Performance testing device and method for segmented igniter of solid orbit control engine

Abstract

The present application relates to the technical field of performance test of solid attitude and orbit control engine igniter, and particularly relates to a segmented igniter performance test device and method for solid attitude and orbit control engine, which mainly consists of a segmented igniter and a volume-adjustable simulated combustion chamber. The igniter is designed as multiple segmented structures, and the length of the igniter is adjusted by adding an intermediate connecting section, and each segment is connected by bolts. The nozzle device is designed as a detachable structure, and the nozzle device or cage device can be freely replaced. The segmented igniter and the volume-adjustable simulated combustion chamber are connected by threads, the piston and the rear end cover of the simulated combustion chamber are connected by threads to adjust the moving distance, and a locking device is arranged on the piston rod to prevent the piston from moving during the test. The present application can realize performance tests of different igniter charges, different nozzle devices and different initial volumes of the combustion chamber, and lays a foundation for the design of solid attitude and orbit control engine igniter.

Description

Technical Field

[0001] This invention relates to the field of solid-propellant attitude control engine igniter performance testing technology, specifically to a segmented igniter performance testing device and method for solid-propellant attitude control engines. Background Technology

[0002] Solid rocket engines are the primary power source for weapons such as rockets and missiles, and their combustion performance directly determines the ballistic performance of the weapon. As the first ignition element of a rocket engine, the igniter must reliably ignite the propellant inside the engine, enabling the weapon to enter normal operation as intended. Therefore, the performance of the igniter plays a crucial role in the operational performance of the weapon. The complex and ever-changing battlefield environment places higher demands on the rapid response and stability of the rocket engine ignition process. Although there are relatively detailed design references for igniters, there are still weaknesses in their performance testing, particularly regarding the universality of testing for ignition propellant type, propellant mass, and ignition pressure. This study explores the relationship between different propellant types, propellant quantities, and ignition pressures and changes in combustion chamber volume, providing a basis for rocket engine igniter design.

[0003] A Chinese patent with publication number CN116378857A discloses a rocket engine simulation test device and method. This patent mainly aims to change the volume of the combustion chamber by adjusting the volume blocks inside the combustion chamber, simulating the ignition closed-circuit test of rocket engines with different initial cavity volumes. However, although this patent can effectively adjust the initial volume of the combustion chamber, it fails to efficiently explore the relationship between the propellant quantity and type and the change in the initial volume of the combustion chamber. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention proposes a segmented igniter performance testing device and method for solid rocket motors, solving the problem that while existing technologies use different volume blocks to adjust the initial volume of the combustion chamber, although simple and effective, they require the pre-customization of a large number of volume blocks, resulting in redundancy. This invention enables performance testing of different ignition propellant types, propellant quantities, and ignition pressures.

[0005] To address the aforementioned technical problems, one objective of this invention is to provide a performance testing device and method for a segmented igniter used in a solid rocket motor, comprising a segmented igniter and a volume-adjustable simulated combustion chamber device. This simulated combustion chamber device consists of an ignition tube, an ignition tube pressure screw, a pressure sensor, a front section of the igniter combustion chamber housing, a propellant support ring, ignition propellant, an igniter combustion chamber connecting section, a rear section of the igniter combustion chamber housing, a propellant baffle ring, an igniter nozzle section, a simulated combustion chamber housing, a piston, a simulated combustion chamber rear end cover, a locking device, a nozzle pressure screw, a nozzle, and a plug. The ignition tube is located at the front section of the igniter combustion chamber housing and is tightened by the ignition tube clamping screw; The igniter combustion chamber is composed of a front section of the igniter combustion chamber shell, a connecting section of the igniter combustion chamber, and a rear section of the igniter combustion chamber shell, which are connected by bolts. The front section of the igniter combustion chamber shell is designed with a pressure measuring seat for connecting a pressure sensor. The combustion chamber of the igniter is limited by a propellant support ring and a propellant retaining ring to prevent the propellant from moving. The volume-adjustable simulated combustion chamber consists of a simulated combustion chamber shell, a piston, and a simulated combustion chamber rear end cover, wherein the piston and the simulated combustion chamber rear end cover are designed with mutually cooperating trapezoidal threads. The trapezoidal thread of the locking device is adapted to the thread of the piston. After the combustion chamber volume is adjusted to the test position, the piston is fastened by the locking device cooperating with the rear end cover of the simulated combustion chamber. The nozzle plug is bonded to the nozzle expansion section, and the nozzle is fastened by the nozzle clamp screw.

