50 results about "Weapon system" patented technology

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.

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.

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 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.

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.

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 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.

This utility model discloses a team-based collaborative combat simulation robot, belonging to the field of robotics technology, including a perception system, a decision-making system, a motion system, a weapon system, and a communication system. The perception system acquires information about the robot's surrounding environment and its own state. The decision-making system formulates execution plans based on the environmental and state information, including action and confrontation decisions. The motion system executes actions based on action decisions. The weapon system performs confrontation tasks based on confrontation decisions. The communication system enables information exchange. This utility model achieves this by: accurately capturing information through the perception system to provide a basis for decision-making; efficiently generating plans through the decision-making system; flexibly executing actions through the motion system; accurately completing confrontation tasks through the weapon system; and ensuring information exchange through the communication system. The coordinated operation of these systems enables the robot to perform tasks effectively in complex scenarios, improving overall combat effectiveness and adaptability.

A suppressor for a multi-barrel weapon system includes an adapter baffle configured to engage the weapon system and receive the muzzles of the barrels, a plurality of extension baffles configured to be aligned with and arranged in a stack on the adapter baffle, and an endcap baffle configured to align with the extension baffles and engage the final extension baffle in the stack. A plurality of projectile apertures in each baffle aligns with the muzzles to define a plurality of parallel bullet paths. Each projectile aperture can be in fluid communication with each other projectile aperture. Each extension baffle can include a plurality of internal vanes configured to circulate propellant gasses emitted from the muzzles of each barrel within an interior space at least partially defined by the extension baffle. The adapter baffle can define an expansion space in which propellant gases emitted from each muzzle comingle during discharge of the weapon system.

The invention provides a warhead capable of switching a fragment mode, a weapon system and a control method thereof, and the warhead capable of switching the fragment mode comprises a shell provided with a first notch groove and a second notch groove, and the depth of the first notch groove is larger than that of the second notch groove; the outer wall of the annular first charge is attached to the inner wall of the shell; the explosion-proof ring is positioned on the inner side of the first charge; the second charge is positioned on the inner side of the explosion-proof ring; wherein the first charge and the second charge are configured to be capable of independently detonating or synchronously detonating, and under the condition that the second charge is independently detonated, the first notch groove is broken, the second notch groove is kept complete, and a first fragment is formed; and under the condition that the first charge and the second charge are synchronously detonated, the first notch groove and the second notch groove are both fractured, and a second fragment with the size smaller than that of the first fragment is formed. According to the warhead, a hardware structure does not need to be replaced, fragment output modes can be dynamically switched at the tail section of flight according to the target type, and the multi-scene combat adaptability is remarkably improved.

The invention discloses an electric steering engine shock resistance control algorithm suitable for a gun shooting environment, and belongs to the technical field of steering engine control. In order to solve the problems of steering engine gear extrusion deformation and control failure caused by transient high overload in the gun shooting process, a multi-source information fusion decision module is introduced on the basis of a double-closed-loop control architecture. The core of the method is that an acceleration characteristic dominant decision is utilized, and the response delay of a sensor is dynamically adjusted by constructing an impact time delay self-adaptive compensation function, so that accurate time sequence prediction of impact moment is realized; and meanwhile, an active micro-motion clamping stagnation detection mechanism based on touch instant return logic is established, the steering engine is driven to perform high-precision micro-amplitude swing within a preset angle range, and mechanical stress is actively recognized and released by monitoring current abnormal feedback. Clamping stagnation and damage of the internal structure of the steering engine under strong impact can be avoided from the source, and the survivability and control precision of a weapon system in an extreme environment are remarkably improved.

The invention discloses a multifunctional controllable launcher base for a gun, belongs to the field of unmanned equipment, and is mainly used for quickly modifying a standard gun into an unmanned or remote control weapon. Comprising a buffer rack fixed on unmanned equipment and used for fixing a safety module and a first-shot filling module and buffering firing and resetting actions of a standard gun; the safety module is used for limiting the position of the trigger to achieve safety and can relieve limiting of the trigger; the electric firing module is connected with the standard firearm and is used for rotating to pull the trigger to move backwards after the safety module is released, and the firing action is completed; and the first filling module is used for pushing the bolt handle to move backwards, the bolt frame is separated from the bolt handle when moving in place, and the bolt frame returns to the initial position when recoiling, so that filling circulation is completed. The unmanned weapon system has the advantages of being compact in structure, light in weight, high in shooting speed, good in safety and the like, and the combat effectiveness and task continuity of the unmanned weapon system are remarkably improved.

