Static test device and test method for landing device

Abstract

The invention relates to the technical field of aerospace, in particular to a landing device static test device and test method, and aims to solve the problem that various parameters of a carrier rocket landing device cannot be obtained in the prior art. The landing device static test device comprises a driving mechanism, a landing device, a base, a supporting plate and a supporting frame, the power end of the driving mechanism is fixedly connected with the base, the output end of the driving mechanism is connected with one end of the landing device, and the driving mechanism is used for applying a static load to the landing device to simulate an impact load when a rocket lands. The other end of the landing device is rotationally connected with the supporting plate, the landing device is used for bearing impact loads generated when the rocket lands, and the supporting plate is fixed to the supporting frame. The landing device static test device and test method provided by the invention are used for static tests of carrier rocket landing devices.

Description

Technical Field

[0001] The present disclosure relates to the field of aerospace technology, and in particular to a landing device static test device and a test method. Background Art

[0002] The landing device is used to absorb the initial kinetic energy of the launch vehicle during the vertical landing process, reduce the impact load during the landing process, and achieve a soft landing of the recovered rocket. The carrying capacity is the core of the landing device, and the landing device needs to be subjected to ground static verification tests.

[0003] Existing landing test devices are usually used to simulate the dynamic characteristics of a horizontal landing vehicle landing and impacting the ground. They can test whether the overload, strength and stiffness of the landing device meet the technical index requirements. However, the overload, strength and stiffness of the landing device obtained by the above-mentioned landing test device cannot be used as various parameters of the launch vehicle landing device.

[0004] Therefore, how to solve the problem that various parameters of the launch vehicle landing device cannot be obtained in the prior art is one of the important issues that need to be urgently solved in this field. Summary of the invention

[0005] In view of this, the embodiments of the present disclosure provide a landing device static test device and test method to solve the problem in the prior art that various parameters of the launch vehicle landing device cannot be obtained.

[0006] According to one aspect of the present disclosure, a landing device static test device is provided, including: a driving mechanism, a landing device, a base, a support plate and a support frame, the power end of the driving mechanism is fixedly connected to the base, the output end of the driving mechanism is connected to one end of the landing device, the driving mechanism is used to apply a static load to the landing device to simulate the impact load during the landing of the rocket, the other end of the landing device is rotatably connected to the support plate, the landing device is used to bear the impact load during the landing of the rocket, and the support plate is fixed on the support frame.

[0007] In addition, according to the landing device static test device of one aspect of the present disclosure, the landing device static test device further includes a first connecting member and a second connecting member, and the output end of the driving mechanism is rotationally connected to the landing device through the first connecting member; The second connecting member is fixedly connected to the support plate, and the landing device is rotatably connected to the support plate via the second connecting member.

[0008] According to the landing device static test device of one aspect of the present disclosure, the first connecting member and the second connecting member are both made of alloy material.

[0009] According to a landing device static test device according to one aspect of the present disclosure, the landing device static test device also includes a plurality of reinforcing ribs, one end of each reinforcing rib is fixedly connected to the support frame, and the other end of each reinforcing rib is fixedly connected to the support plate.

[0010] According to a landing device static test device according to one aspect of the present disclosure, the landing device includes a main leg and an auxiliary leg, one end of the main leg and one end of the auxiliary leg are connected to the output end of the driving mechanism, and the other end of the main leg and the other end of the auxiliary leg are fixedly connected to the support plate.

[0011] According to a landing device static test device according to one aspect of the present disclosure, a groove for placing the landing device is formed inside the auxiliary leg.

[0012] According to a landing device static test device according to one aspect of the present disclosure, the main legs and the auxiliary legs are distributed at an acute angle along a direction close to the support plate.

[0013] According to the landing device static test device of one aspect of the present disclosure, the main support leg is at least one of a pneumatic telescopic rod, a hydraulic telescopic rod and an electric telescopic rod.

