Landing leg unfolding and folding test tool and test method

Abstract

The invention relates to the technical field of aerospace, and particularly provides a landing leg unfolding and folding test tool and test method, and the test tool comprises an upper support frame and a lower support frame; the upper supporting frame is rotationally arranged on the lower supporting frame, and a tool wall plate is fixedly installed on the upper supporting frame. The upper supporting frame has two states: in the first state, the tool wall plate on the upper supporting frame is perpendicular to the horizontal plane; in the second state, the included angle between the tool wall plate on the upper supporting frame and the horizontal plane is an acute angle, and the upper fulcrum connecting bases, the thrust spring connecting bases and the lower fulcrum connecting bases are symmetrically installed on the opposite side faces of the tool wall plate; the upper fulcrum connecting base is arranged at the end, away from the lower supporting frame, of the tool wall plate, the lower fulcrum connecting base is arranged at the end, close to the lower supporting frame, of the tool wall plate, and the thrust spring connecting base is arranged between the upper fulcrum connecting base and the lower fulcrum connecting base and located at the position close to the upper fulcrum connecting base. The problem that an existing test device cannot carry out a carrier rocket landing leg ground unfolding and folding test is solved.

Description

Technical Field

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

[0002] The main function of a rocket's landing legs is to ensure a safe and smooth landing after the rocket completes its mission, supporting recovery and reuse, thereby reducing costs and improving mission efficiency. The landing legs are in a retracted state during the rocket's flight to ensure the rocket's good aerodynamic shape. When a certain flight altitude is reached during the recovery phase, the landing legs are reliably deployed to meet the requirements for rocket landing. In order to ensure that the landing legs can be reliably deployed at different attitude angles of the rocket, a ground deployment test of the landing legs is required to verify the rationality of the landing leg design. However, the existing test equipment is unable to carry out ground deployment tests of the launch vehicle's landing legs. Therefore, it is necessary to design a test fixture that can perform deployment tests of the landing legs. Summary of the Invention

[0003] The present disclosure is proposed in view of the above problems. The present disclosure provides a landing leg extension and retraction test tool and a test method.

[0004] According to one aspect of the present disclosure, there is provided a landing leg deployment and retraction test fixture, comprising an upper support frame and a lower support frame;

[0005] The upper support frame is rotatably arranged on the lower support frame, and a tooling wall panel is fixedly installed on the upper support frame; the upper support frame has two states: in the first state, the tooling wall panel on the upper support frame is perpendicular to the horizontal plane; in the second state, the tooling wall panel on the upper support frame is at an acute angle to the horizontal plane.

[0006] An upper fulcrum connecting seat, a thrust spring connecting seat and a lower fulcrum connecting seat are symmetrically installed on one opposite side of the tooling wall panel; the upper fulcrum connecting seat is arranged at an end of the tooling wall panel away from the lower support frame, and the lower fulcrum connecting seat is arranged at an end of the tooling wall panel close to the lower support frame, and the thrust spring connecting seat is arranged between the upper fulcrum connecting seat and the lower fulcrum connecting seat, and is located close to the upper fulcrum connecting seat.

[0007] In addition, according to a landing leg deployment and retraction test fixture according to one aspect of the present disclosure, when the upper support frame is in the first state, the upper support frame and the lower support frame are fixed by a quick lock.

[0008] In addition, a landing leg deployment and retraction test tooling according to one aspect of the present disclosure further includes a support rod and an inclined bracket; when the upper support frame is in the second state, the quick lock is in the open state, and the two sides of the upper support frame are fixedly connected to the lower support frame through the support rod and the inclined bracket respectively.

[0009] In addition, according to a landing leg deployment and retraction test tooling according to one aspect of the present disclosure, there are two upper support frames, and the two upper support frames are respectively located at opposite edges of the same side of the tooling wall panel.

