CN216482564U - Composite projectile for determining projectile system concentration and jump angle accuracy - Google Patents

Composite projectile for determining projectile system concentration and jump angle accuracy Download PDF

Info

Publication number
CN216482564U
CN216482564U CN202120305824.5U CN202120305824U CN216482564U CN 216482564 U CN216482564 U CN 216482564U CN 202120305824 U CN202120305824 U CN 202120305824U CN 216482564 U CN216482564 U CN 216482564U
Authority
CN
China
Prior art keywords
projectile
component
standard
mass
catapult
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN202120305824.5U
Other languages
Chinese (zh)
Inventor
赵成吉
赵海旭
贾凤云
赵海虹
赵馥琳
杨斯涵
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shenyang Hongxiang Composite Elastic Technology Co ltd
Original Assignee
Shenyang Hongxiang Composite Elastic Technology Co ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Shenyang Hongxiang Composite Elastic Technology Co ltd filed Critical Shenyang Hongxiang Composite Elastic Technology Co ltd
Priority to CN202120305824.5U priority Critical patent/CN216482564U/en
Application granted granted Critical
Publication of CN216482564U publication Critical patent/CN216482564U/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Landscapes

  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

The composite projectile for determining the density and jump angle precision of the projectile system consists of a component I (1) and a component II (2), wherein the component I (1) is a homogeneous spherical body with the diameter identical to that of a standard projectile device and is of a solid or hollow structure; the mass center and the geometric center of the component I (1) are coincident and are at the sphere center; when the component I (1) moves in a medium, an included angle between the geometric axis of the component I (1) and the velocity vector line thereof is zero, and the motion track of the component I (1) can be described by a particle motion differential equation with three degrees of freedom; the second component (2) is a revolving body structural member with the cross section consistent with the caliber of the standard catapult; the mass of the composite projectile is the same as or similar to that of the standard projectile; the number of the first assemblies (1) is at least one. The utility model can determine the density of the standard projectile and the standard catapult and greatly improve the shooting precision of the shooter. The method has pioneering significance in the related technical field and the extended engineering application field.

