A device and method for measuring low-pressure combustion of solid propellants

Abstract

This invention discloses a solid propellant low-pressure combustion measurement device, comprising a combustion chamber formed by a top plate, a bottom plate, and a chamber wall; an optical measurement assembly located outside the combustion chamber; and a laser located above the combustion chamber. The combustion chamber has a propellant-carrying platform. Stepped holes are formed in the middle of both the top and bottom plates, and upper and lower cover plates are detachably mounted thereon. Both the upper and lower cover plates are stepped shafts, respectively cooperating with the stepped holes in the top and bottom plates. A through hole is formed in the middle of the upper cover plate, and a glass plate is installed in the through hole. The propellant-carrying platform includes a stage and a propellant holder. The stage is fixed to the top surface of the lower cover plate, and the propellant holder is detachably mounted on the stage. A propellant loading groove is formed on the top surface of the propellant holder. A glass viewing window and an evacuation port are provided on the chamber wall. The optical measurement assembly includes a high-speed CCD camera, a fiber optic spectrometer, a photoresistor sensor, and a flame sensor. The laser includes a laser generator and an incident light path. This device is capable of measuring the low-pressure combustion of solid propellants.

Description

Technical Field

[0001] This invention belongs to the field of solid rocket engine testing technology, specifically relating to a solid propellant low-pressure combustion measurement device and method. Background Technology

[0002] With the development of new equipment, the combustion performance of solid propellants under low-pressure environments has received increasing attention. Low-pressure environments have a significant impact on the combustion performance of solid propellants. In order to obtain the low-pressure combustion performance parameters of solid propellants, a low-pressure combustion test device for solid propellants is needed.

[0003] Laser remote ignition is a highly reliable and safe experimental method for solid propellant ignition and combustion experiments. By adjusting the laser power and laser loading time, the laser ignition energy and energy density of solid propellants can be precisely controlled, with minimal influence from external factors such as propellant combustion pressure and the propellant combustion environment.

[0004] Currently, there are few solid propellant laser ignition test devices used for low-pressure combustion measurements. Therefore, there is a need to develop a low-pressure ignition and combustion test device that can record, measure, and analyze the combustion process of solid propellants under low pressure. Summary of the Invention

[0005] To address the limitation of existing solid propellant ignition and combustion devices in measuring propellant combustion parameters under low-pressure conditions, this invention provides a solid propellant low-pressure combustion measurement device and method.

[0006] The solid propellant low-pressure combustion measuring device of the present invention includes a combustion chamber consisting of a top plate, a bottom plate and a box wall connected to form a square box, an optical measuring component located outside the combustion chamber and a laser located above the combustion chamber, and a propellant loading platform inside the combustion chamber;

[0007] Both the top plate and the bottom plate have through-holes in the middle, and an upper cover plate and a lower cover plate are detachably installed on them. The upper cover plate and the lower cover plate are both stepped shafts, which are used in conjunction with the stepped holes of the top plate and the bottom plate, respectively, and seal the stepped holes of the top plate and the bottom plate.

[0008] The top cover has a through hole running vertically through the middle, and a glass plate is installed in the through hole to seal it.

[0009] The drug-carrying platform includes a platform and a drug seat. The platform is fixed to the top surface of the lower cover plate, and the drug seat is detachably installed on the platform. The top surface of the drug seat is recessed downward to form a drug loading groove.

[0010] The chamber wall is equipped with a glass viewing window and an exhaust port for extracting air from the combustion chamber.

[0011] The optical measurement components include a high-speed CCD camera, a fiber optic spectrometer, a photoresistor sensor, and a flame sensor. The optical measurement components measure combustion parameters in the combustion chamber through a glass window.

[0012] The laser includes a laser generator and an incident light path for guiding the laser emitted by the laser generator. The laser passes through the incident light path and a glass plate to reach the charge tank.

[0013] By installing a removable top cover plate on the top plate, the top cover plate can be removed, and cleaning tools can be inserted into the combustion chamber cavity through the stepped holes in the top plate for cleaning; by installing a removable bottom cover plate on the bottom plate, the bottom cover plate can be removed, and the cleaned waste residue can be discharged through the stepped holes in the bottom plate, and it can also be used for the collection of post-combustion products.

