67 results about "Ballistics" patented technology

A polymeric cartridge subassembly for use in medium caliber weaponry, comprising a metallic base having a rearward surface, an open forward surface, and a coupling element therebetween. A polymeric casing is mated with the base coupling element via a coupling end, and includes a forward end opening, an opposite end, and a middle body portion therebetween. The forward end opening is adapted to receive a projectile, and the coupling end has an outer diameter less than that of the middle body portion to facilitate mating with the base coupling element. The polymeric casing is formed from a graphene-reinforced polymer matrix composite which is light-weight; producing necessary ballistics for medium caliber ammunition without deformation of the polymeric casing after firing.

The invention discloses a guided rocket inner ballistic proportioning parameter design method for reducing peak heat flow, which puts forward design requirements on guided rocket engine inner ballistic parameters from the perspective of overall design, introduces inner ballistic curve proportioning parameters, and realizes reduction of outer ballistic peak heat flow by optimizing the proportioning parameters. The matching parameters are iterated through a double-loop optimization framework, the outer loop aims at reducing peak heat flow, the inner loop is rapidly evaluated through a ballistic optimization method, and the optimal matching parameters of the inner ballistic of the guided rocket engine are rapidly obtained. According to the method, integrated design of the inner trajectory and the outer trajectory of the guided rocket is achieved, the design dimension of the guided rocket is increased, a new scheme optimization approach is provided for overall designers, and the adaptation degree of an overall scheme and an engine scheme is improved.

The invention provides a liquid-gas phase change ejection inner trajectory modeling method, a liquid-gas phase change ejection simulation method and electronic equipment. A liquid-gas phase change ejection system comprises at least one phase change power unit. The liquid-gas phase change ejection inner trajectory modeling method comprises the step of dividing a liquid-gas phase change ejection inner trajectory into a phase change power unit flow model, a primary chamber energy model and a projectile body motion parameter model. According to the method, the liquid-gas phase change ejection inner ballistic model comprising the multiple phase change power units is constructed, the acting time of the phase change device is prolonged, the preset speed can be achieved when the ejection overload control requirement is high and the overload does not exceed the limit value, and the inner ballistic parameter change process in the carbon dioxide phase change ejection expansion acting process can be accurately calculated.

A bullet tracking system comprising a sensor sub-system that generates bullet tracking data by tracking a position and range of a bullet discharged from a remote-controlled weapon and traveling to an intended target; a processor that processes the bullet tracking data to determine aim adjustments of the weapon for subsequent firing of bullets to compensate for tracked bullet ballistics to improve an accuracy of the bullets for reaching the intended target; and a control sub-system to make the aim adjustments of the weapon.

The invention discloses an energetic propellant based on magnesium-nickel-based metal hydride blending as well as a preparation method and application of the energetic propellant. The preparation method comprises the following steps: step 1, taking metal Mg and Ni elementary substances as raw materials, and preparing magnesium-nickel-based metal alloy powder by adopting a mechanical alloying method; s2, the magnesium-nickel-based metal alloy powder is subjected to hydrotreating, and magnesium-nickel-based metal hydride is obtained; and S3, the magnesium-nickel-based metal hydride is coated with graphene, mechanical ball milling is conducted, the magnesium-nickel-based metal hydride and a monoaromatic propellant are mixed, and the energetic propellant based on magnesium-nickel-based metal hydride mixing is obtained. The characteristic that metal hydride can release hydrogen in a high-temperature environment is utilized, and the release rate of hydrogen energy is regulated and controlled through the size and the proportion, so that the combustion characteristic of propellant powder and the chamber pressure of an inner trajectory during artillery launching are changed, and finally the kinetic energy of a gun muzzle is improved.

