CN115753179A - Firer actuated perforator for detecting section of planet - Google Patents
Firer actuated perforator for detecting section of planet Download PDFInfo
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Abstract
The invention discloses a firer-actuated perforating tool for detecting a planet section, which relates to the technical field of lunar soil water ice sample sampling and solves the problems that the penetration and pore-forming of a perforating bullet emitted by the perforating tool on a lunar soil water ice layer cannot meet the quality conditions of a sampling space and total load required by a sampler in the sampling process, and the leakage of combustion residues of the perforating bullet in the emission process causes pollution to in-situ lunar soil water ice and the like ‑19 And g, the product can be stored for a long time under the condition of low-temperature environment.
Description
Technical Field
The invention relates to the technical field of lunar soil water ice sample sampling, in particular to a firer actuated perforator for detecting a planet section.
Background
Since Watson et al first proposed the possibility of water ice on the moon in 1961, evidence of water ice substances in a permanently shaded area of the south pole of the moon was found by various means such as ground-based remote sensing, satellite-borne remote sensing and ground penetrating radar. In the process of sampling and detecting the lunar soil water ice structure of the lunar polar region, the lunar soil water ice sample is usually collected by adopting an impact drilling mode. However, for a high-strength lunar soil water ice structure, a single impact drilling sampling mode has low submerging efficiency and low speed, and cannot meet the index requirements of low power consumption and high speed of sampling detection operation under an environmental condition of an polar region. Therefore, the invention provides the low-power-consumption, high-efficiency and pollution-free firer-actuated perforator used in cooperation with a sampling detection machine, the dynamic penetration mode is adopted in the adopted process to realize penetration hole forming and crushing of high-strength lunar soil water ice, a channel is provided for the sampling detection of a subsequent machine, and meanwhile, the crushing action greatly reduces the strength of lunar soil water ice texture, and the rapid sampling operation of the sampling machine is facilitated. However, in the sampling process, the penetration pore-forming of the perforating bullet launched by the perforator on the lunar soil water ice layer cannot meet the quality conditions of the sampling space and the total load required by the sampler, and meanwhile, the combustion residue leakage of the perforating bullet in the launching process can pollute the lunar soil water ice in situ.
In conclusion, in the design process of the perforator for the lunar soil water ice penetration pore-forming at the extreme low temperature and high strength in the permanent shadow pit of the lunar polar region, the light and small design of the penetration perforation and the perforator with high efficiency is realized reasonably according to the mechanical characteristic parameters and the sampling detection requirements of the lunar soil water ice, and meanwhile, the pollution of the burning residues of the propellant to the in-situ lunar soil water ice sample and the problem of excessive mechanical disturbance of the launching process to the flasher and the mechanical arm are avoided through the sealing anti-fouling design and the low recoil launching design.
Disclosure of Invention
The invention aims to provide a firer-actuated perforator for detecting a planet section, which aims at the technical characteristics that a perforating bullet for perforating a hole by penetrating lunar soil water ice at an extreme low temperature and high strength in a permanent shadow pit of a lunar polar region needs to have low recoil in a perforating process, high perforating effect and no pollution when perforation is finished.
In order to achieve the purpose, the invention adopts the technical scheme that:
a firer-actuated perforating gun for star profile detection, comprising: penetrating a projectile body 5, a clamping sleeve 6, a launching barrel 3 and high-energy gunpowder 4, the launching barrel 3 comprising: the high-energy powder conveying device comprises a cavity part 15 and a tubular part 14 connected with an opening of the cavity part 15, an igniter 2 is mounted at the bottom of the cavity part 15, the cavity part 15 is used for containing the high-energy powder 4, a sealing piston 7 is arranged at the opening of the cavity part 15, the sealing piston 7 is used for preventing the high-energy powder 4 from entering the tubular part 14, a penetration projectile body 5 is arranged in the tubular part 14, the bottom of the penetration projectile body 5 is movably connected with the sealing piston 7, the tubular part 14 is mounted in a clamping sleeve 6, and a multiplexing interface 11 connected with a control system is arranged on the outer wall of the clamping sleeve 6.
The above-mentioned firer-actuated perforator facing the detection of the section of the planet, wherein, still include: a plurality of positioning rings 10 are arranged in the tubular part 14, the inner diameter of each positioning ring 10 is matched with the outer diameter of the penetration body 5, and the penetration body 5 and the launching barrel 3 are coaxially arranged through the plurality of positioning rings 10.
The above-mentioned firer-actuated perforating gun for detecting the section of the planet, wherein, it also includes: the tail plug 1 is installed at the bottom of the cavity portion 15, and the tail plug 1 is used for blocking the leakage of the high-energy gunpowder 4 from the bottom of the cavity portion 15.
The above-mentioned firer-actuated perforator facing the detection of the section of the planet, wherein, still include: and the sealing ring 9 is arranged between the launching barrel 3 and the sealing piston 7.
The firer-actuated perforator facing the detection of the planet section has the advantages that the outer diameter of the penetration projectile body 5 is 15mm, and the length of the penetration projectile body 5 is 85mm.
The above-mentioned firer-actuated perforator facing the detection of the celestial body section has a length of the launching barrel 3 of 420mm.
The firer-actuated perforating gun facing the planet section detection is characterized in that the inner diameter of one end, away from the cavity part 15, of the tubular part 14 is smaller than that of one end, connected with the cavity part 15, of the tubular part 14, the outer diameter of one end, away from the cavity part 15, of the tubular part 14 is larger than that of one end, connected with the cavity part 15, of the tubular part 14, and the outer wall of the tubular part 14 is matched with the inner wall of the clamping sleeve 6.
The firer-actuated perforating gun for detecting the section of the planet is characterized in that the penetration projectile body 5 is in a bullet shape, and the penetration projectile body 5 and the sealing piston 7 are movably connected through a plurality of shearing pins 8.
In the firer-actuated perforating tool for detecting the section of the planet, a plurality of cavity spaces 13 are arranged between the inner wall and the outer wall of the clamping sleeve 6, and the cavity spaces 13 are used for sound insulation and shock absorption in the perforating process.
In the above-mentioned firer-actuated perforating gun for detecting a section of a planet, the multiplexing interface 11 and the igniter 2 are connected by two initiation signal cables 12.
Due to the adoption of the technology, compared with the prior art, the invention has the positive effects that:
(1) The invention can realize penetration and perforation of high-strength lunar soil water ice, and the penetration depth of the high-strength lunar soil water ice material is more than 160mm;
(2) The invention can realize low back force clamping emission, penetration body emission speed: more than 350m/s, the diameter of the bullet hole is more than 15mm, and the recoil after launching is less than 5N;
(3) The invention can realize high-efficiency sealing of combustion products of the driving gunpowder, and the leakage of pollutants is less than 8.62 multiplied by 10 -19 And g, accidental ignition does not occur under the long-term storage condition, and the storage can be carried out under the low-temperature environment condition for a long time.
(4) The invention can realize impact crushing of the lunar soil water ice structure with high strength, reduce the mechanical strength of the lunar soil water ice structure and greatly improve the efficiency of sampling detection operation.
Drawings
Fig. 1 is a schematic front view of a firer-actuated perforating gun of the present invention oriented toward detection of a star profile.
Fig. 2 is a schematic top view of a firer-actuated perforating gun of the present invention oriented toward a star profile survey.
Fig. 3 is a diagram of the perforating charge system of a firer-actuated perforating gun of the present invention directed to detection of a star profile.
Figure 4 is a conical projectile trajectory profile of a firer-actuated perforating gun of the present invention directed to a star profile exploration.
Figure 5 is a sharp oval projectile trajectory profile for a firer-actuated perforating gun of the present invention directed to a star profile detection.
Fig. 6 is a schematic diagram of the geometry of the penetration body of the firer-actuated perforator facing the detection of the planet section.
Figure 7 is a ballistic deflection characteristic curve of different aspect ratios for a firer-actuated perforating gun of the present invention directed to a star profile exploration.
FIG. 8 is a 350m/s different strength configuration penetration depth prediction curve for a firer-actuated perforating gun of the present invention directed at a planet profile survey.
FIG. 9 is a gradient configuration different speed penetration depth prediction curve of a firer-actuated perforating tool for celestial section detection according to the present invention.
Fig. 10 is a P-t plot for a firer-actuated perforating gun of the present invention directed to detection of a star profile.
Fig. 11 is a v-t plot for a firer-actuated perforating gun of the present invention directed to detection of a star profile.
Fig. 12 is a P-L plot of a firer-actuated perforating gun of the present invention directed to detection of a star profile.
Fig. 13 is a v-L plot for a firer-actuated perforating gun of the present invention directed to detection of a star profile.
In the drawings: 1. tail blocking; 2. an igniter; 3. launching a barrel; 4. high-energy gunpowder; 5. penetrating the projectile body; 6. a clamping sleeve; 7. a sealing piston; 8. a shear pin; 9. a seal ring; 10. a positioning ring; 11. multiplexing an interface; 12. detonating the signal cable; 13. a cavity space; 14. a tubular portion; 15. a cavity portion.
Detailed Description
The invention is further described with reference to the following drawings and specific examples, which are not intended to be limiting.
Referring to fig. 1-13, there is shown a firepower actuated perforating gun for detection of a star profile, comprising: the penetration body 5, centre gripping sleeve 6, launching barrel 3 and high energy powder 4, launching barrel 3 includes: the high-energy powder conveying device comprises a cavity part 15 and a tubular part 14 connected with the opening of the cavity part 15, an igniter 2 is mounted at the bottom of the cavity part 15, the cavity part 15 is used for containing high-energy powder 4, a sealing piston 7 is arranged at the opening of the cavity part 15, the sealing piston 7 is used for preventing the high-energy powder 4 from entering the tubular part 14, a penetration projectile body 5 is arranged in the tubular part 14, the bottom of the penetration projectile body 5 is movably connected with the sealing piston 7, the tubular part 14 is mounted in a clamping sleeve 6, and a multiplexing interface 11 connected with a control system is arranged on the outer wall of the clamping sleeve 6.
