System and method for testing heat insulation performance of aircraft leading edge structure test piece

Abstract

The invention provides an aircraft leading edge structure test piece heat insulation performance test system and test method, and relates to the field of aircraft performance test. The test system comprises a test piece, a heat insulation box, a temperature measurement assembly and a temperature measurement assembly, the test piece comprises a fixed surface, a first wing surface and a second wing surface which are sequentially connected end to end, and a first control point and a fourth control point are arranged on the outer surface and the inner surface of a connecting area of the first wing surface and the second wing surface respectively; a second control point and a fifth control point are respectively arranged on the outer surface and the inner surface of the first airfoil, and a third control point and a sixth control point are respectively arranged on the outer surface and the inner surface of the second airfoil; the test piece is arranged in the heat insulation box; the heating device comprises a plurality of heating assemblies which surround the first wing surface and the second wing surface and are distributed at intervals; the temperature measuring assembly comprises a plurality of temperature sensors, and the temperature sensors test the temperature of the first control point, the temperature of the second control point, the temperature of the third control point, the temperature of the fourth control point, the temperature of the fifth control point and the temperature of the sixth control point in one-to-one correspondence.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aircraft performance testing, and in particular to a thermal insulation performance testing system and a testing method for an aircraft leading edge structure test piece. Background Art

[0002] The leading edge structure of an aircraft is mainly used for thermal protection in the high temperature area of ​​a hypersonic aircraft, and plays an important role in ensuring flight safety and improving the overall performance of the aircraft. In order to formulate a reasonable and effective thermal protection design scheme, it is urgent to conduct a thermal insulation performance test on the leading edge structure of the aircraft to evaluate the thermal insulation performance.

[0003] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present disclosure, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0004] The present invention provides a 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 the present disclosure, a system for testing thermal insulation performance of an aircraft leading edge structure test piece is provided, comprising:

[0006] A test piece, comprising a fixed surface, a first wing surface and a second wing surface, wherein the fixed surface has a first side edge and a second side edge that are relatively distributed, an end of the first wing surface is connected to the first side edge, an end of the second wing surface is connected to the second side edge, and an end of the first wing surface away from the first side edge is connected to an end of the second wing surface away from the second side edge; 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 arranged 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 arranged 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 arranged opposite to the third control point;

[0007] an insulating box, wherein the test piece is arranged in the insulating box, and the fixing surface faces the side wall of the insulating box;

[0008] A heating device, comprising a plurality of heating components that are spaced apart and surround the first airfoil and the second airfoil;

[0009] The temperature measurement component includes multiple temperature sensors, and each of the temperature sensors tests 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 one by one.

[0010] In an exemplary embodiment of the present disclosure, the test piece further includes a front wall rib provided on the fixing surface, and the test system further includes:

[0011] The fixed ears include a fixing rod and a fixing portion, wherein the fixing portion 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 portion is detachably connected to the front wall rib.

[0012] In an exemplary embodiment of the present disclosure, the fixing portion includes a boss, a first ear portion and a second ear portion, the boss is connected to the fixing rod, the first ear portion and the second ear portion are both located on a side of the boss away from the fixing rod, and the first ear portion and the second ear portion are arranged in parallel and spaced apart, a first threaded hole is provided on the first ear portion, and a second threaded hole is provided on the second ear portion; the first threaded hole and the second threaded hole are arranged opposite to each other, and the front wall rib can penetrate into between the first ear portion and the second ear portion;

[0013] The test system further comprises a first fastening member and a second fastening member, wherein the first fastening member can pass through the first threaded hole and press against the front wall rib; the second fastening member can pass through the second threaded hole and press against the front wall rib.

[0014] In an exemplary embodiment of the present disclosure, the testing system further includes:

[0015] A first heat-insulating gasket, located between the first fastening member and the front wall rib;

[0016] The second heat-insulating gasket is located between the second fastening member and the front wall rib.

[0017] In an exemplary embodiment of the present disclosure, the first fastening member and the second fastening member are both bolts.

