A transfer carriage and method for solid rocket engine vertical testing

Abstract

The application discloses a transfer bracket and method for vertical test of solid rocket engine, and belongs to the field of ground test of solid rocket engine. The transfer bracket comprises a fixed half ring, a first rotating shaft, a first movable half ring, a connecting piece, a second movable half ring and a second rotating shaft. The fixed half ring is fixed to a transfer vehicle, the first movable half ring is hinged to one end of the fixed half ring through the first rotating shaft, the second movable half ring is hinged to the other end of the fixed half ring through the second rotating shaft, and the other ends of the two movable half rings are detachably connected through the connecting piece. The three half rings are enclosed into a complete annular support structure in the connected state, and are used for bearing the vertically seated engine; after the connecting piece is removed, the two movable half rings can be rotated outward to open, and an open channel is formed for the engine nozzle to translate and separate. The application provides a complete bearing structure during transfer, and the channel for the nozzle to pass through is formed after being positioned, so that the bracket and the nozzle are separated without interference.

Description

Technical Field

[0001] This invention belongs to the field of solid rocket engine ground testing technology, specifically relating to a transfer fixture for upright solid rocket engine testing, and more specifically to a transfer bracket with an openable toroidal structure and a method for transferring the engine using the transfer bracket. Background Technology

[0002] Solid rocket engines provide propulsion for aircraft and are one of the most crucial components of an aircraft. Upright testing is an important ground test in the research and testing phase of solid rocket engines, verifying the rationality of the engine design and evaluating its actual performance. Vertical transport of the solid rocket engine is a necessary prerequisite for upright testing, and the transport bracket is the key structural component for connecting and securing the engine to the transport vehicle.

[0003] Currently, several device designs for vertical transport of solid rocket motors exist. For example, Chinese patent CN115783504A discloses a self-leveling vertical transport device for solid rocket motors. This device automatically levels itself using the product's own weight and mainly includes a transport frame, horizontal rocker arms, vertical rocker arms, a mounting base, and a hydraulic damping cylinder. The horizontal and vertical rocker arms maintain the product's vertical position by rotating along the axis of rotation. Another example is Chinese patent CN219154345U, which discloses a vertical transport device for solid rockets, including a vehicle body, a mounting frame, and a rocket fixing frame. The rocket fixing frame is vertically positioned and internally fixed with several rocket fixing devices. The extension and retraction of these devices adapt to the fixing requirements of different core stages.

[0004] However, all of the aforementioned existing technical solutions have shortcomings. In the actual operation of the upright test, after the engine is carried vertically by the transport vehicle to the test position, subsequent test docking operations are still required. The engine's tail nozzle is located inside the space enclosed by the transport bracket, which itself is a closed ring structure. When the transport vehicle needs to be withdrawn, the bracket structure cannot make way for the nozzle position, preventing the transport vehicle from moving the bracket out of the nozzle area. This necessitates additional disassembly or hoisting procedures, which not only affects the efficiency of the connection between the transport and testing procedures but also increases the safety risks during operation. Summary of the Invention

[0005] The purpose of this invention is to solve the problem that existing solid rocket motor vertical transport devices, after the engine arrives at the test position, cannot open the nozzle position due to the closed ring structure of the bracket, leading to difficulties in removing the transport vehicle and poor process connection. The invention proposes a transport bracket and method with a segmented combined ring bearing structure. This bracket provides complete ring support during transport to meet the requirements of vertical heavy-load transport. After the engine is in place, part of the ring surface can be opened to form a channel for the nozzle to be removed. Thus, while ensuring the reliability of transport, it can achieve interference-free removal of the transport vehicle and bracket, significantly improving test efficiency and operational safety.