Further, in a preferred embodiment, the method further comprises: the positioning ring 10 is provided with a plurality of positioning rings 10 in the tubular part 14, the inner diameter of each positioning ring 10 is matched with the outer diameter of the penetrating projectile body 5, and the penetrating projectile body 5 and the launching barrel 3 are coaxially arranged through the plurality of positioning rings 10.
Further, in a preferred embodiment, the method further comprises: the tail plug 1 is arranged at the bottom of the cavity part 15, and the tail plug 1 is used for preventing the high-energy gunpowder 4 from leaking from the bottom of the cavity part 15.
Further, in a preferred embodiment, the method further comprises: a sealing ring 9 is arranged between the sealing ring 9, the launching barrel 3 and the sealing piston 7.
Further, in a preferred embodiment, the outer diameter of penetrating projectile 5 is 15mm and the length of penetrating projectile 5 is 85mm.
Further, in a preferred embodiment, the length of the launching barrel 3 is 420mm.
Further, in a preferred embodiment, the inner diameter of the end of the tubular part 14 remote from the cavity part 15 is smaller than the inner diameter of the end of the tubular part 14 connected to the cavity part 15, the outer diameter of the end of the tubular part 14 remote from the cavity part 15 is larger than the outer diameter of the end of the tubular part 14 connected to the cavity part 15, and the outer wall of the tubular part 14 matches the inner wall of the clamping sleeve 6.
Further, in a preferred embodiment, penetrating projectile 5 is bullet-shaped, and penetrating projectile 5 and sealing piston 7 are movably connected by a plurality of shear pins 8.
Further, in a preferred embodiment, a plurality of cavity spaces 13 are provided between the inner wall and the outer wall of the clamping sleeve 6, and the plurality of cavity spaces 13 are used for sound insulation and shock absorption of the perforation process.
Further, in a preferred embodiment, the multiplexing interface 11 and igniter 2 are connected by two initiation signal cables 12.
The above are merely preferred embodiments of the present invention, and the embodiments and the protection scope of the present invention are not limited thereby.
The present invention also has the following embodiments in addition to the above:
in a further embodiment of the invention, the technical requirement is: in the process of sampling the lunar soil water ice sample in the lunar polar region, firstly, removing the surface layer anhydrous low-strength lunar soil by adopting a rapid drilling mode, and then, carrying out penetration pore-forming on the high-strength lunar soil water ice layer with rich water content by adopting a perforating bullet, so as to provide a working space for the sampling machine to sample the in-situ lunar soil water ice. In order to meet the quality conditions of sampling space and total load required by the sampler and simultaneously avoid pollution of in-situ lunar soil water ice caused by leakage of combustion residues in the launching process, the technical requirements of the perforating bullets are shown in table 1.
Table 1 perforating charge specification table
In a further embodiment of the invention, the firer actuated perforating charge system comprises and operates on the principle of: the initiating explosive actuating perforating bullet consists of four parts, namely a high-efficiency penetration bullet body unit, a high-efficiency initiating explosive actuating unit, a launching unit and an interface unit, as shown in figure 3. The perforating bullet can be clamped by a mechanical arm or launched on a specific launcher, the main control system of the flasher provides an ignition signal for the igniter 2 through the mechanical-electrical multiplexing interface 11, the partition igniter 2 ignites the propellant powder to generate a large amount of high-pressure explosive gas to push the penetration bullet 5 to accelerate to a target speed in the launching barrel 3 and then to launch, and the penetration bullet 5 completes penetration hole forming on the lunar soil water ice profile at the inertia speed.
In a further embodiment of the invention, the charge penetration charge 5 is designed: as shown in fig. 4 and 5, the trajectory characteristic curves of penetration projectiles 5 with different geometric configurations penetrating dry sand target body materials are shown, and it can be seen from the trajectory characteristic curves that the resistance of penetration projectiles 5 with a pointed oval structure in the penetration process is far lower than that of penetration projectiles 5 with a conical structure, and the oval penetration projectiles 5 can reach a greater penetration depth at the same speed cost, which is beneficial to a sampler to realize sampling detection of a deeper lunar water ice profile, and the penetration of the perforating bullets in the scheme adopts a pointed oval structure, as shown in fig. 6. During the penetration process of penetrating projectile 5, due to the inhomogeneous characteristic of lunar soil water ice medium, a deflecting moment is generated on penetrating projectile 5, so that the trajectory deflects, and the deflection characteristic curve during the penetration process of penetrating projectile 5 under different length-diameter ratio parameters is shown in fig. 7. As can be seen from fig. 7, in order to suppress the deviation of the trajectory by the yawing moment and maximize the penetration depth, it is required that the aspect ratio L/D of the penetrating projectile body 5 be >5.
In a further embodiment of the invention, according to a classical end-point ballistics theory, for a small-mass penetration bullet, a Forrestal penetration depth prediction formula can be adopted to predict the perforation depth of the perforation bullet, as shown in formula (1).
In the formula: p-penetration depth; n-spring modulus; a-the diameter of the projectile; ρ — target bulk density; m-mass of the elastomer; f. of c ' -uniaxial compressive strength; s-value of intensity coefficient;
in a further embodiment of the present invention, the S value is a strength factor value of the target material, and for a material meeting the moore yield criterion, the relationship between the S value and the uniaxial compressive strength of the target material can be approximately expressed by equation (2).
S＝82.6(f c '/10 6 ) -0.544 (2)
In a further embodiment of the present invention, it is found from the expressions (1) and (2) that, when the penetration depth is constant, the smaller the diameter of the projectile body is, the lower the requirement for the firing rate is, and the more advantageous the lightweight design of the entire perforating charge is. In the project, the requirement of sampling detection can be met by a penetration hole with the diameter of 15mm, so that the diameter D of the projectile body is selected to be 15mm, and the length L of the projectile body is selected to be 85mm. In order to ensure that penetration projectile body 5 does not lose efficacy in the process of penetration and hole formation of high-strength lunar soil water ice and has high launch kinetic energy, penetration projectile body 5 is required to be made of high-strength, high-toughness and high-density materials, and high-density nickel-tungsten alloy materials are adopted to meet the requirements, and the material parameters are shown in table 2. The mass of penetrating projectile 5 calculated from the geometry of penetrating projectile 5 is about 200g. FIG. 8 shows the penetration depth curves obtained in the homogeneous lunar soil texture at different intensities at an emission speed of 350m/s with the above parameters in equation (1). Since the strength characteristic of the true lunar soil water ice texture is in gradient distribution, the lunar soil water ice texture is assumed to be in linear gradient change with the change rate of 30MPa/m, and the calculated penetration prediction curve of the penetration projectile body 5 under different launching speeds is shown in FIG. 9. According to NASA detection data, the ultimate strength of lunar soil water ice in a permanent shadow pit of south pole of the moon is 40MPa, in order to meet the requirement of engineering coverage, the scheme is designed according to the strength of a target body of 40MPa, and according to data in figures 8 and 9, the penetration depth is about 168mm under the speed condition of 350/s, and the design requirement is basically met.
TABLE 2 penetration parameter table for elastomer material
| Parameter name | Parameter value |
| Name of Material | Nickel-tungsten alloy |
| Density (kg/m) 3 ) | 18000 |
| Young's modulus (GPa) | 619.5 |
| Poisson ratio | 0.28 |
| Mohs Hardness (HM) | 32 |
| Yield strength | 1450MPa |
In a further embodiment of the present invention, in order to meet the coverage requirement, the penetration depth of penetration projectiles 5 with different masses at different launching speeds and the corresponding parameters of the charge, total mass, envelope and launching kinetic energy are matched, the matching result is shown in table 3, and the specific matching process is performed in the following analysis.
TABLE 3 40MPa lunar soil water and ice invasion perforating bullet parameter table
In a further embodiment of the invention, the high-efficiency fire-actuated unit design of the perforating charge comprises the following steps: the high-efficiency initiating explosive device is composed of two parts, namely an insensitive high-energy propellant and a partition plate igniter 2, and is used as an energy module of the whole initiating explosive device, so that on one hand, the requirement of reducing the explosive loading amount by a high energy ratio is required, and the light weight requirement of a system is further met; on the other hand, the device is required to have extremely high safety, and the accidental ignition action and failure are avoided in the long-time storage process in the space environment. In order to meet the requirements, the scheme selects the type of the high-energy powder 4 and the igniter 2 of the perforating charge. In the scheme, insensitive propellant powder with high burning speed, high explosive power and excellent long-time storage is selected as high-energy explosive 4 of the perforating charge, and the main components and the energy index of the propellant powder are respectively shown in tables 4 and 5. When the geometric and quality parameters of the penetration bullet 5 are completely determined, the launching speed is determined by two parameter values of the length of the launching barrel 3 of the perforating bullet and the launching chamber pressure, and the launching chamber pressure of the perforating bullet depends on the total charge amount of the perforating bullet. According to the motion characteristics of the projectile in the trajectory, the relation between the time t and the projectile speed and the relation between the shot stroke length L in the bore and the bore speed are obtained as shown in the formula (3) and the formula (4). The bore pressure value of the perforating bullet is increased along with the increase of the charge amount, and the over-large bore pressure is not beneficial to the safety of the perforating bullet launching process, so that the bore pressure requirement is reduced by properly increasing the length parameter of the launching barrel 3 under the condition that the launching speed requirement is definite, and the safety of a perforating bullet system is further improved. The length of the perforating charge is temporarily set to 420mm due to the limitation of the mounting size of the jumper.
