Special-shaped solid rocket engine centrifugal overload ignition test device and method

Abstract

The invention discloses a centrifugal overload ignition test device and method for a special-shaped solid rocket engine, and belongs to the technical field of solid rocket engines. The centrifugal overload ignition test device comprises a centrifugal machine assembly, two fixing assemblies and two pressure test assemblies. Each fixing assembly comprises a fixing frame, a positioning disc and a cage type frame, and the fixing frame is of a columnar structure; each pressure testing assembly comprises a connecting joint, a flexible pressure guiding pipe, a pressure sensor and a support. The flexible pressure guiding pipe penetrates through the corresponding fixing frame and the cage type frame. According to the centrifugal overload ignition test device for the special-shaped solid rocket engine provided by the embodiment of the invention, the centrifugal machine can be driven to rotate through thrust generated by the centrifugal overload ignition test device, so that a dynamic incremental centrifugal overload ignition test can be realized, and the pressure of a combustion chamber in the special-shaped solid rocket engine can be accurately measured; and the flexible pressure guide pipe can be manually and flexibly bent and deformed according to the structures of the fixing frame and the cage type frame and then penetrates through the fixing frame.

Description

Technical Field

[0001] The 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] The centrifugal overload ignition test of the engine plays an important role in the development of solid rocket engines. In order to simulate the flight overload conditions of solid rocket engines, different overload tests are carried out to provide more comprehensive verification data for the development of solid rocket engines.

[0003] One of the main functions of a certain type of solid rocket engine is to provide a tangential rolling control torque to the weapon system. When used in pairs, the weapon system can be rotated to make it rotate at a certain speed around the flight direction during flight, producing 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-shaped 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 cannot accurately measure the pressure inside the upper shell of the special-shaped solid rocket engine during the test. Summary of the invention

[0005] In view of the above 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 by fully 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 to accurately measure the pressure inside the upper shell of the special-shaped solid rocket engine.

[0006] To achieve the above-mentioned object, 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; The centrifuge assembly includes a centrifuge output shaft, a rotating arm and a cable, wherein the centrifuge output shaft is perpendicular to the rotating arm and is drivingly connected to the middle part of the rotating arm, and the cable is arranged on the centrifuge output shaft and the rotating arm, and the cable is used to be electrically connected 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, and each of the fixing assemblies includes a fixing frame, a positioning plate and a cage frame. The fixing frame is a columnar structure, which is used to surround the upper shell of the special-shaped solid rocket engine along the circumferential direction. The positioning plate is fixed to the top of the fixing frame, and the positioning plate is provided with avoidance holes 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, and 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.

[0007] Optionally, the fixing frame includes two half brackets arranged opposite to each other, each of the half brackets 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.

[0008] Optionally, a clamp is fixedly provided at the bottom of each half bracket, and the two clamps are detachably connected. The middle parts of the two half brackets are detachably connected by two oppositely arranged connecting hoops. A connecting plate is provided on the side of each half bracket facing the positioning plate, and each connecting plate is parallel to the positioning plate and connected by bolts.

[0009] 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.

[0010] Optionally, 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.

[0011] Optionally, the bottom of the cage frame has a bottom plate, and the bottom peripheral wall 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 adapter seats are inserted on the rotating arm, and each of the bottom plates is fixed on the corresponding adapter seat.

[0012] Optionally, the flexible pressure-inducing tube is formed by welding of stainless steel, and both ends of the flexible pressure-inducing tube are mechanical threaded interfaces.

[0013] Optionally, the flexible pressure-guiding tube has a specification of Φ5mm×Φ3mm×200mm.

[0014] Optionally, the cable corresponds to an RC filter circuit, and the matching capacitor of the RC filter circuit is 50nF and the resistor is 5kΩ.