[0006] To achieve the above objectives, the technical solution provided by this invention is:

[0007] On the one hand, a transfer bracket for upright testing of solid rocket motors is provided, including a fixed half-ring, a first rotating shaft, a first movable half-ring, a connector, a second movable half-ring, and a second rotating shaft;

[0008] The fixed semi-ring has an arc-shaped structure and is used for fixed installation onto the transfer vehicle;

[0009] One end of the first movable semi-ring is rotatably connected to the first end of the fixed semi-ring via a first rotating shaft;

[0010] One end of the second movable half-ring is rotatably connected to the second end of the fixed half-ring via the second rotating shaft;

[0011] The other end of the first movable half ring and the other end of the second movable half ring are detachably connected by a connector.

[0012] The fixed half-ring, the first movable half-ring, and the second movable half-ring, when connected by the connector, together form a complete ring support structure to support the solid rocket motor mounted on it in a vertical position.

[0013] After the connector is removed, the first and second movable semi-rings can be rotated outward around the first and second rotating axes respectively, so that the annular support structure forms an opening channel for the engine nozzle to be moved out.

[0014] Furthermore, the central angle of the fixed semi-ring is 240°, and the central angles of the first and second movable semi-rings are both 60°.

[0015] Furthermore, both the first and second rotating shafts are pins; the two ends of the fixed half ring are respectively provided with a first ear seat, and the corresponding ends of the first and second movable half rings are respectively provided with a second ear seat, and the pin passes through the corresponding first and second ear seats, so that the first and second movable half rings are respectively hinged to the fixed half ring.

[0016] Furthermore, the first movable semi-circle rotates outward around the first rotating axis by an angle of not less than 60°, and the second movable semi-circle rotates outward around the second rotating axis by an angle of not less than 60°.

[0017] Furthermore, a cage-like frame structure is adopted; the edges of the fixed semi-ring, the first movable semi-ring, and the second movable semi-ring are respectively provided with plate-like reinforcing structures, and the non-edge parts are respectively provided with tubular reinforcing structures.

[0018] Furthermore, the connector is a connecting bolt, which passes through the plate-shaped reinforcing structure at the corresponding edges of the first and second movable semi-rings, connecting the two in a detachable manner.

[0019] Furthermore, the lower end face of the ring support structure is provided with an installation interface for connecting to the transfer vehicle.

[0020] Furthermore, the upper end face of the annular support structure is provided with a connecting ring for connecting with the rear skirt connection surface of the solid rocket motor.

[0021] On the other hand, a method for transporting a solid rocket motor for an upright test using the aforementioned transfer bracket is provided, including the following steps:

[0022] Step 1: Securely install the fixed half-ring onto the transport vehicle, with the opening facing the direction in which the transport vehicle is heading towards the test station;

[0023] Step 2: Install one end of the first movable half ring onto the first end of the fixed half ring via the first rotating shaft, so that the first movable half ring can rotate around the first rotating shaft;

[0024] Step 3: Install one end of the second movable half ring onto the second end of the fixed half ring via the second rotating shaft, so that the second movable half ring can rotate around the second rotating shaft;

[0025] Step 4: Connect the other end of the first movable half ring to the other end of the second movable half ring using a connector, so that the fixed half ring, the first movable half ring, and the second movable half ring together form a complete ring support structure.

[0026] Step 5: The solid rocket motor is placed vertically on the ring support structure and connected and fixed. The motor is then transported upright to the test site by a transport vehicle.

[0027] Step 6: Disconnect the engine from the transfer bracket, lift the engine vertically and detach it from the transfer bracket, so that the engine nozzle is located inside the annular support structure.

[0028] Step 7: Remove the connecting parts, rotate the first movable half around the first rotating shaft outward to open it, and rotate the second movable half around the second rotating shaft outward to open it, so that the annular support structure forms an opening channel for the engine nozzle to be moved outward.

[0029] Step 8: The transfer vehicle moves the open transfer bracket horizontally outward, allowing the engine nozzle to pass through the open channel, thereby achieving interference-free separation of the transfer bracket and the engine nozzle in the horizontal direction.

