A combined aerodynamic thermal-vibration test device for small wing-rudder structures

Abstract

The present invention relates to the technical field of thermal environment testing of small airfoil structures of high-speed aircraft, and in particular to an aerodynamic thermal-vibration combined testing device for small wing-rudder structures. The exciter and the slide base plate of the testing device are arranged on a base; the horizontal slide is slidably connected to the slide base plate, and the exciter is connected to the horizontal slide through a rigid connecting rod; the test piece is fixed on the horizontal slide, and the test piece is arranged relative to the nozzle of the arc heater. The arc heater is used to heat the air, and the heating efficiency is very high. The maximum temperature of the supersonic airflow obtained can reach 3000-6000℃, which far exceeds the heating capacity limit of static heating devices such as quartz lamps. The high-temperature, high-speed and high-shear airflow is sprayed onto the surface of the test piece, and the test environment is closer to the actual service environment of the airfoil structure and materials. The test results are more valuable for the safety and reliability design of hypersonic aircraft.

Description

Technical Field

[0001] The invention relates to the technical field of thermal environment testing of small wing-shaped structures of high-speed aircraft, and in particular to an aerodynamic thermal-vibration combined testing device for a small wing-rudder structure. Background Art

[0002] With the continuous increase of the Mach number of aircraft design, the impact of the aerodynamic heating problem on the aircraft structure has become more and more obvious. For example, when a high-speed aircraft quickly passes through the atmosphere, it is affected by the flow resistance of the air and strongly compresses the air in front, thereby converting kinetic energy into thermal energy. The surface temperature of the aircraft can reach about 600-2000℃. In view of the different high-temperature thermal environments faced by different parts of the aircraft, different thermal protection materials need to be used to thermally protect the aircraft structure. In addition, during the long-term flight of the aircraft, the attitude control structures such as wings and rudders will vibrate continuously for a long time. The high temperature generated by aerodynamic heating will change the elastic properties of materials and structures, and will also cause thermal stress inside the structure, causing deformation of the structure, thereby causing changes in the vibration characteristics such as the natural frequency and modal vibration shape of the wings and rudders of high-speed aircraft structures, which will have a great impact on the flutter characteristics and control characteristics of the aircraft, causing safety accidents. Therefore, it is very important to conduct thermal-vibration joint ground tests on structural parts such as wings and rudders.

[0003] The existing thermal-vibration joint test generally uses quartz lamp radiation heating to provide a thermal environment. Its heating capacity is limited, which is far from the aerodynamic heating environment of thousands of degrees Celsius that the aircraft actually faces. The heating method is obviously inconsistent with the aerodynamic thermal environment during actual service, and it cannot simulate the strong shear effect of high-speed airflow on the aircraft surface during flight. The heating equipment has thermal hysteresis and cannot accurately simulate the high heating rate nonlinear heating environment faced by the aircraft in flight states such as large maneuvering and changing orbits. The vibration load is loaded using a vibration table. The standard vibration table and the supporting power amplifier are generally large in size, have high requirements for power supply and working environment, are troublesome to install and disassemble, and have relatively large operating noise. There are many small structural parts on high-speed aircraft, such as small wings and rudder structures; in addition, the thermal-vibration joint assessment of heat-resistant materials on aircraft is generally carried out by cutting smaller sizes, such as 100*100mm specifications. It is very inconvenient to use existing test equipment to conduct vibration assessment of small structural parts and materials in a thermal environment, and there are obvious problems of high testing costs and low assessment efficiency. Therefore, there is an urgent need to design a small-scale aerodynamic thermal-vibration combined test system. Summary of the invention

[0004] The first object of the present invention is to provide a small wing-rudder structure aerodynamic thermal-vibration combined test device, which can solve the problems existing in the existing test devices;

[0005] The present invention provides a small wing-rudder structure aerodynamic thermal-vibration combined test device, which comprises a base, a slide base plate, a horizontal slide, a heat insulation plate, a vibration exciter, a rigid connecting rod and an arc heater;

[0006] The vibration exciter and the slide base plate are arranged on the base;

[0007] The horizontal slide is slidably connected to the slide bottom plate, and the vibration exciter is connected to the horizontal slide via a rigid connecting rod;

[0008] The test piece is fixed on a horizontal slide, and the test piece is arranged opposite to the nozzle of the arc heater.

[0009] Preferably, the vibrator and the slide base plate are fixed to the base by bolts.

