608results about "Ammunition testing" patented technology

The invention relates to the technical field of trajectory analysis, in particular to a trajectory aiming trajectory analysis method which comprises the following steps: acquiring wind speed time-varying data and centroid parameters, calculating wind disturbance stress and screening a maximum value, judging a rotating direction trend, executing pitch angle consistency judgment, and calculating an angle adjustment rate to generate boundary parameters. The method comprises the steps of analyzing a target speed trend to judge delay, calculating a deviation trend difference value, extracting wind disturbance sudden change to mark a high-sensitivity zone, judging that deviation coincides with the high-sensitivity zone, and generating a dynamic correction instruction set. Modeling analysis is carried out on a target delay trend by combining a direction included angle and mode difference change in a target speed trend sequence, and a trajectory correction mapping relation is constructed by combining flight parameters and timestamps, so that the adjustability and striking precision of an overall hit path are effectively improved.

The invention relates to a bending moment-torque composite loading device for testing the load capacity of a steering engine, and belongs to the technical field of ammunition weapon system testing. In the device, the pressure head, the pressurizing rod and the composite loading slip ring synchronously rotate along with the rotation of the rudder wing, so that the applied pressure can be ensured to be always perpendicular to the rudder surface and is closer to the real wind resistance working condition during flight. The bending moment output device and the torque output device are coupled together through the composite loading slip ring, so that the bending moment and the torque can be loaded at the same time and are closer to the actual flight condition.

The invention relates to the technical field of fault detection, and discloses a redundant strapdown inertial measurement unit fault diagnosis and isolation method and system, so as to improve the overall performance of fault processing. The method comprises the following steps: determining target objects of fault diagnosis, wherein the target objects are grouped gyroscopes or add tables in the same redundant strapdown inertial measurement unit; the method comprises the following steps: calculating a variation trend and a constant of any gyroscope or accelerometer in a target object based on previous continuous frames based on a least square method, then calculating a predicted value of a current frame according to the variation trend and the constant, then calculating whether a difference value between the predicted value of the current frame and a measured value is greater than a set prediction threshold value, and if so, judging whether the difference value is greater than the set prediction threshold value. And judging that the corresponding gyroscope or accelerometer has a fault, and performing isolation processing on the gyroscope or accelerometer having the fault.

The invention discloses an explosion load simulation test device, system and method, and belongs to the technical field of explosion tests. The device comprises a driving section and a driven section, the driving section comprises a test pipeline which is used for guiding and accommodating methane-air mixed gas and deflagration products, a plurality of through holes which can be sealed by bolts are formed in the test pipeline, an obstacle partition plate and a polyethylene film are arranged in the test pipeline, and the polyethylene film is used for forming an inflation section; the driven section comprises an expansion section, a straight section and a structural section which are connected in sequence, the first end of the expansion section is connected with the test pipeline and used for diffusing shock waves generated by detonation, and the two ends of the straight section are connected with the second end of the expansion section and the structural section respectively and used for completing shaping of the blast load and improving the uniformity of blast load distribution on the structural section; and the structural section is used for bearing explosion load driven by detonation of methane and air mixed gas. According to the invention, the methane-air mixed gas is used as an explosion source, so that the test safety is improved, and the test cost is reduced.

The invention discloses a device and method for testing the cross-medium water entry of a navigation body under the wave condition, and relates to the technical field of missile body water entry testing equipment.The device for testing the cross-medium water entry of the navigation body under the wave condition comprises an experimental water tank, and a wave maker is arranged in the experimental water tank; the adjusting module comprises a launching platform capable of adjusting the inclination angle; the emission module comprises an emitter and a driving source, the emitter is arranged on the emission platform, the driving source is in butt joint with one end of the emitter, the other end of the emitter is provided with a rectification structure, and high-pressure gas provided by the driving source enables a carbon body loaded on the emitter to be released at a certain initial speed; the rectification structure is used for reducing interference generated by gas turbulence in the radial direction of the launcher when the projectile body leaves the launcher. According to the invention, a stable wave page is generated through the cooperation of the motion phases of the two wave generators, the process that a projectile body enters water under a real sea condition is simulated, and more accurate experimental data is provided for the design and optimization of a cross-medium motion body.

