CN111623665A - Missile launching forward-impact recoil test system and method - Google Patents
Missile launching forward-impact recoil test system and method Download PDFInfo
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- CN111623665A CN111623665A CN202010247259.1A CN202010247259A CN111623665A CN 111623665 A CN111623665 A CN 111623665A CN 202010247259 A CN202010247259 A CN 202010247259A CN 111623665 A CN111623665 A CN 111623665A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A31/00—Testing arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A23/00—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles
- F41A23/02—Mountings without wheels
- F41A23/16—Testing mounts
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Abstract
A missile launching forward-impact recoil test system belongs to the technical field of tactical missile tests and comprises a bracket, a guide rail arranged on the bracket, a sliding block arranged on the guide rail in a sliding manner, a hoop-shaped connecting frame connected with the sliding block and a pulling pressure sensor; the connecting frame is used for fixing the missile launching canister; one end of the pull pressure sensor is connected with the support, and the other end of the pull pressure sensor is connected with the connecting frame and used for measuring the forward-thrust recoil force of missile launching. The missile launching recoil test system is simple in structure, convenient to operate, high in accuracy and low in cost.
Description
Technical Field
The invention relates to a missile launching forward-stroke recoil test system and method, in particular to a simple low-cost shoulder-carried missile launching forward-stroke recoil test system and method, and belongs to the technical field of tactical missile testing.
Background
In modern war, the performance of weapon affects the result of war to a certain extent, the result of testing dynamic parameters of weapon is the important index for testing the performance of weapon, especially for individual shoulder-carried missile, the generated recoil and recoil impulse is one of the important indexes to be tested. During the launching process of the shoulder-carried missile, if the forward-thrust and backward-sitting momentum is large, the guide cylinder can deviate from the initial aiming position during ejection, and even threaten the personal safety of a shooter, so that the forward-thrust and backward-sitting momentum of the individual shoulder-carried missile during launching is reduced, and the method has important significance. At present, the acquisition of the forward-stroke and backward-sitting movement parameters of a weapon system in China mainly adopts the following three ways:
(1) modeling simulation solution. A mathematical model is established through the local analysis of the whole weapon system and all components, the required parameter size is obtained through the solution of a model equation set, and the solution process is generally realized through corresponding simulation software. The method needs to establish an equation, the steps are complicated and long, and the accuracy of the solution result is uncertain.
(2) And (5) building a test system for testing a target range. And (3) aiming at the content to be analyzed and the acquired parameters, a test scheme is formulated, a test system hardware platform is established, corresponding test software is compiled, and an actual numerical value is measured in the test process. The hardware testing platform related to the method is high in cost and long in time consumption period, and the application of the testing system is limited.
(3) Theoretical analysis was combined with testing. The method has the advantages that data obtained by theoretical analysis can be compared with data obtained by experimental test and mutually checked, which plays an important role in correcting the established mathematical model and perfecting the test scheme; it also combines the disadvantages and disadvantages of the first two approaches.
In addition, most of current military scientific research institutions carry out recoil test research on firearms, frame-mounted weapons and the like, and the research literature on launching impact force test of small tactical missiles, shoulder-carried missiles and the like is few, so that the establishment of a set of simple and low-cost test system has important significance.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: aiming at the problems that the cost for testing the transient impact force needs to be high in the current market and the forward-thrust and backward-thrust impulse generated in the process of launching the shoulder-carried missile is rarely researched, the defects in the prior art are overcome, and the system and the method for testing the forward-thrust and backward-thrust impulse are provided.
The purpose of the invention is realized by the following technical scheme:
a missile launching recoil test system comprises a bracket, a guide rail arranged on the bracket, a sliding block arranged on the guide rail in a sliding manner, a hoop-shaped connecting frame connected with the sliding block and a pulling pressure sensor; the connecting frame is used for fixing the missile launching canister; one end of the pull pressure sensor is connected with the support, and the other end of the pull pressure sensor is connected with the connecting frame and used for measuring the forward-thrust recoil force of missile launching.
The missile launching recoil test system preferably further comprises an amplifier, a data acquisition card and an upper computer;
the amplifier is used for amplifying the measurement data of the tension and pressure sensor, the data acquisition card is used for acquiring the amplified measurement data, and the upper computer is used for processing the acquired measurement data.
The missile launching forward-impact recoil test system preferably further comprises a calibration component, wherein the calibration component comprises a vertical rod, a calibration object and at least one calibration pull pressure sensor; the calibration pull pressure sensor is arranged at the front end or the rear end of the missile launching barrel; the calibration object passes through the thin rope and the top end of the vertical rod, and is used for making circular motion and impacting the calibration pull pressure sensor; the position of the vertical rod and the length of the thin rope are adjusted, so that the motion direction of the calibration object is coincided with the axial direction of the missile launching tube when the calibration object impacts the front end or the rear end of the missile launching tube.
