CN112098460A - Coupling burning method based on special burning device for propellant powder grains - Google Patents
Coupling burning method based on special burning device for propellant powder grains Download PDFInfo
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- 239000003380 propellant Substances 0.000 title claims abstract description 194
- 239000000843 powder Substances 0.000 title claims abstract description 182
- 238000000034 method Methods 0.000 title claims abstract description 32
- 230000008878 coupling Effects 0.000 title claims abstract description 6
- 238000010168 coupling process Methods 0.000 title claims abstract description 6
- 238000005859 coupling reaction Methods 0.000 title claims abstract description 6
- 238000010438 heat treatment Methods 0.000 claims abstract description 214
- 230000005855 radiation Effects 0.000 claims abstract description 14
- 239000007789 gas Substances 0.000 claims description 96
- 230000007246 mechanism Effects 0.000 claims description 92
- 238000009413 insulation Methods 0.000 claims description 23
- 238000012544 monitoring process Methods 0.000 claims description 23
- 238000007789 sealing Methods 0.000 claims description 8
- 230000008859 change Effects 0.000 claims description 7
- 230000003247 decreasing effect Effects 0.000 claims description 4
- 239000002360 explosive Substances 0.000 claims description 3
- 238000011049 filling Methods 0.000 claims description 3
- 230000001360 synchronised effect Effects 0.000 claims description 2
- 238000009841 combustion method Methods 0.000 claims 2
- 230000002269 spontaneous effect Effects 0.000 abstract description 20
- 238000002485 combustion reaction Methods 0.000 abstract description 14
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- 238000005485 electric heating Methods 0.000 description 2
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- G01N25/00—Investigating or analyzing materials by the use of thermal means
- G01N25/50—Investigating or analyzing materials by the use of thermal means by investigating flash-point; by investigating explosibility
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Abstract
The invention discloses a coupling roasting method based on a special roasting device for a propellant powder column, which realizes heat conduction heating, heat radiation heating or heat convection heating of the propellant powder column in the roasting device, can also realize at least two heating modes in three heating modes, and can control different humidity of the propellant powder column according to actual test conditions. The invention improves the accuracy of simulating spontaneous combustion and spontaneous explosion of the propellant caused by the influence of the environment, and has safe test. The invention is suitable for the technical field of propellant powder column burning.
Description
Technical Field
The invention belongs to the technical field of propellant powder grain roasting, and particularly relates to a coupling roasting method based on a special roasting device for propellant powder grains.
Background
Ammunition is an important component of weaponry and is a terminal body for destroying targets in a combat system. Among the ammunition components, the propellant is most susceptible to decomposition and heat release under the influence of the environment, so that spontaneous combustion and spontaneous explosion occur.
The existing propellant powder burning explosion research adopts the classical thermal explosion theory to carry out qualitative theoretical analysis, but lacks experimental verification, and particularly, the large-dosage large-diameter experiment is still in the theoretical stage at present; some small experiments are carried out, but the theoretical guidance closely connected with engineering is lacked; some theoretical models ignore the fact that the thermal decomposition of the propellant is related to the experienced reaction process, in addition, the radiation is ignored on the boundary condition of heat dissipation, and the convective heat transfer coefficient is also considered as a constant, so that the accuracy of truly simulating the spontaneous combustion and spontaneous explosion of the propellant caused by the influence of the environment is ensured.
Disclosure of Invention
The invention provides a grain heat conduction burning method, a heat radiation burning method and a heat convection burning method which can improve the accuracy of simulating spontaneous combustion and spontaneous explosion of a propellant powder caused by the influence of the environment and improve the test safety performance.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a heat conduction roasting method for explosive column includes the following steps:
s1, assembling the propellant powder grain with one of the two fixing seats, and ensuring that the heat insulation rod on the fixing seat is inserted into the assembling hole of the propellant powder grain;
s2, inserting the heat insulation rod on the other fixing seat into the corresponding assembly hole of the propellant powder grain, when the heat insulation rod is completely inserted into the propellant powder grain, assembling the fixing seat and the corresponding end part of the propellant powder grain, and tightly connecting the two fixing seats and the heating cylinder to form a sealed space;
s3, filling the heating cylinder with heat-conducting gas, keeping the pressure in the heating cylinder at normal pressure, and humidifying the heating cylinder to make the humidity in the heating cylinder reach a preset value;
s4, continuously heating the heating cylinder until the heating cylinder is heated to a preset temperature, and controlling the heated amount of the heating cylinder to keep the preset temperature in a preset time;
s5, monitoring the temperature changes of the propellant powder grain at different radial depths until the propellant powder grain burns, analyzing to obtain the time length required by the burning of the propellant powder grain at the preset temperature, and obtaining the internal burning condition of the propellant powder grain.
Further, in step S1, the end cap of the fixed fixing seat is selected to be connected and fixed with one end of the heating cylinder in advance, or the end cap is assembled with the propellant powder and then connected and fixed with the heating cylinder.
Further, in step S4, the driving mechanism is controlled to drive the fixing base to drive the propellant powder grains to rotate while the heating cylinder is heated.
