Aircraft floor slide rail test device and use method

Abstract

The present invention discloses an aircraft floor slide rail test device, including a clamp A and a clamp B, wherein the clamp A and the clamp B cooperate to clamp and fix the slide rail, and the clamp A is also connected and fixed to the floor rail groove by anchor bolts arranged at both ends thereof; it also includes a loading joint connected to the slide rail; it also includes a ferrule connected to the slide rail and used to fix the loading joint; it also includes two left and right actuators used to apply horizontal loads to the loading joint. A method for using an aircraft floor slide rail test device is also disclosed. The present invention designs an aircraft slide rail clamping structure for simulating the constraints of the aircraft floor slide rail in actual use, designs a special loading joint, a ferrule and an auxiliary loading structure for applying the actual load on the aircraft slide rail, and proposes an equipment connection method and control strategy, which can achieve the elimination of torque influence while applying the test force, can conveniently realize single-direction and multi-direction loading, and has strong practicality.

Description

Technical Field

[0001] The invention relates to an aircraft floor slide rail test device and a use method thereof, which are applied to a research and development test of the bearing capacity or a strength verification test of an aircraft floor slide rail. Background Art

[0002] In the existing aircraft floor rail test, there is a lack of equipment and methods specifically for rail bearing capacity testing. The commonly used method is to perform mechanical calculations and assist with finite element analysis to determine the rail bearing capacity, and to confirm the strength of related auxiliary structures including the rail by planning seat connection static limit / ultimate load tests. The disadvantage of this strength assessment method is that it cannot accurately obtain the bearing capacity of the rail parts, and for manufacturers, it is also impossible to obtain the manufacturing process parameters of the rail of a specific material.

[0003] In practice, the load-bearing capacity of the slide rail is closely related to the initial contact state of the slide rail. In the process of elastic-plastic deformation, the numerical calculation model is complex, and the accuracy of the calculation results also needs to be verified by experimental technology. In order to solve this problem, a device specifically used for aircraft floor slide rail load-bearing capacity testing was invented, and a method for using the device was proposed. Summary of the invention

[0004] The purpose of the present invention is to provide a test device and a method for use in a load-bearing capacity test of an aircraft floor slide rail or a floor slide rail structural strength verification test, so as to solve the problems of the existing aircraft floor slide rail test device and method.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] An aircraft floor slide rail test device includes a fixture A and a fixture B, wherein the fixture A and the fixture B cooperate to clamp and fix the slide rail, and the bottom surfaces of the fixture A and the fixture B contact the inner edge of the slide rail, and the fixture A is also connected and fixed to the floor rail groove through anchor bolts arranged at both ends thereof; further includes a loading joint connected to the slide rail; further includes a ferrule connected to the slide rail and used to fix the loading joint; further includes two left and right actuators used to apply a horizontal load to the loading joint;

[0007] The clamping surface of the clamp A is processed according to the shape of the aircraft slide rail web and the inner edge of the slide rail, and the clamp A is provided with a fastening bolt through hole A; the clamping surface of the clamp B is processed according to the shape of the aircraft slide rail web and the inner edge of the slide rail, and the clamp B is provided with a fastening bolt through hole B; the clamps A and B are connected and fixed by fastening bolts passing through the corresponding holes A and B;

[0008] A connector A and a connector B are respectively provided on both sides of the loading joint. The actuator is a force-controlled actuator. One end of the actuator on the left is connected to the connector A through a sensor A, and one end of the actuator on the right is connected to the connector B through a sensor B. The other ends of the left and right actuators are respectively hingedly connected to the fixing seats, and the fixing seats are connected and fixed to the ground rail groove through anchor bolts.

[0009] As a further solution of the present invention: the outer shapes of the loading joint and the ferrule are both processed to conform to the internal structure of the slide rail flange and the vertical rib.

[0010] As a further solution of the present invention: the ferrule is composed of two symmetrical parts, the lower end of the loading joint is installed on the slide rail and is at the tangent point position, and the ferrule is installed on both sides of the loading joint and fastened by bolts.

