A solid rocket engine double position assembly tool and method

Abstract

This invention provides a dual-station assembly fixture and method for solid rocket motors, belonging to the field of rocket motor assembly technology. The fixture includes a base frame assembly and a support assembly. The base frame assembly has a rotatable optical axis and an elastic positioning mechanism for locking the optical axis at at least three predetermined angles. The support assembly is fixedly connected to the rotating shaft and includes a semi-annular fixing ring, a pressure block assembly, and a pin. The pressure block assembly has an L-shaped groove for clamping lugs and a blocking part. The pin axially blocks the lugs when the rear end of the combustion chamber is facing downwards. The assembly method includes: after fixing the combustion chamber shell, sequentially flipping it so that the front end of the combustion chamber faces upwards to install the front end cap, the rear end faces upwards to install the nozzle, and the front end faces upwards to install the electric igniter and plug. This invention achieves mechanized flipping and multi-angle locking, reducing labor intensity and improving efficiency and safety.

Description

Technical Field

[0001] This invention belongs to the field of solid rocket engine assembly technology, specifically relating to a dual-station assembly fixture and method for solid rocket engines. Background Technology

[0002] In the final assembly process of a certain type of solid rocket motor, the components to be assembled include an adiabatic shell, propellant grains, nozzle, front end cap, electric igniter, and plug. The propellant grains are freely loaded into the adiabatic shell; the front end cap, electric igniter, and plug are installed at the front end of the adiabatic shell via threaded assembly; the nozzle is also installed at the rear end of the adiabatic shell via threaded assembly. According to the existing assembly process, the propellant grains must first be loaded, followed by the assembly of the front end cap; then the motor section is flipped to assemble the nozzle; finally, the motor section is flipped again to assemble the electric igniter and plug. In this entire assembly process, the motor section needs to be flipped twice to assemble the components at both ends.

[0003] Currently, the assembly of engine cylinder sections must be performed in a purely mechanical, non-electrical environment, without the aid of electric or pneumatic tilting equipment. The existing assembly tooling structures used in the process are as follows: Figure 1 As shown, its main structure is a simple cylindrical support frame. During operation, the engine cylinder section is placed vertically into the cylindrical support frame by hand. When the other end needs to be assembled, the operator must take the cylinder section, which weighs about 15 kg, out of the tooling and manually rotate it 180° before putting it back in. The defects of this operation method are: (1) The engine cylinder section weighs about 15 kg. Under the condition of batch production, the frequent manual lifting and turning will result in great physical exhaustion for the operator; (2) The manual turning operation is time-consuming and laborious, and it is necessary to reposition and align it after each turning, resulting in a long assembly time for a single product; (3) During the process of manually turning the heavy cylinder section, there is a risk of dropping it, injuring the operator, or damaging the paint and parts of the product. Summary of the Invention

[0004] The purpose of this invention is to solve the problems of high labor intensity, low assembly efficiency, and certain safety hazards in the assembly of solid rocket motors by frequent manual flipping operations required by existing combustion chamber docking fixtures. In response, this invention provides a dual-station assembly fixture and method for solid rocket motors.

[0005] To achieve the above objectives, the technical solution provided by this invention is:

[0006] A dual-station assembly fixture for a solid rocket motor includes a base assembly, a load-bearing assembly, an elastic positioning mechanism, and pins; the base assembly is used for fixed connection with an external operating platform; the base assembly is provided with a rotating shaft that can rotate around its own axis, and an elastic positioning mechanism for locking the rotating shaft at at least three predetermined angles;

[0007] The support assembly is used to place and fix the engine combustion chamber; the support assembly is connected to the rotating shaft and can rotate synchronously with the rotating shaft; the support assembly includes a semi-annular retaining ring, a pin, and at least one set of pressure block assemblies disposed on the retaining ring;

[0008] The clamping block assembly has a groove for clamping the lugs on the outer wall of the engine combustion chamber housing, and a blocking part for blocking the lugs during the flipping process to prevent the engine combustion chamber from falling off; a pin is inserted into the clamping block assembly to axially block the lugs when the rear end of the engine combustion chamber is facing down, preventing the lugs from sliding out from the opening side of the groove.

[0009] The front end of the engine combustion chamber is used to assemble the engine's front end cap, electric igniter, and plug; the rear end of the engine combustion chamber is used to assemble the engine's nozzle.

