Burner applied to measurement of ballistic curve in electronic control solid propellant

Abstract

The invention discloses a combustor applied to measurement of an inner trajectory curve of an electric control solid propellant, and the combustor comprises a housing which is provided with a cylindrical charging shell section and a conical combustion shell section which are in axial sealing communication; the supporting assembly is used for fixedly supporting the to-be-tested electronic control solid propellant, is arranged in the charging shell section and can slide along the axis of the charging shell section; the electrode array module is used for applying voltage to the to-be-tested electronic control solid propellant and is arranged between the charging shell section and the combustion shell section, and the charging shell section and the combustion shell section are axially and fixedly connected to the two ends of the electrode array module respectively; the propellant moving assembly is used for driving the supporting assembly which fixes the to-be-tested electronic control solid propellant to move towards the electrode array module along the axis of the charging shell section in the charging shell section, and is axially and fixedly connected with the supporting assembly; and the pressure intensity sensor can collect the pressure intensity change in the shell and is fixedly assembled on the outer side wall of the combustion shell section. The device can measure the inner ballistic curve of the electronic control solid propellant.

Description

Technical Field

[0001] The invention relates to the technical field of electronically controlled solid propellant testing, in particular to a burner used for measuring the interior ballistic curve of electronically controlled solid propellant. Background Art

[0002] Propellant, as the energy source for solid motors, plays a decisive role in their performance and operational performance. Electronically controlled solid propellants (ECPs) are a new type of solid propellant that incorporates an electrolytically combustible fuel into traditional solid propellants, achieving combustion when powered on and flameout when powered off. Because they better meet the requirements of intelligent, controllable engines, EPCs have experienced rapid development in recent years.

[0003] The internal ballistic curve, also known as the combustion chamber pressure-time curve, is a key characteristic curve that describes the temporal variation of the combustion chamber's gas pressure. It directly impacts the thrust, combustion stability, and overall performance of solid rocket motors. The internal ballistic curve plays a crucial role in evaluating overall engine performance, guiding structural strength design, optimizing design strategies, and diagnosing faults.

[0004] Existing solid propellant interior ballistic curve test burners typically consist of a front head, combustion chamber, and nozzle. Due to their simple structure and high reliability, they are widely used to test the performance of traditional solid propellant products. Their operating principle is as follows: First, traditional solid propellant is placed into the combustion chamber via wall-mounted casting or free-loading. Second, the front head, combustion chamber, and tail nozzle are connected via flanges or threaded connections. Finally, an igniter on the front head ignites the traditional solid propellant, causing self-sustaining combustion that releases large amounts of gas and heat. The high-temperature gas expands, generating work and is rapidly ejected backward from the nozzle, generating forward thrust. During this process, the chamber pressure is measured over time to obtain the internal ballistic curve of the combustion chamber.

[0005] However, for the new type of electronically controlled solid propellant, since it does not have the characteristic of self-sustaining combustion after ignition, it is necessary to apply voltage to the surface of the electronically controlled solid propellant to cause electrolysis to maintain its continuous combustion process. The existing solid propellant interior ballistic curve test burner that relies on an igniter to ignite the solid propellant cannot measure the interior ballistic curve of the electronically controlled solid propellant. Summary of the Invention

[0006] Based on this, it is necessary to provide a burner for measuring the internal ballistic curve of electronically controlled solid propellant to address the above technical problems, which can measure the internal ballistic curve of electronically controlled solid propellant in a closed burner under the state of electric field combustion.

[0007] The present invention provides a burner for measuring the interior ballistic curve of an electronically controlled solid propellant, comprising:

[0008] The casing comprises a cylindrical charge shell section and a conical combustion shell section which are axially sealed and connected;

[0009] A support assembly for fixedly supporting the electronically controlled solid propellant to be tested, the support assembly being arranged inside the charge shell segment and being able to slide along the axis of the charge shell segment;

[0010] An electrode array module for applying voltage to the electronically controlled solid propellant to be tested, the electrode array module being disposed between the charge shell segment and the combustion shell segment, the charge shell segment and the combustion shell segment being axially fixedly connected to both ends of the electrode array module;

[0011] A propellant moving assembly for driving the support assembly behind which the electronically controlled solid propellant to be tested is fixed to move inside the charge shell segment along the axis of the charge shell segment toward the electrode array module, wherein the propellant moving assembly is axially fixedly connected to the support assembly;

[0012] A pressure sensor can collect pressure changes inside the shell, and the pressure sensor is fixedly assembled on the outer side wall of the combustion shell section.

[0013] In one embodiment, both axial ends of the charge shell segment and both axial ends of the combustion shell segment are integrally connected with fixed flanges;

[0014] A sealing layer is provided at one end of the charge shell section away from the combustion shell section. The sealing layer includes a positioning flange and a sealing flange. The outer diameters of the positioning flange and the sealing flange are equal and larger than the outer diameter of the charge shell section. The positioning flange and the sealing flange are both axially fixedly connected to the fixed flange at the end of the charge shell section away from the combustion shell section. The sealing flange is located between the positioning flange and the charge shell section.

