Testing device for applying full-aircraft static test wingtip load
By designing a test loading device consisting of end diaphragms, center diaphragms, and skin, the problem of inconvenient application of wingtip loads was solved, and the loading accuracy and convenience were improved, meeting the requirements of static testing of the entire aircraft.
Patent Information
- Application Number
- CN202520238368.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-14
- Publication Date
- 2025-12-16
- Estimated Expiration
- 2035-02-14
AI Technical Summary
Existing technologies lack effective testing and loading devices, making it difficult to apply loads to the wingtips, resulting in inconvenient loading and insufficient accuracy.
Design a test device consisting of end diaphragms, middle diaphragms, skin, stiffened wall panels, beams, and loading holes. The load is equivalent through multiple loading holes and counterweight holes, thereby improving loading accuracy and convenience.
It enables precise application of wingtip loads, improves the convenience and accuracy of the loading device, ensures load equivalence, and meets the requirements of the full-aircraft static test.
Smart Images
Figure CN223672810U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model belongs to the technical field of aircraft strength test, and relates to a test device for applying wing tip load of whole aircraft static test. BACKGROUND
[0002] Whole aircraft static test is an indispensable link in the process of aircraft research and development, and is an important basis for evaluating the rationality and strength reliability of aircraft structure. Whole aircraft static test is a ground test for simulating various loads on the aircraft in the air. It simulates complex loads such as aerodynamic force and engine thrust that the aircraft may encounter in the air through a complex loading device and system, and truly applies the loads on the aircraft to evaluate whether the aircraft fuselage structure meets the strength requirements. Ground load calibration test is to obtain the response model of the aircraft structure to external loads, so as to calculate the external loads borne by the aircraft according to the data in flight test.
[0003] When the test is carried out, the load needs to be applied on the wing tip. Since the actual wing tip shape is a double curved surface with large curvature, it is not convenient to apply the load, and a test loading device needs to be designed to replace the wing tip for loading. However, there is no typical device for the test loading device at present. CONTENT OF THE UTILITY MODEL
[0004] The utility model aims at overcoming the defects of the prior art, and provides a test device for applying wing tip load of whole aircraft static test, which can replace the wing tip for static loading, improve the loading precision and convenience, and realize load equivalence.
[0005] To achieve the above-mentioned purpose, the utility model adopts the following technical solutions:
[0006] A test device for applying wing tip load of whole aircraft static test, comprising an end partition plate and a middle partition plate;
[0007] The middle partition plate is provided with a skin on one side and a stiffened wall plate on the other side. The skin and the stiffened wall plate are both two layers, and a beam is arranged between the front and rear ends of the two layers to support and connect the two layers. The beam, the stiffened wall plate and the skin form a torsion box. The end of the beam on the side of the stiffened wall plate is provided with a butt strap. The middle partition plate is divided into front and rear parts. The front half of the middle partition plate extends out of the skin and the stiffened wall plate, and the rear half of the middle partition plate is located between the skin and the stiffened wall plate.
[0008] The end partition plate is provided with an end joint on one side, and the other side of the end partition plate is connected to the side of the skin away from the middle partition plate.
[0009] The end joint is provided with two loading holes, and each corner of the end partition plate is provided with a loading hole. The front half of the middle partition plate is provided with a loading hole on each of the upper and lower sides, and each corner of the rear half of the middle partition plate is provided with a loading hole.
[0010] Preferably, the number of end joints is two, and the two end joints are arranged at intervals.
[0011] Preferably, the upper and lower sides of the beam are connected with the edge strips.
[0012] Further, the middle partition plate divides the edge strips into left and right parts.
[0013] Preferably, the skin is provided with a plurality of rib plates, the plurality of rib plates are arranged in parallel, are arranged in parallel in the front-rear direction, and two ends of the rib plates are connected with the end partition plate and the middle partition plate respectively.
[0014] Further, the beam and the rib plate are provided with three weight-deduction holes.
[0015] Preferably, the skin is provided with an observation hole.
[0016] Preferably, the end partition plate, the middle partition plate, the beam and the skin are provided with weight-deduction holes.
[0017] Preferably, the rear half of the middle partition plate is welded and fixed with the beam, the skin and the reinforced wall plate, the middle of the front half of the middle partition plate is welded with the corresponding beam, and the upper and lower ends of the front half of the middle partition plate are welded and fixed with the upper and lower ends of the rear half of the middle partition plate.
