CN110329538B

CN110329538B - Loading device for aircraft nose radome

Info

Publication number: CN110329538B
Application number: CN201910561845.0A
Authority: CN
Inventors: 任鹏; 何月洲; 杨鹏飞; 王毅; 严冲
Original assignee: AVIC Aircraft Strength Research Institute
Current assignee: AVIC Aircraft Strength Research Institute
Priority date: 2019-06-26
Filing date: 2019-06-26
Publication date: 2022-05-06
Anticipated expiration: 2039-06-26
Also published as: CN110329538A

Abstract

The application belongs to aircraft nose radome loading design technical field, concretely relates to loading device of aircraft nose radome, it has the appearance chamber, it is used for holding aircraft nose radome to hold the chamber, the appearance looks adaptation of its inner wall and aircraft nose radome 1, apply to aircraft nose radome through this additional device and press to the load, because the inner wall that holds the chamber and the appearance looks adaptation of aircraft nose radome, its inner wall can laminate mutually with the outside surface of aircraft nose radome, thereby can be with applying press to load uniform transmission to aircraft nose radome outside surface, with this can simulate the even condition of loading of aircraft nose radome.

Description

Loading device for aircraft nose radome

Technical Field

The application belongs to the technical field of loading design of aircraft nose radars, and particularly relates to a loading device of an aircraft nose radar cover.

Background

In a full-size aircraft structure static strength test, in order to verify the strength of a connection structure of an aircraft nose radar cover and an aircraft body, the stress condition of the aircraft nose radar cover needs to be simulated. At present, loading is mainly carried out through an adhesive tape-loading lever system and a tension and compression pad-loading lever system in a static strength test, but an aircraft nose radar cover is positioned at the front end of an aircraft nose and mainly bears the pressing load in the contrary course, the cambered surface appearance of the aircraft nose radar cover is an irregular structure and has no stress point, and the loading system in the form can not truly simulate the uniform loading condition of the aircraft nose radar cover.

The present application is made in view of the above-mentioned drawbacks of the prior art.

Disclosure of Invention

It is an object of the present application to provide a loading arrangement for an aircraft nose radome which overcomes or mitigates at least one of the disadvantages of the prior art.

The technical scheme of the application is as follows:

a loading device of an aircraft nose radome is provided with a containing cavity, wherein the containing cavity is used for containing the aircraft nose radome, and the inner wall of the containing cavity is matched with the appearance of the aircraft nose radome.

According to at least one embodiment of the present application, a plurality of panels is included, each panel having a front end, a rear end opposite the front end, a first side extending between the front and rear ends, and a second side opposite the first side; the first side edge of any one of the panels is joined to the second side edge of the other panel to define a cavity.

According to at least one embodiment of the present application, a plurality of clips are included and engage the outer sides of the panels.

According to at least one embodiment of this application, still include a plurality of lugs, every lug corresponds and sets up on a yoke.

According to at least one embodiment of the application, a first through hole is defined between the rear ends of the splicing plates, and the first through hole is communicated with the cavity for the tip end of the aircraft nose radome to penetrate through.

According to at least one embodiment of the application, the loading plate is connected with the rear end of each jointed plate on one side, and a second through hole is formed in the loading plate and communicated with the first through hole.

According to at least one embodiment of the present application, the load joint is provided on a side of the load plate facing away from the respective panels.

According to at least one embodiment of the present application, a load plate is attached to the rear end of each panel by screws.

According to at least one embodiment of the present application, each tile is a wood board.

In accordance with at least one embodiment of the present application, a first side edge of any panel overlaps or is joggled with a second side edge of another panel.

Drawings

FIG. 1 is a schematic structural diagram of an aircraft nose radar cover provided by an embodiment of the application;

FIG. 2 is a schematic structural diagram of a loading device of an aircraft nose radar cover provided by an embodiment of the application;

FIG. 3 is a schematic diagram of the operation of a loading device of an aircraft nose radar cover provided by an embodiment of the application;

wherein:

1-aircraft nose radar hood; 2-splicing plate; 3, clamping a hoop; 4-lifting lugs; 5-a loading plate; 6-loading the joint.

Detailed Description

The present application will be described in further detail with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.

The present application is described in further detail below with reference to fig. 1 to 3.

A loading device of an aircraft nose radome comprises a containing cavity, wherein the containing cavity is used for containing the aircraft nose radome 1, and the inner wall of the containing cavity is matched with the appearance of the aircraft nose radome 1.

To the loading device of aircraft nose radome disclosed to above-mentioned embodiment, technical personnel in the art can understand that aircraft nose radome 1 can arrange in and hold the chamber, exert to aircraft nose radome and press to load through this additional device, because the inner wall that holds the chamber and the appearance looks adaptation of aircraft nose radome 1, its inner wall can laminate mutually with aircraft nose radome 1's external surface, thereby can press the load that applys to 1 external surface of aircraft nose radome, with this condition that can simulate aircraft nose radome and evenly bear the load.

