Solid rocket engine circular seam heat treatment equipment and heat treatment method

Abstract

The invention provides solid rocket engine circular seam heat treatment equipment and a heat treatment method, and relates to the technical field of welding, the heat treatment equipment comprises an equipment bottom beam, a driving box, a middle top bracket, a stand column, a driven box, a heat treatment cross beam and a heater; the equipment bottom beam is arranged on the ground, and a driving box, a middle top bracket, a stand column and a driven box are installed on the equipment bottom beam. The driving box is used for fixing one side of a solid rocket engine shell rotating piece. The driven box is used for fixing the other side of the solid rocket engine shell rotating piece. The middle top bracket and the stand column are arranged between the driving box and the driven box; the middle top bracket is used for carrying out supporting and auxiliary clamping on the solid rocket engine shell rotating part; the columns are used for supporting heat-treatment beams; a heater is arranged on the heat treatment cross beam; the heater is used for conducting heat treatment on an annular welding seam in the solid rocket engine shell rotating piece in the process that the solid rocket engine shell rotating piece is driven by the driving box to rotate.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of welding technology, in particular to a solid rocket engine girth joint heat treatment equipment and heat treatment method. BACKGROUND

[0002] In the welding process of high-alloy structural steel (typical for example rocket engine shell), the girth joint is a typical key welding joint. Because the high-alloy structural steel itself has high alloy element content, complex organization and large quenching tendency, the welding joint often has large residual stress and uneven organization after welding. If heat treatment measures are not taken in time, cracks are likely to form in the weld and heat affected zone, which seriously affects the mechanical properties and service life of the welded structure.

[0003] The existing post-weld heat treatment process generally adopts a centralized batch treatment method, that is, after welding is completed, a certain number of workpieces are sent into a heat treatment furnace for overall heat treatment.

[0004] However, centralized heat treatment can cause some workpieces to be unable to be heat treated in time, poor timeliness, and cracks are likely to occur in the weld. Centralized heat treatment requires the entire workpiece to be heated to the process temperature, even if only the weld part needs to be treated, the entire workpiece must be heated, resulting in energy waste and great electric energy consumption. After centralized heat treatment, the parts outside the weld also change in organization, which requires additional mechanical processing or surface treatment, increasing the workload and production cost of subsequent processes and reducing the girth joint heat treatment efficiency. SUMMARY

[0005] In view of the above deficiencies of the prior art, the purpose of the embodiments of the present application is to provide a solid rocket engine girth joint heat treatment equipment and heat treatment method, which can solve the technical problems of poor timeliness, great electric energy consumption, increased workload and production cost of subsequent processes, and reduced girth joint heat treatment efficiency of the existing centralized heat treatment technology.

[0006] In a first aspect, the embodiments of the present application provide a solid rocket engine girth joint heat treatment equipment, comprising: an equipment bottom beam, a driving box, a middle top bracket, a stand column, a driven box, a heat treatment cross beam and a heater; The equipment bottom beam is arranged on the ground, and the driving box, the middle top bracket, the stand column and the driven box are mounted on the equipment bottom beam; The driving box is used for fixing one side of a solid rocket engine shell rotary part and can drive the solid rocket engine shell rotary part to rotate; The driven box is used for fixing the other side of the solid rocket engine shell rotary part; The middle top bracket and the stand column are arranged between the driving box and the driven box; The middle top bracket is used for supporting and assisting clamping the solid rocket engine shell rotary piece; The column is used for supporting the heat treatment crossbeam; The heat treatment crossbeam is provided with the heater; The heater is used for heat treating the annular weld on the solid rocket engine shell rotary piece in the process that the solid rocket engine shell rotary piece is rotated by the driving box.

[0007] The second aspect of the embodiment of the present application provides a solid rocket engine annular seam heat treatment method applied to the solid rocket engine annular seam heat treatment device. Step 1: initializing the driving box and the driven box; Step 2: carrying the solid rocket engine shell rotary piece on the middle top bracket, lifting the solid rocket engine shell rotary piece through the middle top bracket, and making the solid rocket engine shell rotary piece and the main shaft of the driving box and the main shaft of the driven box center coincide; Step 3: fixing one side of the solid rocket engine shell rotary piece through the movement of the driving box; Step 4: fixing the other side of the solid rocket engine shell rotary piece through the movement of the driven box; Step 5: retracting the middle top bracket, and separating the solid rocket engine shell rotary piece from the middle top bracket; Step 6: rotating the solid rocket engine shell rotary piece through the driving box; Step 7: heating the annular weld of the solid rocket engine shell rotary piece through the heater in the process that the solid rocket engine shell rotary piece rotates, and stopping heating after keeping warm for a preset time length; Step 8: taking away the heat of the annular weld through the circulating cooling water, and slowly cooling the annular weld; Step 9: restoring the driving box and the driven box to the initial position, and carrying the heat-treated solid rocket engine shell rotary piece away from the heat treatment device.