Description

Composite projectile for determining projectile system concentration and jump angle accuracy
Technical Field
The utility model relates to the technical field of external ballistic test design and application of standard ejectors and novel composite ejectors, and particularly provides a composite ejector for determining the density and jump angle precision of an ejection system.
Background
The outer projectile technology is the science for researching the movement rule of standard projectile (projectile) in air flight and the problems related to the movement. The outer ballistic theory plays an important role in designing standard projectiles (artillery) and ammunition, and is the theoretical basis for guaranteeing weapon precision and compiling a shooting table. In 1954, the Zhangzhi professor of the military engineering institute of the national people liberation army translated the "foreign ballistics" of the professor of the Soviet-Union Techai, in 1956, the Pufa instructor of the military engineering institute of the national people liberation army published the first foreign ballistics work of China "foreign ballistics", and in 1960, the first foreign ballistic specialty of China was launched. Since then, many external ballistic writings are published in China, and 59 external ballistic writings are listed only on pages 632-634 of the bibliography of the present patent document list [ reference 5 ].
The information of each document which is mainly cited in the technical field of the utility model is listed as follows:
document 1 states Lebin's main edition, artillery general theory, Beijing university of science and engineering publishing agency, 2014.2, (modern weapons fire systems book) national published fund projects and ' twelve-five ' national key publication planning projects, ISBN 978-7-5640-8771-5.
[ article 2] Yi Jian Ping, compiled by the Wangzhong army, Tanjian, Beijing university of science and engineering Press, 2014.2 (modern weapons fire systems Cluster) national published fund project and 'twelve-five' national key publication program, ISBN 978-7-5640-.
[ document 3] Wangzhan, Hewei Dong, Xufuming editions, artillery propellant charge design principle and technology, Beijing university of science and engineering publisher, 2014.2 (modern weapons fire systems suite), national published fund project, and 'twelve-five' national key publication planning project, ISBN 978-7-5640-.
[ article 4] Main edition of the Chin forest, Canon warfare, Beijing, university of Beijing university of science and engineering, Press 2016.6, "twelve five" general advanced education the national level planning textbook ISBN 978-7-5682-.
[ document 5] Korea et al, March and warhead Elepiboly, Beijing university of science and engineering Press, 2014.2 (modern weapons fire systems series) national published fund project and 'twelve-five' national key publication project ISBN 978-7-5640-.
[ document 6] Zhao Chengji, experimental analysis about problems with the conventional jump angle measuring method, war institute, and technology, 1985.04.
[ document 7] edition work Committee for military training teaching materials of general Assembly of the people's liberation army in China, a firing test edition technology, Beijing, national defense industry Press, 2002.1, national defense research engineering technology series teaching materials, a conventional weapon test system, ISBN 7-118-.
The standard projectile has the function of giving the standard projectile initial speed and the firing angle to shoot, and most of the standard projectiles launched by the modern standard projectile are long circular rigid bodies. Most projectiles are oblong rigid bodies, and when the projectiles move in the air, the geometric axes of the projectiles do not coincide with the velocity vector line. The included angle between the geometric axis of the long round rigid body projectile and the flight speed direction thereof is called attack angle for the tail projectile and nutation angle for the rotating projectile.
In order to ensure the flight stability of the oblong rigid body system projectile in the medium, the 3 rd paragraph of [ document 4] artillery ballistics P32 (P32 herein means page 32, hereinafter abbreviated in this format) indicates: the method for realizing the shot flight stability mainly comprises two methods of empennage stability and rotation stability. Document 5P 25-26 describes this further and illustrates the force pattern of the "two stabilization modes in fig. 2.1.1". To ensure stable flight of the projectile, two general methods are: the projectile is made to rotate at high speed like a spinning top, or a tail fin is installed to the projectile. And as indicated by the last natural paragraph of artillery warfare P32 of document 4: the projectile is generally called a projectile with good flight stability, wherein the projectile head is always forward in flight, and the included angle (nutation angle delta) between the axis of the projectile and the trajectory tangent line is always smaller than a certain limit value along the full trajectory. "
The standard catapult for ensuring the stable rotation flight of the projectile is a linear chamber standard catapult provided with a linear chamber barrel, and the standard catapult for realizing the stable flight of the empennage is a slide chamber standard catapult provided with a slide chamber barrel.
As is well known, the standard projectile structure ensures the flight stability of the standard projectile in a medium, and in order to increase the power of the standard projectile and increase the killing effect of the standard projectile, the modern standard projectile launches the long round standard projectile by using a linear chamber standard projectile or a slide chamber standard projectile. The standard projectile is required to be always forward at the head of the full trajectory without turning over. When the system projectile is subjected to external interference in flight, the system projectile can restore to an expected motion state after the interference is removed.
In physical terms, the necessary condition for ensuring the flying stability of the standard projectile is that the included angle between the direction of the projectile axis from the projectile tail to the projectile top and the central velocity vector of the standard projectile (namely, the tail wing type projectile is called as an attack angle delta, and the rotating type projectile is called as a nutation angle) must be changed within a small enough range even if the included angle cannot be zero.
However, the long round type projectile is necessarily overturned in the flying process, and in order to ensure the flying stability, the method for ensuring the stable flying of the type projectile is not divided into two methods at present: one method is to make the standard projectile rotate at high speed around the vertical axis of the standard projectile, and the other method is to install a tail wing on the standard projectile, or to use both the rotating method and the tail wing method on the same standard projectile to solve the stability problem.
Because the long round type projectile always has an attack angle delta during flying in the air, the pressure distribution of the air around the type projectile is changed, the pressure center P is between the ejection top and the mass center of the long round type projectile, and the resultant force R of the air acting on the long round type projectile generates unstable overturning moment M relative to the mass center. How to ensure that the attack angle delta of the long round type projectile changes in a small range all the time in the flying process is the main problem to be solved for the flying stability. However, the long round type projectile almost inevitably overturns in the flying process, and in order to ensure the flying stability, the method for stably flying the type projectile has the following two methods: one method is to make the standard projectile rotate around the vertical axis of the standard projectile at a high speed, and the other method is to install a tail wing on the standard projectile, or to use the rotating method and the tail wing method on the same standard projectile to solve the stability problem. The former is to rotate the standard projectile around the shaft at high speed, so that the projectile rotates rapidly like a gyroscope without toppling; the tail wing is additionally arranged at the tail part of the manufactured projectile to form stable moment resisting overturn.
At present, all standard projectiles thrown out of standard projectiles are oblong revolved bodies and are generally regarded as rigid bodies. The standard projectile motion track consists of two parts, namely the mass center motion of the standard projectile and the motion of the axis of the standard projectile around the mass center. Since there is an attack angle when the standard projectile makes rigid motion, the [ document 5] P153-154 gives a rigid motion equation set of 6 degrees of freedom for all forces and moments acting on the projectile, and the equation set gives the motion of the mass center of the standard projectile rigid body and the motion of the standard projectile axis around the mass center at the same time.
Document 1, section P42-43 of 5.4.3, states that under the basic assumption of an outer trajectory with zero angle of attack, the trajectory of the motion of the center of mass of the projectile will be a plane curve. It is uniquely determined by initial velocity, firing angle and ballistic coefficient. Document 1P 43 fig. 5 to 9 show a diagram of the relationship between the ballistic coefficient and the range when the initial velocity and the firing angle are determined. It is seen from the figure that the ballistic coefficient determines the distance of range. [ document 1] P44 paragraph 2 indicates that: the projectile does the centroidal motion and simultaneously does the circumcenter motion. FIGS. 5-10 show schematic views of spiral trajectory, bias flow and distribution; the 6.1 overview of P47 shows "schematic outline of barrel and shell after combined chamber of figure 6-1". This is analyzed and described in detail in chapters 6 to 13 of P138-342 of document 5.
If the geometric axis of the long round type projectile is consistent with the flying speed direction all the time in the flying process of the long round type projectile, namely the nutation angle (or the attack angle) is zero, the motion trail of the projectile mass center can be described by a projectile mass center motion differential equation with three degrees of freedom.
Under the basic assumption condition, the projectile can be simplified into a mass point, and the motion trail of the mass center of the projectile can be uniquely determined by a differential equation system of the motion of the mass center of the projectile. Document 4P 21-22 gives the differential equation of motion of the center of mass of the projectile starting from the 3 rd natural segment.
[ document 4]]P13 equation (1-43) relating air resistance acceleration aXSimplified as axCh (y) f (v) ch (y) vg (v). "air drag acceleration is expressed as the continuous product of a ballistic coefficient C representing the characteristics of the projectile, a density function h (y) representing the characteristics of the air, and a drag function f (v) representing the effect of the velocity of the projectile relative to the air on the motion. "[ document 4]]P12 formula (1-38) gives the expression C ═ id of the ballistic coefficient C2×103In which i is in [ document 4]]The equations (1-33) of P11 give the expression for the bullet index i: i ═ CX0(Ma1)/CX0N(Ma1) Const. From [ document 4]]The equations (1-34) show that the bullet shape factor is mainly related to the length of the head of the bullet, and the bullet shape factor is smaller when the head is longer, namely the air resistance is smaller. CX0N(Ma1) The resistance coefficient of a standard projectile with the length of the projectile head being 1.2-1.5 times of the length of the projectile diameter is called the Seattle air resistance law, and the resistance coefficient of a standard projectile with the length of the projectile head being 3-3.5 times of the projectile diameter is called the 43-year air resistance law.
[ document 5]]P39 fig. 2.3.3 shows "the law of resistance for year 43 and the law of resistance for ciya's cutting". It can further be seen from the figure that the shorter the projectile head, the greater the drag coefficient, and the difference is about one-fold. [ document 5]]Natural paragraph 2 of P35 gives a graph 2.2.13 of the coefficient of head resistance of the bluff body, as seen: the drag coefficient of the flat head is much greater than the drag coefficient of the hemispherical head. If a spherical bullet (i.e. assembly one 1 is used as the standard bullet, the drag coefficient of the standard bullet is CX0N(Ma1) Then the shape factor i of the spherical pellet is equal to 1, from which it can be deduced: the bullet shape coefficient i of the flat-head projectile is necessarily greater than 1.
[ document 5]]The 3 rd last natural segment of P389 indicates that the aerodynamic force acting on the rocket can be obtained by a wind tunnel blowing method, a numerical calculation method and an engineering calculation method, and can also be extracted from flight test data. "[ document 5]]The last paragraph of P389 goes to 15.5 of P391.1, end of the subsection, point out "extract rocket zero-lift drag coefficient from Radar speed measurement data CXOPrinciple of (1) ". The above two points are the theoretical basis of the method for extracting the resistance coefficient of the homogeneous sphere.
Other background information is described below:
1 for standard catapults and standard ammunition: there are two current ways to provide kinetic energy to the standard projectile: most of the propellant is launched by chemical charge; a small portion is fired with a non-chemical charge. The utility model mainly relates to a projectile launched by chemical charge, and the principle can also be used for non-chemical charge launching.
1.1 the structural characteristics of the body tube of the standard catapult: document 1P 3 first paragraph line 3 indicates that "artillery gun is generally composed of two major parts, a barrel and a gun carriage. The gun body consists of a barrel, a gun tail, a gun bolt and the like. The barrel is the main body of the gun body and is used for endowing the projectile with initial speed and flight direction; the breech is used for containing the breech; breech locks, fires projectiles and withdraws fired cartridges. "document 1" P36, page 2, natural paragraph indicates that "firing of artillery is generally to burn gunpowder in a tubular container (i.e. barrel) with one end closed, and the generated high-temperature and high-pressure gas expands to do work, pushing the object (i.e. projectile) to be thrown to accelerate toward the other end unclosed pipe orifice (i.e. muzzle), and obtaining the maximum throwing speed (i.e. initial speed) at the muzzle.
The prior art mainly comprises two types of catapult barrels: rifled, smoothbore. Document 1P 47 page 6.1 overview fig. 6-1 shows a standard line-chamber type projectile "schematic outline of barrel and shell after chamber". The schematic structure of the breech, breech block, projectile, barrel and muzzle brake is shown. Document 1P 348 section 18.1.4 fig. 18-5 show "connection of breech to barrel and seat plate" of a slide-bore gun.
[ document 1] P57 page 6.2.3 subsection 1, Nature notes: "generally refer to the barrel interior as the bore, the bore generally consists of the powder chamber, the slope chamber and the guide part"; the 2 nd paragraph indicates the chamber: … the common medicine chamber structure comprises four types of medicine chambers of a cartridge loading type medicine chamber, a cartridge split charging type medicine chamber, a medicine split charging type medicine chamber and a semi-combustible cartridge; the utility model is exemplified by a cartridge-containing chamber of a linear chamber catapult. [ document 1] P59 page last Nature notes: the slope chamber is divided into a sliding chamber slope chamber and a linear chamber slope chamber; FIGS. 6-22 show schematic views of the slope chamber structure; [ document 1] page 3, Nature paragraph P60 indicates that: the part of the barrel inner bore, except the medicine chamber and the slope chamber, for guiding the movement of the pill is called a guide part. Generally divided into two types, a linear chamber and a slide chamber.
The structural characteristics of the standard projectile are as follows: [ document 2] P8-13 indicates the following: p8 natural paragraph 1.3.2 consisting of artillery ammunition indicates "artillery ammunition also known as shell", and P8 natural paragraph 2 indicates "shell consisting of two parts, pellet and propellant charge"; the composition of the rifling cannon shell can refer to the composition of the cannon shell in figure 1-1; p8 paragraph 4 indicates that "a projectile is generally composed of a fuze, a body (casing), and a filler, etc.; p8 paragraph 6 indicates that: the projectile is a shell for containing a projectile charge and connecting various parts of the projectile, and is divided into a projectile head part, a cylindrical part, a projectile tail part and the like. Two ends of the cylindrical part are provided with a centering part, a belt (a conduction band) and an air-closed ring; p11 paragraph 2 indicates that "the propellant charge consists of propellant charge, cartridge, primer, and auxiliary elements"; document 3P 173 figures 4-9 show "a structure of a charge for a 100mm antiaircraft gun"; document 3P 182 figures 4 to 26 show a "mortar charge configuration diagram". The mortar shell consists of a tail fin 1, an additional explosive bag 2, a basic explosive tube 3, an explosive body 4, an explosive 5 and a fuse 6. The mortar charge belongs to the charge of split charging of medicine package, it is made up of basic charge and additional medicine package. The basic medicine package is the basic medicine tube. The basic cartridge, the additional medicine bags, the projectile body and the fuse are respectively packaged and stored at ordinary times, the basic cartridge is firstly installed during shooting, and then the additional medicine bags with proper quantity are installed according to the requirement of shooting range. The structure of the basic cartridge of the mortar is shown in figures 4-27, and the structure can be seen from the figures: the bottom of the basic cartridge is the primer, "the basic cartridge is placed in the tail tube 2.9 of the mortar shell". Document 2P 262-264 figures 9-8 and 9-11 give indications in the shape of the mortar shell; "elastomer cylindrical portion, also known as centering portion"; "in order to reduce the discharge of powder gas, a closed gas ring is always arranged in the centering part or a plurality of annular grooves are machined.
[ document 1]]P464 third last natural segmentNote that: "quality of the shot varies from shot to shot due to processing errors in the production. In order to prevent the quality difference of the shot from being too large and influencing the distribution, a quality grading method is adopted. The quality symbols are classified into nine grades as shown in Table 21-1. "the mass symbol for each shot is determined according to table 21-1, the symbol should be written on the body of the shot. One mass grading symbol differs from the mass of the standard bomb by + 1/3%, the heaviest 4 mass grading symbols "+ + + + +", the mass being that of the standard bomb
Figure BDA0002931530640000041
The lightest 4 mass grading symbols "- - - -", the mass is that of the standard bullet
Figure BDA0002931530640000042
Document 2P 236 section 8.2.2 "cartridge construction" indicates that the length of the cylindrical part of the mouth part of the cartridge is approximately equal to the length of the cylindrical part of the tail of the projectile (typically (0.80-1.25) d). The "beveled shoulder" is the transition from the nozzle to the barrel. The shape of the barrel is adapted to the shape of the chamber of the bore, and is generally a truncated cone. ";
document 3 subsection 0.1.1 of P1 indicates that "artillery primer charge is a collective term for gunpowder in ammunition and for auxiliary elements of the charge". The powder charge provides the firing energy for the weapon, and is one of the key factors determining the power of the weapon. "
[ document 4] the 12.1-segment gun powder charge structure of P205 indicates that: the gunpowder charging structure is designed by selecting the position of propellant in a powder chamber, the structure of an igniter and other charging elements under the condition of determining a ballistic scheme and the shape and size of gunpowder, so that the charging can meet ballistic indexes and the requirements of production, transportation, storage, service life and the like. "in turn" the significant impact … … on internal ballistic performance of charge configuration failure caused ballistic anomalies. "
2 about shooting precision, shooting accuracy and shooting intensity and data processing
[ document 5] P396 Nature paragraph 6 indicates that: "weapon firing precision consists of intensity and accuracy. Concentration is the degree to which a group of impact points spread around an average impact point, and accuracy is the degree to which the average impact point deviates from the aiming point ".
Document 2P 22-25 also discusses shot accuracy in more detail, indicating that the accuracy of the product is described in terms of accuracy and intensity. Accuracy refers to the difference between the mean and true values of multiple measurements of a sample. Concentration is the degree to which a set of impact points spread around an average impact point'
[ document 2]]P23 paragraph 7 indicates that: "A large number of observations indicate that the coordinates of the projectile landing point relative to the average landing point are two-dimensional random variables on a plane and satisfy the normal distribution law. "if the number of shots in a set of tests is n, the spatial coordinates are Xi、Yi、ZiThe average values of a group of test results are respectively
Figure BDA0002931530640000051
Mean deviation of coordinates X, Y, Z:
Figure BDA0002931530640000052
3 test methods
3.1[ article 7] ] 3.2 of P73-85 shows "test method of velocity measurement test, data processing and common velocity measurement equipment. "fitting amount test" is given in 3.3 of "document 7" P85-87, "jump angle test" is given in pages 7P 87-90, and "range and density test" is given in 3.6 of "document 7" P94-104. [ document 7] P104-105 describes the outline of the implementation of the vertical target test and the test equipment. Document 7P 109-126 describes a shot test for determining the spatial coordinates of a projectile.
3.2[ ref 5] P383 "main item of 15.4.1 external ballistic outdoor test" A review of the 3.1 test item was made.
3.3 people hope to obtain a method with good technical effect for determining the density and jump angle precision of a projectile system.
The standard projectile is thrown out from the standard projectile device. The function of the standard projectile and the propellant is mainly to endow the standard projectile with certain initial speed and ejection angle ejection, and the function of the standard projectile is to destroy a target.
In use, a user first gives a firing angle and a direction to the standard projectile to fire the standard projectile at the same initial velocity. After the standard projectile hits the target, measuring the coordinates of the drop point of the standard projectile, shooting 3 groups by a shooting angle generally, and shooting 5-10 groups by each group to send out the standard projectile. Drop scatter is more often than not normally distributed.
The movement of the system projectile in the air is interfered by various factors, so that the system projectile deviates from a preset track, and the falling points of the various system projectiles are scattered. The distance and direction coordinates (X) of the point of the projectile are then measurediZi) which may be taken from the target plane at the target point corresponding to the discrete impact points of the projectile firing count.
