Three-way loading piece for static test of external hanging structure of airplane

Abstract

The invention provides a three-way loading piece for a static test of an external hanging structure of an airplane. The three-way loading piece mainly comprises a connecting conical bolt, a heading connector, a vertical connector, a lateral connector and a loading piece box section. The invention provides a three-way loading piece of an external hanging structure, which can replace a load generated by a real hanging object so as to carry out loading on a static test of a hanging box section, and can also reduce the manufacturing scale so as to reduce the test cost and shorten the manufacturing period.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft structural design, and relates to a three-way loading member for static tests of aircraft external suspension structures. Background Art

[0002] The lower wing skin is designed with an external suspension box section for mounting various suspended objects. It is a key structure of the aircraft, which undertakes the function of transmitting the load on the suspended object to the wing and is one of the main assessment parts of the whole aircraft.

[0003] The static test of the wing-mounted box section is to expose the details of the wing-mounted box section body, the connection area between the wing-mounted joint and the wing, and to verify the strength of the wing-mounted box section body, the connection between the wing-mounted joint and the wing, and the docking bolts between the wing-mounted joint and the wing. Summary of the Invention

[0004] The present invention provides a three-way loading member for static tests of aircraft external suspension structures, which can not only take into account the true load transmission of the external suspension joint of the wing, but also reduce the manufacturing scale, thereby reducing the manufacturing, test costs and manufacturing cycle.

[0005] The present invention provides a three-way loading member for static tests of aircraft external suspension structures, including: two side wall plates in the shape of a Chinese character "Ri", a cross beam, and a skin;

[0006] The two side wall plates in the shape of a Chinese character "Ri" are connected by a cross beam to form a rectangular frame structure, and the skin is arranged on both sides of the rectangular frame structure to form a loading member box section;

[0007] A lifting lug 1 is arranged above the side wall plate, a vertical load lug 3 is arranged below, a course load lug 2 is arranged at the outer bottom, and lateral load lugs 4 are arranged at the top and bottom of the side.

[0008] Optionally, the positions and directions of each lug are determined according to the load magnitudes and pressure centers in each direction of the suspended object load;

[0009] The load magnitudes and pressure centers in each direction of the suspended object load are determined according to the CFD calculation results of the whole aircraft and the analysis data of the wind tunnel pressure measurement test.

[0010] Optionally, the length of the three-way loading member for static tests of aircraft external suspension structures is the same as the distance between the wing-mounted box section joints.

[0011] Optionally, the width of the three-way loading member for static tests of aircraft external suspension structures is required to be symmetric, and the aerodynamic pressure center and the center of gravity are located on the symmetric center plane of the width. The width limit condition of the three-way loading member for static tests of aircraft external suspension structures is that it can install the widths of the two side cross beams plus the width of the middle joint.

[0012] Optionally, the number of the lateral load lugs 4 is four, the thickness is 25 mm, the number of the vertical load lugs 3 is two, and the thickness is 25 mm.

[0013] Optionally, the number of the heading load ears 2 is two, and the thickness is 25 mm.

[0014] Optionally, the structure of the lifting ear piece 1 is the same as the ear piece structure connected to the real lifting box section, and there are two of them, and the lifting ear pieces 1 are arranged above the two side wall panels.

[0015] Optionally, the number of beams is 4.

[0016] The present invention provides a three-dimensional loading component for static testing of aircraft external hanging structures. Compared with a loading component for hanging objects of a real aircraft, the three-dimensional loading capability of the hanging objects to be able to be tested to be transmitted to a wing hanging box section is retained, and other secondary structures are simplified. The test component has a simple design, a simple manufacturing process, and is convenient to install. It saves tooling and has matching rigidity. It fully utilizes the role of finite elements in modern aircraft design, retains the most important testing and transmission structures, simplifies secondary transmission and support structures, and thus has low manufacturing costs, short manufacturing cycles, and ensures model development nodes. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments of the present invention. It is obvious that the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0018] Figure 1 It is a schematic diagram of the structure of the three-way loading part of the static test of the external structure of the present invention;

[0019] Figure 2 It is a schematic diagram of the installation of the three-way loading component of the static test of the external structure of the present invention;

[0020] Figure 3 This is a schematic diagram of the three-way loading device configuration for the static test of the external structure of the present invention. Figure 1 ;

[0021] Figure 4 This is a schematic diagram of the three-way loading device configuration for the static test of the external structure of the present invention. Figure 2 ;

[0022] Description of reference numerals:

[0023] 1-Lifting ears;

[0024] 2- Heading load lugs;

[0025] 3-Vertical load lugs;

[0026] 4-Side load lugs. DETAILED DESCRIPTION

[0027] The following will make a detailed description of the three-way loading component for the static test of the aircraft external suspension structure provided by the present invention with reference to the accompanying drawings.

[0028] As Figure 1-4 shown, the three-way loading component for the static test of the aircraft external suspension structure provided by the present invention includes: two side wall plates in the shape of a Chinese character "ri", a cross beam, and a skin;

[0029] The two side wall plates in the shape of a Chinese character "ri" are connected by a cross beam to form a rectangular frame structure, and the skin is arranged on both sides of the rectangular frame structure to form a loading component box section;

[0030] A hoisting lug 1 is arranged above the side wall plate, a vertical load lug 3 is arranged below, a course load lug 2 is arranged at the outer bottom, and lateral load lugs 4 are arranged at the top and bottom of the side.

[0031] The hoisting lug 1 is a connection joint with the hoisting box section, with a quantity of 2; the course load lug 2 is a vertical and course connection joint, with a quantity of 2; the vertical load lug 3 is a connection joint with the vertical direction, with a quantity of 2; the lateral load lug 4 is a lateral and vertical connection joint, with a quantity of 4.

