A simple test platform for aircraft tail fins

Abstract

This invention provides a simplified test platform for aircraft tail fins, mainly comprising four box-section partition assemblies, two pairs of tail fin docking lugs, a base, two outer skins, two joint support assemblies, two small partitions, an upper platform surface assembly, and a lower platform surface assembly. During static tail fin tests, the platform is bolted to a test track at the test site. The tail fin test piece is connected to the platform via the docking lugs, and a loading test is performed on the test piece. This invention satisfies the requirements for elastic statically determinate support during testing while avoiding the waste of time, materials, and labor costs associated with using the original structure (the entire aircraft). Compared to testing with the original structure (the entire aircraft), this simplified aircraft tail fin test platform has lower requirements for test site size and test piece hoisting equipment, thus significantly reducing testing costs.

Description

Technical Field

[0001] This invention belongs to the field of aerospace structural design technology, specifically relating to a simplified test platform for aircraft tail fins. Background Technology

[0002] The static test mission of the tail structure of a certain type of aircraft, in which the fuselage has no test parts, is only used to provide elastic statically determinate support for the test parts.

[0003] Currently, static tests on aircraft tail structures are typically conducted using the actual aircraft fuselage structure.

[0004] However, after the static test, the actual fuselage structure of the aircraft can no longer be used, resulting in a huge waste of test materials. Due to the high cost of the fuselage, the cost of static testing of aircraft remains high. Summary of the Invention

[0005] This invention provides a simplified test platform for aircraft tail fins, thereby avoiding the use of original structural components as test pieces and significantly reducing test costs.

[0006] This invention provides a simplified test platform for an aircraft tail section, comprising: a first segment partition assembly 1, a second segment partition assembly 2, a third segment partition assembly 3, a fourth segment partition assembly 4, a first set of mating double-ear connectors 5, a second set of mating double-ear connectors 6, a base 7, a skin 8, a first connector support assembly 9, a second connector support assembly 10, a small partition 11, an upper platform surface assembly 12, and a lower platform surface assembly 13; wherein,

[0007] The first box section partition assembly 1, the first joint support assembly 9, the second box section partition assembly 2, the third box section partition assembly 3, the second joint support assembly 10, and the fourth box section partition assembly 4 are trapezoids with the same height and gradually decreasing width, arranged parallel to each other, and vertically fixed on the base 7.

[0008] The upper platform surface assembly 12 is disposed on the top surface of the box section partition assembly and the joint support assembly, forming a frame structure; the lower platform surface assembly 13 is disposed between the upper platform surface assembly 12 and the base 7; at least one small partition 11 is connected between the upper platform surface assembly 12 and the lower platform surface assembly 13.

[0009] The first set of docking double-ear connectors 5 and the second set of docking double-ear connectors 6 are disposed above the upper surface assembly 12 of the platform and are respectively connected to the first connector support assembly 9 and the second connector support assembly 10 for connecting the aircraft tail.

[0010] Skin 8 is provided on both sides of the frame structure along the flight direction.

[0011] Optionally, the first cassette section partition assembly 1, the second cassette section partition assembly 2, the third cassette section partition assembly 3, and the fourth cassette section partition assembly 4 each include: a first profile and a first plate;

[0012] The first profiles are connected to each other to form a "day" - shaped trapezoidal frame, and the first plates are fixed to the trapezoidal frame formed by the first profiles. Through - holes are provided on the first plates.

[0013] Optionally, the first joint support assembly 9 and the second joint support assembly 10 each include: a second profile, a column, and a second plate;

[0014] The second profiles are connected to each other to form a "day" - shaped trapezoidal frame, and the second plates are fixed to the trapezoidal frame formed by the second profiles;

[0015] A plurality of columns are supported between the second profiles arranged horizontally.

[0016] Optionally, the obliquely - arranged second profiles are L - shaped machined profiles with a stepped increase in cross - section and thickness.

[0017] Optionally, the material of the first plate or the second plate is the same as that of the skin 8;

[0018] The thickness of the second plate is greater than the thickness of the first plate.

