Positioning and stress application tool for solid rocket engine in threaded connection mode

Abstract

The invention discloses a solid rocket engine positioning stress application tool for a threaded connection mode, and belongs to the technical field of solid rocket engine final assembly. The tool comprises a circular ring base, a pressing plate and a bolt. A plurality of limiting bolts are evenly distributed on the annular surface of the annular base and fix the annular base to the end face of the top cover through threaded holes in the end face of the front skirt of the engine. Two sides of the pressing plate are fixed on the inner diameter surface of the circular base. The pressing plate is provided with a plurality of screw holes, and the positions of the screw holes are aligned with the corresponding pressure measuring screw holes in the center of the top cover. And a plurality of bolts are respectively screwed into the pressure measuring screw holes in the top cover through the screw holes in the pressing plate, so that the pressing plate is fixed. The designed tool is pressed on the top cover, and the manual hand holding state is replaced.

Description

Technical Field

[0001] The invention relates to a solid rocket engine positioning and afterburner tooling for a threaded connection method, belonging to the technical field of solid rocket engine assembly. Background Art

[0002] When the threaded engine is formally assembled, the sealing ring is installed and tightened with a special assembly tool. When assembling with the original tool, one person is required to hold the tool, two people apply force symmetrically, and one person is required to provide safety supervision. The sealing ring and the sealing groove are both lateral sealing structures. It is time-consuming and laborious to apply a larger torque, and it is impossible to assemble them in one go. If necessary, sleeves need to be added on both sides of the handle to lengthen the force arm and tighten. The operator's work intensity is high and repeated force application is required, which poses a risk of thread biting.

[0003] When tightening with an extended sleeve, the tooling cannot be positioned and falls off the slot. The tooling and sleeve may cause harm to the assembler, and there is a risk of damaging the product. The use of the tooling will cause uneven force on the mating surface, and there is a risk of damage to the threads and sealing rings on the mating surface, affecting the assembly quality. There is a current situation of uneven force during the force application process of the assembly operation, which causes the putty on the mating surface to not be evenly squeezed during the assembly process, the filling gap is uneven, and the seal is damaged. Defects in assembly tooling seriously affect the batch production rhythm of the product. A process mode or tool that can meet the simultaneous positioning and uniform force application work is needed to eliminate the safety hazards of tooling slipping and bumping operations.

[0004] At present, no relevant technology or similar structure has been found through searching the public database for relevant positioning and booster tooling. Summary of the invention

[0005] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and propose a solid rocket engine positioning and boosting tooling for a threaded connection method, wherein the tooling is pressed against the engine top cover by threaded connection with the engine top cover, thereby replacing the manual hand-holding state.

[0006] The technical solution of the present invention is:

[0007] A solid rocket engine positioning and afterburner tooling for threaded connection, comprising a ring base, a pressure plate and bolts;

[0008] The annular base is annular, and a plurality of limiting bolts are evenly distributed on the surface of the annular ring. All the limiting bolts pass through the same number of threaded holes on the end face of the front skirt of the engine to fix the annular base on the end face of the top cover;

[0009] The pressure plate is a flat plate structure, and both sides of the pressure plate are fixed to the inner diameter surface of the circular base; a plurality of screw holes are arranged on the pressure plate, and the number of the screw holes is the same as the number of the pressure measuring holes in the center of the top cover, and the position of each screw hole is aligned with the corresponding pressure measuring hole in the center of the top cover;

[0010] The plurality of bolts are respectively passed through the screw holes on the pressure plate and screwed into the pressure measuring screw holes on the top cover to fix the pressure plate.

[0011] Furthermore, the materials of the ring base, the pressure plate and the bolts are all 304 stainless steel.

[0012] Furthermore, the outer diameter of the annular base is the same as the diameter of the top cover of the solid rocket engine.

[0013] Furthermore, a handle is provided on each side of the circular ring base to facilitate symmetrical force application during assembly.

[0014] Furthermore, the length of the pressing plate is greater than the inner diameter of the annular base.

[0015] Furthermore, the bolts have the same diameter as the screw holes on the pressure plate and the pressure measuring holes on the top cover.