In the formula:
s-area of the inner cavity of the launching barrel 3; p is the ballistic bore pressure value; m-penetration projectile 5 mass; phi represents the mass correction coefficient of penetration projectile body 5, and 1-1.3 is taken; t is the time from the start of static combustion; v-any instantaneous warhead speed;
in a further embodiment of the invention, a basic equation of the ballistic theory can be obtained according to an empirical formula of the ballistic calculation in bravain, a gas state and a basic equation of energy conversion, as shown in formula (5). Substituting the formula (3) and the formula (4) into the formula (5) to obtain a formula (6), substituting the high-energy gunpowder 4 parameter and the geometric structure parameter of the launching barrel 3, iterating by adopting a four-step Runge Kutta method, and calculating to obtain the loading of the high-energy gunpowder 4 of 24g, so that the 350m/s launching requirement of the penetration projectile body 5 can be met.
In the formula:
L φ free container of medicine chamberThe product has long reduced diameter; l is 0 -an acceleration segment length; f, the efficacy of the fire and the drug; omega-propellant charge; θ - θ = k-1,k is the gas adiabatic index; Δ — packing density; delta m -powder density; alpha-combustion chamber residual capacity; psi-powder charge coefficient;
TABLE 4 propellant major ingredients
| Nitrocellulose (%) | Nitroglycerin (%) | The rest of the additives (%) | Moisture (%) |
| 63.5±2 | 34±2 | 2％ | ≤0.5 |
TABLE 5 propellant energy index number
In a further embodiment of the invention, according to the requirements of GJB344A-2005 general Specification for insensitive Electrical squibs, the igniter 2 should have high safety, antistatic, anti-stray current, dielectric withstand voltage, and reliability of not less than 0.999. Therefore, the igniter 2 in the scheme selects a double-bridge ignition circuit with high reliability, adopts triple protection measures of current, voltage and power to avoid accidental actuation ignition in the process of long-term storage, and detailed performance parameters of the igniter are shown in table 6.
TABLE 6 igniter Performance parameters Table
In a further embodiment of the invention, the perforating charge launching barrel 3 is designed as follows: the launching barrel 3 is a main body of the whole perforating bullet system and mainly comprises a high-strength alloy equal-strength launching tube, a clamping sleeve 6 and a sealing piston 7. The sealing piston 7 and the launching barrel 3 jointly form a closed combustion cavity to seal the combustion residues of the high-energy gunpowder 4 in the launching barrel 3, so that the in-situ lunar soil caused by the large leakage of the combustion residues of the propellant is effectively avoided. High-pressure gas generated by detonation of the high-energy gunpowder 4 in the launching process pushes the perforating charge to accelerate to a target launching speed by pushing the sealing piston 7, and the launching barrel 3 is used as a recoil body and flies away from the sealed combustion residues in the opposite direction of launching so as to balance the launching recoil force. In order to ensure that the perforating charge can be smoothly separated from the elastic interface of the mechanical arm in the launching process, the overall appearance of the perforating charge is required to be an isometric body. Therefore, the perforating bullet adopts the porous composite material structure in the design process, the launching barrel 3 with non-equal diameter is coated into an equal-diameter body, the coated porous composite material structure isolates the launching barrel 3 from the mechanical arm clamping interface, the impact vibration energy in the launching process can be effectively absorbed, and the mechanical disturbance to the mechanical arm is reduced.
In a further embodiment of the invention, in order to meet the high pressure resistance of the launching barrel 3, the aviation ultra-high strength steel 40CrNi2SiMoVA is selected as the material of the launching barrel 3 in the design, and the tensile strength σ b =1860MPa and σ r0.2=1515MPa. The results of matching equation 6 with the charge parameters show that the inner trajectory curves of the charges, which can be solved using the 4 th-order lunger tower method, are shown in fig. 10 to 13. In order to meet the requirement of light weight of the system, the corresponding equal-strength design is carried out on the launching barrel 3 according to the variation value of the chamber pressure of the launching barrel 3, and the geometric parameters of the launching barrel 3 can be calculated by the formulas (7) and (8).
r 2 ＝ar 1 (8)
In the formula: a-the ratio of the inner diameter to the outer diameter of the launching barrel 3 is proportional coefficient; sigma r0.2 -the required value of the material of the launching barrel 3; p is 3 chamber pressure of the launching barrel; r is 1 The inner diameter of the launching barrel 3 is 15mm; r is a radical of hydrogen 2 -the outer diameter of the launching barrel 3;
in a further embodiment of the invention, the structural parameters of the launch barrel 3 corrected according to the P-L data of the internal trajectory are shown in table 7.
TABLE 7 theoretical size table for launching barrel
In a further embodiment of the present invention, the perforating bullet multiplexing interface 11 is designed as follows: the perforating bullet is carried and launched by the mechanical arm, the perforating bullet is carried in a perforating bullet cabin of the flying apparatus, when perforating operation is carried out, the mechanical arm needs to cooperate to clamp and transfer the perforating bullet through the clamping interface, and a communication relation between the main control system of the flying apparatus and the perforating bullet is established through the electrical multiplexing interface 11. The interface mode of the mechanical and electrical multiplexing interface 11 is adopted in the scheme, the mechanical arm adopts an elastic soft clamping mode for the perforating charge, the total mass of the perforating charge is 1.24kg, and the maximum static friction coefficient value between the elastic clamping piece and the perforating charge clamping sleeve 6 is 0.5. Therefore, under the gravity condition of the moon, the clamping force of the elastic clamping piece on the perforating charge is required to be more than 5N, and in order to ensure a certain design allowance, the clamping force of the elastic clamping piece in the scheme is designed to be 10N. The rest part of the penetrating projectile 5 is separated from the clamping interface of the mechanical arm in the launching process and flies away in the opposite direction of launching to balance the recoil force in the launching process of the penetrating projectile 5, the recoil force to the mechanical arm in the whole process is only the friction force of the clamping interface, and the recoil force is expected to be less than 5N and the action time is expected to be less than 1ms.
In a further embodiment of the present invention, the perforating charge system design results in: the results of the parameters of the charge, based on the above design results, are shown in table 8.
Table 8 perforating bullet function parts quality statistical table
In a further embodiment of the invention, in order to further verify the penetration capability of the perforating charge and the accuracy of theoretical model calculation, the perforating charge is analyzed by a numerical simulation method. The target body adopted in the simulation process is 40MPa of high-strength lunar soil water ice, the penetration projectile body 5 is a high-strength nickel-tungsten alloy material, and the specific parameters are shown in tables 9 and 10.
TABLE 9 lunar soil water ice material mechanical property parameter table
| Parameter name | Parameter value |
| Constitutive model | Johnson cook model |
| Density (kg/m) 3 ) | 1800 |
| Young's modulus (MPa) | 1000 |
| Poisson ratio | 0.4 |
| Specific heat capacity at constant pressure (J/kg. K) | 654 |
| Compressive strength of uniaxial (MPa) | 40 |
| Yield stress (MPa) | 8.3 |
| Hardening Strength (MPa) | 200 |
| Coefficient of strain rate | 0.02 |
| Coefficient of hardening | 0.808 |
| Temperature coefficient of | 0.9 |
TABLE 10 penetration table for mechanical property of elastomer material
| Parameter name | Parameter value |
| Name of Material | YG6 |
| Density (kg/m) 3 ) | 15000 |
| Young's modulus (GPa) | 619.5 |
| Poisson ratio | 0.28 |
| Specific heat capacity at constant pressure (J/kg. K) | 176 |
In a further embodiment of the invention, during the numerical simulation process, the uniaxial compression test data for simulating lunar soil water ice is firstly adopted to perform mechanical calibration on the penetration target material, and then a simulation model is established according to penetration simulation requirements. The force model of penetration action has high symmetry, so in order to reduce the calculation scale, a 1/2 finite element model is adopted for calculation analysis. In the simulation test process, firstly, preprocessing operations such as geometric modeling and grid division are carried out by using Workbenck software, and then the processed geometric model is led into an LS-DYNA arithmetic unit to carry out solving operation.
In a further embodiment of the invention, a total of 2 penetration simulation tests are planned based on the design results of the charges. Penetration depths of the projectiles 5 under different launch speed conditions are calculated respectively, and simulation results and theoretical calculation results are shown in table 11.
Table 11 simulation test matrix table
| Serial number | Penetration of the projectile mass | Penetration of projectile diameter | Speed of rotation | Depth of penetration simulation | Depth of |
|
| 1 | 200g | 15mm | 350m/s | | 170mm | |
| 2 | 200g | 15mm | 400m/s | 238mm | 208mm |
In a further embodiment of the invention, a fire-working penetration effect test system is built for verifying the feasibility of the fire-working actuated perforating bullet scheme principle. The firer-actuated penetration bomb is vertically hung on the upper end and the lower end of the protective wood board by cotton threads and is about 500mm away from soil, the firer-actuated penetration bomb body is driven to penetrate to a clay object at high speed, and the penetration condition is recorded through high-speed photography in the process. The mass of the penetration bomb is 215g, and the size of the penetration bomb is
In a further embodiment of the invention, 4 explosive loads of the high-energy gunpowder actuated by the firer are changed, three penetration tests are respectively carried out, 3 test pieces all work normally, and the shell is not obviously deformed and damaged after the tests. And (4) carrying out penetration on ballistic trajectories and holes, and carrying out penetration on speed and depth data. At penetration speeds of 114.3m/s, 132.7m/s and 118.4m/s, penetration depths of 450mm, 520mm and 400mm are respectively realized.
In a further embodiment of the invention, use is made of
The caliber light gas gun and the pressure-regulating gas are used for energy storage and acceleration, penetration bomb is accelerated to 260-550 m/s, and penetration is carried out to the simulated star soil target body. The penetration process is recorded by a high-speed camera system. The method comprises the steps of adopting 0.1-1 mm particle size GUA-1A lunar soil simulant as a raw material, adding water, freezing at-20 ℃ to prepare a soil water ice sample with 5% of water content, and forming
The strength is about 4 MPa.