[0019] Optionally, the lower - end face assembly 13 of the platform includes: a third profile, a fourth profile, and a plurality of third plates; the third plates are trapezoidal;

[0020] Between the first cassette section partition assembly 1 and the first joint support assembly 9, between the first joint support assembly 9 and the second cassette section partition assembly 2, between the second cassette section partition assembly 2 and the third cassette section partition assembly 3, between the third cassette section partition assembly 3 and the second joint support assembly 10, and between the second joint support assembly 10 and the fourth cassette section partition assembly 4, third plates are connected;

[0021] Third profiles are connected to the two slant edges on both sides of each third plate;

[0022] The fourth profiles are arranged parallel to each other along the course and are connected to the third plates.

[0023] Optionally, each fourth profile is evenly arranged on both sides of the symmetry axis of the third plate, and the fourth profile located on the symmetry axis is a channel - shaped profile.

[0024] Optionally, the upper - end face assembly 12 of the platform includes a fifth profile, a trapezoidal plate, and a rectangular plate;

[0025] The fifth profiles are connected to each other to form a trapezoidal frame,

[0026] The trapezoidal plate is fixed to the trapezoidal frame formed by the fifth profiles, and through - holes are provided on the trapezoidal plate;

[0027] The rectangular plate is placed above the trapezoidal plate, and its two ends are connected to the first box section partition assembly 1 and the fourth box section partition assembly 4. The symmetry axes of the rectangular plate and the trapezoidal plate are consistent.

[0028] Optionally, the small partition 11 is located between the second box section partition assembly 2 and the third box section partition assembly 3.

[0029] Optionally, there are two small partitions 11.

[0030] This invention provides a simplified test platform for aircraft tail fins, avoiding the use of original structural components as test specimens and thus significantly reducing testing costs. Through extensive preliminary simulations and component calculations, this invention identifies the main influencing areas and load transfer characteristics, designs the platform's components, and installs fixing devices at its base. This provides the necessary elastic statically determinate support for testing while avoiding the waste of time, materials, and labor costs associated with using the original structure (the entire aircraft). Compared to testing with the original structure (the entire aircraft), this simplified aircraft tail fin test platform has lower requirements for test site size and test specimen hoisting equipment. Attached Figure Description

[0031] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the embodiments of the present invention will be briefly introduced below. Obviously, 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 effort.

[0032] Figure 1 This is a schematic diagram of a simplified test platform for the tail fin.

[0033] Figure 2 Diagram of the box section partition assembly;

[0034] Figure 3 Diagram of the connector support assembly;

[0035] Figure 4 Diagram of a small partition;

[0036] Figure 5 This is a diagram of the upper surface components of the platform.

[0037] Figure 6 This is a diagram of the lower surface components of the platform.

[0038] Explanation of reference numerals in the attached figures:

[0039] 1-First box section partition assembly;

[0040] 2-Second box section partition assembly;

[0041] 3-Third box section partition assembly;

[0042] 4-Fourth box section partition assembly;

[0043] 5-First set of mating double-ear connectors;

[0044] 6-Second set of mating double-ear connectors;

[0045] 7-Base;

[0046] 8-Skin;

[0047] 9-First joint support assembly;

[0048] 10-Second connector support assembly;

[0049] 11-Small partition;

[0050] 12-Platform upper surface component;

[0051] 13-Platform lower end face component. Detailed Implementation

[0052] The simplified test platform for aircraft tail fins provided by the present invention will be described in detail below with reference to the accompanying drawings.

[0053] like Figure 1-6 As shown, a simplified test platform for an aircraft tail fin includes: a first box section partition assembly 1, a second box section partition assembly 2, a third box section partition assembly 3, a fourth box section partition assembly 4, a first set of docking double-ear connectors 5, a second set of docking double-ear connectors 6, a base 7, a skin 8, a first connector support assembly 9, a second connector support assembly 10, a small partition 11, an upper platform surface assembly 12, and a lower platform surface assembly 13.

