An outer protection tooling suitable for manufacturing a liner of a rocket engine of different caliber

Abstract

The utility model belongs to solid motor propellant technical field discloses an outer protection tool suitable for different caliber rocket engine lining manufacturing, including tile (1), cushion block (2), wear -resisting strip (3), locating block (4), tensioning tool (5), the tile (1) includes two pieces of upper tile and a piece of lower tile, and the upper tile is a quarter of circular ring, and the lower tile is semicircular ring, and two pieces of upper tile one end is hinged with the both ends of lower tile respectively, and three can enclose a circular ring, and the other end of two pieces of upper tile is connected through tensioning tool (5), the cushion block (2) is evenly arranged in the inner side of upper tile, lower tile, wear -resisting strip (3) is fixed in the end face of upper tile, lower tile, and locating block (4) is set up at the connecting place of two pieces of upper tile. The utility model's technical scheme effectively guarantees the compactness and safety of outer protection tool and shell cooperation, improves production efficiency.

Description

Technical Field

[0001] This utility model belongs to the field of solid rocket propellant technology, specifically relating to an external protective tooling suitable for manufacturing the liner of rocket engines of different calibers. Background Technology

[0002] The liner of a composite solid propellant is a crucial component of a rocket engine's propellant charge. It possesses specific mechanical properties and flame-retardant capabilities, protecting the engine casing from ablation and ensuring the integrity of the propellant charge. Liner manufacturing involves uniformly coating a prepared side-packing slurry onto the inner surface of the casing or the insulation layer using a centrifugal coating process, followed by curing under specific temperature and time conditions. The liner molding process also affects adhesion; uniform coating is essential for good bonding. The liner directly impacts the rocket engine's internal ballistic performance and operational reliability, and is also a key factor influencing the service life of the composite solid propellant charge.

[0003] The centrifugal coating process for composite solid propellant liners involves horizontally mounting the casing on a chuck or rollers, and using the high-speed rotation of the casing to deposit the liner slurry onto the inner wall of the casing. It is then cured under specific temperature and time conditions to form the liner. Because some metal casings have easily damaged structures such as external attachments and accessories on their outer surface, or because non-metallic casings require high protection of their outer surface, protective tooling is designed during the centrifugal manufacturing process to prevent damage to the casing during operation. Currently, the outer protective tooling for liner manufacturing consists of two semi-circular bearings with felt inside, connected by bolts. During installation, the lower half is first placed on a bracket, the casing is hoisted onto the bracket, and then the upper half of the outer protective tooling is attached to the casing to match the pre-placed half, and then tightened with bolts. Custom tooling is required for engines of different calibers, resulting in high costs, difficult on-site management, complex installation processes, and high labor intensity. Utility Model Content

[0004] (a) Technical problems to be solved

[0005] The technical problem this utility model aims to solve is that different caliber engines require customized tooling, which results in high costs, difficult on-site management, complex installation processes, and high labor intensity.

[0006] (II) Technical Solution

[0007] To solve the above-mentioned technical problems, this utility model provides an external protective tooling suitable for manufacturing the liner of rocket engines of different calibers, including a bearing 1, a pad 2, a wear-resistant strip 3, a positioning block 4, and a tensioning tool 5;

[0008] The bearing 1 includes two upper bearings and one lower bearing. The upper bearing is a quarter-circle shape, and the lower bearing is a semi-circle shape. One end of the two upper bearings is hinged to both ends of the lower bearing, and the three can form a ring. The other ends of the two upper bearings are connected by a tensioning tool 5. The pads 2 are evenly distributed on the inner sides of the upper and lower bearings. The wear-resistant strips 3 are fixed to the end faces of the upper and lower bearings. The positioning block 4 is set at the connection of the two upper bearings.

[0009] Furthermore, the joint between the two upper tiles is provided with support ears.

[0010] Furthermore, the tightening tool is a puller.

[0011] Furthermore, the bearing plate is matched with the outer diameter of the shell.

[0012] Furthermore, the thickness of the pads can be adjusted to accommodate changes in the shell diameter.

[0013] Furthermore, the wear-resistant strip is made of stainless steel and contacts the retaining wheel of the coating machine housing support mechanism.

[0014] (III) Beneficial Effects

[0015] Compared with existing technologies, this utility model has the following advantages: it can be quickly adapted to the manufacturing of rocket engine liners of different calibers, balancing ease of operation and reliability of protection; by selecting suitable pads and optimizing the fitting method, rapid adaptation is achieved; the clamping method is optimized, reducing the labor intensity of clamping installation; and it effectively ensures the tightness and safety of the fit between the outer protective tooling and the shell, improving production efficiency. Attached Figure Description

[0016] Figure 1 This utility model provides an external protective tooling for the manufacture of engine liners for rockets of different calibers;

[0017] Figure 2 This is a schematic diagram of a tile-holding structure.

[0018] Figure 3 This is a schematic diagram of the pad block;

[0019] Figure 4 This is a schematic diagram of a wear-resistant strip;

[0020] Figure 5 This is a schematic diagram of the positioning block;

[0021] Figure 6 This is a diagram illustrating the tightening tool. Detailed Implementation

[0022] To make the objectives, contents, and advantages of this utility model clearer, the specific embodiments of this utility model will be described in further detail below with reference to the accompanying drawings and examples.

[0023] The external protective tooling provided in this embodiment, suitable for manufacturing the liner of rocket engines of different calibers, includes a bearing 1, a pad 2, a wear-resistant strip 3, a positioning block 4, and a tightening tool 5.