[0014] Furthermore, the diameter of the stepped holes in the top plate decreases sequentially from top to bottom, and the hole wall has three steps. A groove is formed at the connection between the tread and the riser of the second step to create a first sealing ring groove. The stepped hole structure of the bottom plate is symmetrical to that of the top plate. The stepped shaft of the upper cover plate also has three steps, with a groove formed at the connection between the tread and the riser of the second step to create a second sealing ring groove. The stepped shaft structure of the lower cover plate is symmetrical to that of the upper cover plate. First and second sealing rings are placed in the first and second sealing ring grooves, respectively. A low-pressure environment can be achieved through the use of stepped sealing and sealing ring sealing. Support feet are provided at the bottom of the bottom plate, allowing the lower cover plate to be suspended, facilitating its installation and removal.

[0015] Furthermore, the through hole on the top cover plate is a stepped hole, and the stepped hole wall is a two-stage step. The lower step surface of the second-stage step, which is parallel to the top surface of the top cover plate, serves as a support surface, and the glass plate is placed on the support surface. An annular pressure plate is also installed on the top surface of the top cover plate. The pressure plate presses and fixes one edge of the glass plate. A third sealing ring groove is opened on the bottom surface of the pressure plate, and a third sealing ring is placed in the third sealing ring groove. The third sealing ring is located between the pressure plate and the top cover plate. A fourth sealing ring is also provided between the pressure plate and the glass plate.

[0016] Furthermore, the platform includes a first circular plate and a first cylinder vertically fixed to the top surface of the first circular plate. The first cylinder and the first circular plate are coaxial, and the diameter of the first cylinder is smaller than the diameter of the first circular plate. The first circular plate is installed on the top surface of the lower cover plate, and a recessed mounting groove is provided on the top surface of the first cylinder.

[0017] Furthermore, the medicine holder includes a second circular plate and a second cylinder vertically fixed to the bottom surface of the second circular plate. The second cylinder and the second circular plate are coaxial, and the diameter of the second cylinder is smaller than the diameter of the second circular plate. The second cylinder is inserted into the mounting groove, and the second circular plate is mounted and fixed to the top surface of the first cylinder. The medicine loading groove is opened on the top surface of the second circular plate.

[0018] Rapid drug loading is achieved by setting up a stage and a drug holder. During the test, the lower cover plate is removed first, and the stage is also removed at the same time. The pre-loaded drug holder is installed on the stage, and then the lower cover plate is installed on the bottom plate to complete the drug loading.

[0019] The present invention also provides a measurement method using the above-mentioned solid propellant low-pressure combustion measurement device, comprising the following steps: 1) pre-filling the solid propellant into the propellant loading slot of the propellant seat; 2) removing the lower cover plate, installing the propellant seat on the platform on the lower cover plate, installing the lower cover plate, and using a vacuum pump to pressurize the combustion chamber to a predetermined pressure; 3) using a laser to emit a laser to ignite the solid propellant in the propellant loading slot of the combustion chamber, and simultaneously using an optical measurement component to record the flame morphology, ignition delay time, flame temperature, and metal particle agglomeration phenomenon during the combustion process.

[0020] Beneficial effects: The solid propellant low-pressure combustion measurement device of the present invention can collect and record combustion data and metal particle agglomeration phenomena of solid propellant under different pressures by controlling the ambient pressure of solid propellant, thereby further analyzing and studying the low-pressure combustion characteristics of solid propellant; the solid propellant is pre-filled into the charging slot on the propellant seat; after the charging is completed, the combustion chamber is pressurized to a predetermined pressure by connecting a vacuum pump to a vacuum pipeline and connecting it to the evacuation port to achieve low pressure; the laser remotely ignites the solid propellant through laser, and the optical measurement component measures the solid propellant through a glass window. The flame morphology, ignition delay time, flame temperature, and metal particle agglomeration during the propellant rotation combustion process are photographed and recorded, thereby enabling the study of the combustion characteristics of solid propellants under low pressure. By setting the stepped hole structure of the top and bottom plates, the stepped shaft structure of the upper and lower cover plates, and the sealing method, stepped seals and sealing ring seals can be used to achieve a low-pressure environment in the combustion chamber. By setting the through-hole structure and sealing method of the upper cover plate, a low-pressure environment in the combustion chamber can be achieved. By setting the stage and propellant seat structure, rapid propellant loading can be achieved. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the structure of the solid propellant low-pressure combustion measuring device of the present invention;

[0022] Figure 2 This is a half-sectional schematic diagram of the solid propellant low-pressure combustion measuring device of the present invention;

[0023] Figure 3 This is a schematic diagram of the upper cover plate; where (a) is a cross-sectional view and (b) is a top view.

[0024] Figure 4 This is a schematic diagram of the lower cover plate; where (a) is a cross-sectional view and (b) is a top view.

[0025] Figure 5 Here is a schematic diagram of the platform structure; where (a) is a cross-sectional view and (b) is a top view.

