CN115451755A - Bullet-based launching device applied to fire-fighting mortar and parameter design method thereof - Google Patents

Bullet-based launching device applied to fire-fighting mortar and parameter design method thereof Download PDF

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CN115451755A
CN115451755A CN202211049416.3A CN202211049416A CN115451755A CN 115451755 A CN115451755 A CN 115451755A CN 202211049416 A CN202211049416 A CN 202211049416A CN 115451755 A CN115451755 A CN 115451755A
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pressure chamber
projectile
chamber
pressure
fire
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CN115451755B (en
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何志一
杨国来
吴清乐
孙全兆
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Nanjing University of Science and Technology
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Nanjing University of Science and Technology
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
    • F41F1/06—Mortars
    • A—HUMAN NECESSITIES
    • A62—LIFE-SAVING; FIRE-FIGHTING
    • A62C—FIRE-FIGHTING
    • A62C19/00—Hand fire-extinguishers in which the extinguishing substance is expelled by an explosion; Exploding containers thrown into the fire
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

Abstract

The invention discloses a bullet-based launching device applied to a fire-fighting mortar and a parameter design method thereof, wherein the device comprises a projectile body, a propellant powder, a reverse high-pressure chamber, a primer, a fuel gas leakage hole and a powder chamber; the inverted high-pressure chamber is divided into two chambers with different pressures by a bottom plate, the chamber close to the projectile body is the high-pressure chamber, and the other pressure chamber is the low-pressure chamber; wherein the medicine chamber and the propellant powder are arranged in the high-pressure chamber; the primer is arranged in the threaded through hole at the bottom of the high-pressure chamber through a thread pair, is communicated with the explosive chamber and the low-pressure chamber, and can ignite the propellant powder in the explosive chamber after being impacted and triggered by a firing pin at the tail part of a gun; the elastic rear body tube and the bottom surface of the high-pressure chamber jointly form a low-pressure chamber; the bottom plate is provided with a gas leakage hole, and after the gas leakage hole is emitted, the inverted high-pressure chamber and the projectile body are ejected out of the body pipe together. The invention expands the application occasions of the mortar, solves the problem of low overload launching of the mortar and has higher engineering significance.

