48 results about "External ballistics" patented technology

The invention relates to a light-gas gun pneumatic separation sabot, and aims at solving the problems that for an existing sabot, an additional device is needed to conduct separation on the sabot, the effect is not ideal and the cost is increased. The light-gas gun pneumatic separation sabot is composed of an upper supporting disc, a lower supporting disc and a base plate; the upper supporting disc and the lower supporting disc are two corresponding semi-cylinders. An upper half bullet hole is formed in the center of the upper supporting disc, and the middle of the upper half bullet hole is hollowed out to be of a hollow structure; the lower supporting disc and the base plate are formed to be a whole, a lower half bullet hole is formed in the center of the lower supporting disc, and the middle of the lower half bullet hole is hollowed out to be of the hollow structure; two seal grooves are carved on the base plate. The upper half bullet hole of the upper supporting disc corresponds to the lower half bullet hole of the lower supporting disc, a semicircle notch of the upper supporting disc is engaged with a boss of the lower supporting disc, under the condition of not adding a separating device, automatic separation of the sabot and a bullet is achieved through air resistance in a target chamber, and the light-gas gun pneumatic separation sabot has the advantages of improving the external ballistic property of the bullet and reducing the firing cost.

The invention discloses a mortar shell bullet mechanical trigger fuse with a penetration time self-adaptive function. The mortar shell bullet mechanical trigger fuse comprises a body, a pneumatic insurance mechanism / trigger ignition mechanism, an inertia ignition mechanism, an explosive-proof mechanism, a recoil insurance mechanism, an anti-recovery mechanism of the recoil insurance mechanism, a delay arming mechanism, a setting mechanism, a detonating tube, a booster tube and a bottom screw. Two insurances of the fuse respectively depend on an inner ballistic environment and an outer ballistic environment during launching to be released, and the two insurances of an explosive-proof piece are both in an insurance state at a filling stage and before getting out of a gun muzzle, so that thesafety is good. A fault insurance characteristic is possessed, in case that the recoil insurance mechanism is accidentally relieved, the fuse can be automatically switched into a fault insurance state, and safety in a credible service processing environment is guaranteed; a booster tube adopts an energy-gathered charging structure, so that the detonating capacity is high; the fuse has the characteristics of redundant ignition and redundant fire insulation, is high in reliability, and can ensure the treatment safety of unexploded ammunition explosives; and the fuse is simple in structure, is easy to process and low in cost.

The invention discloses a method for determining an initial orbit of spacecraft based on a precise orbit model. On the basis of the precise orbit model and a laplace equation, a weighted least squaresconditional equation of ground-based radar orbit measurement data, space-based optical angle measurement data, GNSS and Beidou orbit measurement data is established, and improved values of initial positions and velocity are iteratively solved by integrating different kinds of orbit measurement data by using two methods of a direct synthesis method or a federated synthesis method. According to themethod for determining the initial orbit of spacecraft based on the precise orbit model, the complete or incomplete external ballistic observation data, the position and velocity component observation data and the space-based angle measurement data can be directly combined to carry out the satellite-rocket separation initial orbit calculation, and the unique initial orbit output is produced.

The invention discloses an external ballistic trajectory tail section bottom explosion speed-increasing penetration armor-piercing projectile. According to the external ballistic trajectory tail section bottom explosion speed-increasing penetration armor-piercing projectile, a plurality of delivery modes such as missile, rocket, artillery, air drop, unmanned aerial vehicle and manual layout delivery modes are adopted. The external ballistic trajectory tail section bottom explosion speed-increasing penetration armor-piercing projectile is characterized in that a shaped charge is additionally arranged at the rear portion of a penetration warhead; a proximity fuse is additionally arranged at the front end of the warhead; and when the warhead is a certain distance away from the surface of a target, the fuse controls the shaped charge at the rear portion of the penetration warhead to be detonated, so that shaped charge jet flow is jetted backwards to generate an instantaneous reaction force, so that the penetration warhead is pushed to greatly increase speed in an extremely short time and within an extremely short distance, and is ejected to and penetrates the target; the warhead can obtain high penetration capacity without a bulky and huge barrel artillery or the long-distance acceleration of a rocket; and series multi-stage shaped charges can also be used, so that the warhead canobtain higher speed.