The invention also discloses a heat radiation burning method for the grain, which comprises the following steps:
s1, assembling the propellant powder grain with one of the two fixing seats, and ensuring that the heat insulation rod on the fixing seat is inserted into the assembling hole of the propellant powder grain;
s2, inserting the heat insulation rod on the other fixing seat into the corresponding assembly hole of the propellant powder grain, when the heat insulation rod is completely inserted into the propellant powder grain, assembling the fixing seat and the corresponding end part of the propellant powder grain, and tightly connecting the two fixing seats and the heating cylinder to form a sealed space;
s3, vacuumizing the heating cylinder, and sealing all channels directly and indirectly communicated with the heating cylinder when the vacuum degree reaches one hundred percent;
s4, continuously heating the heating cylinder until the heating cylinder is heated to a preset temperature, and controlling the heated amount of the heating cylinder to keep the preset temperature in a preset time;
s5, monitoring the temperature changes of the propellant powder grain at different radial depths until the propellant powder grain burns, analyzing to obtain the time length required by the burning of the propellant powder grain at the preset temperature, and obtaining the internal burning condition of the propellant powder grain.
Further, in step S4 and step S5, when the degree of vacuum in the heater cylinder becomes low, two or more times of vacuuming are performed until the degree of vacuum does not change before the propellant grains are burned.
Further, in step S4, the driving mechanism is controlled to drive the fixing base to drive the propellant powder grains to rotate while the heating cylinder is heated.
The invention also discloses a method for roasting and burning the grains by thermal convection, which comprises the following steps:
s1, assembling the propellant powder grain with one of the two fixing seats, and ensuring that the heat insulation rod on the fixing seat is inserted into the assembling hole of the propellant powder grain;
s2, inserting the heat insulation rod on the other fixing seat into the corresponding assembly hole of the propellant powder grain, when the heat insulation rod is completely inserted into the propellant powder grain, assembling the fixing seat and the corresponding end part of the propellant powder grain, and tightly connecting the two fixing seats and the heating cylinder to form a sealed space;
s3, enabling the heated gas to enter the heating cylinder through a thermal convection mechanism to finish the convection or direct current or rotational flow movement of the gas in the heating cylinder;
s4, continuously heating the gas passing through the heating cylinder by the thermal convection mechanism, simultaneously heating the gas in the heating cylinder by the heating cylinder until the temperature in the heating cylinder reaches a preset temperature, and controlling the heating quantity of the heating cylinder and the thermal convection mechanism to keep the propellant powder charge at the preset temperature within a preset time;
s5, monitoring the temperature changes of the propellant powder grain at different radial depths until the propellant powder grain burns, analyzing to obtain the time length required by the burning of the propellant powder grain at the preset temperature, and obtaining the internal burning condition of the propellant powder grain.
Further, in step S4, the gas passing through the heat convection mechanism is humidified by the heat convection mechanism so that the humidity in the heating cylinder is maintained at a predetermined value.
Further, in the step S3, the convection is that the gas enters the heating cylinder from the thermal convection mechanisms at the two ends of the heating cylinder, the two gases collide with each other in the heating cylinder, and the flow rates of the two gases are the same or different; or the flow rate of each gas is gradually increased and then decreased, so as to reciprocate, and the flow rate increase or decrease of the two gases is synchronous or asynchronous.
Further, the swirling flow described in step S3 is divided into a direct swirling flow and a convective swirling flow, wherein,
d, direct current rotational flow: selecting a heat convection mechanism from the gases to enter the heating cylinder, humidifying the gases according to the requirements, sending the gases out of the heating cylinder by the other heat convection mechanism, and simultaneously driving a fixing mechanism for fixing the propellant powder columns to rotate, wherein the fixing mechanism acts on the gases flowing through the fixing mechanism to enable the gases to generate rotational flow;
convection rotational flow: the gas enters the heating cylinder from the heat convection mechanisms at the two ends of the heating cylinder respectively, the two gas strands collide with each other in the heating cylinder, the fixing mechanism for fixing the propellant powder charge is driven to rotate, the gas flowing through the fixing mechanism acts on the fixing mechanism, the gas generates rotational flow, and the gas of the two rotational flow strands collides with each other.
The invention also discloses a multi-item coupling burning method for the propellant powder grains, which comprises the steps of burning the propellant powder grains by at least two methods of the three methods and monitoring the temperature change conditions of the inner part and the space of the propellant powder grains in real time.
