Tail end device for automatic fire extinguishing after test run of solid rocket engine

Abstract

An end device for automatic fire extinguishing after test run of a solid rocket engine comprises an air pipe, an air source collecting system, an air source control system, an end sealing mechanism, a flexibility compensation mechanism and a floating adjusting mechanism, and a support is used for fixing the air source collecting system; the air source collecting system is fixedly connected with the air source control system through an air pipe; the air source control system is connected with the tail end sealing mechanism through an air pipe; the tail end sealing mechanism is fixedly connected with the flexibility compensation mechanism; the flexibility compensation mechanism is connected with the air source control system through an air pipe; and the flexibility compensation mechanism is fixedly connected with the floating adjustment mechanism. According to the automatic fire extinguishing tail end device provided by the invention, flexible butt joint of nozzles with various types of surfaces and multiple structural sizes can be adaptively matched, the universal fire extinguishing requirement after test run of various solid rocket engines is met, and good sealing performance is ensured on the premise that the structures of the engine nozzles are not damaged; and coaxial feeding with the jet pipe of the solid rocket engine is realized.

Description

Technical Field

[0001] The present invention relates to an end device, in particular to an end device suitable for automatic fire extinguishing treatment after a solid rocket engine test run. Background Art

[0002] The refined design of the insulation layer is an important way to improve the performance of solid rocket engines. At present, the ablation state analysis of the insulation layer after the engine test is mainly carried out by measuring the remaining thickness of the insulation layer through the dissection of the combustion chamber. However, the insulation layer structure is still affected by the residual temperature and fire in the combustion chamber after the engine operation and continues to ablate, resulting in the remaining thickness of the insulation layer measured after the combustion chamber dissection being less than the true value, and it can only be compensated by increasing the thickness redundancy of the insulation layer.

[0003] To prevent the ablation of the insulation layer after the engine operation and retain the true ablation state of the insulation layer after the engine operation to the greatest extent, at present, the method of blocking the nozzle of the engine after the test run is usually adopted, that is, a conical simple plug wrapped with asbestos cloth is used to block the engine nozzle, and the combustion chamber of the engine is isolated from the outside air, so that the remaining fire in the combustion chamber slowly extinguishes under the condition of lack of oxygen. However, the use of a simple plug wrapped with asbestos cloth to achieve the effect of isolating the outside air is not ideal, and it is difficult to adapt to engines with different structural parameters such as expansion angles and nozzle lengths. In addition, the fire extinguishing effect by simply blocking the nozzle or suffocating and cooling is not ideal, and it still takes a long time for the remaining fire in the combustion chamber to extinguish.

[0004] The inert medium suffocating and cooling solid rocket engine technology disclosed in Patent CN111122166 A only fills nitrogen into the engine through a linear cylinder carrying a spray gun, but it cannot isolate the continuous inflow of external air into the combustion chamber, and the fire extinguishing effect is not fast enough.

[0005] Therefore, proceeding from the actual situation and combining with the test run site, it is urgent to develop a stable and reliable end device suitable for automatic fire extinguishing after a solid rocket engine test run, which supports changing the previous fire extinguishing method after a solid rocket engine test run, realizes rapid, safe and efficient suffocating fire extinguishing after the engine test run, helps to optimize the design of the insulation layer thickness of the engine, and accelerates the lightweight and performance improvement of the engine. Summary of the Invention

[0006] The object of the present invention is to provide an end device for automatic fire extinguishing after a solid rocket engine test run, which can change the rigid docking process of the previous nozzle blocking, realize the flexible docking of self-adaptive matching of various types of surfaces and nozzles with multiple structural dimensions, break through the sealing problem under the high-temperature environment after a solid rocket engine test run, and solve the general fire extinguishing requirements. The technical solution is as follows:

[0007] An end device for automatically extinguishing a fire after a test run of a solid rocket motor. The end device includes an air pipe, an air source collection system, an air source control system, an end sealing mechanism, a flexible compensation mechanism, and a floating adjustment mechanism, where:

[0008] The air source collection system is fixedly connected to the air source control system through the air pipe;

[0009] The air source control system is connected to the end sealing mechanism through the air pipe;

[0010] The end sealing mechanism is fixedly connected to the flexible compensation mechanism;

[0011] The flexible compensation mechanism is connected to the air source control system through the air pipe;

[0012] The flexible compensation mechanism is fixedly connected to the floating adjustment mechanism.