[0030] Furthermore, in step 7, the first movable semi-rotation around the first rotating axis rotates outward by an angle of not less than 60°, and the second movable semi-rotation around the second rotating axis rotates outward by an angle of not less than 60°.

[0031] The advantages of this invention are:

[0032] 1. The transfer bracket for upright testing of solid rocket engines proposed in this invention adopts an overall ring-shaped frame-type load-bearing structure. The engine sits vertically on the bracket, and the load is evenly transferred to the transfer vehicle through the ring-shaped support structure. This structural form has good axial stiffness and load-bearing capacity, which can meet the heavy-load support requirements during the vertical transfer of solid rocket engines. At the same time, the hollow area of ​​the ring structure can accommodate fragile structures such as the engine tail nozzle, avoiding damage to the nozzle from impacts or compression during transfer.

[0033] 2. This invention designs the annular support structure as a split-combination ring surface formed by a fixed half-ring and two movable half-rings connected in a detachable manner. During transport, the three half-ring segments are spliced ​​together by connectors to form a complete 360° annular structure, ensuring structural integrity during transport. After the engine is positioned and lifted off the ground, the two movable half-rings can be opened by rotating around the pivot by removing the connectors, thus forming an opening channel on the annular support structure for the engine nozzle to move horizontally. The transport vehicle then moves the bracket horizontally outward, allowing the nozzle to pass through this opening channel. This design enables the bracket to have complete annular load-bearing capacity during transport and actively clears the nozzle's path during removal, achieving integrated functionality of closed load-bearing during transport and open clearance during removal. This effectively solves the problem of difficulty in removing the transport vehicle and poor process coordination caused by the inability to clear the nozzle position after the engine arrives at the test position with existing integral closed brackets.

[0034] 3. In this invention, since the movement trajectory of the movable semi-ring rotating around the pivot is an outward swing, the nozzle does not interfere with each other in the horizontal direction when it moves horizontally through the opening channel. The entire withdrawal process does not require additional hoisting and transfer brackets or disassembly of other structures, significantly simplifying the operation process and shortening the process connection time. At the same time, the opening and closing of the movable semi-ring are achieved by manually disassembling and assembling the connecting parts and rotating around the pivot, without relying on external power sources such as hydraulics or electricity, making it highly adaptable to test site conditions and easy and reliable to operate.

[0035] 4. This invention adopts a segmented structure combining fixed and movable half-rings, resulting in a simple overall construction. The main components can be welded from conventional steel, eliminating the need for complex precision machining and thus reducing manufacturing and maintenance costs. Since the fixed half-ring is fixedly mounted on the transport vehicle, and the two movable half-rings are connected to the fixed half-ring via rotating shafts, the assembly relationships between the components are clear. On-site operators can quickly complete the entire process of closing, transporting, opening, and removing the bracket, demonstrating good engineering practicality and application value. Attached Figure Description

[0036] The above and other features and advantages of the invention will become more readily understood from the following description with reference to the accompanying drawings, which are not drawn to scale and some features are enlarged or reduced to show details of specific parts.

[0037] Figure 1 This is a three-dimensional structural diagram of the transfer bracket for the upright test of a solid rocket engine in the closed state according to an embodiment of the present invention;

[0038] Figure 2 This is a three-dimensional structural diagram of the transfer bracket in the open state according to an embodiment of the present invention;

[0039] Figure 3 This is a schematic diagram of the planar structure of the transfer bracket in the closed state according to an embodiment of the present invention;

[0040] Figure 4 This is a schematic diagram of the planar structure of the transfer bracket in the open state according to an embodiment of the present invention.

[0041] In the diagram: 1-Fixed half-ring; 2-First rotating shaft; 3-First movable half-ring; 4-Connector; 5-Second movable half-ring; 6-Second rotating shaft. Detailed Implementation

[0042] The present invention will now be described in detail with reference to the accompanying drawings and exemplary embodiments thereof. It should be noted that the following detailed description of the present invention is for illustrative purposes only and is not intended to limit the scope of the invention.

