Centrifugal overload ignition test device and method for special-shaped solid rocket motor

Abstract

The present invention discloses a centrifugal overload ignition test device and method for a special-shaped solid rocket engine, which belongs to the technical field of solid rocket engines. The centrifugal overload ignition test device includes a centrifuge assembly, two fixed assemblies and two pressure test assemblies; each fixed assembly includes a fixing frame, a positioning plate and a cage frame, and the fixing frame is a columnar structure; each pressure test assembly includes a connecting joint, a flexible pressure-inducing pipe, a pressure sensor and a support, and the flexible pressure-inducing pipe passes through the corresponding fixing frame and cage frame. The centrifugal overload ignition test device for a special-shaped solid rocket engine provided by the embodiment of the present invention can not only realize a dynamic incremental centrifugal overload ignition test by generating thrust by itself to drive the centrifuge to rotate, but also accurately measure the pressure of the combustion chamber in the special-shaped solid rocket engine, and the flexible pressure-inducing pipe can be manually bent and deformed according to the structure of the fixing frame and the cage frame and then passed through.

Description

Technical Field

[0001] The present invention belongs to the technical field of solid rocket engines, and in particular relates to a centrifugal overload ignition test device and method for a special-shaped solid rocket engine. Background Art

[0002] Centrifugal overload ignition testing plays a crucial role in the development of solid rocket engines. To simulate the flight overload conditions of solid rocket engines, various overload tests are conducted, providing comprehensive validation data for solid rocket engine development.

[0003] One of the main functions of a certain type of solid rocket engine is to provide tangential roll control torque to the weapon system. When used in pairs, the weapon system can be rotated to rotate at a certain speed around the flight direction during flight, generating a gyroscopic effect to improve flight stability and hit accuracy. Due to the limitations of the internal space of the weapon system, the solid rocket engine is designed into an "L-shaped" special structure (see Figure 1 , including pipelines and shells, with fuel and igniter in the shell. The pipeline is L-shaped and connected to one end of the shell, and finally the high-temperature and high-pressure gas after combustion is discharged from the side), which is a special-shaped solid rocket engine.

[0004] However, the existing centrifugal overload ignition test equipment and methods are not suitable for the dynamic increasing centrifugal overload conditions generated by the roll control torque of the special-shaped solid rocket engine, and are unable to accurately measure the pressure inside the upper shell of the special-shaped solid rocket engine during the test. Summary of the Invention

[0005] In response to the above-mentioned defects or improvement needs of the prior art, the present invention provides a centrifugal overload ignition test device and method for a special-shaped solid rocket engine, the purpose of which is not only to enable two special-shaped solid rocket engines to be reliably installed in a completely simulated real layout, thereby generating thrust by the centrifuge to drive the rotation to achieve a dynamic incremental centrifugal overload ignition test, but also to accurately measure the pressure inside the upper casing of the special-shaped solid rocket engine.

[0006] To achieve the above objectives, in a first aspect, the present invention provides a centrifugal overload ignition test device for a special-shaped solid rocket engine, the centrifugal overload ignition test device comprising a centrifuge assembly, two fixing assemblies, and two pressure test assemblies;

[0007] The centrifuge assembly includes a centrifuge output shaft, a rotating arm, and a cable. The centrifuge output shaft is perpendicular to the rotating arm and is in transmission connection with the middle portion of the rotating arm. The cable is arranged on the centrifuge output shaft and the rotating arm, and is used to electrically connect to the special-shaped solid rocket engine.

[0008] The two fixing assemblies and the two pressure test assemblies are arranged in a 180° array along the axis of the centrifuge output shaft. Each of the fixing assemblies includes a fixing frame, a positioning plate and a cage frame. The fixing frame is a columnar structure and is used to circumferentially surround the upper shell of the special-shaped solid rocket engine. The positioning plate is fixed to the top of the fixing frame, and the positioning plate is provided with a avoidance hole for avoiding the upper pipeline of the special-shaped solid rocket engine and a plurality of mounting holes for connecting the upper shell of the special-shaped solid rocket engine. The fixing frame is inserted into the inner hole of the cage frame, and the positioning plate is connected to the top of the cage frame. The bottom of the cage frame is vertically fixed to one end of the rotating arm.