[0018] Preferably, the thickness of the upper and lower two layers of the skin away from the middle partition plate is less than the thickness of the upper and lower two layers of the reinforced wall plate away from the middle partition plate.
[0019] Compared with the prior art, the utility model has the following beneficial effects:
[0020] The utility model reserves a loading joint, can replace the adhesive tape loading, improves the loading precision and convenience, the utility model arranges multiple loading holes in each direction, no matter how the load pressure center position changes, can realize the load equivalence.
[0021] Further, the utility model reserves an observation hole on the skin to observe the welding seam and ensure the welding quality.
[0022] Further, the utility model reserves the weight-deduction hole and the weight-deduction hole, and is convenient for weight-deduction and device installation during the test. DRAWINGS
[0023] Figure 1 It is a structural schematic view of the test device for applying the wing tip load of the full machine static test of the utility model.
[0024] Wherein: 1-end joint; 2-end partition plate; 3-middle partition plate; 4-skin; 5-beam; 6-edge strip; 7-rib plate; 8-reinforced wall plate; 9-butting plate. CONCRETE IMPLEMENTING METHOD
[0025] The embodiments of the present application will be described in detail below with reference to the drawings, examples of which are shown in the drawings, wherein the same or similar notations represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the drawings are exemplary and are for the purpose of explaining the present application only, and are not to be understood as limiting the present application.
[0026] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features limited by "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise specifically limited.
[0027] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which the present application belongs. The terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or electrically connected or can communicate with each other; it can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two elements or the interaction relationship between two elements. The term "and / or" used herein includes any and all combinations of one or more related listed items. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances. The terms used in the specification of the present application are only for the purpose of describing the specific embodiments, and are not intended to limit the present application.
[0028] The disclosure below provides many different implementations or examples to implement different structures of the present application. In order to simplify the disclosure of the present application, the components and settings of specific examples are described below. Of course, they are only examples and the purpose is not to limit the present application. In addition, the present application can repeatedly refer to numbers and / or letters in different examples, and such repetition is for the purpose of simplification and clarity, which itself does not indicate the relationship between the various embodiments and / or settings discussed. In addition, the present application provides examples of various specific processes and materials, but those skilled in the art can realize the application of other processes and / or the use of other materials.
[0029] As shown in Figure 1 The test device for applying wing tip load of full machine static test of the present application is composed of 22 components in total, which are end joint 1 (2), end partition plate 2 (1), middle partition plate 3 (1), skin 4 (2), beam 5 (2), edge strip 6 (8), rib plate 7 (2), stiffened wall plate 8 (2) and butt strap 9 (2) in total.
[0030] The end joint 1 is a "T" shaped joint; the end partition plate 2 is a quadrilateral 8mm thick plate; the middle partition plate 3 is a quadrilateral 8mm thick plate; the skin 4 is a quadrilateral 8mm thick plate; the beam 5 is a polygon 8mm thick plate; the edge strip 6 is a quadrilateral 8mm thick plate; the rib plate 7 is a quadrilateral 8mm thick plate; the stiffened wall plate 8 is an 80mm thick plate; and the butt strap 9 is a polygon forged piece.
[0031] The middle partition plate 3 has a skin 4 on one side and a stiffened wall plate 8 on the other side, and both the skin 4 and the stiffened wall plate 8 are two layers, and a beam 5 is arranged at the front and rear ends between the two layers to support and connect the two layers, and the beam 5, the stiffened wall plate 8 and the skin 4 form a torsion box, and the beam 5 has an edge strip 6 connected to the upper and lower sides, forming a C shape, and the end of the beam 5 located on the side of the stiffened wall plate 8 is provided with a butt strap 9 for connecting the front and rear beams of the wing box section, and the middle partition plate 3 is divided into front and rear parts, the front half of the middle partition plate 3 extends out of the skin 4 and the stiffened wall plate 8, and the rear half of the middle partition plate 3 is located between the skin 4 and the stiffened wall plate 8, and the rear half of the middle partition plate 3 is welded and fixed with the beam 5, the skin 4 and the stiffened wall plate 8, and the front half of the middle partition plate 3 is welded with the corresponding beam 5 in the middle, and the upper and lower ends of the front half of the middle partition plate 3 are welded and fixed with the upper and lower ends of the rear half of the middle partition plate 3.