[0043] It should be noted that, in the context of this invention, the terms “upper,” “lower,” “front,” “rear,” “left,” “right,” “vertical,” “horizontal,” “inner,” “outer,” “clockwise,” and “counterclockwise,” etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0044] Furthermore, terms such as "first" and "second" are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature.

[0045] The present invention provides a transfer bracket and method for upright testing of solid rocket engines. It is mainly used to connect and fix the engine to the transfer vehicle during the process of the solid rocket engine being carried and transported to the test position in an upright position by the transfer vehicle, and to achieve interference-free separation between the transfer bracket and the engine nozzle after the engine is in place.

[0046] Reference Figures 1 to 4 As an exemplary embodiment of the present invention, a transport bracket for an upright test of a solid rocket motor includes a fixed half-ring 1, a first rotating shaft 2, a first movable half-ring 3, a connector 4, a second movable half-ring 5, and a second rotating shaft 6. The fixed half-ring 1, the first movable half-ring 3, and the second movable half-ring 5 are all arc-shaped structures. The fixed half-ring 1 is used for fixed installation onto a transport vehicle. The fixed half-ring 1 has a first end and a second end. One end of the first movable half-ring 3 is rotatably connected to the first end of the fixed half-ring 1 via the first rotating shaft 2, allowing the first movable half-ring 3 to rotate relative to the fixed half-ring 1 around the first rotating shaft 2. One end of the second movable half-ring 5 is rotatably connected to the second end of the fixed half-ring 1 via the second rotating shaft 6, allowing the second movable half-ring 5 to rotate relative to the fixed half-ring 1 around the second rotating shaft 6. The other end of the first movable half-ring 3 and the other end of the second movable half-ring 5 are detachably connected via the connector 4. Thus, the fixed semi-ring 1, the first movable semi-ring 3, and the second movable semi-ring 5, when connected by the connector 4, together form a complete annular support structure. This annular support structure is used to support the solid rocket motor mounted on it in a vertical orientation. After the connector 4 is removed, the first movable semi-ring 3 and the second movable semi-ring 5 can be rotated outward around the first rotating shaft 2 and the second rotating shaft 6, respectively, so that the annular support structure forms an opening channel for the engine nozzle to be moved outward.

[0047] like Figure 1As shown, the fixed semi-ring 1 can be connected to the transport vehicle, with its opening facing the direction the transport vehicle is heading towards the test station. One end of the first movable semi-ring 3 is mounted to the first end of the fixed semi-ring 1 via the first rotating shaft 2, and one end of the second movable semi-ring 5 is mounted to the second end of the fixed semi-ring 1 via the second rotating shaft 6. The other ends of the first movable semi-ring 3 and the second movable semi-ring 5 are connected to each other via connector 4. At this time, the fixed semi-ring 1, the first movable semi-ring 3, and the second movable semi-ring 5 together form a complete 360° annular support structure. In this closed state, the solid rocket motor can be vertically positioned on the annular support structure, with the rear skirt connecting surface of the motor fitting into the upper surface of the annular support structure, and the motor's tail nozzle housed within the hollow interior space of the annular support structure. This closed state is the transport working state of the transport bracket. In this state, the transport bracket provides full-circumferential support and fixation for the motor, and the motor's self-weight load is evenly transferred to the transport vehicle through the annular support structure, ensuring the stability and safety of the motor during vertical transport. As the transport vehicle travels along the predetermined path, the engine is safely transported from the assembly station to the test station in an upright position.