The invention relates to the technical field of shock wave overpressure calculation modeling, in particular to a method for constructing a shock wave overpressure calculation model under the condition of high-speed kinetic explosion of open-space ammunition. The method comprises the following steps of: obtaining actual measurement data, removing impurity data, screening actual measurement effective data, performing constant fitting on the actual measurement effective data and three-order, high-order and segmented shock wave overpressure calculation empirical formulas, and calculating overpressure data of each measurement point by using the fitted three-order, high-order and segmented empirical formulas. And comparing the calculated overpressure data with actually measured data, calculating an error, calculating an average error, then selecting a formula with the minimum average error obtained by three empirical formulas as a corresponding ammunition shock wave overpressure calculation formula, and fully considering the influence of different ammunition use environments, falling speeds, falling angles and ammunition specifications and models. And a model support is provided for evaluating the shock wave damage capability of different ammunitions on target striking.

The invention relates to the technical field of military data processing, in particular to a light weapon live ammunition efficiency data acquisition method and system, and the method comprises the following steps: obtaining bullet center coordinates in continuous frames, calculating a motion vector, predicting the position of a hit region, extracting the overlapping information of a brightness sudden change region and the hit region, and recognizing an effective hit region. Contact point arrangement and tearing characteristics are analyzed, a structure response chain segment is generated, a mapping path is constructed according to bullet types, and a live bullet response data structure mapping set is formed. According to the method, through dynamic extraction and motion vector construction of the bullet center point in the continuous image and judgment in combination with prediction of the overlapping proportion of the hit area and the abrupt change boundary, the spatial distribution information of the hit position can be rapidly identified, the contact point group and crack characteristics can be analyzed, and accurate extraction of the geometric response of the bullet area can be realized; according to the bullet type number classification and mapping, a complete response path is formed, and the recognition efficiency, the space precision and the processing continuity of multi-dimensional data in a shooting test are effectively improved.

Systems and methods for testing projectiles is disclosed. The system can include a projectile with one or more portions. Each portion can be rotatable about a major axis of the projectile. The projectile can include one or more sensors. The sensors can determine at least a relative position of the first portion to the second portion. The test system can include a radial centrifugal housing. The centrifugal housing can receive an intake of air, circulate the air radially around the major axis of the projectile, and rotate a first portion of the projectile at a first rate. The test system can include measurement unit to determine a condition of the projectile responsive to rotation of the first portion of the projectile.

The invention discloses a hypergravity field penetration simulation test device, which comprises an air cannon, a launching bullet, a support mechanism, a penetration test mechanism and an acceleration mechanism, and is characterized in that the launching bullet is arranged in the air cannon, the air cannon is arranged in the support mechanism, the bottom of the support mechanism is connected with the top of the penetration test mechanism, and the acceleration mechanism is arranged in the support mechanism; high-pressure gas is filled into the air cannon to push the launching bomb to realize launching; the acceleration mechanism comprises a centrifugal machine and a hanging basket, and the acceleration mechanism provides a super-gravity field environment for the penetration simulation test through rapid rotation; the launching bomb intrudes into the test device to simulate the penetration process. According to the hypergravity field penetration simulation test device provided by the invention, the hypergravity field is applied to the test model through the centrifugal machine, and the test model and a prototype are similar in power, motion and energy, so that a more real penetration process is simulated, various parameters can be conveniently changed, multiple repeated tests can be carried out, and the test efficiency is improved. The test efficiency and the refinement degree are greatly improved, the cost is remarkably reduced, and damage is reduced.

