Supporting device for full-size test of aircraft aileron

Abstract

The utility model belongs to the technical field of airplane structure design and verification, and discloses an airplane aileron full-size test supporting device which comprises a loading mechanism and a bearing mechanism. Wherein a plurality of groups of loading mechanisms are arranged at intervals, each group comprises two loading mechanisms which are arranged at an angle, the two loading mechanisms respectively correspond to one aileron joint of the aileron, and the loading mechanisms are configured to apply tension or pressure to the aileron joints; the bearing mechanism is provided with a supporting structure, and the supporting structure is hinged to the aileron. The loading mechanisms are configured to apply tension or pressure to aileron joints of the ailerons so as to simulate the influence on the ailerons when an aircraft wing deforms, each loading mechanism corresponds to one aileron joint of the aileron so as to ensure that the ailerons can be uniformly stressed, and the bearing mechanism can fully limit the ailerons and prevent the ailerons from overturning in the operation process of the loading mechanisms; the structure of the test equipment is greatly simplified, the aileron angle can be changed, and subsequent aileron loading tests at different angles can be met.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft structure design and verification, especially relates to a full -scale test support device of aircraft aileron. BACKGROUND

[0002] Large aircraft aileron and wing box are connected through multiple joints, and the most serious strain value on the aileron structure can reach 1000-2000 micro-strain, and the strain value of the aileron influenced by the deformation of the wing is about 700 micro-strain, so the deformation of the wing box will inevitably affect the stress and strain distribution of the aileron wing surface.

[0003] The existing full -scale test of aileron uses the mode of full -machine constraint, and the wing box applies matching load, and the aerodynamic load is applied on the aileron surface, and the strain of the wing and the aileron is measured simultaneously. But the wing box loading needs to be matched, which greatly increases the demand of test loading and corresponding measurement equipment, and occupies the time of full -machine test, lengthens the full -machine test cycle and type development cycle. UTILITY MODEL CONTENTS

[0004] The utility model aims at providing a full -scale test support device of aircraft aileron, which can simulate the influence of wing deformation on aileron while supporting aileron.

[0005] To achieve this purpose, the utility model adopts the following technical scheme:

[0006] The full -scale test support device of aircraft aileron comprises:

[0007] Loading mechanism, multiple groups are arranged at intervals along the first direction, and each group of loading mechanism is provided with two angle arrangements, and the two loading mechanisms correspond to an aileron joint of aileron respectively, and the loading mechanism is configured to apply tension or pressure to the aileron joint;

[0008] Bearing mechanism, comprising support structure, the support structure is hinged to the aileron joint.

[0009] As preferred, the bearing mechanism further comprises adjusting structure, and the adjusting structure comprises:

[0010] Fixed seat;

[0011] Adapter seat, rotationally connected to the adapter part of the aileron, and the adapter seat can be locked to the adapter part;

[0012] Adjusting assembly is configured to drive the fixed seat and the adapter seat to approach or move away from each other.

[0013] As preferred, the adjusting assembly comprises:

[0014] A first connecting rod, one end of which is fixedly connected to the adapter;

[0015] a second connecting rod, coaxially arranged with the first connecting rod, wherein an end of the second connecting rod away from the first connecting rod is arranged on the fixing seat;

[0016] The adjusting sleeve rod is configured such that one end of the first connecting rod and the second connecting rod close to each other are screwed to two ends of the adjusting sleeve rod in a one-to-one correspondence.

[0017] Preferably, a locking groove is provided on the fixing seat, and a locking block is fixedly provided on one end of the second connecting rod facing the fixing seat, and the locking block can extend into the locking groove and be locked to the inner wall of the locking groove.

[0018] Preferably, the adjusting sleeve rod is further provided with a handle.

[0019] As an option, it also includes:

[0020] base plate;

[0021] There are multiple loading supports, each loading mechanism corresponds to one loading support, the loading mechanism is rotatably connected to the loading support, and the loading support is adjustably arranged on the base plate;

[0022] The bearing support is fixedly arranged on the bottom plate, and the bearing mechanism is detachably connected to the bearing support.

[0023] Preferably, the bearing support includes a vertical rod connected to the base plate, and the bearing mechanism is arranged on the top of the vertical rod.

[0024] Preferably, the bearing support further comprises:

[0025] a first crossbar connected to the bottom plate, the first crossbar extending along the first direction;

[0026] and / or, a second crossbar connected to the bottom plate, the second crossbar extending along a second direction;

[0027] The first direction is perpendicular to the second direction.

[0028] Preferably, the bearing support further comprises:

[0029] a first diagonal brace, one end of which is connected to the vertical rod and the other end of which is connected to the first cross rod;

[0030] And / or, a second diagonal brace, one end of which is connected to the vertical rod, and the other end of which is connected to the second cross rod.