The precision of the product is described in terms of accuracy and intensity. Accuracy refers to the difference between the mean and true values of multiple measurements of a sample. The density refers to the degree of dispersion of the multiple measurements of the sample from the average. The accuracy index is finished by compiling a firing table by a unit specified by the country. The intensity index is a very important index of the product. It determines the amount, time, and logistics needed to achieve the goal of product destruction. Therefore, both the use units and the units providing the products are very important.
The standard projectile distribution is not modifiable and can only be reduced in size. The larger the mean square error of the distribution, the larger the consumption of the standard projectile damaging the target, the longer the shooting time, and the correspondingly increased chance of being counterstruck. Thus, when designing both the standard projectile and the standard projectile, it is desirable to know the respective mean square deviations of the dispersion.
The densities cannot be obtained computationally accurately, and their accuracy cannot be determined without leaving the shooting test. The index is accomplished by a third party specified by the country by a test method.
People desire to obtain a composite projectile with operability and better technical effect and for determining the density and the jump angle precision of a projectile system and a related technical method thereof.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a composite projectile with excellent technical effect for determining the intensity and the jump angle precision of a projectile system.
The technical problems to be solved in engineering application of the utility model are mainly as follows:
first, measuring the intensity of the projection system requires a ballistic coordinate. The flying track of the standard projectile launched by the standard projectile launcher in the medium consists of two parts, namely mass center movement of the oblong standard projectile and centroclinal movement around the mass center generated by an included angle between a projectile axis of the standard projectile and a flying velocity vector line of the standard projectile. The standard projectile is launched by the standard projectile launcher, and the obtained density comprises the density of the standard projectile launcher and the standard projectile through measuring the coordinates of the impact points of the standard projectile, namely the comprehensive density of the standard projectile launcher and the standard projectile.
The utility model provides a method in engineering practice, which comprises the steps of utilizing a standard projectile and standard launching charge, and launching a composite projectile obtained by transforming the standard projectile by a barrel of the standard projectile so as to separate the mass center motion of the standard projectile from the centroidal motion of a standard projectile axis around a velocity vector line. The utility model keeps the maximum simulation degree of the original projection system.
Secondly, the jump angle of the standard catapult given by the current test method is changed along with the target distance. The definition of the actual jump angle is: at the moment when the projectile exits from the muzzle, the included angle between the initial velocity vector line and the axis of the gun body before shooting is called the jump angle of the standard catapult. The axis of the standard catapult is unique before shooting, the initial velocity vector line is also unique, and obviously, the jump angle of the standard catapult is also unique. However, in the current jump angle test method, the test jump angle is changed along with the jump angle target distance, and the jump angle value is also changed. Therefore, the current jump angle test method gives inaccurate jump angle data. The conclusion of the study of the change law of the jump angle obtained from such data is questionable.
The shooting angle in the shooter is composed of the elevation angle and the jump angle of the catapult, and the shooting angle in the shooter is not accurate because the currently given jump angle is not accurate. Firing angle is a key element in determining whether the weapon system can hit the target.
The firing angle is one of core data for making a firing table, so that if the jump angle is not accurate in the firing table making process, the firing angle in the firing table is also inaccurate. The precision of a product is described in terms of accuracy and intensity according to industry practice: the accuracy refers to the difference between the average value and the true value of multiple measurements of a sample, and the accuracy index is finished by compiling a firing table by a unit specified by the country. The density refers to the discrete degree of a sample measured for multiple times and an average value; the density index is a very important index of the product, and determines the amount and time required for the target damage of the product and the logistics required to achieve the target. Therefore, both the use units and the units providing the products are very important.
The standard projectile distribution is not modifiable and can only be reduced in size. The larger the mean square error of the distribution, the larger the consumption of the standard projectile damaging the target, the longer the shooting time, and the correspondingly increased chance of being counterstruck. Thus, when designing both the standard projectile and the standard projectile, it is desirable to know the respective mean square deviations of the dispersion.
The intensity cannot be obtained accurately by calculation at present, and it is necessary to accurately determine that they are all not separated from the shooting test. This is usually done experimentally by a third party designated by the country. The preferred test method for concentration is: the standard catapult utilizes the propellant to throw the propellant out of the standard catapult; the functions of the standard ejector and the propellant are mainly to endow the projectile with certain initial speed, shooting angle and shooting direction; the projectile acts to destroy the target;
the test method of the concentration is as follows: firstly, endowing a standard catapult with a shooting angle, a shooting direction and an initial speed, and launching a projectile; after the projectile hits the target, measuring the coordinates of the impact points of the projectile, wherein one shooting angle generally shoots 3 groups, and each group shoots 5-10 projectiles; the drop point spread follows a normal distribution;
the utility model provides a method in engineering practice, only shoots the target with a certain distance of jump angle, and the given jump angle result can eliminate the influence of pneumatic jump angle, so that the jump angle is not changed along with the target distance. The technical problem of how to obtain the real jump angle of the standard catapult in the prior art is solved, and the watch compiling simulation precision is improved, so that the efficiency of a launching system is improved, and the related analysis and research work is more operable.
In the engineering application background, the utility model mainly relates to a method for determining the density and the jump angle precision of a casting system, which uses a standard casting machine to cast a composite casting object; the mass center motion trail of the composite projectile is composed of two parts, namely mass center motion of the component I1 and mass center motion of the component II 2 around the rotation axis of the component I;
the utility model relates to a composite projectile for determining the density and jump angle precision of a projectile system, which is characterized in that: the composite projectile is formed by combining a component I1 and a component II 2, wherein: the component I1 is a homogeneous spherical body with the diameter same as that of the standard catapult, and is of a solid or hollow structure; the material is metal or nonmetal or a compound thereof; the mass center of the first component 1 is coincident with the geometric center thereof and is at the spherical center; when the component I1 moves in a medium, an included angle between the geometric axis of the component I1 and a velocity vector line thereof is zero, and a motion track of the component I1 leaving the standard catapult can be described by a particle motion differential equation with three degrees of freedom; the second component 2 is a revolving body structural member with the cross section consistent with the caliber of the standard catapult; the second component 2 is a standard projectile or a local structure of the standard projectile or a simulated structure similar to the standard projectile in nature; the mass of the composite projectile is the same as or similar to that of the standard projectile; the number of the first assemblies 1 is at least one; further preferably: when the composite projectile is launched by using the gunpowder, the second component 2 is a part of the standard projectile capable of sealing the powder gas of the standard projectile;
the method for determining the intensity and the jump angle precision of the casting system is to use a standard casting device to launch a composite casting object consisting of a component I1 and a component II 2, and correspondingly measure the following data: chamber pressure, shooting angle, initial speed, meteorological conditions, resistance coefficient of the first assembly 1, range, ground density, jump angle, intermediate error of jump angle, standing target density, flight time (see the content of the literature 5, missile and rocket outside ballistics P383-387; and the related content of the literature 7, P69-125); if enough components 1 resistance coefficients are measured, the corresponding standard resistance coefficient can be defined according to the measured data; the technical field is also commonly referred to as the standard air resistance law of the spherical bullet.
After the launching is finished, measuring the impact point coordinates of the first assembly 1 and the second assembly 2, and calculating the intensity and the jump angle precision according to the measured impact point coordinates; determining the concentration and jump angle precision of a catapult or a catapult in the catapult system on the basis; this is one of the key innovation points of the present invention. Only two types of data are available in the prior art: first, the comprehensive intensity composed of a catapult and a projectile; secondly, the jump angle precision of the aerodynamic jump angle is included along with the change of the target distance. The utility model removes the influence of aerodynamic jump angle on jump angle precision without considering target distance change.
The method for determining the casting system concentration and the jump angle precision meets the following requirements: firstly, after the component I1 and the component II 2 fly away from a standard catapult, the component I and the component II both obtain the same initial speed and shooting angle, but the ballistic coefficients of the component I and the component II are different, and the component I and the component II are mutually separated and do not influence the respective movement; namely, the rear part of the emission position should be separated from the former part and should not collide with the former part; a high-speed camera is arranged at the initial stage of the trajectory, and the separation condition of the first assembly 1 and the second assembly 2 is monitored to ensure that the first assembly and the second assembly do not interfere with each other; secondly, the assembly I1 is required to be checked before launching, whether the center of mass is coincident with the center of the sphere and the ovality of the center of mass are checked, and if the center of mass does not meet the requirement, the assembly is not selected as a projectile for testing; after transmission, the assembly 1 is also checked and checked for ovality, and if the requirement is not met, the corresponding data are not used as valid test data. (in the method for determining the density and the jump angle precision of the casting system, various typical test processes are required to be specifically carried out by selecting a corresponding method according to the test purpose.)
The method for determining the casting system concentration and the jump angle precision further comprises the following technical contents:
the method for determining the casting system concentration and the jump angle precision sequentially comprises the following steps and requirements:
firstly, determining a test purpose, and preparing test materials and a test site; the test aims at one of the following three: determining the density of a catapult, the density of a catapult and the jump angle precision of the catapult in a catapult system; the requirements for test material preparation are as follows: preparing a composite projectile, a launching power system and a standard projectile for testing which meet the requirements; preparing a test data measuring device;
selecting a test method and preparing a test site;
firstly, a direct weapon intensity test method is used for testing, and standard vertical target intensity of a catapult or a projectile is determined;
secondly, a distance shooting test method is used for testing, and the distance concentration of the standard catapult or the projectile is determined;
thirdly, performing a test by using a jump angle shooting test method to determine jump angles and intensity of the standard catapult;
the test method selected in the step II of the method for determining the intensity of the casting system and the jump angle precision is one or a combination of the following three methods:
firstly, testing according to a test method of neutral target concentration, namely direct weapon concentration in P104-107 in document 7, and determining the vertical target concentration of a standard projectile or a standard projectile;
[ document 7] shows a method for calculating density, which is mainly used for measuring the middle errors of range and ground density, jump angle and jump angle, and measuring the vertical target density: according to the direct projection distance or the effective range of the standard ejector, a vertical target is arranged at a position which is a certain distance away from the standard ejector and is vertical to the ground and is vertical to the direction;
the standard projectile shoots a group of projectiles at the opposite target under constant shooting conditions (such as shooting direction, elevation angle, charging, projectiles and the like), and then measures the height direction coordinates (Y) of the shooting pointsi,Zi) The origin of coordinates is taken as the target surface aiming point according to (Y)i,Zi) I.e. capable of calculating a high-low intermediate error EyAnd median error of direction Ez：
Figure BDA0002931530640000081
Secondly, determining distance concentration of the system projectile or the system projectile according to a range and concentration test of P94-104 in the document 7 (distance concentration, namely 'curved shot concentration', or 'range concentration', namely concentration corresponding to distance shooting, curved shot or range);
thirdly, the jump angle and jump angle intensity of the standard catapult are determined according to a jump angle test method in the document 7P 87-91.
Fig. 1 is a schematic diagram of the utility model suitable for a line-chamber type ejector, and fig. 3 is a schematic diagram of the utility model suitable for a slide-chamber type ejector. The characteristics of figures 1 and 2 and 3 are that the assembly one 1 is in front of the assembly two 2, for determining the concentration and jump angle accuracy of the standard catapult. The characteristics of the attached figures 4 and 5 are that the second component 2 is arranged in front of the first component 1, and the intensity and the jump angle precision of the standard catapult and the standard catapult can be determined simultaneously.
The jump angle precision generally comprises two parts of jump angle concentration and jump angle accuracy (the jump angle accuracy is commonly called as a jump angle); the jump angle density of the standard catapult is described by jump angle scattering;
at the moment that the composite projectile leaves the launching port of the standard projectile device (namely at the moment that the composite projectile is separated from the mechanical connection with powder gas after being ejected out of the launching port of the standard projectile device), an included angle between the speed direction of the composite projectile and the axis of the standard projectile device body tube before shooting is called a jump angle of the standard projectile device; the jump angle of the catapult is a vector, the jump angle in the vertical direction is called as a vertical jump angle or a high-low jump angle and is indicated by a multiple symbol gamma, and the jump angle in the vertical direction is generally vertical when subscripts are not labeled. The horizontal jump angle is often called a transverse jump angle or a transverse jump angle, and the symbol is often represented by a symbol ω. The subscripts are sometimes referred to differently, for example, in the present invention, by y or z for the skip angle in the elevation or lateral direction,
the test method of the standard catapult jump angle test is as follows: setting a jump angle target at a distance from the emission port of the standard catapult, and shooting the jump angle target by using the standard catapult (see, for example, document 5)]P385 fig 15.4.2); the angle jump test is mostly carried out by adopting plane shooting. I.e. the elevation angle of the gun
Figure BDA0002931530640000091
(the elevation angle of the gun does not exceed 2 degrees in general) and satisfies the high-low component jump angle:
Figure BDA0002931530640000092
can be used [ document 7]]The formula in P87-91 calculates the jump angle. High-low component gamma of jump angleyIs according to [ document 7]]P88 formula (3-6):
Figure BDA0002931530640000093
calculating the lateral component omega of the jump anglezIs according to [ document 7]]P88 formula (3-7):
Figure BDA0002931530640000094
in the formula: x is the target distance y, z is the high-low coordinate and the transverse coordinate of the impact point relative to the aiming point, m respectively; g is the acceleration of gravity, m/s2；VpIs the average flight speed over the shot travel x, m/s;
when aiming at the cross line of the target with jump angle, the high-low component gamma of the jump angle in the two formulasyTransverse component omega of the jump anglezNamely the true test jump angle of the catapult. True test vertical jump angle gamma, true jump angle gamma by standard catapult1And aerodynamic jump angle gamma of the projectile2Composition is carried out; the following holds: gamma-gamma1+γ2
Because the composite projectile contains the first homogeneous spherical component 1, the angle of attack of the first component 1 is zero when the component moves in the medium, and therefore the pneumatic jump angle is not contained, the gamma ray2Is not changed with the target distance and has a value of 0, so the test jump angle gamma is the real jump angle gamma of the catapult1The key technical problems in the prior art are as follows: at present, no standard catapult with operability has real jump angle gamma1A method of measurement; the utility model creatively solves the technical problem by improving the projectile and improves the watch shootingAccuracy, from which also the exact jump angle (accuracy) of the projectile launched by the launcher is obtained; and the related jump angle theory has practical significance and operability in practice.
In the prior art, because the standard projectile is usually a long circular rigid body, and the attack angle of the standard projectile is not zero, the jump angle data is inevitably changed along with the target distance. In the present invention, the angle of attack of the first element 1 is zero, so that the jump angle of the first element 1 is invariant with the target distance.
Thirdly, selecting a corresponding launching power system scheme according to the requirements of the corresponding standard projectile on initial speed, chamber pressure and the like when the corresponding standard projectile is launched; for example, for a propellant powered by gunpowder gas, the specific loading capacity is selected according to the requirements of initial speed and chamber pressure;
measuring initial speed, chamber pressure, shooting angle and meteorological observation data during each launching, and obtaining or measuring the resistance coefficient of the assembly I1 in advance;
erecting a high-speed camera at the initial stage of the trajectory, and monitoring the separation condition of the first assembly 1 and the second assembly 2; ensuring that the first component 1 and the second component 2 do not interfere with each other; if interference occurs, the emission test and related data are regarded as invalid;
sixthly, recovering the homogeneous spherical body at the impact point, checking the ovality of the homogeneous spherical body and ensuring the homogeneous spherical body in the flying process; if the requirements cannot be met, the emission test and the related data are regarded as invalid;
seventhly, measuring the coordinates of the impact points of the first component 1 and the second component 2; one of the following data is then calculated: the projectile density, the projectile density and the jump angle precision; if the density of the projectile and the density of the projectile are required to be obtained, the corresponding method in P87-105 of the document 7 is selected after shooting, and the shooting is carried out by aiming at the vertical target and the distance shooting respectively and correspondingly;
measuring the coordinates of the impact points of the first component 1 and the second component 2; one of the following data is then calculated: the concentration of the component I1 is the concentration E1 of the catapult (the catapult is a catapult to be tested, mostly a standard type, or a novel launcher), and the concentration of the component II 2 is the integration of the standard type catapult and the standard type catapultThe concentration Es, corresponding to the projectile concentration E2, is given by the formula: es 2＝E1 2+E2 2Determining;
if the jump angle precision of the catapult is to be obtained, adopting a method for carrying out jump angle test on a jump angle target by a composite projectile and a data processing method to obtain jump angle intensity of the standard catapult, and accordingly obtaining the jump angle of the standard catapult; the common method compared with the method is to reversely calculate the jump angle of the catapult according to the mean value of the coordinates of the impact points of the catapult jump angle intensity test; the efficiency and the effect of the utility model are obviously improved.
If a vertical target or a jump target is used, the height and direction coordinates (Y) of the impact point are measuredi,Zi) The high-low intermediate error E is calculated according to the following formulayAnd median error of direction Ez：
Figure BDA0002931530640000101
If the distance shooting is a ground intensity test, the distance and direction coordinates (X) of the impact points are required to be measuredi,Zi) According to (X)i,Zi) I.e. the distance intermediate error E can be calculatedxAnd median error of direction Ez：
Figure BDA0002931530640000102
In the formula, n is the number of the composite projectile composition, namely the effective launching times;
Figure BDA0002931530640000103
are each a corresponding Xi、Yi、ZiAverage value of (a).
The method for determining the intensity and the jump angle precision of the casting system meets one or the combination of the following requirements:
first, component one is determined using one or a combination of the following methods1 coefficient of resistance in a medium or law of resistance CXqbf(M)：
Theoretical calculation, estimating the air resistance coefficient of a component I1, namely a homogeneous spherical body;
secondly, a wind tunnel is utilized to carry out a blowing test, and the air resistance coefficient of the homogeneous spherical body is further determined;
thirdly, determining the air resistance coefficient of the homogeneous spherical body by using the Doppler radar; [ document 5]]The last natural segment of P389 is ended at section 15.5.1 of P391, which indicates that the method for extracting rocket zero-lift resistance coefficient C from radar speed measurement dataXOPrinciple of (1);