[0010] Preferably, two pairs of optical axis supports are arranged on the bottom plate of the slide, and an optical axis is passed through the two optical axis supports arranged opposite to each other;

[0011] Two slide blocks are provided on each optical axis. The optical axis support is fixed to the bottom plate of the slide table by bolts, and the horizontal slide table is fixed to the four slide blocks by bolts.

[0012] Preferably, one end of the rigid connecting rod is threadedly connected to the horizontal slide, and the other end is connected to the adapter frame of the exciter by bolts.

[0013] Preferably, a slide protection plate is provided on the upper portion of the horizontal slide, and the slide protection plate is fixed to the horizontal slide by high-temperature curing glue.

[0014] Preferably, the base is also provided with a heat insulation plate, a slide base plate, and the components on the slide base plate and the exciter are distributed on both sides of the heat insulation plate.

[0015] Preferably, the small wing-rudder structure aerodynamic thermal-vibration combined test device also includes an infrared pyrometer, a high-speed camera, a computer, a vibration controller, an acceleration sensor and a power amplifier, wherein the infrared pyrometer and the high-speed camera are electrically connected to the computer, the acceleration sensor and the power amplifier are electrically connected to the vibration controller, and the power amplifier is electrically connected to the exciter.

[0016] Preferably, the frequency range of the exciter is 0-3kHz, and the maximum excitation force is 500N;

[0017] The vibration controller outputs random vibration, sinusoidal vibration, and random and sinusoidal vibration patterns;

[0018] The infrared pyrometer is selected according to the test conditions as a monochrome infrared pyrometer with a wavelength response of 1.6 μm and a temperature measurement range of 450-2250°C; or a response wavelength of 1.0 μm and a temperature measurement range of 540-3000°C;

[0019] The acquisition frequency of the high-speed camera should be greater than 5000 frames.

[0020] Preferably, the arc heater is a tubular low-enthalpy arc heater, a segmented medium-enthalpy arc heater, or a laminated high-enthalpy arc heater.

[0021] Preferably, a cooling water channel is provided on the horizontal slide, and the cooling water channel is arranged along the horizontal direction of the horizontal slide, and the diameter of the water channel is less than or equal to 2 / 3 of the thickness of the horizontal slide.

[0022] Beneficial effects: The test device uses an arc heater to heat the air, which has a very high heating efficiency. The maximum temperature of the supersonic airflow can reach 3000-6000℃, far exceeding the heating capacity limit of static heating devices such as quartz lamps. The high-temperature, high-speed and high-shear airflow is sprayed onto the surface of the test piece. The test environment is closer to the actual service environment of the airfoil structure and materials. The test results are more valuable for the safety and reliability design of hypersonic aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0024] Figure 1 A schematic diagram of a disassembled state of an aerodynamic thermal-vibration combined test device for a small wing-rudder structure provided in a specific embodiment of the present invention;

[0025] Figure 2 An assembly diagram of a small wing-rudder structure aerodynamic thermal-vibration combined test device provided for a specific embodiment of the present invention;

[0026] Description of reference numerals:

[0027] 1. Arc heater; 2. Heat insulation board; 3. Adapter frame; 4. Vibrator; 5. Base; 6. Rigid connecting rod; 7. Slider; 8. Slide base plate; 9. Optical axis; 10. Optical axis support; 11. Acceleration sensor; 12. Horizontal slide; 13. Slide protection plate; 14. Test piece; 15. Infrared pyrometer; 16. High-speed camera; 17. Computer; 18. Vibration controller; 19. Power amplifier. DETAILED DESCRIPTION

[0028] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0029] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0030] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined. In addition, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0031] like Figure 1 , Figure 2 As shown, in this embodiment, a small wing-rudder structure aerodynamic thermal-vibration combined test device is provided, which includes a base 5, a slide base plate 8, a horizontal slide 12, a heat insulation plate 2, an exciter 4, a rigid connecting rod 6 and an arc heater 1.

[0032] The vibration exciter 4 and the slide base plate 8 are arranged on the base 5 , the horizontal slide 12 is slidably connected to the slide base plate 8 , and the vibration exciter 4 is connected to the horizontal slide 12 via a rigid connecting rod 6 .

[0033] The test piece 14 is fixed on the horizontal slide table 12 , and the test piece 14 is arranged opposite to the nozzle of the arc heater 1 .

[0034] The test device uses an arc heater 1 to heat the air, and the heating efficiency is very high. The maximum temperature of the supersonic airflow can reach 3000-6000°C, far exceeding the heating capacity limit of static heating devices such as quartz lamps. The high-temperature, high-speed and high-shear airflow is sprayed onto the surface of the test piece 14. The test environment is closer to the actual service environment of the airfoil structure and materials. The test results are more valuable for the safety and reliability design of hypersonic aircraft.

