A test platform suitable for a rocket landing leg return mode

Abstract

The application provides a test platform suitable for a rocket landing leg return mode, which comprises a support assembly, a guide mechanism, a hoisting device and an adjustable landing platform, the guide mechanism is installed on the support assembly, the hoisting device is installed on the top of the support assembly, and the adjustable landing platform is installed on the bottom of the support assembly.

Description

Technical Field

[0001] This invention relates to the field of rocket landing leg design technology, and in particular to a test platform suitable for rocket landing leg return methods. Background Technology

[0002] For reusable rockets, the two main return methods are landing leg recovery and launch tower cantilever recovery. Landing leg recovery is the most common method. During reentry, the rocket's landing legs deploy, the rocket descends to the landing site, and the landing legs make contact with the ground, completing the landing. The design of the landing legs plays a crucial role in the safe recovery and return of the rocket.

[0003] Currently, there is no mature test platform solution for verifying landing leg return technology. The return scheme is mostly verified through actual launches. There is no test platform for full-system testing and verification.

[0004] Existing technical solutions verify recovery technology through actual launches, but due to launch costs and safety restrictions, multiple thorough verifications are not possible. Without a large amount of research and experimental data, it is impossible to obtain crucial data such as the strength, stiffness, and deformation of the landing legs, and the strength, stiffness, and deformation of the shell and internal structural components at different landing angles.

[0005] If the landing legs and rocket casing deform excessively or lack sufficient strength during launch, it may lead to unstable recovery and landing, causing the rocket to tip over and resulting in landing failure. Insufficient strength of the internal structure of the rocket may directly affect rocket control during recovery, also leading to recovery failure.

[0006] Under these conditions, to ensure launch safety, the strength of the rocket's recovery stage needs to be greatly enhanced, which results in a greater excess mass. Furthermore, insufficient testing cannot guarantee the safety of the landing legs and the first-stage rocket body. Summary of the Invention

[0007] The technical problem to be solved by the present invention is to provide a test platform suitable for rocket landing leg return mode, which addresses the shortcomings of the prior art.

[0008] The technical solution of the present invention to solve the above-mentioned technical problems is as follows: A test platform suitable for rocket landing leg return mode, comprising: a support assembly, a guiding mechanism, a lifting device and an adjustable landing platform, wherein the guiding mechanism is installed on the support assembly, the lifting device is installed on the top of the support assembly, and the adjustable landing platform is installed on the bottom of the support assembly.

[0009] The beneficial effects of adopting the technical solution of this invention are as follows: The lifting device is used for lifting the rocket body, hoisting the first-stage rocket body to the test height. The rocket body descends freely along the guide mechanism, and under the action of gravitational acceleration, it can reach the predetermined test speed. The test platform is mainly designed for the landing leg return method, and is used to verify the strength and stiffness of the supporting legs after impact with the adjustable landing platform at different angles and speeds during descent, thus improving the reliability of reusable rockets. Multiple verifications of the landing leg return method can be achieved, improving the safety of reusable rocket recovery while reducing launch test risks and costs. Multiple test verifications can be performed on the first-stage rocket body, providing a data foundation for the overall rocket unit to assess the performance of the first stage.

[0010] Furthermore, the support assembly includes: a main support tower, a pair of auxiliary support towers, and an operating platform. The main support tower and the pair of auxiliary support towers are arranged in a triangular pattern. The operating platform is installed on the top of the main support tower and the top of the pair of auxiliary support towers. The lifting device is installed on the operating platform. The guide mechanism is installed on each of the pair of auxiliary support towers. The lifting device and the adjustable landing platform are both located between the main support tower and the pair of auxiliary support towers.

[0011] The beneficial effects of adopting the above-mentioned further technical solution are as follows: the main support tower and the auxiliary support tower are used for system support, and an operating platform is fixed at the top of the tower. The operating platform is fixed to the upper end of the main support tower and the auxiliary support tower, and a lifting device is fixed to the operating platform, which together provide mechanical support for the test platform. The three support towers are distributed in a triangular pattern, which improves the stability of the system support structure.

[0012] Furthermore, the guiding mechanism includes at least one pair of telescopic devices and one pair of guide rails. The pair of telescopic devices are respectively installed on the pair of auxiliary support towers, and the pair of guide rails are respectively installed on the pair of telescopic devices. Both of the pair of guide rails are located between the pair of auxiliary support towers.