The invention discloses liquid rocket system polarity test equipment and a test method, and the method comprises the steps: carrying out the analysis of the working principles of a rocket system polarity test servo system, a final correction attitude control correction system and an engine power system, selecting a corresponding data collection device, and installing the data collection device at a to-be-detected position. During testing, a corresponding data acquisition device is used for carrying out data acquisition on parts with relative position changes or electromagnetic valve actions in the servo system, the final correction attitude control correction system and the engine power system. The data transmission system transmits the collected test data to the control and data processing system. And the control and data processing system compares the received test data with the instruction data to realize automatic interpretation of the system polarity test. The liquid rocket polarity test data and the system data are effectively and deeply fused, the accurate closed loop of the data is realized, the requirements of systematization and automation of carrier rocket test are met, the product reliability is improved, and the production efficiency is also improved.

The invention provides a carrier rocket ground test system and method supporting visual process configuration. The system mainly comprises: (1) a visual process configuration module, which configures a test process file through a graphical interface; (2) a process analysis and scheduling module for analyzing a process file and converting the process file into a task sequence; the test execution engine module (3) is used for driving bottom hardware and executing a test instruction sequence; (4) the test resource library module is used for storing and managing various information of test elements and various information of test equipment; the execution monitoring and data management module (5) is used for displaying a test execution state in real time and recording whole-process data; according to the method, the test logic and the execution program are separated, and a user can quickly construct, modify and reuse an automatic test process in a graphical mode, so that the test flexibility is greatly improved, and the test adaptability and efficiency are remarkably improved.

The invention discloses an artificial influence weather rocket projectile three-explosion self-destruction body assembly detection system, and relates to the technical field of multivariable comprehensive measurement, and the system comprises a multi-dimensional positioning measurement module which is used for measuring the coaxiality and fitting pressure of a self-destruction body and an engine housing; the multi-parameter measuring module is filled with the medicament to measure the weight, density and internal defects of the medicament; the connection strength dynamic measurement module is used for measuring torque, tensile strength and vibration displacement; the igniter performance parameter measuring module is used for measuring resistance, time delay and safety reliability; the measurement data integration analysis module is used for integrating a data generation report and an encryption log; and the system control and exception handling module is used for coordinating module time sequences, monitoring data and handling exceptions. According to the system, multi-parameter integrated measurement of the three-explosion self-destruction body is realized, the measurement precision of positioning, medicament filling, connection strength and igniter performance is improved, the remain after self-destruction is ensured to be compliant, and the data is traceable.

The utility model relates to an initiating explosive material detection device, in particular to a liquid initiating explosive material state detection device which comprises a working platform, a horizontal sliding assembly used for driving a longitudinal mounting plate to slide back and forth in the horizontal direction is detachably installed at the top end of the working platform, and a mounting platform capable of sliding back and forth in the longitudinal direction is installed on one side of the longitudinal mounting plate. A stirring assembly used for stirring the medicine bowls is installed on the end face of the installation platform and comprises a rotating shaft, a torsion sensor is detachably installed at the top end of the rotating shaft, and a solvent adding assembly is installed on one side of the stirring assembly. The resistance of the rotating shaft is detected through the torsion sensor, the viscosity of a medicament is detected in real time in the stirring process, when the viscosity is too high, the viscosity of a liquid medicine can be automatically diluted through the solvent adding assembly, the situation that the liquid medicine in a medicine bowl is manually detected is avoided, the detection precision is improved, and the detection efficiency is improved. The tedious operation steps are reduced, the task load of workers is reduced, and meanwhile the product quality is guaranteed.

The invention discloses a two-stage separation type projectile support for sub-caliber launching of an unstable projectile body. The two-stage separation type projectile support comprises an outer projectile support body, a projectile tail structure, an inner projectile support body and the projectile body. The missile tail structure is driven to decelerate by using the backward opening resistance of the clamping petals, and the missile tail structure is separated from a flying missile body, so that the problem that the missile tail structure with larger mass cannot be separated can be solved; the inner sabot slides backwards along the axis of the projectile body under the action of air resistance in the flying process, so that the flying stability of a combination formed by the inner sabot and the projectile body is improved, target collision at a small attitude angle at a long distance can be achieved, and meanwhile, due to the fact that the flying distance is prolonged, the projectile tail structure and the projectile body are separated more thoroughly; through the arrangement of the resistance table, the inner projectile support can be separated from the projectile body before collision and can also impact the target body together with the projectile body; due to the fact that the inner projectile support can slide in the axial direction of the projectile body and is small in mass, the penetration influence of the inner projectile support on the projectile body can be ignored.