[0006] Furthermore, the igniter nozzle section is a detachable structure, allowing for the replacement of different nozzle sections or basket-type devices to complete performance tests of different types of ignition devices.

[0007] Furthermore, by bolting together multiple igniter combustion chamber connection sections, it is possible to test different ignition propellant lengths and amounts.

[0008] Furthermore, the simulated combustion chamber housing is also equipped with a pneumatic valve connection port. If the nozzle plug is not opened, the pressure inside the device can be released through the pneumatic valve.

[0009] Furthermore, the piston has a scale engraved on its trapezoidal thread after the combustion chamber volume is calibrated, which facilitates precise volume control.

[0010] Based on the same concept, this invention also proposes a method for testing the performance of a segmented igniter for a solid rocket motor, comprising the following steps: Step 1: Connect the front section of the igniter combustion chamber housing to the igniter combustion chamber connecting section with bolts, and screw the pressure sensor into the pressure measuring seat in the front section of the igniter combustion chamber housing; Step 2: Place the propellant support ring and ignition charge into the front section of the assembled igniter combustion chamber housing and the connection section between the igniter combustion chamber and the igniter combustion chamber. Place the propellant retaining ring into the rear section of the igniter combustion chamber housing. Assemble the segmented igniter housing with bolts. Then connect the igniter nozzle section to the rear section of the igniter combustion chamber housing to complete the assembly of the segmented igniter. Step 3: Connect the piston to the rear end cover of the simulated combustion chamber via threads, and then screw the locking device into the piston rod; Step 4: Connect the simulated combustion chamber housing to the simulated combustion chamber rear end cover using bolts; Step 5: Install pneumatic valves and pressure sensors on the simulated combustion chamber housing; Step 6: Select nozzle plugs of different thicknesses and glue them to the nozzle expansion section, then tighten the nozzle with nozzle screws; Step 7: Use the piston drive rod to drive the piston to the specified test volume position; Step 8: Insert the ignition tube into the front section of the ignition chamber housing and tighten it using the ignition tube clamping screw; Step 9: Ignite the ignition tube and record the pressure-time curve of the igniter and the simulated combustion chamber; if the nozzle plug is not open, release the pressure through the pneumatic valve; Step 10: Change the type, length, and nozzle type of the ignition propellant, and repeat steps 1 to 9 to complete the igniter performance test.

[0011] The above-described one or more technical solutions of the present invention have at least one or more of the following technical effects: 1) The igniter is designed with a segmented combustion chamber shell. Different numbers of igniter combustion chamber shell connecting segments are connected by bolts to realize igniter performance testing for different types of ignition propellants, ignition propellant sizes, ignition propellant quantities, etc.

[0012] 2) The igniter nozzle is designed with a movable connection structure, which allows for the replacement of the basket-type device with nozzle devices of different areas, and the influence of the basket-type device and nozzle device on the performance of the igniter can be investigated.

[0013] 3) The piston assembly inside the simulated combustion chamber is designed with a matching trapezoidal thread on the piston rod and the rear end cover of the simulated combustion chamber. The initial volume of the combustion chamber is adjusted by the movement of the piston to simulate the igniter performance test under different engine initial volume conditions.

[0014] 4) The combustion chamber volume is calibrated by dividing the piston rod trapezoidal thread with the rear end cover of the combustion chamber shell as a reference, so as to achieve precise control of the combustion chamber volume.