[0031] Preferably, the two loading mechanisms in each group are arranged at an angle of 90°.

[0032] Beneficial effects of the utility model:

[0033] The loading mechanism is configured to apply tension or pressure to the aileron joint of the aileron to simulate the impact on the aileron when the aircraft wing is deformed. There are multiple groups of loading mechanisms at intervals, each group includes two loading mechanisms set at an angle, and each loading mechanism corresponds to an aileron joint of the aileron to ensure that the aileron can be evenly stressed. The bearing mechanism can fully limit the aileron to prevent the aileron from overturning during the operation of the loading mechanism. While greatly simplifying the structure of the test equipment, it can realize the change of the aileron angle and meet the subsequent aileron loading tests at different angles. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 This is a schematic structural diagram of one position of the full-scale test support device for an aircraft aileron according to the present invention;

[0035] Figure 2 yes Figure 1 A partial enlarged view of point A in the middle;

[0036] Figure 3 It is a structural schematic diagram of another orientation of the aircraft aileron full-scale test support device of the present invention.

[0037] In the picture:

[0038] 10. Aileron; 100. Aileron connector; 200. Adapter;

[0039] 1. Loading mechanism;

[0040] 2. Carrying mechanism; 21. Support structure; 22. Adjustment structure; 221. Fixing seat; 222. Adapter seat; 223. Adjustment assembly; 2231. First connecting rod; 2232. Second connecting rod; 2233. Adjustment sleeve rod; 2234. Locking block;

[0041] 3. Bottom plate;

[0042] 4. Loading support;

[0043] 5. Bearing support; 51. Vertical rod; 52. First cross bar; 53. Second cross bar; 54. First diagonal brace; 55. Second diagonal brace. DETAILED DESCRIPTION

[0044] The following describes in detail embodiments of the present invention. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar components or components having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present invention, and should not be construed as limiting the present invention.

[0045] In the description of the utility model, unless another definite provision and limitation, the term "connect", "connection", "fixed" should be broad sense understanding, for example, can be fixed connection, also can be detachable connection, can be mechanical connection, also can be electrical connection, can be direct connection, also can be indirectly connected through the intermediate medium, can be two element internal communication or two element's interaction relationship. For ordinary skilled in the art, the above-mentioned term can be understood according to the specific meaning in the utility model.

[0046] In the description of the utility model, unless another definite provision and limitation, the first feature is "on" or "under" the second feature can include the first feature and the second feature direct contact, can also include the first feature and the second feature is not direct contact but is through the contact between other features between them. Moreover, the first feature is "on", "above" and "on" the second feature includes the first feature is directly above and obliquely above the second feature, or just indicates that the first feature is higher than the second feature in horizontal height. The first feature is "under", "below" and "under" the second feature includes the first feature is directly below and obliquely below the second feature, or just indicates that the first feature is less than the second feature in horizontal height.

[0047] The technical scheme of the utility model is further illustrated below by specific embodiments in conjunction with the drawings.

[0048] As Figure 1-Figure 3 shown, the utility model provides a kind of airplane aileron full-size test support device, for supporting airplane aileron 10 and simulating the influence of airplane wing displacement to aileron 10.The airplane aileron full-size test support device includes loading mechanism 1 and bearing mechanism 2. Among them, loading mechanism 1 is spaced apart multiple groups, and each group of loading mechanism 1 is provided with two, two loading mechanism 1 is correspondingly arranged to aileron joint 100 of aileron 10, and loading mechanism 1 is configured to exert tensile force or pressure on aileron joint 100;Bearing mechanism 2 includes support structure 21, and support structure 21 is hinged to aileron joint 100.

[0049] Loading mechanism 1 is configured to exert tensile force or pressure on aileron joint 100 of aileron 10 to simulate the influence of airplane wing deformation on aileron 10, and loading mechanism 1 is spaced apart multiple groups, each group includes two loading mechanism 1 arranged at an angle, and each loading mechanism 1 corresponds to an aileron joint 100 of aileron 10 to ensure that aileron 10 can be uniformly stressed, and bearing mechanism 2 can fully limit aileron 10 to prevent aileron 10 from overturning during the operation of loading mechanism 1, greatly simplify the structure of test equipment, and can change the angle of aileron 10, and can meet the subsequent aileron 10 loading test at different angles.

[0050] Specifically, the two loading mechanisms 1 of each group are arranged at an angle of 90°. The above arrangement makes the tension or pressure on the two loading mechanisms 1 not affect each other.

[0051] In the embodiment, the loading mechanism 1 is an actuator commonly used in the art, which is prior art disclosed in the art and will not be described here.