[0011] As a further solution of the present invention: it also includes an actuator cylinder for applying a vertical load to the loading joint, one end of the actuator cylinder is hinged and fixed, and the other end of the actuator cylinder is connected to the loading joint through a sensor C.

[0012] A method for using an aircraft floor slide rail test device comprises the following steps:

[0013] 1) Clamp the slide rail with the help of clamp A and clamp B. Clamp A and clamp B are connected and fixed by fastening bolts, and clamp A is connected and fixed to the ground rail groove by anchor bolts;

[0014] 2) Place the loading joint into the slide rail, slide it to the tangent point, install the ferrules from both sides of the loading joint, and tighten them with bolts;

[0015] 3) Connectors A and B are installed on the loading joint, and loads are applied to connectors A and B by the actuator. The actuator and the sensor connected to the front end thereof realize closed-loop control, and the control system dynamically obtains the load values ​​of sensor A and sensor B and performs calculations in the calculation channel;

[0016] 4) Multi-directional combined loading is achieved by applying load to the vertically fixed actuator.

[0017] Compared with the prior art, the beneficial effects of the present invention are as follows: the aircraft floor slide rail test device is designed with an aircraft slide rail clamping structure for simulating the constraints of the aircraft floor slide rail in actual use, and is designed with a special loading joint, a ferrule and an auxiliary loading structure for applying the actual load of the aircraft slide rail. An equipment connection method and a control strategy are proposed, which can achieve the elimination of torque influence while applying the test force, can conveniently realize single-direction and multi-directional loading, and has strong practicality. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the clamping of the slide rail clamp in the present invention.

[0019] Figure 2 It is an axonometric schematic diagram of the loading joint in the present invention.

[0020] Figure 3 It is an axonometric schematic diagram of the butt-jointed ferrule in the present invention.

[0021] Figure 4 It is an axonometric schematic diagram of half of the ferrule in the present invention.

[0022] Figure 5 It is a schematic diagram of the connection between the loading joint and the slide rail in the present invention.

[0023] Figure 6 It is a schematic diagram of applying lateral load in the present invention.

[0024] Figure 7 This is a schematic diagram of applying a heading load in the present invention.

[0025] Figure 8 It is a schematic diagram of unidirectional loading in the present invention.

[0026] Fig. 9 It is a schematic diagram of multi-directional loading in the present invention.

[0027] In the figure: 1-clamp A, 2-clamp B, 3-slide rail, 4-fastening bolt, 5-anchor bolt, 6-ground rail groove, 7-loading joint, 8-ferrule, 9-actuator, 10-connector A, 11-connector B, 12-sensor A, 13-sensor B, 14-fixed seat, 15-sensor C. DETAILED DESCRIPTION

[0028] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not 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. Example 1

[0029] See also Figures 1 to 8 In an embodiment of the present invention, an aircraft floor slide rail test device includes a clamp A1 and a clamp B2, wherein the clamp A1 and the clamp B2 cooperate to clamp and fix the slide rail 3, and the bottom surfaces of the clamp A1 and the clamp B2 are in contact with the inner edge of the slide rail 3.

[0030] The clamping surface (the contact surface with the slide rail 3) of the clamp A1 is shaped and processed according to the shape of the web of the aircraft slide rail 3 and the inner edge of the slide rail 3, and a hole A for passing the fastening bolt 4 is opened; the clamping surface (the contact surface with the slide rail 3) of the clamp B2 is shaped and processed according to the shape of the web of the aircraft slide rail 3 and the inner edge of the slide rail 3, and a hole B for passing the fastening bolt 4 is opened; the clamp A1 and the clamp B2 are connected and fixed by the fastening bolts 4 passing through the corresponding holes A and B; the clamp A1 is also connected and fixed to the ground rail groove 6 by the anchor bolts 5 arranged at its two ends.