[0015] 5) A piston drive rod is designed at the tail of the piston rod to facilitate the movement of the piston; and a locking device is designed on the piston screw. When the piston moves to the corresponding volume, the piston is fixed by the locking device to prevent the piston from moving during the ignition pressurization process and affecting the test results.

[0016] 6) Replace the nozzle screw, nozzle, and nozzle plug with a plug. By monitoring the pressure-time curves in each combustion chamber, obtain the ignition pressure and pressure rise rate inside the igniter and at different initial combustion chamber volumes. Furthermore, by bonding plugs of different thicknesses to the nozzle expansion section, the opening pressure of the plug can be obtained, providing a reference for plug bonding strength testing. If the plug is not bonded, adjusting the propellant mass, length, and nozzle throat diameter can obtain the igniter's continuous energy output time. Attached Figure Description

[0017] Figure 1 This invention is a segmented igniter performance testing device; Figure 2 : Front sectional view, right view and top view of the igniter combustion chamber housing; Figure 3 : Main sectional view and left view of the igniter combustion chamber connection section; Figure 4 : Front sectional view and right view of the rear section of the igniter combustion chamber housing; Figure 5 Simulated combustion chamber shell: main sectional view, right view, and left view; Figure 6 : The main sectional view and right view of the simulated combustion chamber rear end cover; Figure 7 Front and right views of the piston; Figure 8 : Main sectional view and right view of the locking device; Figure 9 Schematic diagram of the piston drive rod; Wherein: 1-Ignition tube, 2-Ignition tube pressure screw, 3-Pressure sensor, 4-Front section of igniter combustion chamber housing, 5-Propellant support ring, 6-Ignition charge, 7-Ignition chamber connection section, 8-Rear section of igniter combustion chamber housing, 9-Propellant baffle ring, 10-Ignition nozzle section, 11-Simulated combustion chamber housing, 12-Piston, 13-Rear end cover of simulated combustion chamber, 14-Locking device, 15-Piston drive rod, 16-Pneumatic valve, 17-Nozzle pressure screw, 18-Nozzle, 19-Plug. Detailed Implementation

[0018] This invention discloses a segmented igniter performance testing simulation device and method. It is used to investigate the variation of different ignition propellant types, propellant mass, and ignition pressure with the initial volume of the combustion chamber during igniter performance testing, providing a theoretical basis for solid rocket engine igniter design. The testing device mainly consists of a segmented igniter and an adjustable-volume simulated combustion chamber. The igniter is designed with multiple segments, and its length is adjusted by adding intermediate connecting sections. Bolts are used to connect the segments. The nozzle device is designed as a detachable structure, allowing for free replacement of the nozzle device or a cage-type device. The segmented igniter and the adjustable-volume simulated combustion chamber are connected by threads. The piston and the rear end cover of the simulated combustion chamber are adjusted by threads, and a locking device is installed on the piston rod to prevent piston movement during the test. The present invention proposes a segmented igniter testing device and method for solid rocket motor attitude and orbit control, which can realize performance testing of igniters with different propellant amounts, different nozzle devices and different initial combustion chamber volumes, laying the foundation for solid rocket motor igniter design.

[0019] The technical solutions of the present invention will be clearly and completely described below with reference to the embodiments and accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments obtained. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention are within the scope of protection of the present invention.

[0020] Reference Figure 1 As shown, the present invention provides a segmented igniter performance testing simulation device, comprising a segmented igniter and a volume adjustable simulated combustion chamber device, mainly composed of an ignition tube 1, an ignition tube pressure screw 2, a pressure sensor 3, a front section of the igniter combustion chamber shell 4, a propellant support ring 5, an ignition propellant 6, an igniter combustion chamber connecting section 7, a rear section of the igniter combustion chamber shell 8, a propellant baffle ring 9, an igniter nozzle section 10, a simulated combustion chamber shell 11, a piston 12, a simulated combustion chamber rear end cover 13, a locking device 14, a piston drive rod 15, a pneumatic valve 16, a nozzle pressure screw 17, a nozzle 18, and a plug 19.

