31 results about "Internal ballistics" patented technology

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 present invention relates to a one-dimensional interior ballistic modeling and performance prediction software system of a solid engine. The system comprises a nozzle type selection module, a charge data import module, a nozzle data input module, an igniter data input module, a user selected data input module and a calculated result display module. The nozzle type selection module is used forselecting the set nozzle type; the charge data import module is used for importing the charge data; the nozzle data input module is used for parameter input of the nozzle; the igniter data input module is used for parameter input of the ignition gas mass flow rate; the user selected data input module is used for parameter input of the working end pressure, the design temperature, and the like; andthe calculated result display module is used for displaying a calculated result. According to the system provided by the present invention, defects of the inaccuracy of the conventional zero-dimensional interior ballistic calculation method, the incomplete consideration of the factors affecting the interior ballistics, and the like are overcome, the simulation precision and the modeling speed ofthe internal ballistic performance of the engine are improved, the design and calculation efficiency of the solid engine is improved, and the product development cycle is shortened.

The invention discloses a high property solid propellant rocket engine with a laterally arranged nozzle. The high property solid propellant rocket engine with the laterally arranged nozzle comprises a charging combustion chamber, an ignition device and the nozzle, wherein a combustion chamber shell body of the charging combustion chamber is a hollow cylinder. The high property solid propellant rocket engine with the laterally arranged nozzle is characterized in that the nozzle is fixedly mounted at the opening of the outer side of the combustion chamber shell body in a sealed mode, the included angle between the axis of the nozzle and the axis of the cylinder of the combustion chamber shell body is 10-90 degrees. By arranging the nozzle laterally, the requirements for high thrust and high total impulse of the solid propellant rocket engine in a small using structural space are met; by designing a special-shaped nozzle shell body, the problem of sealed mounting of the laterally arranged nozzle is solved; by designing special-shaped nozzle throats, the problem that fuel gas in the charging combustion chamber flows along the wall caused by the nozzle arranged laterally is solved, and ablation and erosion on the position of the sealed mounting structure of the nozzle are substantially improved, the reliability of heat proof, load-carrying capability and connection sealing design on the position of the sealed mounting structure of the nozzle are improved, the integration of the engine work structure and the uniformity of internal ballistic property are guaranteed.

The invention provides a method for predicting internal ballistic performance of a solid rocket engine. The method comprises the following steps of: establishing a parameterized charging structure model; carrying out analogue simulation on the combustion process of the charging structure model, and outputting a relation curve between combusted thickness and a combustion surface and a relation curve between the combusted thickness and the exposed area of a heat insulation layer; calculating propellant mass flow rates corresponding to different time points according to the relation curve of thecombusted thickness and the area of the combustion surface, calculating the ablation mass flow rates of the heat insulation layer corresponding to the different time points according to the relation curve of the combusted thickness and the exposure area of the heat insulation layer, adding the propellant mass flow rate and the ablation mass flow rate of the heat insulation layer corresponding to the same time point, and outputting the relation curve of time and combustion product mass flow rates; and obtaining an internal ballistic performance curve according to the relation curve of the combustion time and the combustion product mass flow rates. The method obviously improves the prediction precision of the internal ballistic performance in of solid rocket engine before a ignition test, optimizes the performance of the solid rocket engine, and reduces the development time and development cost.

The invention discloses a solid rocket engine erosion combustion rapid parameter identification method, and the method comprises the steps of carrying out an ignition test on a designed standard erosion engine and a standard erosion propellant grain, and obtaining a test pressure intensity curve with erosion pressure intensity peak characteristics; and giving a group of erosion parameters, and substituting the group of erosion parameters into the one-dimensional erosion internal ballistic calculation model to obtain a theoretical pressure intensity curve, and making a curve residual between the test pressure intensity curve and the theoretical pressure intensity curve, and judging whether the curve residual meets the residual requirement or not. And if the requirement is met, outputting the erosion parameter in the erosion inner ballistic calculation as an identification result, and ending the identification calculation; if the curve residual does not meet the requirement, updating anerosion parameter given by iteration through an algorithm, performing inner ballistic calculation again, calculating the curve residual, and judging whether the curve residual meets the requirement ornot; and completing the rapid parameter identification of the erosion combustion after the iteration is ended. The identification method is wide in application, and the erosion parameters of different propellants can be identified.

