Missile rack posture test equipment and test method thereof

Abstract

This invention provides a missile pylon attitude testing device and method. The missile pylon attitude testing device includes a base, a rotating support, a structural support, an angle control mechanism, and a pylon assembly. The rotating support is located on top of the base, and the end of the structural support is rotatably mounted in the rotating support. The base raises the mounting structure to a certain height. The angle control mechanism drives the structural support and the mounting structure to rotate relative to the rotating support and locks them in place. The pylon assembly includes a transfer platform and a pylon. The transfer platform includes a first plate, a collar, and a second plate connected in sequence. The collar is fitted onto the structural support. One side of the pylon is connected to either the first or second plate, and the other side of the pylon houses the mounting structure. This invention can simulate missiles in different attitudes, meeting the attitude requirements for missile launch.

Description

Technical Field

[0001] This invention relates to the field of airborne equipment testing technology, and in particular to a missile pylon attitude testing device and its testing method. Background Technology

[0002] A missile pylon is a connection device used between a missile and a fighter jet, used to detach the missile during launch. Fighter jets are often in different attitudes, requiring the missile to launch normally under various attitudes. Therefore, during ground-based missile launch tests, the pylon must undergo ejection tests under multiple flight attitudes.

[0003] For example, the off-axis missile deflection pylon mechanism disclosed in patent publication number CN104964614B uses a fan-shaped track and hydraulic cylinders to drive the missile's rotation angle. However, the structure is relatively complex, requiring the relative positional changes of fixed and sliding guide plates. Furthermore, it necessitates two hydraulic cylinders vertically suspended from the top of the support frame. The positional changes of two points on the missile are controlled by adjusting the stroke of the two cylinders and a section of arc-shaped guide rail to achieve the final motion state. Moreover, the missile's installation position on the pylon is limited, preventing selective installation based on desired attitude requirements. Later adjustments to the position and angle are only possible through structural modifications. Summary of the Invention

[0004] The purpose of this invention is to provide a missile pylon attitude testing device and its testing method, which has a simple structure and higher flexibility.

[0005] The technical solution of the present invention is as follows: A missile pylon attitude test device includes a base, a rotating support, a structural support, an angle control mechanism, and a pylon assembly. The rotating support is located on the top of the base, and the end of the structural support is rotatably mounted in the rotating support. The pylon assembly is sleeved on the structural support, and the lower end of the pylon assembly forms an installation structure for connecting a missile. The base raises the installation structure to a certain height, and the angle control mechanism is used to drive the structural support and the installation structure to rotate relative to the rotating support and lock them in place.

[0006] The mounting bracket assembly includes a transfer platform and a mounting bracket. The transfer platform includes a first plate, a collar, and a second plate connected in sequence. The collar is sleeved on the structural support. One side of the mounting bracket is connected to the first plate or the second plate, and the other side of the mounting bracket is provided with the installation structure.

[0007] In the above scheme, on the one hand, the angle control mechanism drives the structural support to rotate, so that the mounting bracket for the simulated missile can rotate. Compared with the method of controlling the stroke of two hydraulic cylinders and the arc-shaped guide rail at one end, the structure is simpler and more intuitive, and the angle is more controllable. On the other hand, two mounting platforms are designed on the transfer platform used to connect the mounting bracket. In practice, the appropriate platform can be selected to connect to the mounting bracket according to the attitude requirements, so that the mounting bracket installation position can be selected in a wider range and with greater flexibility.

[0008] Preferably, the outer surface of the first plate is provided with n sliding grooves, and the outer surface of the second plate is provided with m sliding grooves, where n is an even number, m is an odd number, and n < m; the bracket is provided with a slider that matches the sliding grooves.

[0009] Preferably, both the first plate and the second plate are provided with a plurality of first mounting holes arranged along the slide groove. The first mounting holes are located on the side of the slide groove. The bracket is provided with second mounting holes that are adapted to the first mounting holes. The second mounting holes are aligned with some of the first mounting holes and then fixed by fasteners.

[0010] Preferably, the structural support is a stepped shaft, and the collar abuts against the shoulder of the stepped shaft.

[0011] Preferably, multiple collars are arranged between the first plate and the second plate.

[0012] Preferably, the base is a trapezoidal structure that is smaller at the top and larger at the bottom.

[0013] Preferably, the mounting structure is at least one hook disposed at the bottom of the pylon. The hook is L-shaped, with one side connected to the pylon and capable of displacement relative to the simulated missile launch direction, and the other side parallel to the bottom plane of the pylon.

[0014] Preferably, the bracket assembly is fixed to the structural support by fasteners.