[0021] Reference Figure 2 As shown, the ignition tube is inserted into the front section of the igniter combustion chamber housing and secured with a pressure screw. The pressure sensor is connected to the front section of the igniter combustion chamber housing via a thread.

[0022] For reference Figure 3 As shown, the igniter combustion chamber connecting section is connected to the front section of the igniter combustion chamber housing by bolts. The propellant support ring and the ignition charge are sequentially placed into the assembly of the front section of the igniter combustion chamber housing and the igniter combustion chamber connecting section. The propellant retaining ring is placed into the rear section of the igniter combustion chamber housing (e.g., Figure 4 (As shown), and is connected to the assembly of the front section of the igniter combustion chamber housing and the igniter combustion chamber connecting section by bolts. The igniter nozzle section is connected to the rear section of the igniter combustion chamber housing by threads.

[0023] Reference Figure 5 As shown, the simulated combustion chamber housing is designed with a pressure sensor interface, a pneumatic valve interface, and a nozzle interface. The segmented igniter is connected to the simulated combustion chamber housing via threads. The pressure sensor is also connected to the simulated combustion chamber housing via threads.

[0024] Reference Figure 6 As shown, the rear end cover of the simulated combustion chamber is designed with a piston guide section, which is engaged with the piston through a trapezoidal thread.

[0025] Reference Figure 7 As shown, the piston has a concave groove at the contact end with the simulated combustion chamber housing to accommodate an O-ring seal, which provides a sealing function during the test.

[0026] Reference Figure 8 As shown, the locking device is used in conjunction with the piston via a trapezoidal thread. After the volume of the simulated combustion chamber is adjusted to the test position by the piston, the locking device is used in conjunction with the rear end cover of the simulated combustion chamber to fix the piston and ensure that the piston does not move during the test.

[0027] Reference Figure 9 As shown, the piston drive rod is designed with a square groove structure, which cooperates with a square protrusion structure on one side of the piston to complete the movement of the piston in the simulated combustion chamber.

[0028] The aforementioned performance simulation test method for a segmented igniter includes the following steps: Step 1: First, connect the front section 4 of the igniter combustion chamber housing to the igniter combustion chamber connecting section 7 with bolts, and screw the pressure sensor 3 into the pressure measuring seat of the front section 4 of the igniter combustion chamber housing; Step 2: Place the propellant support ring 5 and the ignition charge 6 sequentially into the front section 4 and the connecting section 7 of the assembled igniter combustion chamber housing. Place the propellant retaining ring 9 into the rear section 8 of the igniter combustion chamber housing. Assemble the segmented igniter housing using bolts. Then, select different nozzle devices or basket-type devices and connect them to the rear section 8 of the igniter combustion chamber housing to complete the assembly of the segmented igniter. Step 3: Connect the piston 12 to the rear end cover 13 of the simulated combustion chamber via threads, and then screw the locking device 14 into the piston rod 12; Step 4: Connect the simulated combustion chamber housing 11 to the simulated combustion chamber rear end cover 13 using bolts; Step 5: Install the pneumatic valve 16 and pressure sensor 3 on the simulated combustion chamber housing 11; Step 6: Select nozzle plugs 19 of different thicknesses and glue them to the expansion section of nozzle 18, then tighten nozzle 18 with nozzle screw 17; if testing the continuous output time of the igniter, the nozzle plugs do not need to be glued; otherwise, if testing the pressure rise rate and ignition pressure of the igniter at the specified initial volume of the combustion chamber, the nozzle screw 17, nozzle 18, and plug 19 can be replaced with plugs. Step 7: Use piston drive rod 15 to drive piston 12 to the specified test volume position; Step 8: Insert the ignition tube 1 into the front section 4 of the igniter combustion chamber housing and tighten it using the ignition tube clamping screw 2; Step 9: Ignite the ignition tube 1 and record the pressure-time curve of the igniter and the simulated combustion chamber; if the nozzle plug 19 is not open, depressurize through the pneumatic valve 16; Step 10: Change the type, length, and nozzle type of the ignition propellant, and repeat steps 1 to 9 to complete the igniter performance test.

