Device and method for testing ignition and combustion performance of electronic control solid propellant

Abstract

The invention relates to an electronic control solid propellant ignition and combustion performance testing device and a testing method. Comprising an open type vertical ignition module, a closed integrated base, an outer frame with a sliding rail and a Z-axis variable ignition module supporting table. The open type vertical ignition module enables a propellant to be always in contact with the positive electrode and the negative electrode in the combustion process under the action of a spring and an outer frame with a sliding rail; the open type vertical ignition module provides different ignition pressures for the solid propellant through the Z-axis variable ignition module supporting table. The outer frame with the sliding rail is arranged above the high-precision mass sensor through the sensor fixing frame. The device is suitable for ignition and combustion performance testing of various electronic control solid propellants, is small in size and light in weight, can be conveniently used in a vacuum tank and a high-pressure combustion chamber, and can measure the mass change of the propellants in real time through a built-in high-precision mass sensor; and a propellant mass change curve in the combustion process is recorded through an external interface oscilloscope, so that the real-time combustion speed of the propellant can be further calculated.

Description

Technical Field

[0001] The present invention belongs to the field of solid propellant performance testing, and particularly relates to a device and a testing method for testing the ignition and combustion performance of an electronically controlled solid propellant. Background Art

[0002] Traditional liquid rocket engines can achieve multiple ignition and extinguishing operations, but they have complex structures, most of the propellants are toxic, and the fueling time is too long, which cannot meet the requirements of rapid response operations; solid rocket engines have simple structures and short launch preparation times, but they do not have the function of real-time start and stop of the engine. Electronically controlled solid propellant is a new type of green propellant that can be ignited, burned, and extinguished under the control of external electric energy. It has the ability to be ignited and started multiple times and the thrust can be adjusted, which can meet the needs of small space vehicles for orbit transfer, formation flight, and attitude adjustment. It can also be applied to missile weapons to achieve high-speed maneuverability and rapid penetration.

[0003] In order to comprehensively understand the performance of electronically controlled solid propellants, construct relevant theoretical models, and apply them reasonably, it is necessary to conduct research on the combustion performance of electronically controlled solid propellants. Compared with traditional solid propellant ignition devices, electronically controlled solid propellants need to ensure continuous input of external electric energy throughout the process. Therefore, it is necessary to keep the propellant in close contact with the electrodes throughout the process. The existing technical solutions have low integration, and each component is scattered and combined on an optical platform, with a large number of wires, which increases the risk of experimental operations. At the same time, the combustion products are not easy to clean up and are likely to corrode each component, especially electronic equipment.

[0004] The existing electronically controlled solid propellant ignition test devices use an optical platform as the base and large metal fittings, resulting in poor device integration and low space utilization rate. This increases the weight and volume of the device, requires a large space for ignition testing, limits the experimental conditions for propellant ignition testing, and makes it inconvenient to use the ignition device in a vacuum tank or a high-pressure combustion chamber.

[0005] Traditional propellant burning rate test devices and testing methods can only calculate the burning rate of the propellant based on the initial and extinguished states of the electronically controlled solid propellant or the time when the propellant burning surface reaches the target line, and cannot reflect the real-time change of the burning rate of the propellant during the combustion process. Summary of the Invention

[0006] The purpose of the present invention is to provide a device and a testing method for testing the ignition and combustion performance of an electronically controlled solid propellant, which can improve the integration of the electronically controlled solid propellant ignition device, reduce the weight, and solve the problem of real-time monitoring of the mass change during the combustion process of the electronically controlled solid propellant. The real-time mass change value can be observed through a force value measuring instrument, or the mass change curve of the propellant during combustion can be obtained through an external oscilloscope.

[0007] The technical solution for achieving the object of the present invention is: an electronic control solid propellant ignition and combustion performance testing device, including an open vertical ignition module, a closed integrated base, an outer frame with a slide rail, and a Z-axis variable ignition module support platform. A high-precision mass sensor is provided on the closed integrated base;

[0008] The open vertical ignition module includes a spring. Under the action of the spring and the outer frame with a slide rail, the solid propellant is always in contact with the positive and negative electrodes during the ignition and combustion process. The lower part of the open vertical ignition module is connected to the Z-axis variable ignition module support platform inside the outer frame with a slide rail, and different ignition pressures are provided to the solid propellant through the Z-axis variable ignition module support platform. The outer frame with a slide rail is arranged above the high-precision mass sensor through a sensor fixing frame.

