Thermal examination device for aviation aircraft

Abstract

The utility model discloses an aviation aircraft thermal examination device, and relates to the technical field of thermal examination devices, the aviation aircraft thermal examination device comprises a base, a rotating mechanism, a clamping mechanism and a flame control system, the upper surface of the base is provided with a traveling wave tube noise device, a telescoping mechanism and a gas transmission mechanism, and the traveling wave tube noise device is fixedly connected to the upper surface of the left end of the base; the telescopic mechanism comprises a fixing disc, the fixing disc is fixedly connected to the upper surface of the right end of the base, two hydraulic cylinders are fixedly connected to the left side face of the fixing disc, piston rods are installed on the left side faces of the hydraulic cylinders, connecting rods are fixedly connected to the ends, away from the hydraulic cylinders, of the piston rods, and annular plates are fixedly connected to the ends, away from the piston rods, of the connecting rods. A plurality of flame heating guns are mounted on the inner side wall of the annular plate; through cooperation of the structures, thermal examination can be carried out on different positions of the aviation aircraft, and the thermal examination efficiency and effect are improved.

Description

Technical Field

[0001] This utility model belongs to the technical field of thermal testing devices, specifically a thermal testing device for aircraft. Background Technology

[0002] Aircraft thermal testing is a testing process that evaluates the performance of an aircraft or its components in high-temperature environments. This process is typically achieved using specialized thermal testing equipment to simulate the high-temperature conditions encountered by the aircraft during flight or specific mission environments.

[0003] Utility model CN203658073U discloses a flame-type thermal-noise composite environment testing device, comprising a traveling wave tube noise device, a noise testing system, and a thermal testing device, used for conducting thermal-noise composite environment tests on test specimens. The thermal testing device is a flame-type heating device. The flame-type thermal-noise composite environment testing device uses methane and oxygen to generate the flame. The thermal testing device includes: a gas storage system, a flame pipeline system, a flame heating gun, a flame control system, flame monitors, a flame heating gun mounting plate, and a temperature testing system. The flame heating gun is mounted on the side wall of the traveling wave tube via the flame heating gun mounting plate and extends into the traveling wave tube. Two flame monitors are arranged for the flame heating gun in the upward and downward airflow directions. Under the control of the flame control system, the gas storage system supplies methane and oxygen gas to the flame heating gun through the flame pipeline system. The temperature testing system includes a temperature sensor and a signal conditioner, tests the temperature of the test specimen, and outputs the test information to the flame control system for flame control.

[0004] In the process of developing this application, the following problems were found with this technology: When conducting thermal testing on the aircraft in the above patent documents, the test fixture and the flame heating gun are installed at specific positions inside the traveling wave tube noise device; and different materials may be used in different positions of the aircraft. Passing the thermal test at the same fixed position does not mean that other positions of the aircraft are also qualified. Therefore, a comprehensive thermal test is required. However, when conducting thermal testing in the above documents, only the fixed position can be tested. Other positions of the aircraft may have blind spots that cannot be touched by the flame or insufficient temperature for thermal testing at distant positions, which affects the efficiency and effectiveness of the overall thermal test of the aircraft.

[0005] Therefore, a thermal testing device for aircraft is proposed. Utility Model Content

[0006] The purpose of this utility model is to provide a thermal testing device for aircraft, which enables thermal testing of different positions of aircraft and improves the efficiency and effectiveness of thermal testing.

[0007] The technical solution adopted in this utility model is as follows:

[0008] A thermal testing device for an aircraft includes a base, a rotating mechanism, a clamping mechanism, and a flame control system. A traveling wave tube noise device, a telescopic mechanism, and a gas supply mechanism are installed on the upper surface of the base. The traveling wave tube noise device is fixedly connected to the upper surface of the left end of the base.

[0009] The rotating mechanism includes a motor, which is fixedly connected to the outer left side surface of the base, and a rotating rod is fixedly connected to the output end of the motor.

