Testing device for rudder wing

Abstract

The invention discloses a testing device for a rudder wing. The testing device for the rudder wing comprises a base; the heating mechanism is movably mounted on the base and is provided with a heating space for heating a rudder wing; the adjusting mechanism is connected between the base and the heating mechanism, and the adjusting mechanism is configured to adjust the heating distance between the heating mechanism and the rudder wing and / or the heat radiation angle when the rudder wing is heated. According to the test device for the rudder wing, the heating angle and distance can be adjusted according to the shape of the rudder wing surface of the rudder wing, so that the heating uniformity of the rudder wing surface is ensured, the heat utilization rate is improved, the accuracy of a simulation experiment of the rudder wing is improved, and the design reliability of the rudder wing is improved.

Description

Technical Field

[0001] The present application relates to the technical field of rudder wing detection, and in particular to a testing device for rudder wing. Background Art

[0002] In order to explore the various performances of the rudder wing in the service environment and improve the design reliability of the product, it is necessary to carry out simulation tests on the rudder wing on the ground, that is, to heat the rudder wing. However, the size of the existing test device is relatively fixed, and it is difficult to adjust the heating angle and distance according to the shape of the rudder wing surface. The heat utilization rate is not high, and it is difficult to ensure the heating uniformity of the rudder wing surface. Summary of the invention

[0003] The present application aims to solve at least one of the technical problems existing in the prior art. To this end, the present application proposes a test device for a rudder wing, which can adjust the heating angle and distance according to the shape of the rudder wing surface of the rudder wing to ensure the heating uniformity of the rudder wing surface, and is conducive to improving the heat utilization rate, thereby improving the accuracy of the simulation experiment of the rudder wing, and thereby improving the design reliability of the rudder wing.

[0004] According to an embodiment of the present application, a test device for a rudder wing includes: a base; a heating mechanism, which is movably mounted on the base and is provided with a heating space for heating the rudder wing; an adjusting mechanism, which is connected between the base and the heating mechanism, and is configured to adjust the heating distance between the heating mechanism and the rudder wing and / or the heat radiation angle when heating the rudder wing.

[0005] According to the test device for rudder wings according to the embodiment of the present application, its adjustment mechanism can adjust the heat radiation angle of the heating mechanism to the rudder wings, so as to facilitate the heating of rudder wings of different sizes, and can adjust the heating angle and distance according to the rudder wing surface shape of the rudder wing to ensure the heating uniformity of the rudder wing surface, and is beneficial to improve the heat utilization rate, thereby improving the accuracy of the simulation experiment of the rudder wing, and thereby improving the design reliability of the rudder wing.

[0006] According to some embodiments of the test device for rudder wings of the present application, the adjustment mechanism includes a first adjustment rod, a second adjustment rod and an adjustment nut, the first adjustment rod is hinged to the heating mechanism, the second adjustment rod is hinged to the base, and both ends of the adjustment nut are respectively threadedly matched with the first adjustment rod and the second adjustment rod.

[0007] According to the test device for rudder wings of some embodiments of the present application, both ends of the adjusting nut are respectively sleeved on the first adjusting rod and the second adjusting rod.

[0008] According to some embodiments of the test device for rudder wings of the present application, the heating mechanism includes a first mounting frame, a second mounting frame and a heating lamp, the heating space is defined between the first mounting frame and the second mounting frame, and the heating lamp is provided on the side of the first mounting frame and the second mounting frame facing each other, the first mounting frame and / or the second mounting frame are hinged to the base, and the angle between the first mounting frame and / or the second mounting frame and the base is adjustable.

[0009] According to the test device for the rudder wing of some embodiments of the present application, the heating lamp is detachably mounted on the first mounting frame and the second mounting frame, and the heating surface of the heating lamp is designed to conform to the shape of the rudder wing.

[0010] According to some embodiments of the present application, the test device for the rudder wing also includes: a clamping mechanism, which is connected to the base and includes a clamping base and two clamping blocks, the clamping base is connected to the base, the two clamping blocks are both installed on the clamping base, and at least one of the two clamping blocks can slide along the clamping base relative to the other so that the two clamping blocks clamp or release the rudder wing.

[0011] According to some embodiments of the test device for rudder wings of the present application, the clamping mechanism also includes a rotating shaft and a bearing, the bearing is installed on the clamping base and sleeved on the rotating shaft, the rotating shaft passes through at least one of the clamping blocks and is threadedly matched with the clamping block.

[0012] According to some embodiments of the present application, the test device for the rudder wing also includes an actuating mechanism, which is installed on the base and includes a hydraulic actuator and a first pull rod. The output end of the hydraulic actuator is connected to the first pull rod, and the first pull rod is suitable for passing through one side of the rudder wing to the other side of the rudder wing and cooperating with the other side of the rudder wing in a limiting manner.

