A space vector measurement auxiliary sphere for radome assembly
By designing the space vector measurement auxiliary ball for radome assembly, the invisible lock intersection point is transferred to the measurable surface. The digital laser tracker measurement is used to solve the problem of the accuracy of the intersection point between the radome and the fuselage in the aircraft structure, and realizes the realization of the accuracy of the connection point between the radome and the fuselage. The assembly accuracy and quality guarantees, saving time and cost.
Patent Information
- Application Number
- CN201911286672.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2019-12-14
- Publication Date
- 2025-01-03
- Estimated Expiration
- 2039-12-14
AI Technical Summary
In aircraft structures, traditional manufacturing methods are difficult to achieve spatial position accuracy of the intersection point between the radome and the fuselage, resulting in the problems of inconsistency, interference, or inability to install during installation, especially when using composite materials and complex fixture designs. .
Design a space vector measurement auxiliary ball for radome assembly. By installing it on the lock, the invisible lock intersection point is transferred to the physical surface that can be directly measured. The space vector value is collected by using a digital laser tracker and the theoretical intersection position is reversed. Ensure assembly accuracy.
It realizes accurate installation of pre-predicted assembly locks, avoids assembly interference and deviation, reduces the time and cost of assembly adjustment, and improves the quality and economic benefits of parts delivery.
Smart Images
Figure CN111025247B_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of measuring equipment, in particular to a space vector measurement auxiliary sphere for radome assembly. Background Art
[0002] The interchangeability of aircraft products is one of the important indicators for evaluating the quality and maintenance performance of aircraft products. Due to the requirement of interchangeability in aircraft structures, the spatial position accuracy of connection intersections is required to be high. In order to meet the requirements of interchangeability in aircraft structures, traditional manufacturing methods generally use direct transfer through analog quantities, that is, using 1:1 samples, gauges, etc. in standard working methods to try to meet the spatial position of connection intersections, which requires high accuracy. However, this manufacturing method is often difficult to implement when manufacturing large aircraft.
[0003] The connection between the radome and the fuselage of Boeing civil aircraft is completed by coordinating the installation and locking of six sets of locks distributed on the edge of the open end of the radome with the corresponding devices on the front frame of the fuselage. The six sets of locks installed on the radome are designed to have their intersection points with the fuselage connection lock cylinders located inside the structure. Even if the manufacturing deviations of the lock cylinder and the lock body meet the design tolerance requirements, if they are not coordinated and matched during installation, it will still affect the coordination of the lock body and the lock cylinder when the radome is installed on the fuselage, and the coincidence of the radome axis with the fuselage axis.
[0004] From a manufacturing perspective, the main body of the radome is made entirely of advanced composite materials: epoxy resin-based reinforced glass fiber cloth and aramid paper honeycomb core. The material properties themselves determine its physical properties: rebound after curing and deformation under external pressure. The current fixture design assumes that the radome is completely positioned in the fixture without gaps before processing. However, it is not easy to achieve seamless and complete fit of the fixture when the larger-sized deformable composite radome is placed in the trimming and assembly fixture. When trimming, drilling and installing metal components, deviations may occur due to positioning, coordination, or forced assembly under conditions of deformation of parts, possible local stress release, etc. Whether the axis of the part, the axis of the processed hole and the corresponding axis of the rigid fixture are consistent cannot be verified intuitively.
[0005] From the inspection point of view, the intersection of the lock core of the theoretical lock in the design is not on the physical surface of the lock body, but on the spatial point inside the lock body. Its position and measurement relationship cannot be directly collected. In addition, due to the manufacturing deviation of the lock body itself, it is impossible to complete the modeling using a digital laser tracker. In other words, it is impossible to predict whether the assembled six sets of locks meet the theoretical design requirements.