In a further embodiment of the invention, the diameter of the penetration bomb is 30mm, the length of the penetration bomb is 150mm, the mass of the penetration bomb is 250g, penetration tests are carried out at three speeds of 260m/s, 482.6m/s and 550m/s, and the maximum penetration depth is 585mm.
In a further embodiment of the invention, according to the dynamics modeling analysis of the firearm firing process, the posture characteristic of the rifle during the fixed-branch firing and the sub-chamber ejection is determined by the performance characteristics of the rifle, the local atmospheric characteristics of the firing and the gravity characteristics. In the scheme, the working environment of the perforating bullet is in a vacuum state, and meanwhile, the speed direction of the penetration bullet 5 is consistent with the local gravity direction, so that the launching posture of the penetration bullet 5 is only related to the structural characteristics of the perforating bullet. According to a bullet/cannon interaction model in the bullet ballistics in the gun and combined with a high-speed shooting and recording result in the launching test process, when the result is only influenced by the structural characteristics of the gun and the cannon, the attitude deflection angle in the bullet launching process is smaller than 0.2 degrees.
In a further embodiment of the invention, after the core drill removes the dry lunar soil with low strength on the surface layer, the mechanical arm transfers the rotary perforating bullet to be aligned with the prefabricated hole drilled by the core drill, and the distance between the bore of the perforating bullet and the sampling detection point is about 450mm. When an ignition signal of a main control system is received, high-energy powder 4 of the perforating bullet is ignited to push a penetration bullet body 5 to be launched, and the deflection angle of the posture of the penetration bullet body 5 when the penetration bullet body 5 is taken out of the chamber is set to be 0.2 degrees according to the hypothesis of a bullet/cannon interaction model of inner bullet ethology. According to the calculation result, when the penetration projectile 5 enters the prefabricated hole, the axis deviates about 1.5mm from the original axis, the diameter of the prefabricated hole is 5mm larger than that of the penetration projectile 5, and a single side has a cavity margin of about 2.5mm, so that the penetration projectile 5 can smoothly enter the prefabricated hole.
In a further embodiment of the invention, the high-energy explosive 4 may have a small amount of bound water during storage, the mass of the bound water being less than or equal to about 0.5% of its own moisture content, whereby the maximum moisture mass of the high-energy explosive 4 itself is estimated to be about 0.12g. The high-energy gunpowder 4 is mainly nitrocellulose and nitroglycerin, and water substances are generated in the deflagration process, so the maximum value of the water yield of the propellant in the deflagration process is estimated by adopting an element conservation mode.
The nitrocellulose combustion reaction simplifies the equation:
C 12 H 17 (ONO 2 ) 3 O 7 →8.5H 2 o + the remaining substances (1)
459 8.5×18
24g×65.5％ 5.240g
C 12 H 14 (ONO 2 ) 6 O 7 →7H 2 O + the remaining substances (2)
642 7×18
24g×61.5％ 2.897g
Nitroglycerin combustion reaction equation:
4C 3 H 5 N 3 O 9 →10H 2 O+12CO 2 +O 2 +6N 2 (3)
4×227 10×18 12×44 32 6×28
24g×36％1.713g
24g×32％1.523g
in the further embodiment of the invention, according to the calculation, the water mass in the combustion products of the high-energy gunpowder 4 is 4.610-6.953 g.
In a further embodiment of the invention, the type of charge in the igniter 2 comprises: lead stefenate, lead azide and black powder. The H element in the lead stevensonate exists mainly in the lead stevensonate molecule and in a small amount of volatile matter, wherein the maximum mass of water generated by the combustion reaction is 0.9238mg, the maximum mass ratio of the volatile matter is about 0.03%, and the maximum mass of the water is calculated to be about 0.0048mg. The H element in the lead azide was mainly present in a small amount of volatile matter, and the mass ratio was about 0.03% at the maximum, and the maximum mass of moisture was calculated to be about 0.018mg. The H element in the black powder is mainly present in a small amount of volatile matter, the mass ratio is about 1% at the maximum, and the maximum mass of the water is calculated to be about 3mg. The maximum mass of moisture in the combustion products of igniter 2 was calculated to be about 4mg.
In a further embodiment of the present invention, it is shown according to the above calculation result that about 7g of moisture will be generated during the firing process of the fire-activated perforating charge, so that the combustion products need to be sealed by the sealing piston 7, and the interference of leakage to the detection precision is avoided. The prior sealing mature technology of initiating explosive devices has the leakage rate less than or equal to 5 multiplied by 10 -7 Pa·m 3 The working environment of the perforating bullet is in a vacuum state, the pressure value of a transmitting chamber is 450MP, and the leakage rate is less than or equal to 2.25 multiplied by 10 before the piston moves in place -3 Pa·m 3 And s. Because the movement time of the piston is about 2ms, the total leakage quantity is less than or equal to 4.5 multiplied by 10 -6 Pa·m 3 The total leakage amount of the water substance is about 8.62 multiplied by 10 by substituting the volume value of the cavity of the launching barrel 3 into the obtained leakage amount -19 g, the emission process can be considered almost free of water substance leakage.
In a further embodiment of the invention, in order to further verify the sealing performance of the piston of the perforating charge in the launching process, autodyn is adopted in the scheme to perform simulation analysis on the strength of the piston body impacting the 3 openings of the launching barrel in the launching process. According to the simulation result, in the process that the piston body impacts the opening of the launching barrel 3, the launching barrel 3 does not have strength failure, and the piston body can fly away in the opposite direction of penetration together with the launching barrel 3.
In a further embodiment of the invention, the force state of the penetration process of the penetrating projectile 5 is generally described by using the theory of spherical cavity expansion. The theory of spherical cavity expansion holds that the tunnel cavity after the penetration of the projectile body is formed by the spherical dynamic expansion of the target material at a certain speed after the target material is subjected to speed exchange in the process of forward movement of the projectile body tip. During expansion, the material surrounding the elastomer is pressed against each other. Because the different radiuses of each point of the target material from the axis of the projectile body are different, the stress level at each point is different, and at the moment, different areas centered on the axis of the projectile body are formed by the target material due to the difference of macroscopic deformation behaviors.
In a further embodiment of the invention, for a target material, the boundary between different response regions is the range of propagation of the corresponding stress wave, c is the plastic wave velocity and cd is the elastic wave velocity. In the elastic region, the stress-strain relation of the target body material is in the elastic range, and after the penetration process is finished, the deformation can be recovered. In the plastic region, the target material stress level exceeds its yield limit or failure strength, at which point the target material will fail irreversibly. The lunar soil water ice material can be described by adopting a Drucker-Prager Cap model, the shear strength of the lunar soil water ice material is rapidly attenuated when yielding, and the shear strength of the lunar soil water ice material is 0 when the stress value reaches the ultimate compaction pressure of the lunar soil water ice, so that the part of the subregion of the plastic region is called as a crushing region. For lunar soil water ice target material, the propagation velocity of plastic wave is about 5 times of the cavity expansion velocity, and the diameter of the calculated plastic area is 75mm. The lunar soil water ice target body material in the crushing area has extremely low strength, so that the lunar soil water ice target body material is beneficial to further adopting machines to collect in-situ lunar soil water ice samples in the later period.
In a further embodiment of the invention, a finite element numerical simulation method is sampled in order to research thermal disturbance on the lunar soil water ice in the penetration process, and a simulation test is carried out on the thermodynamic effect in the penetration process. The average temperature of the south pole lunar surface is 40K, the critical value of the volatilization of the lunar soil water ice is 150K, the temperature rise of a pore-forming area due to the penetration effect is less than 85K, and the lunar soil water ice cannot volatilize and escape due to thermal disturbance generated by the penetration effect, so that the in-situ characteristics of the lunar soil water ice cannot be damaged due to penetration pore-forming.
In a further embodiment of the invention, the high-speed shooting result in the test of simulating the star soil sample by air cannon penetration is matched with the result derived by the cavity expansion theoretical model. The density of the simulated star soil water ice used in the test is 1.8g/cm, the results of analyzing the speed and kinetic energy of sputtering in the penetration test process through the result of high-speed camera shooting are shown in table 12, and the data results in the table show that the speed of the sputtering material and the energy carried by the sputtering material are both at a lower level.
TABLE 12 simulated star soil water ice penetration sputters average particle kinetic energy table
| Sample code | Mass of projectile | Kinetic energy of projectile body | Speed of particle sputtering | Average particle kinetic energy |
| HIT-VRS-2D | 250g | 2812.5J | 7m/s | 0.176J |
| HIT-VRS-2W | 250g | 3200J | 6m/s | 0.130J |
| HIT-VRS-3W | 250g | 3698J | 10.9m/s | 0.405J |
In a further embodiment of the invention, in the high-speed camera result of the vertical penetration test of the firer actuation, the splashing speed of the large-particle-size clay particles in the penetration test process is about 6.19m/s at most, and the scattering diameter is about 3.9m.
In a further embodiment of the invention, according to the analysis result of the cavity expansion model in the classical end-point ballistic theory, the sputtering phenomenon in the penetration process is mainly caused by the free surface effect generated when the reflected tensile stress wave is transmitted to the surface of the target material, so that the sputtering phenomenon occurs in the pit-opening stage in the penetration process. The preformed hole is drilled before the perforating bullet is perforated and the pit is built during the perforating bullet entering process, so that the stress tension wave generated by the penetration acting cable is greatly attenuated when being transmitted to the lunar soil surface, and the generated spatter is reduced.
