Static testing device for aero seat

Abstract

The utility model provides a static testing device for an aero seat, belongs to the technical field of aero seat testing, and solves the technical problem that static testing of the structural strength of the aero seat is lacked in the prior art. An aero seat static test device comprises a mounting seat, an aero seat body fixed on the mounting seat, a regulation and control frame fixed on one side of the mounting seat, a downward pressing frame slidably arranged on the regulation and control frame, a driving frame fixed on the downward pressing frame, a pressure plate arranged on the driving frame, the pressure plate comprising a seat plate and a back plate hinged to the seat plate, guide sliding grooves are formed in the seat plate and the back plate, a guide sliding seat is slidably connected into each guide sliding groove, a driving assembly is arranged in the driving frame and connected with the two guide sliding seats, and a regulation and control assembly is arranged in the regulation and control frame and connected with the lower pressing frame. The aero seat static test device has the advantage of realizing static test on the overall structural strength of the aero seat.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft seat testing technology, and relates to a static testing device, particularly an aircraft seat static testing device. Background Technology

[0002] Aircraft seats are seats installed on aircraft. The design of aircraft seats takes into account the special environment and safety requirements of aviation flights. Therefore, aircraft seats must meet strict safety standards to ensure that passengers can be protected to the greatest extent in the event of an accident during flight. This includes testing and certifying aircraft seats to ensure that the seats can withstand impact forces and maintain structural integrity.

[0003] A search revealed a Chinese patent document disclosing an aircraft seat testing device [Application No.: 202311725689.X; Publication No.: CN 117740413 B]. This aircraft seat testing device includes a test platform. One side of the test platform is used to mount a seat, and the other side is equipped with a turbulence device. A bidirectional synchronous motor is fixedly connected to the center of an offset block. Both output ends of the bidirectional synchronous motor are fixedly connected to a first eccentric block. One end of a support column is fixedly connected to one side of the offset block, and the other end of the support column is fixedly connected to the test platform. Rotation of the first eccentric block causes the offset block to move up and down on a first fixed column via a second spring. The first spring also causes a moving frame to move left and right. The offset block, in turn, causes the support column to move the test platform, thus simulating turbulence during aircraft flight. This allows for testing of aircraft seats under turbulence conditions, reducing potential loopholes in aircraft seat testing, and further improving the safety of aircraft seats during use.

[0004] While this patent reduces the loopholes in aircraft seat testing and further improves the safety of aircraft seats during use, testing aircraft seats under turbulent conditions is a dynamic test, and static testing of the structural strength of the aircraft seats themselves is also very necessary. Utility Model Content

[0005] The purpose of this invention is to address the aforementioned problems in existing technologies by proposing a static testing device for aircraft seats. The technical problem this invention aims to solve is: how to perform static testing on the overall structural strength of aircraft seats.

[0006] The objective of this utility model can be achieved through the following technical solutions:

[0007] A static testing device for an aircraft seat includes a mounting base and an aircraft seat body fixed on the mounting base. An adjustment frame is fixed to one side of the mounting base, a pressure frame is slidably mounted on the adjustment frame, a drive frame is fixed on the pressure frame, and a pressure plate is mounted on the drive frame. The pressure plate includes a seat plate and a back plate hinged to the seat plate. Guide grooves are provided on both the seat plate and the back plate, and a guide slide is slidably connected in each guide groove. A drive assembly is provided in the drive frame and is connected to two guide slides. An adjustment assembly is provided in the adjustment frame and is connected to the pressure frame.

[0008] The working principle of this utility model is as follows: the pressure plate can be controlled to press down through the control component, thereby driving the pressure plate to perform pressure testing on the aircraft seat, and the pressure is distributed to the back of the aircraft seat through the drive component, thereby improving the test effect and obtaining more comprehensive static test data of the aircraft seat.

[0009] The drive assembly includes a pair of extended arms slidably connected within the drive frame and a bidirectional lead screw rotatably connected within the drive frame. A servo motor is fixed within the drive frame, and a drive gear is coaxially fixedly connected to the output shaft of the servo motor. A drive gear is coaxially fixedly connected to the bidirectional lead screw. The drive gear and the drive gear mesh. The threaded sections on both sides of the bidirectional lead screw are threadedly connected to the corresponding extended arms. One end of each of the two extended arms is rotatably connected to the corresponding guide slide.

[0010] Using the above structure, the servo motor drives the drive gear to rotate, which in turn drives the drive gear to rotate. The drive gear then drives the bidirectional lead screw to rotate, which in turn drives the two extension arms to extend, thereby moving the guide slide. The guide slide then pushes the seat plate and backrest, enabling overall pressure testing of the aircraft seat base and backrest. The angle of the seat plate and backrest can be adjusted to match the seating posture of the aircraft seat, thus improving the testing results.