[0008] The technical scheme provided by the embodiment of the present application has at least the following beneficial effects: (1) In the embodiment of the present application, the solid rocket engine annular seam heat treatment device can perform online heat treatment on the annular weld immediately after welding, without transferring the whole shell to a large heat treatment furnace, avoiding cumbersome links such as carrying and loading, having good timeliness, and being capable of effectively eliminating welding residual stress and preventing cracks in the weld and heat affected zone.

[0009] (2) In the embodiment of the present application, the annular weld can be locally heat treated by the heater, without heating the whole workpiece, saving the power consumption.

[0010] (3) In the embodiment of the present application, the annular weld can be locally heat treated by the heater, avoiding the change of the structure of the part other than the weld due to heating, without additional post-treatment, reducing the subsequent processing workload and production cost, improving the efficiency of the annular seam heat treatment, making the appearance of the shell more beautiful, and more meeting the requirements of high precision and high quality of parts in the field of aerospace. BRIEF DESCRIPTION OF DRAWINGS

[0011] The accompanying drawings are included to provide a further understanding of the embodiments of the present application, and are incorporated herein and constitute a part of the detailed description. It should be apparent to those skilled in the art that the accompanying drawings are only a few embodiments of the present application and other drawings can be obtained by those skilled in the art without creative work.

[0012] Figure 1 is a structural front view of a solid rocket engine annular seam heat treatment equipment provided by the embodiment of the present application.

[0013] Figure 2 is a structural side view of a solid rocket engine annular seam heat treatment equipment provided by the embodiment of the present application.

[0014] Figure 3 is a structural schematic view of a driving box provided by the embodiment of the present application.

[0015] Figure 4 is a structural schematic view of a driven box provided by the embodiment of the present application.

[0016] Figure 5 is a flowchart of a solid rocket engine annular seam heat treatment method provided by the embodiment of the present application.

[0017] BRIEF DESCRIPTION OF DRAWINGS: 1 - equipment bottom beam; 2 - driving box; 21 - first cylinder fixing seat; 22 - first cylinder; 23 - pneumatic chuck; 24 - clamping jaw; 25 - motor; 26 - speed reducer; 27 - first main shaft; 3 - middle top bracket; 4 - stand column; 5 - driven box; 51 - second cylinder fixing seat; 52 - second cylinder; 53 - second main shaft; 54 - tail top mold; 6 - heat treatment cross beam; 7 - heater; 8 - solid rocket engine shell rotary part; 9 - heating monitor. DETAILED DESCRIPTION

[0018] In order to make the personnel in the art better understand the technical solutions in the embodiments of the present application, the technical solutions of the present application will be clearly and completely described below in conjunction with the drawings. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. It should be understood that these descriptions are only exemplary and are not used to limit the scope of the present application. Based on the embodiments of the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor should belong to the scope of protection of the present application.

[0019] In addition, in the following description, the description of well-known structures and techniques is omitted to avoid unnecessary confusion of the concepts disclosed in the present application.

[0020] The exemplary embodiments will be described in detail below with reference to the accompanying drawings. In the following description, the same numbers in different drawings represent the same or similar elements unless otherwise expressed. The embodiments described in the following exemplary embodiments do not represent all the embodiments consistent with the present application.

[0021] Reference is made to the drawings that accompany the specification Figures 1 to 4 The structure of the solid rocket engine annular gap heat treatment equipment provided by the embodiments of the present application comprises: an equipment bottom beam 1, a driving box 2, a middle top bracket 3, a stand column 4, a driven box 5, a heat treatment cross beam 6 and a heater 7.

[0022] The equipment bottom beam 1 is arranged on the ground and is the foundation and load-bearing member of the whole equipment. The driving box 2, the middle top bracket 3, the stand column 4 and the driven box 5 are installed on the equipment bottom beam 1, and the overall stability and structural strength of the equipment are ensured through the equipment bottom beam 1.