[0013] The beneficial effects of adopting the above-mentioned further technical solution are: the guide mechanism is installed on the side of the auxiliary support tower. When installing the first stage rocket body, the guide mechanism can be retracted. After the first stage is in place, the guide mechanisms on the left and right sides move towards the middle and extend. The guide mechanism contacts the slider, restricting the slider to slide only along the guide mechanism. The guide mechanism and the slider together restrict the first stage rocket body.

[0014] Furthermore, the telescopic device includes: a first sleeve, a second sleeve, and a telescopic cylinder. The two ends of the telescopic cylinder are respectively connected to the auxiliary support tower and the guide rail. The first sleeve and the second sleeve are both sleeved on the outside of the telescopic cylinder. One end of the first sleeve is connected to the auxiliary support tower, one end of the second sleeve is slidably mounted on the other end of the first sleeve, and the other end of the second sleeve is connected to the guide rail.

[0015] The beneficial effects of adopting the above-mentioned further technical solution are: the telescopic guide rail is installed on the side of the auxiliary support tower. When installing the first stage rocket body, the guide rail can be retracted. After the first stage is in place, the left and right guide rails move towards the middle and extend. The guide rail contacts the slider, restricting the slider to slide only along the guide rail groove. The guide rail and the slider together restrict the first stage rocket body.

[0016] Furthermore, an initial loading device is installed on the top of the support assembly. The initial loading device includes an arrow body locking device and a loading device, with the arrow body locking device mounted on the loading device.

[0017] The beneficial effects of adopting the above-mentioned further technical solutions are as follows: The initial loading device is used to provide initial kinetic energy to the rocket body during high-speed or stall descent. The design of the initial loading device and the adjustable landing platform can simulate the landing of the rocket's first-stage body at different angles and speeds. The initial loading device can provide initial kinetic energy to the system. If the maximum speed of the rocket body's free fall along the guide rail still cannot meet the test speed requirements, the rocket body is lifted to the maximum height of the test system. The operating platform is equipped with an initial loading device consisting of a rocket body locking device and a loading device. The locking device can lock and fix the adapter slider.

[0018] Furthermore, the arrow body locking device is a pin connected to an electric push rod or a pin connected to a hydraulic push rod, and the loading device is a pneumatic ejection loading device or an electromagnetic ejection loading device.

[0019] The beneficial effects of adopting the above-mentioned further technical solution are as follows: The initial loading device is used to provide initial kinetic energy to the rocket body during high-speed or stall descent. The initial loading device can be a pneumatic or electromagnetic ejection loading device, which can provide initial kinetic energy to the system. The loading device is used to provide initial vertical downward kinetic energy to the system. After the rocket body locking device locks the rocket body, the pneumatic or electromagnetic ejection force of the loading device acts on the upper surface of the adapter mounting base. After the rocket body locking device unlocks, the ejection push rod pushes the rocket body downward, thereby verifying the landing legs and rocket body strength under different descent kinetic energies.

[0020] Furthermore, the adjustable landing platform includes: a fixed platform, multiple attitude adjustment cylinders, and a landing platform, wherein the multiple attitude adjustment cylinders are mounted on the fixed platform, and the landing platform is mounted on the multiple attitude adjustment cylinders.

[0021] The beneficial effects of adopting the above-mentioned further technical solution are: the adjustable landing platform design can simulate the landing of the first stage of a rocket at different angles. By adjusting the extension and retraction of multiple attitude adjustment cylinders, the landing platform can be adjusted at different angles to verify different landing angles of the first stage.

[0022] Furthermore, the lifting device is a winch with lifting and hoisting function, a crane with lifting and hoisting function, a counterweight with lifting and hoisting function, or a lifting cylinder with lifting and hoisting function.

[0023] The beneficial effects of adopting the above-mentioned further technical solution are: the lifting device is used for rocket body hoisting, lifting the first-stage rocket body to the test height. This facilitates the selection of the lifting device according to actual needs, improving its applicability.

[0024] Furthermore, the lifting device is detachably connected to a sub-stage rocket body, the top of the sub-stage rocket body is equipped with a rocket body adapter block, the rocket body adapter block is equipped with a slider adapted to the guide mechanism, and the bottom of the sub-stage rocket body is equipped with multiple support legs.