[0013] The air source collection system includes a support frame, a gas cylinder group, a gas supply pipeline, a pressure display unit, and a pressure control unit;

[0014] The support frame is used to fix the air source collection system. The gas cylinder group is arranged inside the support frame. The gas supply pipeline is connected to the gas cylinder group. The pressure display unit and the pressure control unit are arranged on the gas supply pipeline. The pressure display unit is located between the gas cylinder group and the pressure control unit;

[0015] The air source control system includes an external protection housing, a blowing control unit, a compensation gas supply control unit, and a compensation gas supply adjustment unit;

[0016] The external protection housing is fixed on the wall. The blowing control unit and the compensation gas supply control unit are both arranged inside the external protection housing. The compensation gas supply adjustment unit is fixed on the outside of the external protection housing;

[0017] The end sealing mechanism includes a gas supply pipe, a sealing fixing plate, a sealing support frame, an extension support, a transfer transition plate, an air outlet pipe, and a flexible sealing layer;

[0018] The gas supply pipe is horizontally arranged and connected to the air source control system; the sealing fixing plate is vertically arranged on the gas supply pipe; the sealing support frame is fixedly connected to the sealing fixing plate by bolts; the extension support is installed on the right end face of the sealing fixing plate by bolts; the transfer transition plate is fixedly installed on the right side of the extension support; the air outlet pipe passes through the sealing support frame and is arranged parallel to the gas supply pipe, and the flexible sealing layer is coated and bonded on the outside of the sealing support frame;

[0019] The flexible compensation mechanism includes a floating unit and a fixed unit; the floating unit is fixedly installed on the right side of the adapter transition plate, and the fixed unit is arranged on the right side of the floating unit and is flexibly connected to the floating unit;

[0020] The floating adjustment mechanism includes an adapter support, a flange shaft, a rotating bearing I, a support positioning plate, an actuator docking plate, a transmission gear, a shaft support I, a rotating bearing II, a shaft support II, a transmission rack, a stop locking knob, and an adjustment handwheel;

[0021] The adapter support is arranged on the end face of the fixed unit and is fixedly connected to it;

[0022] The flange shaft is fixedly installed on the adapter support through a threaded interface;

[0023] The rotating bearing I is arranged outside the flange shaft and is rotatably connected to it;

[0024] The support positioning plate passes through the rotating bearing I and is perpendicularly arranged with the flange shaft;

[0025] The actuator docking plate is perpendicularly arranged with the support positioning plate and is fixedly connected to it;

[0026] The transmission gear passes through the flange shaft and is fixedly connected to it by a key connection;

[0027] The shaft support I is arranged on the end face of the support positioning plate and is fixedly connected to it;

[0028] The rotating bearing II is fixedly installed inside the shaft support I;

[0029] The shaft support II is arranged on the right side of the shaft support I and is fixed on the support positioning plate;

[0030] The transmission rack passes through the shaft support I and the shaft support II and is installed inside the rotating bearing II;

[0031] The stop locking knob is arranged on the right side of the shaft support II and is fixedly installed on the transmission rack;

[0032] The adjustment handwheel is arranged on the right side of the stop locking knob and is fixedly installed on the transmission rack;

[0033] Preferably, the floating unit remains in a floating state during the docking and sealing process between the end sealing mechanism and the engine nozzle, and also remains in a floating state during the disconnection process of the end sealing mechanism from the engine nozzle, and remains in a fixed state during the rest of the working process;

[0034] Preferably, the flexible sealing layer is made of elastic and ablative-resistant materials and produces slight elastic deformation when docking with engine nozzles with different expansion angles;

[0035] The preparation method of the flexible sealing layer comprises the following steps:

[0036] (1) The preparation tooling for the flexible sealing layer is a combined pressing die, including an inner die and an outer die;