[0015] A first through hole is provided at the center of the positioning flange, a second through hole is provided at the center of the sealing flange, and a sleeve is vertically provided at the center of one side of the sealing flange facing the charge shell segment. The inner diameter of the sleeve is equal to the inner diameter of the second through hole. The sleeve is integrally connected to the sealing flange and communicated with the second through hole.

[0016] In one embodiment, the propellant moving assembly is provided with a transmission rod, a stepping motor, a cylindrical motor mounting chamber and a supporting flange;

[0017] The outer side wall of the motor installation room is fixedly equipped with a wiring barrel;

[0018] The motor mounting chamber is axially fixedly connected to the center of the side of the positioning flange away from the sealing flange, the stepping motor is axially assembled inside the motor mounting chamber, and the supporting flange is fixedly assembled at one end of the motor mounting chamber away from the charge shell section;

[0019] The front end cover of the stepper motor abuts against the positioning flange, and the rear end cover abuts against the supporting flange;

[0020] The transmission rod is inserted into the connecting hole formed by the second through hole and the sleeve. An internal threaded hole is provided at the end of the transmission rod away from the sleeve. The output shaft of the stepper motor is inserted into the first through hole, and the part extending from the first through hole is provided with an external thread. The output shaft of the stepper motor is threadedly connected to the internal threaded hole.

[0021] In one embodiment, along the direction from the charge shell segment to the combustion shell segment, the electrode array module includes, in sequence, a first insulating sheet, a first electrode sheet, a second insulating sheet, a second electrode sheet, and a third insulating sheet, all of which are axially aligned and attached to each other and are annular, and the axes of the first insulating sheet, the first electrode sheet, the second insulating sheet, the second electrode sheet, and the third insulating sheet all coincide with the axis of the charge shell segment;

[0022] The first insulating sheet, the first electrode sheet, the second insulating sheet, the second electrode sheet and the third insulating sheet are all fixedly connected to the fixed flange of the charge shell segment close to the combustion shell segment and the fixed flange of the combustion shell segment close to the charge shell segment;

[0023] A plurality of conductive strips are fixedly mounted in parallel and at equal intervals on the first electrode sheet along a first direction and on the second electrode sheet along a second direction, wherein the first direction and the second direction are both perpendicular to the axis of the first electrode sheet and are perpendicular to each other;

[0024] A plurality of conductive teeth extending into the charge shell segment are evenly spaced on one side of the conductive strip facing the charge shell segment. The conductive teeth on the conductive strip of the first electrode sheet are staggered with the conductive teeth on the conductive strip of the second electrode sheet.

[0025] In one embodiment, a plurality of groups of positioning grooves for assembling conductive strips are evenly spaced on the side walls of the first electrode sheet and the second electrode sheet facing the charge shell segment, and each conductive strip is embedded in a group of positioning grooves.

[0026] In one embodiment, the outer diameters of the first insulating sheet, the first electrode sheet, the second insulating sheet, the second electrode sheet, and the third insulating sheet are equal and larger than the outer diameter of the charge shell segment, and the inner diameters are smaller than or equal to the inner diameter of the charge shell segment;

[0027] A plurality of wiring ears are evenly spaced on the neck-facing outer wall surfaces of the first insulating sheet, the first electrode sheet, the second insulating sheet, the second electrode sheet and the third insulating sheet. The wiring ears of the first insulating sheet, the first electrode sheet, the second insulating sheet, the second electrode sheet and the third insulating sheet are all aligned along the axis of the charge shell segment.

[0028] In one embodiment, the support assembly includes a medicine holder for pushing the electronically controlled solid propellant to be tested to move and at least one support member for supporting the electronically controlled solid propellant to be tested in the charge shell segment;

[0029] The medicine tray is conical, the top of the medicine tray is fixedly connected to the part of the transmission rod extending from the sleeve, and the bottom of the medicine tray is perpendicular to the axis of the charge shell segment;

[0030] The support member is provided with an annular support block which can be sleeved on the electronically controlled solid propellant to be tested, at least three fixed support columns and at least three adjustable support columns;

[0031] All fixed support columns are evenly distributed along the circumference of the support block, and all adjustable support columns are evenly distributed along the circumference of the support block;

[0032] Each fixed support column is fixedly connected to the support block, and each adjustable support column is threadedly connected to the support block.

[0033] In one embodiment, a nozzle and a pressure cap are provided at one end of the combustion shell section away from the charge shell section. The nozzle is fixedly connected to the charge shell section through the pressure cap, and the pressure cap is fixedly connected to the fixed flange at the end of the combustion shell section away from the charge shell section.

[0034] In one embodiment, the burner is further provided with a power supply module and a data acquisition module, and the pressure sensor is fixedly mounted on the outer side wall of the combustion shell section;

[0035] The stepping motor, the first electrode sheet and the second electrode sheet are all electrically connected to the power module, and the pressure sensor is electrically connected to the data acquisition module.