[0018] In an exemplary embodiment of the present disclosure, the outer circumference of the fixing rod is provided with threads, and the testing system further comprises:

[0019] A first fixing member is sleeved on the outer periphery of the fixing rod and is located on a side of the inner wall of the insulation box close to the test piece, and the first fixing member is provided with an internal thread;

[0020] The second fixing part is sleeved on the outer circumference of the fixing rod and is located on the side of the outer wall of the insulation box away from the test piece. The second fixing part is provided with an internal thread. Rotating the first fixing part and the second fixing part can fix the fixing rod to the insulation box.

[0021] In an exemplary embodiment of the present disclosure, the testing system further includes:

[0022] The heat-insulating cotton fills the gap between the fixing surface and the heat-insulating box.

[0023] According to one aspect of the present disclosure, a method for testing the thermal insulation performance of an aircraft leading edge structure test piece is provided, comprising using any one of the above-mentioned systems for testing the thermal insulation performance of an aircraft leading edge structure test piece to perform a thermal insulation performance test.

[0024] In an exemplary embodiment of the present disclosure, the testing method includes:

[0025] Heating the first control point to a first preset temperature, heating the second control point to a second preset temperature, and heating the third control point to a third preset temperature;

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

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

[0028] In an exemplary embodiment of the present 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 thermal insulation performance testing system and method for aircraft leading edge structure test pieces disclosed in the present invention can fix the test piece in an insulating box, heat the first control point, the second control point and the third control point through a heating component, and at the same time, detect the temperatures of the fourth control point, the fifth control point and the sixth control point. The thermal insulation performance of the connection area between the first wing surface and the second wing surface is judged by the temperature of the fourth control point, the thermal insulation performance of the first wing surface 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.

[0030] It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The accompanying drawings herein are incorporated into the specification and constitute a part of the specification, illustrate embodiments consistent with the present disclosure, and together with the specification are used to explain the principles of the present disclosure. Obviously, the accompanying drawings described below are only some embodiments of the present disclosure, and for ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without creative work.

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

[0033] Figure 2 It is a schematic diagram of the assembly of the test piece and the insulation box in the embodiment of the present disclosure.

[0034] Figure 3 1 is a top view of the thermal insulation box and the test piece in the embodiment of the present disclosure.

[0035] Figure 4 It is a schematic diagram of the coordination between the fixed ears and the front wall ribs in the embodiment of the present disclosure.

[0036] Figure 5 Schematic diagram of the temperature loading spectrum in the embodiment of the present disclosure.

[0037] In the figure: 1. test piece; 11. fixing 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. fixing ears; 41. fixing rod; 42. fixing part; 421. boss; 422. first ear; 423. second ear; 51. first fastener; 52. second fastener; 61. first insulation gasket; 62. second insulation gasket; 71. first fixing part; 72. second fixing part; 8. fixing block. DETAILED DESCRIPTION

[0038] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in a variety of forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be comprehensive and complete and will fully convey the concepts of the example embodiments to those skilled in the art. The same reference numerals in the figures represent the same or similar structures, and thus their detailed description will be omitted.

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

[0040] The terms "a", "an", "the" and "said" are used to indicate the presence of one or more elements / components / etc.; the terms "including" and "having" are used to indicate an open-ended inclusive meaning and mean that there may be additional elements / components / etc. in addition to the listed elements / components / etc. The terms "first", "second", ... "sixth" are used only as labels and are not intended to limit the quantity of their objects.