In a further embodiment of the invention, low-recoil, high-efficiency, pollution-free penetration pore-forming critical technology (HIT): the perforating bullet for the perforation penetration of the lunar soil water ice with extreme low temperature and high strength in the permanent shadow pit of the lunar polar region needs to have the technical characteristics of low recoil in the perforation process, high perforating effect and no pollution when perforation is finished.
In a further embodiment of the invention, in the launching process, the mechanical arm adopts an elastic soft clamping mode for the perforating bullet, the rest part of the perforating bullet 5 is separated from a clamping interface of the mechanical arm in the launching process and flies away in the opposite direction of launching so as to balance the recoil force in the launching process of the penetrating bullet 5, the recoil force to the mechanical arm in the whole process is only the clamping force of the clamping interface, and is expected to be less than 5N, and the action time is less than 1ms.
In a further embodiment of the invention, a cavity expansion theoretical model of the penetration process is combined with test results of penetration test and numerical simulation test for simulating lunar soil, and penetration of the penetration projectile 5 in the penetration process of the penetration projectile 5 to the lunar soil water ice simulating target material is analyzedThe influence rule of the penetration resistance characteristic and the penetration hole characteristic; the shape characteristics and the length-diameter ratio characteristics of the penetration projectile body 5 are optimally designed, penetration resistance of the penetration projectile body 5 and trajectory deflection in the penetration process are reduced, and penetration perforating efficiency of the perforating bullet is maximized. In order to reduce the load requirement when the mechanical arm clamps the perforating charge, the equal-strength structural design is adopted in the design process of the launching tube, so that the scheme forms a clamping sleeve 6 with a porous structure on the surface of the metal launching tube 3 by light composite winding, and the perforating charge is enveloped into one
The cylindrical structure of (3) makes the launching barrel (3) smoothly separated in the launching process. The composite material porous clamping sleeve 6 has certain energy absorption and vibration isolation characteristics, and can effectively reduce disturbance of strong vibration in the launching process to the mechanical arm.
In a further embodiment of the invention, in order to reduce the large-area leakage of combustion residues generated in the combustion process of the high-energy propellant, a sealed piston 7 is adopted in the design, and the high-energy propellant and the launching barrel 3 form a closed combustion cavity together. High-energy high-pressure gas generated by deflagration of the high-energy propellant powder pushes the perforating bullet to accelerate to a target launching speed by pushing the sealing piston 7, and the penetration projectile body 5 completes penetration hole forming on lunar soil water ice by means of the inertia speed of the projectile body out of the chamber; the sealing piston 7 is retained in the launching barrel 3 due to the blocking effect of the shaft shoulder at the opening of the launching barrel 3, seals the combustion residue in the launching barrel 3 and flies away from the sampling detection point along with the launching barrel 3, thereby effectively avoiding the leakage and pollution of the combustion residue.
In a further embodiment of the present invention, the clamping tool is mounted during the test in the following manner: set up the protecting wall in the left and right sides of concrete target body, it sets up the shelf to be close to the protecting wall, the upper end of shelf is connected with the perforator through the centre gripping armed lever, the open end of perforator transmission barrel 3 is vertical down, open end and concrete target body upper surface distance are 500mm, the some firearm 2 of perforator is connected through multiplexing interface 11 and exploder, it has the foil gage to bond on the centre gripping armed lever, foil gage and data acquisition system connect, set up the protection network outside the protecting wall, set up the protection network simultaneously in the top of perforator, set up an at least high-speed camera system in the outside of protection network, shoot the process of the test, concrete target body material carries out the ratio according to geotechnical test standard, pouring and maintenance are handled, adopt special cutter to cut standard sample piece, test its unipolar compressive strength on unipolar compression testing machine.
In a further embodiment of the invention, the detonation signal cable transmits a firing signal to ensure that high-energy propellant powder is detonated to generate high-energy high-pressure detonation gas to push the penetration projectile body 5 to accelerate, and the penetration perforation is carried out on the concrete target body; the launching barrel 3 and the positioning sleeve fly away in the opposite direction to counteract most of the recoil during launching. Recording the launching speed of the penetration projectile body 5, the recoil speed of the launching barrel 3 and the sputtering state of the broken target body in the penetration process by a high-speed camera device in the launching process; the mechanical disturbance amount of the launching process is measured through a strain gauge adhered to the arm lever. And filling the high-energy propellant according to the inner trajectory calculation result.
In a further embodiment of the invention, the firer-actuated perforating bullet works by clamping and launching an elastic clamp holder at the tail end of a mechanical arm, the mass of the firer-actuated perforating bullet system is about 1.3kg, the minimum clamping capacity of the clamp holder needs to be more than or equal to 2N under the condition of 1/6g low gravity of the lunar surface, the safety margin mu =2.5 is considered, and the maximum clamping capacity of the elastic clamp holder is designed to be about 5N. Due to the existence of the counter acting force of the clamping force, the launching process causes certain mechanical disturbance to the mechanical arm. In order to study the disturbance of the launching process, the test was carried out by fixedly connecting a 0.6m long arm to the launching cradle by means of bolts. The tail end of the arm rod clamps the perforating charge through the elastic clamping interface, the maximum clamping force of the clamping device on the perforating charge can be changed through the pre-tightening of the adjusting spring, and the clamping force of the clamping device is adjusted to be about 5N by adopting the standard mass block before the test, so that the disturbance on the mechanical arm rod caused by the clamping effect can be simulated to the maximum extent in the launching process.
In a further embodiment of the invention, in order to realize the high-efficiency low-recoil launching of the initiating explosive actuated perforating charge and effectively seal combustion products driving the high-energy gunpowder 4, a launching mode of self-balancing recoil of the launching barrel 3 is adopted. Mainly comprises a launching barrel 3, a high-strength penetration projectile body 5 and an elastic clamping interface. High-pressure high-energy explosive gas generated by the detonation of the high-energy gunpowder 4 is emitted in the emitting process, and the penetration projectile body 5 is pushed by the piston to accelerate the penetration on the surface of the lunar soil water ice; the launching barrel 3 flies away in the direction opposite to the launching direction of the penetration projectile body 5 to balance the recoil force of the launching of the penetration projectile body 5; the sealing piston 7 seals residual gas generated by combustion of the high-energy explosive 4 in the launching barrel 3 and flies away from a perforation target point together with the launching barrel 3.
In a further embodiment of the present invention, the initiating explosive device is composed of four major parts, namely a high-efficiency penetration explosive body 5 unit, a high-efficiency initiating explosive device unit, a launching unit and an interface unit. The perforating bullet can be clamped by a mechanical arm or launched on a specific launcher, the main control system of the flasher provides an ignition signal for the igniter 2 through a mechanical-electrical multiplexing interface, the partition plate igniter 2 ignites the propellant powder to generate a large amount of high-pressure explosive gas to push the penetration bullet 5 to be launched in the launching barrel 3 after accelerating to a target speed, and the penetration bullet 5 completes penetration hole forming on the lunar soil water ice profile at the inertia speed.
In a further embodiment of the invention, the launching barrel 3 is the main body of the whole perforating charge system and mainly comprises a high-strength alloy equal-strength launching tube, a clamping sleeve 6 and a sealing piston 7. The sealing piston 7 and the transmitting barrel 3 jointly form a closed combustion cavity to seal the combustion residues of the high-energy gunpowder 4 in the transmitting barrel 3, so that the in-situ lunar soil caused by the large leakage of the combustion residues of the propellant is effectively avoided. High-pressure gas generated by detonation of the high-energy gunpowder 4 in the launching process pushes the perforating charge to accelerate to a target launching speed by pushing the sealing piston 7, and the launching barrel 3 is used as a recoil body and flies away from the sealed combustion residues in the opposite direction of launching so as to balance the launching recoil force. In order to ensure that the perforating charge can be smoothly separated from the elastic interface of the mechanical arm in the launching process, the overall appearance of the perforating charge is required to be an isometric body. Therefore, the perforating bullet adopts the porous composite material structure in the design process, the launching barrel 3 with non-equal diameter is coated into an equal-diameter body, the coated porous composite material structure isolates the launching barrel 3 from the mechanical arm clamping interface, the impact vibration energy in the launching process can be effectively absorbed, and the mechanical disturbance to the mechanical arm is reduced.
In a further embodiment of the invention, the perforating bullet is launched by a mechanical arm, the perforating bullet is loaded in a perforating bullet cabin of the flying apparatus, when perforating operation is carried out, the mechanical arm needs to cooperate to clamp and transfer the perforating bullet through a clamping interface, and a communication relation between a main control system of the flying apparatus and the perforating bullet is established through an electrical multiplexing interface 11. The interface mode of the mechanical and electrical multiplexing interface 11 is adopted in the scheme, the mechanical arm adopts an elastic soft clamping mode for the perforating charge, the total mass of the perforating charge is 1.24kg, and the maximum static friction coefficient value between the elastic clamping piece and the perforating charge clamping sleeve 6 is 0.5. Therefore, under the condition of lunar gravity, the clamping force of the elastic clamping pieces on the perforating charge is required to be more than 5N, and in order to ensure a certain design allowance, the clamping force of the elastic clamping pieces in the test process is designed to be 10N. The rest part of the penetration projectile 5 is separated from a clamping interface of the mechanical arm in the launching process and flies away in the opposite direction of the launching to balance the recoil force in the launching process of the penetration projectile 5, the recoil force to the mechanical arm in the whole process is only the friction force of the clamping interface, and is expected to be less than 5N, and the action time is less than 1ms.
In a further embodiment of the invention, in order to verify the penetration performance and the sealing performance of the perforating bullet, on one hand, the penetration performance of a penetration bullet 5 of the initiating explosive device actuated perforating bullet and the temperature rise states of the bullet and lunar soil in the penetration process are preliminarily verified in a numerical simulation mode. The LS-DYNA software is suitable for dynamic analysis of materials, and numerical analysis is carried out on the penetration perforation process by adopting the LS-DYNA software in the test process; and carrying out a fireman actuation penetration test in the special target cabin.