[0010] The clamping mechanism is located inside the base. The clamping mechanism includes a housing. The end of the rotating rod away from the first motor extends movably into the interior of the base and is fixedly connected to the housing. A limit groove is provided on the right side of the housing. The second motor is fixedly connected to the inner bottom surface of the housing. A lead screw is fixedly connected to the output end of the second motor. The end of the lead screw away from the second motor is rotatably connected to the inner wall of the top of the housing through a bearing. The lead screw has two threaded sections with opposite directions of rotation. Clamping plates are threadedly connected to the two threaded sections of the lead screw respectively. There are two clamping plates. A clamping block is fixedly connected to one side of the two clamping plates with their ends away from the lead screw close to each other.

[0011] The telescopic mechanism includes a fixed plate, which is fixedly connected to the upper right surface of the base. Two hydraulic cylinders are fixedly connected to the left side of the fixed plate. A piston rod is installed on the left side of the hydraulic cylinder. A connecting rod is fixedly connected to the end of the piston rod away from the hydraulic cylinder. An annular plate is fixedly connected to the end of the connecting rod away from the piston rod. Several flame heating guns are installed on the inner sidewall of the annular plate.

[0012] Furthermore, several of the flame heating guns are equidistantly arranged on the inner sidewall of the annular plate, and a temperature sensor is installed on the inner sidewall of the annular plate between two adjacent flame heating guns.

[0013] Furthermore, the outer surface of the clamping plate is slidably connected to the inner surface of the limiting groove.

[0014] Furthermore, the gas supply mechanism includes a gas storage system, which is fixedly connected to the upper surface of the base on the right side of the fixed plate. The gas outlet of the gas storage system is connected to a gas supply pipe. A gas guide channel is opened inside the connecting rod. One end of the gas guide channel is connected to the flame heating gun, and the end of the gas supply pipe away from the gas storage system is connected to the gas guide channel.

[0015] Furthermore, a solenoid valve is installed on the outer surface of the gas pipeline near the gas storage system.

[0016] Furthermore, the inner wall of the traveling wave tube noise device is covered with a rigid heat-insulating layer.

[0017] In summary, due to the adoption of the above technical solution, the beneficial effects of this utility model are:

[0018] In this invention, when conducting thermal testing on an aircraft, the aircraft can be placed inside the traveling wave tube noise device after passing through the center of the annular plate. At this point, motor two can be activated to rotate the lead screw. The two clamping plates will then move closer together under the rotation of the lead screw, thereby causing the two clamping blocks to move closer together and clamp the aircraft. Next, motor one can be activated to rotate the rotating rod, which in turn rotates the clamping mechanism, allowing the clamped aircraft to rotate so that the flame heating gun can perform thermal testing on different positions of the rotating aircraft. Simultaneously, the hydraulic cylinder can be activated to move the piston rod laterally, causing the connecting rod to move laterally. This laterally moving connecting rod causes the annular plate to move laterally along the outside of the aircraft, allowing the flame heating gun to perform thermal testing on different positions of the aircraft. Through the combination of these structures, thermal testing can be performed on different positions of the aircraft, improving the efficiency and effectiveness of the thermal testing. Attached Figure Description

[0019] Figure 1 This is a cross-sectional view of the present invention;

[0020] Figure 2 This is a schematic diagram of the telescopic mechanism in this utility model;

[0021] Figure 3 In this utility model Figure 1 Enlarged view of point A.

[0022] The diagram shows the following components: 1-base, 2-traveling wave tube noise device, 3-rotating mechanism, 4-clamping mechanism, 5-telescopic mechanism, 6-gas supply mechanism, 31-motor one, 32-rotating rod, 41-box, 42-motor two, 43-lead screw, 44-clamping plate, 45-limiting slide groove, 46-clamping block, 51-fixed plate, 52-hydraulic cylinder, 53-piston rod, 54-connecting rod, 55-gas guide cavity, 56-annular plate, 57-flame heating gun, 58-temperature sensor, 61-gas storage system, 62-gas supply pipe, 63-solenoid valve. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below in conjunction with the embodiments of this utility model. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model. Example

