A static test loading device for a missile skin

Abstract

The utility model relates to the technical field of skin static force load test, concretely relates to a missile skin static test loading device. The device includes a missile skin, a test truss, a skin support fixing block, a lifting eye screw, a weight tray, a fixed pulley, a weight, a steel wire rope, a guide wheel and a guide wheel support, one lifting eye screw is fixed at each force load loading position on the missile skin, the steel wire rope is fixed on the ring of the lifting eye screw by using a rope clamp, the direction of force load is changed to vertical downward through the fixed pulley and the guide wheel, the other end of the steel wire rope is connected with the weight tray, and the weight corresponding to the force load loading point is placed on the tray to simulate the test load of the missile skin loading point, the test truss is used for fixing the skin support fixing block, the fixed pulley and the guide wheel support, and the fixed pulley and the guide wheel are used for changing the direction of the steel wire rope. The utility model is simple in structure, realizes the static loading of the missile skin quickly, and satisfies the static test demand of other structural members.

Description

Technical Field

[0001] This utility model relates to the field of static load testing technology for bomb skin, specifically to a static load testing device for bomb skin. Background Technology

[0002] The skin is a crucial component of the bomb's inverted suspension assembly. During flight, its outer surface bears uniformly distributed aerodynamic loads. Ground tests require realistic simulation of these aerodynamic loads to assess the skin's performance. Static load testing of the skin involves applying inward or outward loads point-by-point along the normal direction of the curved surface at the loading points of the structure, and then observing the deformation at the displacement measurement points of the skin structure.

[0003] To achieve weight reduction, aerial bombs typically use composite materials such as glass fiber or carbon fiber for their skin. Currently, static loading tests on composite skins mainly involve dividing the load on the skin's outer surface into zones and applying loads using tension or compression levers and hydraulic actuators. Common loading methods include distributed loading blocks / canvas tab loading, clamp loading, and perforated clamp loading. Loading block and canvas tab loading methods are typically used to apply aerodynamic loads to the skin surface. Loading blocks or distributed tension levers are attached to the skin surface, and loads are applied to the test specimen by applying loads to these blocks or tabs. Loading block loading is suitable for distributed tension and compression loads, while canvas tab loading is only suitable for tension loads; both can achieve distributed composite loads. Clamps are connected to the test specimen primarily through adhesion and preload; this method can withstand large normal loads. The perforated clamping loading method requires drilling holes in the skin, which damages the skin structure itself. It can achieve the combined action of point, surface concentrated force loads or combined loads. Since the connection is rigid, the load capacity depends on the load capacity of the connecting bolts. The load per unit area is significantly better than the above two methods, and the load direction is not restricted.

[0004] The disadvantages of loading block and canvas strip loading methods are that the load-bearing capacity per unit area of ​​the loading block or canvas strip is limited. This necessitates increasing the number or area of ​​loading blocks or canvas strips to improve load-bearing capacity. Under high load requirements, this can lead to numerous loading points and a complex load synthesis system, potentially even resulting in the inability to load due to excessive load within a limited area. For composite materials with low interlaminar shear strength, interlaminar pull-out may occur during testing, causing unnecessary damage to the specimen. The clamping plate loading method has low tangential load-bearing capacity and is prone to slippage, making it unsuitable for specimens with high centrifugal forces. Furthermore, the clamping plate loading method requires several upper and lower clamping plates, which need to be fixed with bolts, resulting in a complex structure. When there are many loading points on the specimen, the required clamping plates occupy a significant amount of space. The disadvantage of the perforated clamping loading method is that it requires the design of clamping fixtures. For irregular curved surfaces, the boundary effect is significant, and the layout of the connecting holes directly affects the local strength of the specimen. Summary of the Invention

[0005] Based on the above-mentioned technical problems, this utility model proposes a static test loading device for bomb skin to solve the problems of limited load capacity, test piece damage, inability to adapt to test pieces with large centrifugal force, and the layout of perforated clamping connection holes directly affecting the test results of existing common static test loading methods for composite material skin.

[0006] To address the aforementioned technical problems, one objective of this utility model is to provide a static loading test device for bomb skin. This device comprises a bomb skin 1, a test truss 2, a skin support and fixing block 3, lifting eye screws 4, a weight tray 5, a fixed pulley 6, weights 7, a steel wire rope 8, a guide wheel 10, and a guide wheel bracket 11.

[0007] A lifting eye screw 4 is fixed on the bomb skin 1 at each force load position. The wire rope 8 is fixed to the ring of the lifting eye screw 4 by rope clamp. The wire rope 8 changes the direction of the force load to vertical downward through the fixed pulley 6 and the guide wheel 10.

