Device for testing propagation process of shock waves in solid propellant
By burying manganese copper piezoresistive sensors in solid propellants and controlling shock wave pressure using gaskets and attenuation partitions, the problem of difficulty in accurately simulating the detonation process of solid propellants in the prior art is solved, and effective anti-shock wave safety is achieved Research and numerical simulations broaden the range of experiments and reduce costs.
Patent Information
- Application Number
- CN202420108798.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-01-16
- Publication Date
- 2025-01-03
- Estimated Expiration
- 2034-01-16
AI Technical Summary
The prior art is difficult to accurately simulate and study the detonation process of solid propellants under shock wave stimulation, and lacks effective reaction models and equations of state, which affects the safety of shock wave resistance.
Design a test device to control the shock wave pressure by burying a manganese copper piezoresistive sensor in a solid propellant, and use a gasket and attenuation partition to control the shock wave pressure, collect the propagation process data of the shock wave inside the propellant, which is the reaction model and the state equation. Establish a foundation.
It improves the accuracy and test range of shock wave safety research of solid propellants, provides effective numerical simulation data, and reduces the test cost.
Smart Images
Figure CN222299410U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of solid propellant shock detonation, in particular to a device for testing the propagation process of shock waves in solid propellants. Background Art
[0002] Solid propellant is the power source of various solid motors. It is an energetic material with specific properties. When it is stimulated by shock waves, "hot spots" may be generated inside. The "hot spots" spread to the surroundings and ignite the unreacted propellant, causing the propellant to be detonated by the shock wave. Therefore, studying the propagation process of shock waves inside the propellant is helpful to improve the safety of the propellant against shock waves.
[0003] At present, numerical simulation technology is one of the effective means to study the safety performance of propellants when facing various stimuli. In order to accurately simulate the detonation process of propellants, an accurate reaction model and state equation are very necessary. The utility model can test the propagation of shock waves of different sizes inside the propellant, and provides a method for establishing the propellant reaction model and state equation, thereby providing a basis for the numerical simulation of impact detonation of solid propellants. Utility Model Content
[0004] The purpose of the utility model is to provide a device for testing the propagation process of shock waves in solid propellants, and to provide a method for studying the safety performance of solid propellants against shock waves and numerical simulation of solid propellant shock detonation. The input shock wave pressure is controlled by controlling the thickness of the gasket and the attenuation partition, and the shock wave pressure at different positions in the solid propellant is tested by the manganese copper piezoresistive sensor pre-buried in the solid propellant, so as to obtain the complete propagation process of the shock wave in the solid propellant.
[0005] The purpose of the utility model is achieved through the following technical solutions: a device for testing the propagation process of shock waves in solid propellants, comprising a base plate, a plurality of solid propellants are stacked on the base plate, an attenuation baffle is provided on the top of the plurality of solid propellants, the attenuation baffle is fixed to the base plate by bolts and nuts, a plurality of gaskets are placed on the attenuation baffle, an explosive column is placed on the gasket, a detonator base is provided on the explosive column, a detonator is inserted in the detonator base, a trigger is fixed on the side of the explosive column, the trigger is connected to a constant current power supply, a piezoresistive sensor is respectively provided on the top of each fixed propellant, and the piezoresistive sensor is respectively connected to the constant current power supply and an oscilloscope.
[0006] In a preferred embodiment, the detonator is a No. 8 industrial electric detonator.
[0007] In a preferred embodiment, the trigger is a single enameled wire adhered to the explosive column by means of tape, and the shock wave generates an "on-off" signal through the trigger, and the piezoresistive sensor starts to collect pressure information.
[0008] In a preferred embodiment, the explosive column is a cast Pentrite column with a height of 50 mm and a diameter of 50 mm.
[0009] In a preferred embodiment, the gasket is a cylindrical stainless steel gasket with a thickness of 3 to 10 mm and a diameter of 8 mm.
[0010] In a preferred embodiment, the attenuation baffle is an aluminum or polymethacrylic circular plate with a thickness of 5 to 10 mm and a diameter of 200 mm.
[0011] In a preferred embodiment, the piezoresistive sensor is a long strip manganese-copper piezoresistive sensor with a thickness of 1 mm, and the upper and lower surfaces of the piezoresistive sensor are coated with aluminum foil and polytetrafluoroethylene film.
[0012] In a preferred embodiment, the solid propellant is a cubic block with a thickness of 10 to 25 mm and a side length of 50 mm.
[0013] In a preferred embodiment, the collection area of the piezoresistive sensor is located on the central axis of the solid propellant.
[0014] Compared with the prior art, the utility model has the following advantages:
[0015] 1. The utility model distributes a plurality of manganese-copper piezoresistive sensors at different positions inside the solid propellant and wraps the piezoresistive sensors, thereby ensuring the test accuracy and providing effective data support for studying the safety of solid propellant against shock waves.
[0016] 2. The device has a wide range of applications. By controlling the thickness of the gasket and the thickness of the attenuation partition, the input shock wave pressure can be effectively controlled, which broadens the test range for the impact detonation research of solid propellants under different pressures.