[0013] According to some embodiments of the test device for rudder wings of the present application, the actuating mechanism further includes a lever plate, a second pull rod, a third pull rod and a fourth pull rod, the second pull rod is connected between the output end of the hydraulic actuator and the lever plate, the third pull rod and the fourth pull rod are both connected to the lever plate, and the third pull rod and the fourth pull rod are both suitable for passing through from one side of the rudder wing to the other side of the rudder wing and cooperating with the other side of the rudder wing in a limiting manner.

[0014] According to the test device for rudder wings in some embodiments of the present application, the base includes a plurality of structural beams, and any two of the structural beams are detachably connected.

[0015] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become apparent from the description below, or will be learned through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0017] Figure 1 Schematic diagram of a test device for rudder wings according to some embodiments of the present application Figure 1 ;

[0018] Figure 2 Schematic diagram of a test device for rudder wings according to some embodiments of the present application Figure 2 ;

[0019] Figure 3 Schematic diagram of the adjustment mechanism of some embodiments of the present application;

[0020] Figure 4 A cross-sectional view of an adjustment mechanism according to some embodiments of the present application;

[0021] Figure 5 Schematic diagram of the heating mechanism of some embodiments of the present application Figure 1 ;

[0022] Figure 6 Schematic diagram of the heating mechanism of some embodiments of the present application Figure 2 ;

[0023] Figure 7 A cross-sectional view of a first mounting frame according to some embodiments of the present application;

[0024] Figure 8 A schematic diagram of a first installation frame of some embodiments of the present application;

[0025] Fig. 9 Schematic diagram of a clamping mechanism according to some embodiments of the present application;

[0026] Fig.10 A cross-sectional view of the clamping mechanism of some embodiments of the present application Figure 1 ;

[0027] Fig.11 A cross-sectional view of the clamping mechanism of some embodiments of the present application Figure 2 ;

[0028] Fig.12 Schematic diagram of the actuating mechanism of some embodiments of the present application Figure 1 ;

[0029] Fig.13 Schematic diagram of the actuating mechanism of some embodiments of the present application Figure 2;

[0030] Fig.14 A cross-sectional view of an actuating mechanism of some embodiments of the present application;

[0031] Fig.15 A schematic diagram of a base according to some embodiments of the present application;

[0032] Fig.16 Schematic diagram of a structural beam according to some embodiments of the present application;

[0033] Fig.17 Schematic diagram of the guide rail body of some embodiments of the present application.

[0034] A test device 100 for a rudder wing;

[0035] Base 1; structural beam 10; cross beam 11; longitudinal beam 12; vertical beam 13; upper panel 101; lower panel 102; reinforcing plate 103; end panel 104; middle panel 105; guide rail adapter plate 14; guide rail 15; heating mechanism mounting seat 16; adjustment mechanism mounting seat 17; slider 18; guide rail body 19; set screw 20;

[0036] Clamping mechanism 2; clamping base 21; first slider 22; second slider 23; bearing seat 24; clamping block 25; bearing cover plate 26; rotating shaft 27; bearing 28; heating lamp 29;

[0037] Heating mechanism 3; first mounting frame 30; second mounting frame 31; heat insulation board 32; connecting lug 33; screw 34; water inlet pipe 35; water outlet pipe 36; adapter lug 37;

[0038] Actuating mechanism 4; hydraulic actuator 38; actuator adapter plate 39; tension seat 40; lever plate 41; first pull rod 42; second pull rod 43; third pull rod 44; fourth pull rod 45;

[0039] Adjustment mechanism 5; first adjustment rod 51; second adjustment rod 52; adjustment nut 53; rudder wing 6. DETAILED DESCRIPTION

[0040] In order to better understand the technical solutions provided by the embodiments of this specification, the technical solutions of the embodiments of this specification are described in detail below through the accompanying drawings and specific embodiments. It should be understood that the embodiments of this specification and the specific features in the embodiments are detailed descriptions of the technical solutions of the embodiments of this specification, rather than limitations on the technical solutions of this specification. In the absence of conflict, the embodiments of this specification and the technical features in the embodiments can be combined with each other.

[0041] In this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply that there is any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or equipment. In the absence of more restrictions, the elements limited by the statement "comprise one..." do not exclude the existence of other identical elements in the process, method, article or equipment including the elements. The term "more than two" includes two or more than two situations.