[0054] A simple test platform for an aircraft tail fin is a riveted assembly, consisting of three layers from top to bottom: the first layer is the upper end face assembly 12 of the platform; the second layer is the lower end face assembly 13 of the platform; and the third layer is the base 7.

[0055] The upper surface assembly 12 of the first-layer platform comprises a fifth profile, trapezoidal plates, and rectangular plates. The fifth profile is divided into reinforced and ordinary profiles. The reinforced profiles are arranged on both sides of the trapezoidal plates and connect to the first and second sets of tail fin connectors, simultaneously transmitting the tail fin's directional load. The ordinary profiles are arranged parallel to both sides of the rectangular plates, which are positioned above the trapezoidal plates and connected at both ends to the first and fourth box-section partition assemblies 1 and 4, respectively. The symmetrical axes of the rectangular and trapezoidal plates are aligned. To reduce structural weight and provide construction access, concentric holes are provided between each partition assembly in both the rectangular and trapezoidal plates. The ordinary and rectangular profiles within the fifth profile together constitute the reinforcement structure of the opening area of ​​the upper surface assembly 12 on the platform, used to compensate for the weakening effect of the trapezoidal plate openings and improve the plate's stability.

[0056] The second-layer platform lower end face component 13 includes: a third profile, a fourth profile, and multiple third plates; the third plates are trapezoidal.

[0057] A third plate is connected between the first box section partition assembly 1 and the first joint support assembly 9, between the first joint support assembly 9 and the second box section partition assembly 2, between the second box section partition assembly 2 and the third box section partition assembly 3, between the third box section partition assembly 3 and the second joint support assembly 10, and between the second joint support assembly 10 and the fourth box section partition assembly 4.

[0058] Each third plate has a third profile connected to its two beveled sides;

[0059] The fourth profiles are arranged parallel to each other along the flight direction and are connected to the third plate.

[0060] The lower end face component 13 of the platform is used to simulate the support of the tail wing docking platform by the tail wing connection area panel.

[0061] The third layer is the base 7, which is made of 60mm thick steel plate and is used to constrain the entire device.

[0062] A simplified test platform for an aircraft tail fin is divided into three sections from front to back, based on the joint positions: the front joint box section, the middle platform section, and the rear joint box section.

[0063] The front junction box section consists of the first junction box partition assembly 1, the first set of docking double lug connectors 5, the first connector support assembly 9, the second junction box partition assembly 2, the upper end face assembly of the platform 12, and the lower end face assembly of the platform 13. The front junction box section is mainly used to simulate the fuselage tail fin front junction connection area and to diffuse the vertical and lateral loads of the tail fin.

[0064] The intermediate platform area consists of two small partitions 11, an upper platform surface assembly 12, and a lower platform surface assembly 13. The intermediate platform area is used to simulate the support provided by the fuselage tail platform to the connection area, and the small partitions 11 are used to support the stability of the platform area.

[0065] The rear connector box section is composed of the third box section partition assembly 3, the second set of docking double lug connectors 6, the second connector support assembly 10, the fourth box section partition assembly 4, the upper end face assembly of the platform 12, and the lower end face assembly of the platform 13. The rear connector box section is used to simulate the rear connector connection area of ​​the fuselage tail fin and to diffuse the vertical and lateral loads of the tail fin.

[0066] Finally, skin 8 is arranged on both sides of the device to improve the overall stability and strength of the platform.

[0067] Through extensive preliminary simulations and component calculations, the main influencing areas and load transfer characteristics of the test were determined. The platform components were designed, and a fixing device was installed at its bottom. This design not only meets the requirements for elastic statically determinate support for the test but also avoids the waste of time, materials, and labor costs associated with using the original structure (the entire aircraft). Compared to testing with the original structure (the entire aircraft), this simplified aircraft tail fin test platform has lower requirements for test site size and test component hoisting equipment.

[0068] 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 person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should be covered within the protection scope of the present invention.