Due to the adoption of the structure, compared with the prior art, the invention has the technical progress that: because the two ends of the heating cylinder are respectively provided with the heat convection mechanisms, the heating mode is as follows: firstly, selecting a heat convection mechanism for gas to enter the heating cylinder, and discharging the gas from the other heat convection mechanism out of the heating cylinder, so that heat exchange between the propellant powder column and the direct-current gas is realized; secondly, the gas enters the heating cylinder from the two heat convection mechanisms, and two strands of gas generate convection in the heating cylinder, so that the heat exchange between the propellant powder columns and the convection gas is realized; thirdly, gas enters the heating cylinder in the two forms, the fixing mechanism is rotated at the same time to enable the propellant powder grain to rotate, the fixing mechanism disturbs the gas and forms rotational flow, the rotational flow is divided into two types, namely direct-current rotational flow and convection rotational flow, and heat exchange of the propellant powder grain under the condition of gas rotational flow is realized; selecting a heat convection mechanism from gas to enter and fill the heating cylinder to seal each channel communicated with the heating cylinder, heating the heating cylinder, and transferring heat to the propellant powder columns through the gas in the cylinder so as to heat the propellant powder columns through heat conduction; closing all channels communicated with the heating cylinder, only leaving a thermal convection mechanism to be communicated with the heating cylinder, and vacuumizing the heating cylinder through the thermal convection mechanism to enable the propellant powder columns in the heating cylinder to be in a vacuum state, so that the heat can heat the propellant powder columns only in a thermal radiation mode, and further the simulated propellant powder column thermal radiation heating is realized; sixthly, combining at least two modes in the five heating modes, and heating in a combined mode; seventhly, in the heating modes from one to six, along with the control of the humidity in the heating cylinder, the simulated spontaneous combustion duration and the spontaneous combustion condition of the propellant powder columns under different temperature and humidity combinations are realized; in conclusion, the invention can simulate various conditions of spontaneous combustion of the propellant powder charge and improve the accuracy of simulating spontaneous combustion and spontaneous explosion of the propellant powder due to environmental influence.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention.
In the drawings:
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a cross-sectional view of an axial structure of an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of the embodiment of the present invention after the detachment of the driving mechanism;
FIG. 4 is a schematic structural view of the two fixing mechanisms for clamping and fixing the propellant charge in accordance with the embodiment of the present invention;
FIG. 5 is a schematic view of a fixing mechanism coupled to an end cap according to an embodiment of the present invention;
FIG. 6 is a schematic structural diagram illustrating a connection between a fixing base and a monitoring unit in a fixing mechanism according to an embodiment of the present invention;
FIG. 7 is a schematic view of the structure of FIG. 6 from another angle;
FIG. 8 is a schematic structural diagram of another fixing base according to an embodiment of the present invention;
fig. 9 is a schematic structural diagram of a thermal convection mechanism according to an embodiment of the present invention.
Labeling components: 1-horizontal cylinder, 2-base, 3-end cover, 4-assembly cavity, 5-bearing, 6-sealing cover, 7-fixing seat, 8-rotating shaft, 9-female joint, 10-wire channel A, 11-wire channel B, 12-guide plate, 13-sleeve body, 14-locking bolt, 15-conductive slip ring, 16-driven wheel, 17-driving wheel, 18-driving motor, 19-first electromagnetic heating coil, 20-outlet pipe, 21-propellant powder column, 22-assembly hole, 23-heat insulation rod, 24-hollow cavity, 25-first temperature sensor, 26-humidity sensor, 27-pressure sensor, 28-inlet manifold, 29-second electromagnetic heating coil, 30-connecting pipe, 31-uniform distribution pipes, 32-joint pipes, 33-connecting sleeves, 34-inlet branch pipes and 35-second temperature sensors.
Detailed Description
Preferred embodiments of the present invention will be described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are for purposes of illustration and explanation only and are not intended to limit the present invention.
The invention discloses a propellant powder grain burning device capable of changing multiple burning modes, which comprises a heating cylinder, a driving mechanism, two fixing mechanisms and two heat convection mechanisms as shown in figure 1, wherein the heating cylinder has a heating function, and the general adopted modes comprise: the heating cylinder comprises a horizontal cylinder body 1, and a steam heating pipe or a hot oil heating pipe or an electric heating wire or a first electromagnetic heating coil 19 is spirally wound on the periphery of the horizontal cylinder body 1; and the heating cylinder comprises a horizontal cylinder body 1, the horizontal cylinder body 1 is of an interlayer structure, and a steam heating coil or a hot oil heating coil or an electric heating wire or a first electromagnetic heating coil 19 is arranged in the interlayer or is directly communicated with media such as hot water, hot oil or steam. The horizontal cylinder 1 is supported by a base 2. Two end covers 3 are respectively through bolt demountable installation at the axial both ends of cartridge heater for seal into sealed space with the cartridge heater, and foretell two fixed establishment rotate respectively and connect on two end covers 3, and fixed establishment is used for fixed propellant powder grain 21 and monitors propellant powder grain 21 temperature. One of the two fixing mechanisms is in transmission connection with a driving mechanism, and the driving mechanism is arranged outside the heating cylinder. The two heat convection mechanisms are installed at both axial ends of the heating cylinder and are both communicated with the inside of the heating cylinder, and a first temperature sensor 25, a humidity sensor 26 and a pressure sensor 27 