[0015] The present invention also provides a test method for the above-mentioned missile pylon attitude test equipment, comprising the following steps: setting the attitude angle of the simulated missile before launch, and determining the platform connected to the pylon and confirming the final connection position of the pylon on the platform according to the attitude requirements of the simulated missile; then rotating the determined platform to below the structural support, and installing the pylon at the confirmed position on the platform; then installing the simulated missile on the mounting structure of the pylon; activating the angle control mechanism to drive the structural support, pylon assembly and simulated missile to rotate and reach the preset angle, then stopping the angle control mechanism and locking the pylon assembly; releasing the simulated missile to complete the test.

[0016] Compared with related technologies, the beneficial effects of the present invention are as follows:

[0017] I. This invention drives the structural support to rotate through an angle control mechanism, thereby rotating the mounting bracket for the simulated missile. Compared to controlling the stroke of two hydraulic cylinders and an arc-shaped guide rail at one end, the structure is simpler, more intuitive, and the angle is more controllable.

[0018] Second, the present invention designs two installation platforms on the adapter platform used to connect the hanger. In practice, the appropriate platform can be selected to connect to the hanger according to the posture requirements, so that the hanger installation position can be selected in a wider range and with greater flexibility.

[0019] Third, this invention can simulate missiles in different attitudes to meet the attitude requirements for missile launch. Attached Figure Description

[0020] Figure 1 A three-dimensional structural schematic diagram of the missile pylon attitude test equipment provided by the present invention;

[0021] Figure 2 A front view structural schematic diagram of the missile pylon attitude test equipment provided by the present invention;

[0022] Figure 3 for Figure 1 A schematic diagram showing the disassembled components of the mounting bracket and the simulated missile.

[0023] Figure 4 A schematic diagram of the connection structure for the transfer platform, hanger, and structural support.

[0024] In the attached diagram: 1. Base; 2. Rotation support; 3. Structural support; 4. Transfer platform; 41. First plate; 42. Collar; 43. Second plate; 44. Slide groove; 45. First mounting hole; 5. Hanger; 51. Slider; 52. Second mounting hole; 53. Hook; 6. Simulated missile; 7. Angle control mechanism; 8. Fastener; 9. Hanger assembly. Detailed Implementation

[0025] The present invention will now be described in detail with reference to the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other. For ease of description, the terms "upper," "lower," "left," and "right" used below only indicate that they correspond to the upper, lower, left, and right directions in the accompanying drawings and do not limit the structure.

[0026] like Figure 1 , Figure 2 As shown, the missile pylon attitude test equipment provided in this embodiment includes a base 1, a rotation support 2, a structural support 3, an angle control mechanism 7, and a pylon assembly 9.

[0027] Two bases 1 are spaced apart and are trapezoidal structures with a smaller top and a larger bottom. The upper plane of each base forms a mounting surface. A rotating support 2 is provided on each mounting surface, and the angle control mechanism 7 is provided on one of the mounting surfaces.

[0028] The angle control mechanism 7 consists of a motor and a gearbox. An input gear is mounted on the outer ring of the structural support 3 near the angle control mechanism 7, and the input gear meshes with the output gear of the gearbox. Simultaneously, the connection between the gearbox and the rotating support 2, as well as the structural sealing, must be considered. The two ends of the structural support 3 are rotatably mounted inside the two rotating supports 2 via bearings. The structural support 3 is a stepped shaft, and its shoulder is used to abut and limit the movement of the collar 42 of the hanger assembly 9.

[0029] like Figure 3 , Figure 4 As shown, the mounting bracket assembly 9 includes a transfer platform 4 and a mounting bracket 5. The transfer platform 4 includes a first plate 41, a collar 42, and a second plate 43 connected in sequence. The outer surface of the first plate 41 has n grooves 44, and the outer surface of the second plate 43 has m grooves 44, where n is an even number, m is an odd number, and n < m. In this embodiment, n = 2, m = 3. In addition, both the first plate 41 and the second plate 43 have multiple first mounting holes 45 arranged along the grooves 44. The first mounting holes 45 are located beside the grooves 44. The positions of the even-numbered grooves 44 and the odd-numbered grooves 44 are different, so that they can be selected as needed when actually installing the mounting bracket 5, so that the range of posture adjustment is wider and can better meet the requirements.

[0030] Multiple collars 42 are arranged between the first plate 41 and the second plate 43. The collars 42 are fitted onto the structural support 3, with one end face abutting against the shoulder of the stepped shaft, and the adapter platform 4 is fixed to the structural support 3 by fasteners 8.

[0031] The bracket 5 is provided with a slider 51 that is adapted to the slide groove 44. The slider 51 has second mounting holes 52 on both sides that are adapted to the first mounting holes 45. During installation, the slider 51 is slidably placed in a certain slide groove 44 at the corresponding position, and then the second mounting holes 52 are aligned with some of the first mounting holes 45 and fixed by fasteners 8.