[0036] In one embodiment, a first annular sealing groove is provided on a side of the sealing flange facing the charge shell segment, wherein the inner diameter of the first sealing groove is larger than the inner diameter of the charge shell segment and the outer diameter is smaller than the outer diameter of the charge shell segment;

[0037] Two annular second sealing grooves are provided inside the sleeve;

[0038] At least one annular third sealing groove is provided on both sides of the first electrode sheet, on the outer side of the fixed flange of the charge shell segment close to the combustion shell segment, and on the outer side of the fixed flange of the combustion shell segment close to the charge shell segment. The inner diameter of the third sealing groove is larger than the inner diameter of the charge shell segment, and the outer diameter is smaller than the outer diameter of the charge shell segment.

[0039] O-type sealing rings are arranged inside the first sealing groove and the third sealing groove, and O-type sealing rings and Y-type sealing rings are arranged inside the two second sealing grooves respectively.

[0040] The beneficial effects of the present invention are as follows: the burner of the present invention for measuring the interior ballistic curve of an electronically controlled solid propellant can measure the interior ballistic curve of the electronically controlled solid propellant. The propellant moving assembly can push the support assembly behind which the electronically controlled solid propellant to be measured is fixed, so as to realize the movement of the electronically controlled solid propellant to be measured toward the electrode array module within the sealed burner shell, and the electronically controlled solid propellant to be measured is energized through the electrode array module so that the electronically controlled solid propellant can be electrolytically burned within the burner shell. The combination of the propellant moving assembly and the electrode array module can realize the continuous combustion of the electronically controlled solid propellant to be measured, and the interior ballistic curve of the electronically controlled solid propellant can be determined by collecting the change in the pressure inside the shell over time through the pressure sensor. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 A schematic structural diagram of a burner for measuring the interior ballistic curve of an electronically controlled solid propellant provided in an embodiment of the present invention;

[0042] Figure 2 A schematic diagram of the cross-sectional structure of a burner for measuring the interior ballistic curve of an electronically controlled solid propellant provided in an embodiment of the present invention, taken along a plane passing through the axis of the shell after the burner is loaded with the electronically controlled solid propellant to be measured;

[0043] Figure 3 A schematic structural diagram of a positioning flange provided in an embodiment of the present invention;

[0044] Figure 4 A schematic structural diagram of a sealing flange provided in an embodiment of the present invention;

[0045] Figure 5 A schematic structural diagram of an electrode array module provided in an embodiment of the present invention;

[0046] Figure 6 A schematic structural diagram of a first insulating sheet provided in an embodiment of the present invention;

[0047] Figure 7 A schematic structural diagram of a first electrode sheet provided in an embodiment of the present invention;

[0048] Figure 8 A schematic diagram of the assembly relationship between the first electrode sheet or the second electrode sheet and the conductive strip provided in an embodiment of the present invention;

[0049] Figure 9 A schematic structural diagram of a conductive strip provided in an embodiment of the present invention;

[0050] Figure 10 A schematic structural diagram of a support member provided in an embodiment of the present invention.

[0051] Explanation of reference numerals: 100, shell; 110, charge shell segment; 120, combustion shell segment; 130, fixed flange; 200, support assembly; 210, charge tray; 220, support member; 221, support block; 222, fixed support column; 223, adjustable support column; 300, electrode array module; 310, first insulating sheet; 320, first electrode sheet; 321, conductive strip; 322, conductive tooth; 323, positioning groove; 330, second insulating sheet; 340, second electrode sheet; 350, third insulating sheet Plate; 360, wiring ear; 370, third sealing groove; 400, propellant moving assembly; 410, transmission rod; 420, stepping motor; 430, motor mounting chamber; 440, supporting flange; 450, wiring barrel; 500, sealing layer; 510, positioning flange; 511, first through hole; 520, sealing flange; 521, second through hole; 522, sleeve; 523, first sealing groove; 524, second sealing groove; 600, nozzle; 700, gland; 800, electronically controlled solid propellant to be tested. DETAILED DESCRIPTION

[0052] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0053] It should be noted that in the description of the present invention, “upper”, “lower”, “top”, “bottom”, orientation or position relationship is based on the attached Figure 1 Regarding the orientation or positional relationship shown, it should be understood that these orientation terms are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, it should not be understood as a limitation on the present invention.

[0054] In one embodiment, Figure 1 and Figure 2 As shown, the burner of this embodiment for measuring the interior ballistic curve of an electronically controlled solid propellant includes:

[0055] The casing 100 includes a cylindrical charge shell section 110 and a conical combustion shell section 120 which are axially sealed and communicated with each other.

[0056] Specifically, the end of the combustion shell section 120 with a larger cross-sectional area is fixedly connected to the charge shell section 110 .

[0057] The support assembly 200 is used to fix and support the electronically controlled solid propellant 800 to be tested. The support assembly 200 is arranged inside the charge shell segment 110 and can slide along the axis of the charge shell segment 110.

[0058] The electrode array module 300 is used to apply voltage to the electronically controlled solid propellant 800 to be tested. The electrode array module 300 is arranged between the charge shell segment 110 and the combustion shell segment 120. The charge shell segment 110 and the combustion shell segment 120 are respectively axially fixedly connected to the two ends of the electrode array module 300.

[0059] When the electronically controlled solid propellant 800 to be tested contacts the electrode array module 300 , the electrode array module 300 can energize the electronically controlled solid propellant 800 to be tested, thereby achieving electrolytic combustion of the electronically controlled solid propellant 800 to be tested in the combustor housing 100 .

