Rocket engine thrust chamber copper inner wall slotting quick-release tooling and use method

Abstract

The application discloses a rocket engine thrust chamber copper inner wall milling groove quick dismounting tool and a use method thereof, wherein the tool comprises a clamping body, a positioning plate, a pressing plate, a nut, a lifting nut, a first lifting ring screw, a handle and a bottom plate; the bottom of the clamping body is connected with the bottom plate; the positioning plate is connected with the top of the clamping body; a rocket engine thrust chamber copper inner wall workpiece is sleeved on the outer surface of the whole composed of the clamping body and the positioning plate; the pressing plate is pressed through a mandrel and the upper end of the rocket engine thrust chamber copper inner wall workpiece; the nut is threadedly connected with the mandrel, and the lower end of the nut is pressed against the upper end of the pressing plate; the lifting nut is connected with the upper end of the mandrel, and the first lifting ring screw is connected with the lifting nut; and the bottom plate is connected with an external machine tool workbench. The application has the advantages of convenient and accurate positioning, quick and convenient dismounting and safe and reliable use.

Description

Technical Field

[0001] This invention belongs to the field of machining technology for rocket engine components, and particularly relates to a quick-release tooling for milling grooves on the copper inner wall of a rocket engine thrust chamber and its usage method. Background Technology

[0002] The copper inner wall is a key component of the thrust chamber of a liquid oxygen / kerosene rocket engine. With advancements in rocket engine theory and technology, the design of this component has become increasingly precise, with stricter requirements for dimensional and geometric tolerances, and more complex surface structures. One type of rocket engine thrust chamber copper inner wall has a maximum diameter of nearly 1 meter, while its wall thickness is less than 10 mm. Due to limitations in its volume, mass, and wall thickness, positioning, clamping, and machining processes are all highly challenging. Existing tooling relies on its outer surface perfectly fitting the inner surface of the copper inner wall to achieve circumferential and axial positioning, thus ensuring machining accuracy. However, in actual machining, although machining accuracy can be guaranteed using this method, due to cutting forces, gravity, and atmospheric pressure after fitting, the copper inner wall component often becomes extremely tightly fitted to the tooling, sometimes even becoming impossible to detach from it.

[0003] In actual production, to solve this problem, methods such as hammering with a wooden mallet or pouring hot water are usually used to detach the parts from the tooling. However, these methods are all trial work and cannot be guaranteed to be effective. They are also time-consuming and labor-intensive, which seriously affects the production schedule. In addition, when the copper inner wall of the rocket engine thrust chamber is clamped to the corresponding tooling, the combined volume and mass of the two are relatively large, making it difficult to control precisely during operation. This often leads to accidental damage to the product during the disassembly of the parts from the tooling after processing. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a quick-release tooling and method for milling grooves on the inner copper wall of a rocket engine thrust chamber, which has the advantages of convenient and accurate positioning, quick and convenient tire removal, and safe and reliable use.

[0005] The objective of this invention is achieved through the following technical solution: a quick-release fixture for milling grooves on the copper inner wall of a rocket engine thrust chamber, comprising: a clamping body, a positioning plate, a pressure plate, a nut, a lifting nut, a first eye bolt, a handle, and a base plate; wherein, the bottom of the clamping body is connected to the base plate; the positioning plate is connected to the top of the clamping body; the copper inner wall workpiece of the rocket engine thrust chamber is sleeved on the outer surface of the integral formed by the clamping body and the positioning plate; the pressure plate passes through a mandrel and presses against the upper end of the copper inner wall workpiece of the rocket engine thrust chamber; the nut is threadedly connected to the mandrel, and the lower end of the nut presses against the upper end of the pressure plate; the lifting nut is connected to the upper end of the mandrel, and the first eye bolt is connected to the lifting nut; the base plate is connected to an external machine tool worktable.

[0006] The aforementioned quick-release tooling for milling grooves in the copper inner wall of the rocket engine thrust chamber also includes: a second eye screw; wherein the second eye screw is screwed into the top of the positioning plate; the screwing in of the second eye screw can lift the positioning plate and the workpiece in the copper inner wall of the rocket engine thrust chamber together from the clamping body.