[0015] In a second aspect, the present invention provides a centrifugal overload ignition test method for a special-shaped solid rocket engine. 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: Fix each dummy engine on the corresponding fixing assembly, and arrange each fixing assembly in a 180° 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 pyrotechnics in the dummy engine, the zero position output of the pressure sensor, and the centrifuge speed are normal; Inflate the shell of each dummy engine to the designed working pressure, start the centrifuge according to the centrifugal dynamic overload value of each dummy engine, perform a load cold air simulation test, and detect whether the pressure sensor feedback, the ignition signal of the pyrotechnics and the centrifuge speed are normal; The special-shaped solid rocket engine to be tested is fixed on the corresponding fixed assembly, and the fixed assemblies are arranged in a 180° array at both ends of the rotating arm. The centrifuge is first started at a smaller constant centrifugal overload value to balance the friction resistance generated during the rotation of the centrifuge assembly. The special-shaped solid rocket engine is then ignited and the centrifuge is driven to rotate. A formal test is carried out to confirm the real-time overload value of the special-shaped solid rocket engine and the pressure inside the casing when the special-shaped solid rocket engine is working.

[0016] The above-mentioned improved technical features can be combined with each other as long as they do not conflict with each other.

[0017] For a centrifugal overload ignition test device for a special-shaped solid rocket engine provided by an embodiment of the present invention, on the one hand, the fixing frame is a columnar structure, and the fixing frame can surround the upper shell of the special-shaped solid rocket engine along the circumferential direction, thereby realizing the circumferential fixation of the upper shell of the special-shaped solid rocket engine. In addition, a plurality of mounting holes for connecting the upper shell of the special-shaped solid rocket engine are provided on the positioning plate, so that bolts and positioning pins are inserted into the mounting holes to connect the shell and the positioning plate, thereby realizing the axial fixation of the upper shell of the special-shaped solid rocket engine, and finally each special-shaped solid rocket engine is firmly and reliably fixed on the fixing assembly and the rotating arm, ensuring the stability of the subsequent overload test. In addition, the two fixing assemblies and the two pressure test assemblies are arranged in a 180° array along the axis of the centrifuge output shaft, so that the two special-shaped solid rocket engines can be installed by completely simulating the real layout (the exhaust direction of each pipeline is arranged along the rotation tangent direction of the rotating arm). After the two special-shaped solid rocket engines are ignited, they can generate thrust by themselves to drive the centrifuge output shaft to accelerate its rotation. The rotation speed of the corresponding centrifuge is determined by the rotation of the centrifuge output shaft, thereby calculating and determining the load of the corresponding special-shaped solid rocket engine. This also enables the dynamic incremental centrifugal overload ignition test of the special-shaped solid rocket engine to be realized, satisfying the dynamic incremental centrifugal overload condition generated by the roll control torque of the special-shaped solid rocket engine.

[0018] On the other hand, the connection joint, the flexible pressure-conducting pipe and the pressure sensor are connected in sequence, the connection joint is used to be inserted into the corresponding special-shaped solid rocket engine upper shell, the flexible pressure-conducting pipe runs 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, so that the gas generated after combustion in the shell is transmitted to the pressure sensor through the connection joint and the flexible pressure-conducting pipe, and the pressure sensor is used to accurately measure the air pressure in the shell, avoiding the risk of high temperature damage caused by directly setting the pressure sensor in the shell. In addition, the flexible pressure-conducting pipe can be manually bent and deformed according to the structure of the fixing frame and the cage frame, and then passed through, so that the overall structure is compact.

[0019] 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

[0020] Figure 1 is a schematic structural diagram of a special-shaped solid rocket engine provided by an embodiment of the present invention; Figure 2It is a structural schematic diagram of a centrifugal overload ignition test device for a special-shaped solid rocket engine provided by an embodiment of the present invention; Figure 3 is a schematic structural diagram of a centrifuge assembly provided by an embodiment of the present invention; Figure 4 is a schematic diagram of the arrangement of cables provided by an embodiment of the present invention; Figure 5 is a schematic diagram of the structure of a fixing assembly provided by an embodiment of the present invention; Figure 6 is a schematic diagram of the assembly of the positioning plate and the fixing frame provided in an embodiment of the present invention; Figure 7 is a schematic structural diagram of a positioning plate provided in an embodiment of the present invention; Figure 8 is a schematic diagram of the structure of a pressure test assembly provided by an embodiment of the present invention; Fig. 9 is a schematic structural diagram of a fixing frame provided by an embodiment of the present invention; Fig.10 is a structural schematic diagram of a cage frame provided by an embodiment of the present invention; Fig.11 is a cross-sectional view of a flexible pressure-inducing tube provided in an embodiment of the present invention; Fig.12 is a schematic diagram of the principle of an RC filter circuit provided by an embodiment of the present invention; Fig.13 The present invention provides a flow chart of a centrifugal overload ignition test method for a special-shaped solid rocket engine.