[0014] According to another aspect of the present disclosure, a test method of a landing device static test device is provided, which is applied to the above-mentioned landing device static test device. The test method of the landing device static test device includes: Complete the assembly of the landing gear static test device according to the assembly process of the landing gear static test device; When the landing gear static test device is assembled, apply static load to the landing gear static test device to detect the accuracy of the test data obtained by the landing gear static test device; When the test of the landing gear static test device is completed, the static load of the landing gear static test device is unloaded step by step and the static load of the landing gear static test device is returned to zero; According to the requirements of the test task, static loads are applied to the landing gear static test device step by step to obtain various parameters of the landing gear static test device; After obtaining various parameters of the landing gear static test device, the static load of the landing gear static test device is unloaded step by step and the static load of the landing gear static test device is returned to zero.

[0015] According to a testing method of a landing gear static test device according to one aspect of the present disclosure, when the landing gear static test device is assembled, applying a static load to the landing gear static test device to detect the accuracy of test data obtained by the landing gear static test device also includes: Apply a static load to the landing device, and control the driving mechanism to apply the static load to the landing device step by step, wherein the static load is 30% of the preset static load; When the static load applied by the landing gear reaches 30% of the preset static load, start testing various parameters of the landing gear static test device; When each parameter of the landing gear static test device matches the preset parameter, the landing gear static test device is unloaded step by step and the load of the landing gear static test device is returned to zero.

[0016] At least one of the above-mentioned technical solutions adopted in the embodiments of the present disclosure can achieve the following beneficial effects: in the above-mentioned landing device static test device, the power end of the driving mechanism is fixedly connected to the base, the output end of the driving mechanism is connected to one end of the landing device, and the other end of the landing device is rotatably connected to the support plate, and the support plate is fixed on the support frame. On this basis, the driving mechanism applies a static load to the landing device to simulate the impact load during the landing of the rocket. After the driving mechanism completes the application of the static load to the landing device, by detecting the changes in the landing device, since the landing device is used to bear the impact load during the landing of the rocket, various parameters of the landing device during the landing of the carrier rocket are obtained by detecting the landing device, which effectively solves the problem that various parameters of the landing device of the carrier rocket cannot be obtained in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0018] Figure 1 FIG. 1 is a schematic diagram of the overall assembly structure of a static test device for a landing device according to an embodiment of the present disclosure; Figure 2 is a schematic structural diagram illustrating a landing device according to an embodiment of the present disclosure; Figure 3 is a schematic structural diagram illustrating a driving mechanism according to an embodiment of the present disclosure; Figure 4 is a flow chart further illustrating a test method of a static test device for a landing device according to an embodiment of the present disclosure; Figure 5 The flowchart further illustrates a static test device for detecting a landing device according to an embodiment of the present disclosure.

[0019] Reference numerals: 1-driving mechanism, 2-landing device, 21-main supporting leg, 22-auxiliary supporting leg, 221-groove, 23-first connecting piece, 24-second connecting piece, 3-support plate, 4-support frame, 5-base, 6-reinforcement rib. DETAILED DESCRIPTION

[0020] Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as being limited to the embodiments described herein, which are instead provided for a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are only for exemplary purposes and are not intended to limit the scope of protection of the present disclosure.

[0021] It should be understood that the various steps described in the method embodiments of the present disclosure may be performed in different orders and / or in parallel. In addition, the method embodiments may include additional steps and / or omit the steps shown. The scope of the present disclosure is not limited in this respect.

[0022] The term "including" and its variations used in this document are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments". Relevant definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc. mentioned in this disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0023] It should be noted that the modifications of "one" and "plurality" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, it should be understood as "one or more".

[0024] The names of the messages or information exchanged between multiple devices in the embodiments of the present disclosure are only used for illustrative purposes and are not used to limit the scope of these messages or information.

[0025] The landing device is used to absorb the initial kinetic energy of the launch vehicle during the vertical landing process, reduce the impact load during the landing process, and achieve a soft landing of the recovered rocket. The carrying capacity is the core of the landing device, and the landing device needs to be subjected to ground static verification tests.

[0026] Existing landing test devices are usually used to simulate the dynamic characteristics of a horizontal landing vehicle landing and impacting the ground. They can test whether the overload, strength and stiffness of the landing device meet the technical index requirements. However, the overload, strength and stiffness of the landing device obtained by the above-mentioned landing test device cannot be used as various parameters of the launch vehicle landing device.