The invention relates to a military or police nonlethal fragmentation bomb-shell type small specific kinetic energy bullet, belonging to the weaponry industry and bullet technical field. The technical problems to be solved are that the prior nonlethal kinetic energy bullet is mainly a cloth bag bullet and a bean bag bullet as well as a rubber bullet; the cloth bag bullet and the bean bag bullet have big kinetic energy and small specific kinetic energy, the bullet route is not good, and the bullet is easily deformed in the external ballistic curve to influence the energy deposit and the shooting accuracy as well as the effective range; the rubber bullet has small mass, small kinetic energy and is easy to ricochet. The technical outline of the invention lies in that the hard shell-type small specific kinetic energy bullet is invented according to the shelled egg structure mechanics principle to basically solve the problems of the cloth bag bullet and the bean bag bullet as well as the rubber bullet; besides, a soft shell-type small specific kinetic energy bullet is invented on the basis of the hard shell-type small specific kinetic energy bullet by combining the performance of the rubber. The main application of the invention lies in the aspect of the military operation in urban area, the counter strike, the hostage rescue, the overwhelming and the arrestment of criminal suspects.

Systems to measure muzzle exit conditions of for ammunition improve fire control solutions and reduce shot-to-shot dispersion in both conventional and air-burst programmable ammunition. A first system optically measures coordinate grids on a projectile to measure the initial boundary conditions of external ballistic flight. A second system measures muzzle velocity and, when firing “post-shot” programmable ammunition, the systems calculates a unique time-of-flight optimized for the actual muzzle velocity and transmits the time to detonate signal by using either optically or Radio Frequency signals transmits an optimized time of burst to a projectile. A third system measures muzzle velocity coupled to a ballistic calculator and, when used with ammunition having ferrous characteristics, the force is applied to exiting ammunition to slow or increase the muzzle velocity to a consistent, standardized target velocity. The systems are separately or in combination incorporated into kits that readily improve the performance of weapon systems.

The invention relates to an ultra-caliber launching overload testing method and system. The testing system comprises an acceleration sensor, a data line, a distance control line, a free end of a pluggable joint, a fixed end of the pluggable joint, a base, a data acquisition card, a USB (universal serial bus) cable and a computer, wherein the acceleration sensor arranged in an object to be launched is used for detecting launching overload, the data line with the pluggable joint is used for transmitting launching overload data, and the data is stored in the external computer. The ultra-caliber launching overload testing method has the characteristics that measuring result is accurate and direct, a launching system does not need to be destructively modified, and an internal space of the object to be launched is basically not occupied and an external ballistics process of the object to be launched is not influenced.

A method for geometrically enhancing of the flight of a projectile fired from a weapon to an intended target, including development of a flat annular face on the outermost end of the ogive portion of the projectile, such flat annular face being oriented in a plane that is substantially perpendicular to, and concentric with, the longitudinal centerline of the projectile, and further including extraction of extraneous material from the meplat cavity of the projectile while establishing at least a void volume within the meplat cavity which is substantially concentric with the longitudinal centerline of the projectile and of substantially uniform size and geometry from projectile to projectile. Geometric alteration of the wall thickness of the flat annular face also may be provided. An enhanced projectile and a round of ammunition are disclosed.

Improvements to projectile devices (particularly air guns) include techniques for measuring and controlling the velocity of projectiles in the barrel and after leaving the barrel, allowing the use of non-toxic projectiles. Tracking of a projectile's flight by its unique sound and / or its unique electromagnetic signal or signal modulation are also provided, along with after-barrel guidance that can be used to improve accuracy. Control for discriminating between authorized and unauthorized users is also provided. A projectile device can also be used for inexpensive and harmless practice using optical and / or acoustic information gathered by targeting and imaging systems built into the device.