[0021] In all the drawings, the same reference numerals represent the same technical features, specifically: 1. Centrifuge assembly; 11. Centrifuge output shaft; 12. Swivel 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 pipe; 33. Pressure sensor; 34. Support; 35. First connector; 36. Sealing ring; 100. Shell; 200. Pipeline. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain 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 can be combined with each other as long as they do not conflict with each other.

[0023] 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 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, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0024] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0025] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0026] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0027] Example: Figure 2 FIG. 1 is a schematic 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.

[0028] Figure 3 Schematic diagram of the structure of the centrifuge assembly provided by the embodiment of the present invention. 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 drivingly connected to the middle of the rotating arm 12. The cable 13 is arranged on the centrifuge output shaft 11 and the rotating arm 12 (see Figure 4 ), cable 13 is used to electrically connect to the special-shaped solid rocket engine.

[0029] 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 .

[0030] Figure 5 is a schematic diagram of the structure of a fixing assembly provided in 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.

[0031] Figure 8 is a schematic diagram of the structure of a pressure test assembly provided by an embodiment of the present invention, such as 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.

[0032] For a centrifugal overload ignition test device for a special-shaped solid rocket engine provided by an embodiment of the present invention, on the one hand, the fixing frame 21 is a columnar structure, and the fixing frame 21 can surround the special-shaped solid rocket engine upper shell 100 along the circumferential direction, thereby realizing the circumferential fixation of the special-shaped solid rocket engine upper shell 100. In addition, a plurality of mounting holes 222 for connecting the special-shaped solid rocket engine upper shell 100 are provided on the positioning plate 22, so that bolts and positioning pins are inserted into the mounting holes 222 to connect the shell 100 and the positioning plate 22, thereby realizing the axial fixation of the special-shaped solid rocket engine upper shell 100, and finally each special-shaped solid rocket engine is firmly and reliably fixed on the fixing assembly 2 and the rotating arm 12, ensuring the stability of the subsequent overload test. In addition, the two fixing assemblies 2 and the two pressure test assemblies 3 are arranged in a 180° array along the axis of the centrifuge output shaft 11, so that the two special-shaped solid rocket engines can be installed by completely simulating the real layout (the exhaust direction of each pipeline 200 is arranged along the rotation tangent direction 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, and thus realizing the dynamic increasing centrifugal overload ignition test of the special-shaped solid rocket engine, which meets the dynamic increasing centrifugal overload condition generated by the roll control torque of the special-shaped solid rocket engine.

[0033] On the other hand, the connection joint 31, the flexible pressure-conducting pipe 32 and the pressure sensor 33 are connected in sequence, the connection joint 31 is used to be inserted into the corresponding special-shaped solid rocket engine upper shell 100, the flexible pressure-conducting pipe 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, so that the gas generated after combustion in the shell 100 is transmitted to the pressure sensor 33 through the connection joint 31 and the flexible pressure-conducting pipe 32, and the pressure sensor 33 is used to accurately measure the air pressure in the shell 100, avoiding the risk of high temperature damage caused by directly setting the pressure sensor 33 in the shell 100. In addition, the flexible pressure-conducting pipe 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, so that the overall structure is compact.

[0034] 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.

[0035] 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 on the rotating arm 12 through the cage frame 23. In addition, the ignition signal of the special-shaped solid rocket engine and other test signals can be transmitted through the cable 13.

[0036] In addition, the pressure test component 3 can adopt a dual-path redundant design.