[0007] The aforementioned quick-release tooling for milling grooves in the copper inner wall of the rocket engine thrust chamber also includes: T-bolts and nuts; wherein, the base plate is connected to the external machine tool worktable via T-bolts and nuts.

[0008] The aforementioned quick-release tooling for milling grooves in the copper inner wall of the rocket engine thrust chamber also includes: a first screw; wherein the positioning plate is connected to the top of the clamping body via the first screw.

[0009] The aforementioned quick-release tooling for milling grooves in the copper inner wall of the rocket engine thrust chamber also includes: a second screw; wherein the bottom of the clamping body is connected to the base plate via the second screw.

[0010] In the aforementioned quick-release tooling for milling grooves in the copper inner wall of the rocket engine thrust chamber, the first eye bolt is an M30 eye bolt.

[0011] In the aforementioned quick-release tooling for milling grooves in the copper inner wall of the rocket engine thrust chamber, the second eye bolt is an M12 eye bolt.

[0012] In the aforementioned quick-release tooling for milling grooves in the copper inner wall of the rocket engine thrust chamber, the nut is an M16 shoulder nut.

[0013] In the aforementioned quick-release tooling for milling grooves in the copper inner wall of the rocket engine thrust chamber, the first screw is an M12 socket head cap screw.

[0014] In the aforementioned quick-release tooling for milling grooves in the copper inner wall of the rocket engine thrust chamber, the second screw is an M20 socket head cap screw.

[0015] A method for using a quick-release tooling for milling grooves on the copper inner wall of a rocket engine thrust chamber, comprising:

[0016] The clamp body is connected to the base plate by the second screw. The positioning plate passes through the upper end spindle of the clamp body. Then, the positioning plate is rotated circumferentially to align the zero-position scale line on the surface of the positioning plate with the scale line of the clamp body. Finally, the clamp body is fixed to the positioning plate by the first screw.

[0017] The workpiece of the inner copper wall of the rocket engine thrust chamber is sleeved on the outer surface of the whole consisting of the clamp and the positioning plate; the pressure plate passes through the mandrel and presses against the upper end face of the workpiece of the inner copper wall of the rocket engine thrust chamber, and the nut is threadedly connected to the mandrel so that the lower end of the nut presses against the upper end of the pressure plate.

[0018] Connect the lifting nut to the upper end of the mandrel, and connect the first eye bolt to the lifting nut; use the first eye bolt to lift and place the copper inner wall workpiece of the rocket engine thrust chamber onto the machine tool table, and connect the base plate to the machine tool table using T-bolts and nuts; then perform external machining and milling on the copper inner wall workpiece of the rocket engine thrust chamber.

[0019] After processing, the lifting nut, nut, pressure plate, and first screw are disassembled in sequence. Then, the second eye screw is tightened to lift the positioning plate and the workpiece of the copper inner wall of the rocket engine thrust chamber together from the clamp. Then, the lifting equipment is connected to the second eye screw, and the lifting equipment lifts the positioning plate. Relying on the force of the contact between the positioning plate and the workpiece of the copper inner wall of the rocket engine thrust chamber, the workpiece of the copper inner wall of the rocket engine thrust chamber rises and detaches from the clamp, thus realizing the rapid disassembly of the workpiece.

[0020] Compared with the prior art, the present invention has the following advantages:

[0021] (1) The split-type combined positioning structure of the present invention can fully inherit the advantages of the original tooling. The positioning is simple and reliable. During the machining of the outer shape and milling groove of the copper inner wall of the rocket engine thrust chamber, the positioning accuracy and machining accuracy can be effectively guaranteed.

[0022] (2) This invention solves the problem that the milling and turning fixtures originally used for the copper inner wall of the rocket engine thrust chamber are inconvenient to disassemble after processing, difficult to control the disassembly process, and have low efficiency.