Description

Bullet-based launching device applied to fire-fighting mortar and parameter design method thereof
Technical Field
The invention relates to the field of fire fighting, in particular to a shell-based launching device applied to a fire-fighting mortar and a parameter design method thereof.
Background
The fire-fighting mortar is one of civil fields, and the shot is improved on the basis of the structure of the traditional mortar, so that the fire-fighting mortar can realize the purpose of extinguishing fire after being thrown and exploded. The fire-fighting mortar is mainly used for urban and forest fire fighting. In practical application, after the fire mortar has launched the fire mortar and has forced the bullet, there is the demand of assessing again the scene of a fire, and at this moment additional unmanned aerial vehicle system of reuse can increase the burden of front-line fire control undoubtedly, if at this moment can utilize current mortar system transmission photoelectric detection original paper to accomplish the real-time aassessment to the scene of a fire and then guide the front-line fire control, can alleviate the burden of front-line fire control, more simple and convenient acquisition scene of a fire information, accomplish information-based fire control. However, civil photoelectric elements often cannot bear high emission overload of a common fire-fighting mortar, and the problem of emission overload becomes the first difficult problem of the photoelectric detection element emitted by the mortar.
Disclosure of Invention
The invention aims to provide a bullet-based launching device applied to a fire-fighting mortar and a parameter design method thereof, which realize the compatibility of the mortar and a low-overload launching platform on the premise of not influencing the structure of the original mortar, simultaneously reduce the launching overload born by launching special bullets containing photoelectric elements and avoid the irreversible damage of the special bullets.
The technical solution for realizing the purpose of the invention is as follows:
a bullet-based launching device applied to a fire-fighting mortar comprises a bullet body, a launching powder, a reverse high-pressure chamber, a primer, a fuel gas leakage hole and a powder chamber; the inverted high-pressure chamber is divided into two chambers with different pressures by a bottom plate, the chamber close to the projectile body is the high-pressure chamber, and the other pressure chamber is the low-pressure chamber; wherein the medicine chamber and the propellant powder are arranged in the high-pressure chamber; the primer is arranged in the threaded through hole at the bottom of the high-pressure chamber through a thread pair, is communicated with the explosive chamber and the low-pressure chamber, and can ignite the propellant powder in the explosive chamber after being impacted and triggered by a firing pin at the tail part of a gun; the elastic rear barrel and the bottom surface of the high-pressure chamber jointly form a low-pressure chamber; the bottom plate is provided with a gas leakage hole, and after the gas leakage hole is emitted, the inverted high-pressure chamber and the projectile body are ejected out of the body pipe together.
Furthermore, the reverse high-pressure chamber and the projectile body are connected by a thread pair, the launched reverse high-pressure chamber and the projectile body are ejected out of the body pipe together, and low-overload high-low-pressure launching of the photoelectric detection element is completed while the conventional fire-fighting mortar projectile explosive launching is not influenced;
furthermore, the explosive tube and the emission primer are connected with the reverse high-pressure chamber through a thread pair;
furthermore, the primer is made of high-pressure-resistant materials so as to prevent ignition during screwing.
A parameter design method for a fire-fighting mortar shell-based launching device comprises the following steps:
step 1, determining the maximum overload borne by a mortar to launch a special projectile containing a photoelectric element, and setting the initial parameters of a projectile-based launching device structure;
step 2, calculating the combustion rate of the propellant after ignition according to the inner trajectory to obtain a pressure change curve of the high-pressure chamber;
step 3, solving a projectile motion rule at the initial launching stage and a projectile internal cavity pressure change rule after the projectile by taking a high-pressure chamber pressure change curve as a boundary condition through fluid dynamics numerical simulation;
step 4, judging whether the current bearing capacity meets the maximum overload borne by the special projectile or not based on the movement rule of the projectile at the initial launching stage and the pressure change rule of the inner cavity of the flow field after the projectile, and if so, determining the structural parameters of the projectile-based launching device; if the structural parameters of the missile-based launching device are not optimized and adjusted, and the steps are repeated.
Further, the combustion rate after ignition of the propellant in the step 2 can be expressed as
Figure BDA0003823280650000021
