A hinge with locking function for aircraft nose radome

Abstract

The present application belongs to the field of aviation radome, and relates to a hinge with locking function for aircraft nose radome. When the size of aircraft nose radome is small, the space is narrow and insufficient to arrange a support rod, so the opening mode of the above aircraft nose radome is difficult to meet the requirements. The present application provides a hinge with locking function for aircraft nose radome, which comprises a rotating shaft and a rotating body. The rotating shaft is fixed on the aircraft body, the rotating body has a transverse circular hole and a longitudinal groove in communication with the circular hole at the end, the circular hole is sleeved on the rotating shaft, and the rotating shaft has a plurality of insertion slots on the circumference. A lever is rotatably installed in the longitudinal groove. One side of the lever is connected with a compression spring in the longitudinal groove, and the other side of the lever provides a pressing force to the lower protrusion of the end of the lever to press into the insertion slot. A fixing ring is rotatably installed in the longitudinal groove. The support rod mechanism is omitted, the structural design of the aircraft nose radome with small size is facilitated, and the structural weight is reduced.

Description

Technical Field

[0001] This invention belongs to the field of aviation radomes and relates to a hinge with locking function for an aircraft nose radome. Background Technology

[0002] The current main way to open the aircraft nose radome is that after the aircraft nose radome is opened around the hinge, it is supported by a strut and then fixed after opening to a certain angle, so as to facilitate the maintenance of the electronic equipment in the radar compartment.

[0003] When the size of the aircraft nose radome is small, the space is too small to accommodate the support rods, so the opening method of the aircraft nose radome mentioned above cannot meet the requirements. Summary of the Invention

[0004] To address the problem that small aircraft nose radomes are difficult to install support struts due to limited space, this invention proposes a hinge with locking function for aircraft nose radomes.

[0005] This invention provides a hinge with a locking function for an aircraft nose radome, comprising a pivot and a rotating body. The pivot is fixed to the fuselage, and the rotating body has a transverse circular hole and a longitudinal groove communicating with the circular hole at its end. The circular hole fits onto the pivot, and the pivot has several slots on its circumference. A lever is rotatably mounted in the longitudinal groove, and one side of the lever is connected to a compression spring in the longitudinal groove, providing a pressing force to the lower protrusion at the other end of the lever to press into the slot. A retaining ring is rotatably mounted in the longitudinal groove. When locking is not required, the upper latch at the end of the lever engages with the retaining ring, and the lower protrusion disengages from the slot.

[0006] Advantageously or alternatively, the shaft has a circumferential groove in the middle region along its length, which is evenly divided into several slots by rectangular blocks.

[0007] Advantageously or alternatively, the lever has a pin hole in the middle, which is mounted in a longitudinal groove by a first pin.

[0008] Advantageously or alternatively, the lever has an upper latch at the end away from the pivot and a lower protrusion at the end near the pivot.

[0009] Advantageously or alternatively, the lever has an arcuate arm near the pivot, with a lower protrusion at the end of the arcuate arm.

[0010] Advantageously or alternatively, the curvature of the arc arm matches the pivot.

[0011] Advantageously or alternatively, the lower protrusion has a rectangular cross-section.

[0012] Advantageously or alternatively, the retaining ring is located below the upper bayonet.

[0013] Advantageously or alternatively, a pair of stop pins are also installed in the longitudinal groove, distributed on both sides of the retaining ring, to prevent the retaining ring from falling into the bottom of the longitudinal groove when it is disengaged from the lever.

[0014] Advantageously or alternatively, the retaining ring is mounted in the longitudinal groove by a second pin, or by a coaxial structure at the opening.

[0015] Once the aircraft's nose radome is opened to a certain angle, it can be locked, thus allowing the radome to be fixed without the need for a strut after it has been opened to a certain angle. The locking mechanism can also unlock the rotating body, allowing the aircraft's nose radome to close normally.

[0016] Beneficial effects: It eliminates the strut mechanism, which facilitates the structural design of smaller aircraft nose radomes and reduces structural weight.

[0017] The features, functionalities, and advantages already discussed can be implemented independently in various examples, or combined in other examples. Further details of the examples can be seen in the following description and accompanying figures. Attached Figure Description

[0018] When read in conjunction with the accompanying drawings, the embodiments, preferred modes of use, other objects, and descriptions thereof will be best understood by referring to the following detailed description of embodiments of the invention, wherein: Figure 1 This is a schematic diagram of the hinge with locking function according to the present invention; Figure 2 This is a schematic diagram of the rotating shaft structure; Figure 3 This is a schematic diagram of the lever structure.

[0019] 1-Shaft, 2-Slot, 3-Rotating body, 4-Lever, 5-First pin, 6-Compression spring, 7-Fixing ring, 8-Stop pin, 9-Horizontal round hole, 10-Vertical groove, 11-Second pin, 12-Pin hole, 13-Upper bayonet, 14-Arc arm, 15-Lower protrusion Detailed Implementation The disclosed examples will be described more fully with reference to the accompanying drawings, in which some (but not all) of the disclosed examples are shown. In fact, many different examples may be described, and these examples should not be construed as limited to those set forth herein. Rather, these examples are described so that this disclosure will be thorough and complete, and will fully convey the scope of this disclosure to those skilled in the art.