are installed on the heating cylinder. The working principle and the advantages of the invention are as follows: because the two ends of the heating cylinder are respectively provided with the heat convection mechanisms, the heating modes of the heating cylinder for the propellant powder grain 21 are various, specifically: firstly, selecting a heat convection mechanism from the gases to enter the heating cylinder, and discharging the gases out of the heating cylinder from the other heat convection mechanism, so that the heat exchange between the propellant powder column 21 and the direct current gas is realized; secondly, the gas enters the heating cylinder from the two heat convection mechanisms, and two strands of gas generate convection in the heating cylinder, so that the heat exchange between the propellant powder grains 21 and the convection gas is realized; thirdly, gas enters the heating cylinder in the two forms, the fixing mechanism is rotated at the same time to enable the propellant powder grain 21 to rotate, the fixing mechanism disturbs the gas and forms rotational flow, the rotational flow is divided into two types, namely direct-current rotational flow and convection rotational flow, and heat exchange of the propellant powder grain 21 is realized under the condition of gas rotational flow; selecting a heat convection mechanism from gas to enter and fill the heating cylinder to seal each channel communicated with the heating cylinder, heating the heating cylinder, transferring heat to the propellant powder grains 21 through the gas in the cylinder, and further heating the propellant powder grains 21 through heat conduction; closing all channels communicated with the heating cylinder, only leaving a thermal convection mechanism to be communicated with the heating cylinder, and vacuumizing the heating cylinder through the thermal convection mechanism to enable the propellant powder columns 21 in the heating cylinder to be in a vacuum state, so that heat can only heat the propellant powder columns 21 in a thermal radiation mode, and further the simulated propellant powder columns 21 are heated in a thermal radiation mode; sixthly, combining at least two modes in the five heating modes, and heating in a combined mode; seventhly, in the heating modes from the first to the sixth, along with the control of the humidity in the heating cylinder, the simulated spontaneous combustion duration and the spontaneous combustion condition of the propellant powder columns 21 under different temperature and humidity combinations are realized; in conclusion, the invention can simulate various conditions of spontaneous combustion of the propellant powder charge 21 and improve the accuracy of simulating spontaneous combustion and spontaneous explosion of the propellant powder caused by environmental influence.
As a preferred embodiment of the present invention, as shown in fig. 1-2, the heat convection mechanism includes an inlet header pipe 28, a distributor pipe 31, a connecting pipe 30, and a plurality of inlet branch pipes 34. The inlet branch pipes 34 are uniformly constructed on the end cover 3, each inlet branch pipe 34 extends into the heating cylinder along the axial direction of the heating cylinder, gas entering the heating cylinder through the inlet branch pipes 34 cannot be blocked by the end part of the propellant powder column 21 at the end, one end of each inlet branch pipe 34, which is positioned outside the heating cylinder, is communicated with the annular uniform distribution pipe 31, and the uniform distribution pipe 31 is communicated with the inlet main pipe 28 through at least two connecting pipes 30 communicated with the uniform distribution pipe 31. The working principle of the embodiment is as follows: the gas passes through the inlet header 28, the connecting pipe 30, the uniform distribution pipe 31 and each inlet branch pipe 34 in sequence by a power source (generally a gas pump), then enters the heating cylinder, and exchanges heat with the propellant powder column 21. In order to keep the temperature of the gas and the temperature in the heating cylinder constant, in the embodiment, a second electromagnetic heating coil 29 is sleeved outside the inlet manifold 28 or each connecting pipe 30 and used for heating the gas flowing through, and the second electromagnetic heating coil 29 is complementary with the heating of the heating cylinder, so that the spontaneous combustion and spontaneous explosion of the propellant powder column 21 under the condition of thermal convection are simulated. In the present embodiment, in order to replace the thermal convection mechanism with different air guide amounts, as shown in fig. 9, a joint pipe 32 is configured on the even distribution pipe 31 at a position corresponding to each inlet branch pipe 34, and the joint pipe 32 and the corresponding inlet branch pipe 34 are connected through a connecting sleeve 33. Wherein, the difference of the thermal convection mechanism of different air conduction volume lies in: the number of connecting tubes 30, the diameter of the inlet manifold 28, the length of the connecting tubes 30, etc.
As a preferred embodiment of the present invention, as shown in fig. 2, an outlet tube 20 is constructed on the cartridge heater, and the outlet tube 20 is closed by a sealing cap. The heating cylinder adopting the structure is mainly applied to the thermal convection working condition of the propellant powder grain 21, namely, hot gas enters the heating cylinder from two thermal convection mechanisms in opposite directions and generates convection, and then the mixed gas is discharged from the outlet pipe 20. Or two pipelines communicated with the outlet pipe 20 are installed on the outlet pipe, the two pipelines are respectively connected with two power sources (air pumps), the outlets of the power sources are connected with the inlets of the corresponding thermal convection mechanisms, so that the two gases form circulation between the heating cylinder and the two thermal convection mechanisms, the full utilization of heat is facilitated, the energy consumption is saved, the fluctuation of the temperature in the heating cylinder is fully reduced, and the test accuracy is improved.
In a preferred embodiment of the present invention, in order to prevent the heating cylinder and/or the fixing mechanism from being damaged due to the excessive pressure of the heating cylinder when the propellant charge 21 is exploded, a safety relief valve is installed on at least one of the heating cylinder and the end cap 3.
