Rudder wing unfolding testing device

Abstract

The invention relates to a rudder wing unfolding test device used for testing a rudder wing, the rudder wing comprises a rudder body and a wing plate, one side of the wing plate is hinged to the rudder body through a pin shaft, the other side of the wing plate extends outwards, and the rudder wing unfolding test device is used for testing whether the wing plate can smoothly overturn relative to the rudder body or not. The rudder wing unfolding testing device comprises a base station, a first support, a second support, a torsion source and a rotating shaft, one end of the first support and one end of the second support are fixedly connected with the base station, a first groove is formed in the other end of the first support, the rotating shaft is installed at the other end of the first support through a rolling bearing, and a second groove is formed in one end of the rotating shaft. The other end of the rotating shaft is provided with a clamping groove, and the two ends of the torsion source are sleeved with the first groove and the second groove respectively. By adopting the technical scheme provided by the invention, the torsion bar is adopted as a power source to load the pin shaft of the rudder wing, the duration of output torsion of the torsion bar is short, the output torsion is mild, and the rudder wing can be prevented from being damaged.

Description

Technical Field

[0001] The present invention belongs to the technical field of rudder wings, and in particular relates to a rudder wing deployment test device. Background Art

[0002] To ensure smooth flight after exiting the canister, missiles with tube-type missiles must maintain a precise, deployed rudder configuration. If the rudders fail to deploy promptly after launch, or if their deployment configuration fails to meet design requirements, the missile can easily flip and fall after exiting the canister, resulting in a launch failure. Therefore, after the rudders are fabricated, they are typically tested to ensure smooth deployment.

[0003] For example, patent document CN215725482U discloses a rudder wing folding and unfolding mechanism. The mechanism comprises a first hinge assembly and a second hinge assembly, each capable of rotating along its own axis. The first hinge assembly is connected to the fixed and folding ends of the rudder wing, respectively, and the second hinge assembly is connected to the fixed and folding ends of the rudder wing, respectively. After folding, the fixed and folding ends of the rudder wing are unfolded and coplanar by the first hinge assembly. The first and second hinge assemblies have coaxial rotation axes for folding or unfolding. This patented technology ensures that the fixed and folding ends of the rudder wing are coplanar after unfolding, eliminating manual assembly and adjustment, ensuring deployment accuracy, and effectively improving work efficiency. However, in existing rudder wing deployment test devices, a power source such as a motor is generally used to load the pin shaft of the rudder wing. Since the motor output power lasts for a long time, the flipping movement stroke of the wing plate relative to the rudder body is likely to exceed the limit, causing damage to the rudder wing. If other power sources are used to load the rudder wing pin shaft, the rudder wing pin shaft is unevenly stressed due to uneven loading, which can easily cause the pin shaft to break along its length. Summary of the Invention

[0004] In order to solve the above technical problems, the present invention provides a rudder wing deployment test device.

[0005] The present invention provides a rudder wing deployment test device, which is used to test the rudder wing. The rudder wing includes a rudder body and a wing plate, one side of the wing plate is hinged to the rudder body by a pin shaft, and the other side of the wing plate extends outward. The rudder wing deployment test device is used to test whether the wing plate can smoothly flip relative to the rudder body. The rudder wing deployment test device includes a base, a first support, a second support, a torque source and a rotating shaft. One end of the first support and one end of the second support are both fixedly connected to the base, and the other end of the first support is provided with a first groove. The rotating shaft is installed on the other end of the first support using a rolling bearing, one end of the rotating shaft is provided with a second groove, and the other end of the rotating shaft is provided with a card slot, and the two ends of the torque source are respectively fitted into the first groove and the second groove.

[0006] The torque source may be replaced by a torsion bar.

[0007] The first groove is a hexagonal blind groove.

[0008] The second groove is a hexagonal blind groove.

[0009] The clamping slot is a cylindrical blind slot.

[0010] The rudder wing deployment test device also includes a third support and a clamping mechanism, the clamping mechanism includes a support rod, a pressure plate, a pad and a locking nut, the surface of the pressure plate is provided with a limiting hole, one end of the third support and one end of the support rod are fixedly connected to the base, the other end of the third support is provided with a V-shaped supporting groove, the other end of the support rod is threadedly connected to the locking nut, and the support rod also passes through the limiting hole, the pad is clamped between one end of the pressure plate and the base, and the rudder body is clamped between the other end of the pressure plate and the V-shaped supporting groove.

