Aircraft leading edge structure test piece thermal insulation performance test system and test method

Abstract

The present disclosure provides a kind of aircraft leading edge structure test piece thermal insulation performance test system and test method, it is related to aircraft performance test field.The test system includes test piece, heat insulation box, temperature measuring component and temperature measuring component, test piece includes fixed surface, first airfoil and second airfoil connected in order, the outer surface and inner surface of the connecting area of first airfoil and second airfoil are respectively provided with first control point and fourth control point, the outer surface and inner surface of first airfoil are respectively provided with second control point and fifth control point, the outer surface and inner surface of second airfoil are respectively provided with third control point and sixth control point;Test piece is located in heat insulation box;Heating device includes multiple heating components distributed at intervals around first airfoil and second airfoil;Temperature measuring component includes multiple temperature sensors, each temperature sensor is one-to-one corresponding test first control point, second control point, third control point, fourth control point, fifth control point and the temperature of sixth control point.

Description

Technical Field

[0001] This disclosure relates to the field of aircraft performance testing technology, and more specifically, to a testing system and method for testing the thermal insulation performance of an aircraft leading edge structure test piece. Background Technology

[0002] The leading-edge structure of an aircraft is primarily used for thermal protection in the high-temperature region of hypersonic vehicles, playing a crucial role in ensuring flight safety and improving the overall performance of the aircraft. To develop a reasonable and effective thermal protection design scheme, it is urgent to conduct thermal insulation performance tests on the leading-edge structure of the aircraft to evaluate its thermal insulation performance.

[0003] It should be noted that the information disclosed in the background section above is only used to enhance the understanding of the background of this disclosure, and therefore may include information that does not constitute prior art known to those skilled in the art. Summary of the Invention

[0004] This disclosure provides a test system and method for testing the thermal insulation performance of an aircraft leading edge structure test piece, which can evaluate the thermal insulation performance of the aircraft leading edge structure and provide data support for the structural design of the leading edge structure.

[0005] According to one aspect of this disclosure, a system for testing the thermal insulation performance of an aircraft leading-edge structure test piece is provided, comprising:

[0006] The test specimen includes a fixed surface, a first wing surface, and a second wing surface. The fixed surface has a first side and a second side surface that are distributed opposite to each other. One end of the first wing surface is connected to the first side surface, and one end of the second wing surface is connected to the second side surface. The end of the first wing surface away from the first side surface is connected to the end of the second wing surface away from the second side surface. A first control point is provided on the outer surface of the connection area between the first wing surface and the second wing surface. A second control point is provided on the outer surface of the first wing surface. A third control point is provided on the outer surface of the second wing surface. A fourth control point is provided on the inner surface of the connection area between the first wing surface and the second wing surface, and the fourth control point is directly opposite to the first control point. A fifth control point is provided on the inner surface of the first wing surface, and the fifth control point is directly opposite to the second control point. A sixth control point is provided on the inner surface of the second wing surface, and the sixth control point is directly opposite to the third control point.

[0007] An insulation chamber, wherein the test specimen is placed inside the insulation chamber, and the fixing surface faces the side wall of the insulation chamber;

[0008] The heating device includes a plurality of heating components spaced apart around the first wing surface and the second wing surface;

[0009] The temperature measurement component includes multiple temperature sensors, each of which measures the temperature of the first control point, the second control point, the third control point, the fourth control point, the fifth control point, and the sixth control point.

[0010] In one exemplary embodiment of this disclosure, the test piece further includes front wall stiffeners disposed on the fixed surface, and the testing system further includes:

[0011] The fixed double ears include a fixing rod and a fixing part. The fixing part is located at one end of the fixing rod. The fixing rod is detachably connected to the side wall of the insulation box, and the fixing part is detachably connected to the front wall rib.

[0012] In one exemplary embodiment of this disclosure, the fixing part includes a boss, a first ear, and a second ear. The boss is connected to the fixing rod. The first ear and the second ear are both located on the side of the boss away from the fixing rod, and the first ear and the second ear are arranged in parallel and spaced apart. The first ear has a first threaded hole, and the second ear has a second threaded hole. The first threaded hole and the second threaded hole are directly opposite each other, and the front wall rib can extend into the space between the first ear and the second ear.

[0013] The testing system further includes a first fastener and a second fastener, wherein the first fastener can pass through the first threaded hole and press against the front wall rib; and the second fastener can pass through the second threaded hole and press against the front wall rib.