In a further embodiment of the invention, during the numerical simulation process, the uniaxial compression test data for simulating lunar soil water ice is firstly adopted to perform mechanical calibration on the penetration target material, and then a simulation model is established according to penetration simulation requirements. The force-bearing model of the penetration function has high symmetry, so that in order to reduce the calculation scale, a 1/2 finite element model is adopted for calculation analysis. In the simulation test process, firstly, preprocessing operations such as geometric modeling and grid division are carried out by using Workbenck software, and then the processed geometric model is led into an LS-DYNA arithmetic unit to carry out solving operation.
In a further embodiment of the invention, a finite element numerical simulation method is sampled in order to research thermal disturbance on the lunar soil water ice in the penetration process, and a simulation test is carried out on the thermodynamic effect in the penetration process. The average temperature of the south pole lunar surface is 40K, the critical value of the volatilization of the lunar soil water ice is 150K, the temperature rise of a pore-forming area due to the penetration effect is less than 85K, and the lunar soil water ice cannot volatilize and escape due to thermal disturbance generated by the penetration effect, so that the in-situ characteristics of the lunar soil water ice cannot be damaged due to penetration pore-forming.
In a further embodiment of the invention, in order to further verify the sealing performance of the piston of the perforating charge in the launching process, the simulation analysis is carried out on the strength of the piston body impacting the opening 3 of the launching barrel in the launching process. According to the simulation result, in the process that the piston body impacts the opening of the launching barrel 3, the launching barrel 3 does not have strength failure, and the piston body can fly away in the opposite direction of penetration together with the launching barrel 3.
In a further embodiment of the invention, in order to verify the reliability of firing of the perforating charge and simultaneously grasp whether the structural strength of the launching barrel 3 meets the requirements, a firing end-touching test is carried out in an explosion test tower. 24g of propellant powder is filled in a charge cavity of the initiating explosive charge, a firing line is connected, 2A direct current is adopted for firing, the state of the penetration type perforator after firing is recorded, after the firing test is finished by Kong Dan, the structural form keeps better integrity, the sealing piston 7 does not extrude out of the launching tube 3 under the action of high-pressure gas, and the combustion residual product can be effectively sealed.
In a further embodiment of the invention, it is difficult to perform penetration perforation tests under limited conditions due to site conditions using truly simulated lunar soil water ice materials, and therefore the target material used in the tests is a concrete material with similar strength characteristics to lunar soil water ice materials. Before carrying out penetration perforation test, a standard cutter is adopted to cut a standard sample on the cured target body material, and a universal testing machine is adopted to test the uniaxial compressive strength of the sample. The uniaxial compressive strength value is 31.97MPa.
In a further embodiment of the invention, a test tool is arranged, a firer-actuated perforating bullet is clamped on a support assembly by an elastic clamp, the lower end of a penetration type perforating gun is about 560mm away from the surface of concrete, a firing line is connected, 2A direct current is used for firing, the penetration condition of the penetration type perforating gun is recorded by high-speed photography, the penetration speed of the penetration type perforating gun is calculated, the launching speed of the bullet can be calculated by high-speed shooting after the test is finished, according to the test result of the table 17, when the loading quantity of the perforating bullet is 28g, the speed of the penetration type bullet 5 reaches 353.13m/s, the design requirement is met, and according to the test result, the penetration depth of a 32MPa target material reaches 240.82mm and is far higher than 180mm of the theoretical penetration depth, so that the result of theoretical prediction is low. Therefore, for a 40MPa lunar soil water ice material, the actual penetration depth will also be higher than the theoretical penetration depth of 168mm.
In a further embodiment of the invention, silica gel is adopted to perform reverse molding treatment on the penetration trajectory in the test process, and the trajectory deflection of the penetration stroke of the initiating explosive charge is smaller according to the reverse molding result of the trajectory.
In a further embodiment of the invention, penetration projectile 5 is removed after the test is completed, and the projectile is found to have no change in shape, so that the material meets the penetration perforation requirement of high-strength lunar soil water ice.
In a further embodiment of the invention, the fire-actuated perforating bullet works by being clamped and launched by an elastic clamp holder at the tail end of a mechanical arm, the mass of a fire-actuated perforating bullet system is about 1.3kg, the minimum clamping capacity of the clamp holder needs to be more than or equal to 2N under the condition of 1/6g low gravity of the lunar surface, the safety margin mu =2.5 is considered, and the maximum clamping capacity of the elastic clamp holder is designed to be about 5N. Due to the existence of the counter acting force of the clamping force, the launching process causes certain mechanical disturbance to the mechanical arm. The tail end of the arm rod clamps the perforating charge through the elastic clamping interface, the maximum clamping force of the clamp holder on the perforating charge can be changed through the pre-tightening of the adjusting spring, and the clamping force of the clamp holder is adjusted to be about 5N by adopting the standard mass block before the test, so that the disturbance of the mechanical arm rod caused by the clamping effect can be simulated to the maximum extent in the launching process.
In a further embodiment of the invention, the test principle: when the penetration type perforator works, the perforator is clamped and launched by an elastic clamp at the tail end of a mechanical arm, a certain safety margin is considered according to the 1/6g low-gravity environment condition of the lunar surface, and the maximum clamping capacity of the elastic clamp is designed to be 5N. Due to the clamping force, the launching process causes certain mechanical disturbance to the mechanical arm. In order to study the disturbance of the launching process, the test was carried out by fixedly connecting a 0.6m long arm to the launching cradle by means of bolts. The tail end of the arm rod clamps the penetration type perforator through the elastic clamping interface, the maximum clamping force of the clamp on the penetration type perforator can be changed through the preset value of the adjusting spring, and the standard mass block is adopted to adjust the clamping force of the clamp to be about 5N before the test, so that the disturbance of the mechanical arm rod caused by the clamping effect can be simulated to the maximum extent in the launching process.
In a further embodiment of the invention, after the fire of the penetration type perforator, high-energy propellant powder is filled in the penetration type perforator to be combusted to generate high-temperature and high-pressure gas to push the penetration projectile body 5 to accelerate and penetrate the concrete target; high-temperature high-pressure gas generated by burning the high-energy propellant is sealed in a sealed cavity formed by the propellant barrel 3, the plug, the piston and the like; the launching barrel 3, the plug, the piston and the like fly away in the opposite direction of the flying direction of the penetration projectile body 5, and most of recoil in the launching process is counteracted. Recording the speed of a penetration projectile body 5, the recoil speed of the launching barrel 3 and the sputtering state of a target body broken object in the penetration process by a high-speed photographic system in the transmission process; and measuring the mechanical disturbance quantity of the launching process by a vibration measuring sensor adhered to the arm lever.
In a further embodiment of the invention, the firer actuated perforator key technology analysis: in the design process of a perforator for the penetration and pore-forming of lunar soil water ice at extremely low temperature and high strength in a permanent shadow pit of a lunar polar region, the light-weight and miniaturized design of a penetration and perforator with high efficiency is realized according to mechanical characteristic parameters and sampling detection requirements of the lunar soil water ice reasonably; the pollution of propellant combustion residues to an in-situ lunar soil water ice sample and the problem of overlarge mechanical disturbance to a leapfrog and a mechanical arm in a launching process are avoided by a sealed anti-fouling design and a low recoil launching design.
In a further embodiment of the invention, a high-efficiency penetration pore-forming technology for high-strength lunar soil water ice is as follows: in order to realize high-efficiency penetration perforation of high-strength lunar soil water ice under the south pole extreme low-temperature environment condition, the method is mainly realized from two aspects of geometric configuration optimization of penetration projectile body 5 and transmission speed matching of penetration projectile body 5, and the specific implementation method is as follows: (1) carrying out the optimal design of the geometrical configuration of the projectile body 5: analyzing the influence rule of penetration resistance characteristic and penetration hole characteristic of penetration projectile 5 in the penetration process of the penetration projectile 5 to the simulated lunar soil water ice target material by combining a cavity expansion theoretical model of the penetration process and the test results of a penetration test and a numerical simulation test; the optimal design is carried out on the bullet shape characteristic and the length-diameter ratio characteristic of the penetration bullet 5, the penetration resistance of the penetration bullet 5 and the trajectory deflection in the penetration process are reduced, and the penetration perforating efficiency of the perforator is maximized. Because the small-size and large-mass penetration body 5 can realize larger penetration depth at the same launching cost, the miniaturization and light-weight design of the perforator are facilitated, and the YG6 tungsten alloy material with high density is selected as the material of the penetration body 5. (2) penetration of projectile 5 launching speed matching: and (3) according to the data of the uniaxial compression-resistant shear test of the lunar soil water ice simulated at the ultralow temperature, establishing a stress yield model of the lunar soil water ice. And correcting a Forrestal penetration prediction formula by using a yield model of the lunar soil water ice, and matching the transmitting speed of the penetration projectile body 5, the corresponding propellant charge and the length parameter of the transmitting barrel 3 by combining the penetration depth required by lunar soil water ice in-situ sampling detection.
In a further embodiment of the invention, a low recoil non-polluting launch technique: (1) low recoil launching technology: as shown in fig. 2, the system composition diagram of the firer-actuated perforator is shown, in the launching process, the mechanical arm is used for elastically and flexibly clamping the perforator, the rest part of the perforator in the launching process is separated from a clamping interface of the mechanical arm and flies away in the opposite direction of launching to balance the recoil force in the launching process of the penetration projectile 5, the recoil force to the mechanical arm in the whole process is only the clamping force of the clamping interface, and is expected to be less than 20N, and the action time is less than 1ms.