[0042] In order to explore the various performances of rudder and wing products in the service environment and improve the design reliability of the products, it is necessary to carry out simulation tests on the rudder and wing products on the ground. That is, while heating the rudder and wing products, structural forces are applied to the rudder and wing products to verify the compliance of the performance of the rudder and wing products under the force-heat coupling conditions.

[0043] In the related art, the device for the mechanical and thermal coupling test of rudder wing products is a special equipment, that is, for each specification of rudder wing products, a special test device suitable for it needs to be designed, which is not universal and has a high test cost. This type of special test device, on the one hand, designs a corresponding number of actuators according to the number of concentrated loads on the rudder wing surface, that is, adopts a point-to-point loading method. Due to the limitation of the external structural size of the actuator, it is impossible to test products with small structural dimensions of rudder wing products or small concentrated load distribution spacing; on the other hand, it is impossible to adjust the heating angle and distance according to the shape of the rudder wing surface of the rudder wing product, the thermal utilization rate is not high, and it is difficult to ensure the heating uniformity of the rudder wing surface.

[0044] To this end, the present application proposes a testing device 100 for the rudder wing 6 .

[0045] like Figure 1 and Figure 2 As shown, the test device 100 for the rudder wing 6 according to the embodiment of the present application includes: a base 1, a heating mechanism 3 and an adjustment mechanism 5.

[0046] The heating mechanism 3 can be movably mounted on the base 1 and is provided with a heating space for heating the rudder wing 6. The adjusting mechanism 5 is connected between the base 1 and the heating mechanism 3, and the adjusting mechanism 5 is configured to adjust the heating distance between the heating mechanism 3 and the rudder wing 6 and / or the heat radiation angle when heating the rudder wing 6.

[0047] There may be a plurality of heating mechanisms 3 , and the plurality of heating mechanisms 3 may be arranged around the circumference of the rudder wing 6 to achieve heating of the rudder wing 6 in multiple directions.

[0048] The adjusting mechanism 5 is connected between the base 1 and the heating mechanism 3 , and the adjusting mechanism 5 is configured to adjust the heating distance between the heating mechanism 3 and the rudder wing 6 and / or the heat radiation angle during heating.

[0049] For example, the number of adjusting mechanisms 5 and heating mechanisms 3 is the same, and each heating mechanism 3 can be adjusted by the corresponding adjusting mechanism 5. In this way, the heating angle and distance can be adjusted according to the shape of the rudder wing 6 surface of the rudder wing 6 to ensure the heating uniformity of the rudder wing 6 surface, and it is beneficial to improve the heat utilization rate, thereby improving the accuracy of the simulation experiment of the rudder wing 6, and thereby improving the design reliability of the rudder wing 6.

[0050] According to the test device 100 for the rudder wing 6 of the embodiment of the present application, its adjustment mechanism 5 can adjust the heat radiation angle of the heating mechanism 3 to the rudder wing 6, so as to facilitate the heating of rudder wings 6 of different sizes, and can adjust the heating angle and distance according to the shape of the rudder wing 6 surface of the rudder wing 6 to ensure the heating uniformity of the rudder wing 6 surface, and is beneficial to improve the heat utilization rate, thereby improving the accuracy of the simulation experiment of the rudder wing 6, and thereby improving the design reliability of the rudder wing 6.

[0051] In some embodiments, Figure 3 and Figure 4 As shown, the adjustment mechanism 5 includes a first adjustment rod 51, a second adjustment rod 52 and an adjustment nut 53. The first adjustment rod 51 is hinged to the heating mechanism 3, the second adjustment rod 52 is hinged to the base 1, and the two ends of the adjustment nut 53 are respectively threadedly engaged with the first adjustment rod 51 and the second adjustment rod 52. Therefore, the first adjustment rod 51 and / or the second adjustment rod 52 can be relatively rotated with the adjustment nut 53 to achieve the movement of the first adjustment rod 51 and / or the second adjustment rod 52 in the axial direction of the adjustment nut 53, thereby adjusting the heating distance between the heating mechanism 3 and the rudder wing 6 and / or the heat radiation angle during heating.

[0052] In some embodiments, Figure 3 and Figure 4 As shown, two ends of the adjusting nut 53 are respectively sleeved on the first adjusting rod 51 and the second adjusting rod 52 .

[0053] Therefore, it is easy to reduce the difficulty of connecting the adjusting nut 53 with the first adjusting rod 51 and the second adjusting rod 52 , and it is beneficial to realize the threaded cooperation between the adjusting nut 53 and the first adjusting rod 51 and the second adjusting rod 52 .