Claims

1. A simplified test platform for an aircraft tail fin, characterized in that, Comprising: The first box-section partition component (1), the second box-section partition component (2), the third box-section partition component (3), the fourth box-section partition component (4), the first group of docking double-ear joints (5), the second group of docking double-ear joints (6), the base (7), the skin (8), the first joint support component (9), the second joint support component (10), the small partition (11), the upper end-face component of the platform (12), the lower end-face component of the platform (13); wherein, The first box-section partition component (1), the first joint support component (9), the second box-section partition component (2), the third box-section partition component (3), the second joint support component (10), and the fourth box-section partition component (4) are trapezoids with the same height and gradually decreasing widths, are arranged parallel to each other, and are vertically fixed on the base (7); The upper end-face component of the platform (12) is arranged on the top surfaces of the box-section partition components and the joint support components to form a frame structure; the lower end-face component of the platform (13) is arranged between the upper end-face component of the platform (12) and the base (7); at least one small partition (11) is connected between the upper end-face component of the platform (12) and the lower end-face component of the platform (13); The first group of docking double-ear joints (5) and the second group of docking double-ear joints (6) are arranged above the upper end-face component of the platform (12) and are respectively connected to the first joint support component (9) and the second joint support component (10) for connecting the aircraft tail fin; The skins (8) are arranged on both sides of the frame structure along the course.

2. The simplified test platform for aircraft tail fins according to claim 1, characterized in that, The first box-section partition component (1), the second box-section partition component (2), the third box-section partition component (3), and the fourth box-section partition component (4) each include: the first profile and the first plate; The first profiles are connected to each other to form a "day"-shaped trapezoidal frame, the first plates are fixed on the trapezoidal frame formed by the first profiles, and through holes are provided on the first plates.

3. The simplified test platform for aircraft tail fins according to claim 1, characterized in that, The first joint support component (9) and the second joint support component (10) each include: the second profile, the columns, and the second plates; The second profiles are connected to each other to form a "day"-shaped trapezoidal frame, and the second plates are fixed on the trapezoidal frame formed by the second profiles; A plurality of columns are supported between the second profiles arranged horizontally.

4. The simplified test platform for aircraft tail fins according to claim 3, characterized in that, The second profiles arranged obliquely are L-shaped machined profiles with stepped increases in cross-section and thickness.

5. The simplified test platform for aircraft tail fins according to claim 2 or 3, characterized in that, The material of the first plate or the second plate is the same as that of the skin (8); The thickness of the second plate is greater than the thickness of the first plate.

6. The simplified test platform for aircraft tail fins according to claim 1, characterized in that, The lower end-face component of the platform (13) includes: the third profile, the fourth profile, and a plurality of third plates; the third plates are trapezoids; Third plates are connected between the first box-section partition component (1) and the first joint support component (9), between the first joint support component (9) and the second box-section partition component (2), between the second box-section partition component (2) and the third box-section partition component (3), between the third box-section partition component (3) and the second joint support component (10), and between the second joint support component (10) and the fourth box-section partition component (4); The third profiles are connected to the two slant edges on both sides of each third plate; The fourth profiles are arranged parallel to each other along the course and are connected to the third plates.

7. The simplified test platform for aircraft tail fins according to claim 6, characterized in that, Each fourth profile is evenly distributed on both sides of the axis of symmetry of the third plate, and the fourth profile located on the axis of symmetry is a channel profile.

8. The simplified test platform for aircraft tail fins according to claim 1, characterized in that, The upper surface component (12) of the platform includes a fifth profile, a trapezoidal plate and a rectangular plate; The fifth profile is interconnected to form a trapezoidal frame. The trapezoidal plate is fixed on the trapezoidal frame composed of the fifth profile, and the trapezoidal plate has through holes; The rectangular plate is placed above the trapezoidal plate, and the two ends are connected to the first box section partition assembly (1) and the fourth box section partition assembly (4). The symmetry axes of the rectangular plate and the trapezoidal plate are consistent.

9. The simplified test platform for aircraft tail fins according to claim 1, characterized in that, The small partition (11) is located between the second box section partition assembly (2) and the third box section partition assembly (3).

10. The simplified test platform for aircraft tail fins according to claim 1, characterized in that, There are 2 small partitions (11).

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