The invention discloses a method for constructing a law model of plasma generated by propellant powder, belonging to the field of plasma, the method comprises the following steps: S1, under the hypothesis of an inner trajectory and in a high-pressure state, a firing pin impacts the bottom of a hearth, primer is ignited, main charge is ignited through the primer, the main charge is combusted to generate high-temperature and high-pressure fuel gas, the fuel gas is used for doing work and pushing the projectile to move, and finally the projectile is launched out., S2, constant volume state analysis, S3, combustion process assumption, S4, plasma rule model construction and S5, model verification. The construction method disclosed by the invention is more scientific and reasonable; the physical process of propellant powder combustion is analyzed, the internal ballistic theory, the combustion theory, the plasma theory and the like are combined, a mathematical model of the plasma generation law of propellant powder under the high-pressure state is finally established, the result of numerical simulation is compared with the test result, and the correctness and feasibility of the model are determined.

The invention discloses a method for estimating ballistic parameters in a combustion light-gas gun. The method comprises the following steps: (10) acquiring initial parameters of a combustion chamber:acquiring a solution domain and a sectional area of the combustion chamber and distribution of main parameters on the solution domain; (20) constructing a compressible reaction flow N-S model: constructing a one-dimensional viscous compressible reaction flow numerical model according to ballistic characteristics in the combustion light gas gun; (30) initializing a node parameter matrix: carryingout node interpolation on main parameters and initializing the main parameters to a main variable of a control equation set; (40) solving a node parameter matrix: solving the node parameter matrix based on a WAF-HLLC Riemann solver to obtain main parameters; and (50) determining internal ballistic parameters: calculating flow field parameters according to the main parameters, inversely solving anenthalpy value formula based on a Newton approximation method, updating the node temperature T, and obtaining the internal ballistic parameter distribution of the combustion light gas gun at a specified moment. The ballistic parameter estimation method is high in accuracy and wide in application range.

The invention realizes a three-dimensional simulation method for simulating a trajectory motion state and a flow field distribution condition in a projectile under a forced angular vibration conditionby using a bidirectional fluid-solid coupling technology on the basis of an ANSYS software platform. The process from the movement of the projectile in the chamber to the discharge of the projectileout of the chamber is a high-temperature, high-pressure and multi-chemical reaction process, and the actual experimental measurement is difficult. The process is simulated by using a numerical simulation technology, so that the analysis of the motion state and the flow field change of the projectile in the chamber is facilitated. According to the method, a cannon barrel forced angular vibration equation is introduced by using a bidirectional fluid-solid coupling numerical simulation method, and numerical simulation is carried out on the process that the projectile is moved from the static state to the out-of-bore state under the forced angular vibration condition. The result obtained through simulation of the method is beneficial to research of the motion state of the launched projectile and the distribution situation of the flow fields inside and outside the chamber when forced angular vibration is generated in the advancing process of the artillery, and certain significance is achieved for research and development of self-propelled weaponry.

The invention provides a charging structure suitable for low-temperature ignition. The charging structure comprises a propellant grain, and a center hole with the two ends being through is formed in the center of the propellant grain in the axial direction; an inner conical opening which is coaxial with the center hole and communicates with the center hole is formed in one end of the propellant grain; an ignition powder ring mounting groove is formed in the end face of the other end of the propellant grain, an ignition powder ring is mounted in the ignition powder ring mounting groove in an embedded mode, and the ignition powder ring and the center hole are coaxially arranged; the end face of one end of the ignition powder ring and the bottom of the ignition powder ring mounting groove are bonded through a nitrocotton solution bonding layer; and a coating layer is arranged on the side wall of the propellant grain. According to the charging structure, on the premise that the internal ballistic property is met, the charging ignition reliability in the low-temperature environment can be effectively improved; and the phenomena of delayed ignition, ignition failure and the like during charging low-temperature ignition can be effectively improved, and the ignition reliability of charging in the low-temperature environment is greatly improved.

The invention relates to the technical field of propellant powder, in particular to a method for calculating trajectory characteristic parameters in flaky multilayer propellant powder. The combustiongradual increasing property of the multilayer propellant powder is represented by adopting a combustion speed ratio method, so that the problem that the combustion gradual increasing property of the multilayer propellant powder can only be qualitatively represented and cannot be quantitatively represented is solved. A transition layer gradient function method is adopted, calculation of the inner trajectory of the multi-layer propellant powder is optimized, and the inner trajectory characteristic parameters of the flaky multi-layer propellant powder can be obtained through one-time inner trajectory circulation. The same coordinate mode in the direction from the outer layer to the inner layer is adopted, so that all characteristic parameters of the propellant in the combustion process are converted into a single relation with the coordinate as a variable, the combustion increasability of the multi-layer propellant can be quantitatively represented, and the method is suitable for any propellant of a multi-layer complex structure.