As a preferred embodiment of the present invention, the fixing mechanism comprises a fixing base 7 and a plurality of monitoring units, as shown in fig. 3 to 8. Wherein, the both ends of launching powder grain 21 and the position department that is located different radial length have opened a plurality of pilot holes 22 respectively, and each pilot hole 22 extends along the axial of launching powder grain 21, and each monitoring unit stretches into in the launching powder grain 21 through corresponding pilot hole 22 respectively. Fixing base 7 rotates to be connected on corresponding end cover 3, and fixing base 7 keeps away from the recess that corresponding end cover 3's one end was constructed and supplies 21 tip assemblies of propellant powder charge to fixed 21 tip of propellant powder charge, when two end covers 3 assemblies on the cartridge heater, the both ends of propellant powder charge 21 are fastened the centre gripping by two fixing base 7. Each monitoring unit can be dismantled and connect on fixing base 7 to stretch into in the propellant powder grain 21 along the axial of propellant powder grain 21, and each monitoring unit is located the position department of the different radial length of propellant powder grain 21. Thus, these monitoring units monitor the temperature change and combustion condition of the propellant charge 21 at different radial depths. Specifically, the monitoring unit comprises an insulating rod 23 with a hollow cavity 24, the insulating rod 23 extends into the propellant charge column 21, one end of the insulating rod 23 is detachably connected with the fixed seat 7, a plurality of second temperature sensors 35 extending out of the insulating rod 23 are installed on the insulating rod 23 at intervals, the number of the second temperature sensors 35 is generally at least three, the second temperature sensors 35 are not collinear, the arrangement of the non-collinear is mainly to ensure that the temperature on the non-identical line in the assembly hole 22 is measured, the average value after the deviation from a larger value is removed is closer to the real condition, the conducting wire of each second temperature sensor 35 is connected to a sub-connector through the hollow cavity 24 of the insulating rod 23, the sub-connector is constructed on the end part of the insulating rod 23, a female connector 9 is constructed on the fixed seat 7, a plurality of conducting wire passages A10 corresponding to each female connector 9 are constructed on the fixed seat 7, the lead channels A10 converge on a lead channel B11, the leads of each female joint 9 pass through the corresponding lead channel A10 and converge at the lead channel B11, the converged leads pass through the lead channel B11 to be electrically connected with a PC end, and the insulating rod is connected with the fixed seat 7 through the insertion of the sub joint and the female joint 9. The PC terminal is also electrically connected to a first temperature sensor 25, a humidity sensor 26, a pressure sensor 27, a first electromagnetic heating coil 19, a second electromagnetic heating coil 29, and a second temperature sensor 35.
As a preferred embodiment of the present invention, the specific rotational connection manner of the fixing base 7 and the end cover 3 is as follows: as shown in fig. 5, a rotating shaft 8 is configured at one end of the fixing base 7 away from the propellant powder column 21, the rotating shaft 8 extends out of the heating cylinder through the corresponding end cover 3 along the axis of the propellant powder column 21, and the rotating shaft 8 is rotatably connected with the end cover 3. Preferably, an assembly cavity 4 is formed on the end face of one side, far away from the propellant powder grain 21, of the end cover 3, the assembly cavity 4 is sunken towards the propellant powder grain 21, a bearing 5 matched with the assembly cavity 4 is assembled in the assembly cavity 4, the assembly cavity 4 is sealed through a sealing cover 6 detachably connected with the end cover 3, one end face, close to the fixing mechanism, of the assembly cavity 4 is close to the corresponding fixing mechanism, the rotating shaft 8 is assembled with the bearing 5 through the assembly cavity 4, and the rotating shaft 8 penetrates through the sealing cover 6 and extends out of the end cover 3. The purpose of the end cover 3 provided with the assembly cavity 4 is to ensure that after the propellant powder grain 21 in the heating cylinder is exploded, impact force affects the bearing 5 or directly damages the bearing 5, and the end cover 3 is matched with the sealing cover 6 to reduce impact borne by the bearing 5. The wire passage B11 is configured in the center of the rotating shaft 8 and extends out of one end of the rotating shaft 8 outside the end cover 3, the conductive slip ring 15 is installed at the end of the rotating shaft 8, the wire is electrically connected with the PC end through the conductive slip ring 15, and the wire is not twisted during the rotation of the rotating shaft 8.
As a preferred embodiment of the present invention, as shown in fig. 8, a sleeve 13 is formed at an end of the fixed base 7 away from the propellant charge 21, and an end of the rotating shaft 8 extends into the sleeve 13 and is fastened together by a plurality of locking bolts 14. Thus, the fixing seats 7 with different types can be replaced to adapt to the fixation of the propellant powder columns 21 with different lengths and radiuses.
As a preferred embodiment of the present invention, as shown in fig. 5, the outer circumferential surface of the fixed base 7 has a circular radial cross section, and a plurality of baffles 12 are uniformly formed on the outer circumferential surface of the fixed base 7. Like this, drive the pivoted process of propellant powder grain 21 at fixing base 7, the gas that gets into in the heating cylinder through heat convection mechanism is by the rotation of guide plate 12 and takes place the whirl, and then accelerates the heat transfer of propellant powder, and the heat transfer is even. In order to improve the efficiency of the swirling flow, as shown in fig. 6-8, the angle between the guide plate 12 and the outer peripheral surface of the fixing base 7 is the same, and the inclination direction of the guide plate 12 is the same as the rotation direction of the fixing base 7.