A method for geometrically enhancing of the flight of a projectile fired from a weapon to an intended target, including development of a flat annular face on the outermost end of the ogive portion of the projectile, such flat annular face being oriented in a plane that is substantially perpendicular to, and concentric with, the longitudinal centerline of the projectile, and further including extraction of extraneous material from the meplat cavity of the projectile while establishing at least a void volume within the meplat cavity which is substantially concentric with the longitudinal centerline of the projectile and of substantially uniform size and geometry from projectile to projectile. Geometric alteration of the wall thickness of the flat annular face also may be provided. An enhanced projectile and a round of ammunition are disclosed.

The invention provides a method for estimating an external ballistic flight state of a cannonball. The method comprises the steps of modeling a system, improving a filtering algorithm and selecting the number of sample points. The improved filtering algorithm is adopted for estimation of external ballistic parameters of the cannonball; a point-mass trajectory equation serves as a state model of the system; and a radar measurement equation serves as a measurement model of the system. The estimation method adopts an improved nonlinear filtering algorithm. According to the method for estimating the external ballistic flight state of the cannonball, a state estimation error can be kept near a certain steady-state range after filtering is started for 5s, so that the convergence effect is good.The estimation method has the advantages that a conventional estimation method is remarkably improved, the measurement precision of external ballistic parameters of a missile rocket is improved, the introduction of a linearization error is avoided under the condition of ensuring the filtering precision and the algorithm calculation amount, and the filtering precision is improved, so that an important basis is provided for performing accurate ballistic control on the cannonball.

The invention provides an open three-dimensional arrangement type ultrasonic automatic target-reporting device. The open three-dimensional arrangement type ultrasonic automatic target-reporting device comprises a target holder, a computer, a display and a power source. Six ultrasonic sensors, an ambient temperature compensation sensor, an ambient wind speed and direction compensation apparatus and a data acquisition processor are mounted on the target holder, every three of the six ultrasonic sensors are in a horizontal row, the six ultrasonic sensors are positioned on the same horizontal line in both horizontal and vertical directions and are positioned on the same horizontal plane, and a certain included angle is formed between the horizontal plane and each of the six ultrasonic sensors. The open three-dimensional arrangement type ultrasonic automatic target-reporting device has the advantages that the target holder with the six ultrasonic sensors is used, an acoustic model of an exterior ballistic trajectory is established by an ambient compensation circuit according to a geometrical relationship between supersonic speed shell shock wave shapes and an ultrasonic sensor array by means of applying ultrasonic inspection, an acoustical principle and an aerodynamics modeling method, and intersection points of pill tracks of direct aiming light weapons and heavy weapons and target surfaces are solved finally according to parameters of measured sensor time and the like so as to solve coordinates of impact points. The open three-dimensional arrangement type ultrasonic automatic target-reporting device solves the problem of heavy weapon training.

The invention provides an anti-riot kinetic-energy bullet launching simulation system and a control method. In order to solve the problem that uniform bullet accelerating cannot be realized by interior and exterior ballistic experiments in the prior art, the anti-riot kinetic-energy bullet launching simulation system comprises a gas injecting system, a launching chamber and a launching tube, wherein the gas injecting system comprises a compressor, a gas storage tank and a high-pressure tank; the compressor communicates with the gas storage tank through a pipeline; the compressor fills compressed air into the inner tank of the gas storage tank; the gas storage tank communicates with the high-pressure tank; the launching chamber is used for filling anti-riot kinetic-energy bullets; the high-pressure tank communicates with the launching chamber through a pipeline, and is controlled by a high-speed solenoid valve to launch; the launching tube is mounted at the front end of the launching chamber; the anti-riot kinetic-energy bullets realize multi-caliber launching through a special bullet support, and the anti-riot kinetic-energy bullets can be accelerated and launched in the launchingtube; the high-pressure tank is connected to a pressure compensating mechanism; and the pressure compensating mechanism can realize pressure compensation in a launching process, so that consistency ofoutlet speed is improved by uniformly accelerating the bullets.