[0014] In one exemplary embodiment of this disclosure, the testing system further includes:

[0015] The first heat insulation pad is located between the first fastener and the front wall rib;

[0016] The second heat insulation pad is located between the second fastener and the front wall reinforcement strip.

[0017] In one exemplary embodiment of this disclosure, both the first fastener and the second fastener are bolts.

[0018] In one exemplary embodiment of this disclosure, the outer periphery of the fixing rod is threaded, and the testing system further includes:

[0019] The first fixing member is sleeved on the outer periphery of the fixing rod and located on the inner wall of the insulation box near the test piece. The first fixing member is provided with internal threads.

[0020] The second fixing member is sleeved on the outer periphery of the fixing rod and located on the outer wall of the insulation box away from the test piece. The second fixing member has an internal thread, and rotating the first fixing member and the second fixing member can fix the fixing rod to the insulation box.

[0021] In one exemplary embodiment of this disclosure, the testing system further includes:

[0022] Insulating cotton is used to fill the gap between the fixed surface and the insulation box.

[0023] According to one aspect of this disclosure, a method for testing the thermal insulation performance of an aircraft leading-edge structure test specimen is provided, comprising conducting thermal insulation performance testing using the thermal insulation performance testing system for aircraft leading-edge structure test specimens described in any one of the above claims.

[0024] In one exemplary embodiment of this disclosure, the testing method includes:

[0025] The first control point is heated to a first preset temperature, the second control point is heated to a second preset temperature, and the third control point is heated to a third preset temperature.

[0026] The temperature values ​​of the fourth control point, the fifth control point, and the sixth control point are detected;

[0027] When the temperature at the fourth control point is less than the first threshold, it is determined that the thermal insulation of the connection area between the first wing and the second wing meets the requirements; when the temperature at the fifth control point is less than the second threshold, it is determined that the thermal insulation of the first wing meets the requirements; when the temperature at the sixth control point is less than the third threshold, it is determined that the thermal insulation of the second wing meets the requirements.

[0028] In one exemplary embodiment of this disclosure, the first preset temperature is 800℃~1400℃, the second preset temperature is 350℃~550℃, and the third preset temperature is 450℃~700℃; the first threshold is 100℃~150℃, the second threshold is 50℃~70℃, and the third threshold is 40℃~60℃.

[0029] The disclosed test system and method for testing the thermal insulation performance of aircraft leading edge structure test specimens can fix the test specimen in an insulated chamber and heat the first, second, and third control points through a heating component. At the same time, the temperature of the fourth, fifth, and sixth control points can be detected. The thermal insulation performance of the connection area between the first and second wing surfaces can be determined by the temperature of the fourth control point, the thermal insulation performance of the first wing surface can be determined by the temperature of the fifth control point, and the thermal insulation performance of the second wing surface can be determined by the temperature of the sixth control point, thereby providing data support for the design of the leading edge structure.

[0030] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and are not intended to limit this disclosure. Attached Figure Description

[0031] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this disclosure and, together with the description, serve to explain the principles of this disclosure. It is obvious that the drawings described below are merely some embodiments of this disclosure, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort.

[0032] Figure 1 This is a schematic diagram of the thermal insulation performance testing system for the leading edge structure test piece of an aircraft in this embodiment of the present disclosure.

[0033] Figure 2 This is a schematic diagram of the assembly of the test specimen and the insulation box in an embodiment of this disclosure.

[0034] Figure 3 This is a top view of the insulation box and test specimen in an embodiment of this disclosure.

[0035] Figure 4 This is a schematic diagram illustrating the connection between the fixed double ears and the front wall reinforcement strip in an embodiment of this disclosure.

[0036] Figure 5 This is a schematic diagram of the temperature loading spectrum in an embodiment of this disclosure.

[0037] In the figure: 1. Test piece; 11. Fixed surface; 12. First wing surface; 13. First control point; 14. Second control point; 15. Front wall rib; 2. Insulation box; 21. Outer shell; 22. First insulation wall; 23. Second insulation wall; 24. Third insulation wall; 3. Heating device; 31. Heating assembly; 4. Fixed double ears; 41. Fixed rod; 42. Fixed part; 421. Boss; 422. First ear; 423. Second ear; 51. First fastener; 52. Second fastener; 61. First heat insulation pad; 62. Second heat insulation pad; 71. First fastener; 72. Second fastener; 8. Fixed block. Detailed Implementation

[0038] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, they are provided so that this disclosure will be thorough and complete, and will fully convey the concept of the exemplary embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and therefore their detailed description will be omitted.