The invention discloses a high-low temperature high-frequency angular vibration device based on a hydrostatic shaft system, which comprises a high-frequency angular vibration table, a high-low temperature box and a control system, and is characterized in that the high-frequency angular vibration table comprises a base, a hydrostatic bearing, a torque motor, an adapter, an encoder, a conductive slip ring, a thermal insulation shaft and a workbench; the base is located at the bottom, the torque motor stator is fixedly connected with the base and located in the base, the torque motor rotor is connected with the internal motor shaft, the hydrostatic bearing is located on the outer circumference of the base, and the top of the motor shaft is fixedly connected with the hydrostatic bearing through the adapter. An encoder is arranged at the bottom shaft end of the motor shaft; the conductive slip ring is mounted on the encoder; the top of the adapter is connected with a workbench located in the high-low temperature box through a thermal insulation shaft. The control system controls the temperature of the high-low temperature box and the angular frequency, the angular rate and the angular position of the high-frequency angular vibration table. According to the invention, high-frequency angular vibration can be realized in high and low temperature environments.

The invention discloses a calculation method for reversely deducing an initial speed based on mass and position information of a fragment behind a target. The method comprises the following steps: firstly, manufacturing an after-target fragment recovery device, carrying out armor piercing test, and collecting and recording the material, quality and position information of each after-target fragment; then, typical fragments behind the target are selected, a trajectory test is conducted on the fragment recovery device, and the speed attenuation rule of the fragments behind the target when the fragments penetrate through the fragment recovery device is obtained; and finally, reversely deducing the initial speed of the fragment after target based on the obtained fragment speed attenuation rule. According to the method, the problems of stacking of the fragments behind the target, fuzzy boundary and the like during X-ray shooting are effectively solved, the initial speed of each fragment behind the target can be obtained, and data support can be provided for damage ability evaluation of secondary killing behind the target.

The invention provides a power measurement and control system and method for a liquid carrier rocket, and relates to the field. Comprising a to-be-tested real equipment system used for completing a rocket body test; the simulator is used for installing a simulation equipment system, and simulation equipment in the simulation equipment system is in one-to-one correspondence with real equipment in the real equipment system; the control machine is in communication connection with the real equipment system and / or the simulator and is used for issuing a target instruction to the real equipment system and / or the simulator in the rocket body testing process; the front-end machine is in communication connection with the control machine and the simulator and is used for forwarding first feedback information after the simulator executes the target instruction to generate the first feedback information; the monitoring machine is in communication connection with the front-end machine, the real equipment system and the simulator and is used for receiving first feedback information and / or second feedback information in the rocket body testing process and monitoring the first feedback information and / or the second feedback information; the second feedback information is feedback information generated after the real equipment system executes the target instruction.

The invention relates to the technical field of projectile trajectory detection, in particular to a trajectory detection and calculation method for a high-speed flying projectile, and the method comprises the steps: arranging a plurality of binocular vision collectors, a pressure sensor array and a plurality of high-speed cameras at two sides of a flight path of the projectile; three-dimensional point cloud data, shock wave pressure pulsation signals and moving track images of the projectile are collected respectively. Collected data are subjected to filtering, registration, mesh generation, splicing, deblurring and the like and then are aligned and fused according to timestamps, more accurate position and speed information is obtained through a weighted average method, then trajectory points of projectiles are calculated, and noise is eliminated through a smoothing algorithm. Finally, the method can generate the complete space trajectory of the projectile in the flight process, and the analysis result is displayed in a visual mode. According to the technical scheme, through multi-sensor data fusion, the precision and stability of projectile trajectory detection are improved, and the problem that in the prior art, trajectory calculation is low in accuracy is effectively solved.