[0025] The beneficial effects of adopting the above-mentioned further technical solution are: multiple test verifications can be carried out on the first-stage rocket body, thereby providing a data basis for the overall rocket unit to assess the performance of the first stage. The telescopic guide mechanism is installed on the side of the auxiliary support tower. When installing the first-stage rocket body, the guide mechanism can be retracted. After the first stage is in place, the guide mechanisms on the left and right sides extend towards the center, contacting the slider and restricting the slider to slide only along the guide mechanism. The guide mechanism and the slider together restrict the first-stage rocket body.

[0026] Furthermore, the first-stage rocket body is equipped with a testing device for detecting the strength, stiffness, deformation, structural strength, and internal structural strength of the rocket body under impact load.

[0027] The beneficial effects of adopting the above-mentioned further technical solutions are: by arranging detection devices on the rocket body, stress and strain data at different locations on the rocket body can be monitored in real time at the moment of landing. For internal material cracks, non-destructive testing equipment such as ultrasonic or magnetic flaw detection can be used to detect the internal stress damage of the material.

[0028] The advantages of additional aspects of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0029] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0030] Figure 1 This is one of the structural schematic diagrams of an experimental platform for rocket landing leg return mode provided in an embodiment of the present invention.

[0031] Figure 2 This is the second structural schematic diagram of a test platform for rocket landing leg return mode provided in an embodiment of the present invention.

[0032] Figure 3 The third schematic diagram of the structure of the test platform for rocket landing leg return mode provided in the embodiment of the present invention.

[0033] Figure 4 The fourth schematic diagram of the structure of the test platform for rocket landing leg return mode provided in the embodiments of the present invention.

[0034] Figure 5 The fifth schematic diagram of the structure of the test platform for rocket landing leg return mode provided in the embodiments of the present invention.

[0035] Figure 6 This is the sixth structural schematic diagram of a test platform for rocket landing leg return mode provided in an embodiment of the present invention.

[0036] Figure 7 The seventh schematic diagram of the structure of the test platform for rocket landing leg return mode provided in the embodiments of the present invention.

[0037] Explanation of reference numerals: 1. Support assembly; 2. Guiding mechanism; 3. Lifting device; 4. Adjustable landing platform; 5. Main support tower; 6. Auxiliary support tower; 7. Operating platform; 8. Telescopic cylinder; 9. Guide rail; 10. Initial loading device; 11. Rocket body locking device; 12. Loading device; 13. Fixed platform; 14. Attitude adjustment cylinder; 15. Landing platform; 16. First stage rocket body; 17. Rocket body adapter block; 18. Sliding block; 19. Telescopic device; 20. First sleeve; 21. Second sleeve. Detailed Implementation

[0038] The principles and features of the present invention are described below with reference to the accompanying drawings. The embodiments described are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0039] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0040] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0041] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0042] In the description of the embodiments of the present invention, it should be noted that if terms such as "upper", "lower", "horizontal", "inner" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of the invention is usually placed during use, they are only for the convenience of describing the present 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, and therefore should not be construed as a limitation of the present invention.

[0043] In the description of the embodiments of the present invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" 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 the present invention according to the specific circumstances.

[0044] like Figures 1 to 7 As shown, this embodiment of the invention provides a test platform suitable for rocket landing leg return mode, including: a support assembly 1, a guide mechanism 2, a lifting device 3, and an adjustable landing platform 4. The guide mechanism 2 is installed on the support assembly 1, the lifting device 3 is installed on the top of the support assembly 1, and the adjustable landing platform 4 is installed on the bottom of the support assembly 1.

[0045] The beneficial effects of adopting the technical solution of this invention are as follows: The lifting device is used for lifting the rocket body, hoisting the first-stage rocket body to the test height. The rocket body descends freely along the guide mechanism, and under the action of gravitational acceleration, it can reach the predetermined test speed. The test platform is mainly designed for the landing leg return method, and is used to verify the strength and stiffness of the supporting legs after impact with the adjustable landing platform at different angles and speeds during descent, thus improving the reliability of reusable rockets. Multiple verifications of the landing leg return method can be achieved, improving the safety of reusable rocket recovery while reducing launch test risks and costs. Multiple test verifications can be performed on the first-stage rocket body, providing a data foundation for the overall rocket unit to assess the performance of the first stage.