[0039] Although relative terms such as "up" and "down" are used in this specification to describe the relative relationship of one component of an icon to another, these terms are used only for convenience, such as according to the orientation of the examples shown in the accompanying drawings. It is understood that if the device of the icon is flipped upside down, the component described as "up" will become the component described as "down." When a structure is "up" of another structure, it may mean that the structure is integrally formed on the other structure, or that the structure is "directly" mounted on the other structure, or that the structure is "indirectly" mounted on the other structure through another structure.

[0040] The terms “a,” “one,” “the,” and “the” are used to indicate the existence of one or more elements / components / etc.; the terms “including” and “having” are used to indicate an open-ended inclusion and that other elements / components / etc. may exist in addition to those listed. The terms “first,” “second,”…“sixth” are used only as markers and are not a limitation on the number of objects.

[0041] This disclosure provides a system for testing the thermal insulation performance of an aircraft leading-edge structure test piece, such as... Figures 1-3 As shown, the testing system may include a test specimen 1, an insulation chamber 2, a heating device 3, and a temperature measuring component, wherein:

[0042] Test piece 1 includes a fixed surface 11, a first wing surface 12, and a second wing surface (not shown in the figure). The fixed surface 11 has a first side and a second side that are distributed opposite to each other. One end of the first wing surface 12 is connected to the first side, and one end of the second wing surface is connected to the second side. The end of the first wing surface 12 away from the first side is connected to the end of the second wing surface away from the second side. A first control point 13 is provided on the outer surface of the connection area between the first wing surface 12 and the second wing surface. A second control point 14 is provided on the outer surface of the first wing surface 12. A third control point is provided on the outer surface of the second wing surface. A fourth control point is provided on the inner surface of the connection area between the first wing surface 12 and the second wing surface. The fourth control point is directly opposite to the first control point 13. A fifth control point is provided on the inner surface of the first wing surface 12. The fifth control point is directly opposite to the second control point 14. A sixth control point is provided on the inner surface of the second wing surface. The sixth control point is directly opposite to the third control point.

[0043] Test specimen 1 is placed inside insulation box 2, with the fixing surface 11 facing the side wall of insulation box 2;

[0044] The heating device 3 includes a plurality of heating components 31 that are spaced apart around the first wing surface 12 and the second wing surface;

[0045] The temperature measurement component includes multiple temperature sensors, each corresponding to test the temperature of the first control point 13, the second control point 14, the third control point, the fourth control point, the fifth control point, and the sixth control point.

[0046] The disclosed aircraft leading edge structure test specimen thermal insulation performance testing system can fix the test specimen 1 in an insulation box 2 and heat the first control point 13, the second control point 14 and the third control point through the heating component 31. At the same time, the temperature of the fourth control point, the fifth control point and the sixth control point can be detected. The thermal insulation performance of the connection area between the first wing surface 12 and the second wing surface is judged by the temperature of the fourth control point, the thermal insulation performance of the first wing surface 12 is judged by the temperature of the fifth control point, and the thermal insulation performance of the second wing surface is judged by the temperature of the sixth control point, thereby providing data support for the design of the leading edge structure.

[0047] The following is a detailed description of each part of the thermal insulation performance testing system for the aircraft leading edge structure test piece in this embodiment:

[0048] like Figure 1 and Figure 2 As shown, the test piece 1 may include a fixed surface 11, a first wing surface 12, and a second wing surface. The fixed surface 11 may be a plane, having a first side and a second side surface that are relatively distributed. The first wing surface 12 may be a curved surface, and one end of the first wing surface 12 may be connected to the first side surface of the fixed surface 11. The second wing surface may also be a curved surface, and one end of the second wing surface may be connected to the second side surface of the fixed surface 11. In addition, the end of the first wing surface 12 away from the first side surface may be connected to the end of the second wing surface away from the second side surface. In some embodiments of this disclosure, the fixed surface 11, the first wing surface 12, and the second wing surface may be an integral structure, and the fixed surface 11, the first wing surface 12, and the second wing surface may be connected end to end in sequence.