[0037] (2) Select an adiabatic material with an elongation rate higher than 500% and an ablation rate lower than 0.07 mm / s for circular cutting. Fill the cut blank into the outer die in the order of placing the one with a larger outer diameter at the bottom and the one with a smaller outer diameter at the top. Place the inner die into the outer die, and ensure that the guide posts arranged on the outer die enter the central holes of the inner membrane;

[0038] (3) Place the combined pressing die on a flat vulcanizing machine, control the temperature range of 150°C - 160°C, and preheat the adiabatic material for 2 min - 3 min;

[0039] (4) According to the pressing processes of 1 MPa - 3 MPa, 5 MPa - 7 MPa, 8 MPa - 10 MPa, and 12 MPa - 15 MPa, press in sequence, and the pressure holding times are 2 min - 3 min, 2 min - 3 min, 2 min - 3 min, and 10 min - 15 min respectively;

[0040] (5) Use a triangular knife to cut off the waste edges of the blank outside the combined pressing die, and push up the inner membrane through the bolts arranged on the outer die to complete demolding.

[0041] Compared with the prior art, the beneficial effects of the present invention are:

[0042] (1) By setting the end sealing mechanism, it can realize the flexible docking of self - adapting to match various types of surfaces and nozzles with multiple structural sizes, and solve the universal fire - extinguishing requirements after the test runs of various solid rocket engines.

[0043] (2) By setting the flexible sealing layer, it solves the sealing problem in the high - temperature environment after the test run of the solid rocket engine, realizes the function of self - adapting nozzle profile based on micro - deformation elastic compensation, and ensures good sealing performance without damaging the structure of the engine nozzle.

[0044] (3) By setting the flexible compensation mechanism, it can change the rigid docking process of blocking the nozzle in the past, realize self - adapting flexible docking and sealing, and avoid the risk of damaging and knocking the nozzle during the automatic fire - extinguishing process.

[0045] (4) By setting the floating adjustment mechanism, it can adjust the level of the overall end device, compensate for and solve the problem of uneven ground during the test run of the solid rocket engine, and realize coaxial feeding with the nozzle of the solid rocket engine. Description of the Drawings

[0046] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0047] Figure 1 It is a three-dimensional structural schematic diagram of the end device provided by the present invention for automatically extinguishing fire after the test run of a solid rocket motor.

[0048] Figure 2 It is a three-dimensional structural schematic diagram of the gas source gathering system provided by the present invention.

[0049] Figure 3 It is a three-dimensional structural schematic diagram of the gas source control system provided by the present invention.

[0050] Figure 4 It is a three-dimensional structural schematic diagram of the end sealing mechanism provided by the present invention.

[0051] Figure 5 It is a three-dimensional structural schematic diagram of the flexible sealing layer provided by the present invention.

[0052] Figure 6 It is a front view of the flexible compensation mechanism and the floating adjustment mechanism provided by the present invention.

[0053] Figure 7 It is a rear view of the flexible compensation mechanism and the floating adjustment mechanism provided by the present invention.

[0054] Figure 8 It is a front view of the butt joint sealing between the end sealing mechanism and the nozzle of the solid rocket motor provided by the present invention.

[0055] Figure 9 It is a front view of the combined pressing die provided by the present invention.

[0056] Figure 10 It is a three-dimensional structural schematic diagram of the inner mold provided by the present invention.

[0057] Figure 11 It is a three-dimensional structural schematic diagram of the outer mold provided by the present invention.

[0058] Reference numerals:

[0059] 1. Gas source gathering system: support frame 1-1; gas cylinder group 1-2; gas supply pipeline 1-3; pressure display unit 1-4; pressure control unit 1-5;

[0060] 2. Gas source control system: an external protective housing 2-1; a blowing control unit 2-2; a compensation air supply control unit 2-3; a compensation air supply adjustment unit 2-4;

[0061] 3. End sealing mechanism: an air supply pipe 3-1; a sealing fixing plate 3-2; a sealing support frame 3-3; an extension bracket 3-4; a transfer transition plate 3-5; an air outlet pipe 3-6; a flexible sealing layer 3-7;

[0062] 4. Flexible compensation mechanism: a floating unit 4-1; a fixed unit 4-2;

[0063] 5. Floating adjustment mechanism: a transfer support 5-1; a flange shaft 5-2; a first rotating bearing 5-3; a support positioning plate 5-4; a connecting plate 5-5; a transmission gear 5-6; a first shaft support 5-7; a second rotating bearing 5-8; a second shaft support 5-9; a transmission rack 5-10; a stop locking knob 5-11; an adjustment handwheel 5-12;

[0064] 6. Solid rocket engine;

[0065] 7. Combined pressing die: an inner die 7-1; an outer die 7-2.