[0023] (3) The present invention eliminates the instability of the original manual trial disassembly of parts, avoids accidental damage to the product during the disassembly process, and improves production reliability. Attached Figure Description

[0024] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0025] Figure 1 This is a schematic diagram of the structure of the quick-release tooling for milling grooves on the copper inner wall of the rocket engine thrust chamber provided in an embodiment of the present invention. Detailed Implementation

[0026] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the disclosure to those skilled in the art. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0027] Figure 1 This is a schematic diagram of the structure of the quick-release tooling for milling grooves on the copper inner wall of a rocket engine thrust chamber provided in an embodiment of the present invention. Figure 1 As shown, the quick-release fixture for milling grooves on the copper inner wall of the rocket engine thrust chamber includes: a clamping body 1, a positioning plate 2, a pressure plate 4, a nut 5, a lifting nut 6, a first lifting eye bolt 7, a handle 8, and a base plate 10. Among these,

[0028] The bottom of the fixture body 1 is connected to the base plate 10; the positioning plate 2 is connected to the top of the fixture body 1; the workpiece of the inner copper wall of the rocket engine thrust chamber is sleeved on the outer surface of the integral assembly formed by the fixture body 1 and the positioning plate 2; the pressure plate 4 passes through the mandrel and presses against the upper end of the workpiece of the inner copper wall of the rocket engine thrust chamber; the nut 5 is threadedly connected to the mandrel, and the lower end of the nut 5 presses against the upper end of the pressure plate 4; the lifting nut 6 is connected to the upper end of the mandrel, and the first eye screw 7 is connected to the lifting nut 6; the base plate 10 is connected to the external machine tool worktable. Specifically, the first eye screw 7 is an M30 eye screw.

[0029] After the clamping body 1 and the positioning plate 2 are engaged, they fit tightly against the inner surface of the copper inner wall of the thrust chamber to achieve precise positioning; then, the interaction of the nut 5, the pressure plate 4, and the M12 socket head cap screw 3 completes the firm clamping; finally, the lifting nut 6 and the M30 eye bolt 7 make it easy to move and transport.

[0030] After processing, the lifting nut 6, nut 5, pressure plate 4, and M12 socket head cap screw 3 are disassembled in sequence. Then, four evenly distributed M12 eye bolts 9 are screwed on and the lifting equipment is used to gradually lift the positioning plate 2. The force of the positioning plate 2 and the copper inner wall workpiece in contact with each other drives the entire copper inner wall of the thrust chamber to rise and separate from the clamping body 1, thus realizing the rapid disassembly of the workpiece.

[0031] The fixture body 1 and the positioning plate 2 are separate parts that are integrated and machined together. After the two are fixed together, the outer surface of the assembly is precisely machined according to the inner wall and cavity dimensions of the copper inner wall of the rocket engine thrust chamber, and the surface roughness is no higher than Ra1.6. After the integrated machining is completed, a zero-position scale line is drawn along the generatrix direction at the junction of the outer surfaces so that the original contour can be quickly found when disassembled and reused.

[0032] The tapering structure of the part where the positioning plate 2 fits against the copper inner wall of the rocket engine thrust chamber ensures that the positioning plate 2 can drive the copper inner wall to rise synchronously during the lifting process.

[0033] In addition to the 4-Ф20 through holes on the positioning plate 2 that can be connected to the clamp body 1, there are also 4 evenly distributed M12 threaded through holes. When unloading the tire, the second lifting eye screw 9 can be symmetrically and gradually turned to make it press down against the end face of the clamp body 1. Under the action of mutual force, the copper inner wall of the thrust chamber will loosen from the clamp body 1, which can ensure the safety and reliability of subsequent hoisting and lifting.

[0034] The dimensions of the small end mandrel of the fixture body 1 are as follows: and It can be precisely positioned with the inner holes of the positioning plate 2 and the pressure plate 4 respectively. The small end face of the clamping body 1 has 4 M12 threaded holes evenly distributed, which can be fixedly connected to the positioning plate 2 by M12 internal hexagonal head screws 3. The large end face has 8 M20 threaded holes evenly distributed, which can be fixedly connected to the base plate 10 by M20 internal hexagonal head screws 11.