[0017] 3. The device is easy and quick to assemble. The components are directly bonded together using vacuum silicone grease, and then fixed with bolts and nuts. Under the condition of having relevant qualifications, the above components can be obtained through procurement channels, and the test cost is low. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] Figure 1 It is a structural schematic diagram of the utility model;
[0019] Figure 2 The original curve diagram of the voltage signal of the piezoresistive sensor at different positions inside the HTPE propellant is used to test it;
[0020] Figure 3 This is the shock wave pressure curve after processing the original voltage signal curve. DETAILED DESCRIPTION
[0021] The following detailed description of the embodiments of the present invention is further described in detail in conjunction with the accompanying drawings and examples. The detailed description of the following embodiments and the accompanying drawings are used to exemplarily illustrate the principles of the present invention, but cannot be used to limit the scope of the present invention, that is, the present invention is not limited to the preferred embodiments described, and the scope of the present invention is defined by the claims.
[0022] In the description of the present invention, it should be noted that, unless otherwise specified, “plurality” means two or more; the terms “first”, “second”, etc. are used for descriptive purposes only and cannot be understood as indicating or implying relative importance; for ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.
[0023] Embodiment 1
[0024] See also Figure 1 The present embodiment provides a device for testing the propagation process of shock waves in solid propellants, comprising a bottom plate 9, on which a plurality of solid propellants 11 are stacked, an attenuation baffle 8 is arranged on the top of the plurality of solid propellants 11, the attenuation baffle 8 is fixed to the bottom plate 9 by bolts 6 and nuts 7, a plurality of gaskets 5 are arranged on the attenuation baffle 8, an explosive column 4 is arranged on the gasket 5, a detonator base 2 is arranged on the explosive column 4, a detonator 1 is inserted in the detonator base 2, a trigger 3 is fixed on the side of the explosive column 4, the trigger 3 is connected to a constant current power supply, a piezoresistive sensor 10 is arranged on the top of each fixed propellant 11, and the piezoresistive sensor 10 is connected to a constant current power supply and an oscilloscope respectively.
[0025] In this embodiment, the detonator 1 is a No. 8 industrial electric detonator, which is used to detonate the explosive column 4 and input the shock wave pressure downward. The detonator base 2 is a wooden cylindrical base with a thickness of 20 mm and a diameter of 40 mm, and has a round hole in the center for fixing the detonator 1.
[0026] The trigger 3 is a single enameled wire, which is adhered to the explosive column 4 by means of tape. The shock wave passes through the trigger to generate an "on-off" signal, and the piezoresistive sensor 10 starts to collect pressure information.
[0027] In this embodiment, the explosive column 4 is a cast Pentrite column with a height of 50 mm and a diameter of 50 mm.
[0028] In this embodiment, the gasket 5 is a cylindrical stainless steel gasket with a thickness of 3 to 10 mm and a diameter of 8 mm. The size of the gap between the detonating charge column 4 and the attenuation partition 8 is controlled by the thickness of the gasket.
[0029] In this embodiment, the attenuation baffle 8 is an aluminum or polymethacrylic circular plate with a thickness of 5 to 10 mm and a diameter of 200 mm. By using attenuation baffles 8 of different thicknesses, different shock wave pressures are input to the fixed propellant.
[0030] In this embodiment, the piezoresistive sensor 10 is a long strip of manganese-copper piezoresistive sensor with a thickness of 1 mm, and the shape of the collection area of the piezoresistive sensor is "H-type" or "∏-type". In order to avoid the influence of noise on the collection effect of the piezoresistive sensor, aluminum foil and polytetrafluoroethylene film are used to wrap the upper and lower surfaces of the piezoresistive sensor 10.
[0031] In this embodiment, the solid propellant 11 is a cubic charge block with a thickness of 10 to 25 mm and a side length of 50 mm.
[0032] In this embodiment, the collection area of the piezoresistive sensor 10 is located on the central axis of the solid propellant 11 .
[0033] The attenuation baffle 8 and the bottom plate 9 are fixed by three bolts 6 with a diameter of 8 mm and matching nuts 7 .
[0034] After the detonator 1 detonates the explosive column 4, a shock wave overpressure is generated that propagates downward, and an "on-off" signal is generated when passing through the trigger 3. The manganese-copper piezoresistive sensor below starts to collect pressure information. The shock wave overpressure generated by the explosive column 4 passes through the air gap between the gaskets 5 and the attenuation effect of the attenuation partition 8, and is transmitted to the solid propellant block. When passing through the manganese-copper piezoresistive sensors at different positions, pressure signals of different sizes are generated, thereby showing the propagation process of the input shock wave overpressure inside the solid propellant block.