[0009] Furthermore, the outer frame with a slide rail includes: support rods, slide rails, an outer frame base, sliders, and L-shaped slide rail fixing blocks;

[0010] Four support rods are fixed at the four corners of the outer frame base. An insulating gasket is provided between each support rod and the outer frame base. Two L-shaped slide rail fixing blocks are fixed on the opposite sides of the outer frame base. An insulating gasket is provided between the L-shaped slide rail fixing blocks and the outer frame base. The slide rails are perpendicularly arranged on the outer frame base through the slide rail fixing blocks.

[0011] Furthermore, the open vertical ignition module further includes an insulating fixing block, a negative electrode connection block, a slider adapter block, an insulating block, a spring fixing frame, a molybdenum grid, a top positive electrode plate, and a middle negative electrode plate;

[0012] The top positive electrode plate is fixedly connected to the support rod. The molybdenum grid is placed inside the top positive electrode plate, and insulating fixing blocks are installed on both sides. The molybdenum grid, the top positive electrode plate, and the support rod form a relatively fixed whole. The upper end of the slide rail passes through the insulating fixing block;

[0013] The middle negative electrode plate is connected to the slider through the negative electrode connection block and the slider adapter block to form a relatively fixed whole. The electronic control solid propellant is placed between the middle negative electrode plate and the molybdenum grid. An insulating block is connected below the middle negative electrode plate, and a spring is provided between the insulating block and the spring fixing frame;

[0014] The middle negative electrode plate is supported by the spring to move up and down along the slide rail, ensuring that the propellant is always in contact with the positive and negative electrodes during ignition and combustion.

[0015] Furthermore, a U-shaped groove with a width of 1 ± 0.1 mm is opened in the middle of the top positive electrode plate. Through holes smaller than the molybdenum grid are opened on the upper and lower side walls of the U-shaped groove. The molybdenum grid is placed in the U-shaped groove of the top positive electrode plate.

[0016] Furthermore, the upper part of the enclosed integrated base is a base cover. A sensor fixing bracket is provided on the base cover, and a high-precision mass sensor is arranged inside the sensor fixing bracket. The outer frame base and the sensor fixing bracket are fixedly connected relative to each other.

[0017] Furthermore, a wireless switch module, a 12V DC power supply, a force value measuring instrument, a relay, and a multi-functional delay controller are also installed inside the enclosed integrated base;

[0018] The wireless switch module inputs a signal to the multi-functional delay controller. The multi-functional delay controller controls the relay to close and turn on the ignition circuit; the high-precision mass sensor is connected to the force value measuring instrument, and the force value measuring instrument is connected to the oscilloscope. The high-precision mass sensor records the change in the mass of the propellant in real time, reads the mass data through the force value measuring instrument, and transmits it to the oscilloscope, and obtains the curve of the sensor signal value changing with time through the oscilloscope.

[0019] A method for testing the ignition and combustion performance of an electrically controlled solid propellant by using the above-mentioned electrically controlled solid propellant ignition and combustion performance testing device includes the following steps:

[0020] Step (1): After ignition, the electrically controlled solid propellant burns between the positive and negative electrodes of the open vertical ignition module. The change value of the total mass is recorded by the high-precision mass sensor, and the sensor signal is transmitted to the oscilloscope through the force value measuring instrument to obtain the curve of the sensor signal value changing with time;

[0021] Step (2): Calculate the burning rate of the propellant:

[0022]

[0023] Among them, M1 and M2 are the readings of the sensor before and after the ignition of the propellant respectively, V is the linear burning rate of the propellant, ρ is the density of the propellant, S is the cross-sectional area of the propellant, and t1 and t2 are the moments when the voltage is applied to both ends of the propellant and the moment when the voltage is removed respectively;

[0024] Step (3): Calculate the dynamic burning rate of the propellant based on the mass change rate of the propellant:

[0025]

[0026] Among them, v is the dynamic burning rate of the propellant, a is the corresponding coefficient of the sensor signal and the mass, and y is the corresponding function of the curve of the sensor signal value changing with time obtained through the oscilloscope.