[0020] See Figure 1The schematic diagram of the hinge structure shown illustrates that the rotating body 3 has a transverse circular hole 9 and a longitudinal groove 10 communicating with the transverse circular hole 9 on its end structure. The transverse circular hole 9 is fitted with a rotating shaft 1, and the rotating shaft 1 has several spaced slots 2 machined on its circumference. A first pin 5 is transversely installed in the longitudinal groove 10, and a lever 4 is rotatably mounted on the first pin 5. The lever 4 is connected to one end of a compression spring 6 on the side away from the rotating shaft 1, and the other end of the compression spring 6 is connected to the longitudinal groove 10. The compression spring 6 provides pressure to one side of the lever 4, thereby pressing the lower protrusion 15 at the other end of the lever 4 into the slot 2, at which point the rotating body 3 is locked and will not rotate. When the lever 4 on the side of the compression spring 6 is pressed, the lower protrusion 15 of the lever 4 disengages from the slot 2, at which point the rotating body 3 can rotate around the rotating shaft 1.

[0021] A second pin 11 is also installed in the longitudinal groove 10 of the rotating body 3, and the fixing ring 7 is rotatably mounted on the second pin 11. In another embodiment, the lower end of the fixing ring 7 is open, and it is directly installed in the holes on both sides of the longitudinal groove 10 through a coaxial structure at the opening, thereby having a rotation function. To prevent the rotating body 3 from getting stuck when rotating freely, the end of the lever 4 away from the rotating shaft 1 needs to be locked in the fixing ring 7. Stop pins 8 are also provided on both longitudinal sides of the fixing ring 7 to prevent the fixing ring 7 from falling into the bottom of the longitudinal groove 10 of the rotating body 3 when it is disengaged from the lever 4.

[0022] Figure 2 In the middle, the rotating shaft 1 is a cylinder with a groove in the middle. The groove is divided into several slots 2 by evenly arranged rectangular blocks.

[0023] Figure 3 In the middle, the lever 4 has a pin hole 12 in the middle, an upper latch 13 at one end of the lever 4, and an arc-shaped arm 14 at the other end of the lever 4, with a lower protrusion 15 at the end of the arc-shaped arm 14.

[0024] Descriptions of various advantageous arrangements have been shown for illustrative and descriptive purposes, but such descriptions are not intended to be exclusive or limited to the disclosed forms. Many modifications and variations will be apparent to those skilled in the art. Furthermore, different advantageous examples may be described as having different advantages compared to other advantageous examples. One or more examples have been selected and described in order to best illustrate the principles and practical applications of the examples, and to enable those skilled in the art to understand that this disclosure contains various examples with various modifications suitable for the particular intended use.

Claims

1. A hinge with a locking function for an aircraft nose radome, characterized in that: Includes a rotating shaft (1) and a rotating body (3). The rotating shaft (1) is fixed to the machine body. The rotating body (3) has a transverse circular hole (9) at its end and a longitudinal groove (10) communicating with the circular hole (9). The circular hole (9) is fitted onto the rotating shaft (1). The rotating shaft (1) has a circumferential groove in the middle region along its length, and several slots (2) are evenly divided by rectangular blocks. A lever (4) is rotatably installed in the longitudinal groove (10). One side of the lever (4) is connected to a compression spring (6) in the longitudinal groove (10), and the lever (4) is connected to a lower protrusion (1) at the other end of the lever (4). 5) Provides a clamping force to press into the slot (2), the lever (4) has an upper latch (13) at the end away from the pivot (1), the lever (4) has an arc arm (14) at the part near the pivot (1), the end of the arc arm (14) has the lower protrusion (15), the arc of the arc arm (14) matches the pivot (1); a retaining ring (7) is rotatably installed in the longitudinal groove (10), when locking is not required, the upper latch (13) at the end of the lever (4) is engaged in the retaining ring (7), and the lower protrusion (15) is disengaged from the slot (2).

2. The hinge with locking function for an aircraft nose radome according to claim 1, characterized in that: The lever (4) has a pin hole (12) in the middle and is installed in the longitudinal groove (10) by a first pin (5).

3. The hinge with locking function for an aircraft nose radome according to claim 1, characterized in that: The cross-section of the lower protrusion (15) is rectangular.

4. The hinge with locking function for an aircraft nose radome according to claim 1, characterized in that: The fixing ring (7) is located below the upper bayonet (13).

5. The hinge with locking function for an aircraft nose radome according to claim 1, characterized in that: A pair of stop pins (8) are also installed in the longitudinal groove (10), distributed on both sides of the fixing ring (7) to prevent the fixing ring (7) from falling into the bottom of the longitudinal groove (10) when it is separated from the lever (4).

6. The hinge with locking function for an aircraft nose radome according to claim 1, characterized in that: The fixing ring (7) is installed in the longitudinal groove (10) by the second pin (11) or by the coaxial structure at the opening.

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