A test device for a rocket landing buffer system

Abstract

This invention provides a test device for a rocket landing cushioning system, including a cushioning bracket and landing legs. Multiple sets of cushioning positioning modules are distributed sequentially from top to bottom on the outer side of the cushioning bracket. Each cushioning positioning module corresponds one-to-one with a positioning point inside the landing leg. Each cushioning positioning module includes a Y-axis floating component, a Z-axis floating component, and a positioning block. Digital display sensor modules are connected to both the Y-axis and Z-axis floating components. A joint connecting rod is also provided at the lower end of the Z-axis floating component. The front end of the positioning block has an installation end face. The beneficial effects of this invention are: simulating a real-world scenario, cryogenic fuel is added before launch. Due to the influence of fuel pressure and low temperature, deformation occurs at each mounting point of the landing leg, changing the initial state of the landing leg. Based on the deformation data of the landing leg, its performance under complex working conditions can be thoroughly understood, assisting researchers in improving the landing leg structure and materials, enhancing the reliability and stability of the rocket landing cushioning system, and reducing the risk of rocket landing.

Description

Technical Field

[0001] This utility model mainly relates to the field of landing buffer test technology, specifically to a test device for a rocket landing buffer system. Background Technology

[0002] In the current field of rocket launch technology, reusable launch vehicles have become one of the core development directions in the aerospace industry due to their significant advantage of greatly reducing the cost of space exploration. The landing cushioning system, as a key component for the safe recovery of reusable rockets, directly determines the success or failure of the rocket recovery mission in terms of its reliability. To ensure the stability of the landing leg structure, it is necessary to test the landing legs' ability to withstand vibration environments during the launch phase. In existing technologies, most landing cushioning system test devices have certain limitations in design. They often focus only on testing the cushioning performance of the landing legs themselves, but ignore a key factor: during the launch and flight of the rocket, the combustion of fuel will generate huge pressure inside the rocket body. This pressure will cause the rocket shell to deform to a certain extent, and the deformation of the shell will be directly transmitted to the landing legs connected to it, changing their original structural state and mechanical properties.

[0003] Due to structural design limitations, existing test devices cannot accurately simulate the complex conditions that closely resemble the initial state of a real launch. This results in a significant deviation between the test environment and the actual working environment, making it impossible to obtain comprehensive and accurate performance data of the landing legs under real conditions. This causes many inconveniences for the design and optimization of the rocket landing buffer system.

[0004] It should be noted that the above content falls within the scope of the inventor's technical knowledge. Due to the vast and complex nature of the technical content in this field, the above content of this application does not necessarily constitute prior art. Utility Model Content

[0005] 1. The technical problem to be solved by the utility model: This invention provides a test device for a rocket landing buffer system to solve the technical problems existing in the background art.

[0006] 2. Technical Solution: To achieve the above objectives, the technical solution provided by this utility model is as follows: a test device for a rocket landing buffer system, comprising a buffer support and landing legs. Multiple sets of buffer positioning modules are distributed sequentially from top to bottom on the outer side of the buffer support. Each buffer positioning module corresponds one-to-one with a positioning point inside the landing leg. The buffer support has a quarter-circle arc structure, and four sets of the buffer support are assembled to form a circle. The number of buffer supports corresponds to the number of landing legs. Each buffer positioning module includes a Y-axis floating component, a Z-axis floating component, and a positioning block. Digital display sensor modules are connected to both the Y-axis and Z-axis floating components. A joint connecting rod is also provided at the lower end of the Z-axis floating component. The front end of the positioning block has an installation end face.

[0007] Furthermore, the Y-axis floating assembly includes a handwheel actuator, a positioning seat, and an execution block. The execution block has two limit blocks at its front end, and the positioning block is embedded in the front end of the execution block on both sides through the limit blocks.

[0008] Furthermore, the execution block includes a moving part and a mounting part, the moving part being located within the positioning seat and slidably connected to it at its bottom.

[0009] Furthermore, the digital display sensing module includes a displacement sensor, a digital display, and a connecting bracket. The displacement sensor is connected to the execution block and the positioning seat respectively through the connecting bracket. The digital display is connected to the displacement sensor through a data cable and is fixed inside the buffer bracket.

[0010] Furthermore, the Z-axis floating assembly includes a locking block, a linkage shaft, and a limiting seat. The locking block is fixed to the lower end of the positioning block, and a through groove is formed at the lower end of the locking block along the Y-axis direction. The limiting seat is fixed to the outside of the buffer bracket, and a floating groove is formed on the limiting seat.

[0011] Furthermore, the linkage shaft passes through the floating groove of the limiting seat, and its upper end is embedded in the through groove of the card block, while its lower end is provided with a locking pin.