[0027] Compared with the prior art, the remarkable advantages of the present invention are:

[0028] (1) The ignition and combustion performance testing device for the electro-controlled solid propellant of the present invention abandons the huge and heavy optical flat plate and the dovetail lifting table, integrates the ignition device in a device with length, width and height of 50 mm, 50 mm and 100 mm respectively, greatly reduces the volume and weight of the ignition device, improves the portability of the ignition device, and can be conveniently placed into the vacuum tank and the high-pressure combustion chamber for experiments.

[0029] (2) The ignition and combustion performance testing device for the electro-controlled solid propellant of the present invention integrates electronic components in the base and uses a housing for protection to prevent the combustion products of the propellant from directly contacting the electronic components, thereby improving the durability of the device.

[0030] (3) The ignition and combustion performance testing device for the electro-controlled solid propellant of the present invention records the mass change of the electro-controlled solid propellant during the ignition process through a high-precision mass sensor, and can directly calculate the linear burning rate by recording with the force value measuring instrument on the base. By combining the data read from the external oscilloscope for calculation, the curve of the linear burning rate of the propellant changing with time can be obtained.

[0031] (4) Other parts around the positive and negative plates of the ignition and combustion performance testing device for the electro-controlled solid propellant of the present invention are blocked. The open design enables researchers to directly observe the morphological changes of the propellant itself during the ignition and combustion processes, and an infrared camera can also be used to record the surface temperature changes of the propellant.

[0032] (5) The ignition and combustion performance testing device for the electro-controlled solid propellant of the present invention uses a Z-axis variable ignition module support platform inside, which can be adjusted according to the type and size of the electro-controlled solid propellant to be tested, thereby improving the applicability of the ignition device. Description of the Drawings

[0033] Figure 1 is the overall three-dimensional view of the ignition and combustion performance testing device for the electro-controlled solid propellant of the present invention.

[0034] Figure 2 is the structural diagram of the outer frame of the ignition and combustion performance testing device for the electro-controlled solid propellant of the present invention.

[0035] Figure 3 is the open vertical ignition module diagram of the ignition and combustion performance testing device for the electro-controlled solid propellant of the present invention; among them, (a) is the exploded view and (b) is the assembled view.

[0036] Figure 4 is the schematic diagram of the high-precision mass sensor of the ignition and combustion performance testing device for the electro-controlled solid propellant of the present invention; among them, (a) is the three-dimensional view and (b) is the front view.

[0037] Figure 5It is the layout diagram of the internal components of the inheritance base of the ignition and combustion performance test device for the electronically controlled solid propellant of the present invention.

[0038] Figure 6 It is the overall structure diagram of the ignition and combustion performance test device for the electronically controlled solid propellant of the present invention.

[0039] Explanation of reference numerals:

[0040] 1 - Open vertical ignition module, 2 - Closed integrated base, 3 - Force value measuring instrument, 4 - Outer frame with slide rail, 5 - Z-axis variable ignition module support platform, 6 - Multifunctional delay controller, 7 - Support rod, 8 - Slide rail, 9 - Outer frame base, 10 - Slide block, 11 - Slide rail fixing block, 12 - Insulation fixing block, 13 - Negative connection block, 14 - Slide block adapter block, 15 - Insulation block, 16 - Spring fixing frame, 17 - Molybdenum grille, 18 - Top positive plate, 19 - Intermediate negative plate, 20 - Spring, 21 - Base cover, 22 - High-precision mass sensor, 23 - Sensor fixing frame. Detailed implementation manners

[0041] The present invention will be further described in detail below with reference to the accompanying drawings.