[0010] In addition, according to a landing leg extension and retraction test tooling according to one aspect of the present disclosure, the upper support frame includes a first connecting rod and a second connecting rod, one end of the first connecting rod is vertically fixed to the tooling wall panel, and the other end is fixedly connected to one end of the second connecting rod, and the other end of the second connecting rod is fixedly connected to the tooling wall panel; when the upper support frame is in a first state, the first connecting rod and the lower support frame are fixed by the quick lock; when the upper support frame is in a second state, the inclined bracket is located between the first connecting rod and the lower support frame, and the inclined bracket is fixedly connected to the first connecting rod and the lower support frame respectively, one end of the support rod is fixedly connected to the tooling wall panel, and the other end is fixedly connected to the lower support frame.

[0011] In addition, according to a landing leg extension and retraction test tooling according to one aspect of the present disclosure, a thrust spring pad is further provided on the tooling wall panel, and the thrust spring pad is located between the thrust spring connecting seat and the lower support point connecting seat.

[0012] In addition, according to a landing leg extension and retraction test tooling according to one aspect of the present disclosure, there are two lower support point connection seats located on the same side of the tooling wall panel, and the two lower support point connection seats are respectively located at opposite edges close to the tooling wall panel.

[0013] In addition, according to a landing leg deployment and retraction test tooling according to one aspect of the present disclosure, a pulling support is provided at one end of the tooling wall panel away from the lower support frame, and an unlocking mechanism for locking and fixing the auxiliary leg is provided on the pulling support.

[0014] In addition, according to a landing leg deployment and retraction test fixture according to one aspect of the present disclosure, the lower support frame is fixedly connected to the ground.

[0015] According to another aspect of the present disclosure, a test method is provided for the landing leg extension and retraction test fixture described above, comprising the following steps:

[0016] S1. Hinging one end of the main leg of the landing leg to the upper support point connecting seat via a pin, hinging the other end to one end of the auxiliary leg via a pin, and hinging the other end of the auxiliary leg to the lower support point connecting seat via a pin;

[0017] S2. Hinge one end of the thrust spring to the thrust spring connecting seat through a pin;

[0018] S3. Rotate the auxiliary leg upward around the hinged connection with the lower support seat so that the auxiliary leg is parallel to the tooling wall panel and locked. At this time, the thrust spring is in a compressed state, and the other end of the thrust spring presses against the ball-and-socket structure of the auxiliary leg, and the main leg is in a retracted state.

[0019] S4, adjusting the upper support frame to be in the first state or the second state;

[0020] S5. Unlocking the auxiliary support legs to determine whether the design of the landing support legs is reasonable.

[0021] The present invention deploys the landing legs by rotatably mounting an upper support frame on a lower support frame, installing a tooling panel on the upper support frame, providing a connection seat for fixing the main and auxiliary landing legs, and installing a thrust spring on the tooling panel to drive the landing legs to deploy. By adjusting the angle between the tooling panel on the upper support frame and the horizontal plane, the deployment of the landing legs at different rocket attitude angles is simulated, thereby verifying the rationality of the landing leg design. This solves the problem that existing test equipment cannot conduct ground deployment and retraction tests of launch vehicle landing legs. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The above and other purposes, features, and advantages of the present disclosure will become more apparent through a more detailed description of the embodiments of the present disclosure in conjunction with the accompanying drawings. The accompanying drawings are intended to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and are not intended to limit the present disclosure. In the drawings, the same reference numerals generally represent the same components or steps.

[0023] Figure 1 is a front view of the landing leg deployment and retraction test fixture disclosed in the present disclosure in a first state;

[0024] Figure 2 yes Figure 1 Left view of;

[0025] Figure 3 is a front view of the landing leg deployment and retraction test fixture disclosed in the present disclosure when it is in the second state;

[0026] Figure 4 yes Figure 3 Left view of;

[0027] Figure 5 This is a state diagram of the upper support frame in the first state with the landing legs retracted;

[0028] Figure 6 is a state diagram of the upper support frame in the first state with the landing legs deployed;

[0029] Figure 7 This is a diagram showing the upper support frame in the second state, with the landing legs mounted on the side of the tooling panel away from the upper support frame for deployment testing;

[0030] Figure 8 This is a diagram showing the upper support frame in the second state, with the landing legs installed on the side of the tooling panel close to the upper support frame for deployment testing;

[0031] Figure 9 is a flow chart of the steps of the test method disclosed in the present disclosure.