[0060] A propellant moving assembly 400 is used to drive the support assembly 200, which is fixed with the electronically controlled solid propellant 800 to be tested, to move along the axis of the charge shell segment 110 toward the electrode array module 300 within the charge shell segment 110. The propellant moving assembly 400 is axially fixedly connected to the support assembly 200.

[0061] A pressure sensor can collect pressure changes inside the casing 100 , and the pressure sensor is fixedly mounted on the outer side wall of the combustion shell section 120 .

[0062] Specifically, an M20 internal threaded hole is provided on the side wall of the combustion shell section 120 for connecting a pressure sensor. The pressure change inside the combustion shell section 120 collected by the pressure sensor can be used to determine the internal ballistic curve of the electronically controlled solid propellant.

[0063] In this embodiment, the support assembly 200 secures the electronically controlled solid propellant 800 under test to a central position within the charge shell section 110, facilitating movement of the electronically controlled solid propellant 800 under test by the propellant movement assembly 400. The propellant movement assembly 400 propels the support assembly 200 back and forth within the charge shell section 110, thereby enabling the electronically controlled solid propellant 800 under test to move toward the electrode array module 300 within the sealed combustor housing 100, thereby energizing the electronically controlled solid propellant 800 under test and thereby contacting the electrode array module 300.

[0064] The burner for measuring the interior ballistic curve of an electronically controlled solid propellant according to this embodiment can measure the interior ballistic curve of the electronically controlled solid propellant.

[0065] In one embodiment, both axial ends of the charge shell section 110 and both axial ends of the combustion shell section 120 are integrally connected with fixed flanges 130 .

[0066] The function of the fixing flange 130 is to realize the assembly connection between the propellant moving assembly 400 , the charge shell segment 110 , the electrode array module 300 and the combustion shell segment 120 .

[0067] In this embodiment, a sealing layer 500 is provided at the end of the charge shell segment 110 away from the combustion shell segment 120. The sealing layer 500 includes a positioning flange 510 and a sealing flange 520. The outer diameters of the positioning flange 510 and the sealing flange 520 are equal and larger than the outer diameter of the charge shell segment 110. The positioning flange 510 and the sealing flange 520 are both axially fixedly connected to the fixing flange 130 at the end of the charge shell segment 110 away from the combustion shell segment 120. The sealing flange 520 is located between the positioning flange 510 and the charge shell segment 110.

[0068] The positioning flange 510, the sealing flange 520 and the fixing flange 130 at the end of the charge shell section 110 away from the combustion shell section 120 are all provided with at least six bolt holes, and the positioning flange 510, the sealing flange 520 and the fixing flange 130 at the end of the charge shell section 110 away from the combustion shell section 120 are fixedly connected by multiple bolts.

[0069] Specifically, the sealing flange 520 prevents the wall gas from leaking toward the propellant moving assembly 400, ensuring that the gas is ejected from the combustion shell 120 and ensuring measurement accuracy. The positioning flange 510 is used to achieve positioning and assembly of the propellant moving assembly 400.

[0070] like Figure 3 and Figure 4 As shown, a first through-hole 511 is provided at the center of the positioning flange 510, a second through-hole 521 is provided at the center of the sealing flange 520, and a sleeve 522 is provided perpendicularly at the center of the side of the sealing flange 520 facing the charge shell segment 110. The inner diameter of the sleeve 522 is equal to the inner diameter of the second through-hole 521. The sleeve 522 is integrally connected to the sealing flange 520 and communicates with the second through-hole 521. The function of the sleeve 522 is to support the transmission rod 410 and limit the transmission rod 410 in the radial direction.

[0071] In one embodiment, the propellant movement assembly 400 includes a transmission rod 410, a stepper motor 420, a cylindrical motor mounting chamber 430, and a support flange 440. A wiring barrel 450 is fixedly mounted on the outer wall of the motor mounting chamber 430 for passing wires through to connect the stepper motor 420 and a power source.

[0072] The motor mounting chamber 430 is axially fixedly connected to the center of the side of the positioning flange 510 that is away from the sealing flange 520. The stepper motor 420 is axially mounted inside the motor mounting chamber 430. The support flange 440 is fixedly mounted to the end of the motor mounting chamber 430 that is away from the charge shell section 110. The front end cover of the stepper motor 420 abuts the positioning flange 510, and the rear end cover abuts the support flange 440, thereby fixing the position of the stepper motor 420.

[0073] The transmission rod 410 is inserted into the connecting hole formed by the second through hole 521 and the sleeve 522. An internal threaded hole is provided at the end of the transmission rod 410 away from the sleeve 522. The output shaft of the stepper motor 420 is inserted into the first through hole 511, and the part extending from the first through hole 511 is provided with an external thread. The output shaft of the stepper motor 420 is threadedly connected to the internal threaded hole.

[0074] The stepper motor 420 has the functions of adjustable speed and adjustable stroke. Its output shaft is threadedly connected to the internal threaded hole of the transmission rod 410, and the rear end cover is in contact with the support flange 440. When the stepper motor 420 rotates, it drives the transmission rod 410 to move toward the electrode array module 300 in the connecting hole formed by the second through hole 521 and the sleeve 522, and can simultaneously drive the medicine holder 210 to push the electronically controlled solid propellant 800 to be tested toward the electrode array module 300.