[0029] Example 1: Ignition boost rate and ignition pressure test.

[0030] First, connect the front section of the igniter combustion chamber housing to the igniter combustion chamber connecting section using M8 bolts. Then, screw the 0~10MPa pressure sensor into the pressure measuring seat of the front section of the igniter combustion chamber housing. Place the propellant support ring and ignition charge sequentially into the assembled front section of the igniter combustion chamber housing and the igniter combustion chamber connecting section. Place the propellant retaining ring into the rear section of the igniter combustion chamber housing, and then assemble the rear section of the igniter combustion chamber housing using M8 bolts. Based on the actual operating conditions of the igniter design, select a nozzle area of ​​314mm². 2 The nozzle device is connected to the rear section of the igniter combustion chamber housing via threads.

[0031] Connect the piston to the rear end cover of the simulated combustion chamber via threads, then screw the locking device into the piston from the small end. Connect the assembled rear end cover of the simulated combustion chamber to the simulated combustion chamber housing using M8 bolts. Install the pneumatic valve 16 and a pressure sensor with a range of 0~10MPa on the simulated combustion chamber housing. Use the piston drive rod to move the piston to the required 40ml volume position for the test, then tighten the locking device towards the rear end cover side of the simulated combustion chamber to fix the piston and prevent it from moving during the test. Connect the plug to the nozzle interface via threads, ensuring the inner side of the plug is flush with the inner wall of the simulated combustion chamber.

[0032] The ignition tube is installed into the front section of the igniter combustion chamber housing and tightened using the ignition tube clamping screw. The ignition tube is then energized, and pressure sensor data from the front section of the igniter combustion chamber housing and the simulated combustion chamber housing are collected. The ignition pressure and pressure rise rate in the igniter and simulated combustion chamber are calculated from the pressure curves. Combined with actual ignition requirements, it can be determined whether the propellant dosage is appropriate and adjustments can be made.

[0033] Example 2: Igniter energy output duration test.

[0034] First, connect the front section of the igniter combustion chamber housing to the igniter combustion chamber connecting section using M8 bolts. Then, screw the 0~10MPa pressure sensor into the pressure measuring seat of the front section of the igniter combustion chamber housing. Place the propellant support ring and ignition charge sequentially into the assembled front section of the igniter combustion chamber housing and the igniter combustion chamber connecting section. Place the propellant retaining ring into the rear section of the igniter combustion chamber housing, and then assemble the rear section of the igniter combustion chamber housing using M8 bolts. Based on the actual operating conditions of the igniter design, select a nozzle area of ​​314mm². 2 The nozzle device is connected to the rear section of the igniter combustion chamber housing via threads.

[0035] Connect the piston to the rear end cover of the simulated combustion chamber via threads, then screw the locking device into the piston from the small end. Connect the assembled rear end cover of the simulated combustion chamber to the simulated combustion chamber housing using M8 bolts. Install the pneumatic valve 16 and a pressure sensor with a range of 0~10MPa on the simulated combustion chamber housing. Use the piston drive rod to move the piston to the required 40ml volume position for the test, then tighten the locking device towards the rear end cover side of the simulated combustion chamber to fix the piston and prevent it from moving during the test. Secure the nozzle to the nozzle interface of the simulated combustion chamber housing using the nozzle clamping screw.

[0036] The ignition tube is installed into the front section of the igniter combustion chamber housing and tightened using the ignition tube clamping screw. The ignition tube is then energized, and pressure sensor data from both the front section of the igniter combustion chamber housing and the simulated combustion chamber housing are collected. The ignition pressure in the igniter is obtained from the pressure curves, and the energy output duration of the current propellant charge is calculated using the pressure curve collected from the simulated combustion chamber housing. The propellant charge is then adjusted based on this result.