[0048] exist Figure 2 In the shown state, connector 4 has been removed, the first movable semi-ring 3 rotates outward around the first pivot 2 to open, and the second movable semi-ring 5 rotates outward around the second pivot 6 to open. After the two movable semi-rings open, the annular support structure forms an opening channel of a certain width in the area originally occupied by the first movable semi-ring 3 and the second movable semi-ring 5. The width of this opening channel is sufficient for the engine nozzle to pass through unobstructed in the horizontal direction. This open state is the withdrawal working state of the transfer bracket. When the engine is vertically lifted at the test station until it is detached from the transfer bracket, the transfer bracket is switched to this open state. Subsequently, the transfer vehicle drives the transfer bracket in the open state to move horizontally outward. Due to the existence of the opening channel, the engine nozzle passes through the opening channel, achieving interference-free separation of the transfer bracket and the engine nozzle in the horizontal direction. This process does not require additional hoisting of the transfer bracket or disassembly of other structures, and the operation process is simple and efficient.

[0049] Figure 3 This is a top-down view taken along the axis of the transfer bracket, i.e., in the vertical direction. (Combined with...) Figure 3As can be seen more clearly, the fixed half-ring 1, the first movable half-ring 3, and the second movable half-ring 5, when connected by connector 4, together form a complete 360° annular structure. The central angle of the fixed half-ring 1 is 240°, while the central angles of the first movable half-ring 3 and the second movable half-ring 5 are both 60°. This angle distribution allows the fixed half-ring 1 to occupy a large 240° angle range, bearing the main structural load during transport, which is beneficial for maintaining the stability and safety of the overall structure. The two movable half-rings, each with a small 60° angle, are less heavy and easier for operators to easily rotate and open around the axis after removing connector 4. The lower end face of the annular support structure is provided with an installation interface for connecting to the transport vehicle, i.e., through holes on the lower end rings of each half-ring. This installation interface allows the entire transport bracket to be securely fixed to the transport vehicle. The upper end face of the annular support structure is provided with an adapter ring for connecting to the rear skirt connection surface of the solid rocket motor. This adapter ring is composed of the upper end rings of each half-ring. The motor is seated and fixed by engaging with the rear skirt connection surface of the adapter ring. Because the adapter ring can be specifically designed for the rear skirt interface of different engine models, the same transfer bracket body can be adapted to multiple engine models by replacing different adapter rings, eliminating the need to design a complete set of transfer brackets for each model, which greatly reduces the design, manufacturing and management costs of tooling.

[0050] Figure 4 This is a top-down view taken along the axis of the transfer bracket. Figure 4 In the shown state, connector 4 has been removed. The first movable half-ring 3 rotates outward around the first rotating shaft 2 and opens, while the second movable half-ring 5 rotates outward around the second rotating shaft 6, forming an opening channel in the annular support structure for the engine nozzle to slide out. The first movable half-ring 3 rotates outward around the first rotating shaft 2 at an angle of not less than 60°, and the second movable half-ring 5 rotates outward around the second rotating shaft 6 at an angle of not less than 60°. When both movable half-rings are opened by at least 60°, the width of the opening channel is sufficient for the engine nozzle to pass through unobstructed in the horizontal direction. The two movable half-rings open by rotating outward, and their rotation trajectory is located in the outer space of the annular support structure, without encroaching on the internal space of the annular support structure, thus avoiding interference with the engine nozzle located in the internal space. Furthermore, due to the small mass and flexible rotation of the movable half-rings, the operator only needs to apply manual force to complete the opening operation, without the need for external power sources such as hydraulics or electricity, making it highly adaptable to the conditions of the test site.

[0051] In this embodiment, both the first rotating shaft 2 and the second rotating shaft 6 are pins. The two ends of the fixed half-ring 1 are respectively provided with first ear seats, and the corresponding ends of the first movable half-ring 3 and the second movable half-ring 5 are respectively provided with second ear seats. During assembly, the second ear seat at the end of the first movable half-ring 3 is aligned with the first ear seat at the first end of the fixed half-ring 1, and the pin serving as the first rotating shaft 2 is passed through the first and second ear seats, thereby achieving a hinge connection between the first movable half-ring 3 and the fixed half-ring 1. Similarly, the second ear seat at the end of the second movable half-ring 5 is aligned with the first ear seat at the second end of the fixed half-ring 1, and the pin serving as the second rotating shaft 6 is passed through the corresponding first and second ear seats, achieving a hinge connection between the second movable half-ring 5 and the fixed half-ring 1. This hinge structure is simple and reliable, with low friction at the rotating shaft, flexible rotation of the movable half-rings, and easy disassembly and maintenance of the pins.