[0075] like Figure 5 、 Figure 6 and Figure 7 As shown, in one embodiment, along the direction from the charge shell segment 110 to the combustion shell segment 120, the electrode array module 300 includes, in sequence, a first insulating sheet 310, a first electrode sheet 320, a second insulating sheet 330, a second electrode sheet 340 and a third insulating sheet 350, which are axially aligned and fit together and are all annular. The axes of the first insulating sheet 310, the first electrode sheet 320, the second insulating sheet 330, the second electrode sheet 340 and the third insulating sheet 350 all coincide with the axis of the charge shell segment 110 and fit tightly together.

[0076] The first insulating sheet 310, the second insulating sheet 330, and the third insulating sheet 350 are made of insulating materials and have the same shape and size. The first electrode sheet 320 and the second electrode sheet 340 are made of conductive materials and have the same shape and size. The insulating sheets separate the two electrode sheets and insulate the housing 100 from the electrode sheets.

[0077] The first insulating sheet 310 , the first electrode sheet 320 , the second insulating sheet 330 , the second electrode sheet 340 and the third insulating sheet 350 are all fixedly connected to the fixed flange 130 at one end of the charge shell segment 110 close to the combustion shell segment 120 and the fixed flange 130 at one end of the combustion shell segment 120 close to the charge shell segment 110 .

[0078] Specifically, the first insulating sheet 310, the first electrode sheet 320, the second insulating sheet 330, the second electrode sheet 340 and the third insulating sheet 350 are each provided with a number of evenly arranged threaded through holes, and the threaded through holes provided in each are aligned, and the fixed assembly of each insulating sheet and electrode sheet with the charge shell segment 110 and the combustion shell segment 120 is achieved by connecting the threaded through holes with a number of bolts.

[0079] like Figure 8As shown, a plurality of conductive strips 321 are fixedly mounted in parallel and at equal intervals along the first direction on the first electrode sheet 320 and along the second direction on the second electrode sheet 340. The first direction and the second direction are both perpendicular to the axis of the first electrode sheet 320 and are perpendicular to each other. Figure 9 As shown, a plurality of conductive teeth 322 extending toward the interior of the charge shell segment 110 are evenly spaced on the side of the conductive strip 321 facing the charge shell segment 110 , and the conductive teeth 322 on the conductive strip 321 of the first electrode sheet 320 are alternately arranged with the conductive teeth 322 on the conductive strip 321 of the second electrode sheet 340 .

[0080] It should be noted that, in this embodiment, the spacing and number between the conductive strips 321, the spacing and number between the conductive teeth 322, and the tooth area can be specifically set according to actual measurement requirements to meet the measurement requirements of various sizes of electronically controlled solid propellant combustion surfaces, thereby greatly improving the applicability of the burner of this embodiment.

[0081] If both the first and second directions are perpendicular to the axis of the first electrode sheet 320 and are mutually perpendicular, all conductive strips 321 can form an array electrode, increasing the conductive area. Furthermore, each conductive strip 321 is independent of the others. If one or more conductive strips 321 are damaged, they can be replaced individually, significantly reducing redundant maintenance costs for the device.

[0082] More specifically, a plurality of groups of positioning grooves 323 for assembling the conductive strips 321 are evenly spaced on the side walls of the first electrode sheet 320 and the second electrode sheet 340 facing the charge shell segment 110 , and each conductive strip 321 is embedded in a group of positioning grooves 323 .

[0083] In one embodiment, the outer diameters of the first insulating sheet 310 , the first electrode sheet 320 , the second insulating sheet 330 , the second electrode sheet 340 and the third insulating sheet 350 are equal and larger than the outer diameter of the charge shell segment 110 , and the inner diameters are less than or equal to the inner diameter of the charge shell segment 110 .

[0084] A plurality of wiring ears 360 are evenly spaced apart on the neck-facing outer wall surfaces of the first insulating sheet 310 , the first electrode sheet 320 , the second insulating sheet 330 , the second electrode sheet 340 , and the third insulating sheet 350 . The wiring ears 360 of the first insulating sheet 310 , the first electrode sheet 320 , the second insulating sheet 330 , the second electrode sheet 340 , and the third insulating sheet 350 are all aligned along the axis of the charge shell segment 110 .

[0085] The function of the wiring lug 360 is to connect the first electrode sheet 320 and the second electrode sheet 340 to an external power source. For example, the wire can be clamped between the wiring lug 360 where the insulating sheet and the electrode sheet are aligned.

[0086] In one embodiment, the support assembly 200 includes a cartridge 210 for propelling the electronically controlled solid propellant 800 under test and at least one support member 220 for supporting the electronically controlled solid propellant 800 under test within the charge shell segment 110. The cartridge 210 is conical in shape, with the top of the cartridge 210 fixedly connected to the portion of the drive rod 410 extending from the sleeve 522, and the bottom of the cartridge 210 perpendicular to the axis of the charge shell segment 110. The cartridge 210 is used to propel the electronically controlled solid propellant 800 under test.