[0012] Furthermore, one end of the joint link is movably connected to the linkage shaft via a locking pin, and the other end is fixedly connected to the inner side of the buffer bracket.

[0013] Furthermore, the buffer positioning module also includes a base plate whose lower end is fixedly connected to the buffer bracket, and the Y-axis floating component is fixedly connected to the base plate.

[0014] 3. Beneficial effects: Compared with the prior art, the technical solution provided by this utility model has the following advantages: This experimental device can accurately simulate real-world scenarios. Before launch, cryogenic fuel is added. Due to the influence of fuel pressure and low temperature, the mounting points of the landing legs installed on the outer shell will deform, changing the initial state of the landing legs. Based on the deformation data of the landing legs, we can gain a deeper understanding of their performance under complex working conditions, providing strong support for subsequent design optimization. This will help researchers improve the structure and materials of the landing legs, enhance the reliability and stability of the rocket landing buffer system, and effectively reduce the risk of rocket landing.

[0015] It should be noted that the structures not described in this utility model are the same as or can be implemented using existing technology, and will not be elaborated here, as they do not involve the design points and improvement directions of this utility model. Attached Figure Description

[0016] Figure 1 This is an exploded view of the overall structure of this utility model; Figure 2 This is a partial structural schematic diagram of the present invention; Figure 3 This is a schematic diagram of the structure of this utility model from another angle; Figure 4 This is a schematic diagram of the buffer positioning module structure of this utility model; Figure 5 This is a schematic diagram of another angle buffer positioning module structure of this utility model.

[0017] Figure label: 1. Buffer bracket; 2. Landing leg; 3. Buffer positioning module; 31. Y-axis floating assembly; 311. Handwheel actuator; 312. Positioning seat; 313. Actuating block; 314. Limit stop block; 32. Z-axis floating assembly; 321. Locking block; 322. Linkage shaft; 323. Limiting seat; 324. Locking pin; 33. Digital display sensor module; 331. Displacement sensor; 332. Digital display; 333. Connecting frame; 34. Joint connecting rod; 35. Positioning block; 36. Base plate. Detailed Implementation

[0018] To facilitate understanding of this utility model, a more comprehensive description of the utility model will be given below with reference to the accompanying drawings, which show several embodiments of the utility model. However, the utility model can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided so that the disclosure of the utility model will be more thorough and complete.

[0019] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "page", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0020] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0021] In this utility model, unless otherwise explicitly specified and limited, the terms "installed," "connected," "linked," "fixed," "provided with," and "located in" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0022] See attached document Figure 1-5 A test device for a rocket landing buffer system includes a buffer support 1 and landing legs 2. Multiple sets of buffer positioning modules 3 are distributed from top to bottom on the outer side of the buffer support 1. The buffer positioning modules 3 correspond one-to-one with the positioning points inside the landing legs 2. The buffer support 1 has a quarter-circle arc structure, and four sets of the buffer support 1 are assembled to form a circle. The number of buffer supports 1 and landing legs 2 are set in a corresponding manner. The buffer positioning module 3 includes a Y-axis floating component 31, a Z-axis floating component 32 and a positioning block 35. Digital display sensor modules 33 are connected to both the Y-axis floating component 31 and the Z-axis floating component 32. The lower end of the Z-axis floating component 32 is also provided with a joint connecting rod 34. The front end of the positioning block 35 has an installation end face.

