Device for testing retention rate of de-icing and anti-icing fluid of airplane

Abstract

The utility model discloses a device for testing the retention rate of deicing fluid of an airplane, which comprises a bottom frame, a weighing sensor is arranged on the bottom frame, a support rod and a connecting plate are sequentially arranged above the weighing sensor, the connecting plate is connected with a test plate, and the test plate and the horizontal plane are arranged at an inclination angle. According to the utility model, the test plate is inclined relative to the horizontal plane, and the mass change of the residual deicing and anti-icing fluid on the test plate is measured in real time through the weighing sensor, so that the retention rate of the deicing and anti-icing fluid on the test plate is calculated, and the test device is used for testing the retention rate of the deicing and anti-icing fluid on the test plate by temperature, wind speed, wind direction, air pressure and the like. And obtaining an influence rule of meteorological conditions on the airplane deicing and anti-icing fluid retention time.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation material research, in particular to a testing device for the retention rate of aircraft deicing and anti-icing fluid. Background Art

[0002] When an aircraft is operating in winter, the surface of the fuselage may freeze due to snow and low temperature, and the aircraft surface needs to be de-iced. Currently, most of the de-icing and de-icing fluid is sprayed on the aircraft. The time that the aircraft de-icing and de-icing fluid prevents the aircraft surface from freezing is the holding time. According to the test standard (SAEARP5485 / SAEARP5945), the holding time test is carried out on a 300×500mm flat plate, and the flat plate is inclined at a 10° angle to the horizontal plane. The Chinese utility model patent CN205618911U (authorization announcement date: 2016.10.05) discloses a bracket for de-icing and de-icing fluid film stability test, including a bottom plate, a sliding track is arranged parallel to the front end of the bottom plate, and a fixing bolt is arranged on the sliding track. The rear bracket is arranged at the rear end of the bottom plate and fixed to the bottom plate. The bottom surface of the L-shaped front bracket is fixed to the bottom plate by fixing bolts, and the height of the front bracket is lower than that of the rear bracket. Because the height of the front bracket is lower than that of the rear bracket, the above utility model changes the inclination angle of the test plate frame to achieve the target inclination angle.

[0003] After testing, it was found that most of the de-icing fluid will flow away within a few seconds after being poured on the surface of the test plate. The remaining de-icing fluid is the key to providing retention time. The concept of retention rate is introduced: retention rate = (mass of remaining de-icing fluid / mass of initial de-icing fluid*100). Temperature, wind speed, wind direction, and air pressure will all affect the retention rate of de-icing fluid. There is no device in the prior art that can measure the retention rate. Utility Model Content

[0004] In order to solve the above-mentioned deficiencies in the prior art, the utility model provides a test device for the retention rate of aircraft de-icing and anti-icing fluid, which is used to study the retention time of aircraft de-icing and anti-icing fluid.

[0005] In order to achieve the above technical purpose, the technical solution adopted by the utility model is:

[0006] A test device for aircraft deicing fluid retention rate comprises a base frame, a weighing sensor is arranged on the base frame, a support rod and a connecting plate are arranged above the weighing sensor in sequence, a test plate is connected to the connecting plate, and the test plate is arranged at an inclination angle with a horizontal plane.

[0007] Furthermore, the test plate is inclined at an angle of 10° to the horizontal plane.

[0008] Preferably, the test plate and the connecting plate are connected by bolts.

[0009] Another preferred embodiment is that the test plate is made of aluminum alloy material, a magnetic plate is fixedly connected to the back center of the test plate, and the magnetic plate is magnetically connected to the connecting plate.

[0010] Preferably, the magnetic plate is fixed to the test plate by welding or bonding.

[0011] Furthermore, a diagonal brace bracket is fixedly connected to the connecting plate, and the upper top surface of the diagonal brace bracket is set at an inclined angle to the horizontal plane. A clamping column is provided at one end of the diagonal brace bracket away from the connecting plate, and the clamping column is perpendicular to the diagonal brace bracket. A connecting hole is provided on the test plate, and the clamping column is adapted to the connecting hole on the test plate.

[0012] Preferably, the diagonal brace bracket is in a "V" shape, the opening end of the diagonal brace bracket is away from the connecting plate, and the "V"-shaped opening of the diagonal brace bracket is arranged obliquely upward or obliquely downward.