[0031] like Figure 5 As shown, it also includes a loading joint 7 connected to the slide rail 3, and the loading joint 7 is shaped and processed with the flange of the slide rail 3 and the internal structure of the vertical rib to ensure that under the load, the tangent point of the loading joint 7 and the slide rail 3 is the expected position; it also includes a clamping sleeve 8 connected to the slide rail 3 and used to fix the loading joint 7, and the clamping sleeve 8 is shaped and processed with the flange of the slide rail 3 and the internal structure of the vertical rib to ensure that under the load, the tangent point of the clamping sleeve 8 and the slide rail 3 is the expected position, and the clamping sleeve 8 is composed of two symmetrical parts; the assembly method and order of the clamping sleeve 8, the loading joint 7, and the slide rail 3 are as follows: first put the loading joint 7 into the slide rail 3, slide it to Figure 6 , 7 At the tangent point position shown in the figure, the ferrule 8 is installed from both sides of the loading joint 7 and then fastened by bolts; it also includes left and right two actuator cylinders 9 for applying horizontal load to the loading joint 7, and the two sides of the loading joint 7 are respectively provided with a connecting member A10 and a connecting member B11, one end of the left actuator cylinder 9 is connected to the connecting member A10 through a sensor A12, and one end of the right actuator cylinder 9 is connected to the connecting member B11 through a sensor B13, and the other ends of the left and right actuator cylinders 9 are respectively hingedly connected to the fixing seat 14, and the fixing seat 14 is connected and fixed to the ground rail groove 6 through an anchor bolt 5.

[0032] Specific application:

[0033] Reference Figure 1 After the clamps A1 and B2 are fixed to the slide rail 3 by the fastening bolts 4, they are fixed to the universal floor rail groove 6 of the factory building by the anchor bolts 5 to realize the constraint of the slide rail 3;

[0034] Reference Figure 5 , the load is applied to the loading joint 7 or the ferrule 8 through the connector A10 and the connector B11;

[0035] Reference Figure 5 , 6 , when subjected to lateral force F, under the action of connector A10 and connector B11, the sleeve 8 is tangent to the slide rail 3 at point O1, realizing lateral load application;

[0036] Reference Figure 5 ,7 , when subjected to the heading force F, under the action of the connector A10 and the connector B11, the loading joint 7 is tangent to the slide rail 3 at point O2, realizing the application of the heading load;

[0037] Reference Figure 8 , the actuator 9 applies load to the connector A10 and the connector B11. The actuator 9 is a force-controlled actuator, and the sensor connected to its front end realizes closed-loop control. The control system dynamically obtains the load values ​​of the sensors A12 and B13, and performs calculations in the calculation channel. Let the load of the right actuator 9 be Fright, and the load of the left actuator 9 be Fleft. At this time, the distance between the horizontal center line of the connector B11 and the tangent point O1 is H1, and the distance between the horizontal center line of the connector A10 and the tangent point O1 is H2. When loading, the numerical relationship of the loads applied by the two actuators 9 is controlled to satisfy the following relationship:

[0038] Ftarget=Fright-Fleft

[0039] M=Fright*H1-Fleft*H2=0

[0040] In the above formula, Ftarget is the estimated load-bearing capacity limit of the slide rail. The above relationship is used to apply Ftarget while eliminating the additional torque.

[0041] During lateral loading, the distance between the horizontal center line of connector B11 and the tangent point O2, and the distance between the horizontal center line of connector A10 and the tangent point O2 change due to different distances of the tangent points, and the distance parameters need to be reselected. Example 2

[0042] Reference Fig. 9 This embodiment is different from Embodiment 1 in that it also includes an actuator 9 for applying a vertical load to the loading joint 7. One end of the actuator 9 is hinged and fixed, and the other end of the actuator 9 is connected to the loading joint 7 through a sensor C15. On the basis of the original unidirectional loading, multi-directional combined loading is realized.

[0043] The aircraft floor slide rail test device is designed with an aircraft slide rail 3 clamping structure for simulating the constraints of the aircraft floor slide rail 3 in actual use, and is designed with a special loading joint 7, a ferrule 8 and an auxiliary loading structure for applying the actual load to the aircraft slide rail 3. An equipment connection method and a control strategy are proposed, which can achieve the elimination of torque influence while applying the test force, and can conveniently realize single-direction and multi-directional loading, and is highly practical.