[0041] The present disclosure provides a system for testing the thermal insulation performance of a leading edge structure test piece of an aircraft. Figure 1-Figure 3 As shown, the test system may include a test piece 1, an insulation box 2, a heating device 3 and a temperature measurement component, wherein:

[0042] The 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 relatively distributed, one end of the first wing surface 12 is connected to the first side, one end of the second wing surface is connected to the second side, and 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, and the fourth control point is arranged opposite to the first control point 13; a fifth control point is provided on the inner surface of the first wing surface 12, and the fifth control point is arranged opposite to the second control point 14; a sixth control point is provided on the inner surface of the second wing surface; and the sixth control point is arranged opposite to the third control point;

[0043] The test piece 1 is placed in the thermal insulation box 2, with the fixing surface 11 facing the side wall of the thermal insulation box 2;

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

[0045] The temperature measurement component includes a plurality of temperature sensors, each temperature sensor correspondingly testing 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 aircraft leading edge structure test piece thermal insulation performance testing system disclosed in the present invention can fix the test piece 1 in the 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 temperatures 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 can be judged by the temperature of the fourth control point, the thermal insulation performance of the first wing surface 12 can be judged by the temperature of the fifth control point, and the thermal insulation performance of the second wing surface can be 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 test system for the aircraft leading edge structure test piece in the embodiment of the present disclosure:

[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, and the fixed surface 11 may be a plane, which may have a first side and a second side 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 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 of the fixed surface 11. In addition, the end of the first wing surface 12 away from the first side may be connected to the end of the second wing surface away from the second side. In some embodiments of the present disclosure, the fixed surface 11, the first wing surface 12 and the second wing surface may be an integrated 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 then decreases smoothly along the chord direction toward the rear end. In order to reduce the overall temperature error of the test piece 1, the temperature control point can be selected in the middle part of the test piece 1. In some embodiments of the present disclosure, a plurality of control points can be provided on the test piece 1, and 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 respectively.

[0050] like Figure 1 and Figure 3 As shown, the outer surface of the connection area between the first wing surface 12 and the second wing surface may be provided with a first control point 13, and the first control point 13 may be located in the middle 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 a leading edge stationary point of the leading edge structure; please continue to refer to Figure 1 and Figure 3 As shown, the outer surface of the first wing surface 12 is provided with a second control point 14, and the second control point 14 can be located in the central area 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), and the third control point can be located in the central area of ​​the second wing surface. The inner surface of the middle part of the connecting area between the first wing surface 12 and the second wing surface is provided with a fourth control point, and the fourth control point can be arranged opposite to the first control point 13; the central area of ​​the inner surface of the first wing surface 12 is provided with a fifth control point, and the fifth control point can be arranged opposite to the second control point 14; the central area of ​​the inner surface of the second wing surface is provided with a sixth control point, and the sixth control point can be arranged opposite to the third control point.

[0051] Please continue to see Figure 1-Figure 3 As shown, the insulation box 2 is a box body, and the insulation box 2 may at least include 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 plates, and the first insulation wall 22, the second insulation wall 23, and the third insulation wall 24 may all be vertically distributed with the bottom wall, and the first insulation wall 22 and the second insulation wall 23 may be distributed in parallel, and the third insulation wall 24 may be connected between the first insulation wall 22 and the second insulation wall 23. In some embodiments of the present disclosure, a shell 21 is further provided on the outside of the insulation wall, and each insulation wall may be isolated from the external airflow by the shell 21.

[0052] The test piece 1 can be placed in an insulation box 2, such as Figure 2 As shown, the fixing surface 11 of the test piece 1 may face the side wall (e.g., the third insulation wall 24) of the insulation box 2. For example, fixing blocks 8 may be installed at both ends of the length direction of the test piece 1, the test piece 1 may be clamped between the two fixing blocks 8, and then the fixing blocks 8 and the test piece 1 may be placed together in the insulation box 2. At this time, the two fixing blocks 8 are tightly matched with the first insulation wall 22 and the second insulation wall 23, respectively, so as to fix the test piece 1 in the length direction.

[0053] In an exemplary embodiment of the present disclosure, the fixing surface 11 of the test piece 1 may face the third insulation wall 24 of the insulation box 2. Figure 2 As shown, the test piece 1 may further include a front wall rib 15, which may be disposed on the fixing surface 11. For example, the front wall rib 15 may be a sheet-like protrusion disposed on the fixing surface 11, and the front wall rib 15 and the fixing surface 11 are an integrated structure.