[0010] Furthermore, the elastic positioning mechanism includes a support member, an elastic pin, and a flange; the support member is fixedly connected to the side of the base frame assembly and has a first pin hole; the flange and the support member are located on the same side of the base frame assembly, one end of the flange is coaxially nested in the end of the rotating shaft, and the other end is fixedly connected to the bearing assembly; the flange can rotate synchronously with the rotating shaft; multiple positioning holes are evenly distributed circumferentially on the side of the flange; the elastic pin passes through the first pin hole on the support member and can be selectively inserted into any positioning hole on the flange to achieve locking of the rotating shaft at different rotation angles.

[0011] Furthermore, the retaining ring is semi-circular, and its inner diameter is adapted to the outer diameter of the engine combustion chamber, forming a receiving space that encloses the engine combustion chamber shell; the retaining ring also serves as a rotating handle, and the operator can drive the load-bearing component to flip by directly pushing and pulling the retaining ring.

[0012] Furthermore, flat lugs are provided at both ends of the fixing ring. The flat lugs are used to support the lugs of the engine combustion chamber. The pressure block assembly is installed on the flat lugs to clamp the lugs.

[0013] Furthermore, the fixing ring includes two parallel semi-ring bodies, with a planar lug seat mounted between the ends of the two semi-ring bodies; it also includes several reinforcing ribs, which are rod-shaped structures with their ends fixedly connected to the opposite sidewalls of the two semi-ring bodies, to enhance the torsional strength of the fixing ring.

[0014] Furthermore, the clamping block assembly includes a first clamping block group and a second clamping block group; wherein, the first clamping block group includes a large clamping block and at least one large pad for clamping the main connecting lug of the engine combustion chamber; the second clamping block group includes a small clamping block and at least one small pad for clamping the auxiliary lug of the engine combustion chamber;

[0015] The first and second pressure block groups are arranged on each of the planar ear seats at both ends of the fixing ring; the large and small pads are both L-shaped structures and are stacked on the planar ear seats; the large and small pressure blocks are both rectangular blocks with L-shaped grooves inside, which are stacked on the corresponding pad blocks and fixed to the planar ear seats by screws passing through the pressure blocks and pads from top to bottom; the L-shaped grooves inside the pressure blocks and the L-shaped structures of the pads are aligned vertically to form L-shaped grooves for clamping the ear pieces, and the vertical walls of the L-shaped grooves constitute the blocking parts.

[0016] Furthermore, the large pressure block of the first pressure block assembly and the corresponding flat lug are provided with a second pin hole. The pin is fitted in the second pin hole and is used to insert into the second pin hole after the lug of the engine combustion chamber slides into the slide groove to abut against the end face of the main connecting lug, so as to achieve axial blocking when the rear end of the engine combustion chamber is facing downward.

[0017] This invention also provides a solid rocket motor assembly method, which utilizes the aforementioned designed dual-station assembly fixture for solid rocket motors; including the following steps:

[0018] Step 1: Operate the elastic positioning mechanism to release the lock on the rotating shaft and flip the bearing assembly to a horizontal position; then relock the elastic positioning mechanism.

[0019] Step 2: Place the engine combustion chamber with the propellant charge loaded onto the fixing ring of the bearing assembly, so that the lugs on the outer wall of the engine combustion chamber housing slide into the groove of the pressure block assembly, and insert the pin into the pressure block assembly so that the pin abuts against the end face of the lugs to achieve axial fixation;

[0020] Step 3: Operate the elastic positioning mechanism to release the lock on the rotating shaft; flip the bearing assembly to the first predetermined angle so that the front end of the engine combustion chamber faces upward, relock the elastic positioning mechanism, and thread the front end cap to the front end of the engine combustion chamber.

[0021] Step 4: Operate the elastic positioning mechanism to release the lock on the rotating shaft, continue to rotate the bearing assembly to the second predetermined angle so that the rear end of the engine combustion chamber faces upward, relock the elastic positioning mechanism, and thread the nozzle to the rear end of the engine combustion chamber.

[0022] Step 5: Operate the elastic positioning mechanism to release the lock on the rotating shaft, continue to rotate the bearing assembly to the third predetermined angle so that the front end of the engine combustion chamber faces upward, relock the elastic positioning mechanism, and thread the electric igniter and plug to the front end of the engine combustion chamber.