[0016] Furthermore, the method of fixing the top cover using the tool is as follows:

[0017] Step 1: Assemble and check the ring base, turn the ring base and the multiple limit bolts on it left and right, and check the smoothness of the rod movement;

[0018] Step 2: Install the ring base on the end face of the engine top cover, adjust the ring base to fit tightly against the docking end face, so that multiple limit bolts can be installed into the mounting holes on the end face of the engine top cover, and move the ring base to check whether the limit bolts are installed in place;

[0019] Step 3: Install the pressure plate to the corresponding position on the surface of the ring base;

[0020] Step 4: Screw multiple bolts through the screw holes on the pressure plate into the pressure measuring screw holes on the top cover to fix the pressure plate;

[0021] Step 5: Confirm again that all bolts are tightened and there is no shaking of the tooling.

[0022] The advantages of the present invention compared with the prior art are:

[0023] (1) The present invention uses higher strength materials, optimizes the tooling structure, and is convenient and fast to use. In order to reduce costs and improve work efficiency, based on mass production, 304 stainless steel materials are used to increase tooling strength, improve processing accuracy, and process molding in one step. The original half-ring design is optimized into a circular tooling for uniform force.

[0024] (2) The tooling of the present invention enables the engine to be assembled in one go, thus avoiding potential safety hazards. Due to the uniform force, the factors of thread seizure and seal ring damage are reduced. The efficiency of top cover assembly is improved, and when the operator applies torque, the tooling is eliminated from falling off, while the safety risk of injuries caused by tooling falling off is eliminated. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0026] Figure 1 This is a schematic diagram of the structure of the positioning and force adding tooling according to an embodiment of the present invention;

[0027] Figure 2 It is a side view of a positioning and force adding tooling according to an embodiment of the present invention;

[0028] Figure 3 This is a schematic diagram of the structure of a circular ring base according to an embodiment of the present invention;

[0029] Figure 4 This is a schematic diagram of the structure of a pressing plate according to an embodiment of the present invention;

[0030] Figure 5 Schematic diagram of the bolt structure of an embodiment of the present invention. DETAILED DESCRIPTION

[0031] The exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.

[0032] The present invention proposes a solid rocket engine positioning and afterburner tooling for a threaded connection method, such as Figure 1 , Figure 2 As shown, it includes a circular ring base 1, a pressing plate 2, bolts 3, and bolts 4. The circular ring base 1, the pressing plate 2, the bolts 3, and the bolts 4 are connected and installed.

[0033] The ring base 1 is circular, and four limit bolts are evenly distributed on the arc of the ring base surface. Figure 3As shown. Four limit bolts are used to fix the annular base to the top cover end face through the four threaded holes on the front skirt end face. After fixation, place the pressure plate 2 in the middle of the annular base 1, align the screw holes on the pressure plate with the center pressure measuring screw holes on the top cover, and screw bolts 3 and 4 through the screw holes on the pressure plate 2 into the two Φ18mm pressure measuring screw holes on the top cover to fix the pressure plate.

[0034] The ring base 1 is the core part of the present invention, and its diameter is the same as that of the top cover of the solid rocket engine. The ring tooling has two handles on both sides, which is convenient for operators to apply force symmetrically during assembly.

[0035] The pressing plate 2 is in the shape of a strip plate, such as Figure 4 As shown, its length is greater than the inner diameter of the annular base 1.

[0036] Bolt 3 and bolt 4 are the same, such as Figure 5 As shown, the diameter is the same as that of the pressure plate screw hole and the top cover pressure measuring hole.

[0037] The entire tooling is made of 304 stainless steel to increase tooling strength, improve processing accuracy, and process in one step. The original half-ring design is optimized into a circular tooling for uniform force.

[0038] The method for assembling the solid rocket engine positioning and afterburner tooling in one step is as follows:

[0039] Step 1: Assemble and check the symmetrical four-point limit fixing outer side circular ring base 1, turn the circular ring base 1 and the four limit bolts thereon to the left and right, and check the smoothness of the movement of the rod.