[0037] For example, the mounting hole 222 can be inserted with a positioning pin and a connecting bolt to realize the positioning and connection between the housing 100 and the positioning plate 22. The rotating arm 12 is preferably integrally formed of a lightweight aluminum alloy 6061, and the back of the rotating arm 12 is hollowed out to reduce weight, and the cable 13 is conveniently fixed in the weight reduction groove. A socket 131 is provided at one end of the cable 13, and the specification adopts Y11X-1210ZJ, which is convenient for electrical connection with a special-shaped solid rocket engine.

[0038] For example, the cage frame 23 has a size of only Φ220 mm×564 mm, which can achieve reliable and compact fixation of special-shaped solid rocket engines with an envelope size of Φ170 mm×536 mm.

[0039] Fig. 9 is a schematic diagram of the structure of a fixing frame provided by an embodiment of the present invention, such as Fig. 9 As shown, the fixing frame 21 includes two relatively 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 on the top of the two half brackets 211 .

[0040] 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 convenient.

[0041] Exemplarily, the half bracket 211 has a plurality of weight-reducing holes, which not only reduce weight but also facilitate the flexible pressure-guiding tube 32 to pass through.

[0042] 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, and the two half brackets 211 can be reliably connected through the clamp 212 and the connecting hoops 213.

[0043] 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, so that the half bracket 211 and the positioning plate 22 are reliably connected by the connecting plate 214 .

[0044] It should be noted that the structures of the two half brackets 211 may be the same or different. The half brackets 211 may be designed according to the specific spatial structure.

[0045] Fig.10 Schematic diagram of the structure of the cage frame provided by the embodiment of the present invention. Fig.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.

[0046] In addition, the bottom of the cage frame 23 has a bottom plate 232, and the bottom peripheral wall of the cage frame 23 has a plurality of spaced connection ribs, each of which is fixedly connected to the bottom plate 232, and each bottom plate 232 is fixed on the rotating arm 12, and the bottom plate 232 serves to connect the cage frame 23 and the rotating arm 12.

[0047] Furthermore, two adapter seats 121 arranged at intervals are inserted on the rotating arm 12 , and each bottom plate 232 is fixed on the corresponding adapter seat 121 .

[0048] Exemplarily, the bottom plate 232 is connected to the adapter 121 by bolts 24. A positioning groove is provided on the rotating arm 12, and the bottom of the adapter 121 is inserted into the corresponding positioning groove to prevent the cage frame 23 from relative displacement during the rotation of the rotating arm 12.

[0049] Fig.11 is a cross-sectional view of a flexible pressure-inducing tube provided in an embodiment of the present invention, Figure 8 and Fig.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 in the first connector 35, and the connecting joint 31 includes a second connector 311 and an adapter 312 which are coaxially connected to each other, and 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.

[0050] 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 on 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.

[0051] Exemplarily, the second connector 311 has an external thread at one end facing away from the flexible pressure-inducing tube 32, and the adapter 312 has an internal thread at one end, and the external thread and the internal thread match each other. In addition, the adapter 312, the second connector 311 and the first connector 35 are all provided with a sealing ring 36.

[0052] 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-leading 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).

[0053] As for the flexible pressure-inducing pipe, the flexible pressure-inducing pipe is formed by welding of stainless steel, and both ends of the flexible pressure-inducing pipe are mechanical threaded interfaces, with high structural strength, and can withstand high-temperature and high-pressure gas.

[0054] For example, the specification of the flexible pressure-inducing tube may be Φ5 mm (outer diameter)×Φ3 mm (inner diameter)×200 mm (length).

[0055] In this embodiment, the cable 13 uses an RC filter circuit (see Fig.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.

[0056] Fig.13 FIG. 1 is a flow chart of a centrifugal overload ignition test method for a special-shaped solid rocket engine provided by an embodiment of the present invention. Fig.13 As shown, the centrifugal overload ignition test method is based on the above centrifugal overload ignition test method, and the centrifugal overload ignition test method includes: S1. Fix each dummy engine on the corresponding fixing assembly 2, and arrange each fixing assembly 2 in a 180° array at both ends of the rotating arm 12. Start the centrifuge for each dummy engine according to the centrifugal dynamic overload value (i.e., the centrifuge output shaft 11 starts to rotate), and perform a no-load test to check whether the ignition signal of the pyrotechnics in the dummy engine, the zero position output of the pressure sensor 33, and the centrifuge speed are normal.