[0054] In some embodiments, Figure 5 and Figure 6As shown, the heating mechanism 3 includes a first mounting frame 30, a second mounting frame 31 and a heating lamp 29, a heating space is defined between the first mounting frame 30 and the second mounting frame 31, and a heating lamp 29 is provided on the side of the first mounting frame 30 and the second mounting frame 31 facing each other, the first mounting frame 30 and / or the second mounting frame 31 are hinged to the base 1, and the angle between the first mounting frame 30 and / or the second mounting frame 31 and the base 1 is adjustable.

[0055] Therefore, by setting the first mounting frame 30 and / or the second mounting frame 31 to be hinged with the base 1, so that the angle between the first mounting frame 30 and / or the second mounting frame 31 and the base 1 is adjustable, the adjustment mechanism 5 can push the first mounting frame 30 and / or the second mounting frame 31 to rotate relative to the base 1 to adjust the heat radiation angle of the heating lamp 29 to the rudder wing 6, so as to facilitate the heating of rudder wings 6 of different sizes, and can adjust the heating angle and distance according to the shape of the rudder wing 6 surface of the rudder wing 6 to ensure the heating uniformity of the rudder wing 6 surface, and is conducive to improving the heat utilization rate, thereby improving the accuracy of the simulation experiment of the rudder wing 6, and thereby improving the design reliability of the rudder wing 6.

[0056] In some embodiments, the first mounting frame 30 and / or the second mounting frame 31 is provided with a cooling assembly, for example, the cooling assembly may be a water inlet pipe 35 and a water outlet pipe 36, such as Figure 7 and Figure 8 As shown, a water inlet pipe 35 is welded at the lower part of the rear surface of the first mounting frame 30 and the second mounting frame 31 for connecting cooling tap water, and a water outlet pipe 36 is welded at the upper part, and the cooling tap water flows out through the water outlet pipe 36, so as to achieve the purpose of cooling the first mounting frame 30 and the second mounting frame 31 under the test state of the test device.

[0057] In some embodiments, the heating lamp 29 is detachably mounted on the first mounting frame 30 and the second mounting frame 31, and the heating surface of the heating lamp 29 is designed to conform to the shape of the rudder wing 6. Thus, it is convenient to reduce the difficulty of loading and unloading the heating lamp 29, and the heating surface of the heating lamp 29 is designed to conform to the shape of the rudder wing 6, so as to better meet the heating requirements of the rudder wing 6.

[0058] In some embodiments, Figure 1 and Figure 2 As shown, the test device 100 for the rudder wing 6 also includes: a clamping mechanism 2, the clamping mechanism 2 is connected to the base 1, such as Fig. 9 and Fig.10 As shown, it includes a clamping base 21 and two clamping blocks 25. The clamping base 21 is connected to the base 1. The two clamping blocks 25 are both installed on the clamping base 21, and at least one of the two clamping blocks 25 can slide along the clamping base 21 relative to the other, so that the two clamping blocks 25 clamp or release the rudder wing 6.

[0059] Thus, the clamping base 21 can be installed on the base 1 to install the clamping mechanism 2 on the base 1, and the clamping block 25 can slide on the clamping base 21 to adjust the distance between the two clamping blocks 25. For example, when clamping the rudder wing 6, the distance between the two clamping blocks 25 can be increased or decreased by sliding the clamping block 25, thereby achieving clamping of the rudder wing 6.

[0060] In some embodiments, Fig. 9 and Fig.10 As shown, the clamping mechanism 2 further includes a rotating shaft 27 and a bearing 28. The bearing 28 is mounted on the clamping base 21 and sleeved on the rotating shaft 27 (as shown in FIG. Fig.11 As shown), the rotating shaft 27 passes through at least one clamping block 25 and is threadedly matched with the clamping block 25.

[0061] Therefore, after the clamping base 21 limits the clamping block 25 in the circumferential direction of the rotating shaft 27, when the rotating shaft 27 rotates, the clamping block 25 will move along the axial direction of the rotating shaft 27 under the rotational force of the rotating shaft 27, thereby realizing the sliding of the clamping block 25 on the clamping base 21. At the same time, the rotating shaft 27 and the clamping block 25 are threadedly matched, so that when the rotating shaft 27 is not rotating, the rotating shaft 27 and the clamping block 25 can achieve limited matching in the axial direction of the rotating shaft 27, thereby ensuring the stability of the clamping block 25, and making it convenient to use the two clamping blocks 25 to clamp the rudder wing 6.

[0062] In some embodiments, Figure 1 and Figure 2 As shown, the test device 100 for the rudder wing 6 also includes an actuating mechanism 4, which is installed on the base 1 and Figure 12-14 As shown, the actuating mechanism 4 includes a hydraulic actuator 38 and a first pull rod 42. The output end of the hydraulic actuator 38 is connected to the first pull rod 42. The first pull rod 42 is suitable for passing through one side of the rudder wing 6 to the other side of the rudder wing 6 and cooperating with the other side of the rudder wing 6 in a limited position.