[0046] The support assembly 1 can be a frame structure assembled from multiple connecting rods. The adjustable landing platform 4 can simulate ground design.

[0047] The test platform for rocket landing leg return mode provided by the embodiments of the present invention provides a verification platform for the return of the landing leg first stage (first stage rocket body), and can perform multiple test verifications on the first stage rocket body, thereby providing a data basis for the overall rocket unit to assess the performance of the first stage.

[0048] The test platform (suitable for rocket landing leg return methods) verifies the landing leg landing method. It can hoist the first-stage rocket body to different test heights, and adjust the rocket body's attitude relative to the ground platform (adjustable landing platform) during landing. The descent direction is determined by a guide mechanism, and initial kinetic energy is adjusted by releasing or utilizing the thrust of the loading device at different heights. The test platform (suitable for rocket landing leg return methods) can simulate the landing of the first-stage rocket body at different angles and velocities. By deploying sensors on the rocket body, stress and strain data at different locations of the rocket body can be monitored in real time during landing. For internal material cracks, non-destructive testing equipment such as ultrasonic or magnetic particle inspection can be used to detect internal stress damage.

[0049] like Figures 1 to 7 As shown, the support assembly 1 further includes: a main support tower 5, a pair of auxiliary support towers 6, and an operating platform 7. The main support tower 5 and the pair of auxiliary support towers 6 are arranged in a triangle. The operating platform 7 is installed on the top of the main support tower 5 and the top of the pair of auxiliary support towers 6. The lifting device 3 is installed on the operating platform 7. The guide mechanism 2 is installed on each of the pair of auxiliary support towers 6. The lifting device 3 and the adjustable landing platform 4 are both located between the main support tower 5 and the pair of auxiliary support towers 6.

[0050] The beneficial effects of adopting the above-mentioned further technical solution are as follows: the main support tower and the auxiliary support tower are used for system support, and an operating platform is fixed at the top of the tower. The operating platform is fixed to the upper end of the main support tower and the auxiliary support tower, and a lifting device is fixed to the operating platform, which together provide mechanical support for the test platform. The three support towers are distributed in a triangular pattern, which improves the stability of the system support structure.

[0051] The operating platform 7 may include a base plate and a fence, with the fence installed on the base plate. The base plate may have through holes for connecting the lifting device to the first-stage rocket body.

[0052] like Figures 1 to 7 As shown, the guiding mechanism 2 further includes at least a pair of telescopic devices 19 and a pair of guide rails 9. The pair of telescopic devices 19 are respectively installed on the pair of auxiliary support towers 6, and the pair of guide rails 9 are respectively installed on the pair of telescopic devices 19. The pair of guide rails 9 are both located between the pair of auxiliary support towers 6.

[0053] The beneficial effects of adopting the above-mentioned further technical solution are: the guide mechanism is installed on the side of the auxiliary support tower. When installing the first stage rocket body, the guide mechanism can be retracted. After the first stage is in place, the guide mechanisms on the left and right sides move towards the middle and extend. The guide mechanism contacts the slider, restricting the slider to slide only along the guide mechanism. The guide mechanism and the slider together restrict the first stage rocket body.

[0054] like Figures 1 to 7 As shown, the telescopic device 19 further includes: a first sleeve 20, a second sleeve 21, and a telescopic cylinder 8. The two ends of the telescopic cylinder 8 are respectively connected to the auxiliary support tower 6 and the guide rail 9. The first sleeve 20 and the second sleeve 21 are both sleeved on the outside of the telescopic cylinder 8. One end of the first sleeve 20 is connected to the auxiliary support tower 6, one end of the second sleeve 21 is slidably installed on the other end of the first sleeve 20, and the other end of the second sleeve 21 is connected to the guide rail 9.

[0055] The beneficial effects of adopting the above-mentioned further technical solution are: the telescopic guide rail is installed on the side of the auxiliary support tower. When installing the first stage rocket body, the guide rail can be retracted. After the first stage is in place, the left and right guide rails move towards the middle and extend. The guide rail contacts the slider, restricting the slider to slide only along the guide rail groove. The guide rail and the slider together restrict the first stage rocket body.

[0056] As an alternative to the telescopic hydraulic cylinder 8, a pneumatic cylinder or an electric actuator can be used to extend and retract the guide rail. A sliding groove can be provided on the guide rail 9.