[0009] Each of the pressure testing assemblies includes a connecting joint, a flexible pressure-conducting tube, a pressure sensor and a support. The connecting joint, the flexible pressure-conducting tube and the pressure sensor are connected in sequence. The connecting joint is used to be inserted into the corresponding upper casing of the special-shaped solid rocket engine. The flexible pressure-conducting tube passes through the corresponding fixing frame and the cage frame. The support is located on the outer wall of the corresponding cage frame, and the pressure sensor is fixed on the corresponding support.

[0010] Optionally, the fixing frame includes two relatively arranged half brackets, each of the half brackets is an arc-shaped structure, the two half brackets are detachably connected, and the positioning plate is fixed to the top ends of the two half brackets.

[0011] Optionally, a clamp is fixedly provided at the bottom of each half bracket, the two clamps are detachably connected, the middle parts of the two half brackets are detachably connected by two oppositely arranged connecting clamps, and each half bracket is provided with a connecting plate on the side facing the positioning plate, and each connecting plate is parallel to the positioning plate and connected by bolts.

[0012] Optionally, the top of the cage frame has a connecting flange, the connecting flange is stacked below the positioning plate and connected by bolts, and the fixing frame passes through the connecting flange.

[0013] Optionally, each of the pressure testing assemblies further includes a first connector, which is fixed on the support, and the detection end of the pressure sensor is inserted into the first connector, the connecting joint includes a second connector and an adapter that are coaxially connected to each other, the first connector and the second connector are respectively connected to the two ends of the flexible pressure-leading tube, and the adapter is used to be inserted into the corresponding special-shaped solid rocket engine upper casing.

[0014] Optionally, the bottom of the cage frame has a bottom plate, and the outer peripheral wall of the bottom of the cage frame has a plurality of spaced connecting ribs, each of the connecting ribs is fixedly connected to the bottom plate, each of the bottom plates is fixed on the rotating arm, and two spaced adapters are inserted on the rotating arm, and each of the bottom plates is fixed on the corresponding adapter.

[0015] Optionally, the flexible pressure-inducing tube is formed by welding stainless steel, and both ends of the flexible pressure-inducing tube are mechanical threaded interfaces.

[0016] Optionally, the flexible pressure-inducing tube has a specification of Φ5mm×Φ3mm×200mm.

[0017] Optionally, the cable corresponds to an RC filter circuit, and the matching capacitance of the RC filter circuit is 50nF and the resistance is 5kΩ.

[0018] In a second aspect, the present invention provides a centrifugal overload ignition test method for a special-shaped solid rocket motor. The centrifugal overload ignition test method is based on the centrifugal overload ignition test method described in the first aspect, and the centrifugal overload ignition test method includes:

[0019] Fix each dummy engine to the corresponding fixing assembly, and arrange the fixing assemblies in a 180-degree array at both ends of the rotating arm. Start the centrifuge according to the centrifugal dynamic overload value for each dummy engine, perform a no-load test, and check whether the ignition signal of the pyrotechnic device in the dummy engine, the zero-position output of the pressure sensor, and the centrifuge speed are normal;

[0020] The casing of each dummy engine is inflated to the designed working pressure, and the centrifuge is started according to the centrifugal dynamic overload value for each dummy engine to perform a load cold air simulation test to check whether the pressure sensor feedback, the ignition signal of the pyrotechnic device, and the centrifuge speed are normal;

[0021] The shaped solid rocket motor to be tested is fixed on the corresponding fixed assembly, and each of the fixed assemblies is arranged in a 180° array at both ends of the rotating arm. The centrifuge is first started at a small constant centrifugal overload value to balance the friction resistance generated during the rotation of the centrifuge assembly. Then the shaped solid rocket motor is ignited and drives the centrifuge to rotate for a formal test, and the real-time overload value of the shaped solid rocket motor and the pressure inside the casing when the shaped solid rocket motor is working are confirmed.

[0022] The above-mentioned improved technical features can be combined with each other as long as they do not conflict with each other.

