Airplane shell material wind power detection device

Abstract

The invention is suitable for the technical field of airplane shell material detection, and provides an airplane shell material wind power detection device which comprises a base; the fan cover is fixed at the top of the base through a bolt; the fan is fixed on the inner side wall of the fan cover through a bolt; the cover cap is hinged to the outer side wall of the fan cover; the flow guide cover is welded at the central position of the outer side wall of the cover cap; the base is fixed to the position, close to one side of the fan cover, of the top of the base through bolts. The electric push rod is fixed at the top of the base through a bolt; the lifting platform is fixed at the output end of the electric push rod; the three-phase asynchronous motor is fixed at the central position of the outer side wall of the lifting platform through a bolt; the axial rotation of the aircraft shell material is controlled to adjust the windward detection surface, and wind resistance detection can be performed on different surfaces of the aircraft shell material, so that the structural strength of the aircraft shell material under different weather conditions is ensured, and the flight safety of an aircraft is ensured.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft shell material detection, and in particular relates to a wind force detection device for aircraft shell material. Background Art

[0002] During the aircraft processing process, a high-strength shell is required to ensure the strength of the fuselage. The materials selected when making the aircraft shell need to undergo actual testing and cannot remain at the theoretical calculation level in order to ensure the structural strength of the aircraft shell.

[0003] It is difficult to detect the maximum wind force that existing aircraft shell materials can withstand during testing, and it is also difficult to simulate the pressure that the aircraft is subjected to during flight.

[0004] Therefore, a wind force detection device for aircraft shell material is proposed. Summary of the invention

[0005] The present invention provides a wind force detection device for aircraft shell material, aiming to solve the above-mentioned problem.

[0006] The present invention is implemented as follows: a wind force detection device for aircraft shell materials, comprising: a base; a fan cover fixed to the top of the base by bolts; a fan fixed to the inner wall of the fan cover by bolts; and a cover hinged to the outer wall of the fan cover; a deflector welded to the central position of the outer wall of the cover; a base fixed to the top of the base by bolts at a position close to the fan cover; an electric push rod fixed to the top of the base by bolts; a lifting platform fixed to the output end of the electric push rod; a three-phase asynchronous motor fixed to the central position of the outer wall of the lifting platform by bolts; a ball screw fixed to the output end of the three-phase asynchronous motor; a moving platform fixed to the nut seat on the ball screw by screws; a fixing plate welded to the top of the moving platform; a pressure sensor fixed to the outer wall of the fixing plate by bolts; a support plate fixed to the outer wall of the pressure sensor by bolts; a round table welded to the outer wall of the support plate on the side away from the pressure sensor; a stepping motor fixed to the central position of the outer wall of the round table by bolts; and a fixture mounting plate fixed to the output end of the stepping motor.

[0007] Preferably, a through hole is provided on one side outer wall of the cover at a position close to one side of the air deflector, and the cross section of the air deflector is an isosceles trapezoid.

[0008] Preferably, there are four electric push rods in total, and the four electric push rods are symmetrically arranged on the top of the base.

[0009] Preferably, the moving platform and the lifting platform are slidably connected via a sliding block and a sliding groove.

[0010] Preferably, there are two fixing plates in total, and the two fixing plates are symmetrically arranged on the top of the moving platform.

[0011] Preferably, the fixture installation plate and the truncated table are slidably connected, and a fixture installation hole is provided on an outer wall of the fixture installation plate on a side away from the truncated table.

[0012] Preferably, the support plate and the fixing plate are perpendicular to each other.

[0013] Compared with the prior art, the embodiments of the present application have the following beneficial effects:

[0014] By controlling the axial rotation of the aircraft shell material to adjust the wind detection surface, the wind resistance of different surfaces of the aircraft shell material can be tested, thereby ensuring the structural strength of the aircraft shell material under different weather conditions and ensuring the flight safety of the aircraft. The wind is gathered in one area through the deflector, and the vertical and horizontal movement of the aircraft shell material can be used to test the wind resistance of local areas of the aircraft shell material to test the local structural strength of the aircraft shell material. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the structure of the present invention;

[0016] Figure 2 It is a schematic diagram of the explosion of the lifting platform of the present invention;

[0017] Figure 3 It is a schematic diagram of the cooperation between the cover and the air guide cover of the present invention;

[0018] Figure 4 It is a schematic diagram of the explosion of the truncated cone of the present invention.

[0019] In the figure: 1. base; 2. fan cover; 3. fan; 4. cover; 5. air deflector; 6. base; 7. electric push rod; 8. lifting platform; 9. three-phase asynchronous motor; 10. ball screw; 11. moving platform; 12. fixed plate; 13. pressure sensor; 14. support plate; 15. round table; 16. stepping motor; 17. fixture mounting plate. DETAILED DESCRIPTION

[0020] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by technicians in the technical field of this application; the terms used in the specification of the application are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the above-mentioned drawings and any variations thereof are intended to cover non-exclusive inclusions. The terms "first", "second", etc. in the specification and claims of this application or the above-mentioned drawings are used to distinguish different objects, not to describe a specific order.