Preferably, the missile launching recoil test system determines a calibration coefficient by comparing data of the pull pressure sensor and data of the calibration pull pressure sensor, and the calibration coefficient is used for measuring the recoil force launched by the missile.
In the missile launching recoil test system, preferably, the number of the pull pressure sensors is two, and the number of the hoop-shaped connecting frames is two; guide rails are arranged on two sides of the bracket, two sliding blocks capable of sliding are arranged on each guide rail, and the sliding blocks opposite to the two sides are connected with a connecting frame; and for each pulling and pressing force sensor, one end of the pulling and pressing force sensor is fixedly connected with the bracket, and the other end of the pulling and pressing force sensor is fixedly connected with one connecting frame.
According to the missile launching forward-impact recoil testing system, preferably, the center of mass of the missile barrel is located between the two connecting frames.
Preferably, in the missile launching recoil test system, the sum of the measurement data of the two pull pressure sensors is used as the recoil force of missile launching.
In the missile launching forward-impact recoil testing system, the guide rail is preferably a rolling guide rail pair.
Preferably, the missile launching forward-impact recoil test system adopts an S-shaped pull pressure sensor, and the single measuring range is not less than 100 Kg.
A missile launching forward-stroke recoil test method adopts the missile launching forward-stroke recoil test system and comprises the following steps:
s1, calibrating a pull pressure sensor of the test system by using a calibration component, and determining a calibration coefficient;
s2, fixing the missile launcher on the connecting frame, and clearing data of the tension pressure sensor;
s3, after the guided missile in the guided missile launching barrel is ignited, obtaining the measurement data of the pulling pressure sensor;
and S4, determining the actual forward-thrust and backward-thrust impulse value generated when the missile is launched by using the measurement data and the calibration coefficient of the tension-pressure sensor.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention has simple structure and lower cost; the cost for measuring the transient impact force in the current market is higher, according to preliminary investigation, the price of the whole set of test (including contents of software, hardware systems, data analysis and the like) is about more than 3 ten thousand yuan, aiming at the shoulder-carried missile launching, the invention is successfully verified in the flight test, the cost of the whole set of system is only 0.5 ten thousand yuan, and the invention has good economy; the system structure is simple, modular design is realized, and the replacement is convenient;
(2) at present, methods such as 'equivalent to the sensible recoil of a certain weapon' or 'the maximum recoil is not greater than a certain value' are generally adopted in the industry to evaluate the sensible action of the weapon, but the mere discussion of the magnitude of the impact force value is meaningless, the accumulation of the force in time is ignored, and the emission energy or impulse is considered; the invention researches and converts the force and the impulse, successfully obtains the impulse generated in the launching process and plays a certain guiding role for the shooter to launch.
Drawings
FIG. 1 is a block diagram of a test system provided by the present invention;
FIG. 2 is a schematic structural diagram of a testing apparatus according to the present invention;
FIG. 3 is a schematic view of the sensor mounting provided by the present invention;
FIG. 4 is a block diagram of a software system architecture provided by the present invention;
FIG. 5 is a diagram of a test software interface provided by the present invention;
FIG. 6 is a schematic diagram of a calibrated squat of a sensor provided in accordance with the present invention;
FIG. 7 is a schematic diagram of sensor calibration lead-in provided by the present invention;
fig. 8 is a schematic diagram of the integration method provided by the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.
A missile launching recoil test system comprises a bracket, a guide rail arranged on the bracket, a sliding block arranged on the guide rail in a sliding manner, a hoop-shaped connecting frame connected with the sliding block, a tension pressure sensor, an amplifier, a data acquisition card, an upper computer and a calibration assembly; the connecting frame is used for fixing the missile launching canister; one end of the pull pressure sensor is connected with the support, and the other end of the pull pressure sensor is connected with the connecting frame and used for measuring the forward-thrust recoil force of missile launching.
The amplifier is used for amplifying the measurement data of the tension and pressure sensor, the data acquisition card is used for acquiring the amplified measurement data, and the upper computer is used for processing the acquired measurement data.
The calibration component comprises a vertical rod, a calibration object and at least one calibration pull pressure sensor; the calibration pull pressure sensor is arranged at the front end or the rear end of the missile launching barrel; the calibration object passes through the thin rope and the top end of the vertical rod, and is used for making circular motion and impacting the calibration pull pressure sensor; the position of the vertical rod and the length of the thin rope are adjusted, so that the motion direction of the calibration object is coincided with the axial direction of the missile launching tube when the calibration object impacts the front end or the rear end of the missile launching tube. And determining a calibration coefficient by comparing the data of the pull pressure sensor and the calibration pull pressure sensor, wherein the calibration coefficient is used for measuring the recoil of missile launching.
