Wing simulation device

Abstract

A wing simulation device comprises: a main wing simulation member; an aileron simulation piece which is installed on the main wing simulation piece and comprises an upper wing surface and a lower wing surface which are opposite to each other; and the mounting part is arranged at the front edge of the aileron simulation piece and is provided with an upper surface and a lower surface which are opposite to each other. Wherein the aileron simulation piece further comprises at least one pressure measuring hole, and the pressure measuring holes are arranged to penetrate through the upper wing surface or the upper surface of the mounting part; the at least one butt joint hole is arranged to penetrate through the lower surface of the mounting part; and at least one pressure measuring pipeline, each of the pressure measuring pipelines is arranged in the aileron simulation piece and is connected with one of the at least one pressure measuring hole and the corresponding one of the at least one butt joint hole. According to the wing simulation device disclosed by the utility model, the phenomenon that a pressure measuring pipeline is inserted into a groove formed in the outer part of the aileron simulation piece is avoided, so that the influence on the aerodynamic shape of the aileron simulation piece is avoided, and the angle of the aileron simulation piece can be conveniently replaced.

Description

Technical Field

[0001] This utility model relates to the field of civil aircraft testing technology, specifically to a wing simulation device. Background Technology

[0002] Wind tunnel testing is the primary means of obtaining aerodynamic data for aircraft. Pressure wind tunnel testing, in particular, aims to measure the pressure distribution on the surfaces of various aircraft components, such as wings, fuselage, and control surfaces, providing crucial data input for the structural design and strength calculations of the aircraft and its components. Through pressure wind tunnel testing, typical aerodynamic characteristics such as the location of minimum pressure points on the aircraft surface, shock wave locations, and whether airflow separation occurs can be determined.

[0003] Currently, the main method for measuring the surface pressure distribution of wind tunnel test models is to install pressure measuring holes on the model surface. This involves transmitting the local surface pressure to a pressure sensor via these holes and connecting pipes. Generally, the pipes connect one end to a measuring hole on the model surface and the other end to the pressure measuring device. However, wind tunnel test components typically require scaling down the actual size of an aircraft to match the dimensions of the wind tunnel test section and the required blockage. For aircraft control surfaces, the scaled-down dimensions are significantly reduced, which increases the difficulty of designing the pressure measuring holes and connecting pipes.

[0004] Taking the aileron as an example, the aileron is a crucial control surface for aircraft roll maneuvers. For high-aspect-ratio civil aircraft, the aileron is typically located in the wingtip region, where the trailing edge thickness is usually around 10 millimeters. However, scaled down to the dimensions of current mainstream high-speed wind tunnel test sections in China, the trailing edge of the aileron on the test model is only 0.4 millimeters. Arranging pressure measurement pipelines in such a confined space presents immense challenges. As a result, only about 30% of the surface pressure coefficient of the aileron's leading edge can be measured, leaving 70% of the area without data. This significant data gap affects the accuracy of load calculations and assessments, impacting aircraft design safety.

[0005] Meanwhile, the arrangement of pressure measurement holes in the 30% area of ​​the aileron leading edge during the manufacturing of the test model was also quite cumbersome. The conventional approach is to drill pressure measurement holes on one side of the aileron surface, and slot the other side to accommodate the pressure measurement tube. One end of the tube is then connected to the pressure measurement hole on the aileron surface, and the other end to the pressure measuring device. The slotted aileron surface is filled with a special adhesive. This method results in significant surface profile errors on the slotted side of the aileron, limiting the pressure measurement holes to only one side of the aileron, and preventing the placement of pressure measurement holes on both sides of the aileron surface at the same location. Furthermore, this conventional approach involves inserting the aileron pressure measurement tube into the wing through an opening in the aileron nose. Changing the aileron angle by replacing different aileron parts requires reconnecting the pressure measurement tube each time the angle is changed, making the operation cumbersome.

[0006] Therefore, there is a need to propose an improved wing simulation device that can solve the problems and defects existing in the prior art. Utility Model Content

[0007] The purpose of this utility model is to provide a wing simulation device, which includes a main wing simulation component and an aileron simulation component. A pressure measuring tube is pre-arranged in the aileron simulation component. The pressure measuring tube is fluidly connected to the main wing simulation component by matching the docking holes of the main wing simulation component and the aileron simulation component, thus avoiding any impact on the aileron profile.