[0023] Optionally, the equipment bottom beam 1 is made of high-quality carbon structural steel, so that the equipment bottom beam 1 has sufficient bearing capacity and anti-deformation ability, and can meet the support requirements of the large rocket engine shell during clamping and rotation.

[0024] The driving box 2 is used for fixing one side of the solid rocket engine shell rotary part 8 and can drive the solid rocket engine shell rotary part 8 to rotate.

[0025] The driven box 5 is used for fixing the other side of the solid rocket engine shell rotary part 8.

[0026] Optionally, the box bodies of the driving box 2 and the driven box 5 are made of high-quality alloy steel, so as to ensure that the driving box 2 and the driven box 5 have sufficient strength and durability when bearing high power driving and long time working.

[0027] The middle top bracket 3 and the column 4 are arranged between the driving box 2 and the driven box 5. The middle top bracket 3 is used to support and assist clamping of the solid rocket engine shell rotary part 8. When clamping the workpiece, the middle top bracket 3 lifts the solid rocket engine shell rotary part 8 through a supporting wheel or a pneumatic lifting mechanism, so that the axis of the solid rocket engine shell rotary part 8 is coaxial with the main shaft; after the solid rocket engine shell rotary part 8 is clamped by the driving box 2 and the driven box 5, the middle top bracket 3 can be lowered to be separated from the solid rocket engine shell rotary part 8, so as to avoid interference with rotation.

[0028] The column 4 is used to support the heat treatment cross beam 6. The heat treatment cross beam 6 is provided with the heater 7. The heat treatment cross beam 6 ensures that the heater 7 can be adjusted according to the position of the weld, so as to adapt to different models and sizes of rocket engine shells. The heater 7 is used to heat treat the annular weld on the solid rocket engine shell rotary part 8 in the process that the solid rocket engine shell rotary part 8 is rotated by the driving box 2. This local heat treatment of the annular weld only avoids the excessive heating of the non-weld area in the traditional overall heat treatment, and realizes energy-saving, rapid and targeted weld heat treatment.

[0029] In a possible implementation, the solid rocket engine annular seam heat treatment equipment further comprises a heating monitor 9. The heating monitor 9 is used to monitor the temperature at the weld position of the solid rocket engine shell rotary part. Through the heating monitor 9, the temperature at the weld is accurately monitored in real time, and the setting of heating temperature and holding time is simple and convenient.

[0030] In a possible implementation, the heater 7 and the heating monitor 9 can move on the heat treatment cross beam 6. Such a design makes the equipment have stronger adaptability and flexibility: on the one hand, the heater 7 and the heating monitor 9 can be accurately positioned to the annular seam position according to different models and different sizes of solid rocket engine shells, so as to ensure accurate heating and real-time monitoring of the weld area; on the other hand, the moving structure enables the same equipment to meet the process requirements of multiple workpieces, avoids configuring multiple equipment for different specifications of workpieces, improves the universality and economy; meanwhile, in the case that the weld is long or different in position along the axial direction, the heater 7 can be moved to cover the whole weld, so as to realize uniform heating and high-quality heat treatment, thereby significantly improving the reliability and production efficiency of the process.

[0031] In a possible implementation, the active box 2 comprises: a first cylinder fixing seat 21, a first cylinder 22, a pneumatic chuck 23, and a clamping jaw 24. The first cylinder fixing seat 21 is fixedly arranged on the wall surface of the active box 2. The first cylinder 22 is fixedly arranged on the first cylinder fixing seat 21. The first cylinder 22 is connected with the pneumatic chuck 23. The pneumatic chuck 23 is provided with the clamping jaw 24. The first cylinder 22 is used to drive the active box 2 to move and control the pneumatic chuck 23 to move, so as to realize clamping or loosening of the clamping jaw 24. The active box 2 clamps one side of the solid rocket engine shell rotary part 8 through the clamping jaw 24, and can realize automatic, rapid and reliable clamping and releasing. The clamping jaw 24 reliably abuts against the end of the solid rocket engine shell rotary part 8, so as to ensure the coaxiality and stability of the solid rocket engine shell rotary part 8 in the rotating process, and avoid uneven heat treatment of the weld due to eccentricity or sliding. The overall structure is compact, the transmission chain is short, the energy consumption and the failure rate are reduced, and the equipment has the advantages of high precision, high reliability and high efficiency.