[0049] For the leading edge structure of the aircraft, the temperature is highest at the leading edge stagnation point, and decreases smoothly towards the rear end along the chord. To reduce the overall temperature error of the test piece 1, the temperature control points can all be selected at the middle part of the test piece 1. In some embodiments of this disclosure, multiple control points can be provided on the test piece 1. At least one control point can be provided on the first wing surface 12, the second wing surface, and the connection area between the first wing surface 12 and the second wing surface, so as to study the thermal insulation performance of different areas of the test piece 1 separately.

[0050] like Figure 1 and Figure 3 As shown, a first control point 13 may be provided on the outer surface of the connection area between the first wing surface 12 and the second wing surface. The first control point 13 may be located at the middle part of the length direction of the connection area between the first wing surface 12 and the second wing surface. For example, the first control point 13 may be the leading edge stagnation point of the leading edge structure; please continue to see Figure 1 and Figure 3 As shown, the outer surface of the first wing surface 12 is provided with a second control point 14, which may be located in the central region of the first wing surface 12; the outer surface of the second wing surface is provided with a third control point (not shown in the figure), which may be located in the central region of the second wing surface. The inner surface of the middle portion of the connection area between the first wing surface 12 and the second wing surface is provided with a fourth control point, which may be directly opposite the first control point 13; the central region of the inner surface of the first wing surface 12 is provided with a fifth control point, which may be directly opposite the second control point 14; the central region of the inner surface of the second wing surface is provided with a sixth control point, which may be directly opposite the third control point.

[0051] Please continue reading Figures 1-3 As shown, the insulation box 2 is a box body, which may include at least a bottom wall, a first insulation wall 22, a second insulation wall 23, and a third insulation wall 24. The bottom wall, the first insulation wall 22, the second insulation wall 23, and the third insulation wall 24 may all be flat. The first insulation wall 22, the second insulation wall 23, and the third insulation wall 24 may all be perpendicular to the bottom wall. The first insulation wall 22 and the second insulation wall 23 may be parallel to each other. The third insulation wall 24 may be connected between the first insulation wall 22 and the second insulation wall 23. In some embodiments of this disclosure, an outer shell 21 is also provided on the outside of the insulation walls, which can isolate each insulation wall from the external airflow.

[0052] Test specimen 1 can be placed inside the insulation chamber 2, such as Figure 2 As shown, the fixing surface 11 of the test piece 1 can face the side wall of the insulation box 2 (e.g., the third insulation wall 24). For example, fixing blocks 8 can be installed at both ends of the test piece 1 along its length, and the test piece 1 can be secured between the two fixing blocks 8. Then, the fixing blocks 8 and the test piece 1 can be placed together in the insulation box 2. At this time, the two fixing blocks 8 are tightly engaged with the first insulation wall 22 and the second insulation wall 23 respectively, thereby fixing the test piece 1 along its length.

[0053] In one exemplary embodiment of this disclosure, the fixing surface 11 of the test piece 1 may face the third insulating wall 24 of the insulating box 2. Please continue to refer to... Figure 2 As shown, the test piece 1 may also include a front wall rib 15, which may be provided on the fixed surface 11. For example, the front wall rib 15 may be a sheet-like protrusion provided on the fixed surface 11, and the front wall rib 15 and the fixed surface 11 are integrally formed.

[0054] Please continue reading Figure 2As shown, the thermal insulation performance testing system for the leading edge structure test specimen of the aircraft disclosed herein may further include fixed double ears 4. The fixed double ears 4 may include a fixed rod 41 and a fixed part 42. The fixed rod 41 may be rod-shaped, and its outer periphery may be threaded; for example, the fixed rod 41 may be a threaded rod. The fixed rod 41 may pass through the side wall of the insulation chamber 2 and be detachably connected to the side wall of the insulation chamber 2. For example, the fixed rod 41 may pass through the third insulation wall 24 and the outer shell 21, and be detachably connected to both the third insulation wall 24 and the outer shell 21; that is, one end of the fixed rod 41 is located inside the insulation chamber 2. The fixed part 42 may be located at one end of the fixed rod 41 and may be fixedly connected to the end of the fixed rod 41. For example, the fixed part 42 may be located on the end of the fixed rod 41 located inside the test chamber.