[0032] Description of reference numerals:

[0033] 1-upper support frame, 2-lower support frame, 3-quick lock, 4-anchor bolt, 5-pin, 6-tooling wall plate, 7-upper fulcrum connection seat, 8-lower fulcrum connection seat, 9-thrust spring connection seat, 10-traction support, 11-thrust spring pad, 12-tilt bracket, 13-support rod, 14-main support leg, 15-auxiliary support leg, 16-thrust spring;

[0034] 101 is a first connecting rod, 102 is a second connecting rod. DETAILED DESCRIPTION

[0035] In order to make the purpose, technical solutions and advantages of the present disclosure more apparent, the following will describe in detail exemplary embodiments of the present disclosure with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure, and it should be understood that the present disclosure is not limited to the exemplary embodiments described herein.

[0036] See Figures 1-4 As shown, the present disclosure discloses a landing leg deployment and retraction test fixture, including an upper support frame 1, a lower support frame 2, a quick lock 3, a support rod 13 and an inclined bracket 12; the lower support frame 2 is fixed to the ground by anchor bolts 4.

[0037] The upper support frame 1 is rotatably mounted on the lower support frame 2. Specifically, the upper support frame 1 and the lower support frame 2 are rotatably connected via a pin 5, i.e., the upper support frame 1 can rotate around the pin 5. A tooling wall plate 6 is fixedly mounted on the upper support frame 1 by welding; the upper support frame 1 has two states: in the first state, the tooling wall plate 6 on the upper support frame 1 is vertical to the horizontal plane, and the upper support frame 1 and the lower support frame 2 are fixed via a quick lock 3. Figure 1As shown, the tooling panel 6 here simulates the body of the rocket, and the tooling panel 6 is perpendicular to the horizontal plane to simulate the body of the rocket being perpendicular to the horizontal plane; in the second state, the tooling panel 6 on the upper support frame 1 is at an acute angle to the included angle, and the tooling panel 6 here simulates the body of the rocket, and the included angle between the tooling panel 6 and the horizontal plane simulates the included angle between the body of the rocket and the horizontal plane, the quick lock 3 is in the open state, and the two sides of the upper support frame 1 are fixedly connected to the lower support frame 2 by the support rod 13 and the tilt bracket 12 respectively, see Figure 3 Specifically, one end of the support rod 13 is connected to the upper support frame 1 by bolts, and the other end is connected to the lower support frame 2 by bolts, and the tilt bracket 12 is connected to the upper support frame 1 and the lower support frame 2 by bolts.

[0038] An upper fulcrum connection seat 7, a thrust spring connection seat 9 and a lower fulcrum connection seat 8 are symmetrically installed on one opposite side of the tooling wall panel 6. Specifically, the upper fulcrum connection seat 7, the thrust spring connection seat 9 and the lower fulcrum connection seat 8 are all fixed to the tooling wall panel 6 by bolts; the upper fulcrum connection seat 7 is arranged at the end of the tooling wall panel 6 away from the lower support frame 2, and the lower fulcrum connection seat 8 is arranged at the end of the tooling wall panel 6 close to the lower support frame 2. There are two lower fulcrum connection seats 8 located on the same side of the tooling wall panel 6, and the two lower fulcrum connection seats 8 are respectively located at an opposite edge close to the tooling wall panel 6. The thrust spring connection seat 9 is arranged between the upper fulcrum connection seat 7 and the lower fulcrum connection seat 8, and is located close to the upper fulcrum connection seat 7. In specific use, the upper fulcrum connection seat 7 is used to hinge with one end of the main leg 14 of the landing leg, the lower fulcrum connection seat 8 is used to hinge with the auxiliary leg 15 of the landing leg, and the end of the main leg 14 away from the upper fulcrum connection seat 7 is hinged with the end of the auxiliary leg 15 away from the lower fulcrum connection seat 8. The thrust spring connection seat 9 is used to hinge with one end of the thrust spring 16.