[0054] Please continue to see Figure 2As shown, the aircraft leading edge structure test piece thermal insulation performance test system disclosed in the present invention may also include a fixed double ear 4, which may include a fixed rod 41 and a fixed portion 42. The fixed rod 41 may be in the shape of a rod, and its outer circumference may be provided with threads. For example, the fixed rod 41 may be a threaded rod. The fixed rod 41 may pass through the side wall of the insulation box 2 and be detachably connected to the side wall of the insulation box 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 the third insulation wall 24 and the outer shell 21, that is, one end of the fixed rod 41 is located in the insulation box 2. The fixed portion 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 portion 42 may be located on the end of the fixed rod 41 located in the test box.

[0055] In an exemplary embodiment of the present disclosure, Figure 4 As shown, the aircraft leading edge structure test piece thermal insulation performance test system disclosed in the present invention may also include a first fixing member 71 and a second fixing member 72, wherein the first fixing member 71 may be sleeved on the outer periphery of the fixing rod 41, and the first fixing member 71 is located on the side of the inner wall of the insulation box 2 close to the test piece 1, the first fixing member 71 may be provided with an internal thread, and the first fixing member 71 may be connected to the fixing rod 41 by a thread. The second fixing member 72 may also be sleeved on the outer periphery of the fixing rod 41, the second fixing member 72 may be located on the side of the outer wall of the insulation box 2 away from the test piece 1, the second fixing member 72 may be provided with an internal thread, and the second fixing member 72 may be connected to the fixing rod 41 by a thread, and 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 box 2 (for example, the third insulation wall 24 and the shell 21). For example, the first fixing member 71 and the second fixing member 72 may both be nuts.

[0056] In an exemplary embodiment of the present disclosure, the fixing portion 42 can be detachably connected to the front wall rib 15. Figure 4 As shown, the fixing portion 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, which is not particularly limited here. The boss 421 may be connected to the fixing rod 41, and 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 sheet-shaped, and the first ear 422 and the second ear 423 may be arranged in parallel and spaced apart in a direction perpendicular to the central axis of the fixing rod 41.

[0057] The first ear portion 422 may be provided with a first threaded hole (not shown in the figure), which may penetrate the first ear portion 422 along the thickness direction of the first ear portion 422; the second ear portion 423 may be provided with a second threaded hole (not shown in the figure), which 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 to each other, and the front wall rib 15 may penetrate between the first ear portion 422 and the second ear portion 423.

[0058] In an exemplary embodiment of the present disclosure, the fixing rod 41, the boss 421, the first ear 422 and the second ear 423 may be made of metal, alloy or stainless steel, etc. The fixing rod 41, the boss 421, the first ear 422 and the second ear 423 may be an integrated structure.

[0059] Please continue to see Figure 4 As shown, the aircraft leading edge structure test piece thermal insulation performance test system of the present disclosure may also include a first fastener 51 and a second fastener 52. The first fastener 51 and the second fastener 52 may both be strip-shaped, and the outer circumferences of the first fastener 51 and the second fastener 52 are both provided with threads. The material of the first fastener 51 and the second fastener 52 may be metal, alloy or stainless steel, etc. For example, the first fastener 51 and the second fastener 52 may both be bolts.

[0060] The first fastener 51 can pass through the first threaded hole, and rotating the first fastener 51 can tighten the front wall rib 15; the second fastener 52 can pass through the second threaded hole, and rotating the second fastener 52 can tighten the front wall rib 15, and the front wall rib 15 can be fixed between the first fastener 51 and the second fastener 52.