[0032] Based on the CFD calculation results of the whole aircraft and the analysis data of the wind tunnel pressure measurement test in the early stage, the load magnitude and pressure center situation in each direction of the suspended object load are established, so as to determine which parts of the loading dummy must be the same as the real part and how to arrange the lugs in each direction, thereby obtaining the final loading component.

[0033] In the present invention, the hoisting lug 1 is a joint connected to the hoisting box section, with a quantity of 2, and its structure is completely the same as the real structure; the course load lug 2 is a lug for transmitting the course load and also has the ability to transmit the vertical load, with a quantity of 1 at the front and 1 at the back, a total of 2, and the thickness of the lug is 25 mm; the vertical load lug 3 is a lug for transmitting the vertical load, the thickness of the lug is 25 mm, and the vertical load is the maximum load, arranged in 2; the lateral load lug 4 is a lug for transmitting the lateral load and also has the ability to transmit the vertical load, with a quantity of 4 including the upper, lower, and left ones, and the thickness of the lug is 25 mm.

[0034] Based on the CFD calculation results of the whole aircraft and the analysis data of the wind tunnel pressure measurement test in the early stage, the load magnitude and pressure center situation in each direction of the suspended object load are analyzed. The loads include the forward course load, the downward vertical load, and the lateral load. Different suspended object loads, combined with the loading component, form different configurations. When the aircraft is flying under different working conditions, there will also be different centers of gravity and aerodynamic pressure centers. As Figure 3 shown, the aerodynamic pressure center of Configuration 1 is behind the wing-mounted box section, and the aerodynamic pressure center of Configuration 2 is in front of the wing-mounted box section. Comparatively speaking, the lateral load of Configuration 2 is the largest and it is far from the centroid of the pylon, which will generate a relatively large bending moment on the connection joint.

[0035] The three-way loaders of the external structure static test are connected to the wing box section joints through two joints. In order to make the loader structure transmit force most directly and not generate additional bending moment at the joints, the length of the loaders is consistent with the distance between the wing box section joints, such as Figure 2 .

[0036] Due to the limitation of the space at the test site, the width of the loading part is required to be as small as possible, and it must meet the strength and stiffness design requirements. At the same time, in order to make the structure simple to manufacture, transfer the load directly, and not generate additional load and bending moment, the width of the loading part is required to be symmetrical, and the pneumatic pressure center and the center of gravity are set on the symmetrical center plane of the width. The loading part structure transmits force most directly. The width restriction condition of the loading dummy is that it can be installed by superimposing the width of the two side struts (i.e., beams) and the width of the middle joint. See Figure 4 .

[0037] Due to the limitations of the test site space and the specifications of the actuator to be installed, the loading part is required to be as short as possible. From the perspective of load transmission direction, the higher the height, the longer the lever arm and the smaller the load on the joint. In this way, a smaller actuator can be selected, which requires less installation space and is more convenient for loading.

[0038] From the perspective of the loading joints, the load center of gravity and pressure center must be between the lateral upward joint and the lateral downward joint so that the joints on each side can be loaded in the same direction for easy loading. This requires that the dummy must be at least higher than the aerodynamic pressure center of configuration 2 in the vertical direction and facilitate the installation of the joint.

[0039] The above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the field can easily think of various equivalent modifications or substitutions within the technical scope disclosed by the present invention, and these modifications or substitutions should all be covered within the protection scope of the present invention.

Claims

1. A three-way loading device for static testing of aircraft external structures, characterized in that: include: Two Japanese-shaped side wall panels, beams, and skins; Two Japanese-shaped side wall panels are connected by a crossbeam to form a rectangular frame structure, and skins are arranged on both sides of the rectangular frame structure to form a loading box section; A lifting lug (1) is arranged above the side wall plate, a vertical load lug (3) is arranged below the side wall plate, a heading load lug (2) is arranged at the outer bottom, and lateral load lugs (4) are arranged at the top and bottom of the side.

2. The three-way loading device for static test of aircraft external structure according to claim 1 is characterized in that: The position and direction of each ear piece are determined according to the load size and pressure center of the hanging load in each direction; The load size and pressure center of the hanging load in each direction are determined based on the CFD calculation results of the whole aircraft and the wind tunnel pressure test analysis data.

3. The three-way loading device for static test of aircraft external structure according to claim 2 is characterized in that: The length of the three-way loading piece in the static test of the aircraft external structure is consistent with the distance between the joints of the wing hanging box section.

4. The three-way loading device for static test of aircraft external structure according to claim 1, characterized in that: The width of the three-way loading component for static testing of aircraft external structures is required to be symmetrical, and the aerodynamic pressure center and center of gravity are located on the symmetrical center plane of the width. The width restriction condition of the three-way loading component for static testing of aircraft external structures is that it can be installed with the width of the two side beams superimposed on the width of the middle joint.

5. The three-way loading device for static test of aircraft external structure according to claim 1, characterized in that: The number of lateral load lugs (4) is four, and the thickness is 25 mm. The number of vertical load lugs (3) is two, and the thickness is 25 mm.

6. The three-way loading device for static test of aircraft external structure according to claim 1, characterized in that: The number of the heading load lugs (2) is two, and the thickness is 25 mm.

7. The three-way loading device for static test of aircraft external structure according to claim 1, characterized in that: The structure of the lifting ear piece (1) is the same as the structure of the ear piece connected to the real lifting box section, and there are two of them. The lifting ear pieces (1) are arranged above the two side wall plates.

8. The three-way loading device for static test of aircraft external structure according to claim 1, characterized in that: The number of beams is 4.

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