The invention provides an explosive load identification method and system for a pyrotechnic actuator, and the method comprises the steps: step 1, constructing a measurement system for identifying a load generated by the combustion of ballistic combustion powder in a pyrotechnic actuator, the measurement system comprising- an inner wing, an outer wing, the pyrotechnic actuator, an acceleration sensor and an angle sensor; step 2, performing data cleaning on the collected acceleration data and angular velocity data through polynomial fitting; and step 3, according to a Lagrange equation, establishing a mathematical model of a measurement system, and according to the acceleration data and the angular velocity data of the outer wing surface, calculating to obtain an output load of the pyrotechnic actuator. By measuring the acceleration signal and the angular velocity signal, the change of the output load of the pyrotechnic actuator after the external boundary condition is changed can be identified very conveniently, and data support is provided for improving the launching reliability of a weapon system.

The invention provides a signal generator about the internal ballistic pressure for the virtual experiment of the gun firing, which comprises a mount body. The mount body is provided with an external power input port, a data input port and an analog voltage output port. The digital signal processor and the digital-to-analog conversion module are arranged inside the mount body. The digital signal processor comprises a DSP module and a power conversion module. The power conversion module is connected with the external power input port. The DSP module is connected with the data input port. The digital-to-analog conversion module is connected with the analog voltage output port. The signal generator about the internal ballistic pressure for the virtual experiment of the gun firing establishes a channel between the virtual simulation system and the data acquisition instrument to convert the simulation calculation data into the analog voltage signal which can be collected by the acquisition instrument, which students are able to conduct the establishment of the virtual internal ballistic test system, the connection of the training line and the parameter setting of the data acquisition instrument. The signal generator about the internal ballistic pressure for the virtual experiment of the gun firing has the compact overall appearance with the simple and convenient operation.

The invention provides a small-caliber gas gun bore pressure measuring device and a using method thereof and relates to the field of parameter measurement of a trajectory in a gas gun. The small-caliber gas gun bore pressure measuring device comprises a sealing assembly, a measuring assembly and a balance weight base piece which are connected end to end in sequence; and the measuring assembly is composed of piezoelectric ceramic and an auxiliary component connected with the piezoelectric ceramic. According to the small-caliber gas gun bore pressure measuring device, the defects of complex structure, large size, high manufacturing cost, poor program adjustability and measurement stability, unsuitability for measuring the gun bore pressure of small-caliber gas guns and the like of the priorart of gun bore pressure measurement can be effectively overcome.

The invention discloses a combined balance body structure meeting stability of an internal ballistic trajectory and an assembling method thereof. The combined balance body structure meeting the stability of the internal ballistic trajectory comprises an outer cylinder, a plurality of first balance blocks, a second balance block and an electric ignition device; the first balance blocks are sequentially mounted in the outer cylinder in series; the second balance block is mounted in the outer cylinder and located at the tail end of the last first balance block; and the electric ignition device is located in the second balance block. According to the combined balance body structure meeting the stability of the internal ballistic trajectory, by flexibly controlling the mass size of a balance body to be matched with the launching working condition, a projectile and the balance body simultaneously go out of a muzzle and a breech or the projectile is at least guaranteed to go out of the muzzle slightly first; and through the matched electric ignition device, the air tightness of an electric ignition channel is guaranteed, and the electric ignition device can be conveniently mounted on the balance body; and through the split design of the ignition device and the balance body, the independence of the ignition device and the balance body is guaranteed, and mutual interference can be avoided.

The invention belongs to the field of inner trajectory launching, and particularly relates to a series self-adaptive elastic band device for improving the launching safety of a non-rib rifling artillery. A self-adaptive elastic band is formed by connecting a plurality of thin elastic band rings with the same shape and size in series, the adjacent thin elastic band rings are fixed through colloid,and the peeling strength of the colloid is smaller than 1/3 of the damage strength of thin elastic band ring material. According to the series self-adaptive elastic band, due to the fact that the peeling strength of the colloid between the thin elastic band rings is smaller than 1/3 of the damage strength of the thin elastic band ring material, the colloid bonded between the thin elastic band rings is gradually peeled off under the action of elastic band torsion force caused by rifling winding angle changes in the forward movement process of the elastic band along with rifling; and the elasticband rings can rotate relatively within a certain range, so that the problems of damage and function failure of the elastic band due to forced torsion are finally avoided, and the safe launching of projectiles is realized.