[0052] Specifically, the bearing mechanism 2 further comprises an adjusting structure 22, which comprises a fixed seat 221, an adapter seat 222 and an adjusting assembly 223. The adapter seat 222 is rotationally connected to the adapter portion 200 of the aileron 10 and can be locked to the adapter portion 200. The adjusting assembly 223 is configured to drive the fixed seat 221 and the adapter seat 222 to move closer to or away from each other. The above-mentioned adjusting structure 22 is arranged to ensure the stability of the aileron 10 while the loading mechanism 1 loads the aileron 10, and at the same time, the adjusting assembly 223 is configured to drive the fixed seat 221 and the adapter seat 222 to move closer to or away from each other, so that the aileron 10 can rotate under the action of the loading mechanism 1; when the loading mechanism 1 completes the loading of the aileron 10, the adapter seat 222 can be locked to the adapter portion 200 for subsequent test steps, which is simple and convenient. In the embodiment, the adapter seat 222 can be locked to the adapter seat 222 through a bolt structure.

[0053] Specifically, it can be understood that the support structure 21 is detachably hinged to the aileron joint 100, and the support structure 21 can be selectively provided with multiple sizes to adapt to the adjusting assembly 223 in different states. When supporting the aileron 10, the adjusting assembly can be first used in cooperation with the loading mechanism 1 to adjust the aileron 10 to the desired angle by adjusting the distance between the fixed seat 221 and the adapter seat 222 while ensuring the stability of the aileron 10, and then the appropriate size of the support structure 21 is selected and installed to ensure the stability of the aileron 10.

[0054] More specifically, the adjusting assembly 223 comprises a first connecting rod 2231, a second connecting rod 2232 and an adjusting sleeve rod 2233. One end of the first connecting rod 2231 is fixedly connected to the adapter seat 222. The second connecting rod 2232 is coaxially arranged with the first connecting rod 2231, and one end of the second connecting rod 2232 away from the first connecting rod 2231 is arranged on the fixed seat 221. The adjusting sleeve rod 2233 is screwed to both ends of the adjusting sleeve rod 2233 one by one at the ends of the first connecting rod 2231 and the second connecting rod 2232 close to each other. The above-mentioned arrangement can drive the first connecting rod 2231 and the second connecting rod 2232 to move closer to or away from each other by rotating the adjusting sleeve rod 2233, which is simple, durable and not easy to damage, and convenient to operate.

[0055] More specifically, a locking groove is formed on the fixing base 221, and a locking block 2234 is fixedly provided on one end of the second connecting rod 2232 facing the fixing base 221. The locking block 2234 can extend into the locking groove and lock onto the inner wall of the locking groove. The above arrangement enables the second connecting rod 2232 to be detachably connected to the fixing base 221.

[0056] In this embodiment, the locking block 2234 is connected to the inner wall of the locking groove through a bolt structure. In other embodiments, the locking block 2234 can also be locked in the locking groove through a pin or rivet structure, which is not specifically limited here.

[0057] More specifically, the adjusting sleeve 2233 is further provided with a handle, which facilitates the tester to rotate the adjusting sleeve 2233.

[0058] In this embodiment, the adjustment sleeve 2233 is provided with an anti-slip structure. This anti-slip structure can be an anti-slip pad, such as a rubber pad; or, the anti-slip structure can be an anti-slip protrusion. The anti-slip protrusion can be a dot-shaped protrusion or a patterned protrusion of any shape, as long as it can increase the contact friction between the position and the tester's hand. The specific form of the anti-slip structure is referenced in the prior art and is not specifically limited in this embodiment.

[0059] Specifically, the full-scale aircraft aileron test support device also includes a base plate 3, a loading support 4, and a bearing support 5. Multiple loading supports 4 are provided, one for each loading mechanism 1. The loading mechanism 1 is rotatably connected to the loading support 4, which is adjustably mounted on the base plate 3. The bearing support 5 is fixed to the base plate 3, and the bearing mechanism 2 is detachably connected to the bearing support 5. This configuration allows the full-scale aircraft aileron test support device to be compatible with a variety of aileron models 10, providing high versatility.

[0060] More specifically, the bearing support 5 includes a vertical rod 51 connected to the base plate 3, with the bearing mechanism 2 disposed on top of the vertical rod 51. This arrangement enables the vertical rod 51 to bear the load of the aileron 10, thereby improving the stability of the aileron 10. In this embodiment, the bearing mechanism 2 is detachably connected to the top of the vertical rod 51 via a bolt structure.

[0061] More specifically, the support 5 further includes a first crossbar 52 and / or a second crossbar 53. The first crossbar 52 is connected to the base plate 3 and extends along a first direction; the second crossbar 53 is connected to the base plate 3 and extends along a second direction. The first direction is perpendicular to the second direction. This arrangement increases the contact area between the support 5 and the base plate 3, making the support 5 more stable.