[0052] In this embodiment, the connector 4 is a connecting bolt. The connecting bolt passes through the corresponding connecting holes of the first movable half-ring 3 and the second movable half-ring 5, detachably connecting the two. When it is necessary to open the transfer bracket, simply unscrew the connecting bolt with a tool; the operation is simple and quick. When it is necessary to close the transfer bracket, rotate the two movable half-rings back to their mating positions, reinstall the connecting bolt, and tighten it to restore the complete annular support state. This bolted connection method ensures both the structural strength and reliability of the connection in the closed state and meets the operational requirements for quick disassembly in the open state.

[0053] The annular support structure in this embodiment of the invention adopts a squirrel-cage frame structure. Specifically, the fixed half-ring 1, the first movable half-ring 3, and the second movable half-ring 5 are all composed of arc-shaped members at the upper and lower ends and vertical load-bearing members connecting the arc-shaped members. Each half-ring can be formed by welding conventional steel to form a frame structure similar to a squirrel cage. This squirrel-cage frame structure has good axial stiffness and load-bearing capacity, and can effectively transfer the axial load of the engine to the transport vehicle. At the same time, there are gaps between the vertical load-bearing members in the frame structure, so that the entire annular support structure has a light weight while ensuring strength. Plate-shaped reinforcing structures are respectively provided at the edges of the fixed half-ring 1, the first movable half-ring 3, and the second movable half-ring 5. The plate-shaped reinforcing structures are rectangular plate-shaped vertical load-bearing columns with a large cross-sectional area and good compressive strength, which can meet the local strength requirements of key positions such as the connection of the movable half-rings and the ends of the fixed half-rings, and provide sufficient structural space for the installation of connecting bolts. The connecting bolts pass through the plate-like reinforcing structures at the corresponding edges of the first movable semi-ring 3 and the second movable semi-ring 5, connecting the first movable semi-ring 3 and the second movable semi-ring 5 in a detachable manner. Tubular reinforcing structures are respectively provided at the non-edge portions of the fixed semi-ring 1, the first movable semi-ring 3, and the second movable semi-ring 5. These tubular reinforcing structures are circular-sectioned tubular vertical load-bearing columns, which have a relatively low weight while ensuring bending strength, thus contributing to the overall lightweight design.

[0054] The following describes the vertical test transport method for solid rocket motors, which is an exemplary embodiment of the present invention, in conjunction with the transport bracket provided in this embodiment.

[0055] First, fix the fixed half ring 1 to the transport vehicle, ensuring that the opening of the fixed half ring 1 faces the direction in which the transport vehicle is heading towards the test station.

[0056] Next, one end of the first movable half-ring 3 is installed on the first end of the fixed half-ring 1 through the first rotating shaft 2, so that the first movable half-ring 3 can rotate around the first rotating shaft 2, and one end of the second movable half-ring 5 is installed on the second end of the fixed half-ring 1 through the second rotating shaft 6, so that the second movable half-ring 5 can rotate around the second rotating shaft 6.

[0057] Then, the other end of the first movable half-ring 3 is connected to the other end of the second movable half-ring 5 by the connector 4, so that the fixed half-ring 1, the first movable half-ring 3 and the second movable half-ring 5 together form a complete ring support structure, which is in a closed state.