[0006] These factors will cause the connecting components used to assemble the radome and the fuselage to interfere with the fuselage structure, resulting in the radome being out of coaxiality with the fuselage or being unable to be installed. Summary of the invention
[0007] In order to solve the above technical problems, the technical solution provided by the present invention is: a space vector measurement auxiliary ball for radome assembly, the edge of the radome is provided with six sets of locks connected with the fuselage connection lock core, the auxiliary ball is installed on the lock, the center of the auxiliary ball and the design intersection of the radome lock and the fuselage connection lock core are the same point, the auxiliary ball includes a spherical body and a lock core connection body, the spherical body includes a hemisphere 1 and a hemisphere 2 vertically arranged on the inner bottom surface, one end of the hemisphere 1 and the hemisphere 2 are fixedly connected to form an integrated structure, and the hemisphere 1 and the hemisphere 2 are fixedly connected to form an integrated structure. The two outer spherical surfaces are on the same spherical surface, and a U-shaped groove is provided on the side of the hemisphere one away from the hemisphere two, and the U-shaped groove cooperates with the rotary lock shaft of the lock, and the U-shaped groove has a rectangular cross-section and passes through the hemisphere one. The lock core connecting body is a column with a rectangular cross-section and four corners arranged with equilateral chamfers, and one end of the cylinder is fixedly connected to the center of the inner bottom surface of the hemisphere two to form an integrated structure, and the lock core connecting body is provided with a square hole for fixing the rotary lock in the lock, and the square hole has a rectangular cross-section, which passes through the lock core connecting body along a setting direction parallel to the hemisphere one.
[0008] As an improvement, the angle between the bottom surface of the U-shaped groove and the second inner bottom surface of the hemispherical body is an acute angle, and the center line of the U-shaped groove intersects with the center line of the first hemispherical body.
[0009] As an improvement, the cross section of the lock core connecting body is parallel to the bottom surface of the U-shaped groove, and the bottom surface of the square hole is parallel to the bottom surface of the U-shaped groove.
[0010] After adopting the above structure, the present invention has the following advantages: The present invention has a simple structure and is easy to use. The invisible intersection of the lock is transferred to a physical surface that can be directly collected by using an auxiliary ball, and the surface data of the auxiliary ball is measured by a digital laser tracker to collect the space vector value, and then the theoretical intersection position can be inferred to achieve the accuracy of the installation of the assembly lock, avoid the inability to complete the assembly due to interference or uncoordinated deviation during the final assembly, eliminate uncertainty, and ensure the quality of parts delivery. It greatly saves the time for final assembly adjustment and verification, greatly reduces the cost of manpower and material resources, and improves economic benefits. BRIEF DESCRIPTION OF THE DRAWINGS
[0011] Figure 1 The present invention is a schematic structural diagram of a space vector measurement auxiliary sphere for radome assembly.
[0012] Figure 2 The utility model is a schematic diagram of the installation of a space vector measurement auxiliary ball for assembling a radome according to the present invention.
[0013] Figure 3 The invention discloses an internal schematic diagram of a lock when installing a space vector measurement auxiliary ball for radome assembly.
[0014] Figure 4 It is a schematic diagram of the inner side of a lock when installing a space vector measurement auxiliary ball for radome assembly according to the present invention.
[0015] As shown in the figure: 1. Spherical body, 1.1. Hemisphere 1, 1.11. U-shaped groove, 1.2. Hemisphere 2, 2. Lock core connected to body, 2.1. Square hole, 3. Lock, 3.1. Rotary lock shaft, 3.2. Rotary lock. DETAILED DESCRIPTION
[0016] Combined with Figures 1 to 4 A space vector measurement auxiliary ball for radome assembly, the edge of the radome is provided with six sets of locks 3 docking with the fuselage, the auxiliary ball is installed on the lock 3, the center of the auxiliary ball and the design intersection of the lock core connecting the radome lock 3 and the fuselage are the same point, the auxiliary ball includes a spherical body 1 and a lock core connection body 2, the spherical body 1 includes a hemisphere 1.1 and a hemisphere 1.2 vertically arranged on the inner bottom surface, the hemisphere 1.1 and the hemisphere 1.2 are fixedly connected to form an integrated structure, the outer spherical surfaces of the hemisphere 1.1 and the hemisphere 1.2 are on the same spherical surface, and a U-shaped groove is provided on the side of the hemisphere 1.1 away from the hemisphere 2 1.2 1.11, the U-shaped groove 1.11 cooperates with the rotary lock shaft 3.1 of the lock 3, the cross-section of the U-shaped groove 1.11 is a rectangle that penetrates the hemisphere 1.1, the lock core connecting body 2 is a column with a cross-section of a rectangle and four corners arranged with equilateral chamfers, one end of which is fixedly connected to the center of the bottom surface of the hemisphere 2 1.2 to form an integrated structure, the lock core connecting body 2 is provided with a square hole 2.1 for fixedly connecting the rotary lock 3.2 in the lock 3, the cross-section of the square hole 2.1 is a rectangle, and it penetrates the lock core connecting body 2 along a direction parallel to the inner bottom surface of the hemisphere 1.1, and the square hole 2.1 and the penetration direction are perpendicular to the penetration direction of the U-shaped groove 1.11.