[0037] Example 3: Nozzle plug opening test.

[0038] First, connect the front section of the igniter combustion chamber housing to the igniter combustion chamber connecting section using M8 bolts. Then, screw the 0~10MPa pressure sensor into the pressure measuring seat of the front section of the igniter combustion chamber housing. Place the propellant support ring and ignition charge sequentially into the assembled front section of the igniter combustion chamber housing and the igniter combustion chamber connecting section. Place the propellant retaining ring into the rear section of the igniter combustion chamber housing, and then assemble the rear section of the igniter combustion chamber housing using M8 bolts. Based on the actual operating conditions of the igniter design, select a nozzle area of ​​314mm². 2 The nozzle device is connected to the rear section of the igniter combustion chamber housing via threads.

[0039] Connect the piston to the rear end cover of the simulated combustion chamber via threads, then screw the locking device into the piston from the small end. Connect the assembled rear end cover of the simulated combustion chamber to the simulated combustion chamber housing using M8 bolts. Install the pneumatic valve 16 and a pressure sensor with a range of 0~10MPa on the simulated combustion chamber housing. Use the piston drive rod to move the piston to the required 40ml volume position for the test, then tighten the locking device towards the rear end cover of the simulated combustion chamber to fix the piston and prevent it from moving during the test. Secure the nozzle to the nozzle interface of the simulated combustion chamber housing using the nozzle clamp screw. Select nozzle plugs of different thicknesses, calculate the bonding area on the side of the nozzle plug, and bond the nozzle plug to the nozzle outlet section.

[0040] The ignition tube is installed in the front section of the igniter combustion chamber housing and tightened using the ignition tube clamping screw. The ignition tube is energized, and pressure sensor data is collected from both the front section of the igniter combustion chamber housing and the simulated combustion chamber housing. Pressure curves from the two sensors are obtained, and the opening status of the nozzle plug is observed. These curves are then compared and analyzed with the pressure data and the bonding area. By changing the propellant quantity and the bonding area, a matching test study on the nozzle opening pressure and bonding area is conducted. If the plug does not open, the pressure inside the combustion chamber is released using a pneumatic valve.

[0041] Obviously, those skilled in the art can make various modifications and variations to the embodiments of the present invention without departing from the spirit and scope of the embodiments of the present invention. Thus, if these modifications and variations to the embodiments of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention also intends to include these modifications and variations.

Claims

1. A performance testing device for a segmented igniter used in a solid-propellant attitude control engine, comprising a segmented igniter and a volume-adjustable simulated combustion chamber device, characterized in that: The simulation device consists of an ignition tube (1), an ignition tube pressure screw (2), a pressure sensor (3), a front section of the igniter combustion chamber shell (4), a propellant support ring (5), an ignition charge (6), an igniter combustion chamber connecting section (7), a rear section of the igniter combustion chamber shell (8), a propellant baffle ring (9), an igniter nozzle section (10), a simulated combustion chamber shell (11), a piston (12), a simulated combustion chamber rear end cover (13), a locking device (14), a nozzle pressure screw (17), a nozzle (18), and a plug (19). The ignition tube (1) is placed in the front section (4) of the igniter combustion chamber housing and is tightened by the ignition tube clamping screw (2); The igniter combustion chamber is composed of a front section (4) of the igniter combustion chamber housing, a connecting section (7) of the igniter combustion chamber, and a rear section (8) of the igniter combustion chamber housing, which are connected by bolts. The front section (4) of the igniter combustion chamber housing is designed with a pressure measuring seat for connecting a pressure sensor (3). The combustion chamber of the igniter is limited by a propellant support ring (5) and a propellant retaining ring (9) to prevent the propellant (6) from moving. The volume-adjustable simulated combustion chamber consists of a simulated combustion chamber shell (11), a piston (12), and a simulated combustion chamber rear end cover (13), wherein the piston (12) and the simulated combustion chamber rear end cover (13) are designed with mutually cooperating trapezoidal threads; The trapezoidal thread of the locking device (14) is adapted to the thread of the piston (12). After the combustion chamber volume is adjusted to the test position, the piston (12) is fastened by the locking device (14) cooperating with the rear end cover (13) of the simulated combustion chamber. The nozzle plug (19) is bonded to the expansion section of the nozzle (18), and the nozzle (18) is fastened by the nozzle screw (17).