[0032] like Figure 4 As shown, the bottom of the mounting bracket 5 is provided with a hook 53, which is an installation structure for mounting the simulated missile 6. The mounting bracket 5 is L-shaped, with one side connected to the mounting bracket 5 and capable of displacement relative to the launch direction of the simulated missile. This displacement is achieved by a drive component and a return spring within the mounting bracket 5. The other side of the mounting bracket 5 is parallel to the bottom plane of the mounting bracket 5 and is mounted in the mounting hole of the simulated missile 6.

[0033] In this embodiment, there are two hooks 53, and the L-shapes of the two hooks 53 are oriented in the same direction.

[0034] The present invention also provides a test method for the above-mentioned missile pylon attitude test equipment, comprising the following steps: setting the attitude angle of the simulated missile 6 before launch, and determining the platform connected to the pylon 5 and confirming the final connection position of the pylon 5 on the platform according to the attitude requirements of the simulated missile 6. Then, rotating the determined platform to below the structural support 3, and installing the pylon 5 at the confirmed position on the platform. Next, installing the simulated missile 6 on the mounting structure of the pylon 5; activating the angle control mechanism 7 to drive the structural support 3, the pylon assembly 9, and the simulated missile 6 to rotate until a preset angle is reached, then stopping the angle control mechanism 7 and locking the pylon assembly 9. Finally, releasing the simulated missile 6 to complete the test.

[0035] The launch equipment for the simulated missile 6 is based on existing technology and is integrated into the rack 5. Its specific structure and principle will not be described in detail here.

[0036] The above description is merely an embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural or procedural transformations made based on the content of the present invention specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of the present invention.

Claims

1. A missile pylon attitude testing device, characterized in that, The system includes a base (1), a rotating support (2), a structural support (3), an angle control mechanism (7), and a mounting bracket assembly (9). The rotating support (2) is located on the top of the base (1), and the end of the structural support (3) is rotatably mounted in the rotating support (2). The mounting bracket assembly (9) is sleeved on the structural support (3), and the lower end of the mounting bracket assembly (9) forms an installation structure for connecting missiles. The base (1) raises the installation structure to a certain height, and the angle control mechanism (7) is used to drive the structural support (3) and the installation structure to rotate relative to the rotating support (2) and lock them. The mounting bracket assembly (9) includes a transfer platform (4) and a mounting bracket (5). The transfer platform (4) includes a first plate (41), a collar (42), and a second plate (43) connected in sequence. The collar (42) is sleeved on the structural support (3). One side of the mounting bracket (5) is connected to either the first plate (41) or the second plate (43), and the other side of the mounting bracket (5) is provided with the mounting structure. The outer surface of the first plate (41) is provided with n grooves (44), and the outer surface of the second plate (43) is provided with m grooves (44), where n is an even number, m is an odd number, and n < m. The bracket (5) is provided with a slider (51) adapted to the slide groove (44); the angle control mechanism (7) is a motor and a gearbox; the structural support (3) is a stepped shaft, and the collar (42) abuts against the shoulder of the stepped shaft; multiple collars (42) are arranged between the first plate (41) and the second plate (43); the installation structure is at least one hook (53) set at the bottom of the bracket (5), the hook (53) is L-shaped, one side of which is connected to the bracket (5) and can be displaced relative to the simulated missile launch direction, and the other side is parallel to the bottom plane of the bracket (5).

2. The missile pylon attitude testing equipment according to claim 1, characterized in that, The first plate (41) and the second plate (43) are provided with a plurality of first mounting holes (45) arranged along the slide (44). The first mounting holes (45) are located on the side of the slide (44). The bracket (5) is provided with second mounting holes (52) that are adapted to the first mounting holes (45). The second mounting holes (52) are aligned with some of the first mounting holes (45) and then fixed by fasteners (8).

3. The missile pylon attitude testing equipment according to claim 1, characterized in that, The base (1) is a trapezoidal structure with a smaller top and a larger bottom.

4. The missile pylon attitude testing equipment according to claim 1, characterized in that, The hanger assembly (9) is fixed to the structural support (3) by fasteners (8).

5. A test method for a missile pylon attitude test apparatus as described in any one of claims 1-4, characterized in that, Includes the following steps: Set the attitude angle of the simulated missile (6) before launch, and determine the platform connected to the rack (5) and confirm the final connection position of the rack (5) on the platform according to the attitude requirements of the simulated missile (6); Then rotate the determined platform to the underside of the structural support (3), and install the rack (5) at the confirmed position on the platform; then install the simulated missile (6) on the mounting structure of the rack (5); Start the angle control mechanism (7), drive the structural support (3), the hanger assembly (9) and the simulated missile (6) to rotate and reach the preset angle, then stop the angle control mechanism (7) and lock the hanger assembly (9). Release the simulated missile (6) to complete the test.

Images