[0027] In view of the above problems, an exemplary embodiment of the present disclosure provides a landing device static test device and a test method to solve the problem that various parameters of a launch vehicle landing device cannot be obtained in the prior art.

[0028] A landing device static test device according to an embodiment of the present disclosure will be described in detail below with reference to the accompanying drawings.

[0029] Figure 1 The figure shows a schematic diagram of the overall assembly structure of the static test device of the landing device 2 according to the embodiment of the present disclosure. Figure 1 As shown, a static test device for a landing device 2 includes: a driving mechanism 1, a landing device 2, a base 5, a support plate 3 and a support frame 4, the power end of the driving mechanism 1 is fixedly connected to the base 5, the output end of the driving mechanism 1 is connected to one end of the landing device 2, the driving mechanism 1 is used to apply a static load to the landing device 2 to simulate the impact load during the landing of the rocket, the other end of the landing device 2 is rotatably connected to the support plate 3, the landing device 2 is used to bear the impact load during the landing of the rocket, and the support plate 3 is fixed on the support frame 4.

[0030] In practical applications, such as Figure 1 As shown, the power end of the driving mechanism 1 is fixedly connected to the base 5, the output end of the driving mechanism 1 is connected to one end of the landing device 2, the other end of the landing device 2 is rotatably connected to the support plate 3, and the support plate 3 is fixed on the support frame 4. On this basis, the driving mechanism 1 applies a static load to the landing device 2 to simulate the impact load during the landing of the rocket. After the driving mechanism 1 applies the static load to the landing device 2, the change of the landing device 2 is detected. Since the landing device 2 is used to bear the impact load during the landing of the rocket, various parameters of the landing device 2 during the landing of the carrier rocket are obtained by detecting the landing device 2, which effectively solves the problem that various parameters of the landing device 2 of the carrier rocket cannot be obtained in the prior art.

[0031] For example, Figure 1As shown, the static test device of the landing device 2 also includes a first connecting member 23 and a second connecting member 24. The output end of the driving mechanism 1 is rotatably connected to the landing device 2 through the first connecting member 23. The second connecting member 24 is fixedly connected to the support plate 3, and the landing device 2 is rotatably connected to the support plate 3 through the second connecting member 24. It can be understood that the above-mentioned first connecting member 23 and the second connecting member 24 can be connecting members such as pins. On this basis, the first connecting member 23 and the second connecting member 24 are both made of alloy material. Due to the high strength, good toughness and plasticity of the alloy material, it is not easy to break or crush when subjected to external force, and can be deformed through processing to meet different shape and structural requirements.

[0032] For example, Figure 1 As shown, the static test device of the landing device 2 also includes a plurality of reinforcing ribs 6, one end of each reinforcing rib 6 is fixedly connected to the support frame 4, and the other end of each reinforcing rib 6 is fixedly connected to the support plate 3. When the driving mechanism 1 applies a static load to the landing device 2, in order to prevent the support plate 3 from deforming under the action of pressure, a plurality of reinforcing ribs 6 are added between the support plate 3 and the support frame 4, thereby effectively preventing the support plate 3 from deforming under the action of the static load.

[0033] Figure 2 2 is a schematic diagram illustrating the structure of a landing device 2 according to an embodiment of the present disclosure. Figure 2 As shown, the landing device 2 includes a main leg 21 and an auxiliary leg 22, one end of the main leg 21 and one end of the auxiliary leg 22 are connected to the output end of the driving mechanism, and the other end of the main leg 21 and the other end of the auxiliary leg 22 are fixedly connected to the support plate.

[0034] like Figure 2 As shown, the auxiliary leg 22 has a groove 221 for placing the landing device 2. When the rocket body is flying in the air, the auxiliary leg 22 can store the landing device 2 in the groove 221. It should be understood that the outer surface of the groove 221 is an arc-shaped structure, which effectively reduces the air resistance of the rocket body during flight. At the same time, when the rocket body lands, the landing device 2 is opened to reduce the speed of the rocket body during the landing process, thereby reducing the impact load of the rocket body and avoiding damage to the main body of the rocket body. On this basis, along the direction close to the support plate, the main leg 21 and the auxiliary leg 22 are distributed at an acute angle. When opening the landing device 2, no excessive space is required, and the operation can be completed in a smaller space. At the same time, a reasonable opening and closing angle can also make it easier for the main leg 21 to be stored in the auxiliary leg 22.