In some alternative embodiments, a plurality of panels 2 are included, each panel 2 having a front end, a rear end opposite the front end, a first side extending between the front and rear ends, and a second side opposite the first side; the first side edge of any jointed board 2 is jointed with the second side edge of another jointed board 2, thereby enclosing a cavity.

For the loading device of the aircraft nose radome disclosed in the above embodiment, those skilled in the art can understand that the design of the loading device is that the cavity is defined by the plurality of jointed boards 2, the inner side surface of the cavity is easily modified, finally the inner wall of the cavity can be matched with the appearance of the aircraft nose radome 1, and the jointed boards 2 are convenient to assemble and assemble.

In some alternative embodiments, a plurality of clips 3 are included to clip onto the outside of each panel 2.

With respect to the loading device for aircraft nose radomes disclosed in the above embodiments, it will be understood by those skilled in the art that a plurality of clips 3 are designed to be caught at the outer sides of the respective panels 2, so as to enhance the fastening of the joint between the respective panels 2 of the loading device, and to prevent the respective panels 2 from being separated from each other during the application of a compressive load.

In some optional embodiments, the clamping device further comprises a plurality of lifting lugs 4, and each lifting lug 4 is correspondingly arranged on one clamping hoop 3.

For the loading device of the aircraft nose radome disclosed in the above embodiment, as can be understood by those skilled in the art, the lifting lug 4 is arranged on the hoop 3, so that the loading device can be counterweighted by the lifting lug 4, no additional load is generated by the loading device, and the loading precision is ensured.

In some alternative embodiments, the rear ends of the panels 2 enclose a first through hole therebetween, and the first through hole is communicated with the cavity for the tip end of the aircraft nose radome 1 to pass through.

In some alternative embodiments, a loading plate 5 is further included, one side of which is connected to the rear end of each panel 2, and which has a second through hole therein, the second through hole being in communication with the first through hole.

With regard to the loading device for the aircraft nose radome disclosed in the above embodiments, it will be understood by those skilled in the art that the loading plate 5 is provided at the rear end of each panel 2, and the actuating device applies a compressive load to the loading plate 5, and the compressive load is transmitted to each panel 2 through the loading plate 5, thereby increasing the uniformity of the transmission of the compressive load.

In some alternative embodiments, a loading tab 6 is provided on the side of loading plate 5 facing away from each panel 2, which loading tab may be configured as a double lug structure to facilitate connection to an actuating device.

In alternative embodiments, load plate 5 is attached to the rear end of each panel 2 by screws.

In some alternative embodiments, each panel 2 is a wooden board.

As for the loading device of the aircraft nose radome disclosed in the above embodiment, it can be understood by those skilled in the art that each jointed board 2 is made of wood, on one hand, the loading device has light weight, on the other hand, the shape of the inner side surface of the loading device is easy to modify, and the wood jointed board 2 has elasticity to a certain extent, when bearing a compressive load, the inner side surface of the loading device generates a small deformation, so that the loading device can be better attached to the outer surface of the aircraft nose radome, and thus, the compressive load can be uniformly transmitted to the outer surface of the aircraft nose radome.

In alternative embodiments, a first side edge of any panel 2 overlaps or is joggled with a second side edge of another panel 2.

So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.

Claims

1. A loading device of a radome of an aircraft nose is characterized in that,

the aircraft nose radar cover comprises a cavity, wherein the cavity is used for accommodating an aircraft nose radar cover (1), and the inner wall of the cavity is matched with the appearance of the aircraft nose radar cover (1);

the combined jig-saw puzzle comprises a plurality of puzzle pieces (2), wherein each puzzle piece (2) is provided with a front end, a rear end opposite to the front end, a first side edge extending between the front end and the rear end, and a second side edge opposite to the first side edge; the first side edge of any one of the jointed boards (2) is jointed with the second side edge of the other jointed board (2) so as to enclose the cavity; each jointed board (2) is a wood board; a first through hole is defined between the rear ends of the jointed boards (2), and the first through hole is communicated with the cavity so as to allow the tip end of the aircraft nose radome (1) to penetrate through;

the clamp is characterized by also comprising a plurality of clamps (3) clamped on the outer side of each jointed board (2);

the loading device is characterized by further comprising a plurality of lifting lugs (4), wherein each lifting lug (4) is correspondingly arranged on one hoop (3), and the loading device is reversely weighted, so that the loading device does not generate additional load, and the loading precision is guaranteed;

the loading plate is characterized by further comprising a loading plate (5), one side of the loading plate is connected with the rear end of each jointed plate (2), the loaded pressing load on the loading plate can be uniformly transferred to each jointed plate (2), a second through hole is formed in the loading plate, and the second through hole is communicated with the first through hole;

the loading joint (6) is arranged on one side, facing away from each jointed board (2), of the loading plate (5).

2. The loading device of claim 1,

the loading plate (5) is connected with the rear end of each jointed plate (2) through a screw.

3. The loading device of claim 1,

the first side edge of any jointed board (2) is in lap joint or joggled joint with the second side edge of the other jointed board (2).