[0008] According to this utility model, a wing simulation device is proposed, comprising: a main wing simulation component; an aileron simulation component mounted to the main wing simulation component, and comprising: upper and lower wing surfaces opposite to each other; a mounting portion disposed at the leading edge of the aileron simulation component, having upper and lower surfaces opposite to each other. The aileron simulation component further comprises: at least one pressure measuring hole arranged to pass through the upper wing surface or the upper surface of the mounting portion; at least one docking hole arranged to pass through the lower surface of the mounting portion; and at least one pressure measuring line, each of which is disposed within the aileron simulation component and connects one of the at least one pressure measuring hole to a corresponding one of the at least one docking hole. With this arrangement, the pressure measuring holes are fluidly connected to the docking holes through the pressure measuring lines embedded in the aileron simulation component, avoiding the need for slotting and inserting pressure measuring lines on the outside of the aileron simulation component, thereby avoiding any impact on the aerodynamic shape of the aileron simulation component.

[0009] According to another aspect of this disclosure, the main wing simulator has a mating mounting portion, which has at least one mating docking hole corresponding to at least one docking hole of the aileron simulator. This allows for fluid communication of the pressure measuring port to the main wing simulator via the matching docking of the mating docking holes, avoiding the need to re-connect the pressure measuring lines due to changes in the angle of the aileron simulator.

[0010] According to another aspect of this disclosure, a sealing ring is provided on the upper surface of the mating mounting portion of the main wing simulator around each of at least one mating hole. When the main wing simulator and the aileron simulator are joined together, the sealing ring is clamped between the mating hole and its corresponding mating hole, thereby achieving a sealed connection between them and preventing insufficient airtightness from affecting the accuracy of the pressure test data.

[0011] According to another aspect of this disclosure, the aileron simulator has multiple mounting holes penetrating the upper and lower surfaces of the mounting portion, wherein the multiple mounting holes are arranged collinearly with at least one mating hole. Furthermore, the mating mounting portion of the main wing simulator has multiple mating mounting holes, each of which corresponds to each of the multiple mounting holes on the aileron simulator. This arrangement facilitates quick and accurate alignment of the mounting holes and mating holes with the mating mounting holes and mating mating holes on the main wing simulator, and also has aesthetic benefits.

[0012] According to another aspect of this disclosure, the lower surface of the mounting portion of the aileron simulator is abutted against the upper surface of the mating mounting portion of the main wing simulator, wherein at least one mating hole is aligned with at least one mating mating hole. The mating mounting portions, combined with sealing rings, ensure a sealing connection between the mating holes and the mating mating holes to the greatest extent possible.

[0013] According to another aspect of this disclosure, the aileron simulator and the main wing simulator are joined together using fasteners passing through mounting holes in the aileron simulator and mating mounting holes in the main wing simulator, wherein the fasteners include screws or rivets. This connection method provides a more secure attachment of the aileron simulator to the main wing simulator compared to adhesive bonding.

[0014] According to another aspect of this disclosure, the upper surface of the aileron simulator is flush with the upper surface of the mounting portion of the aileron simulator. Additionally, the portion of the lower surface of the aileron simulator located at the leading edge of the aileron simulator protrudes beyond the lower surface of the mounting portion of the aileron simulator. Correspondingly, the upper surface of the mounting portion of the main wing simulator is recessed relative to the upper surface of the main wing simulator, thereby making the wing simulation device, particularly at the junction of the main wing simulator and the aileron simulator, have a smooth surface without recesses, protrusions, or angles.

[0015] According to another aspect of this disclosure, the mounting portion of the aileron simulator extends beyond the length of the aileron simulator in the spanwise direction. Alternatively, it may be slightly shorter than the length of the aileron simulator, but the length of the mounting portion is not significantly shorter than the length of the aileron simulator. This results in a larger contact area between the mounting portion and the mating mounting portion of the main wing simulator, enabling a more secure connection between the main wing simulator and the aileron simulator.

[0016] This invention relates to an airfoil simulation device. The mounting surface of the aileron simulator has mating holes for connecting to the main wing simulator. Pressure testing lines are used within the aileron simulator to connect the pressure testing holes one-to-one with the corresponding mating holes. Furthermore, corresponding mating holes are provided on the corresponding mounting surface of the main wing simulator. By sealing and aligning the mating holes of the aileron simulator with those of the main wing simulator, fluid communication is achieved from the pressure testing holes to the pressure testing lines to the main wing simulator, allowing for pressure testing. This airfoil simulation device avoids slotting the pressure testing lines on the outside of the aileron simulator, thus helping to maintain the integrity of the aileron's profile. Furthermore, the prefabricated pressure testing lines and the sealed alignment of the mating holes of the aileron simulator and the main wing simulator eliminate the need to reconnect the pressure testing lines when replacing aileron parts, improving work efficiency.