[0063] Therefore, the first pull rod 42 can be pulled or pushed by the hydraulic actuator 38 so that the first pull rod 42 applies a load to the rudder wing 6, thereby facilitating a load test on the rudder wing 6.

[0064] There may be a plurality of first tie rods 42 , and the plurality of first tie rods 42 may be respectively connected to the output ends of the hydraulic actuator 38 , so as to apply a plurality of loads to the rudder wing 6 through the plurality of first tie rods 42 .

[0065] In some embodiments, Figure 12-14As shown, the actuating mechanism 4 also includes a lever plate 41, a second pull rod 43, a third pull rod 44 and a fourth pull rod 45. The second pull rod 43 is connected between the output end of the hydraulic actuator 38 and the lever plate 41. The third pull rod 44 and the fourth pull rod 45 are both connected to the lever plate 41, and the third pull rod 44 and the fourth pull rod 45 are both suitable for passing through from one side of the rudder wing 6 to the other side of the rudder wing 6 and cooperating with the other side of the rudder wing 6 in a limiting manner.

[0066] Therefore, through the design of the lever plate 41, the load output by the hydraulic actuator 38 can be transmitted to the third tie rod 44 and the fourth tie rod 45 respectively through the second tie rod 43, that is, the third tie rod 44 and the fourth tie rod 45 are connected in parallel, so that the third tie rod 44 and the fourth tie rod 45 can share the second tie rod 43, thereby simplifying the setting of the tie rod and further reducing the size of the actuating mechanism 4.

[0067] In some embodiments, the base 1 includes a plurality of structural beams 10 , and any two structural beams 10 are detachably connected.

[0068] For example Fig.15 As shown, the structural beam 10 may include any one of a transverse beam 11, a longitudinal beam 12 and a vertical beam 13. Thus, by setting a plurality of structural beams 10, the size of the base 1 can be flexibly adjusted according to the size of the rudder wing 6, so that the base 1 can meet the test requirements of rudder wings 6 of different sizes.

[0069] In some embodiments, Fig.16 As shown, the structural beam 10 can be welded by an upper panel 101, a lower panel 102, a reinforcing plate 103, an end panel 104, and a middle panel 10. Each panel is designed with multiple rows of connection holes at equal distances, which are used for mutual flexible connection between the beams, that is, modular combination connection, to adapt to the rudder wing 6 test of different sizes and specifications.

[0070] In some embodiments, Fig.15 As shown, the structural beam 10 may be provided with a guide rail adapter plate 14, a guide rail 15, a heating mechanism mounting seat 16, and an adjustment mechanism mounting seat 17. The guide rail 15 may be mounted on the structural beam 10 through the guide rail adapter plate 14, and as shown in FIG. Fig.17 As shown, a heating mechanism mounting seat 16 for mounting the heating mechanism 3 and an adjusting mechanism mounting seat 17 for mounting the adjusting mechanism 5 may be provided on the guide rail 15 .

[0071] The following is based on the attached Figure 1-17 A specific embodiment of the test device 100 for the rudder wing 6 of the present application is described as follows:

[0072] like Figure 1 and Figure 2 As shown, the test device 100 for the rudder wing 6 includes a base 1 , a clamping mechanism 2 , a heating mechanism 3 , an actuating mechanism 4 and an adjusting mechanism 5 .

[0073] like Fig.15 As shown, the base 1 includes a plurality of structural beams 10, a guide rail adapter plate 14, a guide rail 15, a heating mechanism mounting seat 16, and an adjustment mechanism mounting seat 17. Among them, the structural beam 10 may include a cross beam 11, a longitudinal beam 12 or a vertical beam 13. The cross beam 11, the longitudinal beam 12 and the vertical beam 13 have the same structure and are welded by an upper panel 101, a lower panel 102, a reinforcing plate 103, an end panel 104, and a middle panel 10. Each panel is designed with multiple rows of connection holes at equal distances, which are used for mutual flexible connection between the beams, i.e., modular combination connection, to adapt to the test of rudder wings 6 of different sizes.

[0074] The guide rail 15 is a finished product including a slider 18 that can slide freely on the rail and a guide rail body 19. The guide rail 15 is fixed to the base 1 through the guide rail adapter plate 14. The heating mechanism mounting seat 16 is fixed to the slider 18 through bolts, and the adjustment mechanism mounting seat 17 is fixed to the guide rail body 19 through bolts. The set screw 20 can relatively fix the slider 18 to the guide rail body 19 as needed.