[0039] By symmetrically arranging the upper support connection seat 7, the thrust spring connection seat 9 and the lower support connection seat 8 on both sides of the tooling wall panel 6, the deployment of the landing legs at different attitude angles of the rocket can be simulated.

[0040] As an implementation method, there are two upper support frames 1, and the two upper support frames 1 are respectively located at opposite edges on the same side of the tooling wall panel 6. This arrangement avoids the upper support frames 1 from interfering with the test. Two parallel upper support frames 1 are provided to support the tooling wall panel 6, making the support more stable. The upper support frame 1 includes a first connecting rod 101 and a second connecting rod 102. One end of the first connecting rod 101 is fixedly installed vertically with the tooling wall panel 6, and the other end is fixedly connected to one end of the second connecting rod 102. The other end of the second connecting rod 102 is fixedly connected to the tooling wall panel 6. When the upper support frame 1 is in the first state, the first connecting rod 101 and the lower support frame 2 are fixed by a quick lock 3. When the upper support frame 1 is in the second state, the tilting bracket 12 is located between the first connecting rod 101 and the lower support frame 2, and the tilting bracket 12 is fixedly connected to the first connecting rod 101 and the lower support frame 2 by bolts. One end of the support rod 13 is fixedly connected to the tooling wall panel 6 by bolts, and the other end is fixedly connected to the lower support frame 2 by bolts. In order to improve the stability of the upper support frame 1, there are multiple second connecting rods 102, and the multiple second connecting rods 102 are arranged in parallel. When it is necessary to simulate the deployment of the landing legs when the arrow of the rocket is vertically upward, the landing legs are installed on the side of the tooling wall 6 away from the upper support frame 1, and the upper support frame 1 is in the first state, and the deployment test is carried out. Figure 5-Figure 6 shown.

[0041] When it is necessary to simulate the deployment of the landing legs when the arrow of the rocket is tilted upward, the landing legs are installed on the side of the tooling wall plate 6 away from the upper support frame 1, and the upper support frame 1 is in the second state, and the deployment test is carried out. Figure 7 When it is necessary to simulate the deployment of the landing legs when the arrow of the rocket is tilted downward, the landing legs are installed on the side of the tooling wall plate 6 close to the upper support frame 1, and the upper support frame 1 is in the second state, and the deployment test is carried out, as shown in FIG. Figure 8 shown.

[0042] A thrust spring washer 11 is also bolted to the tooling wall plate 6 and is located between the thrust spring connection seat 9 and the lower support point connection seat 8. The thrust spring washer 11 can support the thrust spring 16 and also cushion the thrust spring 16 when it separates from the auxiliary support leg 15 and falls at the beginning of the experiment.

[0043] Furthermore, a pulling support 10 is provided at one end of the tooling wall panel 6 away from the lower support frame 2, and an unlocking mechanism for locking and fixing the auxiliary support leg 15 is provided on the pulling support 10. Specifically, the unlocking mechanism is fixedly connected to the pulling support 10 by bolts. The unlocking mechanism is an existing technology, such as mechanical unlocking, pneumatic unlocking, fire attack unlocking, etc.

[0044] The present disclosure discloses a test method for the above landing leg extension and retraction test tool, including the following steps: Figure 9 As shown:

[0045] S1. Hinge one end of the main leg 14 of the landing leg to the upper support connecting seat 7 via a pin, and hinge the other end to one end of the auxiliary leg 15 via a pin. Hinge the other end of the auxiliary leg 15 to the lower support connecting seat 8 via a pin.

[0046] S2. One end of the thrust spring 16 is hinged to the thrust spring connecting seat 9 through a pin;

[0047] S3. Rotate the auxiliary leg 15 upward around the hinge with the lower support seat 8 so that the auxiliary leg 15 is parallel to the tooling wall panel 6 and locked. Specifically, the upward rotation of the auxiliary leg 15 around the hinge with the lower support seat 8 can realize the retraction of the landing leg by a hydraulic actuator. When the auxiliary leg 15 is parallel to the tooling wall panel 6, it can be locked by pulling the unlocking mechanism on the support 10. At this time, the thrust spring 16 is in a compressed state, and the other end of the thrust spring 16 presses against the ball and socket structure of the auxiliary leg 15, and the main leg 14 is in a retracted state.