[0023] In a centrifugal overload ignition test apparatus for a special-shaped solid rocket motor provided by an embodiment of the present invention, a cylindrical mounting bracket is configured to circumferentially surround the special-shaped solid rocket motor upper casing, thereby circumferentially securing the special-shaped solid rocket motor upper casing. Furthermore, a positioning plate is provided with multiple mounting holes for connecting the special-shaped solid rocket motor upper casing. Bolts and locating pins are inserted into the mounting holes to secure the casing and the positioning plate to the special-shaped solid rocket motor upper casing, thereby achieving axial fixation of the special-shaped solid rocket motor upper casing. Ultimately, each special-shaped solid rocket motor is securely and reliably fixed to the mounting assembly and rotating arm, ensuring stability during subsequent overload testing. Furthermore, the two mounting assemblies and two pressure test assemblies are arranged in a 180-degree array along the axis of the centrifuge output shaft, enabling the installation of two special-shaped solid rocket motors to fully simulate a real-world layout (the exhaust direction of each pipeline is arranged along the tangent direction of the rotating arm's rotation). After the two special-shaped solid rocket engines are ignited, they can generate thrust by themselves to drive the centrifuge output shaft to accelerate rotation. The rotation speed of the corresponding centrifuge is determined by the rotation of the centrifuge output shaft, and thus the load of the corresponding special-shaped solid rocket engine is calculated and determined. In this way, the dynamic incremental centrifugal overload ignition test of the special-shaped solid rocket engine can be realized to meet the dynamic incremental centrifugal overload working condition generated by the roll control torque of the special-shaped solid rocket engine.

[0024] On the other hand, the connecting joint, the flexible pressure-inducing pipe, and the pressure sensor are connected in sequence. The connecting joint is used to be inserted into the corresponding special-shaped solid rocket engine upper shell. The flexible pressure-inducing pipe passes through the corresponding fixing frame and cage frame. The support is located on the outer wall of the corresponding cage frame, and the pressure sensor is fixed on the corresponding support. Therefore, the gas generated after combustion in the shell is transmitted to the pressure sensor through the connecting joint and the flexible pressure-inducing pipe. The pressure sensor can accurately measure the air pressure in the shell, avoiding the risk of high temperature damage caused by directly placing the pressure sensor in the shell. In addition, the flexible pressure-inducing pipe can be manually bent and deformed according to the structure of the fixing frame and cage frame before passing through, making the overall structure compact.

[0025] That is to say, the centrifugal overload ignition test device for a special-shaped solid rocket engine provided by an embodiment of the present invention can not only enable two special-shaped solid rocket engines to be reliably installed by completely simulating the actual layout, thereby generating thrust by the centrifuge to drive the rotation to realize a dynamic incremental centrifugal overload ignition test, but also can accurately measure the pressure inside the upper shell of the special-shaped solid rocket engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 1 is a schematic structural diagram of a special-shaped solid rocket engine provided by an embodiment of the present invention;

[0027] Figure 2This is a schematic structural diagram of a centrifugal overload ignition test device for a special-shaped solid rocket motor provided by an embodiment of the present invention;

[0028] Figure 3 1 is a schematic structural diagram of a centrifuge assembly provided by an embodiment of the present invention;

[0029] Figure 4 is a schematic diagram of the arrangement of cables provided by an embodiment of the present invention;

[0030] Figure 5 is a structural diagram of a fixing assembly provided by an embodiment of the present invention;

[0031] Figure 6 1 is a schematic diagram of the assembly of the positioning plate and the fixing frame provided in an embodiment of the present invention;

[0032] Figure 7 is a schematic structural diagram of a positioning plate provided by an embodiment of the present invention;

[0033] Figure 8 is a structural diagram of a pressure testing assembly provided by an embodiment of the present invention;

[0034] Figure 9 is a structural schematic diagram of a fixing frame provided by an embodiment of the present invention;

[0035] Figure 10 1 is a schematic structural diagram of a cage frame provided by an embodiment of the present invention;

[0036] Figure 11 is a cross-sectional view of a flexible pressure-inducing tube provided in an embodiment of the present invention;

[0037] Figure 12 Schematic diagram of the principle of the RC filter circuit provided by an embodiment of the present invention;

[0038] Figure 13 This is a flow chart of a centrifugal overload ignition test method for a special-shaped solid rocket motor provided by an embodiment of the present invention.