In the formula: z is the relative burning thickness of the gunpowder grains; t is time, U 1 Is a burning rate constant; delta 1 1/2 of the initial thickness of the powder grain; p is 1 Is the high pressure chamber pressure. The high pressure chamber pressure is:
Figure BDA0003823280650000022
in the formula: f is the efficacy of the fire and the drug; omega is the medicine loading amount; psi is the percentage of powder burned; rho p Is the density of gunpowder; alpha is the powder gas residual capacity; v 0 Is the volume of the high-pressure medicine chamber.
Wherein ψ and Z satisfy:
ψ＝χZ(1+λZ+μZ 2 )
in the formula: the selection of chi, lambda and mu is related to the shape of gunpowder, wherein square gunpowder is selected, and chi, lambda and mu are all 1.
Directly enters the low-pressure chamber in a gas flowing mode after the pressure change is generated in the high-pressure chamber, wherein the gas mass flow is as follows:
Figure BDA0003823280650000023
in the formula: psi 2 Is the flow coefficient; s. the j Is the area of the broken hole; p 2 Is the low pressure chamber gas pressure. When the gunpowder starts to burn, the pressure difference between the high-pressure chamber and the low-pressure chamber is changed, so that relative flow eta is generated, and the movement of the low-pressure chamber pressure boosting system is changed, wherein the relative flow eta is as follows:
Figure BDA0003823280650000031
the pressures in the high-pressure chamber and the low-pressure chamber after the flow is generated are respectively as follows:
Figure BDA0003823280650000032
Figure BDA0003823280650000033
in the formula: s is the section area of the transmitting tube, k is the thermal insulation coefficient, v, m are respectively specialSpeed and mass of the projectile, psi 3 Calculating coefficients, L, for the secondary work 0 The volume of the medicine chamber is necked long: the quotient of the initial volume of the low-pressure chamber and the cross-sectional area of the launch tube.
Compared with the prior art, the invention has the following remarkable advantages:
(1) The invention adopts the bullet-based low-overload launching design, and the high-pressure chamber in the traditional high-low pressure launching is inverted, and the inverted high-pressure chamber and the bullet body are combined into a whole, so that the invention can be suitable for the launching of the existing fire-fighting mortar barrel, and the high-low pressure launching can be completed on the premise of not changing the structure of the existing mortar barrel and not influencing the launching of the conventional ammunition;
(2) The invention adopts high-low voltage emission, reduces emission overload, simultaneously leads the bore pressure curve to be more saturated compared with the traditional emission bore pressure curve, ensures certain muzzle initial speed, and is suitable for low overload emission of a photoelectric detection element needing certain working altitude.
Drawings
FIG. 1 is a flow chart of the low overload launching device applied to a fire-fighting mortar platform according to the present invention.
Fig. 2 is a three-dimensional structure diagram of the missile-based launching device.
Fig. 3 is a schematic view of the structure of the inverted high-pressure chamber.
Fig. 4 is a half sectional view of an inverted high pressure chamber.
Figure 5 is a high chamber pressure time-varying curve based on internal ballistic.
Fig. 6 is a time-varying curve of shot displacement.
Fig. 7 is a plot of projectile velocity versus time.
Figure 8 is a time varying barrel bore pressure curve.
Detailed Description
The present invention is described in further detail below with reference to the attached drawing figures.
With reference to fig. 2 to 4, the bullet-based launching device applied to the fire-fighting mortar comprises a bullet body 1, a propellant powder 2, a reverse high-pressure chamber 3, a primer 4, a gas leakage hole 5 and a powder chamber 6. Wherein the medicine chamber 6 and the propellant 2 are arranged in the high-pressure chamber 7; the primer 4 is arranged in a threaded through hole 10 at the bottom of the high-pressure chamber through a thread pair, is communicated with the explosive chamber and the low-pressure chamber 8, and can ignite the propellant powder 2 in the explosive chamber 6 after being struck and triggered by a firing pin at the tail of a gun; the elastic rear body tube and the bottom surface of the high-pressure chamber jointly form a low-pressure chamber 8.
Further, the reverse high-pressure chamber 3 is connected with the projectile body 1 through a thread pair 9, the launched reverse high-pressure chamber 3 and the projectile body 1 are ejected out of the body pipe together, and low-overload high-low-pressure launching of the photoelectric detection element is completed while the launching of conventional fire-fighting mortar projectile charges is not influenced.
Further, the chamber 6 and the propellant charge 2 are connected to the counter high pressure chamber 3 by a screw pair 10.
Further, the primer 4 which can bear the chamber pressure of a high-pressure chamber of at least 100Mpa and does not leak gas is adopted to prevent the structure of the primer 4 from being damaged after the explosive deflagration to cause the leakage of gas.
