Simple test platform for empennage of airplane

Abstract

The invention provides a simple test platform for an airplane empennage. The simple test platform mainly comprises four box section partition plate assemblies, two pairs of empennage butt joint double-lug connectors, a base, two outer skins, two connector supporting assemblies, two small partition plates, a platform upper end face assembly and a platform lower end face assembly. When an empennage static test is carried out, the platform is fixed on a test ground rail through bolts on a test ground, an empennage test piece is connected with the platform through a butt joint, and a loading test is carried out on the test piece. According to the invention, the elastic static support required by the test can be met, and the waste of construction period, material and labor cost caused by the use of the original structure (the whole aircraft) can be avoided. Compared with an original structure (the whole aircraft) for testing, the simple test platform for the aircraft empennage has lower requirements on the size of a test site and a test piece hoisting instrument, so that the test cost is greatly reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation technical structure design, and in particular relates to a simple test platform for an aircraft tail. Background Art

[0002] A static test task for the tail wing structure of a certain type of aircraft, in which the fuselage has no test part and is only used to provide elastic static support for the test part.

[0003] At present, when performing static tests on aircraft tail structures, the actual fuselage structure of the aircraft is usually used for testing.

[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 aircraft static testing remains high. Summary of the invention

[0005] The invention provides a simple test platform for an aircraft tail wing, so as to avoid using original structural parts as test parts, thereby greatly reducing the test cost.

[0006] The present invention provides a simple test platform for an aircraft tail, comprising: 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 group of docking double-ear joints 5, a second group of docking double-ear joints 6, a base 7, a skin 8, a first joint support assembly 9, a second joint support assembly 10, a small partition 11, a platform upper end surface assembly 12, and a platform lower end surface assembly 13; wherein,

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

[0008] The upper end surface assembly 12 of the platform is arranged on the top surface of the box segment partition assembly and the joint support assembly to form a frame structure; the lower end surface assembly 13 of the platform is arranged between the upper end surface assembly 12 and the base 7 on the platform; at least one small partition 11 is connected between the upper end surface assembly 12 on the platform and the lower end surface assembly 13 of the platform;

[0009] The first set of butt-jointed double-ear joints 5 and the second set of butt-jointed double-ear joints 6 are arranged above the upper end surface assembly 12 of the platform and are respectively connected to the first joint support assembly 9 and the second joint support assembly 10 for connecting the tail wing of the aircraft;

[0010] Skins 8 are provided on both side surfaces of the frame structure along the heading direction.

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

[0012] The first profiles are interconnected 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 interconnected 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 that 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] Third plates are 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;

[0021] Third profiles are connected to the two inclined 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 of the fourth profiles 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 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 interconnected 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 arranged above the trapezoidal plate, and its two ends are connected to the first box segment partition assembly 1 and the fourth box segment partition assembly 4, and 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, the number of the small partitions 11 is 2.

[0030] The present invention provides a simple test platform for the tail of an aircraft, so as to avoid using the original structural parts as test pieces, thereby greatly reducing the test cost. Through a large number of simulations and component calculations in the early stage, the present invention obtains the main influencing areas and load transfer characteristics of the test, designs the components of the platform, and sets a fixing device at the bottom thereof, which can not only meet the elastic static support required for the test, but also avoid the waste of construction period, materials and labor costs caused by using the original structure (the whole aircraft). Compared with the test of the original structure (the whole aircraft), a simple test platform for the tail of an aircraft has lower requirements on the size of the test site and the hoisting equipment of the test piece. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] 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.

[0032] Figure 1 This is a schematic diagram of the structure of the simple tail wing test platform;

[0033] Figure 2 It is a diagram of the box segment partition assembly;

[0034] Figure 3 It is a diagram of the joint support assembly;

[0035] Figure 4 It is a small partition diagram;

[0036] Figure 5 This is the upper end surface component diagram of the platform;

[0037] Figure 6 This is the assembly diagram of the lower end face of the platform;

[0038] Description of reference numerals:

[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-The first set of docking double-ear connectors;

[0044] 6- The second set of docking double ear connectors;

[0045] 7- Base;

[0046] 8-Skinning;

[0047] 9-first joint support assembly;

[0048] 10-second joint support assembly;

[0049] 11- small partition;

[0050] 12- platform upper end surface assembly;

[0051] 13-Platform lower end face assembly. DETAILED DESCRIPTION

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

[0053] like Figure 1-6 As shown, a simple test platform for an aircraft tail wing 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 group of docking double-ear joints 5, a second group of docking double-ear joints 6, a base 7, a skin 8, a first joint support assembly 9, a second joint support assembly 10, a small partition 11, a platform upper end surface assembly 12, and a platform lower end surface assembly 13.