The invention discloses an attitude estimation method of a rotating projectile correction assembly based on maximum correlation entropy and strong tracking filtering. The method comprises the following steps: establishing a three-axis geomagnetic sensor and MEMS gyroscope combined attitude estimation system model; a rotating projectile attitude estimation algorithm based on square root cubature Kalman filtering is realized on the basis of the constructed system model; based on the maximum correlation entropy criterion of the Cauchy kernel function, correction of the measurement noise of the sensor is realized; based on a strong tracking filtering principle, correction of an innovation covariance matrix is realized; and calculating a rotating projectile correction assembly state vector. Compared with the prior art, the method can effectively reduce the influence of the rapid change of the motion state of the correction assembly in the flight process of the projectile and the external interference on the state estimation, and improves the attitude measurement precision of the rotary projectile correction assembly.

The invention relates to the technical field of data acquisition, in particular to an equipment target control data acquisition system and method, and the system comprises a state potential energy module, a speed projection module, a trajectory fusion module, a collaborative preloading module and an acquisition trigger module. According to the method, a potential function sequence is constructed by obtaining an angular velocity change rate and angular momentum, a characteristic stable section is determined by comparing an identification change point with a fall-back point, attitude stability description is improved, characteristic capture under interference is carried out, an included angle rate is calculated by using inertial navigation velocity projection filtering, and a motion mode analysis section and a data quality focusing key interval are determined by comparing. A multi-node early warning section is determined by fusing radar coordinate trajectory recognition composite section and analysis section time overlapping, early warning accuracy is enhanced by combining internal and external information, a unified scheduling instruction is generated to cooperate with preloading to improve timeliness, a sensor is activated according to the instruction to record and store, accurate and loss-free cooperative acquisition in a key period is guaranteed, and data integrity is improved.

The invention relates to the technical field of rocket power tests, and discloses a liquid oxygen supply system and a liquid oxygen supply method.The liquid oxygen supply system is characterized in that a liquid oxygen storage tank is provided with an extrusion gas inlet and a liquid oxygen inlet and outlet; the gas extrusion subsystem extrudes liquid oxygen in the liquid oxygen storage tank; the liquid oxygen filling subsystem is used for filling liquid oxygen into a liquid oxygen storage tank; the main regulating valve is connected with the liquid oxygen inlet and outlet; the input ends of the plurality of parallel branches are connected with the main regulating valve, and the output ends of the plurality of branches provide liquid oxygen for test pieces at different stations respectively; a branch regulating valve is arranged on each branch; the flow and pressure of each branch are adjusted by adjusting the opening degree of the main adjusting valve and adjusting the opening degree of the branch adjusting valves. The flow of each branch is adjusted by adjusting the opening degree of the adjusting valve of each branch, so that the resistance of each branch is as close as possible, and the high-precision control of the flow and pressure of test pieces at different stations is achieved; and multi-path equal-pressure equal-flow liquid oxygen distribution is realized. And the main regulating valve is combined to regulate the total flow.

The two-dimensional trajectory correction fuze device comprises a wave-transparent cover, a base, a control cabin, a rotary cross-shaped rudder and a battery cabin which are sequentially arranged in the direction from a bullet head to a bullet tail, an electric steering engine is arranged in the rotary cross-shaped rudder, and a radar module is arranged between the base and the wave-transparent cover; a flight control board, a trajectory resolving board and an attitude measurement module are arranged in the control cabin, a navigation module is embedded in the outer wall of the control cabin, a control module is loaded in the flight control board, the navigation module is used for detecting coordinate parameters and speed parameters, the radar module is used for measuring the distance between a warhead and the ground surface, and the attitude measurement module is used for detecting attitude parameters. The trajectory resolving board is used for recognizing aerodynamic parameters, and the control module is used for generating a steering engine control instruction and controlling the electric steering engine to adjust the aerodynamic force vector of the rotary cross rudder according to the steering engine control instruction to conduct trajectory correction. The two-dimensional trajectory correction fuze device has the beneficial effects that the two-dimensional trajectory correction fuze device can be quickly launched, adapts to complex meteorological conditions, is compact in structure and can be interchanged with a standard fuze.