[0035] The exciter 4 and the slide base plate 8 are fixed to the base 5 by bolts, that is, the test device adopts a modular integrated design, and all components of the vibration table are integrated into the base 5, which has a small size and high space utilization.

[0036] The specific connection structure of the horizontal slide 12 and the slide base plate 8 is that two pairs of optical axis supports 10 are arranged on the slide base plate 8, and the optical axis 9 is passed through the two optical axis supports 10 arranged opposite to each other;

[0037] Two slide blocks 7 are provided on each optical axis 9 . The optical axis support 10 is fixed on the slide base plate 8 by bolts. The horizontal slide 12 is fixed on the four slide blocks 7 by bolts.

[0038] One end of the rigid connecting rod 6 is threadedly connected to the horizontal slide 12, and the other end is connected to the adapter frame 3 of the exciter 4 by bolts.

[0039] All components on the vibration table where the slide base plate 8 and other components are located are integrated onto the base 5 by bolts. The replacement of each component can be completed quickly according to the specific test task, which effectively improves the test efficiency.

[0040] A slide protection plate 13 is provided on the upper portion of the horizontal slide 12 , and the slide protection plate 13 is fixed on the horizontal slide 12 by high temperature curing glue.

[0041] The base 5 is also provided with a heat insulation plate 2 , a slide base plate 8 , and components on the slide base plate 8 and the exciter 4 are distributed on both sides of the heat insulation plate 2 .

[0042] The provision of protective components such as the heat insulation plate 2 and the slide protection plate 13 can prevent high-temperature air from causing damage to components such as the vibrator 4.

[0043] The arc heater 1 is a tubular low-enthalpy arc heater 1 , may also be a segmented medium-enthalpy arc heater 1 , or may also be a laminated high-enthalpy arc heater 1 .

[0044] The arc heater 1 is a tubular low-enthalpy arc heater 1 , may also be a segmented medium-enthalpy arc heater 1 , or may also be a laminated high-enthalpy arc heater 1 .

[0045] The frequency range of the exciter 4 is 0-3kHz, and the maximum excitation force output is 500N.

[0046] The vibration controller 18 outputs random vibration, sinusoidal vibration, and a pattern of random and sinusoidal vibration.

[0047] To ensure effective transmission of vibration, the entire assembly should have greater rigidity. The diameter of the rigid connecting rod 6 is generally M8, the length is between 45 and 70 mm, and the material is preferably 45# steel. This embodiment reduces the mass of the horizontal slide 12, strengthens the strength of the connecting rod, and uses a small vibrator 4 to achieve a vibration frequency of up to 2 kHz.

[0048] In order to ensure the effective transmission of vibration, the whole assembly should have a large rigidity, and the rigidity of the adapter frame 3 should also be as large as possible, with a thickness between 10 and 15 mm, and 45# steel is preferably used as the material.

[0049] To ensure greater acceleration during the test, the volume and mass of the horizontal slide 12 should be as small as possible, with a preferred size of 120*120*15mm, and aluminum alloy is preferred as the material; a cooling water channel is opened in the horizontal direction, and the diameter of the water channel is less than or equal to 2 / 3 of the thickness of the horizontal slide 12; at the same time, the area of ​​the horizontal slide 12 must be greater than or equal to the area enclosed by the four optical axis supports 10.

[0050] The slide protection plate 13 is preferably made of mullite fiber insulation tile material. If the test temperature is less than or equal to 650°C, the surface is preferably sprayed with a high reflectivity coating; if the test temperature is greater than 650°C, the surface is preferably sprayed with a high emissivity coating. And its size should be larger than the horizontal slide 12, with a preferred size of 150*150mm and a thickness of 10-15mm.

[0051] The vertical height of the center axis of the M8 internal threaded hole on the horizontal slide 12 is consistent with the height of the center axis of the openings on both sides of the adapter frame 3.

[0052] The aerodynamic thermal-vibration combined test device for a small wing-rudder structure also includes an infrared pyrometer 15, a high-speed camera 16, a computer 17, a vibration controller 18, an acceleration sensor 11 and a power amplifier 19, wherein the infrared pyrometer 15 and the high-speed camera 16 are electrically connected to the computer 17, the acceleration sensor 11 and the power amplifier 19 are electrically connected to the vibration controller 18, and the power amplifier 19 is electrically connected to the exciter 4.