[0075] like Figure 9-11 As shown, the clamping mechanism 2 includes a clamping base 21, a first slider 22, a second slider 23, a bearing seat 24, a clamping block 25, a bearing cover plate 26, a rotating shaft 27, and a bearing 28. The dovetail seat in the clamping mechanism is fixed to the longitudinal beam 12 in the base 1 by bolts to achieve a flexible connection with the base 1. The clamping base 21 can be a dovetail seat, and the base 1 is provided with a groove adapted to the dovetail seat to facilitate the installation of the dovetail seat, so as to enhance the connection stability between the clamping base 21 and the base 1.

[0076] The middle part of the rotating shaft 27 is designed to be a left and right trapezoidal thread, which respectively forms a thread pair with the first slider 22 and the second slider 23; the two ends of the rotating shaft 27 are respectively fixed to the end surface of the dovetail seat through the bearing 28, the bearing seat 24, and the end cover of the bearing 28 to form a rotating pair; the first slider 22 and the second slider 23 are placed in the dovetail seat to form a sliding pair, and the clamping block 25 is a V-shaped structure, which is fastened to the upper part of the first slider 22 and the second slider 23 by screws 34. When working, the two ends of the rotating shaft 27 are driven manually or by a motor to realize the rapid clamping of the tested product (i.e., the rudder wing 6).

[0077] like Figure 5 and Figure 6 As shown, the heating mechanism 3 includes a heating lamp 29, a first mounting frame 30, a second mounting frame 31, a heat insulation board 32, a connecting lug 33, and a screw 34, wherein the heating lamp 29 can be a quartz lamp, which is a finished product and can imitate the rudder wing 6 surface profile of the rudder wing 6. The power of the heating lamp 29 is 5KW-8KW, and the connection form of the two ends is a metal contact sheet, and it is powered by direct current.

[0078] The first installation frame 30 and the second installation frame 31 have the same structure, and are made of copper with good electrical and thermal conductivity. The inner cavity is hollow and is a welded structure. The front surface is processed into a number of evenly distributed grooves, and threaded holes are respectively designed at the grooves. The metal contact pieces at both ends of the quartz lamp are placed in the grooves, and the set screws 20 are used to limit the quartz lamp through the threaded holes at the grooves.

[0079] like Figure 7 and Figure 8 As shown, a water inlet pipe 35 is welded at the lower part of the rear surface of the first mounting frame 30 and the second mounting frame 31 for connecting cooling tap water, and a water outlet pipe 36 is welded at the upper part, and the cooling tap water flows out through the water outlet pipe 36, so as to achieve the purpose of cooling the first mounting frame 30 and the second mounting frame 31 under the test state of the test device.

[0080] The lower part of the first mounting frame 30 and the second mounting frame 31 is fixed with a transfer lug 37 by bolts. The transfer lug 37 is made of a composite material or a ceramic material and has electrical insulation properties. It is connected to the heating mechanism mounting seat 16 through a pin shaft to form a rotating secondary structure. The heating mechanism 3 can be rotated to be parallel to the rudder wing 6 surface to meet the requirement of uniform heating of each heating surface of the rudder wing 6.

[0081] The heat insulation board 32 is an asbestos board with good heat insulation performance, which is fixed to the first mounting frame 30 and the second mounting frame 31 by screws 34, effectively blocking the heat generated by the quartz lamp from radiating outward. The soft property of the asbestos board facilitates opening a hole for the pull rod of the actuating mechanism 4 to pass through.

[0082] The connecting lug 33 is made of a composite material or a ceramic material, has electrical insulation properties, is fixed to the rear surface of the first installation frame 30 by bolts, and is used to connect to the adjustment mechanism 5 .

[0083] When the heating mechanism 3 is working, the first mounting frame 30 and the second mounting frame 31 are connected to the two poles of the external power supply through wires, and the working power of the quartz lamp can be closed-loop regulated by the external power supply to control the overall heating temperature and temperature rise rate of the rudder wing 6.

[0084] like Figure 12-14 As shown, the actuating mechanism 4 includes a hydraulic actuator 38 , an actuator adapter plate 39 , a tension seat 40 , a lever plate 41 , a first pull rod 42 , a second pull rod 43 , a third pull rod 44 , and a fourth pull rod 45 .

[0085] The rear part of the hydraulic actuator 38 is connected to the vertical beam 13 on the base 1 through the actuator adapter plate 39, and can be flexibly fixed on the vertical beam 13 according to the external dimensions of the product being tested.