As shown in figure 1, the parameter design method of the missile-based launching device applied to the fire-fighting mortar comprises the following steps:
step 1, determining the maximum overload borne by a mortar to launch a special projectile containing a photoelectric element, and designing the initial parameters of a projectile-based launching device;
step 2, calculating the combustion rate of the ignited propellant according to the inner trajectory to obtain a pressure change curve of the high-pressure chamber;
and 3, solving the motion rule of the projectile at the initial launching stage and the pressure change rule of the inner cavity of the flow field after the projectile through the hydrodynamic numerical simulation.
Step 4, judging whether the current bearing capacity meets the maximum overload borne by the special projectile or not based on the movement rule of the projectile at the initial launching stage and the pressure change rule of the inner cavity of the flow field after the projectile, and if so, determining the structural parameters of the projectile-based launching device; and if the structural parameters of the projectile-based launching device cannot be optimally adjusted, repeating the steps until the maximum overload which can be borne by the special projectile is met.
Further, in step 2, based on the inner trajectory, the burning rate of the gunpowder can be expressed as
Figure BDA0003823280650000041
In the formula: z is the relative burning thickness of the gunpowder grains; t is time, U 1 Is a burning rate constant; delta. For the preparation of a coating 1 1/2 of the initial thickness of the gunpowder grain; p 1 Is the high pressure chamber pressure. High pressure chamber pressure of
Figure BDA0003823280650000051
In the formula: f is the efficacy of the fire and the drug; omega is the drug loading amount; psi is the percentage of powder burned; ρ is a unit of a gradient p Is the density of gunpowder; alpha is the powder gas residual capacity; v 0 Is the volume of the high-pressure medicine chamber.
Wherein ψ and Z satisfy
ψ＝χZ(1+λZ+μZ 2 )
In the formula: the selection of chi, lambda and mu is related to the shape of gunpowder, wherein square gunpowder is selected, and chi, lambda and mu are all 1.
Directly enters the low-pressure chamber by means of gas flow after pressure change in the high-pressure chamber, wherein the gas mass flow is
Figure BDA0003823280650000052
In the formula: psi 2 Is the flow coefficient; s j Is the area of the broken hole; p 2 Is the low pressure chamber gas pressure. When the gunpowder starts to burn, the pressure difference between the high-pressure chamber and the low-pressure chamber is changed, so that the relative flow eta is generated, and the motion of the pressure boosting system of the low-pressure chamber is changed, wherein the relative flow eta is
Figure BDA0003823280650000053
The pressure of the high-pressure chamber and the low-pressure chamber after the flow is generated is respectively
Figure BDA0003823280650000054
Figure BDA0003823280650000055
In the formula: s is the cross section of the launching tube, k is the thermal insulation coefficient, v, m are the speed and mass of the special projectile respectively, psi 3 Calculating coefficients, L, for the secondary work 0 The volume of the medicine chamber is necked long: the quotient of the initial volume of the low-pressure chamber and the cross-sectional area of the launch tube.
Further, in step 3, a calculated time-varying curve of the pressure in the high-pressure chamber is set on the inner wall of the high-pressure chamber as a boundary condition, the corresponding time-varying curve of the pressure in the high-pressure chamber is specifically described in fig. 5, and a movement law of the projectile at the initial stage of launching and a pressure variation law of the inner cavity of the flow field after the projectile are obtained by using a fluid dynamics numerical simulation, which is specifically shown in fig. 6 to 8. Compared with the traditional structure, the projectile displacement of the inverted high-pressure cavity structure rises faster in the initial stage, and can make faster response to pressure change. The displacement is large at the initial stage of emission, and rises from 0.17m to 0.27m, and the increase is 60%. In addition, the velocity profile of the projectile tends to be flatter than in conventional configurations due to the presence of the double hump in the low pressure chamber.
It should be noted that the known methods related to the present invention are not described in detail, for example, the maximum overload that can be sustained, the law of the movement of the projectile in the initial stage, and the law of the pressure change in the inner cavity of the flow field after the projectile are not described in detail.
The low-overload launching device applied to the fire-fighting mortar provided by the invention realizes the compatibility of the mortar and a low-overload launching platform on the premise of not influencing the structure of the original mortar, reduces the launching overload born by launching special bullets containing photoelectric elements, avoids the irreversible damage of the special bullets, realizes low-overload launching in a bullet-based high-low pressure launching mode, is simple to realize and has good overload reduction effect.