[0023] Step 6: Flip the load-bearing assembly back to the horizontal position and relock the elastic positioning mechanism; pull out the pin to release the fixing of the lugs on the outer wall of the engine combustion chamber housing, and take out the assembled engine combustion chamber.

[0024] Furthermore, the first predetermined angle is a 90° rotation relative to the horizontal position, so that the front end of the engine combustion chamber is vertically upward; the second predetermined angle is a 180° rotation in the same or opposite direction to the first predetermined angle, so that the rear end of the engine combustion chamber is vertically upward; the third predetermined angle is a 180° rotation in the same or opposite direction to the second predetermined angle, so that the front end of the engine combustion chamber is vertically upward.

[0025] Furthermore, the flipping operation in steps 1 and steps 3 to 6 is achieved by directly pushing and pulling the fixing ring, which acts as a rotating handle.

[0026] The advantages of this invention are:

[0027] 1. This invention adopts a purely mechanical design, without any electric or pneumatic components, meeting the special assembly process requirements of solid rocket engines, which require purely mechanical and non-electric assembly. By installing bearing seats and a rotating shaft on the base frame, this invention allows the load-bearing components to rotate around the shaft, transforming manual lifting and turning into mechanical rotation. Operators only need to push the fixing ring to complete the turning of the engine section, eliminating the need for direct handling. This solves the problem of excessive labor intensity caused by manual turning in existing technologies, significantly reducing the operator's workload. Through mechanized turning and quick pin positioning, this invention makes turning and angle locking operations convenient. Using existing tooling, assembling a single product takes approximately 30 minutes, while using the tooling of this invention, this time can be reduced to 20 minutes, increasing efficiency by approximately 33%. This solves the problems of long manual turning times and repeated adjustments for positioning and alignment, which lead to low batch production efficiency in existing technologies.

[0028] 2. The present invention provides an elastic pin in the base frame assembly and provides multiple positioning holes evenly spaced on the circumferential side of the flange mounted on the rotating shaft. This allows the elastic pin to be selectively inserted into different positioning holes, enabling the load-bearing assembly to be fixed and locked in at least three angles, such as horizontal placement, nozzle facing up, and nozzle facing down, and to remain stationary. This solves the problem in the prior art that it is impossible to stably position after manual flipping and that repeated adjustments are required to align it, and ensures the stability of the threaded assembly of the front and rear end components.

[0029] 3. This invention features an L-shaped pad and a pressure block with an L-shaped groove on the fixing ring, forming an open sliding groove. The L-shaped vertical wall acts as a baffle during the flipping process, and a pin is additionally inserted to axially block the product's lugs when the nozzle is facing downwards. The product is reliably limited throughout the flipping and assembly process, ensuring that it will not fall in any of the three states: horizontal, nozzle-up, and nozzle-down. This avoids the safety hazards of product falling, injuring operators, or damaging the product due to unstable manual lifting, as found in existing technologies.

[0030] 4. The present invention divides the tooling structure that mates with the lug on the combustion chamber shell into a large pressure block, a large pad block, a small pressure block, and a small pad block. During operation, the product only needs to slide a short distance on the fixing ring to be placed in place, which reduces the frictional contact between the product and the tooling, reduces the risk of paint scratches, and makes it easier for the operator to push.

[0031] 5. The base of this invention is made by drilling and welding fixed-length channel steel. Compared with purchasing suitable steel and performing full processing, it can save 20%-40% of the manufacturing cost and has good economic efficiency while ensuring strength and functionality. Attached Figure Description

[0032] Figure 1 It is the combustion chamber docking fixture used in existing technology;

[0033] Figure 2 This is a three-dimensional structural schematic diagram of the dual-station assembly fixture for solid rocket motors of the present invention;

[0034] Figure 3 This is a schematic diagram of the base frame assembly in this invention;

[0035] Figure 4 This is a structural schematic diagram of the load-bearing component in this invention; the diagram includes exploded views of the first and second pressure block groups:

[0036] Figure 5 This is a structural schematic diagram of the assembled engine cylindrical section (including the combustion chamber and other assembled components);

[0037] Figure 6 This is a schematic diagram of an engine combustion chamber being horizontally pushed into a retaining ring. This engine combustion chamber is not constrained by pins.