secondly, determining a flight state parameter K:
the ballistic coefficients of the component I1 and the component II 2 which adopt the same law of resistance are respectively C1And C2Then C is2And C1The ratio is defined as the flight state parameter of the composite projectile, denoted as K, and having:
Figure BDA0002931530640000111
in the above formula, m1、m2The mass of the component I1 and the component II 2 respectively; i all right angle1、i2The elastic coefficients of the component I1 and the component II 2 are respectively; CX1 and CX2 are the resistance coefficients of the first component 1 and the second component 2 respectively;
thirdly, before and after the first component 1 and the second component 2 fly away from the standard catapult, determining which of the first component 1 and the second component 2 is in front according to the following basis:
if C is present1Less than C2If K is greater than 1, the requirement is that the first component 1 is always in front of the second component 2 before and after the launching, so that the second component 2 does not interfere with the movement of the first component 1;
if C is present1Greater than C2If K is less than 1, the first component 1 is required to be always behind the second component 2 before and after the launching, so that the first component 1 does not interfere with the movement of the second component 2;
the flight state parameter K is required to be not equal to 1, otherwise, the component one 1 and the component two 2 interfere with each other.
The method for determining the intensity and the jump angle precision of the casting system meets one or the combination of the following requirements:
firstly, when a test for determining the density of a standard projectile is carried out, a first component 1 is in front, a second component 2 is in back, and the sum of the mass of the first component 1 and the mass of the second component 2 is required to be equal to the mass of the original standard projectile;
and secondly, the component I1 and the component II 2 are independent or are combined structures consisting of a plurality of subassemblies. When the number of the component 1 is one, high-density balls such as tungsten core balls are required to be used, but the manufacturing cost is high; when the number of the first assemblies 1 is two, two balls are combined for use; for example: one of the two balls may be a copper ball and the other a nylon ball; wherein: the high-density copper ball is positioned at the forefront relatively far away from the standard catapult base;
thirdly, when gunpowder is used for launching the composite projectile, the second component 2 is an ultra-light projectile of the standard projectile capable of sealing standard projectile gas, and the total mass of the first component 1 and the second component 2 in the composite projectile is equal to the mass of the ultra-heavy projectile of the standard projectile; the composite projectile is generally equivalent to a standard projectile; at the moment, the data obtained by the test can be regarded as effective test data of the standard projectile and the standard ejector;
the typical structure of the aforementioned "powder charge" that is, the chemical charge or the propellant charge in the prior art, which can provide kinetic energy to the projectile (see [ document 3] principle and technology of designing a propellant charge for artillery ] P173, fig. 4-9, structure diagram of a 100mm high-fire gun charge, fig. 4-26 structure diagram of a mortar charge, P182) is: a cartridge, propellant powder and primer; the cartridge, the propellant powder and the primer of the original system projectile are required to be selected as much as possible; or is formed by reforming a part of the original system projectile to be tested; or other types of novel structural projectiles capable of hermetically ejecting gas are reformed according to the design drawings of the original standard projectiles; the ultimate aim is to keep the consistency (high simulation) as much as possible, namely to keep the vibration and initial disturbance of the catapult consistent with the vibration and initial disturbance of the catapult launched by the catapult of the original standard.
The method for determining the projectile and the density of the projectiles further meets one or a combination of the following requirements:
first, when conducting a test for determining the projectile and the density of the projectile simultaneously, assembly one 1 is behind and assembly two 2 is in front, and this time there must be: the sum of the masses of the first component 1 and the second component 2 is less than or equal to the mass of the extra-heavy bullet of the original system bullet; the elastic weight of the standard projectile is divided into 9 mass grading symbols;
secondly, in a test for simultaneously determining the density of the projectile and the ejector, the composite projectile is ejected by using gunpowder, the component II 2 is a standard projectile ultra-light projectile capable of sealing standard projectile gas, the total mass of the component I1 and the component 2 in the composite projectile is approximately equal to the mass of the standard projectile, and the total mass of the composite projectile is equal to the standard projectile; and at the moment, the data obtained by the test is regarded as effective test data of the standard projectile and the standard ejector.
(Note: jump angle of projectile, i.e. aerodynamic jump angle of projectile;)
The method for determining the projectile and the density of the projectiles further meets one or a combination of the following requirements:
first, in a test to determine the density of the projectiles alone, the composite projectile meets the following requirements: the second composite projectile component 2 is behind and the first component 1 is in front;
secondly, when the throwing system is a chamber system throwing device, when the component I1 is in front, the modification requirement of the component II 2 is as follows: removing a fuse and an oval part of a warhead; secondly, all parts of the rear part of the standard projectile, namely a centering part, a cylindrical part, a cylinder with a belt and a tail part, are reserved; thirdly, the inner cavity of the rest part of the standard projectile, namely the rear part, is required to be hollowed; a head screw is additionally arranged on the rear side of the component I1 and the front side of the first centering part, so that the component I1 cannot enter the inner cavity of the centering part at the rear part, which is the rest part of the system projectile; fifthly, uniformly balancing the head screw and the first assembly 1 to enable the mass of the head screw and the mass of the first assembly to be equal to the mass of the original standard projectile;
thirdly, in the composite projectile used by the manufactured linear chamber projectile launcher, the launching power module 3 adopts the launching power module 3 and the assembling mode of the original system launcher, no change is made, and the internal trajectory performance is ensured to be unchanged; that is, the transmission power module 3 is constituted as follows: 3.1 parts of a medicine cylinder, 3.2 parts of propellant powder and 3.3 parts of primer; wherein: the medicine cylinder 3.1 is arranged at the rear part of the tail part of the assembly II 2, the propellant powder 3.2 is arranged in the inner cavity of the medicine cylinder 3.1, and the primer 3.3 is arranged at the rearmost part of the medicine cylinder 3.1; see figures 1 and 2;
when the ejection system is a line-chamber type ejector, and in the composite ejector used by the line-chamber type ejector, the ejection power module 3 is composed of the following ejection power systems adopting the standard ejectors: 3.1 parts of a medicine cylinder, 3.2 parts of propellant powder and 3.3 parts of primer; wherein: the cartridge 3.1 is arranged at the rear part of the tail part 2.5 of the assembly II 2, the propellant powder 3.2 is arranged in the inner cavity of the cartridge 3.1, and the primer 3.3 is arranged at the rearmost part of the cartridge 3.1;
fourthly, when the ejection system is a smoothbore type ejector, the component II 2 is a part of the type ejector or is formed by modifying the type ejector; the requirements of the modification are as follows: the second component 2 removes the standard projectile fuse and the warhead oval part 2.1, and reserves the closed gas ring 2.7 and other parts of the standard projectile; thirdly, simultaneously, the inner cavity at the rear part of the standard projectile is required to be hollowed; a head screw 2.6 is additionally arranged at the back of the component I1 and the front of the first gas-tight ring, so that the component I1 cannot enter an inner cavity of a gas-tight ring 2.7 at the back of the standard projectile; fifthly, the mass of the projectile is uniformly balanced with the component I1 to ensure that the mass sum of the projectile is equal to the mass of the projectile in the original standard; document 2P 262-264 figures 9-8 and 9-11 give indications in the shape of the mortar shell; "elastomer cylindrical portion, also known as centering portion"; "in order to reduce the discharge of powder gas, a closed gas ring is always arranged in the centering part or a plurality of annular grooves are machined. Related explanation: the gas-tight ring is arranged in the cylindrical part of the mortar shell, and grooves are machined only in order to reduce the leakage of powder gas due to the smooth-bore mortar, and the parts of the grooves are called gas-tight rings.
The launching power module 3 adopts the launching power module 3 and the assembly mode of the original standard launcher without any change so as to ensure that the inner ballistic performance is unchanged; the launching power module 3 of the original system launcher has no cartridge case 3.1, the cartridge case 3.1 is served as a closed space formed by matching the tail part of the airtight ring 2.7 of the bullet head part of the assembly two 2 and the inner cavity of the barrel 4, the additional medicine package of the launching powder 3.2 is surrounded outside the tail pipe 2.9 of the bullet tail part 2.5 of the assembly two 2, and the basic powder tube and the primer 3.3 are arranged inside the tail pipe 2.9 of the bullet tail part 2.5 of the assembly two 2 and are arranged at the rearmost part of the bullet tail part 2.5; see figure 3.
Fifthly, when the ejection system is a smoothbore type ejector, in the composite ejector used by the smoothbore type ejector, the emission power module 3 belongs to one part of the component 2. The launch power module 3 is constructed as follows: 3.1 parts of a medicine cylinder, 3.2 parts of propellant powder and 3.3 parts of primer; wherein: the cartridge 3.1 is a closed space formed by matching the assembly II 2 and the inner cavity of the barrel 4, the propellant powder 3.2 is surrounded in a tail pipe 2.9 of the tail part of the assembly II 2, and the primer 3.3 is arranged in the tail pipe 2.9 of the tail part of the assembly II 2 and is arranged at the rearmost part of the tail part 2.5;
sixthly, when the density of the ejector and the projectile is determined simultaneously, the composite projectile meets the following requirements: firstly, a composite projectile component II 2 should select projectiles with the mass of being in a super-light-bullet mode and be arranged in front of a component I1; the end part of the first assembly 1 is tightly attached to the tail part 2.5 of the second chamber projectile assembly 2; or the end part of the first component 1 is clung to the bottom of a tail pipe 2.9 of the tail part 2.5 of the sliding chamber projectile component 2; the quality of the composite projectile is the same as or similar to that of the standard projectile. The composite projectile is a composite structure using chemical charge as launching power; the mass is 'extra light bullet', which means a standard bullet with 4 mass grading symbols 'minus-minus' lighter than the standard bullet, and the mass of one bullet weight grading symbol is plus or minus 1/3% of the standard bullet weight; the bullet weight grading symbol part is equal to the old 'bullet weight symbol' meaning; the second component 2 should be capable of sealing gunpowder gas when in the rear;
seventhly, when the throwing system is a chamber system throwing device, the first component 1 is arranged behind the second component 2, and the requirement for remanufacturing the first component 1 is as follows: firstly, a newly modified cartridge case 3.1 is additionally arranged at the rear part of a component I1, the optimal scheme is that the cartridge case is modified by a standard cartridge case, the opening part of the cartridge case 3.1 is connected with an elastic tail part 2.5 of a component II 2, the component I1 is inevitably arranged at the inclined shoulder part of the cartridge case 3.1, a bullet baffle plate 3.4 for limiting the component I1 is additionally arranged at the rearmost part of the composite projectile component I1, and the bullet baffle plate 3.4 is used for tightly attaching the front part of the component I1 to the elastic tail part 2.5 of the component II 2; so as to prevent the first component 1 and the second component 2 from colliding with each other and exploding the hearth; when a cushion pad is additionally arranged, the cushion pad, the first component 1 and the second component 2 are uniformly weighted to ensure that the mass sum of the cushion pad is equal to that of the projectile in the original standard; when the bullet baffle 3.4 is additionally arranged, the first component 1, the second component 2 and the bullet baffle 3.4 are uniformly weighted to ensure that the sum of the mass of the components is equal to that of the original standard projectile; see fig. 4;
eighthly, when the ejection system is a smoothbore type ejector, the first component 1 is arranged behind the second component 2; a newly modified short medicine cylinder is added at the back of the assembly I1; secondly, preventing the first component 1 and the second component 2 from colliding with each other to cause chamber explosion; one method is that a round baffle 3.4 is arranged at the opening part of the short medicine cylinder, and the baffle 3.4 is used for tightly attaching the end part of the first component 1 and the tail part 2.5 of the second component 2; the propellant powder package and the basic powder tube of the tail pipe 2.9 of the second component 2 arranged at the tail part 2.5 of the bullet are moved into the short powder cylinder; fourthly, primer 3.3 arranged in a tail pipe 2.9 of the tail part 2.5 of the second component 2 is subjected to fire picking treatment; fifthly, installing primer 3.3 at the rear part of the short cartridge case, uniformly balancing the bullet baffle 3.4 with the first component 1 and the second component 2 to ensure that the mass of the bullet baffle equals to that of the projectile in the original standard; see fig. 5; the quality of the original standard projectile is graded. When the concentration of the component I and the component II is determined at the same time, the quality is the quality of the extra-heavy bomb; when the density of the ejectors is determined separately, the mass of the composite ejectors should be the standard projectile weight. There is also a range for the same shot weight level mass.
Document 3P 182 figures 4 to 26 show a "mortar charge configuration diagram". The mortar shell consists of a tail fin 1, an additional explosive bag 2, a basic explosive tube 3, an explosive body 4, an explosive 5 and a fuse 6. The mortar charge belongs to the charge of split charging of medicine package, it is made up of basic charge and additional medicine package. The basic medicine package is the basic medicine tube. The basic cartridge, the additional cartridges, the projectile body and the fuse are respectively packaged and stored at ordinary times, the basic cartridge is firstly mounted during shooting, and then the additional cartridges with proper quantity are mounted according to the requirement of shooting range. The structure diagram of the mortar basic cartridge is shown in figures 4-27, and the diagram shows that: the bottom of the basic cartridge is the primer, "the basic cartridge is placed in the tail tube 2.9 of the mortar shell".
The method for determining the casting system concentration and the jump angle precision meets one or the combination of the following requirements:
firstly, the density and jump angle precision of the ejector can be obtained through the density test of the composite projectile component I1 in front and the component II 2 in back;
secondly, the density test of the first component 1 after the second composite projectile component 2 is in front of the first component can obtain the densities of the projectiles and the ejectors simultaneously; for curved trajectory, ground density is obtained; what is obtained for direct weapon is the concentration of standing targets; shooting the jump angle target to obtain the jump angle precision;
thirdly, the test method for determining the vertical target and the jump angle of the standard catapult meets the following requirements:
the measurement key points of the vertical target density are as follows: according to the direct projection distance or the effective range of the standard ejector, a vertical target is arranged at a position which is a certain distance away from the standard ejector and is vertical to the ground and is vertical to the direction; the standard projectile shoots a group of composite projectiles at opposite targets under constant shooting conditions, and then the height direction coordinates (Y) of the shot points are measuredi,Zi) The origin of coordinates is taken as the aiming point of the target surface according to (Y)i,Zi) I.e. the high-low intermediate error E can be calculatedyAnd median error of direction Ez：
Figure BDA0002931530640000141
In the formula, n is the number of the composite projectile composition for emission, namely the effective emission times;
Figure BDA0002931530640000142
are each a corresponding Yi、ZiAverage value of (d);
the jump angle test adopts flat shooting, i.e. the elevation angle of the gun
Figure BDA0002931530640000143
(generally not more than 2 °), and satisfies: vertical jump angle
Figure BDA0002931530640000144
The accuracy of the standard catapult is described by jump angle, and the concentration of the catapult is described by jump angle dispersion;
at the moment that the composite projectile leaves the emission opening of the standard projectile or the moment that the composite projectile leaves the emission opening of the standard projectile and is separated from the mechanical connection with powder gas, an included angle between the speed direction of the composite projectile and the axis of the body pipe of the standard projectile before shooting is called as a jump angle of the standard projectile;
the test method of the standard catapult jump angle test is as follows: setting a jump angle target at a certain distance from the mouth of the standard ejector, and shooting the jump angle target by the standard ejector;
the results of the measurements were: testing vertical jump angle gamma, true vertical jump angle gamma of standard catapult1Aerodynamic jump angle gamma2(ii) a And has the following components:
γ＝γ1+γ2
according to the foregoing theoretical and experimental results, γ2Is varied with target distance, thereby testing jump angleγAlso varies with target distance; using improved composite projectiles, with an aerodynamic jump angle gamma corresponding to component 12Zero, so that in practice γ is γ ═ γ1
The method for determining the intensity and the jump angle precision of the casting system meets the following requirements:
the test jump angle in jump angle test is formed from two portions of jump angle of standard projectile and aerodynamic jump angle of standard projectile, and the aerodynamic jump angle is changed with target distance, so that the obtained test jump angle also can be changed with target distance, and when the basic trajectory of firing table is compiled, it gives out the gun installation fixed angle
Figure BDA0002931530640000151
A relationship corresponding to ballistic data; the actual firing angle of the projectile at the muzzle is θ, and satisfies:
Figure BDA0002931530640000152
the test method of the concentration is as follows: firstly, endowing a standard catapult with a shooting angle, a shooting direction and an initial speed, and launching a projectile; after the projectile hits the target, measuring the coordinates of the impact points of the projectile, wherein one shooting angle generally shoots 3 groups, and each group shoots 5-10 projectiles; the drop point spread follows a normal distribution;
the movement of the projectile in the air is disturbed by various factors, so that the projectile deviates from a preset track, and the drop point of each projectile is scattered; the distance and direction coordinates (X) of the point of the projectile are then measuredi,Zi) The origin of coordinates can be taken as the target surface aiming point according to (X)i,Zi) I.e. the distance intermediate error E can be calculatedxAnd median error of direction Ez：
Figure BDA0002931530640000153
Corresponding to the projectiles which are launched for multiple times, dispersed impact points are correspondingly arranged;
the method for evaluating the concentration comprises the following steps: assuming the concentration of the standard catapults is E1The density of projectiles is E2The combined concentration of the two is ES(ii) a Consider E1、E2Both are independent random variables; then, the relationship between them is: es 2＝E1 2+E2 2。
The method for determining the intensity and the jump angle precision of the casting system meets the following requirements:
firstly, one or more components 1 thrown by the standard thrower at one time are provided; when the number of the assemblies I1 is larger than 1, the mass of different assemblies I1 is sequentially increased progressively along the launching direction according to the fact that the muzzle of the catapult barrel is in front and the bottom of the catapult barrel is in back, namely the assemblies I are sequentially arranged according to the sequence that the mass is large in front and the mass is small in back;
the system type ejector ejects the composite projectile and meets one of the following requirements: propelling the projectile to move with a chemical charge and propelling the projectile to move with a non-chemical charge;
secondly, the launching power structure of the composite projectile meets the following requirements:
firstly, a chamber type catapult which does not use chemical charge to propel the projectile to move is used; at least one component 1 is provided; when the number of the assemblies I1 is larger than 1, the masses of the assemblies I are sequentially increased along the emission direction; along the launching direction, the last individual of the composite projectile is provided with a launching power structure which provides power for all individuals in the whole composite projectile;
secondly, for a chamber type catapult which propels the projectile to move by chemical charging, a launching power module 3 is arranged on the final composite projectile; the launching power module 3 is used as launching power to provide chamber pressure and initial speed necessary for launching for the component II 2 and all the components I1 in the composite projectile; the launching power module 3 is constructed as follows: a cartridge 3.1, a propellant powder 3.2 and primer 3.3; wherein: the medicine cylinder 3.1 is arranged at the rear end of the composite projectile, the propellant powder 3.2 is arranged in the inner cavity of the medicine cylinder 3.1, and the primer 3.3 is arranged at the rear end of the medicine cylinder 3.1;
when the ejection system is a linear chamber type ejector, and when the component I1 is in front, the modification requirement of the component II 2 is as follows: removing fuze and bullet head oval part 2.1; secondly, all parts of the rear part of the standard projectile, namely a centering part 2.2, a cylindrical part 2.3, a cylinder with a belt and a tail part 2.5, are reserved; thirdly, simultaneously, the inner cavity at the rear part of the standard projectile is required to be hollowed; a head screw 2.6 is additionally arranged at the back of the component I1 and the front of the first centering part, so that the component I1 cannot enter an internal cavity of the centering part 2.2 at the back of the standard projectile; fifthly, the mass of the projectile is uniformly balanced with the component I1 to ensure that the mass sum of the projectile is equal to the mass of the projectile in the original standard;