In a further embodiment of the invention, in order to reduce the load requirement when the mechanical arm clamps the perforator, the design process of the transmitting production tube adopts the design of an equal-strength structure, so that the scheme forms a clamping sleeve 6 with a porous structure on the surface of the metallic transmitting body tube 3 by using light composite winding, and the perforator is enveloped into a sleeve
The cylindrical structure of (3) makes the launching barrel (3) smoothly separated in the launching process. The composite porous clamping sleeve 6 has certain energy absorption and vibration isolation characteristics, and can effectively reduce the disturbance of strong vibration in the launching process to the mechanical arm. (2) pollution-free sealed emission technology: in order to reduce the large-area leakage of combustion residues generated in the combustion process of the high-energy propellant, a mode of sealing a piston 7 is adopted in the design, and the high-energy propellant and the launching barrel 3 form a closed combustion cavity together. High-energy high-pressure gas generated by deflagration of the high-energy propellant powder pushes the perforating bullet to accelerate to a target launching speed by pushing the sealing piston 7, and the penetration projectile body 5 completes penetration hole forming on lunar soil water ice by means of the inertia speed of the projectile body out of the chamber; the sealing piston 7 is retained in the launching barrel 3 due to the blocking effect of the shaft shoulder at the opening of the launching barrel 3, seals the combustion residue in the launching barrel 3 and flies away from the sampling detection point along with the launching barrel 3, thereby effectively avoiding the leakage and pollution of the combustion residue.
In a further embodiment of the invention, the perforator is subordinate to a lunar soil water ice section flexible endoscopic sampling detection system carried by the flight device. After the sampling detection point is selected by the flying device, a cooperative mechanical arm carried by the flying device grabs the perforator and establishes ignition electrical connection with the perforator through a clamping interface, and the mechanical arm transfers the perforator to a predetermined area of the detection point and then adjusts the perforation posture of the perforator. The perforator receives the firing instruction of the flasher, the chemical energy of the propellant powder in the perforator is converted into the kinetic energy of the penetration projectile body 5, and penetration and hole forming are achieved on the lunar surface of the penetration projectile body 5. Meanwhile, the propellant combustion products are sealed in the launching barrel 3 and fly away from the flyer in the opposite direction along with the launching barrel 3.
In a further embodiment of the invention, after the flying device selects the sampling detection point, a cooperative mechanical arm carried by the flying device grabs the perforator and establishes an ignition electrical connection with the perforator through the multiplexing interface 11, and the mechanical arm transfers the perforator to the predetermined area of the detection point and then adjusts the perforation posture of the perforator. The perforator receives a flasher ignition instruction, an igniter 2 in the perforator ignites, high-energy powder 4 is filled in the perforator, the high-energy powder 4 burns to generate high-temperature and high-pressure gas, the sealing piston 7 and the penetration body 5 are pushed to move forwards, the sealing piston 7 and the penetration body 5 are accelerated to a speed of more than 350m/s, when the sealing piston 7 moves to the outlet position of the launching barrel 3, the sealing piston 7 is limited in the launching barrel 3, the sealing piston 7 is separated from the penetration body 5, the penetration body 5 penetrates the moon surface at a high speed after flying out of the launching barrel 3, and a penetration hole forming function is achieved. Meanwhile, the combustion products of the high-energy gunpowder 4 are sealed in the launching barrel 3 and fly away from the flyer along with the shell in the opposite direction.
In a further embodiment of the present invention, the high-energy powder 4 should be a propellant with high burning rate, high explosive power and high gas yield.
In a further embodiment of the invention, the materials of the launching barrel 3, the tail plug 1, the sealing piston 7 and the like are ultrahigh strength steel (sigma r0.2 is more than or equal to 1515 MPa) for aerospace, the positioning ring 10 is made of titanium alloy or aluminum alloy with lower density and higher strength, and the penetration projectile body 5 is made of tungsten alloy steel with high strength and high density.
In a further embodiment of the invention, the firing element in the perforating gun is a mature dual bridge live igniter 2.
In a further embodiment of the invention, the high-energy explosive 4 in the igniter 2 is potassium nitrate ignition powder with the dosage of 0.3g.
The energy required for reliable ignition of the double bridge belt:
W BXQ ＝I 2 Rt＝10^2×0.6×20×10 -3 J＝1.2J
in a further embodiment of the invention, the moisture content of the high-energy explosive 4 itself is equal to or less than 0.5%, whereby the maximum moisture mass of the high-energy explosive 4 itself is estimated to be about 0.12g;
in a further embodiment of the invention, the combustion of the nitrocellulose and nitroglycerine in the high-energy explosive 4 generates moisture.
In a further embodiment of the invention, the nitrocellulose has the formula C 12 H 17 (ONO 2 ) 3 O 7 ～C 12 H 14 (ONO 2 ) 6 O 7 Without an exact combustion reaction equation, a simplified equation is used to estimate the mass of moisture in the combustion products.
In a further embodiment of the invention, the nitrocellulose combustion reaction is simplified by the equation:
C 12 H 17 (ONO 2 ) 3 O 7 →8.5H 2 o + remaining substances
459 8.5×18
24g×65.5％ 5.240g
C 12 H 14 (ONO 2 ) 6 O 7 →7H 2 O + remaining substances
642 7×18
24g×61.5％ 2.897g
In a further embodiment of the invention, the nitroglycerin combustion reaction equation:
4C 3 H 5 N 3 O 9 →10H 2 O+12CO 2 +O 2 +6N 2
4×227 10×18 12×44 32 6×28
24g×36％1.713g
24g×32％1.523g
the calculation shows that the water content in the combustion product of the high-energy gunpowder 4 is (4.610-6.953) g.
In a further embodiment of the invention, the H element in the lead stevensonate resides primarily in the lead stevensonate molecule and in small volatile amounts, wherein the maximum mass of moisture produced by the combustion reaction is about 0.9238mg, the maximum mass of volatile amounts is about 0.03%, and the maximum mass of moisture is calculated to be about 0.0048mg.
In a further embodiment of the invention, the H element in the lead azide is present predominantly in a small amount of volatiles, up to a maximum of about 0.03% by mass, and the maximum mass of moisture is calculated to be about 0.018mg.
In a further embodiment of the invention, the H element in the potassium borate nitrate ignition charge is mainly present in a small amount of volatile matter, the mass ratio is about 1% at the maximum, and the maximum mass of water is calculated to be about 3mg.
In a further embodiment of the invention, the maximum mass of moisture in the combustion products of igniter 2 is calculated to be about 4mg.
In a further embodiment of the invention, the maximum mass of water in the combustion products in the perforating gun is calculated to be about 6.957g.
In a further embodiment of the invention, the penetration of the projectile 5 is designed and calculated: penetration of the projectile 5 mass: 0.2kg; penetration of outer diameter of projectile 5:
penetration projectile 5 length: 85mm; penetration of the elastomer 5 material: tungsten alloy steel.
In a further embodiment of the invention, the inner missile design and calculation: the quality of the pill is as follows: 0.225kg (penetration projectile body 5+ sealing piston 7+ locating sleeve); the outer diameter of the projectile is as follows:
(bore diameter of bore)
) (ii) a Initial speed of the pill: 350m/s (absolute velocity on the moon); expansion coefficient of the medicine chamber: 2.713; volume of the medicine chamber: 0.0308dm3; loading quantity: 24g of a mixture; maximum chamber pressure: 450MPa; the pellet extrusion pressure: 40MPa; gunpowder parameters and powder power: 119.1X 104 kg. Dm/kg; specific heat ratio: 1.231; and (3) remaining capacity: 1dm3/kg; gunpowder density: 1.6g/cm3.
In a further embodiment of the invention, the inner trajectory solution: the curves of the inner trajectory P-L, P-t and the v-L, v-t are obtained by solving through a fourth-order Runge-Kutta method, and the data of the inner missile obtained through solving are shown in a table 13.
Ballistic parameters in Table 13
In a further embodiment of the invention, the launching barrel 3 is designed and calculated: the relationship curve of the chamber pressure, the travel and the time can be obtained from the inner ballistic curve, and the table 14 is the relationship curve of the chamber pressure, the travel and the time.
Ballistic data sheet in table 14
In a further embodiment of the invention, the material selection is: the material of the transmitting barrel 3 is 40CrNi2SiMoVA (300M) with tensile strength sigma b ＝1860MPa，σ r0.2 ＝1515MPa。
In a further embodiment of the invention, the theoretical profile of the launch barrel 3 is determined: by
r 2 ＝ar 1 The theoretical dimensions of the launching barrel 3 can be obtained and are specified in table 15.
In a further embodiment of the invention, the dimensions of the transmitting barrel 3 are shown in table 16.
In a further embodiment of the invention, the transmitting barrel 3 is intensity checked: the strength of the transmitting barrel 3 is checked using the maximum tensile strain theory. The intensity check formula is as follows:
after checking, the strength of the transmitting barrel 3 meets the requirement.
In a further embodiment of the invention, the mass of the various parts of the perforating gun is shown in Table 17.
TABLE 17 perforator major component quality statistics
In a further embodiment of the invention, the penetration of the absolute velocity of the projectile 5 is: from the momentum balance equation: -MV + μ v ωpj +mv a =0, where M represents the weight of the launch barrel 3, the tail plug 1, the igniter 2, and the positioning ring 10, V represents the recoil speed of the launch barrel 3, μ represents the powder mass, and V represents the weight of the powder ωpj Indicating the mean velocity of the powder, m indicating the mass of the penetrating projectile 5, the sealing piston 7 and the locating ring 10, v a Indicating the absolute velocity of penetrating projectile 5.
In a further embodiment of the invention, due to μ v ωpj Smaller and negligible. Calculated to give v a ＝351.1m/s。
In a further embodiment of the present invention, v a And when the penetration speed is more than 350m/s, the initial speed of the penetration projectile body 5 meets the requirement.