[0035] like Figure 1 As shown, the quick-release fixture for milling grooves in the copper inner wall of the rocket engine thrust chamber also includes a second eye screw 9; wherein, the second eye screw 9 is screwed into the top of the positioning plate 2; the screwing in of the second eye screw 9 can lift the positioning plate 2 and the workpiece of the copper inner wall of the rocket engine thrust chamber together from the fixture 1. Specifically, the second eye screw 9 is an M12 eye screw.

[0036] like Figure 1 As shown, the quick-release tooling for milling grooves in the copper inner wall of the rocket engine thrust chamber also includes: T-bolts 12 and nuts 13; wherein, the base plate 10 is connected to the external machine tool worktable via T-bolts 12 and nuts 13. Specifically, nut 13 is an M16 shoulder nut.

[0037] like Figure 1As shown, the quick-release tooling for milling grooves in the copper inner wall of the rocket engine thrust chamber also includes: a first screw 3; wherein, the positioning plate 2 is connected to the top of the clamping body 1 via the first screw 3. Specifically, the first screw 3 is an M12 socket head cap screw.

[0038] like Figure 1 As shown, the quick-release tooling for milling grooves in the copper inner wall of the rocket engine thrust chamber also includes a second screw 11; wherein, the bottom of the clamping body 1 is connected to the base plate 10 via the second screw 11. Specifically, the second screw 11 is an M20 socket head cap screw.

[0039] The copper inner wall workpiece of the rocket engine thrust chamber is fitted onto the outer surface of the integral assembly consisting of fixture 1 and positioning plate 2. The fit quality between the fixture and the inner surface of the thrust chamber copper inner wall workpiece during use directly affects the dimensional and positional accuracy of subsequent machining. This fit quality can be described by the fit coefficient η. Therefore, the fit coefficient of the thrust chamber copper inner wall workpiece is:

[0040] Where η is the fitting coefficient, the larger the coefficient value, the better the fitting effect; a, b, and c are the roundness values ​​of the outer surface of the fixture 1 at the small end, middle, and large end, respectively; M is the pre-tightening torque of screw 3; Δh is the absolute value of the deviation between the measured height of the workpiece on the inner wall of the thrust chamber and the theoretical value; and R1, R2, and R3 are the radii of the inner surface at the small end, middle, and large end, respectively.

[0041] As can be seen from the formula, there are many parameters that affect the fit quality between the tooling and the inner surface of the copper wall. These mainly include the roundness of the tooling surface, the pre-tightening torque, and the diameter and height error of the inner surface of the copper wall. In addition to the variable factors of the product to be processed, the tooling itself includes the pre-tightening torque and the accuracy of the outer surface of the fixture body 1.

[0042] The tooling used in this application significantly affects the bonding effect by adjusting the tightening torque of screw 3. Excessive torque leads to significant deformation of the copper inner wall, severely impacting subsequent processing. Conversely, insufficient torque results in an incomplete bonding. Generally, controlling the tightening torque of each screw within the range of 20–25 N·m, based on actual conditions, ensures good bonding of over 99% of the coverage area while keeping product deformation under control, thus meeting processing requirements.

[0043] This embodiment also provides a method for using a quick-release tooling for milling grooves on the copper inner wall of a rocket engine thrust chamber, the specific steps of which are as follows:

[0044] Step 1: Position the fixture body 1 on the base plate 10 using M20 socket head cap screws 11. The positioning plate 2 passes through the upper end spindle of the fixture body 1 to complete accurate positioning. Then, rotate the positioning plate 2 circumferentially so that the zero-position scale line on its surface is aligned with the scale line on the fixture body 1. Finally, fix the fixture body 1 and the positioning plate 2 using M12 socket head cap screws 3.

[0045] Step 2: Place the workpiece of the inner copper wall of the rocket engine thrust chamber on the fixture, and after the inner surface of the workpiece is in close contact with the outer surface of the fixture, the pressure plate 4 passes through the mandrel cover on the upper end face of the inner copper wall workpiece, and then tighten the nut 5 to achieve complete clamping.