This invention discloses a safe fragmentation grenade with a quasi-spherical integrated detonation and warhead structure, consisting of a fragmentation warhead and a safe delayed-detonation fuse arranged along the warhead's axis. The fragmentation warhead includes a lower body, an upper body, a lower explosive ring, and an upper explosive ring. The safe delayed-detonation fuse is a delayed-detonation fuse with spatial explosion-proof, redundant safety, and explosive handling characteristics, including a detonator base, a flame detonator, a support tube, an impact delay cap, a firing pin, a firing spring, a detonating charge, a sleeve, a pull pin, a pull ring, a safety ball, and a nut. The upper and lower bodies are also the main structural components of the fuse. The integrated detonation and warhead structure is not a simple stacked structure, resulting in a small size and light weight. The nut encloses the pull pin and pull ring, replacing the traditional grip, resulting in a smooth surface and good safety during service and tactical maneuvers. With an outer contour close to a sphere and a center of mass located at the center, its air resistance characteristics are independent of flight attitude, ensuring a stable trajectory, controllable impact point, and long throwing distance.

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.

The invention relates to a system and a method for measuring ballistic trajectories in a light-gas gun and an artillery, and the system comprises a first microwave source assembly, a first power amplifier, a first circulator, a horn antenna, a second microwave source assembly, a second power amplifier, a second circulator, a linear polarization antenna and a microwave reflection and transmission plate, the directions of microwaves emitted by the horn antenna and the linearly polarized antenna form an angle of 90 degrees, the microwave reflection and transmission plate is arranged on an angular bisector of the angle formed by the horn antenna and the linearly polarized antenna, and the microwave reflection and transmission plate enables short-wavelength microwaves emitted by the horn antenna to be directly transmitted to a target to be measured. And long-wavelength microwaves emitted by the linear polarization antenna can be reflected to a to-be-measured target according to an angle of 45 degrees. According to the system for measuring the ballistic trajectory in the light-gas gun and the artillery, long-wave microwaves are reflected on the front surface of forward gas, short waves are reflected on the surface of a projectile, and therefore long-distance, continuous and simultaneous measurement of the speed of the forward gas and the speed of the projectile is achieved.

This invention relates to the field of unmanned aerial vehicle (UAV) automatic control technology, specifically to an UAV automatic window-breaking fire extinguishing system and method. The system uses an airborne lidar and image sensor to accurately measure the distance to the building wall and the target position, while simultaneously using a wind speed sensor to collect wind field data in real time. The control system is based on a ballistic model to comprehensively calculate the launch elevation angle, wind speed compensation, and recoil effects, dynamically adjusts the launch parameters of the fire extinguishing projectile, and uses a buffer mechanism to offset the launch impact, ensuring flight stability.

The invention discloses a variable thrust engine energy / trajectory integrated planning method. The method comprises the steps that a variable thrust engine power and trajectory coupling longitudinal plane model and a variable thrust engine energy trajectory constraint optimization model are established; establishing a variable thrust engine energy trajectory integrated constraint optimization model; parameterized discretization is carried out based on a Gaussian pseudo-spectral method, and the variable thrust engine energy trajectory integrated constrained optimization model is converted into a nonlinear variable thrust engine energy trajectory integrated direct optimization model; and solving a corresponding relation among the energy trajectory integrated direct optimization model of the variable thrust engine, the mass second consumption of the variable thrust engine and the throat bolt displacement based on a sequential quadratic programming method so as to obtain a change curve of a throat bolt displacement instruction. The method is applied to the field of optimization design of the variable thrust engine, the problems of energy trajectory coupling characteristics and thrust constraint conditions are considered, and planning of the variable thrust engine is more practical.

The utility model relates to calibration equipment, an electronic gun calibrator and a sighting telescope for calibrating firearms, the electronic gun calibrator comprises a support, the support is provided with a sighting telescope installation position at the front part and an electronic eyepiece installation position at the rear part, and the tail end of the support is provided with a gun barrel assembly structure; the sighting telescope is mounted at a sighting telescope mounting position on the bracket; the electronic eyepiece is installed at an electronic eyepiece installation position on the support, and the electronic eyepiece can obtain the visual field of the sighting telescope and present the visual field on the image display device; when the support is installed on the gun barrel of the firearm through the gun barrel assembling structure, the aim point of the sighting telescope and the gun barrel are located on the same straight line. According to the electronic rifle calibrator, on the basis of the shooting principle of the rifle, the relation between the front sight and the aperture of the automatic rifle and the accuracy of the sighting telescope are adjusted according to the relation between the trajectory and the sighting base line, and therefore the aim that the sighting point coincides with the shooting impact point is achieved.