[0024] The two upper and lower bearing plates are connected by a pin, allowing the upper bearing plates to rotate open or close around the pin. After tightening, the two upper bearing plates are secured with a fixing pin. The anti-wear strip is fixed to the end face of the bearing plate using countersunk screws. The pad is fixed to the inner wall of the bearing plate using countersunk screws. The positioning block is fixed to the bearing plate using flat-end set screws. Tightening tool 5 is a puller.

[0025] The bearing is designed to match the outer diameter of the housing, made of aluminum alloy with a yield strength of over 110MPa and a tensile strength of over 205MPa. This ensures the required yield and tensile strength for tightening the tooling, guaranteeing stability and reliability during use. It employs a split, fan-shaped aluminum alloy plate, including a lower bearing and two upper bearings, connected in a ring by high-strength cylindrical pins. To ensure a tight fit between the outer protective tooling and the housing, the inner diameter of the outer protective tooling should be smaller than the housing diameter after the pads are installed. This ensures that when the housing falls into the bearing, it will make close contact with the upper end of the lower bearing, leaving a gap between the bottom of the lower bearing and the housing. Therefore, the fan shape of the lower bearing is not perfectly shaped; the center of the upper arc is slightly higher than the center of the lower arc, with a height difference of approximately 3mm.

[0026] A removable pad is installed inside the annular frame, and its thickness can be adjusted to accommodate changes in the shell diameter. The material is high-temperature resistant and high-strength, ensuring stable and reliable operation. The pad has a certain degree of elasticity to prevent damage to the shell. Made of high-temperature resistant polyurethane, the pad can withstand temperatures ≥200℃. The coefficient of friction between the pad and the shell is low.

[0027] The hardness of the pad is approximately Shore hardness (40-60), and it will not damage the housing during the tightening process.

[0028] The wear-resistant strip is made of stainless steel and comes into contact with the guide roller of the coating machine housing support mechanism. It needs to be wear-resistant and is secured with countersunk screws. This ensures that the outer protective fixture is not interfered with during rotation. Stainless steel plates are installed on both sides for wear resistance, and countersunk screws are used to prevent interference between the fixture and the guide roller during rotation.

[0029] The positioning block and the fixing pin are used to tighten the bearing. When tightening, the fixing pin is passed through the through hole of the two upper bearings. During the tightening process, the through hole may not be aligned and the pin cannot pass through smoothly. Therefore, the positioning block and matching ball positioning pin are set to guide and align the bearings during the tightening process.

[0030] The tightening tool utilizes the radial contraction force of a puller (tightening bolt) to clamp the outer protective fixture onto the housing, forming a ring constraint. The puller tool has two claws that tighten by rotating a screw, thus clamping the fixture. When using the puller tool to disassemble and secure the pin, the tightening mechanism only requires tightening one bolt, compared to the traditional fixture which requires tightening four bolts. This reduces the workload and allows for quick assembly and disassembly by a single person.

[0031] The work process is as follows:

[0032] Select pad 3 according to the engine diameter, and install the pad onto the bearing 1 using countersunk screws. Hoist the bearing above the support rollers of the covering equipment bracket, remove the fixing pin, and leave the bearing in an open position. Hoist the engine above the bearing, and slowly lower it using the crane control. After the engine falls, close the bearing, insert the two claws of the tightening tool 5 into the corresponding fixing holes of the bearing, and tighten the nut on the screw using the tool to clamp the fixture. When the positioning block 4 guides the two bearing mating holes above to align, hammer the fixing pin into the mating hole and remove the tightening tool. Start the support rollers to rotate, which drives the outer protective fixture to rotate, thereby driving the engine to rotate, meeting the centrifugal covering requirements. The support mechanism's retaining wheel blocks the side end face of the outer protective fixture to prevent axial movement of the fixture and engine, and the wear-resistant strip 3 prevents wear on the fixture.

[0033] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present utility model, and these improvements and modifications should also be considered within the protection scope of the present utility model.

Claims

1. An external protective tooling suitable for manufacturing the liner of rocket engines of different calibers, characterized in that, Includes bearing plate (1), pad block (2), wear-resistant strip (3), positioning block (4), and tensioning tool (5); The bearing (1) includes two upper bearings and one lower bearing. The upper bearing is a quarter ring and the lower bearing is a semi ring. One end of the two upper bearings is hinged to both ends of the lower bearing, and the three can form a ring. The other ends of the two upper bearings are connected by a tensioning tool (5). The pads (2) are evenly arranged on the inner side of the upper and lower bearings. The wear-resistant strips (3) are fixed on the end faces of the upper and lower bearings. The positioning block (4) is set at the connection of the two upper bearings.

2. The external protective tooling for manufacturing rocket engine liners of different calibers as described in claim 1, characterized in that, Support lugs are provided at the joint between the two upper tiles.

3. The external protective tooling for manufacturing rocket engine liners of different calibers as described in claim 1, characterized in that, The tightening tool is a puller.

4. The external protective tooling for manufacturing rocket engine liners of different calibers as described in claim 1, characterized in that, The bearing plate matches the outer diameter of the shell.

5. The external protective tooling for manufacturing rocket engine liners of different calibers as described in claim 1, characterized in that, The thickness of the pads is adjusted to accommodate changes in the shell diameter.

6. The external protective tooling for manufacturing rocket engine liners of different calibers as described in claim 1, characterized in that, The wear-resistant strip is made of stainless steel and contacts the retaining wheel of the coating machine housing support mechanism.

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