[0048] S4, adjusting the upper support frame 1 to the first state or the second state;

[0049] S5. Unlock the auxiliary leg 15 and start the test. At this time, the thrust spring 16 is expanded under the action of high pressure gas. The auxiliary leg 15 rotates around the hinge between the auxiliary leg 15 and the lower support point connection seat 8 under the push of the thrust spring 16. Each level of the main leg 14 extends along its own axis. Observe the extension of the main leg 14. If each level of the main leg 14 extends along its own axis and reaches its locked position as shown in the figure, Figure 6-Figure 8 If the following equation is shown, the design is reasonable.

[0050] If each level of the main support leg 14 extends along its own axis but cannot extend to its locked position, it is judged that the design is unreasonable.

[0051] During specific implementation, step S4 may be performed first and then steps S1, S2, S3, and S5.

[0052] The basic principles of the present disclosure have been described above in conjunction with specific embodiments. However, it should be noted that the advantages, strengths, and effects mentioned in this disclosure are merely illustrative and not restrictive, and should not be construed as necessarily possessed by each embodiment of the present disclosure. Furthermore, the specific details disclosed above are provided for illustrative purposes and to facilitate understanding, rather than as limitations. These details do not limit the present disclosure to necessarily being implemented using these specific details.

[0053] The block diagrams of the devices, devices, equipment, and systems involved in this disclosure are merely illustrative examples and are not intended to require or imply that they must be connected, arranged, or configured in the manner shown in the block diagrams. As will be appreciated by those skilled in the art, these devices, devices, equipment, and systems can be connected, arranged, or configured in any manner. Words such as "include," "comprise," "have," and the like are open-ended words, meaning "including but not limited to," and can be used interchangeably therewith. The words "or" and "and" used herein refer to the words "and / or" and can be used interchangeably therewith, unless the context clearly indicates otherwise. The word "such as" used herein refers to the phrase "such as but not limited to," and can be used interchangeably therewith.

[0054] Additionally, as used herein, "or" used in a list of items beginning with "at least one" indicates a separate list, so that, for example, a list of "at least one of A, B, or C" means A or B or C, or AB or AC or BC, or ABC (i.e., A and B and C). Furthermore, the word "exemplary" does not mean that the example described is preferred or better than other examples.

[0055] It should also be noted that in the system and method of the present disclosure, each component or each step can be decomposed and / or recombined. Such decomposition and / or recombination should be regarded as equivalent solutions of the present disclosure.

[0056] Various changes, substitutions, and modifications may be made to the technology described herein without departing from the teachings defined by the appended claims. Moreover, the scope of the claims of this disclosure is not limited to the specific aspects of the processes, machines, manufactures, compositions of things, means, methods, and actions described above. Currently existing or later developed processes, machines, manufactures, compositions of things, means, methods, or actions that perform substantially the same function or achieve substantially the same results as the corresponding aspects described herein may be utilized. Accordingly, the appended claims include within their scope such processes, machines, manufactures, compositions of things, means, methods, or actions.

[0057] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present disclosure. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other aspects without departing from the scope of the present disclosure. Therefore, the present disclosure is not intended to be limited to the aspects shown herein, but rather to be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0058] The above description has been provided for the purpose of illustration and description. In addition, this description is not intended to limit the embodiments of the present disclosure to the forms disclosed herein. Although a number of example aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations thereof.

Claims

1. A landing leg extension and retraction test tool, characterized in that: It comprises an upper support frame (1) and a lower support frame (2); The upper support frame (1) is rotatably mounted on the lower support frame (2), and a tooling wall plate (6) is fixedly mounted on the upper support frame (1); the upper support frame (1) has two states: in a first state, the tooling wall plate (6) on the upper support frame (1) is perpendicular to a horizontal plane; in a second state, the tooling wall plate (6) on the upper support frame (1) forms an acute angle with the horizontal plane; An upper fulcrum connection seat (7), a thrust spring connection seat (9) and a lower fulcrum connection seat (8) are symmetrically installed on one opposite side of the tooling wall panel (6); the upper fulcrum connection seat (7) is arranged at one end of the tooling wall panel (6) away from the lower support frame (2), the lower fulcrum connection seat (8) is arranged at one end of the tooling wall panel (6) close to the lower support frame (2), and the thrust spring connection seat (9) is arranged between the upper fulcrum connection seat (7) and the lower fulcrum connection seat (8), and is located close to the upper fulcrum connection seat (7).