The invention relates to the technical field of rockets, in particular to a ducted power rocket which comprises a rocket shell, a carbon fiber main beam, carbon fiber landing legs, a ducted power assembly, a rudder sheet control assembly, a flight control system and a power supply assembly. Wherein the rocket shell is located in a space defined by the multiple carbon fiber main beams, the extending direction of each carbon fiber main beam is the same as that of the rocket shell, and the rocket shell is connected with each carbon fiber main beam through screws or buckles; the carbon fiber landing legs are connected to the carbon fiber main beams and the positions, close to the lower end, of the rocket shell. The power supply assembly, the flight control system, the duct power assembly and the rudder sheet control assembly are sequentially arranged in the rocket shell from top to bottom, the power supply assembly is electrically connected with the flight control system, the duct power assembly and the rudder sheet control assembly, and the flight control system is connected with the duct power assembly and the rudder sheet control assembly. The ducted power rocket is easy to assemble and produce, higher in safety, attractive in appearance and capable of flying in an autonomous hovering mode, and the control difficulty of the ducted power rocket is lowered.

The invention discloses a missile-borne integrated navigation method and a missile-borne integrated navigation device for adaptive switching and sequential updating. The method comprises the following steps: acquiring angular velocity data and specific force data of an IMU (Inertial Measurement Unit), and performing inertial navigation state prediction based on the angular velocity data and the specific force data to obtain a prediction error state vector and a prediction error covariance matrix at the current moment; based on the prediction error state vector and the prediction error covariance matrix, navigation mode adaptive discrimination is carried out, a navigation mode discrimination result at the current moment is obtained, and first measurement information is determined based on the discrimination result; performing sequential measurement updating based on the first measurement information to obtain a posterior error state vector and a posterior error covariance matrix at the current moment; and performing error compensation correction based on the posterior error state vector and the posterior error covariance matrix to obtain navigation information. According to the invention, the technical problems of navigation interruption of a high-dynamic missile-borne platform in a GPS denial environment and large calculated amount and poor robustness of traditional fusion filtering are solved.

The invention discloses a high-speed cross-medium projectile body vertical water entry impact overload / load reduction response characteristic test device and method, belongs to the field of projectile body cross-medium high-speed flight impact tests, and aims to solve the problem of how to give consideration to reduction of impact load borne by a projectile body during cross-medium motion and reduction of self weight. The device comprises an underwater shock wave emitter, a projectile body, a test system and the like. The underwater shock wave generator is composed of a light-gas gun launching tube, a sabot flying plate, a piston, a dynamic pressure sensor and the like. The projectile body is divided into a buffer cap and a non-buffer cap; the test system is composed of a dynamic strain gauge, an axial acceleration sensor, a radial acceleration sensor, a three-dimensional DIC system and the like. According to the invention, different impact wave intensities in water are used for simulating conditions of vertical entry into water at different speeds, impact waves directly act on the front end face of the projectile body to realize impact loading on the projectile body, and the test system is used for realizing research on impact overload / load reduction response characteristics of the projectile body.

The invention discloses an amphibious step chariot muzzle attitude measurement method and device based on process noise adaptive filtering, and the method specifically comprises the steps: determining the installation positions of an optical fiber inertial navigation device, an MEMS inertial navigation device and a photoelectric encoder according to an amphibious step chariot body; according to roll, pitch and course angle information, provided by optical fiber inertial navigation, of a gun and pitch angle and course angle information, provided by a photoelectric encoder, of a barrel of the gun, attitude information of virtual optical fiber inertial navigation is obtained through calculation; carrying out calculation by utilizing MEMS inertial navigation to obtain self attitude information; measuring the difference between the attitude information of the MEMS inertial navigation and the attitude information of the virtual optical fiber inertial navigation; a dynamic lever arm correction method and a flexural deflection noise correction method are adopted, and Sage-Husa process noise self-adaptive Kalman filtering is combined to estimate muzzle attitude information. The system has the capacity of self-adaption to amphibious environments, has the advantages of being convenient to install, stable in performance, high in measurement precision and high in real-time performance, and can effectively cope with complex and dynamic battlefield environments.