[0032] The bottom surfaces of the two end joints 1 are connected to one side of the end partition plate 2, vertically extending outwards from the end partition plate 2, and the two end joints 1 are arranged at intervals, and the other side of the end partition plate 2 is connected to the skin 4 away from the middle partition plate 3.
[0033] A plurality of rib plates 7 are arranged on the skin 4, and the rib plates 7 are arranged in parallel between each other and in the front-rear direction. The rib plates 7 are connected to the end partition plate 2 and the middle partition plate 3 at both ends thereof.
[0034] Three weight-deduction holes are arranged on the beam 5 and the rib plates 7, and are used for weight-deduction of the test device, adjustment of the gravity center of the test device, and ensuring that the test device is in a 0-weight state.
[0035] An observation hole is arranged on the skin 4, and is used for observing the internal welds and ensuring the welding quality.
[0036] Two loading holes are arranged on each of the two end fittings 1, and are used for applying the wing-span load and the vertical load. One loading hole is arranged on each of the four corners of the end partition plate 2, and one loading hole is arranged on each of the upper and lower sides of the front half of the middle partition plate 3. The six loading holes are used for applying the heading load. One loading hole is arranged on each of the four corners of the rear half of the middle partition plate 3, and is used for applying the vertical load.
[0037] Weight-reduction holes are arranged on the end partition plate 2, the middle partition plate 3, the beam 5, and the skin 4.
[0038] The middle partition plate 3 divides the edge strip 6 into left and right parts.
[0039] In the test device, the thickness of the upper and lower layers of the skin 4 on the side away from the middle partition plate 3 is less than the thickness of the upper and lower layers of the stiffened wall plate 8 on the side away from the middle partition plate 3. The top edge and the bottom edge of the test device are arranged at an angle.
[0040] The two end fittings 1 and the end partition plate 2 are connected by 2*5, i.e. ten bolts. The two stiffened wall plates 8 and the middle partition plate 3 are connected by 2*10, i.e. twenty bolts. The two butt strips 9 and the two beams 5 are connected by ten bolts respectively. In addition to the above connections, the remaining connections are all welded.
[0041] During the test, the test device for applying wingtip load of full machine static test of the utility model is installed on the wing instead of the real wingtip structure, the front and rear butt joint belt plate 9 is connected with the front and rear beams of the wing box section, the upper and lower ribbed wall plates 8 are connected with the upper and lower wall plates at the wing end rib respectively, and all are connected by bolts. The three reserved weight holes are used for weight fastening, and the gravity center is adjusted to ensure that the test device is in 0 weight state. According to theoretical calculation, the tensile load is applied on the loading holes of the end joint 1, the middle partition plate 3 and the end partition plate 2 to complete the application of the wingtip load. The test device has a total of 14 loading holes, which are located on the end joint 1, the end partition plate 2 and the middle partition plate 3, wherein the end joint 1 has 4 (2 for each joint) with a radius of 15 mm, the end partition plate 2 has 4 with a radius of 15 mm, and the middle partition plate 3 has 6 with a radius of 15 mm. According to the requirement of full machine static test, the wingtip needs to apply the load along the wing span, the vertical load and the heading load, wherein the main force is the vertical load. The loading hole needs to be able to bear the load in the above-mentioned directions first, and at the same time, at least 2 loading points in the same direction should be provided to ensure the load pressure center position. The 2 end joints 1 are mainly used for applying the load along the wing span and the vertical load, the 4 ear holes on the middle partition plate 3 are used for applying the vertical load, and the front and rear ear holes of the end partition plate 2 and the middle partition plate 3 are used for applying the heading load. In addition, by applying different proportions of load at different loading points in the same direction, the total load and the load pressure center position can be ensured to be consistent with the real situation.
[0042] The above-mentioned sequence numbers of the embodiments of the present application are only for description, and do not represent the advantages and disadvantages of the embodiments.
[0043] In the above-mentioned embodiments of the present application, the description of each embodiment has its own emphasis, and the parts not described in detail in a certain embodiment can be referred to the related description of other embodiments.
[0044] In the several embodiments provided by the present application, it should be understood that the disclosed technology can be implemented in other ways. Of course, the device embodiment described above is only schematic. For example, the division of the units is only a logical function division. There can be another division during actual implementation. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. In addition, the displayed or discussed coupling or direct coupling or communication connection between each other can be indirect coupling or communication connection through some interface, unit or module, and can be electrical or other forms.