[0046] Step 3: After the workpiece is mounted, it is lifted and placed on the machine tool worktable by lifting nuts 6 and M30 eye bolts 7. Tighten T-bolts 12 and shoulder nuts 13 to fix it on the platform. Then the machining program can be started to perform machining such as turning the outer shape and milling grooves.

[0047] Step 4: After processing, disassemble the lifting nut 6, nut 5, pressure plate 4, and M12 socket head cap screw 3 in sequence. Then screw on the four evenly distributed M12 eye bolts 9 to lift the positioning plate 2 and the copper inner wall workpiece together from the clamping body 1. Then, connected by the M12 eye bolts 9, the lifting equipment gradually lifts the positioning plate 2. Relying on the force of the part of the positioning plate 2 and the copper inner wall that are in contact with each other, the entire thrust chamber copper inner wall rises and separates from the clamping body 1, realizing the rapid disassembly of the workpiece.

[0048] The fixture body 1 is positioned on the base plate 10 by M20 socket head cap screws 11. The positioning plate 2 is then positioned and connected to the fixture body 1 by M12 socket head cap screws 3. During processing, the two are combined and machined as a single unit according to the inner surface contour parameters of the copper inner wall of the rocket engine thrust chamber, so that they can fit and be positioned in close contact with the inner surface of the copper inner wall after mating. In actual processing, after the copper inner wall of the rocket engine thrust chamber is adjusted to fit tightly with the positioning plate 2 and the fixture body 1, the pressure plate 4 passes through the positioning plate 2 on the mandrel cover, and then the nuts 5 are tightened in sequence to achieve reliable clamping. The lifting nut 6 and the M30 eye bolt 7 are all fixed to the fixture body 1 by threaded connection to facilitate lifting and handling during processing. After processing, the lifting nut 6, nut 5, pressure plate 4, and M12 socket head cap screw 3 are removed in sequence. Then, four evenly distributed M12 eye bolts 9 are screwed on. During the operation of the lifting equipment, the positioning plate 2 is gradually raised. The force of the part of the positioning plate 2 that is in contact with the copper inner wall drives the entire copper inner wall of the thrust chamber to rise and detach from the clamping body 1, thereby realizing the rapid disassembly of the workpiece.

[0049] The split-type combined positioning structure of this invention fully inherits the advantages of the original tooling, offering simple and reliable positioning. During the machining of the outer shape and milling grooves of the copper inner wall of the rocket engine thrust chamber, it effectively ensures positioning and machining accuracy. This invention solves the problems of inconvenient disassembly of parts, difficulty in controlling the disassembly process, and low efficiency associated with the original milling and turning fixtures used for the copper inner wall of the rocket engine thrust chamber. This invention eliminates the instability of manual, trial-and-error disassembly of parts, avoids accidental damage to the product during disassembly, and improves production reliability. This invention can be used for pressing tires, turning outer diameters, and milling grooves on the thin-walled copper inner wall of the rocket engine thrust chamber. It offers advantages such as convenient and accurate positioning, quick and easy tire removal, and safe and reliable use.

[0050] Although the present invention has been disclosed above with reference to 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 solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A quick-release tooling for milling grooves on the copper inner wall of a rocket engine thrust chamber, characterized in that... include: The clamping body (1), positioning plate (2), pressure plate (4), nut (5), lifting nut (6), first eye bolt (7), handle (8), and base plate (10); among which, The bottom of the clamping body (1) is connected to the base plate (10); The positioning plate (2) is connected to the top of the clamping body (1); The copper inner wall workpiece of the rocket engine thrust chamber is sleeved on the outer surface of the integral body composed of the clamping body (1) and the positioning plate (2); The pressure plate (4) passes through the mandrel and presses against the upper end of the workpiece on the copper inner wall of the rocket engine thrust chamber; The nut (5) is threaded to the spindle, and the lower end of the nut (5) presses against the upper end of the pressure plate (4); The lifting nut (6) is connected to the upper end of the mandrel, and the first eye bolt (7) is connected to the lifting nut (6); The base plate (10) is connected to the external machine tool worktable; It also includes: the second eye bolt (9); wherein, The second eye bolt (9) is screwed into the top of the positioning plate (2); The screwing in of the second eye bolt (9) can lift the positioning plate (2) and the workpiece of the copper inner wall of the rocket engine thrust chamber from the clamp body (1).