[0011] The control assembly includes a control screw rotatably connected within the control frame and a servo motor II fixedly connected within the control frame. The output shaft of the servo motor II is coaxially fixedly connected to the control screw, and the control screw is threadedly connected to the lower pressure frame.

[0012] Using the above structure, the control screw can be rotated by the second servo motor. After the control screw rotates, it will drive the lower pressure frame to move, thereby realizing the downward pressing action and completing the static test of the aircraft seat.

[0013] The seat plate and back plate are made of high-strength aluminum alloy.

[0014] Using the above structure, the seat plate and back plate can be made of high-strength aluminum alloy, which improves the structural strength of the seat plate and back plate and prevents them from disintegrating during the test.

[0015] The bottom four corners of the aircraft seat body are fixedly connected to the mounting base by high-strength positioning bolts.

[0016] By adopting the above structure, the installation strength of the aircraft seat and the mounting base can be improved while ensuring that the aircraft seat can be disassembled and assembled with the mounting base through high-strength positioning bolts.

[0017] Compared with existing technologies, this static testing device for aircraft seats has the following advantages:

[0018] 1. The pressure plate is controlled by the control component to press down, thereby driving the pressure plate to perform pressure testing on the aircraft seat. The pressure is then distributed to the back of the aircraft seat by the drive component, thereby improving the test results and obtaining more comprehensive static test data of the aircraft seat.

[0019] 2. Furthermore, the angles of the seat and backrest can be adjusted to match the seating posture of an aircraft seat, thereby improving the testing results. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structure of this utility model.

[0021] Figure 2 This is a schematic diagram of the internal structure of the control frame in this utility model.

[0022] Figure 3 This is a schematic diagram of the internal structure of the drive frame in this utility model.

[0023] In the diagram, 1. Mounting base; 2. Aircraft seat body; 3. Adjustment frame; 4. Lowering frame; 5. Drive frame; 6. Seat plate; 7. Back plate; 8. Guide slide; 9. Guide slide block; 10. Extension arm; 11. Two-way lead screw; 12. Servo motor one; 13. Drive gear one; 14. Drive gear two; 15. Adjustment lead screw; 16. Servo motor two. Detailed Implementation

[0024] The following are specific embodiments of the present invention, which are described in conjunction with the accompanying drawings. However, the present invention is not limited to these embodiments.

[0025] like Figures 1-3As shown, a static testing device for an aircraft seat includes a mounting base 1, an aircraft seat body 2 fixed on the mounting base 1, an adjustment frame 3 fixed on one side of the mounting base 1, a pressure frame 4 slidably mounted on the adjustment frame 3, a drive frame 5 fixed on the pressure frame 4, a pressure plate mounted on the drive frame 5, the pressure plate including a seat plate 6 and a back plate 7 hinged to the seat plate 6, guide grooves 8 are provided on both the seat plate 6 and the back plate 7, and a guide slide seat 9 is slidably connected in each guide groove 8, a drive assembly is provided in the drive frame 5, the drive assembly is connected to the two guide slide seats 9, and an adjustment assembly is provided in the adjustment frame 3, the adjustment assembly is connected to the pressure frame 4.

[0026] The pressure plate 4 can be controlled by the control component to press down, thereby driving the pressure plate to perform pressure testing on the aircraft seat. The pressure is then distributed to the back of the aircraft seat by the drive component, thereby improving the test results and obtaining more comprehensive static test data of the aircraft seat.

[0027] The drive assembly includes a pair of extension arms 10 slidably connected within the drive frame 5, and a bidirectional lead screw 11 rotatably connected within the drive frame 5. A servo motor 12 is fixed within the drive frame 5. A drive gear 13 is coaxially fixedly connected to the output shaft of the servo motor 12. A drive gear 14 is coaxially fixedly connected to the bidirectional lead screw 11. The drive gear 13 and the drive gear 14 mesh. The threaded sections on both sides of the bidirectional lead screw 11 are threadedly connected to the corresponding extension arms 10. One end of each of the two extension arms 10 is rotatably connected to the corresponding guide slide 9.

[0028] Using the above structure, the servo motor 12 drives the drive gear 13 to rotate. After the drive gear 13 rotates, it drives the drive gear 14 to rotate. The drive gear 14 drives the bidirectional lead screw 11 to rotate. The bidirectional lead screw 11 then drives the two extension arms 10 to extend, thereby pushing the guide slide 9 to move. The guide slide 9 pushes the seat plate 6 and the back plate 7 to achieve overall pressure testing of the aircraft seat base and backrest. The angle of the seat plate 6 and the back plate 7 can be adjusted to fit the sitting posture of the aircraft seat and improve the test results.