[0053] The infrared pyrometer 15 can be selected according to the test conditions as a monochrome infrared pyrometer 15 with a wavelength response of 1.6 μm and a temperature measurement range of 450-2250° C.; or a response wavelength of 1.0 μm and a temperature measurement range of 540-3000° C.

[0054] In order to obtain a clear morphology of the surface of the test piece 14 under high-frequency vibration conditions, the acquisition frequency of the high-speed camera 16 should be greater than 5000 frames.

[0055] The specific method of using the aerodynamic thermal-vibration combined test device for small wing-rudder structures is as follows: first, operate the vibration controller 18 on the computer 17 to input the vibration target spectrum, and the signal drives the exciter 4 to work after passing through the power amplifier 19. The acceleration sensor 11 feeds back the response signal measured on the horizontal slide 12 to the vibration controller 18, and compares and corrects it with the target spectrum to obtain a new drive spectrum, and repeats this process to finally obtain the target spectrum. Then, the arc heater 1 generates an arc through breakdown discharge between electrodes, heats the air and other media entering the heater, and forms a supersonic high-temperature hot air flow after being accelerated by the nozzle expansion, which is sprayed on the leading edge of the test piece 14 such as the wing-rudder, and the infrared pyrometer 15 and the high-speed camera 16 measure the surface temperature and morphology of the airfoil structure in real time.

[0056] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention 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 replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A small wing-rudder structure aerodynamic thermal-vibration combined test device, characterized in that: It includes a base, a slide base plate, a horizontal slide, a heat insulation plate, an exciter, a rigid connecting rod and an arc heater; The vibration exciter and the slide base plate are arranged on the base; The horizontal slide is slidably connected to the slide bottom plate, and the vibration exciter is connected to the horizontal slide via a rigid connecting rod; The test piece is fixed on a horizontal slide, and the test piece is arranged opposite to the nozzle of the arc heater; Two pairs of optical axis supports are arranged on the bottom plate of the slide, and an optical axis is passed through the two optical axis supports arranged opposite to each other; Two sliders are provided on each optical axis, the optical axis support is fixed to the bottom plate of the slide table by bolts, and the horizontal slide table is fixed to the four sliders by bolts; One end of the rigid connecting rod is threadedly connected to the horizontal slide, and the other end is connected to the adapter frame of the exciter by bolts; The small wing-rudder structure aerodynamic thermal-vibration combined test device also includes an infrared pyrometer, a high-speed camera, a computer, a vibration controller, an acceleration sensor and a power amplifier, wherein the infrared pyrometer and the high-speed camera are electrically connected to the computer, the acceleration sensor and the power amplifier are electrically connected to the vibration controller, and the power amplifier is electrically connected to the exciter.

2. The aerodynamic thermal-vibration combined test device for a small wing-rudder structure according to claim 1 is characterized in that: The vibration exciter and the slide base plate are fixed on the base through bolts.

3. The aerodynamic thermal-vibration combined test device for a small wing-rudder structure according to claim 1 is characterized in that: A slide protection plate is arranged on the upper part of the horizontal slide, and the slide protection plate is fixed on the horizontal slide by high temperature curing glue.

4. The aerodynamic thermal-vibration combined test device for a small wing-rudder structure according to claim 1 is characterized in that: The base is also provided with a heat insulation plate, a slide base plate, and components on the slide base plate and an exciter distributed on both sides of the heat insulation plate.

5. The aerodynamic thermal-vibration combined test device for a small wing-rudder structure according to claim 1 is characterized in that: The frequency range of the exciter is 0-3kHz, and the maximum excitation force is 500N; The vibration controller outputs random vibration, sinusoidal vibration, and random and sinusoidal vibration patterns; The infrared pyrometer is selected according to the test conditions as a monochrome infrared pyrometer with a wavelength response of 1.6 μm and a temperature measurement range of 450-2250°C; or a response wavelength of 1.0 μm and a temperature measurement range of 540-3000°C; The acquisition frequency of the high-speed camera should be greater than 5000 frames.

6. The aerodynamic thermal-vibration combined test device for a small wing-rudder structure according to claim 1 is characterized in that: The arc heater is a tubular low-enthalpy arc heater, a segmented medium-enthalpy arc heater, or a laminated high-enthalpy arc heater.

7. The aerodynamic thermal-vibration combined test device for a small wing-rudder structure according to claim 1 is characterized in that: The horizontal slide is provided with a cooling water channel, which is arranged along the horizontal direction of the horizontal slide, and the diameter of the water channel is less than or equal to 2 / 3 of the thickness of the horizontal slide.

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