[0011] A V-shaped pressing groove is further provided on the surface of the pressing plate, and the V-shaped pressing groove and the V-shaped supporting groove are opposite to each other along the vertical direction.

[0012] The limiting hole is a waist-shaped through hole.

[0013] There are multiple pressing mechanisms, and the multiple pressing devices are arranged at equal intervals along the length direction of the rudder body.

[0014] The rudder wing deployment test device also includes a fourth support and a stop pin. One end of the fourth support is fixedly connected to the base, and the other end of the fourth support is provided with a positioning hole. The stop pin is fitted into the positioning hole, and the end of the stop pin rests on the surface of the wing plate.

[0015] The beneficial effects of the present invention are as follows: by adopting the technical solution provided by the present invention, a torsion bar is used as a power source to load the pin shaft of the rudder wing. On the one hand, since the torsion energy that can be stored in the torsion bar is very limited, the duration of the torsion bar output torque is relatively short, so that the flipping movement stroke of the wing plate relative to the rudder body will not exceed a predetermined limit, thereby avoiding damage to the rudder wing. On the other hand, the torsion bar output torque is relatively mild, and the impact force on the pin shaft of the rudder wing is relatively small. In addition, the torsion bar output torque is relatively uniform, so that the load loaded on the pin shaft of the rudder wing is uniform, thereby avoiding the pin shaft from breaking. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a front view of the present invention;

[0017] Figure 2 is a top view of the present invention;

[0018] Figure 3 It is a right side view of the present invention.

[0019] In the figure: 1-rudder wing, 2-rudder body, 3-wing plate, 4-pin shaft, 5-base, 6-first support, 7-second support, 8-torque source, 9-rotating shaft, 10-third support, 11-clamping mechanism, 12-support rod, 13-pressure plate, 14-pad, 15-locking nut, 16-limiting hole, 17-V-shaped support groove, 18-V-shaped pressure groove, 19-fourth support, 20-stop pin, 21-positioning hole. DETAILED DESCRIPTION

[0020] The technical solution of the present invention is further described below with reference to the accompanying drawings, but the scope of protection claimed is not limited to the above;

[0021] The present invention provides a rudder wing deployment test device, such as Figures 1 to 3 As shown, the rudder wing deployment test device is used to test the rudder wing 1. The rudder wing 1 includes a rudder body 2 and a wing plate 3. One side of the wing plate 3 is hinged to the rudder body 2 using a pin shaft 4, and the other side of the wing plate 3 extends outward. The rudder wing deployment test device is used to test whether the wing plate 3 can smoothly flip relative to the rudder body 2. The rudder wing deployment test device includes a base 5, a first support 6, a second support 7, a torque source 8 and a rotating shaft 9. One end of the first support 6 and one end of the second support 7 are both fixedly connected to the base 5. The other end of the first support 6 is provided with a first groove. The rotating shaft 9 is installed on the other end of the first support 6 using a rolling bearing. One end of the rotating shaft 9 is provided with a second groove. The other end of the rotating shaft 9 is provided with a card slot. The two ends of the torque source 8 are respectively fitted into the first groove and the second groove.

[0022] By adopting the technical solution provided by the present invention, a torsion bar is used as a power source to load the pin shaft of the rudder wing. On the one hand, since the torsion energy that can be stored in the torsion bar is very limited, the duration of the torsion bar output torque is relatively short, so that the flipping movement stroke of the wing plate relative to the rudder body will not exceed a predetermined limit, thereby avoiding damage to the rudder wing. On the other hand, the torsion bar output torque is relatively mild, and the impact force on the pin shaft of the rudder wing is relatively small. In addition, the torsion bar output torque is relatively uniform, so that the load loaded on the pin shaft of the rudder wing is uniform, thereby avoiding the pin shaft from breaking.

[0023] Specifically, the torque source 8 can be replaced by a torsion bar. The first groove is a hexagonal blind groove. The second groove is a hexagonal blind groove. The clamping groove is a cylindrical blind groove.