[0062] In this embodiment, the loading support 4 is connected to the base plate 3 via a bolt structure, and a plurality of bolt holes are provided at intervals on the loading support 4 to adjust its position on the base plate 3 .

[0063] Optionally, the bearing support 5 further includes a first diagonal brace 54 and / or a second diagonal brace 55. The first diagonal brace 54 is connected to the vertical bar 51 at one end and to the first crossbar 52 at the other end; the second diagonal brace 55 is connected to the vertical bar 51 at one end and to the second crossbar 53 at the other end. This arrangement strengthens the support for the aileron 10 and prevents it from tipping over during testing.

[0064] In this embodiment, the vertical rod 51, the first horizontal rod 52, the second horizontal rod 53, the first diagonal brace 54 and the second diagonal brace 55 are all C-shaped steel or I-shaped steel in the prior art in this field, and are not described in detail here.

[0065] Obviously, the above embodiments of the present invention are merely examples for the purpose of clearly illustrating the present invention, and are not intended to limit the implementation methods of the present invention. Those skilled in the art will appreciate that other variations or modifications can be made based on the above description. It is not necessary and impossible to enumerate all implementation methods here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the claims of the present invention.

Claims

1. Aircraft aileron full-scale test support device, characterized by: include: A plurality of loading mechanisms (1) are arranged at intervals along a first direction, each group of the loading mechanisms (1) is provided with two loading mechanisms (1) arranged at an angle, the two loading mechanisms (1) respectively corresponding to an aileron joint (100) of the aileron (10), and the loading mechanisms (1) are configured to apply tension or pressure to the aileron joint (100); The carrying mechanism (2) comprises a supporting structure (21), wherein the supporting structure (21) is hinged to the aileron joint (100).

2. The aircraft aileron full-scale test support device according to claim 1, characterized in that: The carrying mechanism (2) further comprises an adjusting structure (22), wherein the adjusting structure (22) comprises: Fixed seat (221); An adapter seat (222) is rotatably connected to the adapter portion (200) of the aileron (10), and the adapter seat (222) can be locked to the adapter portion (200); The adjustment component (223) is configured to drive the fixing seat (221) and the adapter seat (222) to move closer to or farther from each other.

3. The aircraft aileron full-scale test support device according to claim 2, characterized in that: The adjustment component (223) includes: A first connecting rod (2231), one end of which is fixedly connected to the adapter (222); A second connecting rod (2232) is coaxially arranged with the first connecting rod (2231), and an end of the second connecting rod (2232) away from the first connecting rod (2231) is arranged on the fixing seat (221); The adjusting sleeve rod (2233) is configured such that the ends of the first connecting rod (2231) and the second connecting rod (2232) close to each other are screwed to the two ends of the adjusting sleeve rod (2233) in a one-to-one correspondence.

4. The aircraft aileron full-scale test support device according to claim 3, characterized in that: A locking groove is provided on the fixing seat (221), and a locking block (2234) is fixedly provided on one end of the second connecting rod (2232) facing the fixing seat (221), and the locking block (2234) can extend into the locking groove and be locked to the inner wall of the locking groove.

5. The aircraft aileron full-scale test support device according to claim 4, characterized in that: The adjusting sleeve rod (2233) is also provided with a handle.

6. The aircraft aileron full-scale test support device according to claim 1, characterized in that: Also includes: bottom plate (3); A plurality of loading supports (4) are provided, each loading mechanism (1) corresponds to one loading support (4), the loading mechanism (1) is rotatably connected to the loading support (4), and the loading support (4) is adjustably provided on the base plate (3); A bearing support (5) is fixedly arranged on the base plate (3), and the bearing mechanism (2) is detachably connected to the bearing support (5).

7. The aircraft aileron full-scale test support device according to claim 6, characterized in that: The bearing support (5) comprises a vertical rod (51) connected to the bottom plate (3), and the bearing mechanism (2) is arranged on the top of the vertical rod (51).

8. The aircraft aileron full-scale test support device according to claim 7, characterized in that: The bearing support (5) further comprises: a first crossbar (52) connected to the bottom plate (3), wherein the first crossbar (52) extends along the first direction; and / or, a second crossbar (53) connected to the bottom plate (3), wherein the second crossbar (53) extends along a second direction; The first direction is perpendicular to the second direction.

9. The aircraft aileron full-scale test support device according to claim 8, characterized in that: The bearing support (5) further comprises: A first diagonal brace (54), one end of which is connected to the vertical rod (51) and the other end of which is connected to the first cross rod (52); And / or, a second diagonal support rod (55), one end of which is connected to the vertical rod (51) and the other end of which is connected to the second cross rod (53).

10. The aircraft aileron full-scale test support device according to any one of claims 1 to 9, characterized in that: The two loading mechanisms (1) in each group are arranged at an angle of 90°.

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