[0045] The units described as separate components can or can not be physically separate, and the components shown as units can or can not be physical units, that is, they can be located in one place, or they can be distributed on multiple units. According to actual needs, part or all of the units can be selected to achieve the purpose of the embodiment scheme.
[0046] The above description is merely illustrative of the preferred embodiments of this application and numerous modifications and adaptations will be apparent to those skilled in the art without departing from the principles of the application. It is thus intended that the scope of the application be determined by the appended claims and equivalents thereof.
[0047] It should be understood that the above description is intended for illustrating purposes only and is not intended to limit the application. Many embodiments and many applications other than those described herein will be readily apparent to those skilled in the art from this description. The scope of the application should, therefore, be determined not with reference to the above description, but should instead be determined with reference to the appended claims, along with the full scope of equivalents to which such claims are entitled. The disclosures of all articles and references, including patent applications and publications, are incorporated by reference for all purposes. The omission of any aspect of the subject matter disclosed herein is not a disclaimer of such subject matter, nor should it be construed as a disavowal of such subject matter unless it is expressly disclaimed.
Claims
1. A test apparatus for applying wingtip loads during a static test of an entire aircraft, characterized in that, Includes end diaphragms (2) and middle diaphragms (3); One side of the partition (3) is a skin (4) and the other side is a reinforced wall panel (8). Both the skin (4) and the reinforced wall panel (8) are two layers, and a beam (5) is set at the front and rear ends of the two layers to support and connect the upper and lower layers. The beam (5), the reinforced wall panel (8) and the skin (4) form a torsion box. The end of the beam (5) located on the side of the reinforced wall panel (8) is provided with a connecting strip plate (9). The partition (3) is divided into front and rear parts. The front half of the partition (3) extends out of the skin (4) and the reinforced wall panel (8), and the rear half of the partition (3) is located between the skin (4) and the reinforced wall panel (8). An end joint (1) is provided on one side of the end partition (2), and the other side of the end partition (2) is connected to the side of the skin (4) away from the middle partition (3); The end connector (1) is provided with two loading holes, the end partition (2) is provided with one loading hole at each of the four corners, the middle partition (3) is provided with one loading hole on each of the upper and lower sides of the front half, and the middle partition (3) is provided with one loading hole at each of the four corners of the rear half.
2. The test apparatus for applying wingtip loads in a static test of an entire aircraft according to claim 1, characterized in that, There are two end connectors (1), and the two end connectors (1) are spaced apart.
3. The test apparatus for applying wingtip loads in a static test of an entire aircraft according to claim 1, characterized in that, The upper and lower sides of the beam (5) are connected with flanges (6).
4. The test apparatus for applying wingtip loads in a static test of an entire aircraft according to claim 3, characterized in that, The middle partition (3) divides the flange (6) into left and right parts.
5. The test apparatus for applying wingtip loads in a static test of an entire aircraft according to claim 1, characterized in that, Multiple stiffeners (7) are provided on the skin (4). The multiple stiffeners (7) are arranged in parallel with each other and are arranged in parallel along the front and rear direction. The two ends of the stiffeners (7) are connected to the end partition (2) and the middle partition (3) respectively.
6. The test apparatus for applying wingtip loads in a static test of an entire aircraft according to claim 5, characterized in that, There are three buckle holes on the beam (5) and the stiffening plate (7).
7. The test apparatus for applying wingtip loads in a static test of an entire aircraft according to claim 1, characterized in that, An observation hole is provided on the skin (4).
8. The test apparatus for applying wingtip loads in a static test of an entire aircraft according to claim 1, characterized in that, Weight reduction holes are provided on the end diaphragm (2), middle diaphragm (3), beam (5) and skin (4).
9. The test apparatus for applying wingtip loads in a static test of an entire aircraft according to claim 1, characterized in that, The rear half of the partition plate (3) is welded and fixed to the beam (5), the skin (4) and the stiffened wall panel (8). The middle of the front half of the partition plate (3) is welded to the beam (5) at the corresponding position, and the upper and lower ends of the front half of the partition plate (3) are welded and fixed to the upper and lower ends of the rear half of the partition plate (3).
10. The test apparatus for applying wingtip loads in a static test of an entire aircraft according to claim 1, characterized in that, The thickness of the upper and lower layers of the skin (4) on the side away from the middle partition (3) is less than the thickness of the upper and lower layers of the stiffened wall panel (8) on the side away from the middle partition (3).