[0023] The rocket landing buffer system test device is a specialized testing equipment designed to simulate the stress and motion state of a rocket buffer system. Its overall structure and functional adaptability are closely based on the actual working scenario of the rocket landing legs. The device includes two core load-bearing components: buffer support 1 and landing legs 2. Buffer support 1 adopts a quarter-circle arc structure design. This arc structure can not only adapt to the circumferential distribution characteristics of the rocket landing legs, but also optimize the distribution of load stress during the test through structural mechanics. When four sets of buffer supports 1 are assembled and enclosed, they can form a complete circular frame. The installation layout of the landing legs at the bottom of the rocket body is matched, and the number of buffer supports 1 corresponds strictly to the number of landing legs 2, ensuring that each set of landing legs can obtain independent and precise test support. The bottom of the landing legs 2 is connected to the bottom of the buffer support 1 through a hinge structure. On the outside of the buffer bracket 1, multiple sets of buffer positioning modules 3 are distributed from top to bottom. These modules form a one-to-one connection with the preset positioning points inside the landing leg 2. Through multi-point collaborative positioning, the overall attitude of the landing leg 2 is stably constrained. The buffer positioning module 3 is the core functional unit for achieving accurate testing. It integrates the Y-axis floating component 31, the Z-axis floating component 32, and the positioning block 35. It also includes a base plate 36 that is fixedly connected to the buffer bracket 1 at the lower end, providing a stable installation reference for the Y-axis floating component 31. The Y-axis floating component 31 is rigidly connected to the base plate 36 by bolts and other fasteners to ensure that the test accuracy is not affected by the shaking of the foundation during the test. The Y-axis floating assembly 31 is responsible for the position adjustment and floating monitoring of the landing legs in the Y-axis direction (i.e., horizontal radial direction). It consists of a handwheel actuator 311, a positioning seat 312, and an actuator block 313. The handwheel actuator 311 adopts a high-precision threaded transmission structure. The operator can drive the actuator block 313 to move smoothly along the guide rail of the positioning seat 312 by rotating the handwheel, thereby realizing fine-tuning of the position in the Y-axis direction. The actuator block 313 is divided into a moving part and a mounting part. The moving part is embedded in the positioning seat 312, and its bottom slides against the guide rail of the positioning seat 312 through a slider. The connection structure ensures smooth movement and minimizes the deviation of the movement trajectory of the actuator 313 by constraining the straightness of the guide rail. Two limit blocks 314 are provided at the front end of the actuator 313, and the two limit blocks 314 are symmetrically distributed. The two sides of the positioning block 35 are embedded in the front end of the actuator 313 through the limit blocks 314, forming an embedded constraint structure. This structure can prevent the positioning block 35 from shifting laterally during the test and provide a certain buffer margin for the positioning block 35 to avoid damage to the components caused by rigid contact. The Z-axis floating assembly 32 is responsible for positioning the landing leg in the Z-axis direction (i.e., the vertical axis). It adjusts the positioning based on deformation data and includes a locking block 321, a linkage shaft 322, and a limiting seat 323. The locking block 321 is fixed to the lower end of the positioning block 35 with high-strength bolts, forming a rigid connection to ensure that the Z-axis displacement of the positioning block 35 can be fully transmitted to the locking block 321. A through groove is formed at the lower end of the locking block 321 along the Y-axis direction. The width of this through groove matches the diameter of the linkage shaft 322, providing space for the upper end of the linkage shaft 322 to be inserted. The limiting seat 323 is fixed to the outside of the buffer bracket 1 with high-strength bolts and has a floating groove extending along the Z-axis direction. The length and width of the floating groove are determined based on the test... The maximum floating stroke design of the Z-axis required for the test not only provides motion guidance for the linkage shaft 322, but also limits the excessive displacement of the linkage shaft 322 through the groove wall. The linkage shaft 322 passes through the floating groove of the limit seat 323, and its upper end is embedded in the through groove of the locking block 321. The lower end is provided with a locking pin 324. The locking pin 324 not only prevents the linkage shaft 322 from falling out of the limit seat 323, but also provides a mounting fulcrum for the connection of the joint link 34. One end of the joint link 34 is movably connected to the linkage shaft 322 through the locking pin 324, and the other end is fixedly connected to the inner side of the buffer bracket 1. This flexible connection structure can effectively absorb the angular deviation during the test and avoid stress concentration caused by rigid constraints. The digital display sensor module 33 is a key component for realizing the quantitative acquisition of test data. It consists of a displacement sensor 331, a digital display 332, and a connecting frame 333. The displacement sensor 331 adopts a high-precision optical grating sensor or magnetic grating sensor, with a measurement accuracy of up to 0.001mm. It is connected to the execution block 313 and the positioning seat 312 through the connecting frame 333. The part connected to the execution block 313 moves synchronously with the execution block 313, while the part connected to the positioning seat 312 remains fixed. The relative displacement between the two is the floating data in the Y-axis direction. The digital display 332 is connected to the displacement sensor 331 through a data cable and has a data storage function. During the test, the digital display 332 is adjusted according to the known deformation data. The digital display 332 is fixed inside the buffer bracket 1, which is convenient for the operator to observe and avoids interference caused by test vibration. The device's operating logic follows a closed-loop process of "installation-debugging-testing," as detailed below: During the installation phase, the number of buffer supports 1 (usually the same as the number of landing legs 2) and the distribution density of buffer positioning modules 3 are determined based on the size and structural characteristics of the landing legs 2. Longer landing legs require more modules to achieve multi-point support, while shorter landing legs can be appropriately reduced. During installation, the landing legs 2 are fixedly connected to the front mounting faces of the positioning blocks 35 of each set of buffer positioning modules 3 with bolts, ensuring that the axis of the landing legs 2 coincides with the central axis of the circle formed by the buffer supports 1. Subsequently, the installation position is adjusted by rotating the handwheel actuator 311 of the Y-axis floating assembly 31: the handwheel actuator 311 drives the actuator block 313 along the positioning... The seat 312 moves, causing the positioning block 35 and landing leg 2 to make fine adjustments in the Y-axis direction. The digital display 332 displays the adjustment amount in real time until the position deviation of the landing leg 2 is controlled within the design allowable range. After the adjustment is in place, the locking handwheel actuator 311 is tightened to lock it in the locked state to prevent positional deviation during the test. It is worth noting that the buffer positioning module 3 near the lower end of the landing leg 2 only retains the Z-axis floating component 32 and omits the Y-axis floating component 31. This is because the lower end of the landing leg mainly bears the vertical load during landing, and the force in the Y-axis direction is small. There is no need to verify the data in this direction, which simplifies the structure and reduces the test cost. During the testing phase, the entire device was mounted on a vibration table, which simulated the impact vibration environment (including vertical vibration, horizontal vibration, and combined vibration) during rocket landing. During the vibration, the landing leg 2 would float in the Y-axis and Z-axis directions under the impact force: the floating in the Y-axis direction would cause the actuator block 313 to slide along the positioning seat 312, and the displacement sensor 331 would capture this floating amount in real time; the floating in the Z-axis direction would be transmitted to the locking block 321 through the positioning block 35, which would cause the linkage shaft 322 to move up and down along the floating groove of the limit seat 323; the joint link 34 would adjust its own angle during this process to adapt to the offset of the linkage shaft 322 and avoid generating additional resistance. Before the test, the positions of each installation point were adjusted according to the known deformation. During the adjustment process, the accuracy of the data could be observed in real time through the digital display 332. Based on the simulation of real data, the ability of the landing legs to withstand the vibration environment during the launch phase was analyzed, providing strong support for the optimized design of the rocket landing buffer system.