[0038] Figure 7 This is a schematic diagram of the engine combustion chamber being horizontally fixed to the tooling of the present invention by means of pins;

[0039] Figure 8 This is a diagram showing the engine combustion chamber front end in a vertically upward position after the first flip; in this position, the front end cap is installed at the front end of the engine combustion chamber.

[0040] Figure 9 This is a diagram showing the engine combustion chamber rear end in a vertically upward position after the second flip; in this position, the nozzle is installed at the rear end of the engine combustion chamber.

[0041] Figure 10 This is a diagram showing the engine combustion chamber front end in a vertically upward position after the third rotation; in this position, an electric igniter and a plug are installed at the front end of the engine combustion chamber.

[0042] In the diagram: 1-Base frame assembly, 2-Fixed rotating assembly, 3-Rotating shaft, 4-Bearing seat, 5-Flange, 501-Sleeve part, 502-Disc-shaped connecting part, 6-Elastic pin, 7-Base, 701-Support member, 702-First pin hole, 8-Fixing ring, 801-Flat lug seat, 802-Half-ring body, 803-Reinforcing rib, 9-First pressure block assembly, 901-Large pressure block, 902-Large pad, 10-Second pressure block assembly, 1001-Small pressure block, 1002-Small pad, 11-Engine combustion chamber, 12-Main connecting lug, 13-Auxiliary lug, 14-Nozzle, 15-Pin, 16-Front end cap, 17-Electric igniter. Detailed Implementation

[0043] The embodiments of the present invention are described in detail below. These embodiments are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0044] Reference Figure 2 This invention provides a dual-station assembly fixture for a solid rocket motor, comprising a base frame assembly 1 and a support assembly 2. The base frame assembly 1 is used to fix to an external operating platform and provides a rotational support foundation for the support assembly. The base frame assembly 1 is provided with a rotating shaft 3 that can rotate around its own axis, and an elastic positioning mechanism for locking the rotating shaft 3 at at least three predetermined angles. The support assembly 2 is used to place and fix the engine combustion chamber. The support assembly is arranged at one end of the base frame assembly, fixedly connected to the rotating shaft 3, and can rotate synchronously with the rotating shaft 3. The support assembly 2 includes a semi-annular fixing ring 8, a pin 15, and at least one set of pressure block assemblies disposed on the fixing ring.

[0045] Reference Figure 3The base assembly includes a rotating shaft 3, bearing seats 4, flanges 5, resilient pins 6, and a base 7. The base is welded from four channel steels to reduce processing costs and provide sufficient height. The base 7 has several through holes for fixed connection to the existing operating platform using T-slot bolts or other connectors, ensuring the stability of the entire fixture during use. Two ears are vertically welded to the front end of the base 7 (the end closest to the load-bearing component), serving as support members 701. A first pin hole 702 is coaxially formed at the upper end of the support member for installing the resilient pin 6. Two bearing seats 4 are installed parallel to each other at the top ends of the base 7 using screws or other fasteners. The rotating shaft 3 rotatably passes through the two bearing seats 4 and engages with the bearings built into the bearing seats 4, allowing the rotating shaft 3 to rotate circumferentially. In this embodiment, the rotating shaft adopts a smooth shaft structure.

[0046] Flange 5 and support 701 are located on the same side of the base frame assembly. In this embodiment, the end closer to the load-bearing component is defined as the front end of the base frame assembly. Figure 3 As shown, the flange 5 has a two-stage rotational structure. One end of the flange 5, connected to the rotating shaft 3, is provided with a bushing 501. The bushing is coaxially nested within the end of the rotating shaft and fixedly connected to it via set screws or a key, allowing the rotating shaft 3 to drive the flange 5 to rotate synchronously. The other end of the flange 5, connected to the load-bearing assembly, is provided with a disc-shaped connecting part 502. This disc-shaped connecting part has multiple screw mounting holes along its axial direction, and is fixedly connected to the vertical wall on one side of the fixing ring 8 of the load-bearing assembly 2 via multiple screws.