[0054] A simple test platform for an aircraft tail wing is a riveted assembly, which is divided into three layers from top to bottom. The first layer is an upper surface assembly 12 of the platform; the second layer is a lower surface assembly 13 of the platform; and the third layer is a base 7.

[0055] The upper end face assembly 12 of the first platform includes a fifth profile, a trapezoidal plate and a rectangular plate. The fifth profile is divided into a reinforced profile and a common profile. The reinforced profile is arranged on both sides of the trapezoidal plate and is connected to the first group of tail joints and the second group of tail joints, while transmitting the tail heading load; the common profile is arranged in parallel on both sides of the rectangular plate, and the rectangular plate is arranged above the trapezoidal plate, with the first box section partition assembly 1 and the fourth box section partition assembly 4 connected at both ends, and the symmetry axes of the rectangular plate and the trapezoidal plate are consistent. In order to reduce the weight of the structure and provide a construction passage at the same time, concentric holes are provided between the rectangular plate and the trapezoidal plate between each partition assembly. The common profile and the rectangular plate in the fifth profile together constitute a reinforcement structure of the opening area of ​​the upper end face assembly 12 on the platform, which is used to reinforce the weakening of the plate caused by the opening of the trapezoidal plate and improve the stability of the plate.

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

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

[0058] The third profiles are connected to the oblique edges on both sides of each third plate;

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

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

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

[0062] The utility model discloses a simple test platform for an aircraft tail wing, which is divided into a front joint box section area, a middle platform area and a rear joint box section area from front to rear according to joint positions.

[0063] The front joint box section area is composed of a first box section bulkhead assembly 1, a first group of docking double-ear joints 5, a first joint support assembly 9, a second box section bulkhead assembly 2, a platform upper end surface assembly 12, and a platform lower end surface assembly 13; the front box section area is mainly used to simulate the fuselage tail wing front joint connection area and diffuse the tail wing vertical and lateral loads.

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

[0065] The rear joint box section area is composed of the third box section bulkhead assembly 3, the second set of docking double-ear joints 6, the second joint support assembly 10, the fourth box section bulkhead assembly 4, the platform upper end surface assembly 12, and the platform lower end surface assembly 13. The rear joint box section area is used to simulate the fuselage tail rear joint connection area and diffuse the tail vertical and lateral loads.

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

[0067] Through a large number of simulations and component calculations in the early stage, the main influencing areas and load transfer characteristics of the test were obtained, and the components of the platform were designed and fixed at the bottom, which can not only meet the elastic static support required for the test, but also avoid the waste of construction time, materials and labor costs caused by using the original structure (the whole aircraft). Compared with the test of the original structure (the whole aircraft), a simple test platform for the tail of an aircraft has lower requirements on the size of the test site and the hoisting equipment of the test piece.

[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 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 simple test platform for aircraft tail, 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 aircraft tail simple test platform 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) all 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 arranged on the first plates.

3. The simple test platform for aircraft tail wing according to claim 1, characterized in that: The first joint support component (9) and the second joint support component (10) both 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 simple test platform for aircraft tail wing according to claim 3, characterized in that: The second profiles arranged obliquely are L-shaped machined profiles with a stepped increase in cross-section and thickness.

5. The aircraft tail simple test platform 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 simple test platform for aircraft tail wing 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 trapezoidal; 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 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 simple test platform for aircraft tail wing according to claim 6, characterized in that: The fourth profiles are evenly spread out and arranged along both sides of the symmetry axis of the third plate, and the fourth profiles located on the symmetry axis are groove profiles.

8. The aircraft tail simple test platform according to claim 1, characterized in that: The upper end surface component (12) of the platform comprises a fifth profile, a trapezoidal plate and a rectangular plate; The fifth profiles are connected to each other to form a trapezoidal frame. The trapezoidal plate is fixed on the trapezoidal frame formed by the fifth profile, and a through hole is arranged on the trapezoidal plate; The rectangular plate is arranged above the trapezoidal plate, with two ends connected to the first box section partition assembly (1) and the fourth box section partition assembly (4), and the symmetry axes of the rectangular plate and the trapezoidal plate are consistent.

9. The aircraft tail simple test platform 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 simple test platform for aircraft tail wing according to claim 1, characterized in that: The number of small partitions (11) is 2.

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