[0035] For example, Figure 2As shown, the main legs 21 are at least one of a pneumatic telescopic rod 21, a hydraulic telescopic rod 21, and an electric telescopic rod 21. It can be understood that when the landing device 2 is attached to the arrow body, the arrow body is in a working state. When the landing device 2 is deployed on the arrow body, the arrow body is in a non-working state. At this time, the main legs 21 are deployed in a direction away from the arrow body. Taking the hydraulic main legs 21 as an example, when the main legs 21 are deployed in a direction away from the main part of the arrow body, the hydraulic main legs 21 are deployed step by step until the main legs 21 are fully deployed and distributed at an acute angle between the auxiliary legs 22, and finally the arrow body is supported and the arrow body is recovered.

[0036] Figure 3 1 is a schematic diagram showing the structure of the driving mechanism 1 according to an embodiment of the present disclosure. Figure 3 As shown, the driving mechanism 1 acts as a power mechanism to apply a static load to the landing device. It should be understood that the driving mechanism 1 takes a hydraulic actuator as an example, one end of the hydraulic actuator is fixedly connected to the base 5, and the other end of the hydraulic actuator is connected to the landing device, wherein the hydraulic actuator and the upper joint of the actuator are fixed by their own threaded connection, the lower joint of the hydraulic actuator is fixed by its own threaded connection, the upper joint of the actuator and the landing device are hinged by a pin, the lower joint of the actuator and the base 5 are hinged by a pin, and the base 5 is fixed to the ground by anchor bolts. It should be understood that the above-mentioned support frame and the base 5 are fixed on the same plane by connecting parts such as anchor bolts or screws.

[0037] The present disclosure also provides a testing method for a landing device static testing device. Figure 4 is a flow chart further illustrating a test method of a static test device for a landing device according to an embodiment of the present disclosure, such as Figure 4 As shown, the test method of the above-mentioned landing gear static test device is applied to the above-mentioned landing gear static test device, and the test method of the landing gear static test device includes: S401: completing the assembly of the landing gear static test device according to the assembly process of the landing gear static test device; S402: When the landing gear static test device is assembled, a static load is applied to the landing gear static test device to detect the accuracy of the test data obtained by the landing gear static test device; S403: when the test of the landing gear static test device is completed, the static load of the landing gear static test device is unloaded step by step and the static load of the landing gear static test device is returned to zero; S404: According to the requirements of the test task, static loads are applied to the landing gear static test device step by step to obtain various parameters of the landing gear static test device; S405: After obtaining various parameters of the landing gear static test device, unload the static load of the landing gear static test device step by step and return the static load of the landing gear static test device to zero.

[0038] Compared with the prior art, the beneficial effects of the test method of the landing device static test device provided by the embodiment of the present disclosure are the same as the beneficial effects of the landing device static test device provided by the above-mentioned embodiment, which will not be elaborated here.

[0039] Figure 5 is a flow chart further illustrating a static test device for detecting a landing device according to an embodiment of the present disclosure, such as Figure 5 As shown, when the landing gear static test device is assembled, applying a static load to the landing gear static test device to detect the accuracy of the test data obtained by the landing gear static test device also includes: S501: Apply a static load to the landing device, and control the driving mechanism to apply the static load to the landing device step by step, wherein the static load is 30% of the preset static load. It should be understood that the above-mentioned control driving mechanism loads and records each parameter of the landing device step by step according to 10% of the preset load until it is loaded to 30% of the preset load.

[0040] S502: When the static load applied by the landing gear reaches 30% of the preset static load, start detecting various parameters of the landing gear static test device.