[0058] The solid rocket motor is mounted vertically on a ring-shaped support structure. The rear skirt connecting surface of the motor mates with the adapter ring on the upper surface of the ring-shaped support structure, fixing the motor and the transport carrier together. The transport vehicle carries the motor in an upright position, transporting it from the assembly station to the test station. During this process, the motor's own weight is evenly transferred to the transport vehicle through the squirrel-cage-type ring-shaped support structure. The motor's exhaust nozzle is safely contained within the internal space of the ring-shaped support structure, without contacting any other structure.

[0059] After the engine arrives at the test station, first disconnect the engine from the transfer bracket. Use hoisting equipment to lift the engine vertically until it is detached from the transfer bracket. The lifting height should be such that the lower end of the engine nozzle is higher than the upper end of the transfer bracket. At this time, the engine nozzle is located in the internal space of the annular support structure.

[0060] Subsequently, the connecting piece 4 between the first movable half-ring 3 and the second movable half-ring 5 is removed, the first movable half-ring 3 is rotated outward around the first rotating shaft 2 to open by no less than 60°, and the second movable half-ring 5 is rotated outward around the second rotating shaft 6 to open by no less than 60°, so that the annular support structure forms an opening channel for the engine nozzle to pass through.

[0061] Finally, the transfer vehicle moves the open transfer bracket horizontally outwards. Due to the open channel, the engine nozzle passes through the transfer bracket, achieving interference-free horizontal separation between the transfer bracket and the engine nozzle. The transfer bracket is now in use. At this point, the engine is suspended upright at the test position, with no structural obstructions below or around the nozzle, allowing for smooth subsequent test docking operations.

[0062] This invention, through its structural design and operational procedures, achieves seamless integration between the upright transport and testing processes of a solid rocket engine. During transport, the transport bracket provides full-circumferential support and fixation in a complete closed ring, ensuring the safety and reliability of the engine's upright transport. After the engine is in place, by removing the connecting parts and rotating to open the two movable semi-rings, an opening channel is formed on the annular support structure, allowing the nozzle to slide through. When the transport vehicle moves the bracket horizontally out, the nozzle passes through this channel. No additional lifting or disassembly is required during the entire removal process, enabling rapid and safe removal of the transport vehicle and bracket. This design effectively solves the problems of difficulty in removal and poor process integration caused by the inability to clear the nozzle position after the engine arrives at the testing station with existing integral transport brackets, significantly improving the efficiency of process integration and operational safety in upright testing. Meanwhile, the entire bracket structure is simple, easy to manufacture, and convenient to operate. The differentiated angle distribution of the fixed half ring and the movable half ring makes the load-bearing capacity reasonable and the opening and closing effortless. The squirrel cage frame structure takes into account both high load-bearing capacity and lightweight requirements. The introduction of the adapter ring allows the same bracket body to be adapted to different models of engines, which has good versatility and promotion and application value.

[0063] Finally, it should be noted that the features mentioned and / or shown in the above description of exemplary embodiments of the present invention can be combined in the same or similar manner with one or more other embodiments, combined with or substituted for corresponding features in other embodiments. These combined or substituted technical solutions should also be considered to be included within the scope of protection of the present invention.

Claims

1. A transfer bracket for upright testing of solid rocket motors, characterized in that: It includes a fixed half ring (1), a first rotating shaft (2), a first movable half ring (3), a connector (4), a second movable half ring (5), and a second rotating shaft (6); The fixed semi-ring (1) is an arc-shaped structure used for fixed installation on the transfer vehicle; One end of the first movable half ring (3) is rotatably connected to the first end of the fixed half ring (1) via the first rotating shaft (2); One end of the second movable half ring (5) is rotatably connected to the second end of the fixed half ring (1) via the second rotating shaft (6); The other end of the first movable half ring (3) is detachably connected to the other end of the second movable half ring (5) via the connector (4); The fixed half-ring (1), the first movable half-ring (3) and the second movable half-ring (5) together form a complete ring support structure in the connected state of the connector (4) to support the solid rocket motor that is mounted on it in a vertical position; After the connector (4) is removed, the first movable half ring (3) and the second movable half ring (5) can be rotated outward around the first rotating shaft (2) and the second rotating shaft (6) respectively, so that the annular support structure forms an opening channel for the engine nozzle to be moved out.