Claims (10)

1. The missile-based launching device applied to the fire-fighting mortar is characterized by comprising a missile body (1) and an inverted high-pressure chamber (3) connected with the missile body (1), wherein the inverted high-pressure chamber (3) is divided into two chambers with different pressures through a bottom plate, the chamber close to the missile body (1) is a high-pressure chamber (7), and the other pressure chamber is a low-pressure chamber (8); the high-pressure chamber (7) is provided with a medicine chamber (6), the medicine chamber (6) is internally provided with propellant powder (2), the center of the bottom plate is provided with a through hole (10), and primer (4) is arranged in the through hole (10) and is communicated with the medicine chamber (6) and the low-pressure chamber (8); the bottom plate is provided with a gas leakage hole (5), and after the gas leakage hole is emitted, the inverted high-pressure chamber (3) and the projectile body (1) are ejected out of the barrel together.
2. The fire-fighting mortar applied to fire-fighting mortar of claim 1, wherein the reverse high-pressure chamber (3) and the projectile body (1) are connected by a thread pair (9), and the primer (4) is placed in the through hole (10) through the thread pair.
3. The projectile-based launching device applied to fire-fighting mortars according to claim 1, characterised in that the chamber (6) and the propellant charge (2) are connected to the base plate in the counter-pressure chamber (3) by means of a thread pair (10).
4. The projectile-based launching device applied to fire-fighting mortars according to claim 1, characterized in that a primer (4) is used which can withstand a high-pressure chamber pressure of at least 100Mpa and does not leak gas.
5. A method of designing parameters of a projectile-based launching device for fire-fighting mortars as claimed in any one of claims 1 to 4, characterized in that it comprises the steps of:
determining the maximum overload borne by a mortar to emit a special projectile containing a photoelectric element, and setting the initial parameters of the structure of a projectile-based emitting device;
calculating the combustion rate of the ignited propellant according to the inner trajectory to obtain a pressure change curve of the high-pressure chamber;
taking a pressure change curve of the high-pressure chamber as a boundary condition, and solving a projectile motion rule at the initial launching stage and a pressure change rule of a flow field inner cavity after the projectile through fluid dynamics numerical simulation;
judging whether the current bearing capacity meets the maximum overload borne by the special projectile or not based on the projectile motion rule at the initial launching stage and the pressure variation rule of the flow field inner cavity behind the projectile, and if so, determining the structural parameters of the projectile-based launching device; if the structural parameters of the missile-based launching device are not optimized and adjusted, and the steps are repeated.
6. The method of claim 5, wherein the burn rate is:
Figure FDA0003823280640000011
in the formula: z is the relative burning thickness of the gunpowder grains; t is time, U 1 Is a burning rate constant; delta 1 1/2 of the initial thickness of the gunpowder grain; p 1 Is the high pressure chamber pressure.
7. The parameter design method of the missile-based launcher according to claim 6, wherein the high pressure chamber pressure is:
Figure FDA0003823280640000021
in the formula: f is the efficacy of the fire and the drug; omega is the medicine loading amount; psi is the burned percentage of the gunpowder; ρ is a unit of a gradient p Is the density of gunpowder; alpha is the powder gas residual capacity; v 0 Is the volume of the high-pressure medicine chamber.
8. The parameter design method of the bullet-based launching device according to claim 7, wherein the percentage of burnt propellant psi and the relative burning thickness Z of the grains of gunpowder satisfy:
ψ＝χZ(1+λZ+μZ 2 )
in the formula: χ, λ, μ are constants related to the shape of the powder.
9. The parameter design method of the bullet-based launching device according to claim 8, wherein χ, λ, μ are all 1 for square gunpowder.
10. The method of claim 5, wherein the parameter of the missile-based launcher is the volume of the high pressure chamber.
CN202211049416.3A 2022-08-30 2022-08-30 Bullet-based launching device applied to fire-fighting mortar and parameter design method thereof Active CN115451755B (en)

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Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB166149A (en) * 1916-08-30 1921-07-11 Henry Newton Improvements in trench mortars and the like
US3505924A (en) * 1967-04-18 1970-04-14 Allied Res Ass Inc Silent mortar
CN2597939Y (en) * 2002-12-30 2004-01-07 曹文通 Improved structure of fire control shell
CN201637345U (en) * 2010-02-10 2010-11-17 中国船舶重工集团公司第七一三研究所 Sectional type gun tube
CN103940302A (en) * 2013-01-18 2014-07-23 滕德选 Remote projecting device with pressure maintaining following tool
CN111013058A (en) * 2019-12-04 2020-04-17 南京理工大学 Electromagnetic ejection type fire extinguishing bomb

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