[0013] In another preferred embodiment, the diagonal brace bracket is in an "X" shape, and the four corners of the diagonal brace bracket correspond to the four corners of the test plate.

[0014] Furthermore, it also includes a waste liquid collection tray, which is placed at the lower part of the base frame.

[0015] Furthermore, it also includes a counterweight block, which is placed in the base frame.

[0016] The beneficial effects of the utility model are:

[0017] The utility model discloses a test device for the retention rate of aircraft de-icing fluid. The test plate is tilted relative to the horizontal plane, and a weighing sensor is used to measure the mass change of the remaining de-icing fluid on the test plate in real time, so as to calculate the retention rate of the de-icing fluid on the test plate. The utility model is used to test the retention rate of the de-icing fluid on the test plate under the conditions of temperature, wind speed, wind direction, air pressure, etc., so as to obtain the influence of meteorological conditions on the retention time of the aircraft de-icing fluid. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0019] Figure 1 It is a front view of an embodiment of the utility model;

[0020] Figure 2 It is a three-dimensional schematic diagram of an embodiment of the utility model (without the test board);

[0021] Figure 3is a top view of the test board.

[0022] Figure numerals: 1-de-icing fluid, 2-test plate, 3-connecting plate, 4-support rod, 5-weighing sensor, 6-base frame, 7-waste liquid collection tray, 8-diagonal support bracket, 9-clamp column, 10-counterweight block. DETAILED DESCRIPTION

[0023] To make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application generally described and shown in the drawings here can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the application claimed for protection, but merely represents the selected embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians of the art without making creative work are within the scope of protection of the present application.

[0024] A test device for aircraft de-icing fluid retention rate, such as Figure 1 , Figure 2 , Figure 3 As shown, it includes a base frame 6, a weighing sensor 5 is arranged on the base frame 6, a support rod 4 and a connecting plate 3 are arranged above the weighing sensor 5 in sequence, the connecting plate 3 is connected to a test plate 2, and the test plate 2 is arranged at an angle with the horizontal plane. Preferably, the test plate 2 is inclined at a 10° angle with the horizontal plane. The de-icing liquid 1 is evenly poured on the test plate 2, and the mass change of the remaining de-icing liquid 1 on the test plate 2 is measured in real time by the weighing sensor 5, and the data is transmitted to the computer to calculate the retention rate of the de-icing liquid, and the retention rate = (the mass of the remaining de-icing liquid / the mass of the initial de-icing liquid * 100); the test temperature, wind speed, wind direction and other conditions can be changed to test the influence of different meteorological conditions on the retention rate of the de-icing liquid.

[0025] Preferably, the test plate 2 is connected to the connecting plate 3 by bolts. Another preferred method is that the test plate 2 is made of aluminum alloy material, a magnetic plate is fixedly connected to the center of the back of the test plate 2, the magnetic plate is fixed to the test plate 2 by welding or bonding, and the magnetic plate is magnetically connected to the connecting plate 3, which is convenient for taking the test plate 2, and does not change the flatness of the front of the test plate 2, and does not affect the test results.

[0026] Furthermore, a diagonal brace bracket 8 is fixedly connected to the connecting plate 3, and the upper top surface of the diagonal brace bracket 8 is set at an angle to the horizontal plane. A clamping column 9 is provided at one end of the diagonal brace bracket 8 away from the connecting plate 3, and the clamping column 9 is perpendicular to the diagonal brace bracket 8. A connecting hole is provided on the test plate 2, and the clamping column 9 is adapted to the connecting hole on the test plate 2. Preferably, the diagonal brace bracket 8 is in a "V" shape, and the open end of the diagonal brace bracket 8 is away from the connecting plate 3, and the "V"-shaped opening of the diagonal brace bracket 8 is set obliquely upward or obliquely downward. Another preferred embodiment is that the diagonal brace bracket 8 is in an "X" shape, and the four corners of the diagonal brace bracket 8 correspond to the four corners of the test plate 2.

[0027] Furthermore, it also includes a waste liquid collection tray 7, which is placed at the lower part of the base frame 6 and is used to collect the de-icing liquid dripping from the test plate 2 to prevent the ground or the test bench from being slippery.