[0057] 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.

[0058] The following steps are used to fix the engine fake: a. Connect the connecting joint 31, the flexible pressure-inducing pipe 32 and the pressure sensor 33 in sequence, and insert the connecting joint 31 into the corresponding upper housing 100 of the dummy engine.

[0059] 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 .

[0060] 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-conducting tube 32 , and fix the support 34 on the outer wall of the cage frame 23 .

[0061] 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.

[0062] 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 engine dummy is damaged and whether the engine dummy is reliably fixed.

[0063] S2. Inflate the shell of each dummy engine to the designed working pressure (simulating the working pressure inside the shell), start the centrifuge of each dummy engine according to the centrifugal dynamic overload value, perform a load cold air simulation test, and check whether the feedback of the pressure sensor 33, the ignition signal of the pyrotechnic device and the centrifuge speed are normal.

[0064] 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.

[0065] S3. Fix the special-shaped solid rocket engine to be tested on the corresponding fixed assembly 2, and arrange the fixed assemblies 2 in a 180° array at both ends of the rotating arm 12. First, start the centrifuge at a smaller 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 shell when the special-shaped solid rocket engine is working.

[0066] It should be noted that the special-shaped solid rocket engine is also fixed using steps ad.

[0067] 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 rolling control torque generated by the special-shaped solid rocket engine during the 31s operation can achieve a dynamic incremental centrifugal overload of 0→16g.

[0068] Exemplarily, in step S3, it is also possible to detect whether the resistance of the pyrotechnic product in the special-shaped solid rocket engine meets the required value.

[0069] It will be easily understood by those skilled in the art that the above description is only 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 protection scope 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, wherein the centrifuge output shaft is perpendicular to the rotating arm and is drivingly connected to the middle part of the rotating arm, and the cable is arranged on the centrifuge output shaft and the rotating arm, and the cable is used to be electrically connected 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, and each of the fixing assemblies includes a fixing frame, a positioning plate and a cage frame. The fixing frame is a columnar structure, which is used to surround the upper shell of the special-shaped solid rocket engine along the circumferential direction. The positioning plate is fixed to the top of the fixing frame, and the positioning plate is provided with avoidance holes 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, and 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 engine according to claim 1, characterized in that: The fixing frame comprises two half brackets arranged opposite to each other, each of the half brackets 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 engine according to claim 2, characterized in that: A clamp is fixedly provided at the bottom of each half bracket, and the two clamps are detachably connected. The middle parts of the two half brackets are detachably connected by two oppositely arranged connecting hoops. A connecting plate is provided on the side of each half bracket 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 engine 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 engine 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 engine 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 engine according to claim 1, characterized in that: The flexible pressure-inducing pipe is formed by welding of stainless steel, and both ends of the flexible pressure-inducing pipe are mechanical threaded interfaces.

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

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

10. A centrifugal overload ignition test method for a special-shaped solid rocket engine, 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 on the corresponding fixing assembly, and arrange each fixing assembly in a 180° 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 pyrotechnics in the dummy engine, the zero position output of the pressure sensor, and the centrifuge speed are normal; Inflate the shell of each dummy engine to the designed working pressure, start the centrifuge according to the centrifugal dynamic overload value of each dummy engine, perform a load cold air simulation test, and detect whether the pressure sensor feedback, the ignition signal of the pyrotechnics and the centrifuge speed are normal; The special-shaped solid rocket engine to be tested is fixed on the corresponding fixed assembly, and the fixed assemblies are arranged in a 180° array at both ends of the rotating arm. The centrifuge is first started at a smaller constant centrifugal overload value to balance the friction resistance generated during the rotation of the centrifuge assembly. The special-shaped solid rocket engine is then ignited and the centrifuge is driven to rotate. A formal test is carried out to confirm the real-time overload value of the special-shaped solid rocket engine and the pressure inside the casing when the special-shaped solid rocket engine is working.

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