[0026] Figure 6 This is a schematic diagram of the drug reservoir structure; where (a) is a cross-sectional view and (b) is a top view.

[0027] In the diagram, 1 is the combustion chamber; 11 is the top plate; 12 is the bottom plate; 121 is the support leg; 13 is the chamber wall; 131 is the glass window; 132 is the exhaust port; 14 is the upper cover plate; 141 is the second sealing ring groove; 142 is the through hole; 15 is the lower cover plate; 16 is the glass plate; 17 is the pressure plate; 18 is the first sealing ring; 19 is the second sealing ring; 2 is the optical measurement assembly; 3 is the laser; 4 is the propellant loading platform; 41 is the platform; 411 is the first circular plate; 412 is the first cylinder; 413 is the mounting groove; 42 is the propellant seat; 421 is the second circular plate; 422 is the second cylinder; and 423 is the propellant loading groove. Detailed Implementation

[0028] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments, but the present invention is not limited to the embodiments.

[0029] like Figures 1-2 As shown, the present invention is a solid propellant low-pressure combustion measurement device, including a combustion chamber 1 formed by a top plate 11, a bottom plate 12 and a box wall 13 connected to form a square box, an optical measurement component 2 located outside the combustion chamber 1 and a laser 3 located above the combustion chamber 1, and a propellant platform 4 inside the combustion chamber 1.

[0030] Both the top plate 11 and the bottom plate 12 have stepped holes that extend vertically through the middle, and an upper cover plate 14 and a lower cover plate 15 are detachably installed on them respectively. The upper cover plate 14 and the lower cover plate 15 are both stepped shafts, which are used in conjunction with the stepped holes of the top plate 11 and the bottom plate 12 respectively, and seal the stepped holes of the top plate 11 and the bottom plate 12 respectively.

[0031] Specifically, such as Figure 2 As shown, the diameter of the stepped holes in the top plate 11 decreases from top to bottom. The stepped holes have three steps, with a groove forming a first sealing ring groove at the connection between the tread and the riser of the second step. The stepped hole structure of the bottom plate 12 is symmetrical to that of the top plate 11. Figure 3 As shown, the upper cover plate 14 has a three-step stepped shaft, with a groove forming a second sealing ring groove 141 at the connection between the tread and the riser of the second step. The stepped shaft structure of the lower cover plate 15 is symmetrical to that of the upper cover plate 14 (e.g., Figure 4As shown in the diagram, a first sealing ring 18 and a second sealing ring 19 are respectively placed in the first sealing ring groove and the second sealing ring groove 141. Mounting holes are provided on the upper cover plate 14 and the lower cover plate 15, and screw holes are provided on the top plate 11 and the bottom plate 12. Screws are used to fasten the upper cover plate 14 to the top plate 11 and the lower cover plate 15 to the bottom plate 12. A support leg 121 is integrally formed at the bottom of the bottom plate 12 to suspend the lower cover plate 15, thereby facilitating the installation and removal of the lower cover plate 15.

[0032] The upper cover plate 14 has a through hole 142 extending vertically through its center, and a glass plate 16 is installed in the through hole 142 to seal it. Specifically, as shown... Figure 3 As shown, the through hole 142 on the upper cover plate 14 is a stepped hole. Each hole in the stepped hole is circular and coaxial with the central axis of the combustion chamber 1. The stepped hole wall has two steps, and the lower step surface on the second step, parallel to the top surface of the upper cover plate 14, serves as a support surface. The glass plate 16 is placed on the support surface. A circular pressure plate 17 is also installed on the top surface of the upper cover plate 14. The pressure plate 17 presses and fixes one edge of the glass plate 16. A third sealing ring groove is formed on the bottom surface of the pressure plate 17, in which a third sealing ring is placed. The third sealing ring is located between the pressure plate 17 and the upper cover plate 14. A fourth sealing ring is also provided between the pressure plate 17 and the glass plate 16. Each sealing ring is, for example, a silicone gasket. The specific structure and installation of the through hole 142, pressure plate 17, and glass plate 16 on the upper cover plate 14 can be found in the prior art.

[0033] The drug-carrying platform 4 includes a platform 41 and a drug seat 42. The platform 41 is fixed to the top surface of the lower cover plate 15, and the drug seat 42 is detachably installed on the platform 41. The top surface of the drug seat 42 is recessed downward to form a drug loading groove 423 with a circular cross-section.