[0047] The bushing portion of flange 5 has multiple locating holes evenly distributed circumferentially on its side. These locating holes are elongated blind holes used to engage with the elastic pin 6 to rotate the shaft at different angles. The number of these holes matches the number of angles required for locking by the tooling. In this embodiment, there are four locating holes, with an included angle of 90° between adjacent holes. These correspond to the fixed ring 8 being in a horizontal state, the front end of the engine combustion chamber facing upwards, the rear end of the engine combustion chamber facing upwards, and the intermediate state during the 90° rotation process, respectively. The elastic pin 6 passes through the first pin hole 702 on the support member and can be selectively inserted into any of the locating holes to lock the rotating shaft 3 at different rotation angles, thereby achieving locking of the bearing component at different rotation angles.

[0048] Reference Figure 4 and Figure 5 , Figure 5This diagram illustrates the required structure of the assembled engine cylindrical section (including the combustion chamber and other assembly components). The retaining ring 8 is semi-circular, with its inner diameter matching the outer diameter of the engine combustion chamber to form a receiving space enclosing the combustion chamber shell. The semi-circular retaining ring facilitates the insertion and removal of the engine combustion chamber. The retaining ring can be locked at a specified angle and kept stationary by the cooperation of the flange 5 and the elastic pin 6. The retaining ring 8 also serves as a rotating handle; the operator can drive the load-bearing assembly 2 to rotate by directly pushing or pulling the retaining ring 8, eliminating the need for a separate handle component. Two flat lugs 801 are provided at each end of the retaining ring 8. These flat lugs have identical structures and are symmetrically distributed. The upper surface of each flat lug is flat and serves to support the main connecting lug 12 or auxiliary lug 13 of the engine combustion chamber shell.

[0049] Specifically, the fixing ring 8 includes two parallel semi-ring bodies 802, with a planar lug mounted between the ends of the two semi-ring bodies on the same side and fixedly connected to the semi-ring bodies by screws. Since components such as the nozzle and front end cap are assembled using threaded connections, a large tightening torque is required during assembly. Therefore, this invention provides several reinforcing ribs 803 between the two semi-ring bodies of the fixing ring 8. The reinforcing ribs are rod-shaped structures, with their two ends fixedly connected to the opposite sidewalls of the two semi-ring bodies, to enhance the overall rigidity and torsional strength of the fixing ring 8, prevent deformation of the tooling after repeated use, and ensure the reliability of the tooling for long-term use.

[0050] The clamping block assembly includes a first clamping block group 9 and a second clamping block group 10, which are disposed on each of the planar lugs at both ends of the fixing ring. The first clamping block group 9 includes a large clamping block 901 and at least one large pad 902 for clamping the main connecting lug 12 of the engine combustion chamber; the second clamping block group 10 includes a small clamping block 1001 and at least one small pad 1002 for clamping the auxiliary lug 13 of the engine combustion chamber. Specifically, both the large pad 902 and the small pad 1002 are L-shaped structures and are stacked on the planar lugs; both the large clamping block 901 and the small clamping block 1001 are rectangular blocks with L-shaped grooves inside, which are stacked on the corresponding pad blocks and fixedly connected to the planar lugs by long screws passing through the clamping blocks and pad blocks from top to bottom. The L-shaped groove inside the pressure block aligns with the L-shaped structure of the pad block, forming an L-shaped slide groove for clamping the lugs. The vertical wall of this L-shaped slide groove constitutes a blocking part, used to prevent the lugs from falling off during the flipping process. Specifically, during rotation, when the front end of the engine combustion chamber is facing downwards, the lugs on the outer wall of the combustion chamber housing tend to slide downwards under the influence of gravity. At this time, the vertical wall of the L-shaped slide groove can directly block the end face of the lugs, preventing the engine combustion chamber from falling out of the L-shaped slide groove. The open side of the L-shaped slide groove is used to accommodate the corresponding main connecting lug or auxiliary lug. During assembly, the lugs on the outer wall of the engine combustion chamber housing are slid horizontally into the corresponding L-shaped slide groove from the open side.

[0051] Furthermore, during the assembly of the bearing assembly 2, the height of the L-shaped groove can be changed by adjusting the number of large shims 902 and small shims 1002 (i.e., increasing or decreasing the number of shim layers). For example, when there are batch differences in the size of the lugs due to different engine models, the number of shims can be increased or decreased to match the height of the L-shaped groove with the actual size of the lugs, ensuring a tight fit between the engine combustion chamber and the tooling, and avoiding engine combustion chamber shaking due to excessive clearance or assembly difficulties due to insufficient clearance.