The invention relates to a soil-biodegradable injection-mouldable thermoplastic composition, suitable for use in ammunition, especially in wads and other components of cartridges for shooting sports and hunting. The composition comprises one or more biodegradable polyesters, preferably polybutylene adipate terephthalate (PBAT) and / or polybutylene terephthalate with sebacic acid (PBTSeb), with high fluidity, and in a proportion of ≥51%, and may be complemented with plasticised starch. This composition achieves above 90% biodegradation in soil in much less than two years, together with high impact resistance, lower moisture absorption (with the associated advantages of greater dimensional stability, lower production costs and better and safer ballistics), compatibility with existing injection and production processes, and lower production costs owing to its greater fluidity.

The invention relates to an apparatus for providing a ballistic solution. In one embodiment, the present disclosure relates to a device for storing more than one ballistic calculator for providing a ballistic solution. In one embodiment, the device communicates with one or more laser rangefinders.

The present invention discloses a method and system for filtering the flight parameters of a rotating missile based on prior knowledge of trajectory, which selects the system state equation with the rotating missile attitude quaternion q as the filter state variable and solves the system quaternion q by magnetic measurement. MR The system observation equation as the filter observation variable is solved by the missile body attitude quaternion matrix #imgabs0# to solve the magnetic measurement system quaternion q MR ; Then construct the missile attitude filtering model, use the Kalman filter algorithm to complete the optimal filtering estimation of the state equation X(k) #imgabs1#, calculate the optimal estimation of the rotating missile attitude quaternion #imgabs2# and substitute it into the missile attitude quaternion matrix #imgabs3#, calculate the optimal missile attitude quaternion matrix #imgabs4# and calculate the missile velocity V n and the missile flight position P n , completing the real-time parameter measurement of the rotating missile flight, thereby effectively improving the accuracy and reliability of testing the rotating missile status.

A ballistic detection system includes a projectile detector; electromagnetic radiation detection equipment; and a ballistics analysis computer configured to obtain image data captured by first and second cameras in accordance with timing specified by the projectile detector, determine points in three-dimensional space, which correspond to image artifacts of a projectile, using intrinsic and extrinsic parameters of the first and second cameras, define a trajectory of the projectile within a target volume using the points in three-dimensional space, and optionally find a point of intersection of the trajectory of the projectile with an object associated with the target volume.

The invention discloses a rainfall enhancement and hail suppression rocket projectile trajectory prediction method and system fused with a three-dimensional meteorological field, and belongs to the technical field of artificial influence weather, and the method comprises the following steps: constructing the three-dimensional meteorological field; carrying out thrust-temperature self-adaptive modeling; carrying out six-degree-of-freedom dynamics modeling; carrying out ballistic numerical integral solving; and outputting and applying a result. According to the invention, continuous interpolation is carried out on meteorological data to construct a three-dimensional meteorological field, an engine thrust-temperature adaptive model is established, a six-degree-of-freedom kinetic equation is constructed according to an out-of-rocket ballistic theory, and a numerical integration method is combined to realize whole-process trajectory simulation of a rocket projectile from launching to landing. Therefore, the precision and reliability of trajectory prediction are effectively improved, and a scientific basis is provided for safety control and effect evaluation of artificial influence weather operation.

A polymeric cartridge subassembly for use in medium caliber weaponry, comprising a metallic base having a rearward surface, an open forward surface, and a coupling element therebetween. A polymeric casing is mated with the base coupling element via a coupling end, and includes a forward end opening, an opposite end, and a middle body portion therebetween. The forward end opening is adapted to receive a projectile, and the coupling end has an outer diameter less than that of the middle body portion to facilitate mating with the base coupling element. The polymeric casing is formed from a graphene-reinforced polymer matrix composite which is light-weight; producing necessary ballistics for medium caliber ammunition without deformation of the polymeric casing after firing.