[0032] In a possible implementation, the active box 2 further comprises: an electric motor 25, a speed reducer 26, and a first main shaft 27. The electric motor 25 is connected with the first main shaft 27 through the speed reducer 26. The electric motor 25 is connected with the first main shaft 27 through the speed reducer 26, can realize reasonable rotating speed and large torque output while providing sufficient power, and ensures the stability and controllability of the large solid rocket engine shell rotary part 8 in the rotating process. The pneumatic chuck 23 is arranged on the first main shaft 27. The active box 2 drives the first main shaft 27 to rotate through the driving of the electric motor 25, and then drives the solid rocket engine shell rotary part 8 to rotate through the first main shaft 27. The pneumatic chuck 23 is arranged at the front end of the first main shaft 27, so that the driving and clamping form an integrated structure, can directly and efficiently transmit power to the workpiece, and reduces energy loss and error caused by intermediate links. The overall structure is compact and the transmission efficiency is high, which not only improves the rotating precision and operation reliability, but also meets the strict requirements for uniform speed rotation and high coaxiality of the workpiece in the weld heat treatment process.

[0033] In a possible implementation, the driven box 5 comprises: a second cylinder fixing seat 51, a second cylinder 52, a second main shaft 53, and a tail top die 54. The second cylinder fixing seat 51 is fixedly arranged on the wall surface of the driven box 5. The second cylinder 52 is fixedly arranged on the second cylinder fixing seat 51, and the second cylinder 52 is used to drive the movement of the driven box 5. The second main shaft 53 is installed on the driven box 5, and the tail top die 54 is arranged on the second main shaft 53. The driven box 5 is tightly pressed against the other side of the solid rocket engine shell rotary piece 8 through the tail top die 54, so as to ensure the coaxiality and stability of the solid rocket engine shell rotary piece 8 during rotation, and prevent uneven heating of the weld due to workpiece shaking or deviation; at the same time, the pressing mode driven by the cylinder has the characteristics of convenient operation and stable clamping force, can effectively reduce the artificial operation burden, and improve the clamping efficiency, so that the whole heat treatment process is more safe, accurate and efficient.

[0034] In a possible implementation, the solid rocket engine annular seam heat treatment equipment further comprises: a cold water machine. The cold water machine is used to transmit circulating cooling water, and heat generated at the annular weld after heat treatment is taken away by the circulating cooling water, so as to slow cool the annular weld, avoid the generation of organizational brittleness or new cracks due to too fast or too slow natural cooling, and effectively improve the reliability and service life of the solid rocket engine shell; at the same time, the circulating system of the cold water machine has the advantages of energy saving and environmental protection, high cooling efficiency, and reusable water resources, which can ensure process stability while reducing operation cost.

[0035] In a possible implementation, the middle top bracket 3 is arranged on the equipment bottom beam 1 in a liftable manner. The solid rocket engine shell rotary piece 8 is carried and placed on the middle top bracket 3, the solid rocket engine shell rotary piece 8 is lifted by the middle top bracket 3, and the solid rocket engine shell rotary piece 8 is made to be coaxial with the main shaft of the driving box 2 and the main shaft of the driven box 5, then one side of the solid rocket engine shell rotary piece 8 is fixed by the movement of the driving box 2. The other side of the solid rocket engine shell rotary piece 8 is fixed by the movement of the driven box 5. After the solid rocket engine shell rotary piece 8 is fixed, the middle top bracket 3 falls down, so that the solid rocket engine shell rotary piece 8 is separated from the middle top bracket 3. The middle top bracket 3 has the lifting function, can bear the support and positioning function in the initial stage of workpiece clamping, lift the heavy solid rocket engine shell rotary piece 8, and make the solid rocket engine shell rotary piece 8 accurately aligned with the main shaft center of the driving box 2 and the driven box 5, so as to ensure the coaxiality and precision of workpiece clamping; after the two ends of the workpiece are fixed, the middle top bracket 3 falls down and is separated from the workpiece, so as to avoid interference with the rotation of the workpiece. The structure not only reduces the difficulty in the process of workpiece carrying and clamping, and reduces the labor intensity, but also effectively prevents the workpiece from sagging or deviating due to self-weight, and ensures the stability, safety and processing quality in the process of weld heat treatment.

[0036] With reference to the accompanying drawings Figure 5 The solid rocket engine annular seam heat treatment method provided by the embodiment of the present application is applied to the solid rocket engine annular seam heat treatment device, and comprises the following steps. Step 1: initialize the driving box 2 and the driven box 5.