[0066] Specific implementation mode

[0067] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments. It should be noted that the accompanying drawings are all in a very simplified form and use non-precise ratios, only for the purpose of conveniently and clearly assisting in explaining the embodiments of the present invention.

[0068] As Figure 1 shown, a terminal device for automatically extinguishing fire after a solid rocket engine test run, the terminal device includes a gas pipe, a gas source collection system 1, a gas source control system 2, an end sealing mechanism 3, a flexible compensation mechanism 4, a floating adjustment mechanism 5, wherein:

[0069] The gas source collection 1 system is fixedly connected to the gas source control system 2 through a gas pipe;

[0070] The gas source control system 2 is connected to the end sealing mechanism 3 through a gas pipe;

[0071] The end sealing mechanism 3 is fixedly connected to the flexible compensation mechanism 4;

[0072] The flexible compensation mechanism 4 is connected to the gas source control system 2 through a gas pipe;

[0073] The flexible compensation mechanism 4 is fixedly connected to the floating adjustment mechanism 5.

[0074] The gas source gathering system 1 includes a support frame 1-1, a gas cylinder group 1-2, a gas supply pipeline 1-3, a pressure display unit 1-4, and a pressure control unit 1-5, as Figure 2 shown;

[0075] The support frame 1-1 is used to fix the gas source gathering system 1;

[0076] The gas cylinder group 1-2 is arranged inside the support frame 1-1, the gas supply pipeline 1-3 is connected to the gas cylinder group 1-2, the pressure display unit 1-4 and the pressure control unit 1-5 are arranged on the gas supply pipeline 1-3, and the pressure display unit 1-4 is located between the gas cylinder group and the pressure control unit 1-5;

[0077] The gas source control system 2 includes an external protection housing 2-1, a blowing control unit 2-2, a compensation gas supply control unit 2-3, and a compensation gas supply adjustment unit 2-4, as Figure 3 shown;

[0078] The external protection housing 2-1 is fixed on the wall, the blowing control unit 2-2 and the compensation gas supply control unit 2-3 are both arranged inside the external protection housing 2-1, and the compensation gas supply adjustment unit 2-4 is fixed on the outside of the external protection housing 2-1;

[0079] The end sealing mechanism 3 includes a gas supply pipe 3-1, a sealing fixing plate 3-2, a sealing support frame 3-3, an extension support 3-4, a transfer transition plate 3-5, an air outlet pipe 3-6, and a flexible sealing layer 3-7, as Figure 4 、 Figure 5 shown;

[0080] The gas supply pipe 3-1 is arranged horizontally and is connected to the gas source control system 2; the sealing fixing plate 3-2 is arranged vertically on the gas supply pipe 3-1; the sealing support frame 3-3 is fixedly connected to the sealing fixing plate 3-2 by bolts; the extension support 3-4 is installed on the right end face of the sealing fixing plate 3-2 by bolts; the transfer transition plate 3-5 is fixedly installed on the right side of the extension support 3-4; the air outlet pipe 3-6 passes through the sealing support frame 3-3 and is arranged parallel to the gas supply pipe 3-1, and the flexible sealing layer 3-7 is coated and bonded on the outside of the sealing support frame 3-3;

[0081] The flexible compensation mechanism 4 includes a floating unit 4-1 and a fixing unit 4-2; the floating unit 4-1 is fixedly installed on the right side of the transfer transition plate 3-5, and the fixing unit 4-2 is arranged on the right side of the floating unit 4-1 and is flexibly connected to the floating unit 4-1, as Figure 6 shown;