The invention discloses an artillery launching state monitoring system based on digital twinning. The system mainly comprises an artillery launching physical entity, a real-time data acquisition and analysis module, an artillery digital twinning model construction module, an artillery state monitoring and shooting precision prediction module and an artillery shooting data self-adaptive regulation and control module. According to the method, a digital twinning technology is utilized, an artillery digital twinning model is constructed, artillery state data, projectile information data and meteorological information data are dynamically collected, the position of a projectile impact point is predicted through artillery launching dynamics calculation and outer ballistic calculation, meanwhile, historical data are stored, and the prediction accuracy is improved. Accuracy of artillery launching dynamics calculation and outer ballistic calculation is continuously optimized, autonomous determination and automatic adjustment of the optimal launching angle and azimuth angle of the artillery are achieved, and finally state monitoring and dynamic control of the artillery launching process are achieved. The problem that when an existing artillery is launched, random factors such as the initial state of the artillery, projectile manufacturing deviation and meteorological changes affect the shooting precision is solved.

The invention discloses a uniform dispensing device and dispensing method for damage assessment microsystems in a warhead. The dispensing device comprises cabins, an inner support, an outer support, areinforcing rod, a push plate, a central explosive pipe, a delayed explosion circuit, an electric detonator and an explosion bolt, wherein the independent cabins are adopted as carriers for the damage assessment microsystems, the cabins are separated from the warhead while arriving at the overhead space of a target area, and the damage assessment microsystems are scattered in a delayed manner. According to the uniform dispensing device and dispensing method for the damage assessment microsystems in the warhead, explosive charging of the warhead and the shapes of projectile bodies are not influenced, so that change for the aerodynamic characteristics of the warhead, and influence on a predetermined flight path due to an impact on the exterior ballistic flight parameters of the warhead in an explosion process are avoided; and when the warhead starts to act, the damage assessment microsystems already uniformly fall to the ground and are dispensed to complete an initialization flow, and are in a working state, and therefore, a scattering mechanism needs to be used as an additional power source and gives a certain initial scattering speed to the damage assessment microsystems.

The invention provides an intelligent grenade launcher aiming device, which adopts the technical scheme that a core intelligent aiming system comprises a laser ranging module, an azimuth angle measuring module, a trajectory resolving module, a control switch module and an indicator lamp array module. The control switch module controls the laser distance measuring module and the azimuth angle measuring module to work through a calibration button and sends measured information to the ballistic calculation module, whether the grenade can be hit or not and the range of the corresponding firing angle are calculated through given grenade parameters, the Longze-Kutta method is used for self-starting, the Adams forecast correction method is used for calculating the follow-up ballistic, and then the grenade is obtained. A numerical solution of an outer ballistic differential equation is obtained, a shot angle corresponding to a shot target is obtained through a bisection method, and finally, soldiers are indicated to perform excitation actions through an indicator light array module, so that the grenades accurately hit the target.

A projectile 360, 460 includes a body having a distal ogive section with external ballistic effect uniforming surface discontinuity (e.g., nose ring groove 369, 469) defined therein to provide an unsupported gap in the ogive profile which affects the flow of air over the front half of the ogive to provide greater aerodynamic uniformity and shot-to-shot consistency with more uniform observed external ballistics and superior terminal ballistics. The bullet's external surface discontinuity feature (369 or 469) creates effects in the flowfield that dominate any dynamic effects from bullet-to-bullet manufacturing inconsistency and resultant differences in dynamic behavior.

The invention provides an external trajectory optical measurement precision analysis method based on a virtual platform. The method comprises the following steps: S1, three-dimensional modeling; s2, constructing virtual outer ballistic trajectory optical measurement equipment; s3, generating a target three-dimensional flight animation; s4, outputting a two-dimensional image sequence; s5, setting an error term; s6, performing image processing and parameter calculation; s7, measurement precision analysis. According to the virtual platform-based external ballistic optical measurement precision analysis method, precision analysis can be performed on an image processing software algorithm, and the precision analysis capability of optical measurement equipment from hardware to a software algorithm whole system is achieved; the method can analyze the measurement precision of dynamic outer trajectory parameters related to target motion, such as flight speed and attack angle, and has the capability of analyzing the static and dynamic full-parameter measurement precision of the outer trajectory.