[0042] As Figure 1-6 shown, the ignition and combustion performance test device for the electronically controlled solid propellant includes an open vertical ignition module 1, a closed integrated base 2, a force value measuring instrument 3, an outer frame with a slide rail 4, a Z-axis variable ignition module support platform 5, and a multifunctional delay controller 6.

[0043] The outer frame with a slide rail 4 is installed on the high-precision mass sensor 22 by screws. The Z-axis variable ignition module support platform 5 is installed inside the outer frame base 9. The lower part of the open vertical ignition module 1 is connected to the Z-axis variable ignition module support platform 5, and the upper part is fixedly connected to the outer frame. The high-precision mass sensor 22 is installed in the base cover 21 of the closed integrated base with a sensor fixing frame 23 to measure the mass change of the upper device and the propellant in real time.

[0044] The outer frame with a slide rail 4 includes: an outer frame base 9 made of 304 stainless steel with a side length of 54 mm. Four support rods 7 with a diameter of 6 mm are fixed at the four corners of the outer frame base 9. Insulating gaskets are placed under each support rod for the positive and negative poles of the insulating ignition device. Two slide rail fixing blocks 11 are fixed near the corresponding two sides of the outer frame base 9. Gaskets are also placed under the fixing blocks 11. The slide rail 8 with a width of 5 mm is fixed to the slide rail fixing blocks 11 by inner hexagon screws and is perpendicular to the outer frame base 9.

[0045] The open vertical ignition module 1 includes an insulating fixing block 12 , a negative electrode connecting block 13 , a slider adapter block 14 , an insulating block 15 , a spring fixing frame 16 , a molybdenum grid 17 , a top positive electrode plate 18 , a middle negative electrode plate 19 , and a spring 20 .

[0046] The top positive plate 18 is connected to the outer frame 4 with a slide rail through an inner hexagon screw, and the spring fixing frame 16 is supported at the bottom by a Z-axis variable ignition module support platform 5 fixed on the outer frame base 9, and the Z-axis variable ignition module support platform 5 is fixed on the outer frame base 9; the outer frame is fixed on the top of the high-precision mass sensor 22 through an inner hexagon screw; the high-precision mass sensor 22 (accuracy 2.0±0.05% mV / V, range 0-10N) is placed inside the sensor fixing frame 23 on the base cover 21; a small square window is opened on the integrated base 2 for reading the indication of the X505 force measuring instrument 3 and the multi-function delay controller 6 (YF-55); when igniting, the wireless switch inputs a closing switch signal to the multi-function delay controller 6, and the multi-function delay controller 6 controls the relay to close and connect the ignition circuit.

[0047] A groove with a width of 1 mm is cut inside the top positive plate 18 for placing the molybdenum grid 17. Insulating fixing blocks 12 made of polytetrafluoroethylene are installed in the notches on both sides, and the upper end of the slide rail 8 passes through the insulating block 12; the L-shaped negative connection block 13 is installed at the notches on both sides of the intermediate negative plate 19 with a main plane side length of 25 mm, and the upper end is coated with insulating glue to prevent direct contact between the positive and negative poles during use. The negative connection block 13 is connected to the slider 10 through the through hole of the slider adapter block 14, and the slider 10 and the slide rail 8 form a track that can slide freely up and down; the intermediate negative plate 19 is connected to the insulating block 15 through the thread at the bottom, and a 50 mm long spring 20 with a spring fixing frame 16 at the bottom is used to support the insulating block 15 and the intermediate negative plate 19 above the insulating block; the molybdenum grid 17 and the top positive plate The plate 18 and the support rod 7 form a whole, the intermediate negative plate 19, the negative connecting block 13, the slider adapter block 14 and the slider 10 are connected as a whole, the propellant is placed between the intermediate negative plate 19 and the molybdenum grid 17, and the intermediate negative plate 19 is supported by a spring and moves up and down along the slide rail to ensure that the propellant always maintains good contact with the positive and negative during ignition and combustion; the 0.1mm round copper nose of the positive electrode wire is installed between the insulating sheet below the top positive plate 18 and above the support rod 7, and the 0.1mm round copper nose of the negative electrode wire is installed between the intermediate negative plate 19 and the insulating block 15. The positive and negative electrode wires are transmitted into the closed base through the wiring holes on the base cover 21, connected to the internal relay of the closed base, and pass through the corresponding wiring ports from the wiring holes at the rear of the closed base to connect to the external programmable power supply.