In a further embodiment of the invention, the analysis of lunar soil profile characteristics: since Watson et al first proposed the possibility of water ice on the moon in 1961, evidence of water ice substances in a permanently shaded area of the south pole of the moon was found by various means such as ground-based remote sensing, satellite-borne remote sensing and ground penetrating radar. But is limited by the remote sensing detection principle and influenced by factors such as interference of surface star soil on signals, and the like, and the error of the result obtained by low-orbit remote sensing detection and lander patrol detection is larger. Therefore, in order to further and deeply analyze the scientific information of the water ice state in the moon shadow pit, the deep high-fidelity sample collection and in-situ detection are required to be realized. In order to better meet the requirement of permanent shadow pit sampling detection, the reasonable design of the sampling detection machine tool and the parameter optimization of the sampling detection system, the texture and the mechanical characteristics of lunar soil profiles in the lunar south pole permanent shadow pits are analyzed.
In a further embodiment of the present invention, there are several features of the profile configuration in the permanent shadow pits of the moon polar region based on the analysis of a large amount of telemetry data at the early stage of NASA. Under the thin frost layer, anhydrous dry soil with average thickness of about 400mm and extremely low strength is distributed, and the ice soil mixing layer is distributed in a region with thickness of about 1m between the dry soil layer and the lunar rock layer in a large area.
In a further embodiment of the invention, because lunar soil in different depth sections is subjected to different degrees of weathering, the water content of the ice soil mixed layer is distributed in a gradient manner along the depth of the section, and the closer to the lunar soil surface layer, the ice soil mixed layer is and the lower the water content is. According to the engineering requirements of sampling detection, according to the average value of the water content of the lunar soil water ice, a region with the section depth of 400 mm-800 mm is defined as a lunar soil water ice layer with the water content of 5%, and a depth region below 800mm is defined as a lunar soil water ice layer with the water content of 10%.
In a further embodiment of the invention, according to the analysis result of the lunar soil profile characteristics, in order to realize in-situ sampling detection of a lunar soil water ice sample with a water-rich rate, a sampling detection tool needs to enter a lunar soil profile layer with a depth range of 400 mm-800 mm for multipoint sampling.
In a further embodiment of the invention, the density is 1.98g/cm 3 The mechanical properties of the water-free dry lunar soil of (1) are shown in Table 18.
TABLE 18 lunar soil mechanics characteristic parameter Table
In a further embodiment of the invention, the average uniaxial compressive strength of the anhydrous dry lunar soil is about 0.005MPa by substituting the parameters of the internal friction angle and the cohesion force of the lunar soil into the following formula.
In a further embodiment of the invention, the uniaxial compressive strength of the lunar soil water ice with a certain water content is related to the water content of the lunar soil water ice and the temperature environment. In the previous pre-research work, a uniaxial compression test is carried out on simulation samples of lunar soil water ice with water contents of 5% and 10% under different temperature conditions, and uniaxial compression strength values under different temperature conditions are measured through the uniaxial compression test. Considering the equipment limitation of the existing low-temperature freezing condition, the low temperature can only reach minus 80 ℃, and the uniaxial compressive strength of the lunar soil water ice under the extreme low-temperature condition of 40K (-230 ℃) at the south pole of the moon can be considered to be explored by a data extension method. The project combines the existing test data and the result of NASA test at-200 ℃ and adopts the S-type function y = a/(1 + exp) (-k (x-x) e ) ) carrying out regression modeling on the uniaxial compressive strength of a sample at-200 to-10 ℃, and obtaining the simulated lunar soil water ice compressive strength data under the condition of 5 percent of water content of 10 percent and at-230 ℃ by an epitaxial method.
In a further embodiment of the present invention, according to the above calculation and analysis results, uniaxial compressive strength values of lunar soil water ice with different water contents under the condition of 40K (-230 ℃) extreme low temperature environment are obtained, as shown in Table 19.
TABLE 19 uniaxial compressive strength parameter table for lunar soil with different water contents
| Lunar soil type | Waterless dry lunar soil | Lunar soil water ice with 5% water content | Lunar soil water ice with 10% water content |
| Compressive strength of single axis | 0.005MPa | 10MPa | 40MPa |
In a further embodiment of the present invention, according to the analysis results of the above target characteristics and the system sampling detection requirements, in order for the endoscopic sampling probe to perform in-situ detection sampling on lunar soil water ice with rich water content, it is required that the depth of the detection sampling hole formed by the penetration projectile 5 after penetration is completed is about 800mm, that is, the penetration projectile 5 completely penetrates through the dry soil layer and the ordinary lunar soil water ice layer with a water content of 5% and a penetration depth of one projectile length in the high-strength lunar soil water ice layer with a water content of 10%.
In a further embodiment of the present invention, the penetration efficiency of penetrating projectile 5 is related to its initial kinetic energy, and the relationship between penetration depth of penetrating projectile 5 to achieve the target penetration depth and the initial kinetic energy of penetrating projectile 5 can be obtained according to a semi-empirical formula obtained from a large number of target practice correction theories by Forrestal et al, as shown in the following formula.
In the formula: p-penetration depth; e k Penetration of the initial kinetic energy of the projectile; n-spring modulus; a-the diameter of the projectile; ρ -target bulk density; m-mass of the elastomer; f. of c ' -uniaxial compressive strength; s-value of intensity coefficient;
in a further embodiment of the present invention, the S value is a strength factor value of the target material, and for a material meeting the moore yield criterion, the relationship between the S value and the uniaxial compressive strength of the target material can be approximately expressed by the following formula. Uniaxial compressive strengths of the lunar soil water ice of different water contents are shown in table 19.
S＝82.6(f c '/10 6 ) -0.544
In a further embodiment of the invention, the kinetic energy required for penetrating the dry lunar soil, the lunar soil water ice with a water content of 5% and for achieving a penetration depth in the lunar soil water ice with a water content of 10% is respectively E according to the formula 1 、E 2 、E 3 The initial kinetic energy E of the penetrating projectile 5 can be obtained from the conservation of energy z ＝E 1 +E 2 +E 3 The initial launch velocity of penetration projectile 5 is
m is the mass of penetrating projectile 5.
In a further embodiment of the invention, the material of the penetrating elastomer 5 is chosen to have a density of 15g/cm 3 The matching results of the YG6 tungsten alloy material are shown in Table 20.
Table 20 penetration projectile body parameter matching result table
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention.
Claims (10)
1. A fireactuated perforating gun for detection of a star profile, comprising: penetration body (5), centre gripping sleeve (6), launching barrel (3) and high energy powder (4), launching barrel (3) includes: the high-energy powder gun comprises a cavity portion (15) and a tubular portion (14) connected with an opening of the cavity portion (15), an igniter (2) is installed at the bottom of the cavity portion (15), the cavity portion (15) is used for containing the high-energy powder (4), a sealing piston (7) is arranged at the opening of the cavity portion (15), the sealing piston (7) is used for blocking the high-energy powder (4) from entering the tubular portion (14), a penetration projectile body (5) is arranged in the tubular portion (14), the bottom of the penetration projectile body (5) is movably connected with the sealing piston (7), the tubular portion (14) is installed in a clamping sleeve (6), and a multiplexing interface (11) connected with a control system is arranged on the outer wall of the clamping sleeve (6).
2. The firepower-actuated perforating gun for star profile detection as claimed in claim 1, further comprising: the positioning ring (10) is installed in the tubular portion (14), the inner diameter of each positioning ring (10) is matched with the outer diameter of the penetration body (5), and the penetration body (5) and the launching barrel (3) are coaxially arranged through the plurality of positioning rings (10).
3. A firepower actuated perforating gun for star profile detection as claimed in claim 2 further comprising: the tail plug (1) is installed at the bottom of the cavity portion (15), and the tail plug (1) is used for blocking the leakage of the high-energy gunpowder (4) from the bottom of the cavity portion (15).
4. A firepower actuated perforating gun for star profile detection as claimed in claim 3 further comprising: and the sealing ring (9) is arranged between the launching barrel (3) and the sealing piston (7).
5. A firepower actuated perforator facing a planet profile exploration as claimed in claim 1 wherein the outer diameter of the penetrating projectile (5) is 15mm and the length of the penetrating projectile (5) is 85mm.
6. A firepower actuated perforating gun for star profile exploration as claimed in claim 1, characterized in that the length of the launching barrel (3) is 420mm.
7. Fireman actuated perforator facing a planet section probing according to claim 1 wherein the inner diameter of the end of the tubular part (14) remote from the cavity (15) is smaller than the inner diameter of the end of the tubular part (14) connected to the cavity (15), the outer diameter of the end of the tubular part (14) remote from the cavity (15) is larger than the outer diameter of the end of the tubular part (14) connected to the cavity (15), the outer wall of the tubular part (14) and the inner wall of the clamping sleeve (6) matching.
8. Firepower actuated perforator facing a planet profile exploration, according to claim 1, wherein the penetrating projectile (5) is bullet shaped, the penetrating projectile (5) and the sealing piston (7) being articulated by means of a plurality of shear pins (8).
9. Fireman actuated perforator facing a star profile exploration according to claim 1 wherein a plurality of cavity spaces (13) are provided between the inner and outer wall of the clamping sleeve (6), a plurality of said cavity spaces (13) being used for sound and shock damping of the perforation process.
10. A firepower-actuated perforating gun for star profile detection as claimed in claim 1, characterized in that the multiplex interface (11) and the igniter (2) are connected by two initiation signal cables (12).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211490082.3A CN115753179A (en) | 2022-11-25 | 2022-11-25 | Firer actuated perforator for detecting section of planet |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211490082.3A CN115753179A (en) | 2022-11-25 | 2022-11-25 | Firer actuated perforator for detecting section of planet |
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| CN202211490082.3A Pending CN115753179A (en) | 2022-11-25 | 2022-11-25 | Firer actuated perforator for detecting section of planet |
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