[0041] S503: When each parameter of the landing gear static test device matches the preset parameter, the landing gear static test device is unloaded step by step and the load of the landing gear static test device is returned to zero. It should be understood that the above-mentioned step-by-step unloading is carried out step by step at 10% of the preset load and each parameter of the landing gear is recorded until the load of the landing gear static test device is returned to zero.

[0042] The above descriptions are only some embodiments of the present disclosure and an explanation of the technical principles used. Those skilled in the art should understand that the scope of disclosure involved in the present disclosure is not limited to the technical solutions formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above disclosed concept. For example, the above features are replaced with the technical features with similar functions disclosed in the present disclosure (but not limited to) by each other to form a technical solution.

[0043] Although some specific embodiments of the present disclosure have been described in detail by way of example, it should be understood by those skilled in the art that the above examples are for illustration only and are not intended to limit the scope of the present disclosure. It should be understood by those skilled in the art that the above embodiments may be modified without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.

Claims

1. A landing equipment static test device, characterized in that: include: A driving mechanism, a landing device, a base, a support plate and a support frame, wherein the power end of the driving mechanism is fixedly connected to the base, the output end of the driving mechanism is connected to one end of the landing device, the driving mechanism applies a static load to the landing device to simulate the impact load during rocket landing, the other end of the landing device is rotatably connected to the support plate, the landing device is used to bear the impact load during rocket landing, and the support plate is fixed to the support frame.

2. The landing gear static test device according to claim 1, characterized in that: The landing device static test device further comprises a first connecting member and a second connecting member, and the output end of the driving mechanism is rotationally connected to the landing device through the first connecting member; The second connecting member is fixedly connected to the support plate, and the landing device is rotatably connected to the support plate via the second connecting member.

3. The landing gear static test device according to claim 2, characterized in that: The first connecting member and the second connecting member are both made of alloy material.

4. The landing gear static test device according to claim 1, characterized in that: The landing device static test device also includes a plurality of reinforcing ribs, one end of each of the reinforcing ribs is fixedly connected to the support frame, and the other end of each of the reinforcing ribs is fixedly connected to the support plate.

5. The landing gear static test device according to claim 1, characterized in that: The landing device includes a main leg and an auxiliary leg, one end of the main leg and one end of the auxiliary leg are both connected to the output end of the driving mechanism, and the other end of the main leg and the other end of the auxiliary leg are both fixedly connected to the support plate.

6. The landing gear static test device according to claim 5, characterized in that: A groove for placing the landing device is provided inside the auxiliary leg.

7. The landing gear static test device according to claim 5, characterized in that: Along the direction approaching the support plate, the main legs and the auxiliary legs are distributed at an acute angle.

8. The landing gear static test device according to claim 5, characterized in that: The main supporting leg is at least one of a pneumatic telescopic rod, a hydraulic telescopic rod and an electric telescopic rod.

9. A test method for a landing device static test device, applied to the landing device static test device according to any one of claims 1 to 8, characterized in that: The test method of the landing gear static test device includes: Complete the assembly of the landing gear static test device according to the assembly process of the landing gear static test device; When the landing gear static test device is assembled, apply static load to the landing gear static test device to detect the accuracy of the test data obtained by the landing gear static test device; When the test of the landing gear static test device is completed, the static load of the landing gear static test device is unloaded step by step and the static load of the landing gear static test device is returned to zero; According to the requirements of the test task, static loads are applied to the landing gear static test device step by step to obtain various parameters of the landing gear static test device; After obtaining various parameters of the landing gear static test device, the static load of the landing gear static test device is unloaded step by step and the static load of the landing gear static test device is returned to zero.

10. The test method of the landing gear static test device according to claim 9, characterized in that: When the landing gear static test device is assembled, applying static load to the landing gear static test device to detect the accuracy of the test data obtained by the landing gear static test device also includes: Apply a static load to the landing device, and control the driving mechanism to apply the static load to the landing device step by step, wherein the static load is 30% of the preset static load; When the static load applied by the landing gear reaches 30% of the preset static load, start testing various parameters of the landing gear static test device; When each parameter of the landing gear static test device matches the preset parameter, the landing gear static test device is unloaded step by step and the load of the landing gear static test device is returned to zero.

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