[0086] The third pull rod 44 and the fourth pull rod 45 respectively pass through the fixing holes of the tested product and are fixed to the lever plate 41 . The resultant force of the two pull rods is transmitted to the tension seat 40 through the second pull rod 43 .

[0087] The front part of the hydraulic actuator is connected to the tension seat 40 through a pin. The first pull rod 42 directly passes through the fixed hole of the tested product and is fixed to the tension seat 40. The combined force formed by the first pull rod 42 and the second pull rod 43 is transmitted to the hydraulic actuator 38 through the tension seat 40. The hydraulic actuator 38 is externally connected to a servo controller to control the loading load in real time.

[0088] Utilizing the principle of force and torque balance, the tie rod can be determined according to the number of load points, and the layout position of the upper-level tie rod is determined according to the torque balance. For example, the position of the second tie rod 43 is determined by the torque balance of the third tie rod 44 and the fourth tie rod 45, and the position of the actuator is determined according to the torque balance of the first tie rod 42 and the second tie rod 43.

[0089] The adjustment mechanism 5 includes a first adjustment rod 51, a second adjustment rod 52, and an adjustment nut 53, all of which are made of steel. The two ends of the adjustment nut 53 are respectively designed with a left-hand thread and a right-hand thread; one end of the first adjustment rod 51 is a fork-ear structure, connected with the connecting lug 33 through a pin to form a rotation pair, and the other end is designed as a left-hand thread, forming a thread pair with the adjustment nut 53; one end of the second adjustment rod 52 is a fork-ear structure, connected with the adjustment mechanism mounting seat 17 through a pin to form a rotation pair, and the other end is designed as a right-hand thread, forming a thread pair with the adjustment nut 53. By driving the adjustment nut 53 manually or by a motor, the angle adjustment of the heating mechanism 3 can be quickly achieved.

[0090] Here, the main operation flow of the test process based on the test device 100 for the rudder wing 6 is described in detail as follows:

[0091] a. Install the base 1 according to the structural dimensions of the rudder wing 6;

[0092] b. Fix the clamping mechanism 2 on the base 1;

[0093] c. Fix the heating mechanism 3 and the adjusting mechanism 5 on the base 1;

[0094] d. Adjust the guide rail 15, the slider 18 and the adjusting mechanism 5 on the base 1 to make the heating mechanism 3 away from the clamping mechanism 2 so as to install the rudder wing 6 to be tested;

[0095] e. Quickly clamp the rudder wing 6 test product in the clamping mechanism 2 manually or by electric motor drive;

[0096] f. Adjust the adjustment mechanism 5 on the base 1 so that the heating mechanism 3 is close to the clamping mechanism 2 and the heating angle of the heating mechanism 3 is parallel to the profile of the rudder wing 6;

[0097] g. Reliably connect the actuating mechanism 4 to the base 1 and the product;

[0098] h. Connect the water inlet pipe 35 in the heating mechanism 3 to cooling tap water, and connect the water outlet pipe 36 to the drain;

[0099] i. Turn on the power supply to heat the rudder wing 6, and start the servo controller to apply a tensile load to the rudder wing 6 to implement a force-heat coupling test of the rudder wing 6.

[0100] Therefore, this application has at least the following technical effects:

[0101] 1. The base 1 is a modular structure and can be flexibly assembled into a required base 1 according to the size of the rudder wing 6 structure.

[0102] 2. The clamping mechanism 2 is flexibly fixed on the longitudinal beam 12 in the base 1, and the rudder wing 6 test product is quickly clamped in the clamping mechanism 2 by manual or motor drive.

[0103] 3. The heating mechanism 3 is connected to the guide rail 15 slider 18 in the base 1 through a pin to form a revolute pair, and is symmetrically arranged on both sides of the rudder wing 6 test product. The distance from the product can be achieved by adjusting the guide rail 15 slider 18 in the base 1, and the heating angle with the product profile can be achieved by adjusting the mechanism 5. In addition, the shape of the quartz lamp in the heating mechanism 3 can be manufactured according to the profile of the rudder wing 6, and the test rudder wing 6 profile is heated evenly;

[0104] 4. One end of the actuating mechanism 4 is flexibly fixed on the vertical beam 13 of the base 1, and the other end is fastened to the test product of the rudder wing 6. By using the principle of moment balance, the multi-point loads in the tested product can be synthesized into one actuator load by adding a multi-stage lever structure;

[0105] 5. One end of the adjusting mechanism 5 is connected to the adjusting mechanism mounting seat 17 in the base 1 to form a rotating pair, and the other end is connected to the connecting lug 33 in the heating mechanism 3 to form a rotating pair. The adjusting nut 53 in the adjusting mechanism 5 is driven manually or by an electric motor to achieve the heat radiation angle in the heating mechanism 3 being parallel to the rudder wing 6 surface, thereby improving the heating efficiency.