The invention relates to weapon manufacturing technology, and relates to a non-lethal dyed bullet warhead. The low-power and high-precision dyed warhead of the present invention is composed of a warhead cap [1], a dyeing agent [2], a soft elastic body [3] and a warhead plug [4]. The dyeing agent [2] and the soft elastomer [3] are set in the space between the bullet cap [1] and the bullet plug [4], and one end of the soft elastic body [3] is connected to the bullet plug [4] , the other end goes deep into the dye [2] and has a cross-shaped structure. When the warhead hits the target and breaks, and the dye is sprayed out, the elastic body interacts with the target, prolonging the time for the warhead to collide with the target, and significantly reducing the power of the warhead. Moreover, the soft elastomer [3] has a cross-shaped structure, so when the bullet rotates, it can drive the dyeing agent to make it rotate synchronously with the bullet, thereby ensuring the stability of the internal and external ballistic performance of the bullet, thereby satisfying the requirements of short-distance power, small Long-distance high precision and good dyeing effect are required.

The invention relates to a light-gas gun pneumatic separation sabot, and aims at solving the problems that for an existing sabot, an additional device is needed to conduct separation on the sabot, the effect is not ideal and the cost is increased. The light-gas gun pneumatic separation sabot is composed of an upper supporting disc, a lower supporting disc and a base plate; the upper supporting disc and the lower supporting disc are two corresponding semi-cylinders. An upper half bullet hole is formed in the center of the upper supporting disc, and the middle of the upper half bullet hole is hollowed out to be of a hollow structure; the lower supporting disc and the base plate are formed to be a whole, a lower half bullet hole is formed in the center of the lower supporting disc, and the middle of the lower half bullet hole is hollowed out to be of the hollow structure; two seal grooves are carved on the base plate. The upper half bullet hole of the upper supporting disc corresponds to the lower half bullet hole of the lower supporting disc, a semicircle notch of the upper supporting disc is engaged with a boss of the lower supporting disc, under the condition of not adding a separating device, automatic separation of the sabot and a bullet is achieved through air resistance in a target chamber, and the light-gas gun pneumatic separation sabot has the advantages of improving the external ballistic property of the bullet and reducing the firing cost.

The invention discloses an achieving method of a cartridge-case-free automatic weapon adopting a liquid gun propellant. The weapon is driven by a stepping motor to achieve bullet filling and combustion chamber locking, and combustion chamber airtightness is achieved through a bullet and a fixed type plunger. Separated binary liquid gunpowder (oxidizing agent and combustion agent) is adopted as thegun propellant, a constant pressure adjuster is used for maintaining constant gun propellant ejection pressure, an electronic fire control unit (EFCU) is used for controlling the opening time of an electromagnetic valve so as to accurately control the ejection amount of mixed gun propellant, gunpowder ejection is completed through spraying holes in the plunger, and an electronic igniter is used for igniting the gun propellant to complete bullet launching. The weapon can easily achieve the functions of single launching, multiple launching, continuous launching and blank ammunition and rifle grenade launching; the launching power can be adjusted to achieve the optimal killing and wounding effect; an inner bullet channel can be actively corrected to ensure stability of an outer bullet channel; the shooting precision which is higher compared with bolt weapons can be achieved in the single launching mode, and continuous launching can be achieved for implementing fire control.

The invention discloses a light curtain array outer ballistic parameter testing device which comprises a light curtain array detector, an upper computer signal processing and control device and a photoelectric signal acquisition device. According to the invention, a non-contact photoelectric test principle is applied, the outer ballistic trajectory parameters after the projectile is launched can be accurately tested in a multi-light curtain array mode, the functions of traditional test equipment are enriched, and the device has the advantages of high test precision, simplicity and convenience in operation, high real-time performance and the like.