[0021] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0022] The embodiment of the present invention provides a wind force detection device for aircraft shell materials, such as Figure 1-4 As shown, it includes a base 1, the top of the base 1 is fixedly connected to a fan cover 2 by bolts, the inner side wall of the fan cover 2 is fixedly connected to a fan 3 by bolts, and the outer side wall of the fan cover 2 is hinged with a cover 4, the cover 4 and the fan cover 2 are locked by a mechanical lock, and a guide cover 5 is welded at the central position of the outer wall on the side away from the fan cover 2, the top of the base 1 is fixedly connected to a base 6 by bolts at a side position close to the fan cover 2, the top of the base 6 is fixedly connected to an electric push rod 7 by bolts, a total of four electric push rods 7 are provided, and the four electric push rods 7 are symmetrically arranged on the top of the base 6, the electric push rod 7 is fixedly connected to a lifting platform 8 through the output end on one side thereof, a three-phase asynchronous motor 9 is fixedly connected to the central position of the outer wall on one side of the lifting platform 8 by bolts, and the three-phase asynchronous motor 9 is fixedly connected to the lifting platform 8 through its output end A ball screw 10 is fixedly connected to the output end on one side, and a nut seat on the ball screw 10 is fixedly connected to a moving platform 11 by screws. The moving platform 11 and the lifting platform 8 are slidably connected by a slider and a slide groove. A fixed plate 12 is welded on the top of the moving platform 11. There are two fixed plates 12 in total, and the two fixed plates 12 are symmetrically arranged on the top of the moving platform 11. A pressure sensor 13 is embedded and fixed on the outer wall of one side of the fixed plate 12. A support plate 14 is fixedly connected to the outer wall of the pressure sensor 13 on the side away from the fixed plate 12 by bolts. A round table 15 is welded to the outer wall of the support plate 14 on the side away from the pressure sensor 13. A stepper motor 16 is fixedly connected to the central position of the outer wall of one side of the round table 15 by bolts, and the stepper motor 16 is fixedly connected to a fixture mounting disk 17 through the output end of one side thereof.

[0023] It should be noted that, since it is difficult to detect the maximum wind force that the existing aircraft shell materials can withstand during testing, and thus it is difficult to simulate the pressure that the aircraft is subjected to during flight, this embodiment controls the axial rotation of the aircraft shell material to adjust the wind detection surface, and can perform wind resistance tests on different surfaces of the aircraft shell material, thereby ensuring the structural strength of the aircraft shell material under different weather conditions and ensuring the flight safety of the aircraft. The wind is gathered in one area through the deflector 5, and the vertical and horizontal movement of the aircraft shell material is utilized to perform wind resistance tests on local areas of the aircraft shell material, so as to detect the local structural strength of the aircraft shell material.

[0024] Specifically, in this embodiment, this solution mainly includes a deflector 5 and a clamp mounting plate 17. When in use, a corresponding clamp is made according to the shape of the aircraft shell material, and the clamp is fixed on the clamp mounting plate 17. At this time, the aircraft shell material is clamped and fixed by the clamp, and the aircraft shell material is located on one side of the fan 3. When the wind resistance of the aircraft shell material is tested, the external power supply of the fan 3 is connected, and the fan 3 generates wind to blow to the aircraft shell material, and gradually increases the wind force. The electric push rod 7 is controlled to drive the lifting platform 8 to rise and fall through the output end on one side thereof, and the aircraft shell material rises and falls synchronously to ensure that the aircraft shell material is in the wind flow. After the aircraft shell material is subjected to pressure, the pressure is transmitted to the pressure sensor 13 through the support plate 14. The pressure sensor 13 detects the pressure and records the pressure value when the aircraft shell material is deformed. When the aircraft shell material breaks, the pressure value is recorded, and the stepper motor 16 is controlled to drive the fixture mounting plate 17 to rotate through the output end on one side thereof, and the aircraft shell material rotates axially synchronously, thereby adjusting the wind-receiving surface of the aircraft shell material to detect the wind resistance of different surfaces of the aircraft shell material. When the local area of ​​the aircraft shell material is subjected to pressure resistance testing, after the fan 3 is turned off, the cover 4 is closed, and the cover 4 and the fan cover 2 are combined and locked together. When the test is performed, the three-phase asynchronous motor 9 is controlled to drive the ball screw 10 to rotate through the output end on one side thereof, and the moving platform 11 on the ball screw 10 moves horizontally on the lifting platform 8, and the aircraft shell material moves synchronously, thereby controlling the wind to blow to the aircraft shell material regionally, thereby performing wind resistance testing on the local area of ​​the aircraft shell material to detect the local structural strength of the aircraft shell material.