[0052] When the rear end 16 of the engine combustion chamber faces downwards, the engine combustion chamber is in an inverted state. There is a risk that the lugs on the outer wall of the combustion chamber shell may detach from the corresponding L-shaped grooves. Therefore, this invention provides second pin holes on the large pressure block 901 of the first pressure block assembly and on the corresponding flat lug seat 801, and provides a pin 15. The pin 15 is used to insert into the second pin hole after the lugs of the engine combustion chamber slide into the grooves, so as to abut against the end face of the main connecting lug 12. When the fixture is flipped so that the rear end of the engine combustion chamber faces downwards (i.e.,...), the combustion chamber is inverted. Figure 8 When the state shown is as indicated, the pin 15 axially blocks the main connecting lug 12 from the opening side to prevent the lug from sliding out from the opening side of the groove, thereby ensuring the safety of the combustion chamber in the inverted state.

[0053] Reference Figures 6-9 The specific usage process of the tooling of this invention is as follows:

[0054] Step 1: Adjust the fixed load-bearing components to a horizontal position.

[0055] Operate the resilient pin 6 to pull it out of the positioning hole of flange 5, and then manually rotate the retaining ring 8 until the flat lugs at both ends of the retaining ring 8 are horizontal. At this time, the semi-circular opening of the retaining ring 8 is facing upward. Confirm that the resilient pin 6 is reinserted into the corresponding positioning hole of flange 5, so that the retaining ring 8 remains horizontal and stationary.

[0056] Step 2: Placement and securing of the engine combustion chamber.

[0057] The engine combustion chamber 11, already loaded with propellant, is hoisted as a whole or lifted and placed by operators onto the semi-circular fixing ring 8 of the supporting assembly 2. The engine combustion chamber 11 is placed within the semi-circular ring of the fixing ring 8, and the main connecting lug 12 and auxiliary lug 13 on the outer wall of the engine combustion chamber housing are respectively located on the planar lug seats at both ends of the fixing ring 8.

[0058] The operator pushes the engine combustion chamber horizontally, causing the main connecting lug 12 and auxiliary lug 13 on the outer wall of the engine combustion chamber to slide from the opening side into the L-shaped grooves formed by the large pressure block 11 and the large pad block 12, and the small pressure block 8 and the small pad block 9, respectively. When the lugs are fully slid into the bottom of the grooves, the circumferential position of the engine combustion chamber is restricted by the vertical wall of the L-shaped grooves, preventing it from rotating around its own axis. Figure 6 The state shown.

[0059] Then, axial fixing is performed. Specifically, pin 15 is inserted into the second pin hole on the large pad 12 of the first pressure block assembly, so that pin 15 passes through the second pin hole and abuts against the end face of the main connecting lug 12 facing the rear end of the engine combustion chamber, thus achieving axial fixing. At this time, the engine combustion chamber is blocked axially by pin 15 and cannot slide out of the groove, achieving reliable fixing of the engine combustion chamber to the fixing ring 8. Figure 7 As shown.

[0060] Step 3: First flip - pre-assembly of the end cap.

[0061] First, pull out the elastic pin 6 to release the lock between the flange 5 and the rotating shaft. The operator holds the semi-circular ring of the retaining ring 8 as a rotating handle and flips the bearing assembly 2 to the first predetermined angle so that the front end of the engine combustion chamber faces upward. After flipping it into place, reinsert the elastic pin 6 into the corresponding positioning hole on the flange 5 to lock the fixture.

[0062] In this state, the operator will thread the front end cap 16 onto the front end of the engine combustion chamber; after assembly, it will be inserted into the engine combustion chamber. Figure 8 As shown.

[0063] Step 4: Second flip - assemble the nozzle.

[0064] Operate the elastic pin 6 again, pull out the elastic pin, and release the lock between the flange 5 and the rotating shaft; continue to rotate the bearing assembly 2 to the second predetermined angle so that the rear end of the engine combustion chamber faces upward, and reinsert the elastic pin 6 into the corresponding positioning hole on the flange 5 to lock the tooling.