[0044] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

[0045] The above are only preferred embodiments of the present invention. It should be pointed out that, for those skilled in the art, several modifications and improvements can be made without departing from the concept of the present invention. These should also be regarded as the protection scope of the present invention. These will not affect the effect of the implementation of the present invention and the practicality of the patent.

Claims

1. An aircraft floor slide rail test device, comprising a fixture A (1) and a fixture B (2), characterized in that: The clamp A (1) and the clamp B (2) cooperate to clamp and fix the slide rail (3), and the bottom surfaces of the clamp A (1) and the clamp B (2) are in contact with the inner edge of the slide rail (3). The clamp A (1) is also connected and fixed to the ground rail groove (6) through anchor bolts (5) arranged at both ends thereof; it also includes a loading joint (7) connected to the slide rail (3); it also includes a clamping sleeve (8) connected to the slide rail (3) and used to fix the loading joint (7); it also includes two left and right actuators (9) for applying a horizontal load to the loading joint (7); The clamping surface of the clamp A (1) is processed according to the shape of the web of the aircraft slide rail (3) and the inner edge of the slide rail (3), and the clamp A (1) is provided with a hole A for passing the fastening bolt (4); the clamping surface of the clamp B (2) is processed according to the shape of the web of the aircraft slide rail (3) and the inner edge of the slide rail (3), and the clamp B (2) is provided with a hole B for passing the fastening bolt (4); the clamp A (1) and the clamp B (2) are connected and fixed by fastening bolts (4) passing through the corresponding holes A and B; A connecting member A (10) and a connecting member B (11) are respectively provided on both sides of the loading joint (7); the actuator (9) is a force-controlled actuator; one end of the actuator (9) on the left side is connected to the connecting member A (10) via a sensor A (12); one end of the actuator (9) on the right side is connected to the connecting member B (11) via a sensor B (13); the other ends of the two actuators (9) on the left and right sides are respectively hingedly connected to a fixing seat (14); and the fixing seat (14) is connected and fixed to the ground rail groove (6) via an anchor bolt (5).

2. The aircraft floor slide rail test device according to claim 1, characterized in that: The outer shapes of the loading joint (7) and the clamping sleeve (8) are processed to match the flange of the slide rail (3) and the internal structure of the vertical ribs.

3. The aircraft floor slide rail test device according to claim 2, characterized in that: The clamping sleeve (8) is composed of two symmetrical parts. The lower end of the loading joint (7) is mounted on the slide rail (3) and is located at a tangent point. The clamping sleeve (8) is mounted on both sides of the loading joint (7) and is fastened by bolts.

4. The aircraft floor slide rail test device according to any one of claims 1 to 3, characterized in that: It also includes an actuator (9) for applying a vertical load to the loading joint (7); one end of the actuator (9) is hinged and fixed, and the other end of the actuator (9) is connected to the loading joint (7) via a sensor C (15).

5. A method for using the aircraft floor slide rail test device according to any one of claims 1 to 4, characterized in that: The following steps are involved: 1) The slide rail (3) is clamped and fixed by the clamp A (1) and the clamp B (2), the clamp A (1) and the clamp B (2) are connected and fixed by the fastening bolts (4), and the clamp A (1) is connected and fixed to the ground rail groove (6) by the anchor bolts (5); 2) Place the loading joint (7) into the slide rail (3), slide it to the tangent point, install the ferrules (8) from both sides of the loading joint (7), and tighten them with bolts; 3) Connecting member A (10) and connecting member B (11) are installed on the loading joint (7), and load is applied to connecting member A (10) and connecting member B (11) by the actuator (9). The actuator (9) and the sensor connected to the front end thereof realize closed-loop control, and the control system dynamically obtains the load values ​​of sensor A (12) and sensor B (13), and performs calculations in the calculation channel; 4) By applying a load to the vertically fixed actuator (9), multi-directional combined loading is achieved.

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