[0037] Step 2: carry the solid rocket engine shell rotating part 8 on the middle top bracket 3, lift the solid rocket engine shell rotating part 8 through the middle top bracket 3, and make the solid rocket engine shell rotating part 8 coincide with the center of the main shaft of the driving box 2 and the main shaft of the driven box 5.

[0038] Step 3: fix one side of the solid rocket engine shell rotating part 8 through the movement of the driving box 2.

[0039] Step 4: fix the other side of the solid rocket engine shell rotating part 8 through the movement of the driven box 5.

[0040] Step 5: retract the middle top bracket 3, and separate the solid rocket engine shell rotating part 8 from the middle top bracket 3.

[0041] Step 6: rotate the solid rocket engine shell rotating part 8 through the driving box 2.

[0042] Step 7: heat the annular weld of the solid rocket engine shell rotating part 8 in the process of rotation of the solid rocket engine shell rotating part 8 through the heater 7, and stop heating after keeping warm for a preset time length.

[0043] Step 8: take away the heat of the annular weld through the circulating cooling water, and slowly cool the annular weld.

[0044] Step 9: restore the driving box 2 and the driven box 5 to the initial position, and carry the solid rocket engine shell rotating part 8 after heat treatment away from the heat treatment device.

[0045] The technical scheme provided by the embodiment of the present application has at least the following beneficial effects: (1) In the embodiment of the present application, the solid rocket engine annular seam heat treatment device can perform online heat treatment on the annular weld immediately after welding, without the need to transfer the whole shell to a large heat treatment furnace, thereby avoiding cumbersome links such as carrying and furnace loading, having good timeliness, and being capable of effectively eliminating welding residual stress and preventing cracks in the weld and the heat affected zone.

[0046] (2) In the embodiment of the present application, the heater can perform local heat treatment on the annular weld, without the need to heat the whole workpiece, thereby saving electric energy consumption.

[0047] (3) In the embodiment of the present application, the annular weld can be locally heat treated by the heater, so that the parts other than the weld are not affected by the heat and do not change in structure, no additional post-processing is needed, the subsequent processing workload and production cost are reduced, the efficiency of the annular weld heat treatment is improved, the appearance of the shell is beautiful, and the high-precision and high-quality requirements of the aerospace field for parts are met.

[0048] The present application encompasses any substitutions, modifications, equivalent methods and solutions made to the essence and scope of the present application. In order to make the public have a thorough understanding of the present application, specific details are described in the preferred embodiments of the present application, and the present application can be fully understood without these details by those skilled in the art. In addition, in order to avoid unnecessary confusion to the essence of the present application, well-known methods, processes, procedures, elements and circuits are not described in detail.

[0049] Finally, it should be pointed out that the above embodiments are only used to illustrate the technical solutions of the embodiments of the present application, and not to limit them. Although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that the technical solutions recorded in the foregoing embodiments can be modified, or some technical features can be replaced by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application. Any changes or replacements easily thought of by those skilled in the art within the technical scope disclosed by the present application should be covered within the protection scope of the present application.

Claims

1. A heat treatment device for the circumferential seam of a solid rocket motor, characterized in that, include: Equipment bottom beam (1), drive box (2), top bracket (3), column (4), driven box (5), heat treatment crossbeam (6), and heater (7); The equipment bottom beam (1) is set on the ground, and the active box (2), the top bracket (3), the column (4) and the driven box (5) are installed on the equipment bottom beam (1). The active box (2) is used to fix one side of the solid rocket motor housing rotating part (8) and can drive the solid rocket motor housing rotating part (8) to rotate; The driven box (5) is used to fix the other side of the solid rocket motor housing rotating part (8); The top bracket (3) and the column (4) are arranged between the active box (2) and the driven box (5); The top bracket (3) is used to support and assist in clamping the solid rocket motor housing rotating component (8); The column (4) is used to support the heat treatment beam (6); The heater (7) is provided on the heat treatment beam (6); The heater (7) is used to heat treat the circumferential weld on the solid rocket motor housing rotating part (8) during the rotation driven by the active box (2).

2. The solid rocket motor circumferential seam heat treatment equipment according to claim 1, characterized in that, Also includes: Heating monitor (9); The heating monitor (9) is used to monitor the temperature at the weld position of the solid rocket motor housing rotating component.

3. The solid rocket motor circumferential seam heat treatment equipment according to claim 2, characterized in that, The heater (7) and the heating monitor (9) are movable on the heat treatment beam (6).