[0040] Step 2: Install the ring base 1 on the end face of the engine top cover, adjust the tooling surface of the ring base 1 to be close to the docking end face, ensure that the four limit bolts can be installed into the mounting holes on the end face of the engine top cover, and check whether the limit bolts of the movable ring base 1 are installed in place, there is no installation gap with the docking end face, and there will be no movement with the installation surface.

[0041] Step 3: Move the pressure plate 2 to the corresponding position on the surface of the ring base 1.

[0042] Step 4: Screw the bolts 3 through the screw holes on the pressure plate 2 into the two Φ18mm pressure measuring screw holes on the top cover to fix the pressure plate.

[0043] Step 5: Screw the bolt 4 through the screw hole on the pressure plate 2 into the two Φ18mm pressure measuring screw holes on the top cover to fix the pressure plate.

[0044] Step 6: Confirm again that all bolts are tightened and the tooling does not shake.

[0045] Step 7: After processing, remove the two bolts installed on the pressure plate.

[0046] Step 8: Remove the four limit bolts on the pressure plate and the ring base 1 in turn, clean the surface and threaded holes of the ring base 1, and properly store the tooling to prevent rust and deformation.

[0047] The tooling designed by the present invention is applied to the physical assembly process of an engine product, and result data is collected. Table 1 lists the time required for the assembly of the engine top cover in recent times.

[0048] Table 1 Engine top cover assembly schedule

[0049]

[0050] The above-described embodiments are only preferred specific implementations of the present invention. Common changes and substitutions made by those skilled in the art within the scope of the technical solution of the present invention should be included in the protection scope of the present invention.

Claims

1. A solid rocket engine positioning and afterburner tooling for threaded connection, characterized in that: Including a ring base, a pressure plate and bolts; The annular base is annular, and a plurality of limiting bolts are evenly distributed on the surface of the annular ring. All the limiting bolts pass through the same number of threaded holes on the end face of the front skirt of the engine to fix the annular base on the end face of the top cover; The pressure plate is a flat plate structure, and both sides of the pressure plate are fixed on the inner diameter surface of the circular base; a plurality of screw holes are arranged on the pressure plate, and the number of the screw holes is the same as the number of the pressure measuring holes in the center of the top cover, and the position of each screw hole is aligned with the corresponding pressure measuring screw hole in the center of the top cover; The plurality of bolts are respectively passed through the screw holes on the pressure plate and screwed into the pressure measuring screw holes on the top cover to fix the pressure plate.

2. The solid rocket engine positioning and boosting tooling for threaded connection according to claim 1 is characterized in that: The materials of the ring base, the pressure plate and the bolts are all 304 stainless steel.

3. The solid rocket engine positioning and afterburner tooling for threaded connection according to claim 1 is characterized in that: The outer diameter of the annular base is the same as the diameter of the top cover of the solid rocket engine.

4. The solid rocket engine positioning and boosting tooling for threaded connection according to claim 1, characterized in that: A handle is provided on each side of the circular ring base to facilitate symmetrical force application during assembly.

5. The solid rocket engine positioning and boosting tooling for threaded connection according to claim 1, characterized in that: The length of the pressing plate is greater than the inner diameter of the annular base.

6. The solid rocket engine positioning and boosting tooling for threaded connection according to claim 1, characterized in that: The bolt has the same diameter as the screw hole on the pressure plate and the pressure measuring screw hole on the top cover.

7. The solid rocket engine positioning and boosting tooling for threaded connection according to claim 1, characterized in that: The method for fixing the top cover using the tooling is as follows: Step 1: Assemble and check the ring base, turn the ring base and the multiple limit bolts on it left and right, and check the smoothness of the rod movement; Step 2: Install the ring base on the end face of the engine top cover, adjust the ring base to fit tightly against the mating end face, so that multiple limit bolts can be installed into the mounting holes on the end face of the engine top cover, and move the ring base to check whether the limit bolts are installed in place; Step 3: Install the pressure plate to the corresponding position on the surface of the ring base; Step 4: Screw multiple bolts through the screw holes on the pressure plate into the pressure measuring screw holes on the top cover to fix the pressure plate; Step 5: Confirm again that all bolts are tightened and there is no shaking of the tooling.

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