[0061] In an exemplary embodiment of the present disclosure, the number of the first threaded hole, the second threaded hole, the first fastener 51, and the second fastener 52 can be multiple, and the number of the first threaded holes is equal to the number of the first fasteners 51, and each first fastener 51 can pass through each first threaded hole one by one and respectively press against the front wall rib 15. At the same time, the number of the second threaded holes is equal to the number of the second fasteners 52, and each second fastener 52 can pass through each second threaded hole one by one and respectively press against the front wall rib 15. The setting of multiple first fasteners 51 and multiple second fasteners 52 can enhance the fixing effect of the front wall rib 15 to prevent the accuracy of the test result from being affected by the movement of the test piece 1 during the test process.

[0062] In an exemplary embodiment of the present disclosure, please continue to refer to Figure 4As shown, the aircraft leading edge structure test piece thermal insulation performance test system disclosed in the present invention may also include a first thermal insulation gasket 61 and a second thermal insulation gasket 62, wherein the first thermal insulation gasket 61 may be in the form of a sheet, and its shape may be circular, rectangular, elliptical, polygonal or irregular, and its material may be asbestos, rock wool or glass fiber, etc., and no special limitation is made on the shape and material of the first thermal insulation gasket 61. The first thermal insulation gasket 61 may be located between the first fastener 51 and the front wall rib 15, and the first thermal insulation gasket 61 may be provided to prevent the heat in the test piece 1 from diffusing through the first fastener 51 and the fixed ears 4 during the test, which helps to truly simulate the thermal environment of the leading edge structure and ensure the stability of the test conditions.

[0063] The second thermal insulation gasket 62 can be in the form of a sheet, and its shape can be circular, rectangular, elliptical, polygonal or irregular. Its material can be asbestos, rock wool or glass fiber, etc., and the shape and material of the second thermal insulation gasket 62 are not specifically limited here. The second thermal insulation gasket 62 can be located between the second fastener 52 and the front wall rib 15. The second thermal insulation gasket 62 can be provided to prevent the heat in the test piece 1 from diffusing through the second fastener 52 and the fixed ears 4 during the test, and the stability of the test conditions can be further improved. The materials of the first thermal insulation gasket 61 and the second thermal insulation gasket 62 can be the same or different, and are not specifically limited here.

[0064] In an exemplary embodiment of the present disclosure, there may be a plurality of front wall ribs 15, and the plurality of front wall ribs 15 may be disposed on the fixing surface 11, and the plurality of front wall ribs 15 may be spaced apart along the length direction of the test piece 1. There may also be a plurality of corresponding fixing ears 4, and the plurality of fixing ears 4 may be fixed in coordination with each front wall rib 15 in a one-to-one correspondence.

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

[0066] Please continue to see Figure 1 As shown, the heating device 3 may include a plurality of heating components 31, which may surround the first wing surface 12 and the second wing surface and be equally spaced and distributed around the periphery of the first wing surface 12 and the second wing surface. The heating components 31 may be strip-shaped, and the plurality of heating components 31 may be distributed in parallel. For example, the heating components 31 may be quartz lamps.

[0067] The MTS-complex coordinated control system can be used to control the quartz lamp heating so that each area of ​​the test piece 1 reaches the preset temperature. In this process, the DC voltage value at both ends of the grouped heating unit of the quartz lamp can be adjusted to increase its working power, so that the surface temperature of the test piece 1 quickly reaches the preset value by thermal radiation. The quartz lamp in the present disclosure can be composed of a quartz heating lamp tube, a lamp tube bracket and an outer cover. The quartz heating lamp tube group can be used as a thermal radiation light source. The rated voltage of the quartz heating lamp tube can be 220V, and the rated power can be 4.3kw. The quartz heating lamp tube has a small thermal inertia and can reach 80% of the rated power in about 1s, with rapid heating and cooling.

[0068] The temperature measurement component (not shown in the figure) may include a plurality of temperature sensors, and the number of the temperature sensors is equal to the number of the control points. For example, when the number of the control points is 6, the number of the temperature sensors may also be 6. Each temperature sensor may 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 one by one.