[0035] See also Figure 2 , Figure 3 , Figure 2 The original curves of the voltage signals of the manganese-copper piezoresistive sensors at different locations inside a certain HTPE propellant under test are shown. Figure 3 For Figure 2 The shock wave pressure curve after processing the original curve is shown. Figure 3 It can be seen that inside the HTPE propellant, the shock wave pressure peak shows a decaying trend, indicating that the propellant is not detonated by the input shock wave.
[0036] Embodiment 2
[0037] This embodiment describes the method for using the device for testing the shock wave propagation process in solid propellant disclosed in the first embodiment.
[0038] Step 1: Wrap the upper and lower surfaces of the sheet-shaped manganese-copper piezoresistive sensor with aluminum foil and polytetrafluoroethylene film respectively, and seal it with vacuum silicone ester to remove bubbles.
[0039] Step 2: First place a 10 mm thick solid propellant block at the center of the bottom plate 9, and then place the wrapped manganese copper piezoresistive sensor on the upper surface of the solid propellant block, keep the manganese copper piezoresistive sensor collection area located in the center of the solid propellant block, and seal it with vacuum silicone grease to ensure that there is no gap between the manganese copper piezoresistive sensor and the solid propellant block.
[0040] Step 3: Repeat step 2, stack four solid propellant blocks and four manganese-copper piezoresistive sensors in sequence, and keep the center of each solid propellant block and the collection area of each manganese-copper piezoresistive sensor on the same axis.
[0041] Step 4: Use a 10 mm thick aluminum partition or polymethacrylic acid partition to cover the solid propellant block, and use three 8 mm diameter bolts 6 and matching nuts 7 to fix the device.
[0042] Step 5: Place three stainless steel gaskets with a diameter of 8 mm and a height of 10 mm on the attenuation partition 8, then place a cast Pentrite column with a height of 50 mm and a diameter of 50 mm on the gasket 5, and use tape to stick the trigger 3 to the center of the side of the detonating column 4.
[0043] Step 6: Pass the No. 8 industrial electric detonator through the detonator base 2 to contact the upper surface of the explosive column 4, and keep the detonator 1 and the explosive column 4 on the same axis.
[0044] Step 7: Connect the trigger 3 and the piezoresistive sensor 10 to the constant current power supply and the oscilloscope respectively through data lines.
[0045] The above is only a specific implementation of the utility model, but the protection scope of the utility model is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed by the utility model, which should be included in the protection scope of the utility model. Therefore, the protection scope of the utility model should be based on the protection scope of the claims.
Claims
1. A device for testing the propagation process of shock waves in solid propellants, characterized in that: A base plate (9) is provided, a plurality of solid propellants (11) are stacked on the base plate (9), an attenuation baffle (8) is provided on the top of the plurality of solid propellants (11), the attenuation baffle (8) and the base plate (9) are fixed by bolts (6) and nuts (7), a plurality of gaskets (5) are placed on the attenuation baffle (8), an explosive column (4) is placed on the gasket (5), a detonator base (2) is provided on the explosive column (4), a detonator (1) is inserted in the detonator base (2), a trigger (3) is fixed on the side of the explosive column (4), the trigger (3) is connected to a constant current power supply, and a piezoresistive sensor (10) is respectively provided on the top of each fixed propellant (11), and the piezoresistive sensor (10) is respectively connected to the constant current power supply and an oscilloscope.
2. A device for testing the propagation process of shock waves in solid propellants according to claim 1, characterized in that: The detonator (1) is a No. 8 industrial electric detonator.
3. The device for testing the propagation process of shock waves in solid propellants according to claim 1, characterized in that: The trigger (3) is a single enameled wire, which is adhered to the explosive column (4) by means of adhesive tape. The shock wave passes through the trigger to generate an "on-off" signal, and the piezoresistive sensor (10) starts to collect pressure information.
4. The device for testing the propagation process of shock waves in solid propellants according to claim 1, characterized in that: The detonating charge column (4) is a cast Pentrite charge column with a height of 50 mm and a diameter of 50 mm.
5. The device for testing the propagation process of shock waves in solid propellants according to claim 1, characterized in that: The gasket (5) is a cylindrical stainless steel gasket with a thickness of 3 to 10 mm and a diameter of 8 mm.
6. The device for testing the propagation process of shock waves in solid propellants according to claim 1, characterized in that: The attenuation baffle (8) is an aluminum or polymethacrylic acid circular plate with a thickness of 5 to 10 mm and a diameter of 200 mm.
7. The device for testing the propagation process of shock waves in solid propellants according to claim 1, characterized in that: The piezoresistive sensor (10) is a long strip manganese-copper piezoresistive sensor with a thickness of 1 mm, and the upper and lower surfaces of the piezoresistive sensor (10) are coated with aluminum foil and polytetrafluoroethylene film.
8. The device for testing the propagation process of shock waves in solid propellants according to claim 1, characterized in that: The solid propellant (11) is a cubic block with a thickness of 10 to 25 mm and a side length of 50 mm.
9. The device for testing the propagation process of shock waves in solid propellants according to claim 1, characterized in that: The collection area of the piezoresistive sensor (10) is located on the central axis of the solid propellant (11).