[0065] In this state, the operator will thread the nozzle 14 to the rear end of the engine combustion chamber; after assembly, as shown... Figure 9 As shown.

[0066] Step 5: Third flip - assemble the electric igniter and plug.

[0067] Next, operate the elastic pin 6, pull out the elastic pin, and release the lock between the flange 5 and the rotating shaft; continue to rotate the bearing assembly 2 to the third predetermined angle, so that the front end of the engine combustion chamber faces upward, and reinsert the elastic pin 6 into the corresponding positioning hole on the flange 5 to lock the tooling.

[0068] In this state, the operator will thread the electric igniter 17 and the plug (not shown in the drawing due to view limitations) onto the front end of the engine combustion chamber; after assembly, as shown... Figure 10 As shown.

[0069] Step 6: Remove the assembled engine combustion chamber.

[0070] After completing the threaded assembly of all components, pull out the elastic pin 6 again, flip the bearing assembly 2 back to the horizontal position, and lock it again.

[0071] Pull out pin 15 to release the axial fixation of the engine combustion chamber lugs; then pull the engine combustion chamber horizontally in the opposite direction to the sliding direction to make the lugs slide out of the L-shaped groove; finally, remove the assembled engine combustion chamber from the retaining ring 8 to complete one assembly cycle.

[0072] In this embodiment of the invention, the first predetermined angle is a 90° rotation relative to the horizontal position, so that the front of the engine combustion chamber is vertically upward; the second predetermined angle is a 180° rotation relative to the first predetermined angle in the same or opposite direction, so that the rear end of the engine combustion chamber is vertically upward; the third predetermined angle is a 180° rotation relative to the second predetermined angle in the same or opposite direction, so that the front end of the engine combustion chamber is vertically upward.

[0073] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the scope of the technology disclosed in the present invention, and such modifications or substitutions should all be covered within the scope of protection of the present invention.

Claims

1. A dual-station assembly fixture for a solid rocket motor, characterized in that, Includes base assembly, load-bearing assembly, flexible positioning mechanism and pins; The base frame assembly is used for fixed connection with an external operating platform; the base frame assembly is provided with a rotating shaft that can rotate about its own axis, and an elastic positioning mechanism for locking the rotating shaft at at least three predetermined angles; The support assembly is used to place and fix the engine combustion chamber; the support assembly is connected to the rotating shaft and can rotate synchronously with the rotating shaft; the support assembly includes a semi-annular fixing ring, a pin, and at least one set of pressure block assemblies disposed on the fixing ring; The clamping block assembly has a groove for clamping a lug on the outer wall of the engine combustion chamber housing, and a blocking part for blocking the lug during the flipping process to prevent the engine combustion chamber from falling off; the pin is inserted into the clamping block assembly to axially block the lug when the rear end of the engine combustion chamber is facing down, preventing the lug from sliding out from the opening side of the groove. The front end of the engine combustion chamber is used to assemble the engine's front end cap, electric igniter, and plug; the rear end of the engine combustion chamber is used to assemble the engine's nozzle.

2. The dual-station assembly fixture for solid rocket motors according to claim 1, characterized in that: The flexible positioning mechanism includes a support component, a flexible pin, and a flange; The support member is fixedly connected to the side of the base frame assembly, and a first pin hole is provided on it; The flange and the support are located on the same side of the base frame assembly; one end of the flange is coaxially nested at the end of the rotating shaft, and the other end is fixedly connected to the bearing assembly; the flange can rotate synchronously with the rotating shaft; multiple positioning holes are evenly distributed circumferentially on the side of the flange; The elastic pin passes through the first pin hole on the support member and can be selectively inserted into any of the positioning holes on the flange to lock the rotating shaft at different rotation angles.

3. The dual-station assembly fixture for solid rocket motors according to claim 1, characterized in that: The retaining ring is semi-circular, and its inner diameter is adapted to the outer diameter of the engine combustion chamber, forming a receiving space that encloses the engine combustion chamber shell; the retaining ring also serves as a rotating handle, and the operator can drive the load-bearing component to flip by directly pushing and pulling the retaining ring.

4. The dual-station assembly fixture for solid rocket motors according to claim 3, characterized in that: The fixed ring has planar lugs at both ends, which are used to support the lugs of the engine combustion chamber. The pressure block assembly is installed on the planar lugs to clamp the lugs.