[0055] In one exemplary embodiment of this disclosure, such as Figure 4 As shown, the thermal insulation performance testing system for the leading edge structure test specimen of this disclosure may further include a first fixing member 71 and a second fixing member 72. The first fixing member 71 can be sleeved on the outer periphery of the fixing rod 41, and is located on the inner wall of the insulation chamber 2 near the test specimen 1. The first fixing member 71 may have internal threads, and can be threadedly connected to the fixing rod 41. The second fixing member 72 can also be sleeved on the outer periphery of the fixing rod 41, and is located on the outer wall of the insulation chamber 2 away from the test specimen 1. The second fixing member 72 may have internal threads, and can be threadedly connected to the fixing rod 41. Rotating the first fixing member 71 and the second fixing member 72 can fix the fixing rod 41 to the side wall of the insulation chamber 2 (e.g., the third insulation wall 24 and the shell 21). For example, both the first fixing member 71 and the second fixing member 72 can be nuts.

[0056] In one exemplary embodiment of this disclosure, the fixing part 42 can be detachably connected to the front wall rib 15. Please continue to see Figure 4 As shown, the fixing part 42 may include a boss 421, a first ear 422, and a second ear 423. The boss 421 may be block-shaped, and its cross-section may be circular, elliptical, rectangular, or irregular in shape, without any particular limitation. The boss 421 may be connected to the fixing rod 41. The first ear 422 and the second ear 423 are both located on the side of the boss 421 away from the fixing rod 41. The first ear 422 and the second ear 423 may both be plate-shaped, and the first ear 422 and the second ear 423 may be arranged in parallel and spaced apart along a direction perpendicular to the central axis of the fixing rod 41.

[0057] A first threaded hole (not shown in the figure) may be provided on the first ear portion 422, and the first threaded hole may penetrate the first ear portion 422 along the thickness direction of the first ear portion 422; a second threaded hole (not shown in the figure) may be provided on the second ear portion 423, and the second threaded hole may penetrate the second ear portion 423 along the thickness direction of the second ear portion 423. The first threaded hole and the second threaded hole may be arranged opposite each other, and the front wall rib 15 may extend into the space between the first ear portion 422 and the second ear portion 423.

[0058] In one exemplary embodiment of this disclosure, the fixing rod 41, the boss 421, the first ear 422, and the second ear 423 can all be made of metal, alloy, or stainless steel. The fixing rod 41, the boss 421, the first ear 422, and the second ear 423 can be an integral structure.

[0059] Please continue reading Figure 4 As shown, the thermal insulation performance testing system for the aircraft leading edge structure test piece disclosed herein may further include a first fastener 51 and a second fastener 52. Both the first fastener 51 and the second fastener 52 may be strip-shaped, and both the first fastener 51 and the second fastener 52 may have threads on their outer periphery. The materials of the first fastener 51 and the second fastener 52 may be metal, alloy, or stainless steel, etc. For example, both the first fastener 51 and the second fastener 52 may be bolts.

[0060] The first locking member 51 can pass through the first threaded hole, and rotating the first locking member 51 can tighten the front wall rib 15; the second locking member 52 can pass through the second threaded hole, and rotating the second locking member 52 can tighten the front wall rib 15, thus fixing the front wall rib 15 between the first locking member 51 and the second locking member 52.

[0061] In one exemplary embodiment of this disclosure, the number of first threaded holes, second threaded holes, first fasteners 51, and second fasteners 52 can all be multiple, and the number of first threaded holes is equal to the number of first fasteners 51. Each first fastener 51 can pass through each corresponding first threaded hole and respectively tighten against the front wall rib 15. Simultaneously, the number of second threaded holes is equal to the number of second fasteners 52, and each second fastener 52 can pass through each corresponding second threaded hole and respectively tighten against the front wall rib 15. The arrangement of multiple first fasteners 51 and multiple second fasteners 52 can enhance the fixing effect on the front wall rib 15, preventing the accuracy of the test results from being affected by the movement of the test piece 1 during the test.

[0062] In one exemplary embodiment of this disclosure, please continue to refer to Figure 4As shown, the thermal insulation performance testing system for the leading edge structure test specimen of this disclosure may further include a first thermal insulation pad 61 and a second thermal insulation pad 62. The first thermal insulation pad 61 may be sheet-like, and its shape may be circular, rectangular, elliptical, polygonal, or irregular. Its material may be asbestos, rock wool, or fiberglass, etc. No specific limitations are made on the shape and material of the first thermal insulation pad 61. The first thermal insulation pad 61 may be located between the first fastener 51 and the front wall rib 15. By setting the first thermal insulation pad 61, heat in the test specimen 1 can be prevented from diffusing through the first fastener 51 and the fixed double ears 4 during the test, which helps to realistically simulate the thermal environment of the leading edge structure and ensure the stability of the test conditions.