2. The transfer bracket according to claim 1, characterized in that: The central angle of the fixed half-ring (1) is 240°, and the central angles of the first movable half-ring (3) and the second movable half-ring (5) are both 60°.

3. The transfer bracket according to claim 1, characterized in that: The first rotating shaft (2) and the second rotating shaft (6) are both pins; the two ends of the fixed half ring (1) are respectively provided with first ear seats, and the corresponding ends of the first movable half ring (3) and the second movable half ring (5) are respectively provided with second ear seats. The pin passes through the corresponding first ear seat and second ear seat, so that the first movable half ring (3) and the second movable half ring (5) are respectively hinged to the fixed half ring (1).

4. The transfer bracket according to claim 1, characterized in that: The first movable semi-ring (3) rotates outward around the first rotating shaft (2) by an angle of not less than 60°, and the second movable semi-ring (5) rotates outward around the second rotating shaft (6) by an angle of not less than 60°.

5. The transfer bracket according to claim 1, characterized in that: A cage-like frame structure is adopted; the edges of the fixed semi-ring (1), the first movable semi-ring (3) and the second movable semi-ring (5) are respectively provided with plate-shaped reinforcing structures, and the non-edge parts are respectively provided with tubular reinforcing structures.

6. The transfer bracket according to claim 5, characterized in that: The connector (4) is a connecting bolt, which passes through the plate-shaped reinforcing structure at the corresponding edges of the first movable half ring (3) and the second movable half ring (5) to connect the two in a detachable manner.

7. The transfer bracket according to claim 1, characterized in that: The lower end face of the ring support structure is provided with an installation interface for connecting to the transfer vehicle.

8. The transfer bracket according to claim 7, characterized in that: The upper end face of the annular support structure is provided with a connecting ring for connecting with the rear skirt connecting surface of the solid rocket motor.

9. A method for transporting a solid rocket motor for an upright test using the transfer bracket according to any one of claims 1 to 8, characterized in that, Includes the following steps: Step 1: Fix the fixed half ring (1) to the transfer vehicle, with the opening facing the direction of the transfer vehicle heading towards the test station; Step 2: Install one end of the first movable half ring (3) onto the first end of the fixed half ring (1) through the first rotating shaft (2), so that the first movable half ring (3) can rotate around the first rotating shaft (2); Step 3: Install one end of the second movable half ring (5) onto the second end of the fixed half ring (1) via the second rotating shaft (6) so that the second movable half ring (5) can rotate around the second rotating shaft (6); Step 4: Connect the other end of the first movable half ring (3) to the other end of the second movable half ring (5) through the connector (4), so that the fixed half ring (1), the first movable half ring (3) and the second movable half ring (5) together form a complete ring support structure; Step 5: The solid rocket motor is placed vertically on the ring support structure and connected and fixed. The motor is then transported upright to the test site by a transport vehicle. Step 6: Disconnect the engine from the transfer bracket, lift the engine vertically to detach it from the transfer bracket, and place the engine nozzle inside the annular support structure. Step 7, remove the connector (4), rotate the first movable half ring (3) outward around the first rotating shaft (2) to open, and rotate the second movable half ring (5) outward around the second rotating shaft (6) to open, so that the annular support structure forms an opening channel for the engine nozzle to be moved out. Step 8: The transfer vehicle moves the open transfer bracket horizontally outward, allowing the engine nozzle to pass through the opening channel, thereby achieving interference-free separation of the transfer bracket and the engine nozzle in the horizontal direction.

10. The method according to claim 9, characterized in that: In step 7, the first movable half ring (3) rotates outward around the first rotating shaft (2) by an angle of not less than 60°, and the second movable half ring (5) rotates outward around the second rotating shaft (6) by an angle of not less than 60°.

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