[0017] This utility model summary is provided to introduce concepts in a simplified form, and these concepts will be further described in the following detailed description. This utility model summary is neither intended to identify key or essential features of the claimed subject matter, nor is it intended to limit the scope of the claimed subject matter. Other aspects and advantages of this utility model will become apparent from the following detailed description of the embodiments and the accompanying drawings. Attached Figure Description

[0018] To gain a more complete understanding of this disclosure, reference can be made to the following description of exemplary embodiments taken in conjunction with the accompanying drawings. The drawings are not intended to limit this disclosure to the specific embodiments depicted therein, and are not necessarily to scale. In the drawings:

[0019] Figure 1 This is a bottom view of the aileron simulator of the wing simulator according to a preferred embodiment of the present invention;

[0020] Figure 2 This is a top view of the aileron simulator of the wing simulator according to a preferred embodiment of the present invention;

[0021] Figure 3 This is a perspective 3D view of the aileron simulator, showing the connection relationship between the pressure measurement pipes of the pressure measurement port and the docking port;

[0022] Figure 4 A top view of a portion of the main wing simulation component of the wing simulation device according to a preferred embodiment of this utility model;

[0023] Figure 5 This is a top view of a part of a wing simulation device where the main wing simulator and the aileron simulator are joined together; and

[0024] Figure 6 yes Figure 5 A cross-sectional view taken along line AA of the wing simulation device.

[0025] List of reference numerals

[0026] 100 Wing Simulation Device

[0027] 1 Aileron Simulation Component

[0028] 101 Upper wing surface

[0029] 102 Lower wing surface

[0030] 103 Forefront

[0031] 3 Installation Department

[0032] 31 Upper surface

[0033] 32 Lower surface

[0034] 4 Pressure testing holes

[0035] 5. Connecting holes

[0036] 6. Pressure testing pipeline

[0037] 7 mounting holes

[0038] 2. Main wing simulation component

[0039] 201 Upper wing surface

[0040] 8. Pairing and mounting section

[0041] 81 Upper surface

[0042] 9 mating holes

[0043] 10 Sealing rings

[0044] 11 mating mounting holes

[0045] X-direction Detailed Implementation

[0046] The following description of specific embodiments of this utility model refers to the accompanying drawings, which illustrate particular embodiments in which the utility model can be practiced. The embodiments are intended to describe various aspects of the utility model in sufficient detail to enable those skilled in the art to practice it. Other embodiments and changes may be utilized without departing from the scope of the utility model. Therefore, the following description of specific embodiments should not be considered limiting. The scope of this utility model is defined only by the appended claims and the full scope of their equivalents. The same reference numerals are used throughout the drawings and specific embodiments to refer to the same or similar parts.

[0047] In this article, "front," "up," and "down" refer to the working position relative to the wing simulation device 100 (e.g., ...). Figure 6The relative orientation terminology used (as shown). Specifically, the forward component of the aileron simulator 1 is closer to the main wing simulator 2 than the aft component, and the upper component is as shown. Figure 6 The working position shown is above the component below. The spanwise direction X refers to the direction parallel to the direction extending from the wider wing root to the narrower wingtip of the main wing simulator 2. Figure 5 The example shown is from right to left.

[0048] The wing simulation device 100 includes an aileron simulation component 1 and a main wing simulation component 2, which are joined together by a matching mounting part 3 and a mating mounting part 8, as shown below. Figure 5 and Figure 6 As shown.

[0049] Figure 1 and Figure 2 The bottom and top views of the aileron simulator 1 of the preferred embodiment of the wing simulator 100 are schematically shown. As can be seen from the figures, the aileron simulator 1 generally includes: an upper wing surface 101 and a lower wing surface 102 that are opposite to each other; a mounting part 3 located at the leading edge 103 and having an upper surface 31 and a lower surface 32 that are opposite to each other, wherein the upper surface 31 and the upper wing surface 101 are coplanar; one or more pressure measuring holes 4; and one or more docking holes 5.