The present invention provides a method and system for calculating the body gain of a rotating missile, comprising: step 1: obtaining a boundary characteristic trajectory according to a predicted hit point and a body gain coefficient on a combat airspace boundary; step 2: performing trajectory calculation on all boundary characteristic trajectories to obtain a two-dimensional interpolation table of body gain; step 3: obtaining the body gain coefficient according to the two-dimensional interpolation table of body gain and an interpolation method. Compared with the prior art, the present invention adopts a variable launch angle, calculates the body gain coefficient by two-dimensional interpolation according to the rudder deflection angle and the flight time, provides a new method and new idea for calculating the body gain of a rotating missile, and can more accurately reflect the missile body gain coefficient.

The present invention discloses a casing window opening tool and a window opening method, comprising: a perforation structure, including a gun body and a bullet, wherein an explosive chamber and a trajectory are arranged in the gun body, and the bullet is installed in the trajectory and located in front of the explosive chamber; a hole expansion structure, which is installed at the front end of the gun body; wherein the bullet can utilize the explosive impact force of the explosive in the explosive chamber to shoot out along the trajectory and penetrate the casing to form a perforation, and the hole expansion structure can expand the perforation into a window under the guidance of the bullet. The present invention utilizes the explosive impact energy of the explosive to shoot the bullet out and penetrate the casing of the old well to form a perforation, which can realize rapid perforation positioning outside the casing, and then the hole expansion structure can expand the perforation into a window under the guidance of the bullet, thereby solving the technical problem that the hole expansion structure is affected by the arc outer surface of the casing and the difference in hardness between the casing and the formation, causing it to deviate from the casing and cause the window opening failure, and only one drilling trip is required to complete the window opening operation outside the casing of the old well, with high operation efficiency, simple operation and strong adaptability.

A protective suit to protect a wearer from ballistics and explosives. The protective suit comprises a base garment, an armor plate, and a plurality of shocks coupled to an interior surface of the base garment opposite to the armor plate.

This disclosure is directed to an improved ballistic concrete mixture which is operable to be cast in many forms such as blocks. The improved ballistic concrete mixture provides an effective barrier for stopping projectiles with a kinetic energy of between about 1.0 kJ (750 foot-pounds) and 20.3 kJ (15,000 foot-pounds) in between about 3 inches and 10 inches such as a fifty-caliber round. The improved ballistic concrete mixture is useful in the erecting of new structures which need ballistics protection or for retrofitting existing structures with ballistics protection.

Provided herein are systems and methods that support preferred outcomes of tactical encounters. More particularly, the invention relates to artificial intelligence and machine learning systems and methods to select preferred ballistics solutions and tactical courses of action.

An apparatus, system, computer-readable medium, and / or process to measure, sense, or otherwise determine temperature of a gun barrel (e.g., temperature profile) and use that information to generate instructions to adjust aim of the gun before, during, or after (e.g., next shot) shooting the gun. For example, a gun includes several (e.g., 4, 5) temperature sensors within its barrel that measure the temperature profile of a gun barrel after it is shot (e.g., each time it is shot or after several shots); and these sensors provide their measurements to a processing unit (e.g., CPU, GPU) and the processing unit uses these temperature measurements to generate a temperature profile. In at least one embodiment, the temperature profile may then be used to generate one or more predictions and / or instructions for a user.

The invention discloses a low-overload simulation test bomb, and belongs to the technical field of ammunition engineering and weapon launching. The test bomb comprises a wind cap, a counterweight body, a bomb shell, an engine assembly, a rocket engine and an empennage assembly. The wind cap is fixedly connected to the front end of the projectile shell through a wind cap seat, the wind cap is internally provided with a mounting space for the counterweight bodies, and the mounting number of the counterweight bodies is adjusted as required; the fuse mounting mechanism is fixedly mounted in the projectile shell, the engine assembly is mounted at the rear end of the projectile shell through the connector, the rocket engine is mounted in the engine assembly, and the empennage assembly is fixedly connected to the engine assembly; the simulation test bomb is launched through a launching tube, and launching and flying power is provided by a rocket engine. According to the invention, the low-overload running state of a missile can be simulated, regulation and control of main test parameters such as overload, flight time and flight distance can be realized, and the device can be widely applied to safety release of a safety mechanism and related research of guided ammunition ballistic science under the low-overload condition.