[0025] In a further preferred embodiment of the present invention, Figure 3 As shown, a through hole is provided on one side outer wall of the cover 4 near the side of the air deflector 5, and the cross section of the air deflector 5 is an isosceles trapezoid.

[0026] In this embodiment, the through hole is provided so that the wind blown out by the fan 3 can pass through the cover 4 and enter the air deflector 5, and the air deflector 5 is used to guide and gather the wind, so that the wind is blown toward the aircraft shell material with a smaller wind impact surface, thereby realizing the wind resistance test of a certain area on the aircraft shell material.

[0027] In a further preferred embodiment of the present invention, Figure 4 As shown, the fixture mounting plate 17 and the truncated table 15 are slidably connected, and a fixture mounting hole is provided on the outer wall of the fixture mounting plate 17 away from the truncated table 15, and the support plate 14 and the fixing plate 12 are perpendicular to each other.

[0028] In this embodiment, the fixture mounting plate 17 is used to facilitate the installation and fixation of the fixture that is compatible with the aircraft shell material, and the sliding connection is used to ensure the stability of the rotation of the fixture mounting plate 17 on the round table 15. The vertical support plate 14 and fixing plate 12 can be used to detect the pressure on the aircraft shell material.

[0029] It should be noted that, for the above-mentioned embodiments, for the sake of simplicity, they are all described as a series of action combinations, but those skilled in the art should know that the present invention is not limited by the described order of actions, because according to the present invention, some steps may be performed in other orders or simultaneously. Secondly, those skilled in the art should also know that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily required by the present invention.

[0030] In the several embodiments provided in the present application, it should be understood that the disclosed devices can be implemented in other ways. For example, the device embodiments described above are merely schematic, such as the division of the above-mentioned units. There may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or communication connection shown or discussed can be through some interfaces, and the indirect coupling or communication connection between devices or units can be in the form of telecommunication or other forms.

[0031] The units described above as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0032] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the scope of protection of the invention. Obviously, the described embodiments are only some embodiments of the present invention, rather than all embodiments. Based on these embodiments, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in this field can still combine, add, delete or make other adjustments to the features in the various embodiments of the present invention according to the circumstances without conflict, without making creative work, so as to obtain different other technical solutions that do not deviate from the concept of the present invention in essence, and these technical solutions also belong to the scope of protection of the present invention.

Claims

1. A wind force detection device for aircraft shell materials, characterized in that: include: Base (1); A fan cover (2) fixed to the top of the base (1) by bolts; A fan (3) fixed to the inner wall of the fan cover (2) by bolts; and A cover (4) hinged to the outer side wall of the fan cover (2); A flow guide cover (5) welded to the central position of the outer side wall of the cover (4); A base (6) fixed by bolts to a position on the top of the base (1) near a side of the fan cover (2); An electric push rod (7) fixed to the top of the base (6) by bolts; A lifting platform (8) fixed to the output end of the electric push rod (7); A three-phase asynchronous motor (9) fixed by bolts at the central position of the outer side wall of the lifting platform (8); A ball screw (10) fixed to the output end of the three-phase asynchronous motor (9); A moving platform (11) fixed to a nut seat on the ball screw (10) by screws; A fixed plate (12) welded to the top of the moving platform (11); A pressure sensor (13) fixed to the outer wall of the fixing plate (12) by means of bolts; A support plate (14) fixed to the outer side wall of the pressure sensor (13) by means of bolts; A truncated cone (15) welded to the outer wall of the support plate (14) on a side away from the pressure sensor (13); A stepping motor (16) fixed to the center of the outer side wall of the truncated table (15) by means of bolts; A fixture mounting plate (17) is fixed to the output end of the stepping motor (16).

2. The wind force detection device for aircraft shell material according to claim 1, characterized in that: A through hole is provided on one side outer wall of the cover (4) at a position close to one side of the air deflector (5); the cross section of the air deflector (5) is an isosceles trapezoid.

3. The wind force detection device for aircraft shell material according to claim 1, characterized in that: A total of four electric push rods (7) are provided, and the four electric push rods (7) are symmetrically arranged on the top of the base (6).

4. The wind force detection device for aircraft shell material according to claim 1, characterized in that: The moving platform (11) and the lifting platform (8) are slidably connected via a sliding block and a sliding groove.

5. The wind force detection device for aircraft shell material according to claim 1, characterized in that: There are two fixed plates (12) in total, and the two fixed plates (12) are symmetrically arranged on the top of the moving platform (11).

6. The wind force detection device for aircraft shell material according to claim 1, characterized in that: The clamp installation plate (17) and the round table (15) are slidably connected, and a clamp installation hole is provided on an outer wall of the clamp installation plate (17) on a side away from the round table (15).

7. The wind force detection device for aircraft shell material according to claim 1, characterized in that: The support plate (14) and the fixing plate (12) are perpendicular to each other.

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