[0034] Specifically, such as Figure 5 As shown, the platform 41 includes a first circular plate 411 and a first cylinder 412 vertically fixed to the top surface of the first circular plate 411. The first cylinder 412 and the first circular plate 411 are coaxial, and the diameter of the first cylinder 412 is smaller than the diameter of the first circular plate 411. The first cylinder 412 and the first circular plate 411 are integrally formed, for example. The first circular plate 411 is installed on the top surface of the lower cover plate 15. For example, a ring of mounting holes is evenly distributed around the first cylinder 412 through the top and bottom of the first circular plate 411. Corresponding screw holes are provided on the top surface of the lower cover plate 15. The first circular plate 411 is fastened to the top surface of the lower cover plate 15 with screws. A recessed mounting groove 413 with a circular cross-section is provided along the axis on the top surface of the first cylinder 412.

[0035] like Figure 6As shown, the propellant holder 42 includes a second circular plate 421 and a second cylinder 422 vertically fixed to the bottom surface of the second circular plate 421. The second cylinder 422 and the second circular plate 421 are coaxial, and the diameter of the second cylinder 422 is smaller than the diameter of the second circular plate 421. For example, the second cylinder 422 and the second circular plate 421 are integrally formed. The diameter of the second cylinder 422 is slightly smaller than the diameter of the mounting groove 413. The second cylinder 422 is inserted into the mounting groove 413 to ensure coaxiality. The second circular plate 421 is installed and fixed on the top surface of the first cylinder 412. For example, a ring of mounting holes is evenly distributed around the second cylinder 422 through the second circular plate 421. Corresponding screw holes are opened on the top surface of the first cylinder 412. The second circular plate 421 is fastened to the top surface of the first cylinder 412 with screws. The propellant loading groove 423 is opened on the top surface of the second circular plate 421, and the axis of the propellant loading groove 423 is coaxial with the central axis of the combustion chamber 1.

[0036] The rotation and axial runout of the propellant holder 42 and the stage 41 are restricted by screws, and the coaxiality is ensured by the second cylinder 422 of the propellant holder 42 being inserted into the mounting groove 413 of the stage 41, thereby reducing the error caused by different ignition positions.

[0037] A glass viewing window 131 and an air extraction port 132 for extracting air from the combustion chamber 1 are provided on the chamber wall 13.

[0038] The optical measurement assembly 2 includes a high-speed CCD camera for capturing and storing data, a fiber optic spectrometer for measuring flame temperature, a photoresistor sensor for measuring ignition delay time, and a flame sensor. The optical measurement assembly 2 measures combustion parameters within the combustion chamber 1 via a glass window 131. For example, a bracket is installed on the chamber wall 13 where the glass window 131 is located, and the CCD camera, fiber optic spectrometer, photoresistor sensor, and flame sensor are mounted on the bracket.

[0039] The laser 3 includes a laser generator and an incident light path for guiding the laser emitted by the laser generator. The laser passes through the incident light path and the glass plate 16 to reach the charge tank 423.

[0040] The measurement method using the above-mentioned solid propellant low-pressure combustion measurement device includes the following steps: 1) Pre-filling the solid propellant into the charging slot 423 of the propellant holder 42; 2) Removing the lower cover plate 15, installing the propellant holder 42 on the platform 41 on the lower cover plate 15, installing the lower cover plate 15, using an external vacuum pump to connect the vacuum pipeline and connect it to the evacuation port 132 to pressurize the combustion chamber 1 to a predetermined pressure; 3) Using the laser 3 to emit a laser to ignite the solid propellant in the charging slot 423 in the combustion chamber 1, and simultaneously using the optical measurement component 2 to align with the charging slot 423 in the combustion chamber 1 to record the flame morphology, ignition delay time, flame temperature, and metal particle agglomeration phenomenon during the combustion process.

[0041] Unless otherwise specified, all technologies mentioned above refer to existing technologies.

[0042] Based on the above-described preferred embodiments of the present invention, and through the foregoing description, those skilled in the art can make various changes and modifications without departing from the inventive concept. The technical scope of this invention is not limited to the contents of the specification.