[0028] The measuring range of the weighing sensor 5 is selected to be 0 to 6 kg, and the accuracy is 0.01 g. During the test, the mass of the de-icing fluid 1 poured on the surface of the test plate 2 for each test is about 1 kg, the mass of the test plate 2 is 1.3 kg, plus the weight of the connecting plate 3 and the support rod 4, the measuring range of the weighing sensor 5 can meet the experimental requirements.

[0029] Furthermore, the base frame 6 is provided with a partition and also includes a counterweight 10. According to experimental requirements, the counterweight 10 can be placed in the base frame 6 to increase the stability of the test device and prevent the base frame 6 from tipping over under high wind speed conditions.

[0030] The test device of the utility model keeps the test plate in an inclined setting, and can measure the mass change of the remaining de-icing fluid on the test plate in real time through a weighing sensor, so as to calculate the retention rate of the de-icing fluid on the test plate, and is used to carry out temperature, wind speed, wind direction, and air pressure tests on the retention rate of the de-icing fluid on the test plate, so as to obtain the influence of meteorological conditions on the retention time of the aircraft de-icing fluid.

[0031] Of course, the present invention may have many other embodiments. Without departing from the spirit and essence of the present invention, technicians familiar with the field may make various corresponding changes and deformations based on the present invention, but these corresponding changes and deformations should all fall within the scope of protection of the claims attached to the present invention.

Claims

1. A test device for aircraft deicing fluid retention rate, characterized in that: The device comprises a base frame (6), a weighing sensor (5) is arranged on the base frame (6), a support rod (4) and a connecting plate (3) are arranged in sequence above the weighing sensor (5), a test plate (2) is connected to the connecting plate (3), and the test plate (2) is arranged at an inclination angle with a horizontal plane.

2. The test device for aircraft deicing and anti-icing fluid retention rate according to claim 1, characterized in that: The test plate (2) is inclined at an angle of 10° to the horizontal plane.

3. The test device for aircraft deicing and anti-icing fluid retention rate according to claim 1, characterized in that: The test plate (2) and the connecting plate (3) are connected via bolts.

4. The test device for aircraft deicing and anti-icing fluid retention rate according to claim 1, characterized in that: The test plate (2) is made of an aluminum alloy material. A magnetic plate is fixedly connected to the center of the back of the test plate (2), and the magnetic plate is magnetically connected to the connecting plate (3).

5. The test device for aircraft deicing and anti-icing fluid retention rate according to claim 4, characterized in that: The magnetic plate is fixed to the test plate (2) by welding or bonding.

6. The test device for aircraft deicing and anti-icing fluid retention rate according to claim 1, characterized in that: The connecting plate (3) is fixedly connected with an oblique support bracket (8), the upper top surface of the oblique support bracket (8) is arranged at an inclined angle with the horizontal plane, the end of the oblique support bracket (8) away from the connecting plate (3) is provided with a clamping column (9), the clamping column (9) is perpendicular to the oblique support bracket (8), the test plate (2) is provided with a connecting hole, and the clamping column (9) is adapted to the connecting hole on the test plate (2).

7. The test device for aircraft deicing and anti-icing fluid retention rate according to claim 6, characterized in that: The diagonal brace bracket (8) is in a "V" shape, the opening end of the diagonal brace bracket (8) is away from the connecting plate (3), and the "V"-shaped opening of the diagonal brace bracket (8) is arranged diagonally upward or diagonally downward.

8. The test device for aircraft deicing and anti-icing fluid retention rate according to claim 6, characterized in that: The diagonal support bracket (8) is in an "X" shape, and the four corners of the diagonal support bracket (8) correspond to the four corners of the test plate (2).

9. The test device for aircraft deicing and anti-icing fluid retention rate according to any one of claims 1 to 8, characterized in that: It also comprises a waste liquid collection tray (7), and the waste liquid collection tray (7) is placed at the lower part of the base frame (6).

10. The test device for aircraft deicing and anti-icing fluid retention rate according to claim 9, characterized in that: It also comprises a counterweight block (10), wherein the counterweight block (10) is placed in the base frame (6).

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