[0039] In all the drawings, the same reference numerals represent the same technical features, specifically:

[0040] 1. Centrifuge assembly; 11. Centrifuge output shaft; 12. Rotating arm; 121. Adapter; 13. Cable; 131. Socket; 2. Fixing assembly; 21. Fixing frame; 211. Half bracket; 212. Clamp; 213. Connecting hoop; 214. Connecting plate; 22. Positioning plate; 221. Avoidance hole; 222. Mounting hole; 23. Cage frame; 231. Connecting flange; 232. Bottom plate; 24. Bolt; 3. Pressure test assembly; 31. Connecting joint; 311. Second connector; 312. Adapter; 32. Flexible pressure tube; 33. Pressure sensor; 34. Support; 35. First connector; 36. Sealing ring; 100. Shell; 200. Pipeline. DETAILED DESCRIPTION

[0041] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only intended to illustrate the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

[0042] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0043] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0044] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection; direct connection, or indirect connection through an intermediate medium; internal communication between two components, or interaction between two components, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0045] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0046] Example:

[0047] Figure 2 FIG. 1 is a structural diagram of a centrifugal overload ignition test device for a special-shaped solid rocket engine provided by an embodiment of the present invention. Figure 2 As shown, the centrifugal overload ignition test device includes a centrifuge assembly 1, two fixing assemblies 2 and two pressure test assemblies 3.

[0048] Figure 3 Schematic diagram of the structure of the centrifuge assembly provided by the embodiment of the present invention, such as Figure 3 As shown, the centrifuge assembly 1 includes a centrifuge output shaft 11, a rotating arm 12 and a cable 13. The centrifuge output shaft 11 is perpendicular to the rotating arm 12 and is in transmission connection with the middle of the rotating arm 12. The cable 13 is arranged on the centrifuge output shaft 11 and the rotating arm 12 (see FIG. Figure 4 ), cable 13 is used to electrically connect to the special-shaped solid rocket engine.

[0049] The two fixing assemblies 2 and the two pressure testing assemblies 3 are arranged in a 180° array along the axis of the centrifuge output shaft 11 .

[0050] Figure 5 is a structural diagram of a fixing assembly provided by an embodiment of the present invention, such as Figure 5 As shown, each fixing assembly 2 includes a fixing frame 21, a positioning plate 22 and a cage frame 23. The fixing frame 21 is a columnar structure, which is used to surround the upper shell 100 of the special-shaped solid rocket engine along the circumferential direction. The positioning plate 22 is fixed to the top of the fixing frame 21 (see Figure 6), and the positioning plate 22 is provided with a avoidance hole 221 for avoiding the upper pipeline 200 of the special-shaped solid rocket engine and a plurality of mounting holes 222 for connecting the upper shell 100 of the special-shaped solid rocket engine (see Figure 7 ), the fixing frame 21 is inserted into the inner hole of the cage frame 23, and the positioning plate 22 is connected to the top of the cage frame 23, and the bottom of the cage frame 23 is vertically fixed on one end of the rotating arm 12.

[0051] Figure 8 FIG. 1 is a schematic diagram of the structure of a pressure test assembly provided by an embodiment of the present invention. Figure 8 As shown, each pressure test assembly 3 includes a connecting joint 31, a flexible pressure-conducting tube 32, a pressure sensor 33 and a support 34. The connecting joint 31, the flexible pressure-conducting tube 32 and the pressure sensor 33 are connected in sequence. The connecting joint 31 is used to be inserted into the corresponding special-shaped solid rocket engine upper shell 100. The flexible pressure-conducting tube 32 passes through the corresponding fixing frame 21 and the cage frame 23. The support 34 is located on the outer wall of the corresponding cage frame 23, and the pressure sensor 33 is fixed on the corresponding support 34.

[0052] In the centrifugal overload ignition test apparatus for a special-shaped solid rocket motor provided by an embodiment of the present invention, the fixing frame 21 is a columnar structure that circumferentially surrounds the special-shaped solid rocket motor upper casing 100, thereby circumferentially securing the special-shaped solid rocket motor upper casing 100. Furthermore, the positioning plate 22 is provided with multiple mounting holes 222 for connecting the special-shaped solid rocket motor upper casing 100. Bolts and locating pins are inserted into the mounting holes 222 to connect the casing 100 and the positioning plate 22, thereby axially securing the special-shaped solid rocket motor upper casing 100. Ultimately, each special-shaped solid rocket motor is securely and reliably fixed to the fixing assembly 2 and the rotating arm 12, ensuring stability during subsequent overload testing. Furthermore, the two fixing assemblies 2 and the two pressure test assemblies 3 are arranged in a 180-degree array along the axis of the centrifuge output shaft 11, allowing the installation of the two special-shaped solid rocket motors to fully simulate a real-world layout (the exhaust direction of each pipeline 200 is arranged along the rotational tangent of the rotating arm 12). After the two special-shaped solid rocket engines are ignited, they can generate thrust by themselves to drive the centrifuge output shaft 11 to accelerate rotation (i.e., linear increase). The rotation speed of the corresponding centrifuge is determined by the rotation of the centrifuge output shaft 11, thereby calculating and determining the load of the corresponding special-shaped solid rocket engine. In this way, the dynamic incremental centrifugal overload ignition test of the special-shaped solid rocket engine can be realized to meet the dynamic incremental centrifugal overload working condition generated by the roll control torque of the special-shaped solid rocket engine.