[0017] As a preferred implementation scheme of this embodiment, the angle between the bottom surface of the U-shaped groove 1.11 and the inner bottom surface of the second hemisphere 1.2 is an acute angle, and the center line of the U-shaped groove 1.11 intersects with the center line of the first hemisphere 1.1.
[0018] As a preferred implementation scheme of this embodiment, the cross section of the lock core connecting body 2 is parallel to the bottom surface of the U-shaped groove 1.11, and the bottom surface of the square hole 2.1 is parallel to the bottom surface of the U-shaped groove 1.11.
[0019] In the specific implementation of the present invention, the space vector measurement auxiliary ball is installed on the lock, and the center of the circle corresponding to the spherical body is overlapped with the invisible intersection of the lock. When the assembly begins, the surface data of the auxiliary ball is measured by a digital laser tracker, and the space vector value is collected, and then the center position corresponding to the spherical body can be inferred, thereby obtaining the theoretical intersection position. The accuracy of the assembly lock can be predicted, and the assembly cannot be completed due to interference or uncoordinated deviation during the final assembly, eliminating uncertainty and ensuring the quality of parts delivery.
[0020] The present invention and its embodiments are described above, and such description is not restrictive. The drawings show only one embodiment of the present invention, and the actual structure is not limited thereto. In short, if ordinary technicians in the field are inspired by it, without departing from the purpose of the invention, they can design a structure and embodiment similar to the technical solution without creativity, which should belong to the protection scope of the present invention.
Claims
1. A space vector measurement auxiliary ball for radome assembly, the edge of the radome is provided with six sets of locks connected to the fuselage lock core, the auxiliary ball is installed on the lock, characterized in that: The center of the auxiliary ball and the designed intersection of the lock core connected to the radome lock and the fuselage are the same point. The auxiliary ball includes a spherical body and a lock core connection body. The spherical body includes a hemisphere one and a hemisphere two vertically arranged on the inner bottom surface. One end of the hemisphere one and the hemisphere two are fixedly connected to form an integrated structure, and the outer spherical surfaces of the hemisphere one and the hemisphere two are on the same spherical surface. A U-shaped groove is provided on the side of the hemisphere one away from the hemisphere two, and the U-shaped groove cooperates with the rotary lock shaft of the lock. The cross-section of the U-shaped groove is a rectangle and passes through the hemisphere one. The lock core connection body is a column with a cross-section of a rectangle with four corners arranged as equilateral chamfers, and one end of the column is fixedly connected to the center of the inner bottom surface of the hemisphere two to form an integrated structure. The lock core connection body is provided with a square hole for fixing the rotary lock in the lock. The cross-section of the square hole is a rectangle, and it passes through the lock core connection body along a setting direction parallel to the hemisphere one.
2. The space vector measurement auxiliary sphere for radome assembly according to claim 1, characterized in that: The angle between the bottom surface of the U-shaped groove and the second inner bottom surface of the hemispherical body is an acute angle, and the center line of the U-shaped groove intersects with the center line of the first hemispherical body.
3. The space vector measurement auxiliary sphere for radome assembly according to claim 1, characterized in that: The cross section of the lock core connecting body is parallel to the bottom surface of the U-shaped groove, and the bottom surface of the square hole is parallel to the bottom surface of the U-shaped groove.