Claims

1. A solid propellant low pressure combustion measurement device, characterized by, The application relates to a combustion chamber (1) comprising a square box body formed by a top plate (11), a bottom plate (12) and a box wall (13), an optical measurement assembly (2) located outside the combustion chamber (1) and a laser (3) located above the combustion chamber (1), wherein the combustion chamber (1) is provided with a drug loading pedestal (4) inside; Step holes penetrating from top to bottom are formed in the middle of the top plate (11) and the bottom plate (12), and an upper cover plate (14) and a lower cover plate (15) are detachably installed in the step holes, respectively; the upper cover plate (14) and the lower cover plate (15) are step shafts, are used in cooperation with the step holes of the top plate (11) and the step holes of the bottom plate (12) respectively, and seal the step holes of the top plate (11) and the step holes of the bottom plate (12) respectively; A through hole (142) penetrating from top to bottom is formed in the middle of the upper cover plate (14), and a glass plate (16) is installed in the through hole (142) to seal the through hole (142); The drug loading pedestal (4) comprises a loading table (41) and a drug seat (42), the loading table (41) is fixed to the top surface of the lower cover plate (15), and the drug seat (42) is detachably installed on the loading table (41); the top surface of the drug seat (42) is concave downward to form a drug loading groove (423); A glass window (131) and an air extraction interface (132) for extracting air in the combustion chamber (1) are arranged on the box wall (13); The optical measurement assembly (2) comprises a high-speed CCD camera, a fiber-optic spectrometer, a photoresistor sensor and a flame sensor, and measures the combustion parameters in the combustion chamber (1) through the glass window (131); The laser (3) comprises a laser generator and an incident light path for guiding the laser emitted by the laser generator, and the laser reaches the drug loading groove (423) through the incident light path and the glass plate (16); The hole diameter of the step hole of the top plate (11) gradually decreases from top to bottom, the hole wall of the step hole has three steps, a groove is formed at the connection position between the tread and the kick of the second step to form a first sealing ring groove, the step hole structure of the bottom plate (12) is symmetrical to the step hole structure of the top plate (11); the step of the step shaft of the upper cover plate (14) has three steps, a groove is formed at the connection position between the tread and the kick of the second step to form a second sealing ring groove (141), the step shaft structure of the lower cover plate (15) is symmetrical to the step shaft structure of the upper cover plate (14), and a first sealing ring (18) and a second sealing ring (19) are respectively arranged in the first sealing ring groove and the second sealing ring groove (141); a supporting leg (121) is arranged at the bottom of the bottom plate (12).

2. The solid propellant low-pressure combustion measurement device of claim 1, wherein The through hole (142) on the upper cover plate (14) is a stepped hole, the hole wall step of the stepped hole is a two-step, the lower step surface parallel to the top surface of the upper cover plate (14) on the two-step is a support surface, and the glass plate (16) is placed on the support surface; a ring-shaped pressing plate (17) is also installed on the top surface of the upper cover plate (14), the pressing plate (17) tightly fixes one edge of the glass plate (16), a third sealing ring groove is formed in the bottom surface of the pressing plate (17), a third sealing ring is placed in the third sealing ring groove, and the third sealing ring is located between the pressing plate (17) and the upper cover plate (14); a fourth sealing ring is also arranged between the pressing plate (17) and the glass plate (16).

3. The solid propellant low-pressure combustion measurement apparatus according to claim 2, characterized by The carrier (41) comprises a first circular plate (411) and a first cylinder (412) vertically fixed on the top surface of the first circular plate (411), the first cylinder (412) and the first circular plate (411) are coaxial, and the diameter of the first cylinder (412) is smaller than that of the first circular plate (411); the first circular plate (411) is installed on the top surface of the lower cover plate (15), and the top surface of the first cylinder (412) is provided with a concave installation groove (413).

4. The solid propellant low-pressure combustion measurement apparatus according to claim 3, characterized by The medicine seat (42) comprises a second circular plate (421) and a second cylinder (422) vertically fixed on the bottom surface of the second circular plate (421), the second cylinder (422) and the second circular plate (421) are coaxial, and the diameter of the second cylinder (422) is smaller than that of the second circular plate (421); the second cylinder (422) is inserted into the installation groove (413), and the second circular plate (421) is fixedly installed on the top surface of the first cylinder (412); and the medicine groove (423) is formed in the top surface of the second circular plate (421).

5. A measuring method using the solid propellant low-pressure combustion measuring apparatus according to any one of claims 1 to 4, characterized by, The method comprises the following steps: 1) The solid propellant is pre-filled in the medicine groove (423) of the medicine seat (42); 2) The lower cover plate (15) is disassembled, the medicine seat (42) is installed on the carrier (41) of the lower cover plate (15), the lower cover plate (15) is installed, and the vacuum pump is used to draw the pressure in the combustion chamber (1) to a predetermined pressure; 3) the laser (3) is used to emit laser to ignite the solid propellant in the medicine groove (423) in the combustion chamber (1), and the optical measurement assembly (2) is used to record the flame morphology, ignition delay time, flame temperature and metal particle agglomeration phenomenon of the combustion process.

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