[0024] In addition, the rudder wing deployment test device also includes a third support 10 and a clamping mechanism 11. The clamping mechanism 11 includes a support rod 12, a pressure plate 13, a pad 14 and a locking nut 15. The surface of the pressure plate 13 is provided with a limiting hole 16. One end of the third support 10 and one end of the support rod 12 are fixedly connected to the base 5. The other end of the third support 10 is provided with a V-shaped support groove 17. The other end of the support rod 12 is screwed to the locking nut 15. The support rod 12 also passes through the limiting hole 16. The pad 14 is clamped between one end of the pressure plate 13 and the base 5, and the rudder body 2 is clamped between the other end of the pressure plate 13 and the V-shaped support groove 17.

[0025] In addition, the surface of the pressure plate 13 is also provided with a V-shaped pressure groove 18, and the V-shaped pressure groove 18 and the V-shaped support groove 17 are opposite to each other in the vertical direction. The limiting hole 16 is a waist-shaped through hole. There are multiple clamping mechanisms 11, and the multiple clamping mechanisms 11 are arranged at equal intervals along the length direction of the rudder body 2. The rudder wing deployment test device also includes a fourth support 19 and a stop pin 20. One end of the fourth support 19 is fixedly connected to the base 5, and the other end of the fourth support 19 is provided with a positioning hole 21. The stop pin 20 is fitted into the positioning hole 21, and the end of the stop pin 20 is against the surface of the wing plate 3.

Claims

1. A rudder wing deployment test device, characterized by: The rudder wing deployment test device is used to test a rudder wing (1). The rudder wing (1) includes a rudder body (2) and a wing plate (3). One side of the wing plate (3) is hinged to the rudder body (2) using a pin shaft (4), and the other side of the wing plate (3) extends outward. The rudder wing deployment test device is used to test whether the wing plate (3) can smoothly flip relative to the rudder body (2). The rudder wing deployment test device includes a base (5), a first support (6), a second support (7), a torque source (8) and a rotating shaft (9). One end of the first support (6) and one end of the second support (7) are both fixedly connected to the base (5). The other end of the first support (6) is provided with a first groove. The rotating shaft (9) is installed on the other end of the second support (7) using a rolling bearing. One end of the rotating shaft (9) is provided with a second groove. The other end of the rotating shaft (9) is provided with a card slot. The two ends of the torque source (8) are respectively fitted into the first groove and the second groove.

2. The rudder wing deployment test device according to claim 1, characterized in that: The torque source (8) can be replaced by a torsion bar.

3. The rudder wing deployment test device according to claim 1, characterized in that: The first groove is a hexagonal blind groove.

4. The rudder wing deployment test device according to claim 1, characterized in that: The second groove is a hexagonal blind groove.

5. The rudder wing deployment test device according to claim 1, characterized in that: The clamping slot is a cylindrical blind slot.

6. The rudder wing deployment test device according to claim 1, characterized in that: The rudder wing deployment test device also includes a third support (10) and a clamping mechanism (11). The clamping mechanism (11) includes a support rod (12), a pressure plate (13), a cushion block (14) and a locking nut (15). The surface of the pressure plate (13) is provided with a limiting hole (16). One end of the third support (10) and one end of the support rod (12) are both fixedly connected to the base (5). The other end of the third support (10) is provided with a V-shaped supporting groove (17). The other end of the support rod (12) is screwed to the locking nut (15). The support rod (12) also passes through the limiting hole (16). The cushion block (14) is clamped between one end of the pressure plate (13) and the base (5), and the rudder body (2) is clamped between the other end of the pressure plate (13) and the V-shaped supporting groove (17).

7. The rudder wing deployment test device according to claim 6, characterized in that: The surface of the pressing plate (13) is further provided with a V-shaped pressing groove (18), and the V-shaped pressing groove (18) and the V-shaped supporting groove (17) are opposite to each other along the vertical direction.

8. The rudder wing deployment test device according to claim 6, characterized in that: The limiting hole (16) is a waist-shaped through hole.

9. The rudder wing deployment test device according to claim 5, characterized in that: There are multiple pressing mechanisms (11), and the multiple pressing devices are arranged at equal intervals along the length direction of the rudder body (2).

10. The rudder wing deployment test device according to claim 1, characterized in that: The rudder wing deployment test device further includes a fourth support (19) and a stop pin (20), one end of the fourth support (19) is fixedly connected to the base (5), the other end of the fourth support (19) is provided with a positioning hole (21), the stop pin (20) is fitted into the positioning hole (21), and the end of the stop pin (20) abuts against the surface of the wing plate (3).

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