[0106] It should be noted that the structure in the above embodiment is only used as a preferred embodiment for illustration and does not represent a limitation thereto.

[0107] It should be noted that in the above embodiments, the description of each embodiment has its own emphasis, and for parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0108] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application.

[0109] Although the preferred embodiments of this specification have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of this specification.

[0110] Obviously, those skilled in the art can make various changes and modifications to this specification without departing from the spirit and scope of this specification. Thus, if these modifications and variations of this specification fall within the scope of the claims of this specification and their equivalents, this specification is also intended to include these modifications and variations.

Claims

1. A test device (100) for a rudder wing, characterized in that: include: Base (1); A heating mechanism (3), the heating mechanism (3) being movably mounted on the base (1) and being provided with a heating space for heating the rudder wing; An adjusting mechanism (5), the adjusting mechanism (5) is connected between the base (1) and the heating mechanism (3), and the adjusting mechanism (5) is configured to adjust the heating distance between the heating mechanism (3) and the rudder wing and / or the heat radiation angle when heating the rudder wing.

2. The test device (100) for rudder wing according to claim 1, characterized in that: The adjustment mechanism (5) comprises a first adjustment rod (51), a second adjustment rod (52) and an adjustment nut (53); the first adjustment rod (51) is hinged to the heating mechanism (3); the second adjustment rod (52) is hinged to the base (1); and two ends of the adjustment nut (53) are respectively threadedly engaged with the first adjustment rod (51) and the second adjustment rod (52).

3. The test device (100) for rudder wing according to claim 2, characterized in that: Two ends of the adjusting nut (53) are respectively sleeved on the first adjusting rod (51) and the second adjusting rod (52).

4. The test device (100) for rudder wing according to claim 1, characterized in that: The heating mechanism (3) comprises a first mounting frame (30), a second mounting frame (31) and a heating lamp (29); the heating space is defined between the first mounting frame (30) and the second mounting frame (31); the heating lamp (29) is provided on the side of the first mounting frame (30) and the second mounting frame (31) facing each other; the first mounting frame (30) and / or the second mounting frame (31) are hinged to the base (1); and the angle between the first mounting frame (30) and / or the second mounting frame (31) and the base (1) is adjustable.

5. The test device (100) for rudder wing according to claim 4, characterized in that: The heating lamp (29) is detachably mounted on the first mounting frame (30) and the second mounting frame (31), and the heating surface of the heating lamp (29) is designed to conform to the shape of the rudder wing.

6. The test device (100) for rudder wing according to claim 1, characterized in that: Also includes: A clamping mechanism (2), the clamping mechanism (2) is connected to the base (1) and comprises a clamping base (21) and two clamping blocks (25), the clamping base (21) is connected to the base (1), the two clamping blocks (25) are both mounted on the clamping base (21), and at least one of the two clamping blocks (25) can slide relative to the other along the clamping base (21), so that the two clamping blocks (25) clamp or release the rudder wing.

7. The test device (100) for rudder wing according to claim 6, characterized in that: The clamping mechanism (2) further comprises a rotating shaft (27) and a bearing (28); the bearing (28) is mounted on the clamping base (21) and sleeved on the rotating shaft (27); the rotating shaft (27) passes through at least one of the clamping blocks (25) and is threadedly engaged with the clamping block (25).

8. The test device (100) for rudder wing according to claim 1, characterized in that: It also includes an actuating mechanism (4), which is installed on the base (1) and includes a hydraulic actuator (38) and a first pull rod (42), the output end of the hydraulic actuator (38) is connected to the first pull rod (42), and the first pull rod (42) is suitable for passing through one side of the rudder wing to the other side of the rudder wing and cooperating with the other side of the rudder wing in a limiting manner.

9. The test device (100) for a rudder wing according to claim 8, characterized in that: The actuating mechanism (4) further comprises a lever plate (41), a second pull rod (43), a third pull rod (44) and a fourth pull rod (45), wherein the second pull rod (43) is connected between the output end of the hydraulic actuator (38) and the lever plate (41), the third pull rod (44) and the fourth pull rod (45) are both connected to the lever plate (41), and the third pull rod (44) and the fourth pull rod (45) are both suitable for passing through from one side of the rudder wing to the other side of the rudder wing and being limitedly matched with the other side of the rudder wing.

10. The test device (100) for a rudder wing according to any one of claims 1 to 9, characterized in that: The base (1) comprises a plurality of structural beams (10), and any two of the structural beams (10) are detachably connected.

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