The invention relates to a guided transformation technology of rotating ammunition, in particular to an on-line calibration compensation method for an attitude misalignment angle between a magnetic measurement signal and a projectile body coordinate system. The invention solves the problem that the traditional calibration compensation method cannot calibrate and compensate the attitude misalignment angle between the magnetic measurement signal and the missile body coordinate system. An online calibration compensation method for the attitude misalignment angle between the magnetic measurement signal and the missile body coordinate system. The method is realized by the following steps: Step 1: Real-time acquisition of the three-axis geomagnetic field vector output by the magnetic measurement system during the ballistic flight outside the missile body signal H m ; Step 2: Estimate the roll angle γ of the projectile at any time t in the roll period T of the projectile; Step 3: Obtain the coefficient a of the fitting curve x , b x , c x , a y , b y , c y , a z , b z , c z ;Step 4: Solve the three-axis installation error angle matrix M between the coordinate system of the magnetic measurement system and the coordinate system of the missile body install ; Step 5: Obtain the three-axis geomagnetic field vector signal H under the projectile coordinate system b . The invention is suitable for the guided transformation of rotating ammunition.

The invention discloses a trajectory equation-based miss distance calculation method and system and belongs to the technical field of miss distance calculation. The method comprises the steps of: building a trajectory equation according to the type of a projectile and the influence factors of the movement of the projectile; calculating an outer ballistic trajectory on the basis of the ballistic equation so as to obtain projectile position information; and reading the coordinates of the hitting point of the projectile, and solving a miss distance under a ground coordinate system on the basis ofthe projectile position information. The system comprises a ballistic equation construction module, a projectile position information acquisition module and a miss distance calculation module, and isused for realizing the method. According to the method and system of the invention, the flight time, azimuth angle and launching angle of the projectile are used as initial conditions; the motion trajectory is calculated on the basis of a trajectory equation; and the miss distance, azimuth angle and angular altitude between the projectile and the hitting point are calculated. With the method andsystem of the invention adopted, the miss distance can be predicted in advance; a calculation result shows that the miss distance calculated by the method is very close to a theoretical miss distancecalculation result; calculation precision is high; and a theoretical basis can be provided for the precision evaluation of the miss distance.

The invention provides a ballistic correction device based on relay control and relates to the field of ballistic correction devices based on relay control. The ballistic correction device provided by the invention can be used for the ballistic correction process of a high-rotation stable aircraft or ammunition. According to the ballistic correction device, the positioning and the ballistic measurement are achieved according to a satellite terminal in the exterior ballistic process; through a control unit, flight errors are calculated and instructions are sent out; and consequently, the rudder surface control can be conducted and the ballistic correction force can be provided in the ammunition flight process, the problem about the normal control force required when a high-rotation ammunition body flies can be solved with a relatively low cost, the guidance capacity of traditional ammunition can be achieved, and the ammunition striking precision can be improved. The ballistic correction device comprises a hollow shaft, a rudder loop, an electromagnetic relay, an armature and a friction sheet. The ballistic correction device has the beneficial effects that the structure is more compact; the driving operation is easier and more convenient; the rudder load is effectively reduced; the correction ammunition posture adjustment is facilitated; the correction efficiency is improved; and the ammunition striking precision is higher.

The invention discloses an outer ballistic interruption point correction method based on telemetering apparent acceleration, and the judgment method comprises the following steps: (1) remote time alignment, (2) alignment of telemetering data to outer measurement data, (3) calculation of the components of gravitational acceleration in the radial direction and the earth rotation direction, (4) calculation of the gravitational acceleration of a space target point, (5) calculation of the projection of the earth rotation angular velocity on each axis of the emission coordinate system; and (6) correction of the position of the interruption point. According to the rocket attitude angle condition judgment method based on the externally measured speed, based on the basic ideas of remote and external fusion and internal and external complementation, the externally measured acceleration is calculated by using the telemetering apparent acceleration, and the trajectory information of the interruption point is corrected by using the basic principle of kinematics.