[0050] At least one pressure measuring hole 4 is distributed on the upper wing surface 101 of the aileron simulator 1 and the upper surface 31 of the mounting part 3, and is arranged to pass through the upper wing surface 101 but not through the lower wing surface 102, or pass through the upper surface 31 of the mounting part 3 but not through its lower surface 32. Figure 2 For clarity of view, only one pressure measuring hole 4 is schematically marked, but this does not mean that the aileron simulator 1 has only one pressure measuring hole 4.

[0051] At least one docking hole 5 is used to connect to the main wing simulator 2, so as Figure 1 It is arranged on the lower surface 32 of the mounting part 3 as shown, and passes through the lower surface 32 of the mounting part 3 but does not pass through its upper surface 31.

[0052] The number of pressure testing holes 4 and docking holes 5 are the same, so that they can be matched in pairs.

[0053] Figure 3The internal structure of the aileron simulator 1 is shown in perspective, specifically illustrating the correspondence between the pressure measuring port 4 and the docking port 5. Specifically, the aileron simulator 1 has at least one pressure measuring line 6 internally, and in this preferred embodiment, multiple pressure measuring lines 6. Each of these lines connects a pressure measuring port 4 to a docking port 5, enabling fluid communication between them. Thus, no pressure measuring lines are required externally for the aileron simulator 1, maintaining its complete and smooth aerodynamic shape. For clarity, Figure 3 Only one pressure testing line 6 is shown, along with a pressure testing hole 4 and a docking hole 5 connected to it.

[0054] Go to Figure 4 , Figure 4 The main wing simulator 2 of the wing simulator 100 is shown, which has a mating mounting part 8, and the mating mounting part 8 is provided with mating docking holes 9 corresponding to the docking holes 5 of the aileron simulator 1. The number and distribution position of the mating docking holes 9 correspond to the docking holes 5.

[0055] Figure 6 The diagram illustrates the mating relationship between the mating holes 5 and the mating holes 9 when the main wing simulator 2 and the aileron simulator 1 are joined together. As shown, the lower surface 32 of the mounting portion 3 of the aileron simulator 1 abuts against the upper surface 81 of the mating mounting portion 8 of the main wing simulator 2, and each of at least one mating hole 5 is aligned with a corresponding one of at least one mating hole 9. Preferably, as... Figure 4 As shown, the mating mounting part 8 of the main wing simulator 2 has a sealing ring 10 arranged around each mating docking hole 9 on its upper surface 81. This sealing ring 10 is pressed between the docking holes 5 of the aileron simulator 1 and 9 of the main wing simulator 2 when they are aligned, thus achieving a sealed connection. In this way, the pressure testing hole 4 of the aileron simulator 1 is fluidly connected to the main wing simulator 2 via the pressure testing line 6, the docking hole 5, and the mating docking hole 9, facilitating subsequent pressure testing.

[0056] To ensure secure installation onto the main wing simulator 2, such as Figure 1 and Figure 2 As shown, the aileron simulator 1 has multiple mounting holes 7 that penetrate the upper surface 31 and lower surface 32 of the mounting portion 3. Correspondingly, the main wing simulator 2 is as follows... Figure 4 The mating mounting section 8 also has multiple mating mounting holes 11. When the aileron simulator 1 and the main wing simulator 2 are engaged, fasteners such as screws and rivets are used to fasten the aileron simulator 1 to the main wing simulator through the mounting holes 7 and the mating mounting holes 11.

[0057] Better, such as Figure 1As shown, the multiple mounting holes 7 of the aileron simulator 1 are arranged collinearly with at least one mating hole 5 to facilitate alignment and engagement with the corresponding mating mounting holes 11 and mating mating holes 9 of the main wing simulator 2.

[0058] Preferably, the upper wing surface 101 of the aileron simulator 1 is flush with the upper surface of its mounting portion 3, while the portion of the lower wing surface 102 at the leading edge 103 of the aileron simulator 1 protrudes from the lower surface 32 of the mounting portion 3, forming a stepped portion. Correspondingly, the upper surface 81 of the mating mounting portion 8 of the main wing simulator 2 is recessed relative to the upper wing surface 201 of the main wing simulator 2. Thus, when the main wing simulator 2 and the aileron simulator 1 are... Figure 6 When joined together, the resulting wing simulation device 100 has a smooth surface, especially at the joint of the main wing simulation 2 and the aileron simulation 1, where there are no bends, protrusions or depressions.