[0069] During the test, the temperature of the first control point 13 can be monitored by the temperature sensor corresponding to the first control point 13, the temperature of the second control point 14 can be monitored by the temperature sensor corresponding to the second control point 14, and the temperature of the third control point can be monitored by the temperature sensor corresponding to the third control point, so as to accurately control the heating temperatures 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 the temperature sensor corresponding to the fourth control point, the temperature of the fifth control point can be detected by the temperature sensor corresponding to the fifth control point, and the temperature of the sixth control point can be detected by the temperature sensor corresponding to the sixth control point. The thermal insulation performance of the connection area between the first wing surface 12 and the second wing surface can be judged by the temperature of the fourth control point, the thermal insulation performance of the first wing surface 12 can be judged by the temperature of the fifth control point, and the thermal insulation performance of the second wing surface can be judged by the temperature of the sixth control point, thereby providing data support for the design of the leading edge structure.

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

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

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

[0073] Since the leading edge stagnation point of the leading edge structure has the highest temperature during the operation of the aircraft, the temperature applied to the leading edge stagnation point (i.e., the first control point 13) during the test is the highest, and the temperature of other areas (e.g., the first wing surface 12 and the second wing surface) is slightly lower. Since the environments in which different wing surfaces are located during operation are different, the temperatures borne by different wing surfaces are also different. 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°C to 1400°C, for example, it can be 800°C, 1000°C, 1200°C or 1400°C, of ​​course, it can also be other temperatures, which are not specifically limited here. The second preset temperature corresponding to the second control point 14 can be 350°C to 550°C, for example, it can be 350°C, 400°C, 450°C, 500°C or 550°C, of ​​course, it can also be other temperatures, which are not specifically limited here. The third preset temperature corresponding to the third control point may be 450°C to 700°C. For example, it may be 450°C, 500°C, 550°C, 600°C, 650°C or 700°C. Of course, it may also be other temperatures, which are not specifically limited here.

[0074] The test piece 1 can be heated by a heating assembly 31 , during which the temperatures of the first control point 13 , the second control point 14 and the third control point can be monitored by a temperature sensor to precisely control the temperatures of the first control point 13 , the second control point 14 and the third control point.

[0075] Step S120, detecting 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 corresponding preset temperatures, temperature sensors may 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 of the fourth control point is less than the first threshold value, it is judged 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 of the fifth control point is less than the second threshold value, it is judged that the thermal insulation of the first wing surface 12 meets the requirements; when the temperature of the sixth control point is less than the third threshold value, it is judged 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°C to 1400°C, the first threshold value may be 100°C to 150°C, for example, the first threshold value may be 100°C, 110°C, 120°C, 130°C, 140°C or 150°C. When the second preset temperature corresponding to the second control point 14 is 350°C to 550°C, the second threshold value may be 50°C to 70°C, for example, the second threshold value may be 50°C, 55°C, 60°C, 65°C or 70°C. When the third preset temperature corresponding to the third control point is 450°C to 700°C, the third threshold value may be 40°C to 60°C, for example, the third threshold value may be 40°C, 45°C, 50°C, 55°C or 60°C.

[0079] In the present disclosure, the test effect and test cost are considered, and the double-peak temperature loading spectrum is determined, so that the temperature loading process of heating-cooling-reheating can be carried out, thereby verifying the thermal insulation performance of the test piece 1 when it is repeatedly heated in a short period of time. At the same time, in the actual service environment of the aircraft, the heat dissipation at the leading edge stagnation point (i.e., the first control point 13) is faster, and the heat dissipation at the rear side is slower. When the leading edge structure is repeatedly heated, in order to fully evaluate the heat resistance performance of the leading edge structure, the temperature of the second control point 14 and the third control point should be higher than the temperature of the first heating. The specific temperature loading spectrum is as follows: Figure 5 After the test piece 1 is repeatedly heated, the temperatures of the fourth control point, the fifth control point and the sixth control point can be detected to determine whether the thermal insulation performance of the test piece 1 meets the requirements. If the temperature of any one of the fourth control point, the fifth control point and the sixth control point detected after the test is not within the corresponding threshold range, it is determined that the design of the leading edge structure test piece 1 does not meet the requirements, and the material and structure of the leading edge structure need to be readjusted.