4. The solid rocket motor circumferential seam heat treatment equipment according to claim 1, characterized in that, The active housing (2) includes: a first cylinder mounting base (21), a first cylinder (22), a pneumatic chuck (23), and a gripper (24); The first cylinder mounting base (21) is fixedly mounted on the wall of the drive housing (2); The first cylinder (22) is fixedly mounted on the first cylinder mounting base (21). The first cylinder (22) is connected to the pneumatic chuck (23). The pneumatic chuck (23) is provided with the gripper (24). The first cylinder (22) is used to drive the active box (2) to move and control the pneumatic chuck (23) to move, so as to realize the clamping or releasing of the gripper (24). The active box (2) clamps one side of the solid rocket motor housing rotating part (8) through the gripper (24).

5. The solid rocket motor circumferential seam heat treatment equipment according to claim 4, characterized in that, The drive box (2) also includes: a motor (25), a reducer (26), and a first spindle (27); The motor (25) is connected to the first main shaft (27) via the reducer (26); The pneumatic chuck (23) is provided on the first spindle (27); The active housing (2) is driven by the electric motor (25) to rotate the first main shaft (27), which in turn drives the solid rocket motor housing rotating component (8) to rotate.

6. The solid rocket motor circumferential seam heat treatment equipment according to claim 1, characterized in that, The driven box (5) includes: a second cylinder mounting base (51), a second cylinder (52), a second main shaft (53), and a tail mold (54); The second cylinder mounting base (51) is fixedly installed on the wall of the driven box (5); The second cylinder (52) is fixedly mounted on the second cylinder mounting base (51), and the second cylinder (52) is used to drive the driven box (5) to move; The second spindle (53) is mounted on the driven box (5), and the tail top mold (54) is provided on the second spindle (53). The driven box (5) presses against the other side of the solid rocket motor housing rotating part (8) through the tail mold (54).

7. The solid rocket motor circumferential seam heat treatment equipment according to claim 1, characterized in that, Also includes: Chiller; The chiller is used to transmit circulating cooling water, which carries away the heat from the annular weld after heat treatment, thus slowly cooling the annular weld.

8. The solid rocket motor circumferential seam heat treatment equipment according to claim 1, characterized in that, The top bracket (3) is vertically mounted on the bottom beam (1) of the equipment; The solid rocket motor housing rotating component (8) is transported and placed on the central top bracket (3). The central top bracket (3) lifts the solid rocket motor housing rotating component (8) and makes the center of the solid rocket motor housing rotating component (8) coincide with the center of the main shaft of the active housing (2) and the main shaft of the driven housing (5). Then, by moving the active housing (2), one side of the solid rocket motor housing rotating component (8) is fixed; by moving the driven housing (5), the other side of the solid rocket motor housing rotating component (8) is fixed; after the solid rocket motor housing rotating component (8) is fixed, the central top bracket (3) falls back, so that the solid rocket motor housing rotating component (8) separates from the central top bracket (3).

9. The solid rocket motor circumferential seam heat treatment equipment according to claim 1, characterized in that, The active box (2) and the driven box (5) are made of high-quality alloy steel, and the bottom beam (1) of the equipment is made of high-quality carbon structural steel.

10. A method for heat treatment of the circumferential seam of a solid rocket motor, applied to the heat treatment equipment for the circumferential seam of a solid rocket motor as described in any one of claims 1 to 9, characterized in that, include: Step 1: Initialize the active box (2) and the passive box (5); Step 2: The solid rocket motor housing rotating component (8) is transported and placed on the top bracket (3). The top bracket (3) lifts the solid rocket motor housing rotating component (8) and makes the solid rocket motor housing rotating component (8) coincide with the center of the main shaft of the drive box (2) and the main shaft of the driven box (5). Step 3: By moving the active box (2), one side of the solid rocket motor housing rotating component (8) is fixed; Step 4: By moving the driven box (5), the other side of the solid rocket motor housing rotating part (8) is fixed; Step 5: Retract the top bracket (3) and separate the solid rocket motor casing rotating part (8) from the top bracket (3); Step 6: The active box (2) drives the solid rocket motor housing rotating component (8) to rotate; Step 7: During the rotation of the solid rocket motor housing rotating part (8), the heater (7) heats the annular weld of the solid rocket motor housing rotating part (8), and stops heating after holding the heat for a preset time. Step 8: Use circulating cooling water to remove the heat from the annular weld and slowly cool the annular weld. Step 9: Return the active box (2) and the driven box (5) to their initial positions, and move the heat-treated solid rocket motor housing rotating part (8) away from the heat treatment equipment.

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