[0063] The second heat insulation pad 62 may be sheet-like, and its shape may be circular, rectangular, elliptical, polygonal, or irregular. Its material may be asbestos, rock wool, or fiberglass, etc. No special limitations are placed on the shape and material of the second heat insulation pad 62. The second heat insulation pad 62 may be located between the second fastener 52 and the front wall rib 15. By setting the second heat insulation pad 62, heat in the test specimen 1 can be prevented from diffusing through the second fastener 52 and the fixing lugs 4 during the test, thereby further improving the stability of the test conditions. The materials of the first heat insulation pad 61 and the second heat insulation pad 62 may be the same or different, and no special limitations are placed on this.

[0064] In one exemplary embodiment of this disclosure, there may be multiple front wall ribs 15, each of which can be disposed on the fixing surface 11 and can be spaced apart along the length of the test specimen 1. Correspondingly, there may also be multiple fixing lugs 4, which can be fixed one-to-one with each front wall rib 15.

[0065] In one exemplary embodiment of this disclosure, the thermal insulation performance testing system for the leading edge structure test piece of the aircraft may further include thermal insulation cotton (not shown in the figure). The thermal insulation cotton can fill the gap between the fixed surface 11 and the thermal insulation box 2. The thermal insulation cotton can prevent external cold air from diffusing into the thermal insulation box 2, thereby avoiding the influence of external airflow on the test process and causing measurement errors, which in turn affect the accuracy of the test data.

[0066] Please continue reading Figure 1 As shown, the heating device 3 may include multiple heating components 31, which may surround the first wing surface 12 and the second wing surface and be evenly spaced on the outer periphery of the first wing surface 12 and the second wing surface. The heating components 31 may be strip-shaped, and the multiple heating components 31 may be distributed in parallel. For example, the heating component 31 may be a quartz lamp.

[0067] The quartz lamp heating can be controlled by an MTS-Complex Coordination Control System to ensure that each area of ​​the test piece 1 reaches a preset temperature. During this process, the DC voltage across the heating units of the quartz lamp group can be adjusted to increase its operating power, allowing the surface temperature of the test piece 1 to rapidly reach the preset value through thermal radiation. The quartz lamp in this disclosure can consist of a quartz heating lamp tube, a lamp tube support, and an outer cover. The quartz heating lamp tube group can serve as a thermal radiation source. The rated voltage of the quartz heating lamp tube can be 220V, and the rated power can be 4.3kW. This quartz heating lamp tube has low thermal inertia and can reach 80% of its rated power in about 1 second, exhibiting rapid heating and cooling.

[0068] The temperature measurement assembly (not shown in the figure) may include multiple temperature sensors, the number of which is equal to the number of control points. For example, if there are 6 control points, there can also be 6 temperature sensors. Each temperature sensor can measure the temperature of the first control point 13, the second control point 14, the third control point, the fourth control point, the fifth control point, and the sixth control point.

[0069] During the experiment, the temperature of the first control point 13 can be monitored by a temperature sensor corresponding to the first control point 13, the temperature of the second control point 14 can be monitored by a temperature sensor corresponding to the second control point 14, and the temperature of the third control point can be monitored by a temperature sensor corresponding to the third control point, so as to accurately control the heating temperature of the first control point 13, the second control point 14, and the third control point. After the first control point 13, the second control point 14, and the third control point all reach the preset temperature, the temperature of the fourth control point can be detected by a temperature sensor corresponding to the fourth control point, the temperature of the fifth control point can be detected by a temperature sensor corresponding to the fifth control point, and the temperature of the sixth control point can be detected by a temperature sensor corresponding to the sixth control point, thereby providing data support for the design of the leading edge structure.

[0070] This disclosure also provides a method for testing the thermal insulation performance of an aircraft leading-edge structure test specimen. This method uses the aircraft leading-edge structure test specimen thermal insulation performance testing system in any of the above embodiments to test the thermal insulation performance of the leading-edge structure.

[0071] In one exemplary embodiment of this disclosure, the method for testing the thermal insulation performance of an aircraft leading edge structure test piece may include steps S110-S130, wherein:

[0072] Step S110: Heat the first control point 13 to a first preset temperature, heat the second control point 14 to a second preset temperature, and heat the third control point to a third preset temperature.