[0080] Those skilled in the art will readily appreciate other embodiments of the present disclosure after considering the specification and practicing the invention disclosed herein. This application is intended to cover any modification, use or adaptation of the present disclosure, which follows the general principles of the present disclosure and includes common knowledge or customary techniques in the art that are not disclosed in the present disclosure. The specification and examples are intended to be exemplary only, and the true scope and spirit of the present disclosure are indicated by the appended claims.

Claims

1. A thermal insulation performance testing system for aircraft leading edge structure test pieces, characterized in that: include: A test piece, comprising a fixed surface, a first wing surface and a second wing surface, wherein the fixed surface has a first side edge and a second side edge that are relatively distributed, an end of the first wing surface is connected to the first side edge, an end of the second wing surface is connected to the second side edge, and an end of the first wing surface away from the first side edge is connected to an end of the second wing surface away from the second side edge; 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 arranged 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 arranged 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 arranged opposite to the third control point; an insulating box, wherein the test piece is arranged in the insulating box, and the fixing surface faces the side wall of the insulating box; A heating device, comprising a plurality of heating components that are spaced apart and surround the first airfoil and the second airfoil; The temperature measurement component includes multiple temperature sensors, and each of the temperature sensors tests 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 one by one.

2. The test system according to claim 1, characterized in that: The test piece further includes a front wall rib, which is arranged on the fixing surface, and the test system further includes: The fixed ears include a fixing rod and a fixing part, wherein 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 test system according to claim 2, characterized in that: The fixing portion 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 a 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 is provided with a first threaded hole, and the second ear is provided with a second threaded hole; the first threaded hole and the second threaded hole are arranged opposite to each other, and the front wall rib can penetrate into between the first ear and the second ear; The test system further comprises a first fastening member and a second fastening member, wherein the first fastening member can pass through the first threaded hole and press against the front wall rib; the second fastening member can pass through the second threaded hole and press against the front wall rib.

4. The test system according to claim 3, characterized in that: The test system further comprises: A first heat-insulating gasket, located between the first fastening member and the front wall rib; The second heat-insulating gasket is located between the second fastening member and the front wall rib.

5. The test system according to claim 3, characterized in that: The first fastening member and the second fastening member are both bolts.

6. The test system according to claim 2, characterized in that: The outer circumference of the fixing rod is provided with threads, and the testing system further comprises: A first fixing member is sleeved on the outer periphery of the fixing rod and is located on a side of the inner wall of the insulation box close to the test piece, and the first fixing member is provided with an internal thread; The second fixing part is sleeved on the outer circumference of the fixing rod and is located on the side of the outer wall of the insulation box away from the test piece. The second fixing part is provided with an internal thread. Rotating the first fixing part and the second fixing part can fix the fixing rod to the insulation box.

7. The test system according to any one of claims 1 to 6, characterized in that: The test system further comprises: The heat-insulating cotton fills the gap between the fixing surface and the heat-insulating box.

8. A method for testing the thermal insulation performance of an aircraft leading edge structure test piece, characterized in that: The method comprises using the aircraft leading edge structure test piece thermal insulation performance testing system as described in any one of claims 1 to 7 to perform thermal insulation performance testing.

9. The testing method according to claim 8, characterized in that: The test method includes: Heating the first control point to a first preset temperature, heating the second control point to a second preset temperature, and heating the third control point to a third preset temperature; Detecting the temperature values ​​of the fourth control point, the fifth control point, and the sixth control point; When the temperature of the fourth control point is lower than the first threshold, it is judged that the thermal insulation of the connection area between the first wing surface and the second wing surface meets the requirements; when the temperature of the fifth control point is lower than the second threshold, it is judged that the thermal insulation of the first wing surface meets the requirements; when the temperature of the sixth control point is lower than the third threshold, it is judged that the thermal insulation of the second wing surface meets the requirements.

10. The testing 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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