As a preferred embodiment of the present invention, as shown in fig. 1, the driving mechanism includes a driving motor 18 disposed outside the heating cylinder, an output shaft of the driving motor 18 is provided with a driving wheel 17, a driven wheel 16 is mounted on the rotating shaft 8 of one of the fixed seats 7, and the driving wheel 17 is in transmission connection with the driven wheel 16 through a chain or a belt.
As a preferred embodiment of the invention, the surfaces of the fixing base 7 and the end cap 3 are provided with heat insulation layers to avoid damage of the wires. An explosion-proof thermal imaging camera is mounted on the inner wall of the heating cylinder and used for monitoring the temperature change outside the propellant powder grain 21.
The present invention also provides a propellant powder column burning apparatus, which is different from the above-mentioned device in that two heat convection mechanisms and a guide plate 12 are eliminated, and other parts are the same as the above-mentioned embodiments, and only the propellant powder column 21 is subjected to heat radiation and heat conduction tests. The existing defects are as follows: the propellant powder grain 21 of assembly is with cartridge heater looks adaptation in the current cartridge heater to do not adopt fixed establishment to fix, the temperature sensor in the propellant powder grain 21 is pre-buried in the propellant powder grain 21 at the in-process of propellant powder grain 21 preparation, the wire of temperature sensor all can burn out after the propellant powder grain 21 is exploded, and can only carry out heat conduction test, after the propellant powder grain 21 takes place to explode, the cartridge heater takes place to warp or damage, needs subsequent maintenance. A certain space is formed between the heating cylinder of the propellant powder grain 21 roasting device and the propellant powder grain 21, pressure can be relieved through the safety relief valve in the burning and explosion process, and meanwhile, heat-conducting gas is injected into the space to realize heat conduction heating of the propellant powder grain 21 or the gas in the space is pumped completely, so that the space is in a vacuum state to realize heat radiation heating of the propellant powder grain 21; the setting of monitoring unit, it and fixing base 7 cartridge, the wire of second temperature sensor 35 on the monitoring unit is in adiabatic pole 23, is protected by adiabatic pole 23, has improved second temperature sensor 35's life, and when a certain monitoring unit damaged, only need with its pull out the monitoring unit of renewal can, easy operation. Meanwhile, the invention has convenient adjustment on humidity, is used for the space, can realize the gradual humidification on the propellant powder grain 21 only by humidifying the space, and more truly reduces the situation that the propellant powder grain 21 is in different natural environments.
The invention provides a heat conduction burning method for a grain, which comprises the following steps:
s1, assembling the propellant powder grain 21 with one of the two fixing seats 7, and ensuring that the heat insulation rod 23 on the fixing seat 7 is inserted into the assembling hole 22 of the propellant powder grain 21;
s2, the insulating rod 23 on the other fixed seat 7 is inserted into the corresponding assembly hole 22 of the propellant powder grain 21, when the insulating rod 23 is completely inserted into the propellant powder grain 21, the fixed seat 7 is assembled with the corresponding end part of the propellant powder grain 21, and the two fixed seats 7 are tightly connected with the heating cylinder and enclose to form a sealed space;
s3, filling the heating cylinder with heat-conducting gas, keeping the pressure in the heating cylinder at normal pressure, and humidifying the heating cylinder to make the humidity in the heating cylinder reach a preset value;
s4, continuously heating the heating cylinder until the heating cylinder is heated to a preset temperature, and controlling the heated amount of the heating cylinder to keep the preset temperature in a preset time;
s5, monitoring the temperature changes of the propellant powder grains 21 at different radial depths until the propellant powder grains 21 burn, analyzing to obtain the time length required by the burning of the propellant powder grains 21 at the preset temperature, and obtaining the internal burning condition of the propellant powder grains 21.
As a preferred embodiment of the present invention, in step S1, the end cap 3 of the propellant charge 21 where the fixed fixing seat 7 is located is selected to be connected and fixed with one end of the heating cylinder in advance, or is assembled with the propellant charge 21 and then connected and fixed with the heating cylinder, and the two ways mainly include the convenience for installation of an operator.
As a preferred embodiment of the present invention, in step S4, while heating the heating cylinder, the driving mechanism is controlled to drive the fixing base 7 to drive the propellant powder grains 21 to rotate, so as to heat and humidify the propellant powder grains 21 more uniformly.
The invention also discloses a heat radiation burning method for the grain, which comprises the following steps:
s1, assembling the propellant powder grain 21 with one of the two fixing seats 7, and ensuring that the heat insulation rod 23 on the fixing seat 7 is inserted into the assembling hole 22 of the propellant powder grain 21;
s2, the insulating rod 23 on the other fixed seat 7 is inserted into the corresponding assembly hole 22 of the propellant powder grain 21, when the insulating rod 23 is completely inserted into the propellant powder grain 21, the fixed seat 7 is assembled with the corresponding end part of the propellant powder grain 21, and the two fixed seats 7 are tightly connected with the heating cylinder and enclose to form a sealed space;
s3, vacuumizing the heating cylinder, and sealing all channels directly and indirectly communicated with the heating cylinder when the vacuum degree reaches one hundred percent;
s4, continuously heating the heating cylinder until the heating cylinder is heated to a preset temperature, and controlling the heated amount of the heating cylinder to keep the preset temperature in a preset time;
s5, monitoring the temperature changes of the propellant powder grains 21 at different radial depths until the propellant powder grains 21 burn, analyzing to obtain the time length required by the burning of the propellant powder grains 21 at the preset temperature, and obtaining the internal burning condition of the propellant powder grains 21.