[0087] For example, the top of the medicine holder 210 is threadedly connected to the portion of the transmission rod 410 extending from the sleeve 522 .

[0088] like Figure 10 As shown, the support member 220 is provided with an annular support block 221 that can be sleeved on the electronically controlled solid propellant 800 to be tested, at least three fixed support columns 222, and at least three adjustable support columns 223. All fixed support columns 222 are evenly distributed along the circumference of the support block 221, and all adjustable support columns 223 are evenly distributed along the circumference of the support block 221.

[0089] Specifically, the support block 221 is provided with a plurality of through holes for installing fixed support columns 222 and adjustable support columns 223. Each fixed support column 222 is fixedly connected to a through hole on the support block 221, and each adjustable support column 223 is threadedly connected to a through hole on the support block 221.

[0090] The fixed support column 222 is used to support the mounting block inside the charge housing 100. The adjustable support column 223 is threadedly connected to the through hole of the support block 221. The connection depth can be adjusted according to the diameter of the electronically controlled solid propellant, thereby supporting and fixing electronically controlled solid propellants 800 of different diameters to be tested.

[0091] It should be noted that, in this embodiment, the inner diameter of the annular support block 221 and the length of each support column can be specifically set according to the actual needs of the electronically controlled solid propellant.

[0092] In one embodiment, a nozzle 600 and a gland 700 are provided at the end of the combustion segment 120 away from the charge segment 110. The nozzle 600 is fixedly connected to the charge segment 110 via the gland 700. The gland 700 is fixedly connected to the fixed flange 130 at the end of the combustion segment 120 away from the charge segment 110. The gland 700 has a through hole that communicates with the nozzle 600.

[0093] The combustion gas generated by the combustion of the electronically controlled solid propellant is ejected from the housing 100 through the nozzle 600 .

[0094] In one embodiment, the burner is further provided with a power module and a data acquisition module, and a pressure sensor is fixedly mounted on the outer wall of the combustion shell section 120. The power module is used to output 220V regulated DC, and the pressure sensor has a range of 10MPa.

[0095] The stepping motor 420 , the first electrode sheet 320 and the second electrode sheet 340 are all electrically connected to the power module, and the pressure sensor is electrically connected to the data acquisition module.

[0096] The data acquisition module is used to collect and record the pressure change process inside the burner housing 100 measured by the pressure sensor, and form a pressure-time curve, that is, an internal ballistic curve, according to the pressure transformation process.

[0097] In one embodiment, an annular first sealing groove 523 is provided on the side of the sealing flange 520 facing the charge shell segment 110. The inner diameter of the first sealing groove 523 is larger than the inner diameter of the charge shell segment 110, and the outer diameter is smaller than the outer diameter of the charge shell segment 110. Two annular second sealing grooves 524 are provided inside the sleeve 522. At least one annular third sealing groove 370 is provided on both sides of the first electrode sheet 320, on the outer side of the fixed flange 130 at the end of the charge shell segment 110 near the combustion shell segment 120, and on the outer side of the fixed flange 130 at the end of the combustion shell segment 120 near the charge shell segment 110. The inner diameter of the third sealing groove 370 is larger than the inner diameter of the charge shell segment 110, and the outer diameter is smaller than the outer diameter of the charge shell segment 110. O-rings are provided inside each of the first sealing groove 523 and the third sealing groove 370 to achieve static sealing connections between the flanges, between the flanges and the insulating sheet, and between the insulating sheet and the electrode sheet. An O-ring and a Y-ring are respectively disposed within the two second sealing grooves 524. The combination of the O-ring and the Y-ring enables dynamic sealing when the transmission rod 410 rotates within the sleeve 522. Both sealing rings are made of rubber.

[0098] The sealing ring provided inside the sealing groove can enhance the sealing performance of the housing 100 so that the high-pressure gas generated by the combustion of the solid propellant can only be ejected along the nozzle 600, thereby ensuring measurement accuracy while preventing leakage of the high-pressure gas from damaging the propellant moving assembly 400.

[0099] In a specific embodiment, the positioning flange 510, the sealing flange 520 and the fixing flange 130 at the end of the charge shell section 110 away from the combustion shell section 120 are all provided with eight bolt holes. The stroke of the stepper motor 420 is 250 mm. The outer diameter of the transmission rod 410 is 20 mm. The inner diameter of each electrode sheet is 190 mm, the number of conductive strips 321 on each electrode sheet is 15, and the conductive teeth 322 on each conductive strip 321 are spaced 9 mm apart. The 30 conductive teeth 322 on the two electrode sheets ultimately form an array electrode area covering a diameter of 190 mm. The support assembly 200 includes two support members 220, each support member 220 is provided with 8 support columns.