[0053] On the other hand, the connecting joint 31, the flexible pressure-inducing tube 32, and the pressure sensor 33 are connected in sequence. The connecting joint 31 is used to be inserted into the corresponding special-shaped solid rocket engine upper shell 100. The flexible pressure-inducing tube 32 passes through the corresponding fixing frame 21 and the cage frame 23. The support 34 is located on the outer wall of the corresponding cage frame 23, and the pressure sensor 33 is fixed on the corresponding support 34. Therefore, the gas generated after combustion in the shell 100 is transmitted to the pressure sensor 33 through the connecting joint 31 and the flexible pressure-inducing tube 32. The pressure sensor 33 realizes accurate measurement of the air pressure in the shell 100, avoiding the risk of high temperature damage caused by directly placing the pressure sensor 33 in the shell 100. In addition, the flexible pressure-inducing tube 32 can be manually bent and deformed according to the structure of the fixing frame 21 and the cage frame 23, and then passed through, making the overall structure compact.

[0054] That is to say, the centrifugal overload ignition test device for a special-shaped solid rocket engine provided by an embodiment of the present invention can not only enable two special-shaped solid rocket engines to be reliably installed by completely simulating the actual layout, thereby generating thrust by the centrifuge to drive the rotation to realize a dynamic incremental centrifugal overload ignition test, but also can accurately measure the pressure inside the upper shell of the special-shaped solid rocket engine.

[0055] It is easy to understand that the cage frame 23 has a stable structure and uniform force, and the fixing frame 21 and the positioning plate 22 can be reliably fixed to the rotating arm 12 through the cage frame 23. In addition, the ignition signal and other test signals of the special-shaped solid rocket engine can be transmitted through the cable 13.

[0056] In addition, the pressure test component 3 can adopt a dual-path redundancy design.

[0057] For example, mounting holes 222 can be inserted with locating pins and connecting bolts, thereby achieving positioning and connection between housing 100 and positioning plate 22. The pivot arm 12 is preferably integrally formed from lightweight 6061 aluminum alloy. The back of the pivot arm 12 is hollowed out to reduce weight and facilitate securing the cable 13 within the weight-reducing groove. One end of the cable 13 is provided with a socket 131, specification Y11X-1210ZJ, to facilitate electrical connection to the special-shaped solid rocket motor.

[0058] For example, the cage frame 23 has a size of only Φ220mm×564mm, which can achieve reliable and compact fixation of special-shaped solid rocket engines with an envelope size of Φ170mm×536mm.

[0059] Figure 9 : is a structural diagram of a fixing frame provided by an embodiment of the present invention, such as Figure 9As shown, the fixing frame 21 includes two oppositely arranged half brackets 211 , each half bracket 211 is an arc-shaped structure, the two half brackets 211 are detachably connected, and the positioning plate 22 is fixed to the top of the two half brackets 211 .

[0060] In the above embodiment, the circumferential fixation of the housing 100 can be completed conveniently through the two half brackets 211 , and the assembly is facilitated.

[0061] For example, the half bracket 211 has a plurality of weight-reducing holes, which not only reduce weight but also facilitate the flexible pressure-inducing tube 32 to pass through.

[0062] Furthermore, a clamp 212 is fixedly provided at the bottom of each half bracket 211, and the two clamps 212 are detachably connected. The middle parts of the two half brackets 211 are detachably connected through two oppositely arranged connecting hoops 213. The two half brackets 211 can be reliably connected through the clamp 212 and the connecting hoops 213.

[0063] In addition, a connecting plate 214 is provided on one side of each half bracket 211 facing the positioning plate 22 . Each connecting plate 214 is parallel to the positioning plate 22 and connected by bolts, thereby reliably connecting the half bracket 211 and the positioning plate 22 through the connecting plate 214 .

[0064] It should be noted that the structures of the two half brackets 211 can be the same or different. The half brackets 211 can be designed according to the specific spatial structure.