[0059] Additionally, the mounting part 3 of the aileron simulator 1 is as follows: Figure 1 The length shown extends along the spanwise direction X past the aileron simulator 1, or approximately past the length of the aileron simulator 1. This arrangement ensures that the contact area between the mounting portion 3 and the mating mounting portion 8 of the main wing simulator 2 is large enough to guarantee a secure connection between the main wing simulator 2 and the aileron simulator 1.

[0060] The wing simulation device of this invention embeds the pressure measurement pipeline inside the aileron simulator and uses matching docking holes and mating docking holes to fluidly connect the pressure measurement holes of the aileron simulator to the main wing simulator, facilitating subsequent pressure measurement tests. This avoids the need to slot the pressure measurement pipeline on the aileron simulator, solving the problem in the prior art where the pressure measurement pipeline affects or damages the aerodynamic shape of the aileron simulator. In addition, the matching docking holes and mating docking holes, and the fact that the pressure measurement pipeline is completely located inside the aileron, ensure that the replacement of aileron parts will not affect the wiring of the pressure measurement pipeline, solving the problem in the prior art where changing the angle of the aileron simulator requires readjusting and reconnecting the pressure measurement pipeline.

[0061] As used herein, the terms “comprising,” “including,” “having,” or any other variation thereof are intended to cover non-exclusive inclusion. For example, a method, article, or apparatus that includes a list of elements is not necessarily limited to those elements and may also include other elements not expressly listed or inherent to the method, article, or apparatus.

[0062] This utility model is not limited to the above embodiments, which are merely illustrative and not restrictive. Those skilled in the art, under the guidance of this utility model, can make any possible changes and modifications without departing from the spirit and scope of the claims. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of this utility model, without departing from its scope of protection, fall within the scope defined by the claims.

Claims

1. A wing simulation device, the wing comprising: a main wing simulation piece; an aileron simulation piece mounted to the main wing simulation piece and comprising: upper and lower wings surfaces opposite to each other; a mounting portion provided at a leading edge of the aileron simulation piece, having upper and lower surfaces opposite to each other, characterized in that the aileron simulation piece further comprises: at least one pressure tap hole arranged to pass through the upper wing surface or the upper surface of the mounting portion; at least one docking hole arranged to pass through the lower surface of the mounting portion; and at least one pressure tubing line, each of the at least one pressure tubing line routed within the aileron simulation piece and connecting one of the at least one pressure tap hole with a corresponding one of the at least one docking hole.

2. The wing simulation device of claim 1, wherein, the main wing simulation piece has a counterpart mounting portion provided with at least one counterpart docking hole corresponding to the at least one docking hole of the aileron simulation piece.

3. The wing simulation device of claim 2, wherein, the counterpart mounting portion of the main wing simulation piece is provided with a sealing ring around an upper surface thereof about each of the at least one counterpart docking hole.

4. The wing simulation device of claim 3, wherein, the aileron simulation piece is provided with a plurality of mounting holes penetrating the upper and lower surfaces of the mounting portion, wherein the plurality of mounting holes are arranged collinearly with the at least one docking hole.

5. The wing simulation apparatus according to any one of claims 2 to 4, characterized by a lower surface of the mounting portion of the aileron simulation piece is in abutment with an upper surface of the counterpart mounting portion of the main wing simulation piece, wherein the at least one docking hole is aligned with the at least one counterpart docking hole two by two.

6. The wing simulation apparatus of claim 4, wherein the counterpart mounting portion of the main wing simulation piece is provided with a plurality of counterpart mounting holes, each of the plurality of counterpart mounting holes corresponding to each of the plurality of mounting holes of the aileron simulation piece.

7. The wing simulation apparatus according to claim 6, characterized by the aileron simulation piece is engaged with the main wing simulation piece using fasteners passing through the mounting holes of the aileron simulation piece and the counterpart mounting holes of the main wing simulation piece, wherein the fasteners comprise screws or rivets.

8. The wing simulation device of claim 1, wherein, the upper wing surface of the aileron simulation piece is flush with the upper surface of the mounting portion of the aileron simulation piece.

9. The wing simulation apparatus of claim 1, wherein a portion of the lower wing surface of the aileron simulation piece at the leading edge of the aileron simulation piece protrudes from the lower surface of the mounting portion of the aileron simulation piece.

10. The wing simulation device of claim 1, wherein, the mounting portion of the aileron simulation piece extends along a spanwise direction over a length of the aileron simulation piece.

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