[0057] A telescopic device, a first sleeve 19, and a second sleeve 20 can be fitted onto the outside of each telescopic cylinder 8. One end of the first sleeve 19 can be mounted on the auxiliary support tower 6, and one end of the second sleeve 20 is slidably mounted in the other end of the first sleeve 19. The other end of the second sleeve 20 is connected to the guide rail 9. Both the first sleeve 19 and the second sleeve 20 can be cuboid frame structures. Limit plates are provided at the other ends of both the first sleeve 19 and the second sleeve 20 to prevent the second sleeve 20 from dislodging from the first sleeve 19.

[0058] As an alternative solution for connecting the two ends of the telescopic cylinder 8 to the auxiliary support tower 6 and the guide rail 9 respectively, the two ends of the telescopic cylinder 8 can be connected to the first sleeve and the second sleeve respectively.

[0059] like Figures 1 to 7 As shown, further, an initial loading device 10 is installed on the top of the support assembly 1. The initial loading device 10 includes an arrow body locking device 11 and a loading device 12, with the arrow body locking device 11 mounted on the loading device 12.

[0060] The beneficial effects of adopting the above-mentioned further technical solutions are as follows: The initial loading device is used to provide initial kinetic energy to the rocket body during high-speed or stall descent. The design of the initial loading device and the adjustable landing platform can simulate the landing of the rocket's first-stage body at different angles and speeds. The initial loading device can provide initial kinetic energy to the system. If the maximum speed of the rocket body's free fall along the guide rail still cannot meet the test speed requirements, the rocket body is lifted to the maximum height of the test system. The operating platform is equipped with an initial loading device consisting of a rocket body locking device and a loading device. The locking device can lock and fix the adapter slider.

[0061] Furthermore, the arrow body locking device 11 is a pin connected to an electric push rod or a pin connected to a hydraulic push rod, and the loading device 12 is a pneumatic ejection loading device or an electromagnetic ejection loading device.

[0062] The beneficial effects of adopting the above-mentioned further technical solution are as follows: The initial loading device is used to provide initial kinetic energy to the rocket body during high-speed or stall descent. The initial loading device can be a pneumatic or electromagnetic ejection loading device, which can provide initial kinetic energy to the system. The loading device is used to provide initial vertical downward kinetic energy to the system. After the rocket body locking device locks the rocket body, the pneumatic or electromagnetic ejection force of the loading device acts on the upper surface of the adapter mounting base. After the rocket body locking device unlocks, the ejection push rod pushes the rocket body downward, thereby verifying the landing legs and rocket body strength under different descent kinetic energies.

[0063] like Figures 1 to 7As shown, the adjustable landing platform 4 further includes: a fixed platform 13, a plurality of attitude adjustment cylinders 14 and a landing platform 15, wherein the plurality of attitude adjustment cylinders 14 are mounted on the fixed platform 13 and the landing platform 15 is mounted on the plurality of attitude adjustment cylinders 14.

[0064] The beneficial effects of adopting the above-mentioned further technical solution are: the adjustable landing platform design can simulate the landing of the first stage of a rocket at different angles. By adjusting the extension and retraction of multiple attitude adjustment cylinders, the landing platform can be adjusted at different angles to verify different landing angles of the first stage.

[0065] The fixed platform 13 and the landing platform 15 can be, but are not limited to, circular, square, rectangular, triangular, elliptical, or rhomboid plate structures. Multiple attitude adjustment cylinders 14 can be evenly spaced at the top of the fixed platform 13, and all cylinders 14 can be adjacent to the perimeter of the fixed platform 13. This facilitates rapid adjustment of the landing platform 15's angle.

[0066] Furthermore, the lifting device 3 is a winch with lifting and hoisting function, a crane with lifting and hoisting function, a counterweight with lifting and hoisting function, or a lifting cylinder with lifting and hoisting function.

[0067] The beneficial effects of adopting the above-mentioned further technical solution are: the lifting device is used for rocket body hoisting, lifting the first-stage rocket body to the test height. This facilitates the selection of the lifting device according to actual needs, improving its applicability.

[0068] like Figures 1 to 7 As shown, further, the lifting device 3 is detachably connected to a sub-stage rocket body 16, the top of the sub-stage rocket body 16 is equipped with a rocket body adapter block 17, the rocket body adapter block 17 is equipped with a slider 18 adapted to the guide mechanism 2, and the bottom of the sub-stage rocket body 16 is equipped with multiple support legs.