2. The performance testing device for a segmented igniter for a solid attitude control engine according to claim 1, characterized in that: The igniter nozzle section (10) is a detachable structure. Different nozzle sections or basket-type devices can be replaced to complete the performance test of different types of ignition devices.

3. The performance testing device for a segmented igniter for a solid attitude control engine according to claim 1, characterized in that, By connecting multiple igniter combustion chamber connection sections (7) with bolts, it is possible to test different ignition propellant lengths and ignition propellant quantities.

4. The performance testing device for a segmented igniter for a solid attitude control engine according to claim 1, characterized in that, The simulated combustion chamber housing (11) is also provided with a pneumatic valve (16) connection port. If the nozzle plug (19) is not opened, the pressure inside the device can be released through the pneumatic valve (16).

5. The performance testing device for a segmented igniter for a solid attitude control engine according to claim 1, characterized in that: The piston (12) has a scale engraved on its trapezoidal thread after the combustion chamber volume is calibrated, which facilitates precise volume control.

6. The performance testing device for a segmented igniter for a solid attitude control engine according to claim 1, characterized in that: The piston has a concave groove at the contact end with the simulated combustion chamber housing to accommodate an O-ring seal, which provides a sealing function during testing.

7. The performance testing device for a segmented igniter for a solid attitude control engine according to claim 6, characterized in that: The rear end cover of the simulated combustion chamber is provided with a piston guide section, which is engaged with the piston through a trapezoidal thread.

8. The performance testing device for a segmented igniter for a solid attitude control engine according to claim 1, characterized in that: The piston drive rod is designed with a square groove structure, which cooperates with a square protrusion structure on one side of the piston to complete the movement of the piston in the simulated combustion chamber.

9. The test method for the performance testing device of the segmented igniter for a solid attitude control engine according to any one of claims 1-8, characterized in that, Includes the following steps: Step 1: Connect the front section (4) of the igniter combustion chamber housing to the igniter combustion chamber connecting section (7) with bolts, and screw the pressure sensor (3) into the pressure measuring seat of the front section (4) of the igniter combustion chamber housing; Step 2: Place the propellant support ring (5) and ignition powder (6) into the front section (4) and the connecting section (7) of the assembled igniter combustion chamber housing, and place the propellant retaining ring (9) into the rear section (8) of the igniter combustion chamber housing. Assemble the segmented igniter housing with bolts, and then connect the igniter nozzle section (10) to the rear section (8) of the igniter combustion chamber housing to complete the assembly of the segmented igniter. Step 3: Connect the piston (12) to the rear end cover (13) of the simulated combustion chamber by thread, and then screw the locking device (14) into the piston (12) rod; Step 4: Connect the simulated combustion chamber housing (11) to the simulated combustion chamber rear end cover (13) using bolts; Step 5: Install the pneumatic valve (16) and pressure sensor (3) on the simulated combustion chamber housing (11); Step 6: Select nozzle plugs (19) of different thicknesses and glue them to the expansion section of the nozzle (18), and then tighten the nozzle (18) with the nozzle screw (17); Step 7: Use the piston drive rod (15) to drive the piston (12) to move to the test specified volume position; Step 8: Insert the ignition tube (1) into the front section (4) of the igniter combustion chamber housing and tighten it with the ignition tube clamping screw (2); Step 9: Ignite the ignition tube (1) and record the pressure-time curve of the igniter and the simulated combustion chamber; if the nozzle plug (19) is not open, depressurize through the pneumatic valve (16); Step 10: Change the type, length, and nozzle type of the ignition propellant, and repeat steps 1 to 9 to complete the igniter performance test.

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