[0073] Because the temperature is highest at the leading-edge stagnation point of the leading-edge structure during aircraft operation, the highest temperature is applied to the leading-edge stagnation point (i.e., the first control point 13) during the test. The temperatures in other areas (e.g., the first wing surface 12 and the second wing surface) are slightly lower. Furthermore, due to the different environments experienced by different wing surfaces during operation, the temperatures they withstand also differ. Therefore, the operating temperatures of the second control point 14 in the first wing surface 12 and the third control point in the second wing surface are also different. For example, the first preset temperature corresponding to the first control point 13 can be 800℃ to 1400℃, for example, it can be 800℃, 1000℃, 1200℃, or 1400℃, or other temperatures, without special limitation. The second preset temperature corresponding to the second control point 14 can be 350℃ to 550℃, for example, it can be 350℃, 400℃, 450℃, 500℃, or 550℃, or other temperatures, without special limitation. The third preset temperature corresponding to the third control point can be 450℃ to 700℃. For example, it can be 450℃, 500℃, 550℃, 600℃, 650℃ or 700℃. Of course, it can also be other temperatures, which are not specifically limited here.

[0074] The test piece 1 can be heated by the heating component 31. During this process, the temperature of the first control point 13, the second control point 14 and the third control point can be monitored by the temperature sensor so as to accurately control the temperature of the first control point 13, the second control point 14 and the third control point.

[0075] Step S120: Detect the temperature values ​​of the fourth control point, the fifth control point, and the sixth control point.

[0076] When the first control point 13, the second control point 14 and the third control point are heated to their respective preset temperatures, temperature sensors can be used to detect the temperature values ​​of the fourth control point, the fifth control point and the sixth control point respectively.

[0077] Step S130: When the temperature at the fourth control point is less than the first threshold, it is determined that the thermal insulation of the connection area between the first wing surface 12 and the second wing surface meets the requirements; when the temperature at the fifth control point is less than the second threshold, it is determined that the thermal insulation of the first wing surface 12 meets the requirements; when the temperature at the sixth control point is less than the third threshold, it is determined that the thermal insulation of the second wing surface meets the requirements.

[0078] When the first preset temperature corresponding to the first control point 13 is 800℃ to 1400℃, the first threshold temperature can be 100℃ to 150℃, for example, the first threshold temperature can be 100℃, 110℃, 120℃, 130℃, 140℃, or 150℃. When the second preset temperature corresponding to the second control point 14 is 350℃ to 550℃, the second threshold temperature can be 50℃ to 70℃, for example, the second threshold temperature can be 50℃, 55℃, 60℃, 65℃, or 70℃. When the third preset temperature corresponding to the third control point is 450℃ to 700℃, the third threshold temperature can be 40℃ to 60℃, for example, the third threshold temperature can be 40℃, 45℃, 50℃, 55℃, or 60℃.

[0079] In this disclosure, considering both experimental effects and costs, a bimodal temperature loading spectrum is determined, allowing for a temperature loading process of heating-cooling-reheating, thereby verifying the thermal insulation performance of test piece 1 under repeated heating within a short period. Simultaneously, due to the faster heat dissipation at the leading edge stagnation point (i.e., the first control point 13) and slower heat dissipation at the rear edge in the actual service environment of the aircraft, the temperatures at the second and third control points should be higher than the initial heating temperature to fully assess the heat resistance of the leading edge structure during repeated heating. The specific temperature loading spectrum is as follows: Figure 5 As shown. The temperatures of the fourth, fifth, and sixth control points can be detected after the test specimen 1 is repeatedly heated, thereby determining whether the thermal insulation performance of the test specimen 1 meets the requirements. If the temperature of any of the fourth, fifth, and sixth control points detected after the test is not within its corresponding threshold range, it is determined that the design of the leading edge structure test specimen 1 does not meet the requirements, and the material and structure of the leading edge structure need to be readjusted.

[0080] Other embodiments of this disclosure will readily occur to those skilled in the art upon consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of this disclosure that follow the general principles of this disclosure and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only, and the true scope and spirit of this disclosure are indicated by the appended claims.