[0100] The working process of the burner used for measuring the interior ballistic curve of an electronically controlled solid propellant in this embodiment is as follows: First, the electronically controlled solid propellant 800 to be tested is fixed to the support assembly 200. Then, the support assembly 200 is placed inside the combustion shell 120, and the rear end of the electronically controlled solid propellant 800 to be tested is abutted against the medicine holder 210. Then, all components are assembled according to the above embodiment. Next, the power module and the data acquisition module are turned on. At this time, the propellant moving assembly 400 continuously advances the electronically controlled solid propellant 800 to be tested, so that the propellant contacts and maintains contact with the electrode array module 300 for electrolytic combustion, generating a large amount of combustion gas. The pressure sensor detects the pressure change inside the shell 100 and transmits the measurement data to the data acquisition module. The data acquisition module generates the interior ballistic curve of the electronically controlled solid propellant 800 to be tested based on the pressure conversion data inside the shell 100.

[0101] The burner for measuring the interior ballistic curve of an electronically controlled solid propellant according to this embodiment can be used to perform a closed combustion test on an electronically controlled solid propellant 800 with unknown performance to obtain an interior ballistic curve of the electronically controlled solid propellant combustion that is closer to the actual usage scenario, thereby providing reference data for the design and development of the electronically controlled solid propellant.

[0102] The above-described embodiments merely represent several implementation methods of the present invention. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that a person skilled in the art would be able to make various modifications and improvements without departing from the spirit of the present invention, all of which fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be determined by the appended claims.

Claims

1. A burner used for measuring the interior ballistic curve of an electronically controlled solid propellant, characterized in that: include: A casing (100), the casing (100) comprising a cylindrical charge shell section (110) and a conical combustion shell section (120) which are axially sealed and connected; A support assembly (200) for fixedly supporting the electronically controlled solid propellant (800) to be tested, wherein the support assembly (200) is arranged inside the charge shell segment (110) and can slide along the axis of the charge shell segment (110); An electrode array module (300) for applying voltage to the electrically controlled solid propellant (800) to be tested, the electrode array module (300) being disposed between the charge shell segment (110) and the combustion shell segment (120), the charge shell segment (110) and the combustion shell segment (120) being axially fixedly connected to both ends of the electrode array module (300); a propellant moving assembly (400) for driving a support assembly (200) fixed with an electrically controlled solid propellant (800) to be tested to move inside a charge shell segment (110) along the axis of the charge shell segment (110) toward an electrode array module (300), wherein the propellant moving assembly (400) is axially fixedly connected to the support assembly (200); A pressure sensor capable of collecting pressure changes inside the shell (100) is fixedly mounted on the outer side wall of the combustion shell section (120).

2. The burner for measuring the interior ballistic curve of an electronically controlled solid propellant according to claim 1, characterized in that: Both axial ends of the charge shell section (110) and both axial ends of the combustion shell section (120) are integrally connected with fixed flanges (130); A sealing layer (500) is provided at one end of the charge shell section (110) away from the combustion shell section (120), and the sealing layer (500) includes a positioning flange (510) and a sealing flange (520). The outer diameters of the positioning flange (510) and the sealing flange (520) are equal and larger than the outer diameter of the charge shell section (110). The positioning flange (510) and the sealing flange (520) are both axially fixedly connected to the fixing flange (130) at one end of the charge shell section (110) away from the combustion shell section (120). The sealing flange (520) is located between the positioning flange (510) and the charge shell section (110); A first through hole (511) is provided at the center of the positioning flange (510), a second through hole (521) is provided at the center of the sealing flange (520), a sleeve (522) is vertically provided at the center of one side of the sealing flange (520) facing the charge shell section (110), the inner diameter of the sleeve (522) is equal to the inner diameter of the second through hole (521), and the sleeve (522) is integrally connected to the sealing flange (520) and communicated with the second through hole (521).

3. The burner for measuring the interior ballistic curve of an electronically controlled solid propellant according to claim 2, characterized in that: The propellant moving assembly (400) is provided with a transmission rod (410), a stepping motor (420), a cylindrical motor installation chamber (430) and a supporting flange (440); The outer side wall of the motor installation chamber (430) is fixedly equipped with a wiring barrel (450); The motor mounting chamber (430) is axially fixedly connected to the center of the side of the positioning flange (510) away from the sealing flange (520), the stepping motor (420) is axially assembled inside the motor mounting chamber (430), and the supporting flange (440) is fixedly assembled to the end of the motor mounting chamber (430) away from the charge shell section (110); The front end cover of the stepping motor (420) abuts against the positioning flange (510), and the rear end cover abuts against the supporting flange (440); The transmission rod (410) is inserted into the communicating hole formed by the second through hole (521) and the sleeve (522); an internal threaded hole is provided at one end of the transmission rod (410) away from the sleeve (522); the output shaft of the stepping motor (420) is inserted into the first through hole (511), and the portion extending from the first through hole (511) is provided with an external thread; the output shaft of the stepping motor (420) is threadedly connected to the internal threaded hole.