when the ejection system is a linear chamber type ejector, when the assembly I1 is arranged behind, the remanufacturing requirement is as follows: adding a cartridge 3.1 at the rear part of the component I1, wherein the cartridge 3.1 is obtained by modifying or re-customizing the partial structure of the front end of the cartridge of the original standard projectile, namely the proximal end part of the cartridge opening; the inner diameter of the cartridge 3.1 is required to be the same as the outer diameter of the projectile tail 2.5 of the standard projectile; secondly, a bullet baffle 3.4 is additionally arranged at the rearmost part of the composite projectile; or a baffle plate 3.4 is additionally arranged in the cartridge 3.1 at the rear side of the assembly I1; so as to prevent the first component 1 and the second component 2 from colliding with each other to cause chamber explosion; when a cushion pad is additionally arranged, the cushion pad, the first component 1 and the second component 2 are uniformly weighted to ensure that the mass sum of the cushion pad is equal to that of the projectile in the original standard; when the bullet baffle 3.4 is additionally arranged, the first component 1 and the second component 2 are uniformly weighted to enable the mass sum of the components to be equal to the mass sum of the original standard projectile.
When the jump angle precision of the catapult is determined, the composite projectile meets the following requirements: the second component 2 in the composite projectile is arranged behind or in front of the first component 1; the composite projectile is a composite structure which uses chemical charge as launching power; the composite projectile is also provided with a launching power module 3, and the launching power module 3 is arranged at the rear part of the composite projectile;
firstly, when the ejection system is a smoothbore type ejector and the component II 2 is arranged behind the component I1, the ejection power module 3 belongs to one part of the component II 2; the launch power module 3 is constructed as follows: 3.1 parts of a medicine cylinder, 3.2 parts of propellant powder and 3.3 parts of primer; wherein: the cartridge case 3.1 is a closed space formed by matching the second component 2 and the inner cavity of the barrel 4, the propellant powder 3.2 is the propellant powder of the original structure of the second component 2, and the primer 3.3 is the primer of the original structure of the second component 2 and is arranged at the rearmost part of the second component 2;
secondly, when the ejection system is a smoothbore type ejector and the component II 2 is arranged in front of the component I1, the ejection power module 3 comprises the following components: a cartridge 3.1, a propellant powder 3.2 and primer 3.3; wherein: the medicine cylinder 3.1 is arranged at the rear part of the assembly I1, the propellant powder 3.2 is arranged in the inner cavity of the medicine cylinder 3.1, and the primer 3.3 is arranged at the rearmost part of the medicine cylinder 3.1;
for the sliding chamber type ejector, the component II 2 is a type projectile or is formed by modifying the type projectile; the requirements of the modification are as follows: the second component 2 removes the standard projectile fuse and the warhead oval part 2.1, and reserves the closed gas ring 2.7 and other parts of the standard projectile; the bottom of the tail pipe 2.9 is a primer 3.3 which is impacted or electrically shocked; for a sliding chamber type ejector, the used composite projectile meets one of the following requirements: the device comprises a first component and a second component, wherein the first component is composed of at least one component I1 and 1 component II 2; the second component comprises a second component 2 capable of sealing the gas of the catapult and at least 2 first components 1;
thirdly, for a standard projectile with a secondary caliber, a composite projectile component II 2 is reformed by the standard projectile of the standard projectile, and a component I1 in the composite projectile is used for replacing a bullet core in a bullet holder of the standard projectile with the secondary caliber; before launching, the first assembly 1 is arranged inside the second assembly 2, and the launching power module 3 is served by a power structure of the original second assembly 2; the launch power module 3 is constructed as follows: 3.1 parts of a medicine cylinder, 3.2 parts of propellant powder and 3.3 parts of primer; wherein: the medicine cylinder 3.1 is arranged at the rear part of the assembly II 2, the propellant powder 3.2 is arranged in the inner cavity of the medicine cylinder 3.1, and the primer 3.3 is arranged at the rearmost part of the medicine cylinder 3.1;
fourthly, for the projectile without the cartridge case, the launching power module 3 is equal to a standard projectile; the concrete requirements are as follows: the additional medicine package of the propellant powder 3.2 is bound on the tail pipe 2.9, and the primer 3.3 is arranged at the bottom of the tail pipe 2.9; when the propellant is launched, the propellant slides downwards along the barrel 4 of the standard catapult to impact the firing pin at the bottom of the barrel 4, primer 3.3 ignites propellant powder 3.2, and the propellant powder is ejected out of the barrel 4 by the propellant powder gas.
In addition: some of the terms of the present invention are self-defined and are specifically described as follows:
the "catapult" refers to a tubular catapult or a rocket launcher, an electromagnetic launcher, or the like. The 'standard projectile' refers to a revolving body structural member with the same caliber as a barrel for launching. The standard catapult and the standard catapult refer to the catapult and the catapult to be detected when the method is used for corresponding detection; in principle it should be of existing standard construction. The "standard ejector" refers to an existing ejector. "shaped charge" refers to an existing shaped charge.
The rearmost individual of the composite projectile is provided with a power structure; for chemical charge projectile, with respect to cartridge projectile, it can use the structure of cartridge in the structure diagram of 100mm high-fire gun charge of fig. 4-9 of [ document 3] P173; for the projectile without the cartridge, the structure of the cartridge in the mortar charge structure diagram of figure 4.26 of document 3P 183 and the like can be adopted, so that all the individuals in the composite projectile are launched by the power provided by the rearmost individual.
For the traditional standard ammunition fired by means of an oblong rigid body, the jump angle of the standard ammunition is inevitably changed along with the target distance because the trajectory of the standard ammunition after firing is a spiral trajectory; after the composite projectile containing the homogeneous spherical component I1 is used, the jump angle of the obtained component I1 cannot change along with the target distance, so that the data can be measured and stabilized, and the measurement accuracy of the firing angle in the firing watch is improved. This is very important to establish a more complete shooter.
The technical effects of the utility model are illustrated as follows:
document 2P 34 paragraph 5 states that "it is not sufficient to analyze and calculate the action and performance of ammunition only by theory because of many factors of influence, and thus various tests have to be performed to check the manufacturing quality of ammunition. Of the various tests, what is of decisive significance is the shooting range test. "the range test project is mainly 9 items, wherein there are two items related to the outer ballistic performance |" shooting density and maximum range "; flight stability and flight correctness; and the shooting chart planning is also finished through a shooting range test.
These tests consume a large amount of ammunition and typically require 3 shots per firing angle, 5-10 shots per set. But the obtained concentration data is the comprehensive data of the standard catapult and the standard catapult. If the comprehensive data can not meet the requirements of tactical technical indexes, a development unit needs to know that the problem is that of a standard ejector or a standard projectile. The present invention solves this problem.
The range shooting test consumes a lot of ammunition throughout the various stages of the product. For example, in [ document 5] P399, only the range and intensity test items and the jump angle test items in the shooter test are indicated: in the jump angle test, 21 throwers are needed for one door type thrower; determining the watch setting jump requires the use of 3 artillery arms, which will require 63 ammunitions. The range and intensity test project requires 3-5 shooting angles for only one charge number, each shooting angle shoots 3 groups, and each group has 7 shots, namely 63-105 shots. The consumption of the ammunition accounts for more than half of the total consumption of the ammunition in the shooting test of the shooter.
The utility model provides a test method for researching the movement rule of the projected substance center and the movement rule around the mass center by science and technology personnel in the future.
[ document 5] the last paragraph of nature of P395 states: the firing schedule is a basic file for troops to use a weapon system to fight and train, and the firing schedule provides the ballistic data for carrying out shooting command and effectively playing the fighting effect of a firepower system, and the data comprises the corresponding relation table between the elevation angle of an artillery (rocket artillery) required for shooting a given target position under standard conditions, the shot direction and the target position, which is called a basic data element table;
the test jump angle in the jump angle test is composed of a jump angle of a standard projectile launcher and an aerodynamic jump angle of a standard projectile, and the aerodynamic jump angle changes with the target distance, so that the currently obtained test jump angle also changes with the target distance, and the shooting angle theta is compiled in a shooting table0，
Figure BDA0002931530640000181
Is the elevation angle of the standard catapult and meets the following requirements:
Figure BDA0002931530640000182
the firing angle is one of core data for compiling the firing table, so that if the jump angle is not accurate in the process of compiling the firing table, the compiled firing table is also not accurate.
In fact, prior art tests have only yielded the integrated intensity ESWithout obtaining the standard ejector density E1And system projectile concentration E2(ii) a And E1And E2It is exactly the task unit and the standard projectile manufacturing unit that are most hopefully known.
In order to distinguish the standard catapult and the composite catapult used in the utility model and the standard catapult in the prior art; the ejector used at present and ready for inspection is called a standard ejector, the composite projectile is a novel combined composite projectile, and the standard projectile in the prior art is the source of the component two 2 in the composite projectile.
Supplementary explanation the theoretical basis of the utility model:
the standard projectiles prepared by the standard projectiles are all long circular rigid bodies, and the flight tracks of the long circular rigid bodies in the air after the standard projectiles leave the muzzle are composed of two parts, namely the mass center motion of the long circular standard projectiles and the centroidal motion around the mass center generated by the included angle between the elastic axis of the standard projectiles and the flight speed vector line of the standard projectiles; thus, the density of the drop points comprises the density of the standard catapult and the standard catapult;
the utility model changes the long round type standard projectile in the prior art into a composite projectile, and the composite projectile comprises the following components: a homogeneous spherical body (namely a component I1) and a component II 2 obtained by transforming or imitating a standard projectile; after the composite projectile flies out of the body tube of the standard projectile, the component I1 can fly independently, the axis of the homogeneous spherical body as the component I1 is always coincident with the direction of the motion velocity vector, and the motion nutation angle is zero; the homogeneous spherical body as component one 1 is a rigid projectile which can be considered as a particle moving in air; therefore, the motion trail of the component I1 can be accurately described by particle motion differential equations; the method is calculated based on the vacuum trajectory when the jump angle is calculated, and the actual engineering application needs to process according to the air trajectory; the differential equation of particle motion for air trajectory is shown in equation (3.2.2) in 3.2.1 of [ document 5] P76 and its associated explanation.
The test method of the concentration is as follows: firstly, endowing a shooting angle, a shooting direction and an initial speed to a standard catapult, and launching a composite projectile; after the projectile hits a target, measuring the coordinates of the impact points of the projectile, wherein one shooting angle generally shoots 3 groups, and each group shoots 5-10 projectiles; the drop point spread follows a normal distribution;
the elevation angle in the shooter is the difference between the shooting angle and the jump angle. The jump angle is thus an important parameter in the compilation of a shooter. The jump angle given by the current jump angle test is the sum of the artillery jump angle and the aerodynamic jump angle of the projectile. The aerodynamic jump angle of the projectile is changed with the target distance, so that the jump angle given in the current firing schedule is not the included angle between the upward line and the ray. The shooting accuracy of the shooter will be greatly reduced. The utility model solves the technical problem and fills the blank of the related technology; it must have pioneering significance in the related technical field and the extended engineering application field.
Drawings
The utility model is described in further detail below with reference to the following figures and embodiments:
figure 1 is a schematic diagram of the principle of application of the composite projectile for rifles with a first assembly 1 in front;
figure 2 is a schematic diagram of the principle of application of the composite projectile for rifles with a first assembly 1 in front;
figure 3 is a schematic sketch of the principle of application of a composite projectile for a smoothbore projectile with a first assembly 1 in front;
figure 4 is a schematic diagram of the application principle of the composite projectile for the thread chamber projectile with the assembly one 1 at the back;
figure 5 is a schematic diagram of the principle of application of the composite projectile for the smoothbore projectile with the assembly 1 behind.
Detailed Description
The reference numerals have the following meanings: component one 1, component one A1.1 and component one B1.2; a second component 2, a warhead oval part 2.1, a centering part 2.2, a cylindrical part 2.3, a belt part 2.4, a tail part 2.5, a head screw 2.6, a closed air ring 2.7, a tail wing 2.8 and a tail pipe 2.9; a launching power structure 3, a cartridge 3.1 (hatching is omitted and not shown), a propellant powder 3.2, a basic cartridge 3.2.1 and an additional cartridge 3.2.2; primer 3.3 and a bullet baffle 3.4; a barrel 4.
In FIG. 2, there are 2 modules-1, the higher density module is located closer to the front outlet of the emitter;
in the various embodiments of the utility model, the material of the homogeneous spherical projectile is metallic copper, as not illustrated.
Example 1 method for determining the intensity of a large bore line-chamber projectile individually
1.1 purpose of the test: the large bore line chamber projectile concentration was determined (see figure 1).
1.2 test equipment:
1.2.1 line-chamber projectile apparatus [ reference 4] P11 in the characteristics of the projectile of standard 1-1, the gun with the diameter d of 0.130 m is added with 130 mm of serial number 12. The launching type projectile is a killing blasting bomb, and the mass of the standard bomb is Mt which is 33.4 kg.
1.2.2 the launching power system is composed of a cartridge 3.1 of (component three 3) standard projectile, a launching powder 3.2, a primer 3.3 (both the launching powder 3.2 and the primer 3.3 are standard) and the like;
1.2.3 the composite projectile is composed of a first component 1 and a second component, wherein the first component 1 is arranged in front of the second component 2;
1.2.4 the configuration structure of the barrel, the projectile and the launching power system is shown in the attached figure 1;
1.3 estimating the flight state parameter K of the projectile: (in the present invention, q and m are both mass.)
1.3.1 Components one 1 are homogeneous, solid spheroids with different densities and the mass m in Table 11Since the known projectile has a mass of 33.4kg (kg). The second component 2 is a hollow cylindrical rotating body made of carbon steel, and the modification method comprises the following steps:
first, the bullet nose oval portion of the standard projectile is removed, leaving the other portions of the standard projectile, such as the centering portion, the cylindrical portion, the band enclosing the propellant gas, and the tail portion of the projectile in combination with the cartridge;
secondly, removing the explosive in the projectile body, and adding a head screw in front of the foremost centering part to separate the homogeneous spherical body from the projectile body after the inner cavity is turned;
thirdly, the mass of the balance weight of the turned inner cavity, the head bolt 2.6 and the assembly I1 is m of the table 12；m2＝Mt-m1
1.3.2 Elastoid coefficient i of attachment-1 of standard air resistance law with spherical body 11, the hollow cylinder rotation body takes a spherical body as a component II 2 of the standard air resistance law2Should be greater than 1.
1.3.3 estimating the flight state parameter K of the projectile:
flight state parameter K:
Figure BDA0002931530640000201
1.3.4 the flight state parameters of different materials are shown in table 1, and it can be seen from table 1 that only the material tungsten satisfies that the flight state parameter K is greater than 1, namely when the projectile flies away from the muzzle of the projectile, the first component 1 is in front, and the second component 2 is behind, which are not interfered with each other;
1.3.5 protocol No. 1 was selected for this example. The first component 1 is made of solid homogeneous material tungsten with mass m118.98kg, the modified component II 2 is made of carbon steel, and the modified mass m2It was 14.42 kg. The flight state parameter K is more than 1, the first component 1 is in front, the second component 2 is behind, and the third launching power system component 3 is immediately behind.
TABLE 1
Scheme number 1 2 3 4 5 6
Name of Material Tungsten Brass Carbon steel Malleable cast iron Super hard aluminum Nylon
Density (g/cc) 16.5 8.8 7.8 7.2 2.9 1.11
Assembly 1 homogeneous spherical body mass m1(kg) 18.98 10.12 8.97 8.28 3.34 1.15
Counterweight mass m of component two 22(kg) 14.42 23.28 24.43 25.12 30.06 32.25
m1/m2 1.316 0.435 0.367 0.330 0.111 0.036
Flight state parameter K of different materials ＞1.316 0.435 0.367 0.33 0.11 0.036
1.4 Experimental methods and data processing overview
1.4.1 shooting tests and data processing were carried out in accordance with reference [ article 7] P94, subsection 3.6 "shooting test for determining drop point trajectory (range, concentration test)";
1.4.2 determining the purpose of the test according to 1.1, preparing test equipment according to 1.2, estimating a flight state parameter K according to 1.3 and making a test implementation plan;
1.4.3 installing a high-speed camera at the start of trajectory, monitoring the separation of the first module 1 and the second module 2. Ensuring that the first component 1 and the second component 2 do not interfere with each other.
1.4.4 testing shooting angle, initial speed, chamber pressure and meteorological conditions, and measuring the resistance coefficients of the first component 1 and the second component 2 by using a Doppler radar;
1.4.5) checking whether the initial speed and the chamber pressure corresponding to the charge are satisfactory or not. The selective charge test is carried out, and the charge omega is generally selected between the charge of the system propellant and the charge of the system forced charge. And has the following components: omega-omega0+Δω
In the formula: omega0The dosage of the standard medicine is the dosage of the standard medicine,Δomega is the correction amount of the standard charging;
1.4.6 recovering the homogeneous spherical body of the impact point, checking the ovality of the homogeneous spherical body and ensuring that the homogeneous spherical body is in the flying process; to determine the validity of the data;
1.4.7 shooting 10 shots in each group, measuring the coordinates of the falling points of the homogeneous spherical body, and calculating the concentration of the falling points of the component I1, wherein the concentration is the concentration of the chamber catapult.
Example 2 method for determining the concentration of a line-chamber type catapult alone (component one 1 being two metal balls)
2.1 purpose of the test: the large bore line chamber projectile concentration was determined (see figure 2).
2.2 test equipment:
2.2.1A linear chamber projectile launcher is selected from P11 of [ document 4] d, characteristics of projectile of Standard 1-1, 130 mm Cannon with serial number 12, and the caliber d is 0.130 m. The launching type projectile is a killing blasting bomb, and the mass of the standard bomb is Mt which is 33.4 kg.
2.2.2 the power module component 3 consists of a cartridge 3.1 of standard projectile, standard propellant powder 3.2 and standard primer 3.3;
2.2.3 composite projectile comprised of assembly one 1 and assembly two, assembly one 1 before assembly two after, because metal tungsten is noble metal, change assembly one 1 in embodiment 1 into being made up of two homogeneous metal balls, the material of homogeneous metal ball at the forefront is marked as assembly one A1.1 by brass, and the material of metal ball at the back is marked as assembly one B1.2 by carbon steel, their weight is seen in Table 1 as m respectively1.110.12kg, and m1.2When the weight of the second module 2 is 8.97kg, the weight of the second module is m2＝14.31kg；
2.2.4 the second component 2 is also divided into two parts, wherein one part is adjacent to a homogeneous metal ball made of carbon steel and weighs m with the head screw2.18 kg. The second part comprises a belt of sealed gunpowder gas with weight m2.2See fig. 2 for a schematic of 6.31 kg.).
2.2.5 the structural configuration of the barrel, the projectile and the launching power system is shown in the attached figure 2;
2.3 estimating the flight state parameter K of the projectile: (in the present invention, q and m both mean mass)
2.3.1 flight State parameter K of component one A1.1 and component one B1.2 is here in particular K21：
Figure BDA0002931530640000211
The first component A1.1 and the first component B1.2 are homogeneous spherical bodies, and are opposite to each otherThe shape is the same as the elastic coefficient of the standard air resistance law and is 1, and the mass of the component I A1.1 in the formula is m1Mass m of module one B1.2, 10.12kg28.97kg, so the flight status parameter K21Greater than 1, component one a1.1 is forward and component one B1.2 is rearward. The two do not interfere with each other.
2.3.2 estimation of flight State parameters K for the first component B1.2 and the second first component 2