[0048] The high-precision mass sensor 22 is installed in the square storage compartment of the sensor fixing bracket 23. The sensor fixing bracket 23 is fixed to the base cover 21 by screws. The detachable design facilitates the debugging and installation of the sensor. The enclosed integrated base 2 is internally equipped with a wireless switch module, a 12V DC power supply, a force value measuring instrument, a relay, and a multi-functional delay controller, which efficiently utilizes the space of the base and leaves a certain space for wire arrangement. The force value measuring instrument 3 is connected to the high-precision mass sensor 22 through a data cable, processes the data signal generated by the sensor and outputs the weight value. There is a data cable interface on the force value measuring instrument 3 that can be connected to an oscilloscope, and the data transmission frequency > 10kHz. The 12V DC power supply outputs power to the wireless switch module, the high-precision mass sensor, the force value measuring instrument, and the multi-functional delay controller.

[0049] The present invention relates to a calculation method for the combustion performance of electro-controlled solid propellants:

[0050] After ignition, the electro-controlled solid propellant burns between the positive and negative poles in the open vertical ignition module 1. The total mass continuously changes with the combustion time. The specific values of the change are recorded by the high-precision mass sensor 22. The sensor signal is transmitted to the oscilloscope through the force value measuring instrument, and a curve of the sensor signal value changing with time is obtained.

[0051] The burning rate of the propellant is calculated according to the following formula:

[0052]

[0053] Wherein, M1 and M2 are respectively the readings of the sensor before the ignition of the propellant and after the ignition, V is the linear burning rate of the propellant, ρ is the density of the propellant, S is the cross-sectional area of the propellant, and t1 and t2 are respectively the moments when the voltage is applied to both ends of the propellant and the moment when the voltage is removed.

[0054] Furthermore, the dynamic burning rate of the propellant is calculated based on the mass change rate of the propellant according to the following formula:

[0055]

[0056] Wherein, v is the dynamic burning rate of the propellant, a is the corresponding coefficient between the sensor signal and the mass, and y is the function corresponding to the curve of the sensor signal value changing with time obtained through the oscilloscope.

[0057] The real-time measurement of the mass change of the propellant in the present invention can further calculate the dynamic linear burning rate of the propellant. It not only solves the problems in the background technology, but also, combined with the data obtained from other testing devices, such as the curves of the voltage and current changes of the propellant during combustion, can quantitatively analyze the relationships among parameters such as the linear burning rate, the externally input power, and the voltage and current of the propellant during combustion. It is of great significance for further understanding the combustion mechanism of the propellant and can also rationalize the application of the electro-controlled solid propellant.

Claims

1. Electronically controlled solid propellant ignition and combustion performance test device, characterized in that: It comprises an open vertical ignition module (1), a closed integrated base (2), an outer frame with a slide rail (4) and a Z-axis variable ignition module support platform (5), wherein a high-precision mass sensor (22) is arranged on the closed integrated base (2); The open vertical ignition module (1) comprises a spring (20), and under the action of the spring (20) and the outer frame with a slide rail (4), the solid propellant is always in contact with the positive and negative electrodes during the ignition and combustion process; the lower part of the open vertical ignition module (1) is connected to a Z-axis variable ignition module support platform (5) in the outer frame with a slide rail (4), and different ignition pressures are provided to the solid propellant through the Z-axis variable ignition module support platform (5); the outer frame with a slide rail (4) is arranged above a high-precision mass sensor (22) through a sensor fixing frame (23).

2. The testing device according to claim 1, characterized in that: The outer frame with slide rails (4) comprises: a support rod (7), a slide rail (8), an outer frame base (9), a slide block (10) and an L-shaped slide rail fixing block (11); Four support rods (7) are fixed at four corners of the outer frame base (9), an insulating gasket is provided between each support rod (7) and the outer frame base (9), two L-shaped slide rail fixing blocks (11) are fixed at two opposite sides of the outer frame base (9), an insulating gasket is provided between the L-shaped slide rail fixing blocks (11) and the outer frame base (9), and the slide rail (8) is vertically arranged with the outer frame base (9) through the slide rail fixing blocks (11).