[0082] The floating adjustment mechanism 5 includes an adapter support 5-1, a flange shaft 5-2, a first rotating bearing 5-3, a support positioning plate 5-4, an actuator docking plate 5-5, a transmission gear 5-6, a first shaft support 5-7, a second rotating bearing 5-8, a second shaft support 5-9, a transmission rack 5-10, a stop locking knob 5-11, and an adjustment handwheel 5-12, as Figure 6 , Figure 7 shown;

[0083] The adapter support 5-1 is arranged on the end face of the fixed unit 4-2 and fixedly connected thereto;

[0084] The flange shaft 5-2 is fixedly installed on the adapter support 5-1 through a threaded interface;

[0085] The first rotating bearing 5-3 is arranged outside the flange shaft 5-2 and rotatably connected thereto;

[0086] The support positioning plate 5-4 passes through the first rotating bearing 5-3 and is perpendicularly arranged with the flange shaft 5-2;

[0087] The actuator docking plate 5-5 is perpendicularly arranged with the support positioning plate 5-4 and fixedly connected thereto;

[0088] The transmission gear 5-6 passes through the flange shaft 5-2 and is fixedly connected thereto by key connection;

[0089] The first shaft support 5-7 is arranged on the end face of the support positioning plate 5-4 and fixedly connected thereto;

[0090] The second rotating bearing 5-8 is fixedly installed inside the first shaft support 5-3;

[0091] The second shaft support 5-9 is arranged on the right side of the first shaft support 5-7 and fixed on the support positioning plate 5-4;

[0092] The transmission rack 5-10 passes through the first shaft support 5-7 and the second shaft support 5-9 and is installed inside the second rotating bearing 5-8;

[0093] The stop locking knob 5-11 is arranged on the right side of the second shaft support 5-8 and fixedly installed on the transmission rack 5-10;

[0094] The adjustment handwheel 5-12 is arranged on the right side of the stop locking knob 5-11 and fixedly installed on the transmission rack 5-10;

[0095] Preferably, the floating unit 4-1 remains in a floating state during the docking and sealing process between the end sealing mechanism 3 and the nozzle of the solid rocket motor 6, and also remains in a floating state during the disconnection process of the end sealing mechanism 3 from the nozzle of the solid rocket motor 6, and remains in a fixed state during the rest of the working process;

[0096] Preferably, the flexible sealing layer 3-7 is made of an elastic ablation-resistant material, and produces a small elastic deformation when docking with the nozzles of solid rocket motors with different expansion angles.

[0097] The preparation method of the flexible sealing layer 3-7 includes the following steps:

[0098] (1) The preparation tooling for the flexible sealing layer 3-7 is a combined pressing die 7, which includes an inner die 7-1 and an outer die 7-2, as Figure 9 、 Figure 10 、 Figure 11 shown;

[0099] (2) Select an adiabatic material with an elongation rate higher than 500% and an ablation rate lower than 0.07 mm / s for circular cutting. Fill the cut blanks into the outer die 7-2 in the order of placing the one with a larger outer diameter at the bottom and the one with a smaller outer diameter at the top. Place the inner die 7-1 into the outer die 7-2 to ensure that the guide posts provided on the outer die 7-2 enter the central hole of the inner membrane 7-1.

[0100] (3) Place the combined pressing die on a flat vulcanizing machine, control the temperature range of 150°C - 160°C, and preheat the adiabatic material for 2 min - 3 min.

[0101] (4) According to the pressing process of 1 MPa - 3 MPa, 5 MPa - 7 MPa, 8 MPa - 10 MPa, 12 MPa - 15 MPa, press in sequence, and the pressure holding time is 2 min - 3 min, 2 min - 3 min, 2 min - 3 min, 10 min - 15 min respectively.

[0102] (5) Use a triangular knife to cut off the waste edges of the blanks on the outside of the combined pressing die, and push up the inner membrane through the bolts provided on the outer die to complete demolding.