4. The burner for measuring the interior ballistic curve of an electronically controlled solid propellant according to claim 3, characterized in that: Along the direction from the charge shell section (110) to the combustion shell section (120), the electrode array module (300) sequentially comprises a first insulating sheet (310), a first electrode sheet (320), a second insulating sheet (330), a second electrode sheet (340), and a third insulating sheet (350) which are axially aligned and affixed and are all annular, and the axes of the first insulating sheet (310), the first electrode sheet (320), the second insulating sheet (330), the second electrode sheet (340), and the third insulating sheet (350) all coincide with the axis of the charge shell section (110); The first insulating sheet (310), the first electrode sheet (320), the second insulating sheet (330), the second electrode sheet (340), and the third insulating sheet (350) are all fixedly connected to the fixed flange (130) at one end of the charge shell section (110) close to the combustion shell section (120) and the fixed flange (130) at one end of the combustion shell section (120) close to the charge shell section (110); A plurality of conductive strips (321) are fixedly mounted in parallel and at equal intervals on the first electrode sheet (320) along a first direction and on the second electrode sheet (340) along a second direction, the first direction and the second direction being perpendicular to the axis of the first electrode sheet (320), and the first direction and the second direction being perpendicular to each other; A plurality of conductive teeth (322) extending toward the interior of the charge shell segment (110) are arranged at equal intervals on the side of the conductive strip (321) facing the charge shell segment (110), and the conductive teeth (322) on the conductive strip (321) of the first electrode sheet (320) and the conductive teeth (322) on the conductive strip (321) of the second electrode sheet (340) are arranged in an alternating manner.

5. The burner for measuring the interior ballistic curve of electronically controlled solid propellant according to claim 4, characterized in that: Multiple groups of positioning grooves (323) for assembling the conductive strips (321) are evenly spaced apart on the side walls of the first electrode sheet (320) and the second electrode sheet (340) facing the charge shell section (110), and each conductive strip (321) is embedded in a group of positioning grooves (323).

6. The burner for measuring the interior ballistic curve of electronically controlled solid propellant according to claim 5, characterized in that: The outer diameters of the first insulating sheet (310), the first electrode sheet (320), the second insulating sheet (330), the second electrode sheet (340), and the third insulating sheet (350) are equal and larger than the outer diameter of the charge shell segment (110), and the inner diameters are smaller than or equal to the inner diameter of the charge shell segment (110); A plurality of wiring ears (360) are evenly spaced on the neck-facing outer wall surfaces of the first insulating sheet (310), the first electrode sheet (320), the second insulating sheet (330), the second electrode sheet (340), and the third insulating sheet (350), and the wiring ears (360) of the first insulating sheet (310), the first electrode sheet (320), the second insulating sheet (330), the second electrode sheet (340), and the third insulating sheet (350) are all aligned along the axis of the charge shell segment (110).

7. The burner for measuring the interior ballistic curve of an electronically controlled solid propellant according to claim 6, characterized in that: The support assembly (200) comprises a medicine holder (210) for pushing the electronically controlled solid propellant (800) to be tested to move and at least one support member (220) for supporting the electronically controlled solid propellant (800) to be tested in the charge shell section (110); The medicine tray (210) is conical, the top of the medicine tray (210) is fixedly connected to the portion of the transmission rod (410) extending from the sleeve (522), and the bottom of the medicine tray (210) is perpendicular to the axis of the charge shell segment (110); The support member (220) is provided with an annular support block (221) that can be sleeved on the electronically controlled solid propellant (800) to be tested, at least three fixed support columns (222) and at least three adjustable support columns (223); All fixed support columns (222) are evenly distributed along the circumference of the support block (221), and all adjustable support columns (223) are evenly distributed along the circumference of the support block (221); Each fixed support column (222) is fixedly connected to the support block (221), and each adjustable support column (223) is threadedly connected to the support block (221).

8. The burner for measuring the interior ballistic curve of an electronically controlled solid propellant according to claim 7, characterized in that: A nozzle (600) and a pressure cap (700) are provided at one end of the combustion shell section (120) away from the charge shell section (110); the nozzle (600) is fixedly connected to the charge shell section (110) via the pressure cap (700); and the pressure cap (700) is fixedly connected to a fixed flange (130) at one end of the combustion shell section (120) away from the charge shell section (110).

9. The burner for measuring the interior ballistic curve of electronically controlled solid propellant according to claim 8, characterized in that: The burner is also provided with a power supply module and a data acquisition module; The stepping motor (420), the first electrode sheet (320) and the second electrode sheet (340) are all electrically connected to the power module, and the pressure sensor is electrically connected to the data acquisition module.

10. The burner for measuring the interior ballistic curve of electronically controlled solid propellant according to claim 9, characterized in that: A first annular sealing groove (523) is provided on the side of the sealing flange (520) facing the charge shell segment (110), wherein the inner diameter of the first sealing groove (523) is larger than the inner diameter of the charge shell segment (110), and the outer diameter is smaller than the outer diameter of the charge shell segment (110); Two annular second sealing grooves (524) are provided inside the sleeve (522); At least one annular third sealing groove (370) is provided on both sides of the first electrode sheet (320), on the outer side of the fixed flange (130) at one end of the charge shell segment (110) close to the combustion shell segment (120), and on the outer side of the fixed flange (130) at one end of the combustion shell segment (120) close to the charge shell segment (110). The inner diameter of the third sealing groove (370) is larger than the inner diameter of the charge shell segment (110), and the outer diameter is smaller than the outer diameter of the charge shell segment (110). The first sealing groove (523) and the third sealing groove (370) are both provided with O-type sealing rings, and the two second sealing grooves (524) are respectively provided with O-type sealing rings and Y-type sealing rings.

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