A fixed-wing combat aircraft including an electrical power source, a propulsion system, a low-power non-propulsion assembly including a flight control system, a high-power non-propulsion assembly including an electrical weapon system, and a management unit configured to selectively establish on command multiple operating modes including: a flight mode, in which the management unit distributes the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly, and an attack mode, in which the management unit limits the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly to the power required to allow the aircraft to glide, and reserves a majority of the available electrical power for the high-power non-propulsion assembly.

An automated weapon system is comprised of a human transported weapon comprising a barrel and munitions; sensing means; targeting means; computational logic for determining where to aim the human transported weapon; aim computational logic; firing activation means; and, firing means. The munitions can be aimed towards a targeting area to be propelled through the barrel. The sensing means senses which of up to a plurality of targets are within firing range of the automated weapon system. The targeting means selects a selected target from the targets in the targeting area that are within the firing range, responsive to the sensing. The computational logic determines where to aim the human transported weapon so that the munitions will hit the selected target if fired at a firing time. The aim computational logic adjusts the aim of the munitions through the human transported weapon, to compensate as needed for where the selected target is at the firing time, responsive to the determining where to aim. The firing activation means initiating firing of the munitions at the firing time. The firing means fires the munitions responsive to the adjusting the aim and the initiating firing.

A thermal environment deflection test method for electronic products is used in deflection testing of single units supporting space launch vehicles and missile weapon systems. This method is used to determine product design margins, identify weaknesses, and conduct quantitative deflection testing to improve product reliability. This invention is a reliability enhancement method based on quantitative deflection testing.

A kind of free state body posture and longitudinal axis direction general measuring equipment and method, including first longitudinal axis marker pole and second longitudinal axis marker pole, wherein first longitudinal axis marker pole includes vertically arranged first main branch rod.The positive effect of the present application is that the present application is not affected by the influence of the machine belly shelter, and the universality is strong, and the weapon system calibration of the warplane can be created at any time in the field environment, the longitudinal axis of the machine body is measured in the free state of the machine body, compared with the previous old method, the universality is stronger, and the previous method can be used on a few machine models, and the present method can be used on all machine models.The method of the present application requires less operators, saves manpower compared with the old method, and the body posture determination process can be completed by a single person independently, and through on-site use demonstration, the measurement of the body space posture can be completed by a single person in 2-5 minutes after being skilled.

The embodiment of the invention provides a weapon system. The weapon system comprises a bearing device, a reconnaissance system, a portable weapon station and an integrated control terminal. The reconnaissance system comprises a shell, an optical detection assembly, an acoustic detection assembly and a control assembly, the shell is arranged on the bearing device, the optical detection assembly is arranged on the shell and comprises a plurality of camera devices, the camera devices are sequentially arranged in the circumferential direction of the shell, and the optical detection assembly is used for detecting optical position coordinates of a target object. The optical detection assembly is arranged in the shell, the acoustic detection assembly is arranged in the shell and used for detecting acoustic position coordinates of a target, and the control assembly is arranged in the shell, electrically connected with the optical detection assembly and the acoustic detection assembly and used for determining final coordinates of the target according to the optical position coordinates and the acoustic position coordinates. The portable weapon station is in communication connection with the reconnaissance The integrated control terminal is in communication connection with the reconnaissance system and the portable weapon station.

1. Name of the product in this design: Individual Missile Weapon Equipment (LWS-05B Shoulder-mounted Miniature). 2. Application of this design: This design is intended for use in miniature firearms and weaponry, for individual soldier combat, and for launching missiles from the shoulder. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.