CN204673019U - A kind of radome of fighter installing hole bushing plate - Google Patents

Abstract

The utility model discloses an aircraft radome mounting hole drilling template, which comprises an upper clamping plate, a lower clamping plate, a bush, a locking pin and a product positioner. The mounting hole drilling templates are two radome skin curved surface shapes The assembly structure of the upper and lower clamping plates is docked. When drilling the mounting holes, the radome is set on the fuselage frame plate, and the mounting hole drilling template is set on the radome. There are pin holes on both sides of the upper and lower clamping plates, which are clamped by locking pins to ensure the same The skin surface of the aircraft radome is fitted together. According to the requirements of the installation hole position of the radome, there are corresponding holes on the upper and lower clamping plates. There is a bushing in each hole. The inner hole of the bush is the When the fuselage frame plate is assembled, the center line of the inner hole of the connecting hole is required to be perpendicular to the surface of the corresponding radome skin, so as to ensure the vertical accuracy of the assembly hole. Through the mounting hole drilling template, the entire assembly operation process of radome positioning, hole introduction, and drilling can be quickly realized, the production and manufacturing cycle is shortened, and the product assembly quality is improved.

Description

An aircraft radome installation hole drilling template

technical field

The utility model relates to the technical field of aircraft manufacturing and assembly, in particular to an aircraft radome mounting hole drilling template.

Background technique

During the assembly and installation process of the aircraft radome, in order to meet the technical requirements of the radome installation, in the process, usually before the radome is installed, the final installation hole of the radome is uniformly made on the fuselage frame plate in advance, so as to Make sure that the holes on the radome are consistent with those on the fuselage frame. Because the radome and the frame plate of the fuselage belong to a nested structure, the radome is first positioned and installed on the assembly frame, and then the radome is positioned, and then the holes on the radome are drawn from the frame plate of the fuselage from the inside to the outside, so that Ensure that the hole on the radome meets the assembly requirements of the frame plate of the fuselage. However, this installation coordination method has the following defects:

(1) Due to the structural design requirements of the radome, the fitting relationship between the outside of the radome and the inside of the fuselage frame during assembly. During the assembly process, it is necessary to guide the holes to the radome through the frame plate of the fuselage, but the operating space is narrow, and it is difficult to realize the accurate positioning of the radome and the frame plate holes of the fuselage, which belongs to "blind lead". In addition, the angle of some hole positions is relatively high for manual operation, so that accurate positioning can be achieved. The operation is too difficult, and the frame plate of the fuselage is easy to be damaged.

(2) The assembly process is relatively complicated, due to the accuracy requirements of the hole position requirements of the radome, and the radome needs to be disassembled and installed many times due to the hole introduction, hole making, and hole expansion. The workload of assembly work is heavy, and it is easy to generate accumulated errors in assembly and manufacturing, and it is also easy to damage the radome.

(3) Because the thickness of the interlayer at the junction of the radome and the fuselage frame is 6-7mm, the angle between the center line of each hole and the X-axis of the aircraft coordinate system is not the same, so it is difficult to ensure that the hole is drawn by manual marking. The axis of the hole is perpendicular to the radome, which causes the bolt installation to be skewed, and there are installation quality problems such as the mismatch between the bolt head and the countersunk socket. Moreover, the accuracy of the hole is reduced due to the repeated hole introduction process in the operation process, and the hole becomes larger and the hole Quality problems such as ellipse seriously affect the quality of assembly.

Contents of the invention

Purpose of the invention: In order to solve the deficiencies in the existing radome assembly, the utility model provides a precise positioning, easy-to-operate, and portable aircraft radome installation hole drilling template.

Technical solution of the invention: an aircraft radome mounting hole drilling template, including an upper clamping plate, a lower clamping plate, a bushing, a locking pin and a product positioner, characterized in that: the mounting hole drilling template is two The assembly structure of the butt joint of the upper and lower clamping plates in the shape of a curved surface. When drilling the mounting holes, the radome is set on the frame plate of the fuselage. The drilling template for the mounting holes is set on the radome. Pin holes are provided on both sides of the upper and lower clamping plates , clamped by the locking pin to ensure that it fits the curved surface of the aircraft radome skin. According to the requirements of the radome installation hole position, there are corresponding holes on the upper and lower clamping plates. There are bushes in the holes, and the inner parts of the bushes are The hole is the drilling guide hole for the connection hole when the aircraft radome is assembled with the fuselage frame plate. The center line of the inner hole is required to be perpendicular to the corresponding surface of the radome skin to ensure the vertical accuracy of the assembly hole. There are also L-shaped product locators under the two sides of the lower clamping plate. When drilling the installation holes, the product locators are connected to the frame plate of the fuselage, and a laser tracker is used to track the product locators to ensure that the installation holes are drilled when the template is installed. The relative position requirements of the radome and the frame plate of the fuselage realize the precise positioning of the radome, and the whole assembly operation process of the radome positioning, leading holes, and drilling can be quickly realized through the mounting hole drilling template.