The number of the tension and pressure sensors is two, and the number of the hoop-type connecting frames is two; guide rails are arranged on two sides of the bracket, two sliding blocks capable of sliding are arranged on each guide rail, and the sliding blocks opposite to the two sides are connected with a connecting frame; and for each pulling and pressing force sensor, one end of the pulling and pressing force sensor is fixedly connected with the bracket, and the other end of the pulling and pressing force sensor is fixedly connected with one connecting frame. The center of mass of the missile barrel is positioned between the two connecting frames. And summing the measurement data of the two pull pressure sensors to obtain the recoil force of missile launching. The pull pressure sensor adopts an S-shaped pull pressure sensor, and the single measuring range is not less than 100 Kg.
A missile launching recoil test method adopts the test system and comprises the following steps:
s1, calibrating a pull pressure sensor of the test system by using a calibration component, and determining a calibration coefficient;
s2, fixing the missile launcher on the connecting frame, and clearing data of the tension pressure sensor;
s3, after the guided missile in the guided missile launching barrel is ignited, obtaining the measurement data of the pulling pressure sensor;
and S4, determining the actual forward-thrust and backward-thrust impulse value generated when the missile is launched by using the measurement data and the calibration coefficient of the tension-pressure sensor.
Example (b):
a missile launching recoil test system is shown in figure 1 and comprises a hardware part and a software part, and comprises a test device, a signal conditioning module (amplifier), a porphyrizing PCI-1713 data acquisition card, a power supply, a test notebook, test software and a calibration component.
The test apparatus is shown in fig. 2. Adopt the S type of 2 journey 100Kg to draw pressure sensor, the symmetry is installed on the support, the guide rail adopts rolling guide pair, clamp type link is installed on the slider and can be along with the slider nimble motion on the guide rail, the launch canister is installed on the link, the support has higher rigidity (adopts aluminum alloy material), avoid having great loss among the energy transfer process, the sensor mounting means is as shown in figure 3, draw pressure sensor' S one end to pass through the fix with screw on the support, the other end passes through screw and nut and is connected with the link, consequently the atress on the link can be passed through the screw transmission and is given the sensor.
The software part comprises functions of data acquisition, processing, saving, file management, history playback and the like, and is shown in fig. 4.
a) The data collection program was developed using LabVIEW, the interface of which is shown in figure 5 below. The acquisition card is a data acquisition card of the Hua corporation, and the acquisition module is developed by adopting a driving program provided by the Hua corporation. And the output of the two paths of sensor signals is displayed in the acquisition interface, and the two paths of signals are fitted into a curve of the recoil force of the missile. Because the pull pressure sensor feeds back an analog voltage signal, the data acquisition program is set as an analog voltage input. The board card parameter design is designed according to the selected acquisition card. The sampling rate is set according to the actual requirements of the test.
b) Data processing
The external signal interferes with the acquired analog voltage signal, so that the system needs to write a data processing program. The data processing program processes data by removing singular items and the like, and adopts a software processing mode.
c) Data preservation
The system not only needs to visually display the curve of the recoil and recoil force, but also stores the data into an Excel table.
d) File management
The system can operate on the Excel table through file management.
The calibration component comprises A, B, C three same tension and compression sensors, a vertical rod and an iron block and is used for calibrating the tension and compression sensors, and the calibration method comprises the following steps:
the purpose of calibration in the early stage of the test is to verify that the S-shaped pull pressure sensor can accurately and truly acquire data and ensure that the data acquired by the sensor can truly reflect the forward-thrust and backward-thrust impulse generated by the launching tube in the launching process of the missile. The calibration method is characterized in that a known momentum is input, compared with data acquired by a sensor, and a plurality of groups of tests are carried out to obtain a calibration coefficient K. The calibration schematic diagram is shown in fig. 6 and 7, and the two working conditions of forward stroke and recoil can be calibrated.
The method comprises the steps of tying a string on a vertical rod, tying an iron block with the mass of 0.984Kg at the other end of the string, releasing the iron block from the height h, enabling the iron block to move circularly and impact a sensor B, adjusting the position of the vertical rod, enabling the moving direction to be overlapped with the axial direction of a launching tube when the iron block impacts, enabling the sensor B to output a force-time curve and A, C the sensor to output the force-time curve, obtaining integral values of F (A) x t, F (B) x t and F (C) x t, judging whether F (B) x t is F (A) x t + F (C) x t (a known actual momentum value) or not, and obtaining a coefficient K (known actual momentum)/{ F (A) t + F (C) t } if the integral values are not equal. And respectively carrying out a plurality of groups of tests by adopting different heights h and different masses m to obtain a series of standard kinetic values and corresponding sensor curves, and comparing the standard kinetic values and the corresponding sensor curves to obtain a calibration coefficient K. Therefore, in the actual launching process of the missile, under the model, the integral sum of the A, C sensors is calculated by using the coefficient K, and the actual recoil and recoil impulse value generated in the launching process can be obtained.