[0024] The above-described embodiments are merely illustrative of certain implementations of this utility model, and their descriptions are relatively specific and detailed. However, they should not be construed as limiting the scope of this utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these modifications and improvements all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model patent should be determined by the appended claims.

Claims

1. A rocket landing cushion system test apparatus characterized by: The system includes a buffer support (1) and landing legs (2). Multiple sets of buffer positioning modules (3) are distributed from top to bottom on the outer side of the buffer support (1). The buffer positioning modules (3) correspond one-to-one with the positioning points inside the landing legs (2). The buffer support (1) has a quarter-circle arc structure, and the four sets of buffer supports (1) are assembled to form a circle. The number of buffer supports (1) corresponds to the number of landing legs (2). The buffer positioning module (3) includes a Y-axis floating component (31), a Z-axis floating component (32), and a positioning block (35). A digital display sensor module (33) is connected to both the Y-axis floating component (31) and the Z-axis floating component (32). A joint connecting rod (34) is also provided at the lower end of the Z-axis floating component (32). The front end of the positioning block (35) has an installation end face.

2. The rocket landing buffer system test device according to claim 1, characterized in that: The Y-axis floating assembly (31) includes a handwheel actuator (311), a positioning seat (312), and an execution block (313). The execution block (313) has two limit blocks (314) at its front end. The positioning block (35) is embedded in the front end of the execution block (313) on both sides through the limit blocks (314).

3. The rocket landing cushion system test device of claim 2, wherein: The execution block (313) includes a moving part and a mounting part. The moving part is located inside the positioning seat (312) and its bottom is slidably connected to it.

4. The rocket landing cushion system test device of claim 3, wherein: The digital display sensing module (33) includes a displacement sensor (331), a digital display (332), and a connecting frame (333). The displacement sensor (331) is connected to the execution block (313) and the positioning seat (312) respectively through the connecting frame (333). The digital display (332) is connected to the displacement sensor (331) through a data cable. The digital display (332) is fixed inside the buffer bracket (1).

5. The rocket landing cushion system test device of claim 1, wherein: The Z-axis floating assembly (32) includes a locking block (321), a linkage shaft (322), and a limiting seat (323). The locking block (321) is fixed to the lower end of the positioning block (35). A through groove is provided at the lower end of the locking block (321) along the Y-axis direction. The limiting seat (323) is fixed to the outside of the buffer bracket (1). A floating groove is provided on the limiting seat (323).

6. The rocket landing cushion system test device of claim 5, wherein: The linkage shaft (322) passes through the floating groove of the limiting seat (323), and its upper end is embedded in the through groove of the card block (321), and its lower end is provided with a locking pin (324).

7. The rocket landing cushion system test device of claim 6, wherein: One end of the joint link (34) is movably connected to the linkage shaft (322) via a locking pin (324), and the other end is fixedly connected to the inner side of the buffer bracket (1).

8. The rocket landing cushion system test device of claim 1, wherein: The buffer positioning module (3) also includes a base plate (36) whose lower end is fixedly connected to the buffer bracket (1), and the Y-axis floating component (31) is fixedly connected to the base plate (36).

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