The first component B1.2 is a homogeneous spherical body, the elastic coefficient of the first component B1.2 is 1 relative to the spherical body which is taken as the standard air resistance law, and the mass of the first component B1.2 in the formula is taken as m1Mass m of the second module 2, 8.97kg2The flight state parameter K is greater than 1, component one B1.2 leading and component two 2.12 trailing, 8 kg. They do not interfere with each other
2.3.3 flight State parameter K estimation of two assemblies two 2 in Table 2
As seen from table 2: the two assemblies 2 are carbon steel metal cylinder rotation bodies, the elastic coefficients of the two assemblies can be considered to be similar, and the mass of the former assembly 2 is taken as m1Mass m of the latter module 2, 8kg2The flight state parameter K should also be greater than 1 if 6.31kg, and the first module two 2 is in front of the second module two 2, which is matched with the module one 1, and the two modules should not interfere with each other. The front and back flying sequence of the two can be judged from the high-speed shooting result, if the two interfere with each other, the interference does not influence the test result.
The results of the evaluation are shown in Table 2, and the projectile system is schematically shown in FIG. 2.
2.4 test methods and data processing overview
2.4.1 shooting tests and data processing were carried out according to reference [ article 7] P94, subsection 3.6 "shooting test for determining drop point trajectory (range, concentration test)";
2.4.2 preparing test equipment according to the test purpose determined by 2.1 and a test implementation plan according to 2.2 and estimating a flight state parameter K according to 2.3;
2.4.3 installing a high-speed camera at the initial stage of trajectory, monitoring the separation of the first assembly 1 and the second assembly 2. Ensuring that the first component 1 and the second component 2 do not interfere with each other.
2.4.4 testing the firing angle, the initial speed and the chamber pressure, and measuring the resistance coefficients of the first component 1 and the second component 2 by using a Doppler radar;
2.4.5 checking whether the initial speed and the chamber pressure corresponding to the charging amount are satisfactory or not, if not. The selective charge test is carried out, and the charge omega is generally selected between the charge of the system propellant and the charge of the system forced charge. And has the following components: omega-omega0+Δω
In the formula: omega0The dosage of the standard medicine is the dosage of the standard medicine,Δomega is the correction amount of the standard charging;
2.4.6 recovering the homogeneous spherical body of the impact point, checking the ovality of the homogeneous spherical body and ensuring that the homogeneous spherical body is in the flying process; to determine the validity of the data;
2.4.7 shooting on ground target, measuring the coordinates of the falling points of the homogeneous spherical body, and calculating the density of the falling points, which is the density of the chamber catapult.
The corresponding range of the copper balls is X1, and the density is E11The range of the metal carbon steel ball is X2Concentration of E12Then the density of the ejector is: e1＝(E11/X1+E12/X2)/2
TABLE 2 estimated results of flight State parameters K
The arrangement order from the muzzle Component 1.1 Component one B1.2 First assembly 2 Second module 2
Component configuration Ball with ball-shaped section Ball with ball-shaped section Cylindrical rotary body Cylinder rotating body with elastic belt
Component material Homogeneous brass ball Homogeneous carbon steel ball Carbon steel Carbon steel
Density (g/cc) 8.8 7.8 7.8 7.8
The masses m (kg) of the components 10.12 8.97 8 6.31
Spring constant of each component i 1 1 ＞1 ＞1
m1/m2 10.12/8.97 8.97/8 8/6.31
Estimate K ＞1.128 ＞1.121 ＞1.268
The elastic coefficient of the cylindrical rotating body is larger than that of the homogeneous spherical body in calculation, and the elastic coefficient of the homogeneous spherical body is equal to 1, i2I > 1 but calculated from this table2Taking 1;
2.5 the rest of the description is the same as example 1 and is omitted here.
Example 3 method example for determining the standard projectile and the standard projectile intensity simultaneously
3.1 purpose of the test: the concentration of the large bore line-bore projectile and projectile was determined (see figure 4).
3.2 test equipment:
3.2.1 the linear chamber projectile was selected from the list of "article 4" P11 "characteristics of projectile of standard form 1-1" in table 1, with a gun diameter d of 0.130 m, 130 mm, with a serial number of 12. The launching type projectile is a killing blasting bomb, and the mass of the standard bomb is Mt which is 33.4 kg.
3.2.2 the standard weight of the known projectile of the shooting type was Mt 33.4 kg. The bullet weight of the qualified bullet is within +/-4 bullet weight symbols. The heaviest weight is 34.402 kilograms, the lightest weight is 32.398 kilograms,
3.2.3 the launching power system consists of a cartridge 3.1 of a projectile (component three 3), a propellant powder 3.2 and primer 3.3; (propellant 3.2 and primer 3.3 are of the same type)
3.2.4 composite projectile Module 1 is a homogeneous spherical body of nylon, weight m1＝1.15kg；
3.2.5 composite projectile component two 2 is selected as ultra-light projectile of standard projectile with weight of 32.509 kg.
As shown in the quality classification symbol table 21-1 of the [ document 1] P465 table, the weight of the variation range of one shot weight classification symbol is as follows:
33.4×(±1/3％)＝±0.1113(kg)
the heaviest mass of the extra-heavy projectile is 33.4 x (1+0.03) ═ 34.402kg, the lightest mass of the extra-light projectile is 33.4 x (1-0.03) ═ 32.398kg, if the component two 2 is selected to shoot the extra-light projectile with the heavy mass grading symbol of "- - - -", the sum of the component one 1 and the component two 2 can not exceed 34.402kg, if the propellant charge of the original standard is still selected, the projectile system can still be ensured to keep the ballistic performance requirement of the original standard projectile system;
3.2.6 the first component 1 is tightly attached to the bottom of the second component 2 and is tightly contacted with the tail part of the second component 2. The second composite projectile component 2 is in front of the first component 1;
3.2.7 the sum of the weights of the first assembly 1 and the second assembly 2 is 1.15kg +32.398kg, which is 33.548kg, and a bullet stopping structure for positioning the first assembly 1 is added to the oblique shoulder part of the standard cartridge of the manufacturing projectile, and the structure can be a bullet stopping plate, or a groove is processed on the oblique shoulder part of the standard cartridge of the manufacturing projectile, so as to position the first assembly and prevent the first assembly 1 from colliding with the second assembly to cause the chamber explosion. The weight of the structure cannot exceed 0.854 kg.
3.2.8 the propellant charge adopts standard type propellant charge, this embodiment is carried out without changing the propellant charge amount of the type charge;
3.3 calculating flight State parameters
3.3.1 calculating the spring modulus of the first spherical element
The bullet shape coefficient i of the spherical bullet according to the law of resistance of the spherical bullet 11, spring form coefficient i according to 43 years' law of resistance1＞1。
3.3.2 determining the spring shape factor of the ultra-light-weight and elastic component II
According to the experiment, according to the air resistance law of 1943, the ballistic coefficient of the second extra-light bullet component is 0.471, and the bullet shape coefficient of the second extra-light bullet component is 0.93 and is approximately 1. (derived from [ document 4]]P11 Table 1-1). The resistance coefficient of the spherical bullet is larger than that of the 43-year resistance law,the elastic coefficient of the second component 2 is smaller than that of the first component; therefore, the elastic coefficient of the spherical bullet is larger than that of the second component 2; i.e. i1＞i2。
3.3.3 calculating flight status parameters:
Figure BDA0002931530640000231
the material selected for the component I1 is nylon with mass m11.15kg, the second component has a mass m2＝32.398kg；
According to the air resistance law of the spherical bullet, the bullet shape coefficient i of the second component 22Must be much smaller than the spring constant i of component 11The calculation results are shown in Table 3;
3.3.4 this embodiment chooses scheme 6, and flight state coefficient K is far less than 1, and the subassembly two 2 is preceding, and subassembly one 1 is back, and subassembly two 2 can not disturb the motion of subassembly one 1.
3.4 summary of test methods and data processing:
3.4.1-3.4.6 same as example 1
3.4.7 shooting 10 shots in each group, respectively measuring the landing point coordinates of the homogeneous spherical body and the ultra-light bullet, and simultaneously calculating the impact point density of the component I1 and the component II 2 based on the range.
3.4.8 the concentration of component two 2 measured in this test is the comprehensive concentration recorded as ESThe concentration of the component 1 is the concentration of the standard catapult and is recorded as E1；
3.4.9 the method for solving the component two 2 density is as follows: assuming the concentration of the standard catapults is E1The density of the standard projectile is E2The combined concentration of the two is ES. Consider concentration E1、E2Both are independent random variables. Then the relationship between them is as follows: es 2＝E1 2+E2 2
The density of the standard projectiles was as follows: e2 2＝ES 2-E1 2
TABLE 3
Scheme number 1 2 3 4 5 6
Name of Material Tungsten Brass Carbon steel Malleable cast iron Super hard aluminum Nylon
Density (g/cc) 16.5 8.8 7.8 7.2 2.9 1.11
Assembly one (1) homogeneous spheroid mass m1(kg) 18.98 10.12 8.97 8.28 3.34 1.15
The second component (2) is selected to have a super-light bullet mass m2(kg) - - - - - 32.398
m1/m2 - - - - - 0.035
K - - - - - ＜0.035
Example 4 an example of determining the concentration of vertical targets for a small bore line-bore projectile (see figure 4)
4.1 purpose of the test: and determining the vertical target density and jump angle of the line chamber type catapult of the 12.7 mm large-caliber machine gun.
4.2 test equipment:
4.2.1 the linear chamber type projectile is a standard linear chamber type projectile, a 12.7 mm large-caliber machine gun with the serial number 3 in [ document 4] P11 [ characteristics of standard projectiles in Table 1-1 ] is selected, the caliber d is 0.0127 mm, the ballistic coefficient is 3.155 according to the air resistance law in 1943, and the bullet shape coefficient is 0.94. The known projectile of the launching system is a standard projectile of armor-piercing combustion projectile, and the weight of the standard projectile is
Mt＝0.0483kg；
The standard weight of the known projectile of the projectile type is 0.0483 kg. The qualified bullet weight should be within ± 4 bullet weight symbols. The heaviest weight is 0.0497kg, the lightest weight is 0.0469kg,
4.2.2 the launching power system is composed of a cartridge 3.1 of a standard projectile (component three 3), a standard propellant powder 3.2 and a standard primer 3.3;
4.2.3 composite projectile Module 1 is a homogeneous spherical body of nylon, having a weight m1＝0.00119kg；
4.2.4 selecting the composite projectile component II 2 as an ultra-light projectile of a standard projectile, wherein the weight is 0.0469 kg; the total weight of the two is 0.0481 kg;
(the bullet weight of the light projectile mass symbol is 0.482-0.0478kg, the bullet weights of the light two projectile mass symbols are 0.0478-0.0477kg, the bullet weights of the light three projectile mass symbols are 0.477-0.0472kg, and the bullet weights of the light four projectile mass symbols are 0.0472-0.0469 kg; similarly, the weight of the super-heavy bullet is 0.0497kg, the maximum difference of the weights is 0.0028 kg., so that the component 1 is a nylon ball with the weight of 0.00119kg, the component 2 is a super-light bullet with the weight of 0.0469 kg.. in the above, the first component is a nylon ball with the weight of 0.00119kg, the second component is a projectile with the standard weight, the second component with the weight of 0.0481 kg. is in front, the first component is in back. (note: if the second component 2 is a super-light bullet, the nylon ball can be a rigid ball with the maximum weight of 0.0028 kg)
4.2.5 the first component 1 is tightly attached to the bottom of the second component 2 and is tightly contacted with the tail part of the second component 2. The second composite projectile component 2 is in front of the first component 1;
4.2.6 the sum of the weights of the component I1 and the component II 2 is 0.0481kg, a bullet stopping structure for positioning the component I1 is added on the oblique shoulder part of the standard cartridge of the manufactured projectile, the structure can be a bullet stopping plate, and a groove can also be processed on the oblique shoulder part of the standard cartridge of the manufactured projectile, so as to position the component I and prevent the component I1 from colliding with the component II to cause the explosion.
4.3 estimating the flight state parameter K of the projectile:
the flight state parameter table of the component I and the component II with the same caliber is as follows:
Figure BDA0002931530640000251
according to experiment, the second component 2 has a ballistic coefficient of 3.155 and a bullet shape coefficient of 0.94 according to the air resistance law of 1943. The resistance coefficient of the spherical bullet is larger than that of the 43-year resistance law, and the bullet shape coefficient of the component II 2 is smaller than that of the component I; therefore, the elastic coefficient of the spherical bullet is larger than that of the second component 2; i.e. i1＞i2. Scheme No. 6 was selected for this example. The mass of the second component 2 is greater than the mass of the first component 1. Obviously, the flight state parameter K is less than 1, and the calculation result is shown in Table 4. Namely, the second component is in front of the first component, and the first component is behind the second component, so that the first component does not interfere with the movement of the second component. The projectile system is schematically shown in figure 4
4.4. The test method for intensity is summarized:
4.4.1 tests and data processing were carried out according to the 3.7 "upright test" of reference [ 7] P104:
4.4.2-4.4.7 same as 1.4.2-1.4.7 of example 1
TABLE 4
Scheme number 1 2 3 4 5 6
Name of Material Tungsten (W) Brass Carbon steel Malleable cast iron Super hard aluminum Nylon
Density (g/cc) 16.5 8.8 7.8 7.2 2.9 1.11
Assembly 1 homogeneous spherical body mass m1(kg) 0.01769 0.009435 0.008363 0.007719 0.00311 0.00119
Mass m of 2 super-soft component2(kg) - - - - - 0.0469
m1/m2 - - - - - 0.0254
K - - - - - ＜0.0254
Example 5 example of determining jump angle and jump angle concentration of a medium caliber linear bore antiaircraft gun projectile
5.1 purpose of the test: determining jump angle and jump angle concentration of standard catapult
5.2 test equipment:
5.2.1 selecting 2 standard 57mm high-fire cannons with serial number 6 in the characteristics of the standard shot in the table 1-1 of the [ document 4] P11 by the projectile launcher, wherein the standard shot is thrown into a glowing killing grenade with the same caliber, and the weight Mt of the standard shot is 2.8 kg;
5.2.2 the launching power system is composed of a cartridge 3.1 of a standard projectile (component three 3), a standard propellant powder 3.2, a standard primer 3.3 and the like;
5.2.3 the homogeneous spherical projectile assembly 1 of this patent is made of metallic tungsten with a mass of about m1＝1.599kg；
5.2.4 sealing the second component 2 of the gunpowder gas, selecting a modified standard projectile, and as shown in the attached figure 1, the modification method comprises the following steps:
first, the bullet fuze and the ovoid portion of the standard projectile are removed, leaving the other portions of the standard projectile, such as the centering portion, the cylindrical portion, the belt enclosing the propellant gas, and the tail portion associated with the cartridge;
secondly, removing the explosive in the projectile body, and adding a head screw in front of the foremost centering part to separate the homogeneous spherical body from the projectile body after the inner cavity is turned;
thirdly, the mass of the bullet and the head screw after turning the inner cavity is m2＝1.201kg。
5.3 estimating the flight state parameter K of the composite projectile: (q and m each represents a weight)
5.3.1 the spring shape coefficient i of a ball-shaped bullet taking the ball-shaped bullet as the standard resistance law 11, the spring constant i of the second component 22Is certainly larger than the elastic modulus of the component I1; i.e., greater than 1;
5.3.2 estimating flight State parameters K
The flight state parameter table of the component I and the component II with the same caliber is as follows:
Figure BDA0002931530640000261
the second component 2 is a hollow cylindrical rotating body i2Greater than the elastic modulus i of a homogeneous sphere1，i1Scheme No. 1 is selected for this example. m is1＞m2The flight state coefficient K is larger than 1, the component I1 is in front of the component II 2, and the component II 2 cannot interfere with the motion of the component I1.
5.4 test methods and data processing overview:
5.4.1 test methods in addition to the tests and data processing according to the "test for determination of the Angle of jump" method of reference [ 7] P87, subsection 3.4, the following should be used:
5.4.2-5.4.7 same as in example 1.4.2-1.4.7
TABLE 5
Scheme number 1 2 3 4 5 6
Name of Material Tungsten Brass Carbon steel Malleable cast iron Super hard aluminum Nylon
Density (g/cc) 16.5 8.8 7.8 7.2 2.9 1.11
Mass m of attachment 11(kg) 1.599 0.853 0.756 0.698 0.281 0.1076
Mass m of the attachment 22(kg) 1.201 1.947 2.044 2.102 2.519 2.6924
m1/m2 1.331 0.438 0.3698 0.3320 0.1115 0.0400
K ＞1.331 ＞0.438 ＞0.3698 ＞0.3320 ＞0.1115 ＞0.0400
EXAMPLE 6 method for determining the intensity of a smoothbore type catapult alone (mortar)
6.1 purpose of the test: the piston chamber system catapult density was determined separately (see fig. 3).
6.2 test equipment:
6.2.1 smooth-bore type projectile is a standard smooth-bore type projectile, and the caliber of a standard projectile with the serial number 15 of ' the characteristics of standard projectiles in table 1-1 ' of document 4 ' P11 is selected to be 0.082 m. The standard mass of the standard projectile was 3.10 kg.
6.2.2 the launching power system adopts the launching power system of the original standard projectile;
6.2.3 the homogeneous spherical projectile of this example was made of metallic carbon steel with a mass of about 2.251kg, as shown in Table 6;
6.2.4 sealing the second component 2 of the gunpowder gas, and selecting a modified standard projectile; the mass was 0.849 kg. The structure is as shown in a schematic diagram 1, and the modification method comprises the following steps:
firstly, removing the bullet oval part of the standard projectile and reserving other parts of the standard projectile;
secondly, removing the explosive in the projectile body, and adding a head screw in front of the foremost centering part to separate the homogeneous spherical body from the projectile body after the inner cavity is turned;
thirdly, the mass of the projectile body and the head screw after the inner cavity is turned is about 0.849 kg;
fourthly, in order to ensure the shooting safety, the primer can be changed into an electric shock primer.
6.3 calculating flight State parameters
Calculating the weight m of an accessory 1 of several different density materials1In order to make the weights of the first accessory 1 and the second accessory 2 3.1058kg, the weights of the weighted accessories 2 are as shown in the following table m2. Since the second component is made of carbon steel material, the material of the first component 1 is also made of carbon steel12.251kg, mass m of second modified module 22＝0.849kg。
Spherical bullet shape coefficient i of spherical bullet using spherical bullet as standard resistance law 11, the second component 2 taking the spherical ball as the law of resistance is the elastic coefficient i of the hollow cylinder rotating body2Is certainly larger than the elastic modulus of the component I1 and the elastic modulus i of the component II 22Greater than the elastic modulus i of a homogeneous sphere1，i1The flight state parameter table of the component 1 and the component 2 with the same caliber is as follows:
Figure BDA0002931530640000271
in the embodiment, the scheme No. 3 is selected, the flight state coefficient K is greater than 1, namely the component I1 is behind the component II 2, and the component II 2 cannot interfere with the movement of the component I1. The results are shown in Table 6, and the projectile system is shown schematically in FIG. 3.
6.4 summary of test methods and data processing:
6.4.1-6.4.7 are the same as 1.4.1-1.4.7 of example 1.
TABLE 6
Scheme number 1 2 3 4 5 6
Name of Material Tungsten Brass Carbon steel Malleable cast iron Super hard aluminum Nylon
Density (g/cc) (kg/cm)3) 16.5 8.8 7.8 7.2 2.9 1.11
Assembly 1 homogeneous spherical body mass m1(kg) 4.761 2.539 2.251 2.078 0.837 0.381
Counterweight mass m of component two 22(kg) - 0.561 0.849 1.022 2.263 2.719
m1/m2 - 4.256 2.651 2.033 0.370 0.140
Flight state parameter K of different materials - ＞14.256 ＞12.651 ＞12.033 ＞0.370 ＞0.140
Example 7 example for determining jump Angle and jump Angle Density of Standard catapult
7.1 purpose of the test: determining jump angle and jump angle concentration of standard catapult
7.2 test equipment:
7.2.1 the ejector is a brake type ejector corresponding to the embodiment of the utility model;
7.2.2 construction of the composite projectile one of the composite projectiles of examples 1-6 of the present invention may be selected;
7.3 test methods in addition to the tests and data processing according to the "angle jump test" method of reference [ 7] P87, 3.4, the following should be used:
7.3.1 clear purpose of the experiment
7.3.2 preparation of test devices
7.3.3 estimating a flight state parameter K and making a test implementation plan;
7.3.4 installing a high-speed camera at the initial stage of trajectory, monitoring the separation of the first assembly 1 and the second assembly 2. Ensuring that the first component 1 and the second component 2 do not interfere with each other.
7.3.5 testing the firing angle, the initial speed and the chamber pressure, and measuring the resistance coefficients of the first component 1 and the second component 2 by using a Doppler radar;
7.3.6 checks whether the initial velocity and chamber pressure corresponding to the charge are satisfactory or not. The selective charge test is carried out, and the charge omega is generally selected between the charge of the system propellant and the charge of the system forced charge. And has the following components:
ω＝ω0+Δω
in the formula: omega0The dosage of the standard medicine is the dosage of the standard medicine,Δomega is a correction to the standard chargeAn amount;
7.3.7 recovering the homogeneous spherical body with the impact point, checking the ovality to ensure that the spherical body is a homogeneous spherical body in the flying process; to determine the validity of the data;
7.3.8 each group emits 5-10 shots, shoots jump-angle targets, measures the impact point coordinates of the homogeneous spherical body, calculates jump-angle intensity and jump-angle, which are the intensity and jump-angle of the catapult.
And 7.4, calculating jump angles of the standard catapults, measuring the impact point coordinates of the close-range targets on the homogeneous spherical bodies, and calculating the intensity and the jump angles of the close-range targets. Calculating trajectory descending amount by adopting a vacuum trajectory;
and (3) calculating the jump angle of the 7.5 standard catapult, wherein the trajectory descent amount is coincidently calculated by adopting a projectile mass center motion differential equation system considering air resistance when a long-distance target is shot. See the standing target shooting test for concrete method.