[0103] During operation, as Figures 9 - 11 shown, apply the combined pressing die 7, and press the flexible sealing layer 3-7 according to the preparation method and steps of the flexible sealing layer 3-7, using a flat vulcanizing machine (a conventional device, omitted in the figure); as Figures 4 - 5 shown, apply epoxy resin bonding glue (a conventional material, omitted in the figure), evenly coat and bond the flexible sealing layer 3-7 on the sealing support frame 3-3, place the transition plate 3-5 horizontally downward, and cure it upside down for more than 48 h to form the end sealing mechanism 3; as Figure 1 and Figure 3As shown in the figure, a connected gas path system is built, and the compensation air supply adjustment unit 2-4 is externally connected to an air compressor pump (a conventional device, omitted in the figure). The compensation air supply control unit 2-3 is adjusted to keep the floating unit 4-1 in a fixed state. After the solid rocket engine 6 is tested in the afterburner (a conventional device, omitted in the figure), the adjusting handwheel 5-12 is rotated so that the seal support frame 3-3 of the end seal mechanism 3 is coaxial with the combustion chamber. The stop locking knob 5-11 is adjusted to lock the adjusting handwheel 5-12. Before the solid rocket engine 6 is tested, as Figure 2 shown in the figure, the pressure control unit 1-5 of the gas source collection system 1 is turned on, and the compensation air supply control unit 2-4 is program-controlled (a conventional control strategy, omitted in the figure) so that the floating unit 4-1 remains in a floating state during the docking and sealing process between the end seal mechanism 3 and the solid rocket engine nozzle, and remains in a floating state during the process of the end seal mechanism 3 disengaging from the solid rocket engine 6 nozzle, and remains in a fixed state during the rest of the working process. The blowing control unit 2-2 is program-controlled (a conventional control strategy, omitted in the figure) so that the blowing action is started after the end seal mechanism 3 is docked and sealed with the solid rocket engine 6. After the solid rocket engine 6 is tested, as Figure 8 shown in the figure, under the action of an automatic execution device (a conventional power device, omitted in the figure), the end seal mechanism 3 slowly completes the docking process when approaching the solid rocket engine 6 nozzle. When the flexible seal layer 3-7 contacts the solid rocket engine nozzles with different expansion angles and other structural dimensions, it generates a small elastic deformation to achieve effective sealing. As Figure 1 shown in the figure, the inert gas is blown into the combustion chamber of the solid rocket engine 6 through the intake pipe 3-1, and the blown-out flame is discharged from the outlet pipe 3-6. The flame in the combustion chamber of the solid rocket engine 6 is extinguished, and the hot and cold gas environment exchange is continuously completed until the temperature in the combustion chamber drops below the ablation ignition point of the insulation layer, and the ablation of the insulation layer stops.

[0104] Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and decorations made to the above embodiments based on the technical essence of the present invention without departing from the technical solution of the present invention all belong to the protection scope of the technical solution of the present invention. The content not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.

Claims

1. An end device for automatically extinguishing fire after a test run of a solid rocket motor, characterized in that The end device includes an air pipe, an air source gathering system, an air source control system, an end sealing mechanism, a flexible compensation mechanism, and a floating adjustment mechanism, where: The air source gathering system is connected to the air source control system through an air pipe; The air source control system is connected to the end sealing mechanism through an air pipe; The end sealing mechanism is fixedly connected to the flexible compensation mechanism; The flexible compensation mechanism is connected to the air source control system through an air pipe; The flexible compensation mechanism is fixedly connected to the floating adjustment mechanism.

2. The end device for automatically extinguishing fire after the test run of a solid rocket motor according to claim 1, characterized in that, The air source gathering system includes a support frame, a gas cylinder group, a gas supply pipeline, a pressure display unit, and a pressure control unit; The support frame is used to fix the air source gathering system; The gas cylinder group is arranged inside the support frame, the gas supply pipeline is connected to the gas cylinder group, the pressure display unit and the pressure control unit are arranged on the gas supply pipeline, and the pressure display unit is located between the gas cylinder group and the pressure control unit.

3. The end device for automatically extinguishing fire after a test run of a solid rocket motor according to claim 1, characterized in that, The air source control system includes an external protection housing, a blowing control unit, a compensation air supply control unit, and a compensation air supply adjustment unit; The external protection housing is fixed on the wall, the blowing control unit and the compensation air supply control unit are both arranged inside the external protection housing, and the compensation air supply adjustment unit is fixed on the outside of the external protection housing.