[0065] Figure 10 Schematic diagram of the structure of the cage frame provided by the embodiment of the present invention. Figure 10 As shown, the top of the cage frame 23 has a connecting flange 231, which is stacked under the positioning plate 22 and connected by bolts. The fixing frame 21 passes through the connecting flange 231, and the connecting flange 231 also serves to connect the positioning plate 22 and the cage frame 23.

[0066] In addition, the bottom of the cage frame 23 has a bottom plate 232, and the outer peripheral wall of the bottom of the cage frame 23 has a plurality of spaced connecting ribs, each connecting rib is fixedly connected to the bottom plate 232, and each bottom plate 232 is fixed on the rotating arm 12. The bottom plate 232 serves to connect the cage frame 23 and the rotating arm 12.

[0067] Furthermore, two adapter seats 121 arranged at intervals are inserted on the rotating arm 12 , and each base plate 232 is fixed on the corresponding adapter seat 121 .

[0068] Exemplarily, the bottom plate 232 is connected to the adapter 121 by bolts 24. Positioning slots are provided on the rotating arm 12, and the bottom of the adapter 121 is inserted into the corresponding positioning slots to prevent the cage frame 23 from relative displacement during the rotation of the rotating arm 12.

[0069] Figure 11 is a cross-sectional view of the flexible pressure-inducing tube provided by an embodiment of the present invention, combined with Figure 8 and Figure 11 As shown, each pressure test assembly 3 also includes a first connector 35, which is fixed on the support 34 (fixed by bolts), and the detection end of the pressure sensor 33 is inserted into the first connector 35, and the connecting joint 31 includes a second connector 311 and an adapter 312 that are coaxially connected to each other. The first connector 35 and the second connector 311 are respectively connected to the two ends of the flexible pressure-leading tube 32, and the adapter 312 is used to be inserted into the corresponding special-shaped solid rocket engine upper shell 100.

[0070] In the above embodiment, the first connector 35 serves to connect the pressure sensor 33 and the flexible pressure-inducing tube 32, and the pressure sensor 33 can be fixed to the support 34 through the first connector 35. The second connector 311 serves to connect the flexible pressure-inducing tube 32 and the adapter 312.

[0071] For example, the second connector 311 has an external thread on one end facing away from the flexible pressure-inducing tube 32, and the adapter 312 has an internal thread on one end, and the external thread and the internal thread match. In addition, the adapter 312, the second connector 311 and the first connector 35 are all provided with a sealing ring 36.

[0072] It should be noted that the interface size corresponding to the connecting joint 31 on the shell 100 is 10 mm, while the size of the second connecting head 311 connected to the flexible pressure-inducing tube 32 is 14 mm. Therefore, the size of the docking channel is adjusted from 14 mm to 10 mm through the conversion of the adapter 312 (that is, the size of the left end of the adapter 312 is 14 mm, and the size of the right end of the second connecting head 311 is 10 mm).

[0073] As for the flexible pressure-inducing pipe, the flexible pressure-inducing pipe is welded by stainless steel, and both ends of the flexible pressure-inducing pipe are mechanical threaded interfaces, which have high structural strength and can withstand high-temperature and high-pressure gas.

[0074] For example, the specification of the flexible pressure-inducing tube may be Φ5 mm (outer diameter) × Φ3 mm (inner diameter) × 200 mm (length).

[0075] In this embodiment, the cable 13 adopts an RC filter circuit (see Figure 12), the RC filter circuit matching capacitor is 50nF and the resistor is 5kΩ. The RC filter circuit can eliminate the severe and irregular interference of the centrifuge working power supply, noise and vibration on the pressure output signal of the special-shaped fixed engine.

[0076] Figure 13 FIG. 1 is a flow chart of a centrifugal overload ignition test method for a special-shaped solid rocket motor provided by an embodiment of the present invention. Figure 13 As shown, the centrifugal overload ignition test method is based on the above-mentioned centrifugal overload ignition test method, and the centrifugal overload ignition test method includes:

[0077] S1. Secure each dummy engine to its corresponding fixing assembly 2, and arrange the fixing assemblies 2 in a 180-degree array at both ends of the rotating arm 12. Start the centrifuge (i.e., start the centrifuge output shaft 11 to rotate) according to the centrifugal dynamic overload value for each dummy engine, and perform a no-load test to check whether the ignition signal of the pyrotechnic device in the dummy engine, the zero-position output of the pressure sensor 33, and the centrifuge speed are normal.