Claims

1. A system for testing the thermal insulation performance of an aircraft leading-edge structure test piece, characterized in that, include: The test specimen includes a fixed surface, a first wing surface, and a second wing surface. The fixed surface has a first side and a second side surface that are distributed opposite to each other. One end of the first wing surface is connected to the first side surface, and one end of the second wing surface is connected to the second side surface. The end of the first wing surface away from the first side surface is connected to the end of the second wing surface away from the second side surface. A first control point is provided on the outer surface of the connection area between the first wing surface and the second wing surface. A second control point is provided on the outer surface of the first wing surface. A third control point is provided on the outer surface of the second wing surface. A fourth control point is provided on the inner surface of the connection area between the first wing surface and the second wing surface, and the fourth control point is directly opposite to the first control point. A fifth control point is provided on the inner surface of the first wing surface, and the fifth control point is directly opposite to the second control point. A sixth control point is provided on the inner surface of the second wing surface, and the sixth control point is directly opposite to the third control point. An insulation chamber, wherein the test specimen is placed inside the insulation chamber, and the fixing surface faces the side wall of the insulation chamber; The heating device includes a plurality of heating components spaced apart around the first wing surface and the second wing surface; The temperature measurement component includes multiple temperature sensors, each of which measures the temperature of the first control point, the second control point, the third control point, the fourth control point, the fifth control point, and the sixth control point.

2. The testing system according to claim 1, characterized in that, The test specimen also includes front wall reinforcement bars disposed on the fixed surface, and the testing system further includes: The fixed double ears include a fixing rod and a fixing part. The fixing part is located at one end of the fixing rod. The fixing rod is detachably connected to the side wall of the insulation box, and the fixing part is detachably connected to the front wall rib.

3. The testing system according to claim 2, characterized in that, The fixing part includes a boss, a first ear, and a second ear. The boss is connected to the fixing rod. The first ear and the second ear are both connected to the side of the boss away from the fixing rod. The first ear and the second ear are arranged in parallel and spaced apart. The first ear has a first threaded hole, and the second ear has a second threaded hole. The first threaded hole and the second threaded hole are directly opposite each other. The front wall rib can extend into the space between the first ear and the second ear. The testing system further includes a first fastener and a second fastener, wherein the first fastener can pass through the first threaded hole and press against the front wall rib; and the second fastener can pass through the second threaded hole and press against the front wall rib.

4. The testing system according to claim 3, characterized in that, The testing system also includes: The first heat insulation pad is located between the first fastener and the front wall rib; The second heat insulation pad is located between the second fastener and the front wall reinforcement strip.

5. The testing system according to claim 3, characterized in that, Both the first and second locking components are bolts.

6. The testing system according to claim 2, characterized in that, The outer circumference of the fixing rod is threaded, and the testing system further includes: The first fixing member is sleeved on the outer periphery of the fixing rod and located on the inner wall of the insulation box near the test piece. The first fixing member is provided with internal threads. The second fixing member is sleeved on the outer periphery of the fixing rod and located on the outer wall of the insulation box away from the test piece. The second fixing member has an internal thread, and rotating the first fixing member and the second fixing member can fix the fixing rod to the insulation box.

7. The testing system according to any one of claims 1-6, characterized in that, The testing system also includes: Insulating cotton is used to fill the gap between the fixed surface and the insulation box.

8. A method for testing the thermal insulation performance of an aircraft leading-edge structure test piece, characterized in that, This includes using the thermal insulation performance testing system for aircraft leading edge structure test specimens as described in any one of claims 1-7 to conduct thermal insulation performance testing.

9. The test method according to claim 8, characterized in that, The testing method includes: The first control point is heated to a first preset temperature, the second control point is heated to a second preset temperature, and the third control point is heated to a third preset temperature. The temperature values ​​of the fourth control point, the fifth control point, and the sixth control point are detected; When the temperature at the fourth control point is less than the first threshold, it is determined that the thermal insulation of the connection area between the first wing and the second wing meets the requirements; when the temperature at the fifth control point is less than the second threshold, it is determined that the thermal insulation of the first wing meets the requirements; when the temperature at the sixth control point is less than the third threshold, it is determined that the thermal insulation of the second wing meets the requirements.

10. The test method according to claim 9, characterized in that, The first preset temperature is 800℃~1400℃, the second preset temperature is 350℃~550℃, and the third preset temperature is 450℃~700℃; the first threshold is 100℃~150℃, the second threshold is 50℃~70℃, and the third threshold is 40℃~60℃.

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