2. The landing leg extension and retraction test fixture according to claim 1, characterized in that: When the upper support frame (1) is in the first state, the upper support frame (1) and the lower support frame (2) are fixed via a quick lock (3).

3. The landing leg extension and retraction test fixture according to claim 2, characterized in that: It also includes a support rod (13) and an inclined bracket (12); when the upper support frame (1) is in the second state, the quick lock (3) is in the open state, and both sides of the upper support frame (1) are fixedly connected to the lower support frame (2) through the support rod (13) and the inclined bracket (12).

4. The landing leg extension and retraction test fixture according to claim 3, characterized in that: There are two upper support frames (1), and the two upper support frames (1) are respectively located at opposite edges of the same side of the tooling wall panel (6).

5. The landing leg extension and retraction test fixture according to claim 4, characterized in that: The upper support frame (1) includes a first connecting rod (101) and a second connecting rod (102), one end of the first connecting rod (101) is fixedly installed vertically to the tooling wall panel (6), and the other end is fixedly connected to one end of the second connecting rod (102), and the other end of the second connecting rod (102) is fixedly connected to the tooling wall panel (6); when the upper support frame (1) is in a first state, the first connecting rod (101) and the lower support frame (2) are fixed by the quick lock (3); when the upper support frame (1) is in a second state, the inclined bracket (12) is located between the first connecting rod (101) and the lower support frame (2), and the inclined bracket (12) is fixedly connected to the first connecting rod (101) and the lower support frame (2) respectively, and one end of the support rod (13) is fixedly connected to the tooling wall panel (6), and the other end is fixedly connected to the lower support frame (2).

6. The landing leg extension and retraction test fixture according to claim 1, characterized in that: A thrust spring pad (11) is also provided on the tooling wall plate (6), and the thrust spring pad (11) is located between the thrust spring connecting seat (9) and the lower support point connecting seat (8).

7. The landing leg extension and retraction test fixture according to claim 1, characterized in that: There are two lower support point connection seats (8) located on the same surface of the tooling wall panel (6), and the two lower support point connection seats (8) are respectively located at opposite edges close to the tooling wall panel (6).

8. The landing leg extension and retraction test fixture according to claim 1, characterized in that: A pulling support (10) is provided at one end of the tooling wall plate (6) away from the lower support frame (2), and an unlocking mechanism for locking and fixing the auxiliary support leg (15) is provided on the pulling support (10).

9. The landing leg extension and retraction test fixture according to claim 1, characterized in that: The lower support frame (2) is fixedly connected to the ground.

10. A test method, characterized in that: The landing leg extension and retraction test tool used in any one of claims 1 to 9 comprises the following steps: S1. One end of the main leg (14) of the landing leg is hinged to the upper support point connection seat (7) through a pin, and the other end is hinged to one end of the auxiliary leg (15) through a pin, and the other end of the auxiliary leg (15) is hinged to the lower support point connection seat (8) through a pin; S2. One end of the thrust spring (16) is hinged to the thrust spring connecting seat (9) via a pin; S3. Rotate the auxiliary leg (15) upward around the hinge with the lower support point connection seat (8), so that the auxiliary leg (15) is parallel to the tooling wall plate (6) and locked. At this time, the thrust spring (16) is in a compressed state, and the other end of the thrust spring (16) is pressed against the ball-socket structure of the auxiliary leg (15), and the main leg (14) is in a retracted state; S4, adjusting the upper support frame (1) to be in the first state or the second state; S5. Unlocking the auxiliary support leg (15) to determine whether the design of the landing support leg is reasonable.

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