[0078] It should be noted that the structure of the engine dummy is consistent with the external structure of the special-shaped solid rocket engine to be tested. The only difference is that the pyrotechnics in the engine dummy structure are replaced with counterweights of the same mass, but the ignition signal can also be transmitted through cable 13.

[0079] The following steps are used to fix the fake engine:

[0080] a. Connect the connecting joint 31, the flexible pressure-inducing tube 32, and the pressure sensor 33 in sequence, and insert the connecting joint 31 into the corresponding upper housing 100 of the dummy engine.

[0081] b. The upper housing 100 of the dummy engine is surrounded by the fixing frame 21 , and the fixing frame 21 and the positioning plate 22 are connected so that the upper pipeline 200 of the dummy engine passes through the avoidance hole 221 .

[0082] c. Insert the fixing frame 21 into the cage frame 23 , fix the positioning plate 22 on the top of the cage frame 23 , bend the flexible pressure-inducing tube 32 , and fix the support 34 on the outer wall of the cage frame 23 .

[0083] d. Fix two cage frames 23 at both ends of the rotating arm 12 in a 180° array along the axis of the centrifuge output shaft 11.

[0084] It is easy to understand that the no-load test can also check the dynamic balance of the centrifugal overload ignition test device, and can observe whether the dummy engine is damaged and whether the dummy engine is securely fixed.

[0085] S2. Inflate the casing of each dummy engine to the designed operating pressure (simulating the operating pressure inside the casing). Start the centrifuge for each dummy engine according to the centrifugal dynamic overload value, perform a load cooling simulation test, and check whether the feedback from the pressure sensor 33, the ignition signal of the pyrotechnic device, and the centrifuge speed are normal.

[0086] It is easy to understand that steps S1 and S2 can be used to gradually debug and confirm the relevant parameters and performance of the centrifugal overload ignition test before the formal test.

[0087] S3. Fix the special-shaped solid rocket engine to be tested on the corresponding fixed assembly 2, and arrange each fixed assembly 2 in a 180-degree array at both ends of the rotating arm 12. First, start the centrifuge at a small constant centrifugal overload value to balance the friction resistance generated during the rotation of the centrifuge assembly 1. Then ignite the special-shaped solid rocket engine and drive the centrifuge to rotate. Conduct a formal test and confirm the real-time overload value of the special-shaped solid rocket engine and the pressure inside the casing of the special-shaped solid rocket engine when it is in operation.

[0088] It should be noted that the special-shaped solid rocket motor is also fixed using steps ad.

[0089] In this embodiment, the constant centrifugal overload value required for the friction resistance generated during the rotation of the centrifugal overload ignition test device is 0.1g, and the roll control torque generated by the special-shaped solid rocket engine during the 31s operation can achieve a dynamic incremental centrifugal overload of 0→16g.

[0090] For example, in step S3, it is also possible to detect whether the resistance of the pyrotechnic product in the special-shaped solid rocket motor meets the required value.

[0091] It will be easily understood by those skilled in the art that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A centrifugal overload ignition test device for a special-shaped solid rocket engine, characterized in that: The centrifugal overload ignition test device includes a centrifuge assembly, two fixing assemblies and two pressure test assemblies; The centrifuge assembly includes a centrifuge output shaft, a rotating arm, and a cable. The centrifuge output shaft is perpendicular to the rotating arm and is in transmission connection with the middle portion of the rotating arm. The cable is arranged on the centrifuge output shaft and the rotating arm, and is used to electrically connect to the special-shaped solid rocket engine. The two fixing assemblies and the two pressure test assemblies are arranged in a 180° array along the axis of the centrifuge output shaft. Each of the fixing assemblies includes a fixing frame, a positioning plate and a cage frame. The fixing frame is a columnar structure and is used to circumferentially surround the upper shell of the special-shaped solid rocket engine. The positioning plate is fixed to the top of the fixing frame, and the positioning plate is provided with a avoidance hole for avoiding the upper pipeline of the special-shaped solid rocket engine and a plurality of mounting holes for connecting the upper shell of the special-shaped solid rocket engine. The fixing frame is inserted into the inner hole of the cage frame, and the positioning plate is connected to the top of the cage frame. The bottom of the cage frame is vertically fixed to one end of the rotating arm. Each of the pressure testing assemblies includes a connecting joint, a flexible pressure-conducting tube, a pressure sensor and a support. The connecting joint, the flexible pressure-conducting tube and the pressure sensor are connected in sequence. The connecting joint is used to be inserted into the corresponding upper casing of the special-shaped solid rocket engine. The flexible pressure-conducting tube passes through the corresponding fixing frame and the cage frame. The support is located on the outer wall of the corresponding cage frame, and the pressure sensor is fixed on the corresponding support.