As a preferred embodiment of the present invention, in steps S4 and S5, when the degree of vacuum in the heater cylinder becomes low, two or more times of vacuuming are performed until the degree of vacuum does not change before the propellant charge 21 burns.
As a preferred embodiment of the present invention, in step S4, while heating the heating cylinder, the driving mechanism is controlled to drive the fixing base 7 to drive the propellant powder grains 21 to rotate, so as to heat and humidify the propellant powder grains 21 more uniformly.
The invention also discloses a method for roasting and burning the grains by thermal convection, which comprises the following steps:
s1, assembling the propellant powder grain 21 with one of the two fixing seats 7, and ensuring that the heat insulation rod 23 on the fixing seat 7 is inserted into the assembling hole 22 of the propellant powder grain 21;
s2, the insulating rod 23 on the other fixed seat 7 is inserted into the corresponding assembly hole 22 of the propellant powder grain 21, when the insulating rod 23 is completely inserted into the propellant powder grain 21, the fixed seat 7 is assembled with the corresponding end part of the propellant powder grain 21, and the two fixed seats 7 are tightly connected with the heating cylinder and enclose to form a sealed space;
s3, enabling the heated gas to enter the heating cylinder through a thermal convection mechanism to finish the convection or direct current or rotational flow movement of the gas in the heating cylinder; wherein, the convection is that the gas enters the heating cylinder from the heat convection mechanisms at the two ends of the heating cylinder respectively, the two gases collide with each other in the heating cylinder, and the flow rates of the two gases are the same or different; or the flow rate of each gas is gradually increased and then decreased, and the steps are repeated in such a way that the flow rates of the two gases are increased or decreased synchronously or asynchronously; the swirling flow is divided into a direct swirling flow and a convective swirling flow, wherein,
d, direct current rotational flow: selecting a heat convection mechanism from the gases to enter the heating cylinder, humidifying the gases according to the requirements, sending the gases out of the heating cylinder by the other heat convection mechanism, and simultaneously driving a fixing mechanism for fixing the propellant powder grains 21 to rotate, wherein the fixing mechanism acts on the gases flowing on the fixing mechanism to enable the gases to generate rotational flow;
convection rotational flow: the gas enters the heating cylinder from the heat convection mechanisms at the two ends of the heating cylinder respectively, the two gas streams collide with each other in the heating cylinder, and meanwhile, the fixing mechanism for fixing the propellant powder column 21 is driven to rotate, the gas flowing through the fixing mechanism acts on the fixing mechanism, so that the gas generates rotational flow, and the two rotational flow gas streams collide with each other;
s4, continuously heating the gas passing through the heating cylinder by the thermal convection mechanism, simultaneously heating the gas in the heating cylinder by the heating cylinder until the temperature in the heating cylinder reaches a preset temperature, and controlling the heating quantity of the heating cylinder and the thermal convection mechanism to keep the propellant charge 21 at the preset temperature within a preset time; in order to ensure that the propellant powder charge 21 is in different humidity environments in the test process, humidifying the gas passing through the propellant powder charge by a thermal convection mechanism so as to keep the humidity in the heating cylinder at a preset value;
s5, monitoring the temperature changes of the propellant powder grains 21 at different radial depths until the propellant powder grains 21 burn, analyzing to obtain the time length required by the burning of the propellant powder grains 21 at the preset temperature, and obtaining the internal burning condition of the propellant powder grains 21.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the claims of the present invention.
Claims (10)
1. A heat conduction roasting method for a grain is characterized by comprising the following steps:
s1, assembling the propellant powder grain with one of the two fixing seats, and ensuring that the heat insulation rod on the fixing seat is inserted into the assembling hole of the propellant powder grain;
s2, inserting the heat insulation rod on the other fixing seat into the corresponding assembly hole of the propellant powder grain, when the heat insulation rod is completely inserted into the propellant powder grain, assembling the fixing seat and the corresponding end part of the propellant powder grain, and tightly connecting the two fixing seats and the heating cylinder to form a sealed space;
s3, filling the heating cylinder with heat-conducting gas, keeping the pressure in the heating cylinder at normal pressure, and humidifying the heating cylinder to make the humidity in the heating cylinder reach a preset value;
s4, continuously heating the heating cylinder until the heating cylinder is heated to a preset temperature, and controlling the heated amount of the heating cylinder to keep the preset temperature in a preset time;
s5, monitoring the temperature changes of the propellant powder grain at different radial depths until the propellant powder grain burns, analyzing to obtain the time length required by the burning of the propellant powder grain at the preset temperature, and obtaining the internal burning condition of the propellant powder grain.