Claims (4)

1. A compound projectile for confirming casting system intensity and jump angle precision, its characterized in that: it is formed by the combination of subassembly one (1) and subassembly two (2), wherein: the first component (1) is a homogeneous spherical body with the diameter same as that of the standard catapult, and is of a solid or hollow structure; the mass center of the first component (1) is coincident with the geometric center thereof and is at the spherical center; when the component I (1) moves in a medium, an included angle between the geometric axis of the component I (1) and a velocity vector line thereof is zero, and a motion track of the component I (1) leaving the standard catapult can be described by a particle motion differential equation with three degrees of freedom; the second component (2) is a revolving body structural member with the section consistent with the caliber of the standard catapult;
the mass of the composite projectile is the same as or similar to that of the standard projectile; the number of the first assemblies (1) is at least one.
2. Composite projectile for determining the intensity of the projecting system and the accuracy of the jump angle according to claim 1, characterized in that: the first component (1) is always in front of or behind the second component (2).
3. Composite projectile for determining the intensity of the projecting system and the accuracy of the jump angle according to claim 2, characterized in that: the composite projectile meets one or a combination of the following requirements:
firstly, the first component (1) is in front, the second component (2) is in back, and the mass sum of the first component (1) and the second component (2) is equal to the mass of the projectile in the original standard;
and secondly, the component I (1) and the component II (2) are independent or are combined structures consisting of a plurality of subassemblies.
4. Composite projectile for determining the intensity of the projecting system and the accuracy of the jump angle according to claim 2, characterized in that: the composite projectile meets one or a combination of the following requirements:
firstly, the first component (1) is at the back, the second component (2) is at the front, and the sum of the masses of the first component (1) and the second component (2) is less than or equal to the mass of the extra-heavy bullet of the original standard bullet;
and secondly, the component II (2) is a projectile extra-light projectile which can seal standard projectile gas, and the total mass of the component I (1) and the component II (2) in the composite projectile is not more than the extra-heavy projectile mass of the standard projectile.
CN202120305824.5U 2021-02-03 2021-02-03 Composite projectile for determining projectile system concentration and jump angle accuracy Active CN216482564U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202120305824.5U CN216482564U (en) 2021-02-03 2021-02-03 Composite projectile for determining projectile system concentration and jump angle accuracy