The invention relates to a projectile body penetration icebreaking test device which comprises a rack, a projectile body launching assembly, a positioning clamp, a protection assembly and an image shooting assembly, the rack is provided with a horizontal test surface used for placing a sample, and an opening located below the sample is formed in the horizontal test surface; the bottom of the projectile body launching assembly is a launching end pointing to the horizontal testing face, the projectile body launching assembly is rotationally connected with the rack in the vertical horizontal plane, the positioning clamp is installed on the horizontal testing face of the rack and provided with a positioning end, and the protection assembly is arranged below the horizontal testing face and fixedly connected with the rack. The image shooting assembly is mounted on the rack and is provided with an image acquisition end; the sample can be fixed on the horizontal test surface of the rack through the positioning clamp, the inclination angle of the launching end of the sample can be adjusted by rotating the projectile launching assembly, and the image information of the sample is acquired through the image shooting assembly, so that the impact damage of the projectile to the sample at different penetration angles is researched.

The invention relates to a rocket sled aerodynamic characteristic evaluation method based on a meteorological environment multi-factor coupling effect, and solves the problem of deviation between a simulation evaluation result and an actual test result due to the fact that factors are not effectively combined in an existing evaluation technology. The method comprises the following steps: step 1, acquiring multi-dimensional meteorological data; 2, adjusting the air density; step 3, adjusting a viscosity coefficient; 4, determining the mass fraction of water vapor in the air; and 5, establishing a wet air material. 6, the relative running speed of the rocket sled and the air is determined; 7, solving the steady state of the aerodynamic characteristics of the whole trajectory of the rocket sled; and 8, verifying and correcting the model. The method has the advantages that the aerodynamic characteristics of the rocket sled can be accurately reproduced; two factors, namely air density and dynamic viscosity coefficient, which have great influence on the aerodynamic characteristics of the rocket sled are comprehensively considered; a wet air material model is established, and compared with a previous dry air model, the evaluation precision is higher.

The application discloses an embedded over-the-horizon anti-armor simulation terminal, which comprises a visual display and control device, a direction-finding and angle-measuring device, a laser receiving device and an effect simulation device.The visual display and control device is used for simulating a video of a camera on a shell to realize flight control of the simulated shell; the direction-finding and angle-measuring device is used for obtaining the position, orientation and inclination angle of the shell; the laser receiving device is used for receiving laser information to simulate the situation that the equipment is hit; the effect simulation device is used for generating sound, light and smoke effects when the terminal is launched or damaged; the main control machine is used for data interaction with the visual display and control device, the direction-finding and angle-measuring device, a data acquisition terminal, the laser receiving device and the effect simulation device, and provides a positioning function; the data acquisition terminal is used for data interaction with the main control machine, collecting data of striking events, hitting events, position states, damage states and remaining shell quantity of the embedded over-the-horizon anti-armor simulation terminal, and realizing display, storage and query of the data.The application realizes simulation of over-the-horizon striking operation and data acquisition in a field environment.

The present application relates to trajectory analysis technical field, specifically to a kind of ballistic sighting trajectory analysis method, comprising the following steps, obtain wind speed time-varying data and centroid parameter, calculate wind disturbance stress and screen maximum value, determine the trend of rotation direction, execute pitch angle consistency judgment, calculate angle adjustment rate and generate boundary parameter, analyze target speed trend and determine delay, calculate deviation trend difference, extract wind disturbance mutation mark high sensitive section, judge offset and high sensitive section overlap, generate dynamic correction instruction group, in the present application, wind speed time-varying data is refined to different structural section of projectile body, and wind disturbance stress intensity is calculated by combining respective surface stress, target delay trend is modeled and analyzed by combining direction angle and modulus difference change in target speed trend sequence, trajectory correction amount mapping relationship is constructed by combining flight parameter and time stamp, and the adjustability and strike accuracy of overall hit path are effectively improved.