The present invention relates to a counter-measuring device for determining adjustment errors of a laser weapon, comprising a reference device configured to detect electromagnetic radiation arriving from a predetermined direction and / or to reflect it back in the opposite direction to the predetermined direction, and / or to emit electromagnetic radiation in the opposite direction to the predetermined direction, a position determination device configured to determine a current position relative to the laser weapon, a communication interface for communicating with a receiving unit via a data link, and a control device that is communicatively connected to the reference device, the position determination device and the communication interface, and which is configured toThe invention relates to reading the current position from the positioning device and sending corresponding measurement data for the current position to the receiving unit via the data link, wherein the measuring device is designed as a flying platform. Furthermore, the invention relates to a laser weapon system and a method for correcting the alignment of a laser weapon.

A weapon system for a firearm includes a processor, the processor having an associated memory, and an optical reader, the optical reader configured to receive operator-identification information and transmit the operator-identification information to the processor.

The invention discloses a CuCr2O4 / PPy composite catalyst for a GATo propellant and a preparation method of the CuCr2O4 / PPy composite catalyst. The CuCr2O4 / PPy composite catalyst is a binary compound of spinel type CuCr2O4 nanoparticles and a polypyrrole three-dimensional network. The preparation method comprises the following two steps: preparing spinel type CuCr2O4 nanoparticles by a hydrothermal method; and reacting the CuCr2O4 / PPy composite catalyst with a pyrrole monomer at 0-3 DEG C by an in-situ polymerization method to obtain the CuCr2O4 / PPy composite catalyst. According to the composite catalyst, the burning speed of the GATo propellant can be synchronously increased by 15%-44%, the electrostatic spark sensitivity negative electrode is increased from 1.78 J to 2.45 J, the friction sensitivity burning explosion probability is reduced from 95% to 30%, the impact sensitivity characteristic drop height is increased from 34.5 cm to 52.5 cm, the burning speed increase and the sensitivity reduction of the GATo propellant can be synchronously achieved, the process conditions are mild, industrialization is easy, and the method is suitable for industrial production. The method is suitable for performance regulation and control of high-energy solid propellants in the fields of space carrying, weapon systems and the like

The application discloses a light unmanned aerial vehicle weapon equipment, which comprises an unmanned aerial vehicle and a weapon station, wherein the unmanned aerial vehicle is provided with a square cavity-shaped suspension rack used for suspending the weapon station. The rotor yoke frame of the unmanned aerial vehicle adopts a square frame structure, and the arm adopts a cable-stayed mode, so that the height of the unmanned aerial vehicle is reduced, and the stability of the unmanned aerial vehicle during flight is enhanced. In addition, the arm, the rotor yoke frame and the upper shell are connected into an integrated structure through welding, so that the safety performance of the unmanned aerial vehicle is improved, and the unmanned aerial vehicle is simple to install, disassemble and maintain and high in efficiency. The weapon station changes the arrangement mode of the power mechanism and the photoelectric module of the driven launching cabin, and the power mechanism and the photoelectric module of the launching cabin are changed from the previous longitudinal arrangement mode into a transverse arrangement mode, so that the height of the weapon station is reduced, the stability of the weapon station during flight is improved, and the weapon station is provided with a power mechanism used for driving the rotation of the suspension rack, so that the whole weapon station can rotate in the horizontal direction, and the flexibility of the weapon station is improved.

The invention relates to the technical field of calibration airborne equipment and target plate position positioning, and discloses a laser target plate calibration straightening collimator, which comprises a protection cover and a fixing plate on the right side of the protection cover, and is characterized in that a laser calibration instrument is arranged in the protection cover; the laser calibration instrument comprises a laser main body, a vertical laser transmitter, a first transverse level, a longitudinal level, a horizontal laser transmitter and a switch button, the laser main body is movably mounted at the inner top of the protective cover, and the vertical laser transmitter is fixedly mounted in the middle of the top of the laser main body. Visual collimated laser is utilized through the laser calibration instrument and the laser straightening instrument, the influence of the meteorological environment can be avoided, and all-weather target plate measurement and calibration are implemented for a boresight system of an aircraft; the stability and the accuracy of a fire control weapon mounting system test and measurement target plate of an aircraft can be improved, and errors and uncertainty caused by wind resistance to a steel wire suspension wire plumb and a steel wire horizontal line are effectively solved.