4. The end device for automatically extinguishing fire after a test run of a solid rocket motor according to claim 1, characterized in that The end sealing mechanism includes an air supply pipe, a sealing fixed plate, a sealing support frame, an extension support, a transfer transition plate, an air outlet pipe, and a flexible sealing layer; The air supply pipe is horizontally arranged and connected to the air source control system; The sealing fixed plate is vertically arranged on the air supply pipe; The sealing support frame is fixedly connected to the sealing fixed plate by bolts; The extension support is installed on the right end face of the sealing fixed plate by bolts; The transfer transition plate is fixedly installed on the right side of the extension support; The air outlet pipe passes through the sealing support frame and is arranged parallel to the air supply pipe; The flexible sealing layer is coated and bonded on the outside of the sealing support frame.

5. The end device for automatically extinguishing fire after a test run of a solid rocket motor according to claim 1, characterized in that, The flexible compensation mechanism includes a floating unit and a fixed unit; the floating unit is fixedly installed on the right side of the transfer transition plate, and the fixed unit is arranged on the right side of the floating unit and is flexibly connected to the floating unit.

6. The end device for automatic fire extinguishing after the test run of a solid rocket motor according to claim 1, characterized in that, The floating adjustment mechanism includes a transfer support, a flange shaft, a rotating bearing I, a support positioning plate, an actuator docking plate, a transmission gear, a shaft support I, a rotating bearing II, a shaft support II, a transmission rack, a stop locking knob, and an adjustment handwheel; The transfer support is arranged on the end face of the fixed unit and is fixedly connected to it; The flange shaft is fixedly installed on the transfer support through a threaded interface; The rotating bearing I is arranged outside the flange shaft and is rotatably connected to it; The support positioning plate passes through the rotating bearing I and is arranged perpendicular to the flange shaft; The actuator docking plate is arranged perpendicular to the support positioning plate and is fixedly connected to it; The transmission gear passes through the flange shaft and is fixedly connected to it by key connection; The shaft support I is arranged on the end face of the support positioning plate and is fixedly connected to it; The rotating bearing II is fixedly installed inside the shaft support I; The shaft support II is arranged on the right side of the shaft support I and is fixed on the support positioning plate; The transmission rack passes through the first shaft support and the second shaft support and is installed inside the second rotating bearing; The stop locking knob is arranged on the right side of the second shaft support and fixedly installed on the transmission rack; The adjusting handwheel is arranged on the right side of the stop locking knob and fixedly installed on the transmission rack.

7. The end device for automatically extinguishing fire after a test run of a solid rocket motor according to claim 5, characterized in that, The floating unit remains in a floating state during the docking and sealing process between the end sealing mechanism and the engine nozzle, and also remains in a floating state during the process of the end sealing mechanism disengaging from the engine nozzle, and remains fixed during the rest of the working process.

8. The end device for automatically extinguishing fire after the test run of a solid rocket motor according to claim 4, characterized in that, The flexible sealing layer is made of an elastic ablative-resistant material.

9. The end device for automatically extinguishing fire after the test run of a solid rocket motor according to claim 4 or 8, characterized in that, The preparation method of the flexible sealing layer includes the following steps: (1) The preparation tooling of the flexible sealing layer uses a combined pressing die, including an inner die and an outer die; (2) Select an adiabatic material with an elongation rate higher than 500% and an ablation rate lower than 0.07 mm / s for circular cutting. Fill the cut blank into the outer die in the order of placing the one with a larger outer diameter dimension at the bottom and the one with a smaller outer diameter dimension at the top. Place the inner die into the outer die to ensure that the guide post set on the outer die enters the central hole of the inner membrane; (3) Place the combined pressing die on a flat vulcanizing machine, control the temperature range of 150°C - 160°C, and preheat the adiabatic material for 2 min - 3 min; (4) According to the pressing process of 1 MPa - 3 MPa, 5 MPa - 7 MPa, 8 MPa - 10 MPa, 12 MPa - 15 MPa, press in sequence, and the pressure holding time is 2 min - 3 min, 2 min - 3 min, 2 min - 3 min, 10 min - 15 min respectively; (5) Use a triangular knife to cut off the waste edge of the blank outside the combined pressing die, and push up the inner membrane through the bolts set on the outer die to complete the demolding.

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