[0069] The beneficial effects of adopting the above-mentioned further technical solution are: multiple test verifications can be carried out on the first-stage rocket body, thereby providing a data basis for the overall rocket unit to assess the performance of the first stage. The telescopic guide mechanism is installed on the side of the auxiliary support tower. When installing the first-stage rocket body, the guide mechanism can be retracted. After the first stage is in place, the guide mechanisms on the left and right sides extend towards the center, contacting the slider and restricting the slider to slide only along the guide mechanism. The guide mechanism and the slider together restrict the first-stage rocket body.

[0070] The first-stage rocket body 16 and the rocket body adapter block 17 can be cylindrical structures. There can be two sliders 18, which can also be cylindrical structures, and a pair of sliders 18 are respectively set on both sides of the rocket body adapter block 17.

[0071] Furthermore, the first-stage rocket body 16 is equipped with a testing device for detecting the strength, stiffness, deformation, structural strength, and internal structural strength of the rocket body under impact load.

[0072] The beneficial effects of adopting the above-mentioned further technical solutions are: by arranging detection devices on the rocket body, stress and strain data at different locations on the rocket body can be monitored in real time at the moment of landing. For internal material cracks, non-destructive testing equipment such as ultrasonic or magnetic flaw detection can be used to detect the internal stress damage of the material.

[0073] The sensors used for detection may include, but are not limited to, pressure sensors, displacement sensors, angle sensors, resistance sensors, photoelectric sensors, and / or capacitance sensors.

[0074] The test platform provided in this invention, applicable to the return of rocket landing legs, provides a verification platform for the return of the landing legs of a reusable rocket's first stage. The test platform mainly consists of a main support tower, an auxiliary support tower, a telescopic guide rail (guiding mechanism), an adjustable landing platform, an operating platform, a lifting device, an initial loading device, and a rocket body adapter slider (rocket body adapter block and slider), etc.

[0075] The main support tower and auxiliary support towers are used for system support. An operating platform is fixed to the top of each tower (the main support tower and a pair of auxiliary support towers), collectively providing mechanical support for the test platform. The three support towers (the main support tower and a pair of auxiliary support towers) are arranged in a triangular pattern, enhancing the stability of the system support structure.

[0076] The auxiliary telescopic guide rail (guide mechanism) is installed on the side of the auxiliary support tower. When installing the first stage rocket body, the guide rail can be retracted. After the first stage is in place, the left and right guide rails move towards the middle and extend. The guide rail contacts the slider, restricting the slider to slide only along the guide rail groove. The guide rail and the slider together restrict the first stage rocket body.

[0077] The adjustable landing platform consists of a fixed platform, an adjustment device (multiple attitude adjustment cylinders), and an adjustment platform (landing platform). Multiple sets of cylinders (attitude adjustment cylinders) are installed between the adjustment platform (landing platform) and the fixed platform. By extending and retracting these cylinders, different angles of the adjustment platform (landing platform) can be achieved, which is used to verify different landing angles of the first stage (first stage rocket body).

[0078] The operating platform is fixed to the upper end of the main support tower and a pair of auxiliary support towers. The operating platform is equipped with lifting devices and initial loading devices, etc.

[0079] The lifting device is used for hoisting the rocket body. It can be a winch, crane, counterweight, or hydraulic cylinder, or any other device with lifting capabilities. The initial loading device, such as a pneumatic or electromagnetic catapult, provides initial kinetic energy to the system. The lifting device is used to lift the first-stage rocket body to the test height. The initial loading device is used to verify that it provides initial kinetic energy to the rocket body during high-speed or stall descent.

[0080] The rocket body adapter slider is installed on the upper part of the first stage (first stage rocket body) and connected and fixed to the rocket body. Sliders are provided on the left and right sides. The adapter slider (rocket body adapter slider) consists of two parts: a mounting base and a slider. The mounting base needs to be designed with a connection structure according to the installation interface of different rocket body models to ensure a reliable connection with the recovered rocket body. The slider is of standard form and is used to mate with the guide rail.

[0081] There are two main types of rocket descent speed control. The first type involves the rocket falling freely along a guide rail, reaching the predetermined test speed under the influence of gravity. In this case, only the lifting device, such as the winch motor, needs to automatically unlock and accelerate to the test speed under its own weight. No additional structure is required.