2. The heat-conduction roasting combustion method for explosive column according to claim 1, characterized in that: in step S1, the end cap of the fixed fixing seat is selected to be connected and fixed with one end of the heating cylinder in advance, or the end cap is assembled with the propellant powder charge and then connected and fixed with the heating cylinder.
3. The heat-conduction roasting combustion method for explosive column according to claim 1, characterized in that: in step S4, the driving mechanism is controlled to drive the fixing base to drive the propellant powder grains to rotate while the heating cylinder is heated.
4. A heat radiation burning method for a grain is characterized by comprising the following steps:
s1, assembling the propellant powder grain with one of the two fixing seats, and ensuring that the heat insulation rod on the fixing seat is inserted into the assembling hole of the propellant powder grain;
s2, inserting the heat insulation rod on the other fixing seat into the corresponding assembly hole of the propellant powder grain, when the heat insulation rod is completely inserted into the propellant powder grain, assembling the fixing seat and the corresponding end part of the propellant powder grain, and tightly connecting the two fixing seats and the heating cylinder to form a sealed space;
s3, vacuumizing the heating cylinder, and sealing all channels directly and indirectly communicated with the heating cylinder when the vacuum degree reaches one hundred percent;
s4, continuously heating the heating cylinder until the heating cylinder is heated to a preset temperature, and controlling the heated amount of the heating cylinder to keep the preset temperature in a preset time;
s5, monitoring the temperature changes of the propellant powder grain at different radial depths until the propellant powder grain burns, analyzing to obtain the time length required by the burning of the propellant powder grain at the preset temperature, and obtaining the internal burning condition of the propellant powder grain.
5. The thermal radiation burning method for grain of claim 4, characterized in that: in steps S4 and S5, when the degree of vacuum in the heater cylinder becomes low, two or more times of evacuation are performed until the degree of vacuum does not change before the propellant charge burns.
6. The thermal radiation burning method for grain of claim 4, characterized in that: in step S4, the driving mechanism is controlled to drive the fixing base to drive the propellant powder grains to rotate while the heating cylinder is heated.
7. A method for burning grains by heat convection is characterized by comprising the following steps:
s1, assembling the propellant powder grain with one of the two fixing seats, and ensuring that the heat insulation rod on the fixing seat is inserted into the assembling hole of the propellant powder grain;
s2, inserting the heat insulation rod on the other fixing seat into the corresponding assembly hole of the propellant powder grain, when the heat insulation rod is completely inserted into the propellant powder grain, assembling the fixing seat and the corresponding end part of the propellant powder grain, and tightly connecting the two fixing seats and the heating cylinder to form a sealed space;
s3, enabling the heated gas to enter the heating cylinder through a thermal convection mechanism to finish the convection or direct current or rotational flow movement of the gas in the heating cylinder;
s4, continuously heating the gas passing through the heating cylinder by the thermal convection mechanism, simultaneously heating the gas in the heating cylinder by the heating cylinder until the temperature in the heating cylinder reaches a preset temperature, controlling the heating quantity of the heating cylinder and the thermal convection mechanism to keep the propellant powder charge at the preset temperature within a preset time, and humidifying the gas passing through the heating cylinder by the thermal convection mechanism to keep the humidity in the heating cylinder at a preset value;
s5, monitoring the temperature changes of the propellant powder grain at different radial depths until the propellant powder grain burns, analyzing to obtain the time length required by the burning of the propellant powder grain at the preset temperature, and obtaining the internal burning condition of the propellant powder grain.
8. The method of claim 7, wherein the method comprises: in the step S3, the convection is that the gas enters the heating cylinder from the thermal convection mechanisms at the two ends of the heating cylinder, the two gases collide with each other in the heating cylinder, and the flow rates of the two gases are the same or different; or the flow rate of each gas is gradually increased and then decreased, so as to reciprocate, and the flow rate increase or decrease of the two gases is synchronous or asynchronous.
9. The method of claim 7, wherein the method comprises: the swirling flow described in step S3 is divided into a direct swirling flow and a convective swirling flow, wherein,
d, direct current rotational flow: selecting a heat convection mechanism from the gases to enter the heating cylinder, humidifying the gases according to the requirements, sending the gases out of the heating cylinder by the other heat convection mechanism, and simultaneously driving a fixing mechanism for fixing the propellant powder columns to rotate, wherein the fixing mechanism acts on the gases flowing through the fixing mechanism to enable the gases to generate rotational flow;
convection rotational flow: the gas enters the heating cylinder from the heat convection mechanisms at the two ends of the heating cylinder respectively, the two gas strands collide with each other in the heating cylinder, the fixing mechanism for fixing the propellant powder charge is driven to rotate, the gas flowing through the fixing mechanism acts on the fixing mechanism, the gas generates rotational flow, and the gas of the two rotational flow strands collides with each other.
10. A burning method for multiple coupling of propellant powder grains is characterized in that: the method comprises the steps of roasting and burning the propellant powder column by at least two methods of claim 1, claim 4 and claim 7, and monitoring the temperature change condition of the inside and the space of the propellant powder column in real time.
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