The invention discloses an ejection inner trajectory adjusting method based on a solid cooling agent, in the method, a cooling device loaded with the solid cooling agent is introduced, and the fuel gas temperature is reduced through the cooling device, so that an ejection inner trajectory system can adapt to the low-overload and high-initial-speed requirements of an inner trajectory under the condition of small initial capacity.

The present application relates to a trajectory generation method for mid-course maneuvering penetration. The method includes: defining a landing point coordinate system, a velocity coordinate system, and a missile body coordinate system; constructing a dynamic equation expression of a ballistic missile in the landing point coordinate system; the dynamic equation expression includes a thrust vector and an aerodynamic force vector to be solved; calculating the thrust vector according to the thrust magnitude, the coordinate transformation matrix from the velocity coordinate system to the landing point coordinate system, and the coordinate transformation matrix from the missile body coordinate system to the velocity coordinate system; solving the control quantity in the thrust vector by making the direction of the trajectory change velocity increment of the maneuvering penetration perpendicular to the expected interception direction of the interceptor missile and making the landing point deviation after the maneuvering trajectory change as small as possible to obtain the maneuvering trajectory change velocity increment; using the direction of the maneuvering trajectory change velocity increment to calculate the thrust in the trajectory generation, and then calculating the dynamic equation of the ballistic missile to realize the trajectory generation. The present method can realize the mid-course maneuvering penetration trajectory generation.

The invention belongs to the technical field of military exercise training, and particularly relates to a decision system for calculating a digital ammunition damage effect, and the system comprises a three-dimensional scene restoration module which is used for setting a digital twinborn environment of an actual confrontation exercise environment, and updating changed battlefield elements in real time, including influence elements generated for confrontation exercise; the first communication module is used for data interaction with each client; collision calculation: after an actual trajectory is obtained according to a trajectory algorithm, a hit result is calculated in combination with the figure position, the obstacle and the shielding condition of the digital twin environment battlefield; and performing damage rating, namely performing damage rating according to the hit part in combination with a damage rating rule configured in the system. According to the method, the digital twin environment restored by the three-dimensional scene is adopted, data such as ballistic trajectory, damage conditions and collision information in the confrontation drill can be calculated, and the authenticity and effectiveness in the confrontation drill are enhanced.

An apparatus, system, computer-readable medium, and / or process to measure, sense, or otherwise obtain weight of a projectile and use that information to generate instructions to adjust aim of the projectile. For example, instructions may indicate a desired weight of a projectile for performance.

The invention discloses a high-precision calculation method and system for an outer trajectory of a projectile, and belongs to the technical field of artillery fire control. The method comprises the following steps: firstly, establishing a double-model structure consisting of a mass point differential equation model and a rotation angular velocity attenuation model so as to comprehensively describe mass center movement and rotation around the center of a projectile; and then, a four-order Runge-Kutta algorithm (RKF45) with adaptive step length is adopted to carry out numerical integration solution on the model, and the optimal balance between the calculation precision and the efficiency is realized by estimating a local truncation error in real time and dynamically adjusting the integration step length. According to the method, the defects that a traditional firing table method is low in precision and poor in adaptability and a fixed step size numerical solution method is insufficient in stability are effectively overcome, firing elements with higher precision and higher stability can be provided for a fire control system, and the hit rate and combat effectiveness of artillery are remarkably improved.

Improvements in a ballistic with a multi-part chamber locking assembly is disclosed to allow the casing ejection and reloading sequence to be temporarily slowed down to capture the optimum amount of ignited gun powders expanding gas, prior to the round exiting the barrel. Large slide component(s) of a firearm are replaced with a multi-part chamber locking assembly. This negates the requirement for a round to move laterally after moving vertically. The round only moves vertically thus mitigating the requirement for any forward motion. The multi-part chamber reduces the weight and materials needed to actuate all components of the ejecting and reloading process, so more energy is available to transfer movement of casing ejecting. The round is fired with a hammer or striker through impingement or a firing pin actuated action on a primer to ignite the propellant.