A missile launching recoil test method adopts the test system and comprises the following steps:
a) the method comprises the following steps of placing a cartridge missile on a launching bracket, fixing the launching cartridge through a connecting bracket, and enabling the mass center of the cartridge missile to be located between the two connecting brackets;
b) in an initial state, the nut at the joint of the sensor is fully screwed down to eliminate a threaded connection gap, the A, C sensor is subjected to synchronous equivalent change when stressed through observation of an upper computer, and then peeling and zero clearing are carried out;
c) after the engine is ignited, the launching tube is subjected to acting force and is transmitted to the sensor through the bolt, and the sensor records data;
d) the upper computer reads and stores data to form a force-time curve F (F) (t), sums the A, C sensor data and calculates an integral value; the actual recoil impulse value generated during the launching can be obtained.
e) The data integration method comprises the following steps: and (3) selecting time points t1 and t2, considering (t2-t1) as collision time, summing F values corresponding to all points between the time points and the collision time, multiplying the F values by delta t, and approximately calculating an integral value, wherein an integral diagram is shown in FIG. 8.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A missile launching recoil test system is characterized by comprising a bracket, a guide rail arranged on the bracket, a sliding block arranged on the guide rail in a sliding manner, a hoop-shaped connecting frame connected with the sliding block, and a pull pressure sensor; the connecting frame is used for fixing the missile launching canister; one end of the pull pressure sensor is connected with the support, and the other end of the pull pressure sensor is connected with the connecting frame and used for measuring the forward-thrust recoil force of missile launching.
2. The missile launch recoil test system of claim 1, further comprising an amplifier, a data acquisition card, and an upper computer;
the amplifier is used for amplifying the measurement data of the tension and pressure sensor, the data acquisition card is used for acquiring the amplified measurement data, and the upper computer is used for processing the acquired measurement data.
3. The missile launch recoil test system of claim 1, further comprising a calibration assembly comprising a vertical rod, a calibration object, at least one calibration pull pressure sensor; the calibration pull pressure sensor is arranged at the front end or the rear end of the missile launching barrel; the calibration object passes through the thin rope and the top end of the vertical rod, and is used for making circular motion and impacting the calibration pull pressure sensor; the position of the vertical rod and the length of the thin rope are adjusted, so that the motion direction of the calibration object is coincided with the axial direction of the missile launching tube when the calibration object impacts the front end or the rear end of the missile launching tube.
4. The missile launch recoil test system of claim 3, wherein the calibration factor is determined by comparing data from the pull pressure sensor and the calibration pull pressure sensor for measuring the recoil of the missile launch.
5. The missile launch recoil test system of claim 1, wherein there are two of the pull pressure sensors and two of the bail type mounts; guide rails are arranged on two sides of the bracket, two sliding blocks capable of sliding are arranged on each guide rail, and the sliding blocks opposite to the two sides are connected with a connecting frame; and for each pulling and pressing force sensor, one end of the pulling and pressing force sensor is fixedly connected with the bracket, and the other end of the pulling and pressing force sensor is fixedly connected with one connecting frame.
6. The missile launch recoil test system of claim 5, wherein the missile barrel has a center of mass located between the two connection brackets.
7. The missile launch recoil test system of claim 5, wherein the measurement data of the two pull pressure sensors are summed to form the missile launch recoil force.
8. A missile launch recoil test system according to any one of claims 1 to 5, wherein the guide rail is a rolling guide rail pair.
9. The missile launching recoil test system of any one of claims 1 to 5, wherein the pull pressure sensor is an S-shaped pull pressure sensor, and the single measuring range is not less than 100 Kg.
10. A missile launching recoil test method, characterized in that the test system of claim 3 is adopted, and the method comprises the following steps:
s1, calibrating a pull pressure sensor of the test system by using a calibration component, and determining a calibration coefficient;
s2, fixing the missile launcher on the connecting frame, and clearing data of the tension pressure sensor;
s3, after the guided missile in the guided missile launching barrel is ignited, obtaining the measurement data of the pulling pressure sensor;
and S4, determining the actual forward-thrust and backward-thrust impulse value generated when the missile is launched by using the measurement data and the calibration coefficient of the tension-pressure sensor.
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Application publication date: 20200904 |