A test guidance control method for external ballistic networking, including transforming the coordinates of target data measured by radar, photoelectric equipment and telemetry equipment to optimize the trajectory, and broadcasting the optimized trajectory data to all test equipment in real time, when the target tracking of the test equipment is lost , the received broadcast data is properly extrapolated to guide the device to quickly capture the target, and the ballistic optimization algorithm uses the least squares + Wright criterion. The present invention can complement each other on the ballistic section covered by the guidance and measurement data, and the test parameters can be used as backup and reference for each other, and make reasonable use of the special features of each measurement system, so that each measurement system can complete the test task in the most effective ballistic section. Significantly improve the data collection rate of a single set of equipment. Compared with the traditional test, the tracking rate of the network test equipment using the guidance control system of the present invention is significantly improved.

The invention belongs to the technical field of ultra-high-speed collision research, and aims to provide a high-overload-resistant projectile for a gas detonation driven ultra-high-speed launcher to solve the problem that a traditional projectile structure cannot meet the requirement of bearing higher overload in the acceleration process. The high-overload-resistant projectile comprises a flying body and a combined projectile support structure, an anti-wear projectile support is in interference fit with a launching tube, a containing cavity is formed in the anti-wear projectile support, an anti-overload projectile support is installed in the containing cavity, and the flying body is installed at the front end of the anti-overload projectile support. The high-overload-resistant projectile is scientific and reasonable in design, safe and convenient to assemble, and capable of effectively relieving the wear problem of the launching tube in the launching process, so that the service life of a launching system is prolonged; and the anti-overload projectile support can meet the anti-overload condition, meanwhile, the machining difficulty is low, the gravity center of the flying body moves forwards, the stability of trajectory flight outside the flying body is improved, the friction resistance of the surface of the flying body is reduced, and the speed storage performance of the flying body is improved. The high overload resistance of the projectile is verified through experiments.

The invention discloses a mortar warhead mechanical trigger fuze with a penetration time self-adaptive function, which includes a body, a pneumatic safety mechanism / trigger firing mechanism, an inertia firing mechanism, an explosion-proof mechanism, a recoil safety mechanism and its anti-recovery mechanism, Delay release of insurance mechanism, setting mechanism, detonator, detonator and bottom screw. The two insurances of the fuze depend on the internal ballistic environment and the external ballistic environment respectively to release the insurance, and the two insurances of the flameproof part are in the insurance state during the loading stage and before the muzzle exit, and the safety is good; and it has the feature of fail-safe , in case the recoil insurance mechanism accidentally releases the insurance, the fuze will automatically transfer to the failsafe state to ensure safety in a credible service processing environment; the booster tube adopts a shaped charge structure with strong detonation ability; Redundant flame-resistant features, high reliability, can ensure the safety of unexploded ammunition and explosives disposal. The fuze has simple structure, easy processing and low cost.

The invention belongs to the technical field of weapons and ammunition, and relates to a fuel press-fitting mold for a cylinder thin-wall structure projectile body and a using method of the fuel press-fitting mold. The fuel press-fitting mold comprises a base, an ejector head, a first sleeve, a fastening structure and a pressing rod; a first groove is formed in the top face of the base, and the section of the first groove is circular; the ejector head is coaxially arranged in the first groove in a sleeved manner and is used for limiting the projectile body; the first sleeve is coaxially arranged in the first groove in a sleeved manner and located on the upper side of the ejector head; the fastening structure is arranged on the base and used for fixing the relative positions of the first sleeve and the first groove; and the pressing rod is inserted in the first sleeve. The fuel press-fitting mold is low in manufacturing cost, the manufacturing cost is reduced, the press-fitted shape has good repeatability, then the influence on the aerodynamic characteristic consistency of an outer trajectory is reduced, due to the protection design for the thin-wall part of the projectile body, the thin-wall projectile body can be protected in the press-fitting process, deformation is avoided, it can be guaranteed that high-temperature is not in direct contact with personnel in the whole process, the risk that the personnel are scalded is reduced, the structural adaptability is high, flexibility is achieved, and practicability is high.