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202120305824.5U CN216482564U (en) 2021-02-03 2021-02-03 Composite projectile for determining projectile system concentration and jump angle accuracy

Publications (1)

Publication Number Publication Date
CN216482564U true CN216482564U (en) 2022-05-10

Family

ID=81394055

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202120305824.5U Active CN216482564U (en) 2021-02-03 2021-02-03 Composite projectile for determining projectile system concentration and jump angle accuracy

Country Status (1)

Country Link
CN (1) CN216482564U (en)

Similar Documents

Publication Publication Date Title
Hogg German Artillery of World War Two
US7207276B1 (en) Non-lethal ammunition utilizing a dense powder ballast and a two-stage firing sequence
CN216482564U (en) Composite projectile for determining projectile system concentration and jump angle accuracy
FACKLER et al. Wounding mechanism of projectiles striking at more than 1.5 km/sec
RU159193U1 (en) Shot with a shell simulator
CN113357977A (en) Method for determining casting system density and jump angle precision
US20120085259A1 (en) Cartridge for light-weighted projectiles
RU2399013C1 (en) Round for miniature firearm
CN110081783B (en) Low-damage shot-peening test bomb and recovery method thereof
WO2022040779A1 (en) Spotter ammunition projectile and method for making the same
US8919257B1 (en) 155 mm XM1126 testing/training projectile
US10443970B2 (en) Launch canister to simulate personal and anti-personnel armaments
Schumacher et al. Guided Hard-Launch Munitions: Enabling Advanced Air to Ground Combat
RU2770163C1 (en) Rifle cartridge for smoothbore weapons
Yarwood et al. Novel munition design for low-collateral damage weapons
FI130317B (en) Projectile
US11415398B2 (en) Gas favoring boattail projectile
Driscoll Japanese Ho-301 40 mm cannon and ammunition
RU2272238C1 (en) Set of training facilities
Fedaravicius et al. Development of Mortar Simulator with Shell‐In‐Shell System–Problem of External Ballistics
Roberts The US 37-mm Gun in World War II
Taraszewski et al. Small-caliber grenade projectile applicable to individual grenade launchers
Jasztal et al. Conceptual Design of a Reusable Submunition Dispenser for Unmanned Aerial Vehicles
Hardy et al. Novel Kinetic Effects Warhead Design for Air-to-Ground Munitions
Syroka Sniper Rifle Cartridge

Legal Events

Date Code Title Description
GR01 Patent grant
GR01 Patent grant