[0029] The control assembly includes a control screw 15 rotatably connected within the control frame 3 and a servo motor 16 fixedly connected within the control frame 3. The output shaft of the servo motor 16 is coaxially fixedly connected to the control screw 15, and the control screw 15 is threadedly connected to the lower pressure frame 4.

[0030] With the above structure, the control screw 15 can be rotated by the servo motor 16. After the control screw 15 rotates, it will drive the pressure frame 4 to move, thereby realizing the downward pressing action and completing the static test of the aircraft seat.

[0031] The seat plate 6 and the back plate 7 are made of high-strength aluminum alloy.

[0032] Using the above structure, the seat plate 6 and back plate 7 can be made of high-strength aluminum alloy, which improves the structural strength of the seat plate 6 and back plate 7 and prevents self-disintegration during the test.

[0033] The bottom four corners of the aircraft seat body 2 are fixedly connected to the mounting base 1 by high-strength positioning bolts.

[0034] By adopting the above structure, the installation strength of the aircraft seat and the mounting base 1 can be improved by using high-strength positioning bolts, while ensuring that the aircraft seat can be disassembled and assembled with the mounting base 1.

[0035] The working principle of this utility model is as follows: The four corners of the bottom of the aircraft seat body 2 are fixedly connected to the mounting base 1 by high-strength positioning bolts. The control screw 15 is rotated by the second servo motor 16. After the control screw 15 rotates, it will drive the lower pressure frame 4 to move, thereby achieving the downward pressing action. Then, the drive gear 13 is rotated by the first servo motor 12. After the drive gear 13 rotates, it will drive the second drive gear 14 to rotate. The second drive gear 14 will drive the bidirectional screw 11 to rotate. The bidirectional screw 11 will then drive the two extension arms 10 to extend, thereby pushing the guide slide 9 to move. The guide slide 9 pushes the seat plate 6 and the back plate 7 to achieve the overall pressure test of the aircraft seat base and backrest. The angle of the seat plate 6 and the back plate 7 can be adjusted to fit the sitting posture of the aircraft seat and improve the test effect.

[0036] In summary, by controlling the downward pressure of the pressure plate 4 through the control component, the pressure plate is driven to perform pressure testing on the aircraft seat. The pressure is then distributed to the backrest of the aircraft seat through the drive component, thereby improving the test results and obtaining more comprehensive static test data of the aircraft seat.

[0037] The specific embodiments described herein are merely illustrative examples illustrating the spirit of this utility model. Those skilled in the art to which this utility model pertains may make various modifications or additions to the described specific embodiments or use similar methods to substitute them, without departing from the spirit of this utility model or exceeding the scope defined by the appended claims.

Claims

1. A static testing device for an aircraft seat, comprising a mounting base (1) and an aircraft seat body (2) fixed on the mounting base (1), characterized in that, An adjustment frame (3) is fixed on one side of the mounting base (1). A lower pressure frame (4) is slidably arranged on the adjustment frame (3). A drive frame (5) is fixed on the lower pressure frame (4). A pressure plate is arranged on the drive frame (5). The pressure plate includes a seat plate (6) and a back plate (7) hinged to the seat plate (6). Guide grooves (8) are opened on both the seat plate (6) and the back plate (7). A guide slide (9) is slidably connected in each guide groove (8). A drive assembly is arranged in the drive frame (5). The drive assembly is connected to the two guide slides (9). An adjustment assembly is arranged in the adjustment frame (3). The adjustment assembly is connected to the lower pressure frame (4).

2. The static testing device for aircraft seats according to claim 1, characterized in that, The drive assembly includes a pair of extension arms (10) slidably connected within the drive frame (5) and a bidirectional lead screw (11) rotatably connected within the drive frame (5). A servo motor (12) is fixed within the drive frame (5). A drive gear (13) is coaxially fixedly connected to the output shaft of the servo motor (12). A drive gear (14) is coaxially fixedly connected to the bidirectional lead screw (11). The drive gear (13) meshes with the drive gear (14). The threaded sections on both sides of the bidirectional lead screw (11) are threadedly connected to the corresponding extension arms (10). One end of each extension arm (10) is rotatably connected to the corresponding guide slide (9).

3. The static testing device for aircraft seats according to claim 1, characterized in that, The control assembly includes a control screw (15) rotatably connected inside the control frame (3) and a servo motor (16) fixedly connected inside the control frame (3). The output shaft of the servo motor (16) is coaxially fixedly connected to the control screw (15), and the control screw (15) is threadedly connected to the lower pressure frame (4).

4. The static testing device for aircraft seats according to claim 1, characterized in that, The seat plate (6) and back plate (7) are made of high-strength aluminum alloy.

5. The static testing device for aircraft seats according to claim 1, characterized in that, The bottom four corners of the aircraft seat body (2) are fixedly connected to the mounting base (1) by high-strength positioning bolts.

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