[0024] Reference Figures 1-3 A thermal testing device for an aircraft includes a base 1, a rotating mechanism 3, a clamping mechanism 4, and a flame control system. A traveling wave tube noise device 2, a telescopic mechanism 5, and a gas supply mechanism 6 are mounted on the upper surface of the base 1. The traveling wave tube noise device 2 is fixedly connected to the upper left side of the base 1. A rigid heat-insulating layer is laid on the inner wall of the traveling wave tube noise device 2. The rotating mechanism 3 includes a motor 31, which is fixedly connected to the outer left side of the base 1. A rotating rod 32 is fixedly connected to the output end of the motor 31. The clamping mechanism 4 is located inside the base 1 and includes a housing 41. The end of the rotating rod 32 away from the motor 31 extends movably into the interior of the base 1 and is fixedly connected to the housing 41. A limit groove 45 is provided on the right side of the housing 41. A second motor 42 is fixedly connected to the inner bottom surface of the housing 41. A lead screw 43 is fixedly connected to the output end of the second motor 42. The end of the lead screw 43 away from the second motor 42 passes through… The bearing is rotatably connected to the inner wall of the top of the housing 41. The lead screw 43 has two threaded sections with opposite directions of rotation. Clamping plates 44 are threadedly connected to the two threaded sections with opposite directions of rotation of the lead screw 43. There are two clamping plates 44. The two clamping plates 44 are fixedly connected to a clamping block 46 on one side, with the ends away from the lead screw 43 close to each other. The outer surface of the clamping plate 44 is slidably connected to the inner surface of the limiting slide groove 45. Specifically, when conducting a thermal test on the aircraft, the device is first connected to an external power source. The aircraft can be placed inside the traveling wave tube noise device 2. At this time, the motor 2 can be started to make the lead screw 43 rotate. At this time, the two clamping plates 44 will move closer to each other under the action of the rotation of the lead screw 43, thereby driving the two clamping blocks 46 to move closer to each other and clamp the aircraft. Then, the motor 1 can be started to make the rotating rod 32 drive the clamping mechanism 4 to rotate, thereby driving the clamped aircraft to rotate, so as to conduct a thermal test on the aircraft.

[0025] Reference Figures 1-3The telescopic mechanism 5 includes a fixed plate 51, which is fixedly connected to the upper right surface of the base 1. Two hydraulic cylinders 52 are fixedly connected to the left side of the fixed plate 51. A piston rod 53 is installed on the left side of the hydraulic cylinders 52. A connecting rod 54 is fixedly connected to the end of the piston rod 53 away from the hydraulic cylinder 52. An annular plate 56 is fixedly connected to the end of the connecting rod 54 away from the piston rod 53. Several flame heating guns 57 are installed on the inner side wall of the annular plate 56. Specifically, activating the hydraulic cylinders 52 can cause the piston rod 53 to drive the connecting rod 54 to move laterally. The laterally moving connecting rod 54 can drive the annular plate 56 to move laterally along the outside of the aircraft, so that the flame heating guns 57 can perform thermal testing on different positions of the aircraft. Through the cooperation of the above structures, thermal testing can be performed on different positions of the aircraft, improving the efficiency and effectiveness of thermal testing.

[0026] Reference Figures 1-3 Several flame heating guns 57 are equidistantly arranged on the inner wall of the annular plate 56. Temperature sensors 58 are installed on the inner wall of the annular plate 56 between two adjacent flame heating guns 57. The gas supply mechanism 6 includes a gas storage system 61, which is fixedly connected to the upper surface of the base 1 on the right side of the fixed plate 51. The gas outlet of the gas storage system 61 is connected to a gas supply pipe 62. A gas guide channel 55 is opened inside the connecting rod 54. One end of the gas guide channel 55 is connected to the flame heating gun 57. The end of the gas supply pipe 62 away from the gas storage system 61 is connected to the gas guide channel 55. A solenoid valve 63 is installed on the outer surface of the end of the gas supply pipe 62 near the gas storage system 61. Specifically, the solenoid valve 63 is opened by the flame control system so that the gas in the gas storage system 61 passes through the gas supply pipe 62 and the gas guide channel 55 and is sprayed out from the flame heating gun 57 for combustion, so that the flame heating gun 57 can perform thermal testing on different positions of the rotating aircraft.