Beneficial effects of the invention: the mounting hole drilling template not only guarantees the precision requirements of the radome and the frame hole position of the fuselage during the radome assembly and installation process, but also ensures the verticality requirements of the holes in the drilling process and the relative position requirements of the radome . And the assembly operation can be realized only by drilling the outside of the template from the installation hole, which provides enough operating space for assembly, improves the quality of product assembly, greatly improves production efficiency, shortens the production and manufacturing cycle, and thus improves the economic benefits of the enterprise. .

Description of drawings

Fig. 1 is the front view of the utility model;

Fig. 2 is a top view of the utility model.

In the figure: 1-upper clamping plate, 2-lower clamping plate, 3-bush, 4-locking pin, 5-product locator.

Detailed ways

The utility model will be further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

As shown in accompanying drawings 1 and 2, an aircraft radome installation hole drilling template includes an upper clamping plate 1, a lower clamping plate 2, a bushing 3, a locking pin 4 and a product locator 5. The mounting hole drilling template is an assembly structure in which two upper and lower clamping plates 1 and 2 are docked with the curved surface structure of the radome skin. On the radome, there are pin holes on both sides of the upper and lower clamping plates 1 and 2, which are clamped by the locking pin 4 to ensure that it fits the curved surface of the aircraft radome with a certain gap, so that there is a certain amount of adjustment during assembly. The upper and lower clamping plates 1 and 2 require a certain thickness of 30mm, and the thickness of the template can control the verticality and stability of the drilling tool during the drilling of the installation hole. According to the requirements of the radome installation holes, there are corresponding holes on the upper and lower clamping plates 1 and 2, and a bushing 3 is provided in each hole. The inner hole of the bushing 3 is used when the radome is assembled with the frame plate For the drilling guide hole of the connection hole, the center line of the inner hole must be perpendicular to the surface of the corresponding radome skin to ensure the vertical accuracy of the assembly hole. There is also an L-shaped product locator 5 under both sides of the lower clamping plate 2. When the installation hole is drilled, the product locator 5 is connected to the frame plate of the fuselage, and a laser tracker is used to track the product locator 5 to ensure that the installation hole is drilled when the template is installed. The relative position of the radome and the frame plate of the fuselage is required to realize the precise positioning of the radome. Through the mounting hole drilling template, the entire assembly operation process of radome positioning, leading holes, and drilling can be quickly realized. During the assembly operation, the assembly operation can be realized only by drilling the outside of the formwork from the installation hole, which provides enough operation space for assembly.

Claims (4)

1. A kind of aircraft radome mounting hole drilling template, comprising upper clamping plate [1], lower clamping plate [2], bushing [3], locking pin [4] and product locator [5], is characterized in that: The mounting hole drilling template is an assembly structure in which two upper and lower clamping plates [1], [2] with the surface shape of the radome skin are docked. The hole drilling template is set on the radome, and the upper and lower clamping plates [1], [2] are provided with pin holes on both sides, which are clamped by the locking pin [4] to ensure that it fits the curved surface of the aircraft radome skin, according to the radar According to the requirements of the installation holes of the cover, corresponding holes are opened on the upper and lower clamping plates [1], [2]. 2. a kind of aircraft radome installation hole drilling template according to claim 1, is characterized in that: described upper and lower clamping plates [1], [2] require a certain thickness to be 30mm. 3. a kind of aircraft radome installation hole drilling template according to claim 1 is characterized in that: a bushing [3] is provided in each hole on the upper and lower clamping plates [1], [2], and the bushing The inner hole of cover [3] is the drilling guide hole of the connecting hole when the aircraft radome is assembled with the fuselage frame plate, and the center line of the inner hole is required to be perpendicular to the corresponding surface of the radome skin. 4. a kind of aircraft radome mounting hole drilling formwork according to claim 1 is characterized in that: the lower clamping plate [2] both sides are also provided with L-shaped product locator [5] below, when drilling the mounting hole, the product locator [5] is connected with the frame plate of the fuselage, and a laser tracker is used to track the product locator [5] to ensure the relative position requirements of the radome and the frame plate of the fuselage when the installation hole drilling template is installed.