2. The quick-release tooling for milling grooves on the copper inner wall of the rocket engine thrust chamber according to claim 1, characterized in that... Also includes: T-bolts (12) and nuts (13); wherein, The base plate (10) is connected to the external machine tool worktable by T-bolts (12) and nuts (13).

3. The quick-release tooling for milling grooves on the copper inner wall of the rocket engine thrust chamber according to claim 1, characterized in that... Also includes: First screw (3); where, The positioning plate (2) is connected to the top of the clamping body (1) by the first screw (3).

4. The quick-release tooling for milling grooves on the copper inner wall of the rocket engine thrust chamber according to claim 1, characterized in that... Also includes: Second screw (11); wherein, The bottom of the clamping body (1) is connected to the base plate (10) by the second screw (11).

5. The quick-release tooling for milling grooves on the copper inner wall of the rocket engine thrust chamber according to claim 1, characterized in that: The first eye bolt (7) is an M30 eye bolt.

6. The quick-release tooling for milling grooves on the copper inner wall of the rocket engine thrust chamber according to claim 1, characterized in that: The second eye bolt (9) is an M12 eye bolt.

7. The quick-release tooling for milling grooves on the copper inner wall of the rocket engine thrust chamber according to claim 2, characterized in that: The nut (13) is an M16 shoulder nut.

8. The quick-release tooling for milling grooves on the copper inner wall of the rocket engine thrust chamber according to claim 3, characterized in that: The first screw (3) is an M12 socket head cap screw.

9. A method for using a quick-release tooling for milling grooves on the inner copper wall of a rocket engine thrust chamber, characterized in that... include: The clamp body (1) is connected to the base plate (10) by the second screw (11). The positioning plate (2) passes through the upper spindle of the clamp body (1). Then, the positioning plate (2) is rotated circumferentially to align the zero-position scale line on the surface of the positioning plate (2) with the scale line of the clamp body (1). Finally, the clamp body (1) and the positioning plate (2) are fixed by the first screw (3). The workpiece of the inner copper wall of the rocket engine thrust chamber is sleeved on the outer surface of the whole composed of the clamp (1) and the positioning plate (2); the pressure plate (4) passes through the mandrel and presses on the upper end face of the workpiece of the inner copper wall of the rocket engine thrust chamber, and the nut (5) is threadedly connected to the mandrel so that the lower end of the nut (5) presses against the upper end of the pressure plate (4); Connect the lifting nut (6) to the upper end of the mandrel, and connect the first eye bolt (7) to the lifting nut (6); use the first eye bolt (7) to lift and place the copper inner wall workpiece of the rocket engine thrust chamber onto the machine tool table, and connect the base plate (10) to the machine tool table using T-bolts (12) and nuts (13); then perform external machining and milling on the copper inner wall workpiece of the rocket engine thrust chamber. After processing, the lifting nut (6), nut (5), pressure plate (4), and first screw (3) are disassembled in sequence. Then, the second lifting eye screw (9) is tightened to lift the positioning plate (2) and the workpiece of the copper inner wall of the rocket engine thrust chamber from the clamping body (1). Then, the lifting equipment is connected to the second lifting eye screw (9), and the lifting equipment lifts the positioning plate (2). The workpiece of the copper inner wall of the rocket engine thrust chamber is lifted by the force of the part of the positioning plate (2) and the workpiece of the copper inner wall of the rocket engine thrust chamber. The workpiece of the copper inner wall of the rocket engine thrust chamber rises and gets off the clamping body (1) to achieve rapid disassembly of the workpiece.

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