[0082] If the maximum freefall speed of the rocket body along the guide rail still cannot meet the test speed requirements, the rocket body is hoisted to the maximum height of the test system (a test platform suitable for rocket landing leg return methods). The initial loading device set on the operating platform consists of a rocket body locking device and a loading device. The locking device (rocket body locking device) can lock and fix the adapter slider (rocket body adapter block and slider). The locking device (rocket body locking device) can be a pin structure under the action of an electric push rod or a hydraulic push rod. The loading device is used to provide the system with initial vertical downward kinetic energy. After the locking device locks the rocket body, the loading device's gas ejection or electromagnetic ejection force acts on the upper surface of the adapter mounting base (rocket body adapter block). After the locking device (rocket body locking device) unlocks, the ejection push rod pushes the rocket body downward, thereby verifying the strength of the landing leg and the rocket body under different landing kinetic energies.

[0083] The experimental setup (a test platform suitable for rocket landing leg return methods) allows for multiple verifications of the landing leg return method. The test results enable rocket system engineers to monitor the strength and deformation of the support legs, the structural strength of the rocket body, and the strength of internal components and structures under impact loads during the return and landing process using sensors and testing equipment. This improves the safety of reusable rocket recovery and reduces launch test risks and costs.

[0084] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A test platform suitable for rocket landing leg return mode, characterized in that, include: The system comprises a support assembly, a guiding mechanism, a lifting device, and an adjustable landing platform. The guiding mechanism is mounted on the support assembly, the lifting device is mounted on the top of the support assembly, and the adjustable landing platform is mounted on the bottom of the support assembly. The support assembly includes a main support tower, a pair of auxiliary support towers, and an operating platform. The main support tower and the pair of auxiliary support towers are arranged in a triangular configuration. The operating platform is mounted on the top of both the main support tower and the pair of auxiliary support towers. The lifting device is mounted on the operating platform. The guiding mechanism is mounted on each of the pair of auxiliary support towers. The lifting device and the adjustable landing platform are located between the main support tower and the pair of auxiliary support towers. The guiding mechanism includes at least one pair of telescopic devices and a pair of guide rails. The pair of telescopic devices are respectively mounted on the pair of auxiliary support towers, and the pair of guide rails are respectively mounted on the pair of telescopic devices. The pair of guide rails are located between the pair of auxiliary support towers; the telescopic device includes: a first sleeve, a second sleeve, and a telescopic cylinder, the two ends of the telescopic cylinder are respectively connected to the auxiliary support tower and the guide rail, the first sleeve and the second sleeve are both sleeved on the outside of the telescopic cylinder, one end of the first sleeve is connected to the auxiliary support tower, one end of the second sleeve is slidably installed on the other end of the first sleeve, and the other end of the second sleeve is connected to the guide rail; an initial loading device is installed on the top of the support assembly, the initial loading device includes: a rocket body locking device and a loading device, the rocket body locking device is installed on the loading device; the lifting device is detachably connected to a first-stage rocket body; a detection device for detecting the strength of the support leg, the stiffness of the support leg, the deformation of the support leg, the structural strength of the rocket body, and the strength of the internal single-unit structure of the rocket body under impact load is installed on the first-stage rocket body.

2. The test platform for rocket landing leg return mode according to claim 1, characterized in that, The arrow body locking device is a pin connected to an electric push rod or a pin connected to a hydraulic push rod, and the loading device is a pneumatic ejection loading device or an electromagnetic ejection loading device.

3. The test platform for rocket landing leg return mode according to claim 1, characterized in that, The adjustable landing platform includes: a fixed platform, multiple attitude adjustment cylinders, and a landing platform. The multiple attitude adjustment cylinders are mounted on the fixed platform, and the landing platform is mounted on the multiple attitude adjustment cylinders.

4. The test platform for rocket landing leg return mode according to claim 1, characterized in that, The lifting device is a winch with lifting and hoisting function, a crane with lifting and hoisting function, a counterweight with lifting and hoisting function, or a lifting cylinder with lifting and hoisting function.

5. The test platform for rocket landing leg return mode according to claim 1, characterized in that, The top of the first-stage rocket body is equipped with a rocket body adapter block, and a slider adapted to the guide mechanism is installed on the rocket body adapter block. Multiple support legs are installed at the bottom of the first-stage rocket body.

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