[0027] The implementation principle of an embodiment of an aircraft thermal testing device according to this application is as follows:

[0028] During the thermal testing of the aircraft, the device is first connected to an external power source. The aircraft can then be placed inside the traveling wave tube noise device 2 after passing through the middle of the annular plate 56. At this time, motor 2 42 can be started to rotate the lead screw 43. The two clamping plates 44 will move closer together under the rotation of the lead screw 43, thereby causing the two clamping blocks 46 to move closer together and clamp the aircraft. Then, motor 1 31 can be started to rotate the rotating rod 32 to rotate the clamping mechanism 4, thereby rotating the clamped aircraft. Then, the solenoid valve 63 is opened through the flame control system to activate the gas storage system. The gas from 61 passes through the gas supply pipe 62 and the gas guide cavity 55 and is then ejected from the flame heating gun 57 for combustion, so that the flame heating gun 57 can perform thermal testing on different positions of the rotating aircraft. At the same time, the hydraulic cylinder 52 can be activated to cause the piston rod 53 to drive the connecting rod 54 to move laterally. The laterally moving connecting rod 54 can drive the annular plate 56 to move laterally along the outside of the aircraft, so that the flame heating gun 57 can perform thermal testing on different positions of the aircraft. Through the cooperation of the above structures, thermal testing can be performed on different positions of the aircraft, improving the efficiency and effectiveness of thermal testing.

[0029] The above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A thermal testing device for aircraft, comprising a base (1), a rotating mechanism (3), a clamping mechanism (4), and a flame control system, characterized in that: The upper surface of the base (1) is equipped with a traveling wave tube noise device (2), a telescopic mechanism (5) and a gas supply mechanism (6), and the traveling wave tube noise device (2) is fixedly connected to the upper surface of the left end of the base (1). The rotating mechanism (3) includes a motor (31), which is fixedly connected to the outer left side of the base (1), and the output end of the motor (31) is fixedly connected to a rotating rod (32). The clamping mechanism (4) is located inside the base (1). The clamping mechanism (4) includes a housing (41). The end of the rotating rod (32) away from the motor (31) extends movably into the interior of the base (1) and is fixedly connected to the housing (41). A limit groove (45) is provided on the right side of the housing (41). The inner bottom surface of the housing (41) is fixedly connected to the motor (42). The output end of the motor (42) is fixedly connected to a lead screw. (43) The end of the lead screw (43) away from the motor (42) is rotatably connected to the inner wall of the top of the housing (41) through a bearing. The lead screw (43) has two threaded sections with opposite directions of rotation. Clamping plates (44) are threadedly connected to the two threaded sections of the lead screw (43) respectively. There are two clamping plates (44). The clamping blocks (46) are fixedly connected to one side of the two clamping plates (44) away from the lead screw (43). The telescopic mechanism (5) includes a fixed plate (51), which is fixedly connected to the upper right surface of the base (1). Two hydraulic cylinders (52) are fixedly connected to the left side of the fixed plate (51). A piston rod (53) is installed on the left side of the hydraulic cylinder (52). A connecting rod (54) is fixedly connected to the end of the piston rod (53) away from the hydraulic cylinder (52). An annular plate (56) is fixedly connected to the end of the connecting rod (54) away from the piston rod (53). Several flame heating guns (57) are installed on the inner side wall of the annular plate (56).

2. The thermal testing device for an aircraft as described in claim 1, characterized in that: Several flame heating guns (57) are equidistantly arranged on the inner sidewall of the annular plate (56), and a temperature sensor (58) is installed on the inner sidewall of the annular plate (56) between two adjacent flame heating guns (57).

3. The thermal testing device for aircraft as described in claim 1, characterized in that: The outer surface of the clamping plate (44) is slidably connected to the inner surface of the limiting groove (45).

4. The thermal testing device for an aircraft as described in claim 1, characterized in that: The gas delivery mechanism (6) includes a gas storage system (61), which is fixedly connected to the upper surface of the base (1) on the right side of the fixed plate (51). The gas outlet of the gas storage system (61) is connected to a gas delivery pipe (62). A gas guide channel (55) is provided inside the connecting rod (54). One end of the gas guide channel (55) is connected to the flame heating gun (57). The end of the gas delivery pipe (62) away from the gas storage system (61) is connected to the gas guide channel (55).

5. The thermal testing device for an aircraft as described in claim 4, characterized in that: A solenoid valve (63) is installed on the outer surface of the gas pipeline (62) near the gas storage system (61).

6. The thermal testing device for an aircraft as described in claim 1, characterized in that: The inner wall of the traveling wave tube noise device (2) is covered with a rigid heat-resistant layer.

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