5. The dual-station assembly fixture for solid rocket motors according to claim 4, characterized in that: The fixing ring includes two parallel semi-ring bodies, and the planar ear seat is mounted between the ends of the two semi-ring bodies; It also includes several reinforcing ribs, which are rod-shaped structures with their two ends fixedly connected to the opposite sidewalls of the two semi-rings, respectively, to enhance the torsional strength of the fixed ring.

6. The dual-station assembly fixture for solid rocket motors according to claim 4, characterized in that: The pressing assembly includes a first pressing block group and a second pressing block group; wherein... The first pressure block group includes a large pressure block and at least one large pad block for clamping the main connecting lug of the engine combustion chamber; the second pressure block group includes a small pressure block and at least one small pad block for clamping the auxiliary lug of the engine combustion chamber. The first pressure block group and the second pressure block group are disposed on each planar lug at both ends of the fixing ring. Both the large pad and the small pad have an L-shaped structure and are stacked on the planar ear seat; both the large pressure block and the small pressure block are rectangular blocks with L-shaped slots inside, and are stacked on the corresponding pads respectively, and are fixedly connected to the planar ear seat by screws passing through the pressure blocks and pads from top to bottom. The L-shaped groove inside the pressure block and the L-shaped structure of the pad block are aligned vertically to form an L-shaped sliding groove for clamping the ear piece, and the vertical wall of the L-shaped sliding groove constitutes the blocking part.

7. The dual-station assembly fixture for solid rocket motors according to claim 6, characterized in that: The first pressure block group has a second pin hole on the large pressure block and the corresponding flat lug. The pin is disposed in the second pin hole and is used to insert into the second pin hole after the lug of the engine combustion chamber slides into the groove to abut against the end face of the main connecting lug, so as to achieve axial blocking when the rear end of the engine combustion chamber is facing downward.

8. A method for assembling a solid rocket motor, characterized in that, This is achieved using the dual-station assembly fixture for solid rocket motors as described in any one of claims 1 to 7; and includes the following steps: Step 1: Operate the elastic positioning mechanism to release the lock on the rotating shaft and flip the bearing assembly to a horizontal state; then relock the elastic positioning mechanism. Step 2: Place the engine combustion chamber with the propellant charge loaded onto the fixing ring of the bearing assembly, so that the lugs on the outer wall of the engine combustion chamber housing slide into the groove of the pressure block assembly, and insert the pin into the pressure block assembly so that the pin abuts against the end face of the lugs to achieve axial fixation; Step 3: Operate the elastic positioning mechanism to release the lock on the rotating shaft; flip the bearing assembly to the first predetermined angle so that the front end of the engine combustion chamber faces upward, relock the elastic positioning mechanism, and thread the front end cap to the front end of the engine combustion chamber; Step 4: Operate the elastic positioning mechanism to release the lock on the rotating shaft, continue to rotate the bearing assembly to the second predetermined angle so that the rear end of the engine combustion chamber faces upward, relock the elastic positioning mechanism, and thread the nozzle to the rear end of the engine combustion chamber. Step 5: Operate the elastic positioning mechanism to release the lock on the rotating shaft, continue to rotate the bearing assembly to the third predetermined angle so that the front end of the engine combustion chamber faces upward, relock the elastic positioning mechanism, and thread the electric igniter and plug to the front end of the engine combustion chamber. Step 6: Flip the bearing assembly back to the horizontal position and relock the elastic positioning mechanism; pull out the pin to release the fixing of the lug on the outer wall of the engine combustion chamber housing, and take out the assembled engine combustion chamber.

9. The solid rocket motor assembly method according to claim 8, characterized in that: The first predetermined angle is a 90° rotation relative to the horizontal position, so that the front end of the engine combustion chamber is vertically upward; the second predetermined angle is a 180° rotation relative to the first predetermined angle in the same or opposite direction, so that the rear end of the engine combustion chamber is vertically upward; the third predetermined angle is a 180° rotation relative to the second predetermined angle in the same or opposite direction, so that the front end of the engine combustion chamber is vertically upward.

10. The solid rocket motor assembly method according to claim 8, characterized in that: The flipping operation in steps 1 and steps 3 to 6 is achieved by directly pushing and pulling the fixed ring, which serves as a rotating handle.

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