3. The testing device according to claim 2, characterized in that: The open vertical ignition module (1) also includes an insulating fixing block (12), a negative electrode connecting block (13), a slider adapter block (14), an insulating block (15), a spring fixing frame (16), a molybdenum grid (17), a top positive electrode plate (18) and a middle negative electrode plate (19); The top positive plate (18) and the support rod (7) are fixedly connected, a molybdenum grid (17) is placed inside the top positive plate (18), and insulating fixed blocks (12) are installed on both sides. The molybdenum grid (17), the top positive plate (18) and the support rod (7) form a relatively fixed whole, and the upper end of the slide rail (8) passes through the insulating fixed block (12); The middle negative electrode plate (19) is connected to the slider (10) through the negative electrode connecting block (13) and the slider adapter block (14) to form a relatively fixed whole. The electric-controlled solid propellant is placed between the middle negative electrode plate (19) and the molybdenum grid (17). An insulating block (15) is connected below the middle negative electrode plate (19). A spring (20) is provided between the insulating block (15) and the spring fixing frame (16); The middle negative electrode plate (19) is supported by a spring (20) so as to move up and down along the slide rail (8), thereby ensuring that the propellant is always in contact with the positive and negative electrodes during ignition and combustion.

4. The testing device according to claim 3, characterized in that: A U-shaped groove with a width of 1±0.1 mm is provided in the middle of the top positive plate (18), and through holes smaller than the molybdenum grid (17) are provided on the upper and lower side walls of the U-shaped groove. The molybdenum grid (17) is placed in the U-shaped groove of the top positive plate (18).

5. The testing device according to claim 4, characterized in that: The upper part of the closed integrated base (2) is a base cover (21), a sensor fixing frame (23) is arranged on the base cover (21), a high-precision mass sensor (22) is arranged inside the sensor fixing frame (23), and the outer frame base (9) and the sensor fixing frame (23) are relatively fixedly connected.

6. The testing device according to claim 5, characterized in that: A wireless switch module, a 12V DC power supply, a force value measuring instrument, a relay and a multifunctional delay controller (6) are also installed inside the closed integrated base (2); The wireless switch module inputs a signal to the multifunctional delay controller (6), and the multifunctional delay controller (6) controls the relay to close and connects the ignition circuit; the high-precision mass sensor (22) is connected to the force value measuring instrument (3), and the force value measuring instrument (3) is connected to the oscilloscope. The high-precision mass sensor (22) records the mass change of the propellant in real time, reads the mass data through the force value measuring instrument (3), transmits it to the oscilloscope, and obtains a curve of the sensor signal value changing with time through the oscilloscope.

7. A method for testing the ignition and combustion performance of an electronically controlled solid propellant using the electronically controlled solid propellant ignition and combustion performance testing device according to any one of claims 1 to 6, characterized in that: The steps include: Step (1): After ignition, the electronically controlled solid propellant burns between the positive and negative electrodes of the open vertical ignition module, and the change in total mass is recorded by a high-precision mass sensor. The sensor signal is transmitted to an oscilloscope through a force value measuring instrument to obtain a curve of the sensor signal value changing over time; Step (2): Calculate the propellant burning rate: Where M1 and M2 are the sensor readings before and after the propellant is ignited, respectively; V is the linear burning rate of the propellant; ρ is the propellant density; S is the cross-sectional area of ​​the propellant; t1 and t2 are the time when the voltage is applied to both ends of the propellant and the time when the voltage is removed, respectively; Step (3): Calculate the dynamic burning rate of the propellant based on the propellant mass change rate: Among them, v is the dynamic burning rate of the propellant, a is the corresponding coefficient of the sensor signal and mass, and y is the corresponding function of the curve of the sensor signal value changing with time obtained by the oscilloscope.

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