2. The centrifugal overload ignition test device for a special-shaped solid rocket motor according to claim 1, characterized in that: The fixing frame includes two half brackets arranged opposite to each other, each half bracket is an arc-shaped structure, the two half brackets are detachably connected, and the positioning plate is fixed on the top ends of the two half brackets.

3. The centrifugal overload ignition test device for a special-shaped solid rocket motor according to claim 2, characterized in that: The bottom of each half bracket is fixed with a clamp, the two clamps are detachably connected, the middle parts of the two half brackets are detachably connected by two oppositely arranged connecting clamps, and each half bracket is provided with a connecting plate on the side facing the positioning plate, and each connecting plate is parallel to the positioning plate and connected by bolts.

4. The centrifugal overload ignition test device for a special-shaped solid rocket motor according to claim 1, characterized in that: The top of the cage frame is provided with a connecting flange, the connecting flange is stacked below the positioning plate and connected by bolts, and the fixing frame passes through the connecting flange.

5. The centrifugal overload ignition test device for a special-shaped solid rocket motor according to claim 1, characterized in that: Each of the pressure testing assemblies also includes a first connector, which is fixed on the support, and the detection end of the pressure sensor is inserted into the first connector. The connecting joint includes a second connector and an adapter that are coaxially connected to each other. The first connector and the second connector are respectively connected to the two ends of the flexible pressure-leading tube, and the adapter is used to be inserted into the corresponding special-shaped solid rocket engine upper casing.

6. The centrifugal overload ignition test device for a special-shaped solid rocket motor according to claim 1, characterized in that: The bottom of the cage frame has a bottom plate, and the outer peripheral wall of the bottom of the cage frame has a plurality of spaced connecting ribs, each of which is fixedly connected to the bottom plate, and each of the bottom plates is fixed on the rotating arm. Two spaced adapters are inserted on the rotating arm, and each of the bottom plates is fixed on the corresponding adapter.

7. The centrifugal overload ignition test device for a special-shaped solid rocket motor according to claim 1, characterized in that: The flexible pressure-inducing tube is formed by welding stainless steel, and both ends of the flexible pressure-inducing tube are mechanical threaded interfaces.

8. The centrifugal overload ignition test device for a special-shaped solid rocket motor according to claim 1, characterized in that: The specification of the flexible pressure-inducing tube is Φ5mm×Φ3mm×200mm.

9. A centrifugal overload ignition test device for a special-shaped solid rocket motor according to any one of claims 1 to 8, characterized in that: The cable corresponds to an RC filter circuit, and the matching capacitance of the RC filter circuit is 50nF and the resistance is 5kΩ.

10. A centrifugal overload ignition test method for a special-shaped solid rocket motor, characterized in that: The centrifugal overload ignition test method is based on the centrifugal overload ignition test method according to any one of claims 1 to 9, and the centrifugal overload ignition test method comprises: Fix each dummy engine to the corresponding fixing assembly, and arrange the fixing assemblies in a 180-degree array at both ends of the rotating arm. Start the centrifuge according to the centrifugal dynamic overload value for each dummy engine, perform a no-load test, and check whether the ignition signal of the pyrotechnic device in the dummy engine, the zero-position output of the pressure sensor, and the centrifuge speed are normal; The casing of each dummy engine is inflated to the designed working pressure, and the centrifuge is started according to the centrifugal dynamic overload value for each dummy engine to perform a load cold air simulation test to check whether the pressure sensor feedback, the ignition signal of the pyrotechnic device, and the centrifuge speed are normal; The shaped solid rocket motor to be tested is fixed on the corresponding fixed assembly, and each of the fixed assemblies is arranged in a 180° array at both ends of the rotating arm. The centrifuge is first started at a small constant centrifugal overload value to balance the friction resistance generated during the rotation of the centrifuge assembly. Then the shaped solid rocket motor is ignited and drives the centrifuge to rotate for a formal test, and the real-time overload value of the shaped solid rocket motor and the pressure inside the casing when the shaped solid rocket motor is working are confirmed.

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