[0008] The other end of the steel wire rope 8 is connected to the weight tray 5. The weight 7 corresponding to the force load loading point is placed on the tray 5 to simulate the test load of the bomb skin 1 loading point.

[0009] The test truss 2 is used to fix the skin support fixing block 3, the fixed pulley 6 and the guide wheel bracket 11. The fixed pulley 6 and the guide wheel 10 are used to change the direction of the wire rope 8.

[0010] Furthermore, the test device also includes a dial gauge 9, which is installed at the static test displacement measuring point of the bomb skin 1. The static test displacement measuring points are symmetrically distributed along the central axis of the skin 1, so the dial gauge 9 is symmetrically arranged at the two displacement measuring points.

[0011] Furthermore, holes of a certain size are drilled on the bomb skin 1 at each force load location. The size of the holes is as small as possible to ensure the integrity of the skin structure.

[0012] Furthermore, the guide wheel bracket 11 is composed of two square tubes 14 and several long steel tubes 15.

[0013] Furthermore, the guide wheel 10 is made of thin steel pipe and is fitted onto long steel pipe 15, which is welded together with two square pipes 14.

[0014] Furthermore, the bomb skin 1 is fixed to the skin support fixing block 3 by countersunk screws 13, and the top arc surface of the skin support fixing block 3 is consistent with the inner surface of the contact part of the bomb skin 1.

[0015] Furthermore, each force load on the bomb skin 1 is applied independently, without affecting each other.

[0016] The above-described one or more technical solutions of this utility model have at least one or more of the following technical effects:

[0017] To address the shortcomings of the aforementioned loading methods, this invention employs a method where a hole is drilled at the load application point of the test specimen. A lifting eye screw passes through this hole, and a nut secures the lifting eye screw and the skin. The load or weight is then suspended from the lifting eye screw by a steel wire rope. This loading method is simple to fix and prevents interlayer pull-out of the test specimen during testing. It also requires less space when there are multiple load points on the test specimen.

[0018] This invention provides a static loading test device for bomb skin, which has a simple structure and can quickly realize static loading of bomb skin, and can also meet the static test requirements of other structural components.

[0019] Compared with the prior art, this utility model has the characteristics that each loading point is independent and does not affect the others, and the loading point has a large load-bearing capacity. Attached Figure Description

[0020] Figure 1 Schematic diagram of the static loading test device for bomb skin;

[0021] Figure 2 Schematic diagram of guide wheel bracket;

[0022] Figure 3 : Schematic diagram of the connection between bomb skin and lifting eye bolts and skin support fixing blocks.

[0023] Among them: 1-bomb skin, 2-test truss, 3-skin support fixing block, 4-lifting eye screw, 5-weight tray, 6-fixed pulley, 7-weight, 8-wire rope, 9-dial indicator, 10-guide wheel, 11-guide wheel bracket, 12-nut, 13-countersunk screw, 14-square tube, 15-long steel pipe. Detailed Implementation Plan

[0024] This invention provides a simple loading device for static testing of bomb skin, including a skin support fixing block, eye bolts, nuts, wire ropes, wire rope clips, fixed pulleys, guide wheels, guide wheel brackets, weight trays, counterweights, a test truss, and a dial indicator. The fixed pulleys and guide wheels convert each force load on the bomb skin into the gravity of the vertically downward-facing weights. Holes of a specific size are drilled at each force load location on the bomb skin 1; these holes are kept as small as possible to ensure the integrity of the skin structure. Guide wheels are used instead of fixed pulleys to change the direction of the wire rope, resulting in a simple structure. Each force load on the bomb skin 1 is loaded independently, without mutual interference.

[0025] The skin support fixing block is used to fix the bomb skin. The bomb skin has countersunk holes for fixing the bomb. During the test, the bomb skin is fixed to the skin support fixing block using these countersunk holes, and then the skin support fixing block is fixed to the test truss.

[0026] The bomb skin actually bears a uniformly distributed aerodynamic load, with varying load magnitudes in different areas. Since uniformly distributed loads are difficult to achieve, to facilitate experimental operation, the uniformly distributed load is converted into a concentrated force load based on the bending moment equivalence principle. Sufficiently small holes are drilled at the loading points on the bomb skin, with the hole direction aligned with the normal direction of the curved surface at the loading point. To avoid large-area damage to the skin structure, the holes should be as small as possible, just large enough to pass through the threads of the eye bolts. The eye bolts are secured with nuts, and the wire rope is fixed to the eye bolts using rope clamps. Then, a weight tray and counterweights are suspended from the end of the wire rope for loading. By adjusting the number, position, and angle of the pulleys, the direction of the wire rope at the loading point should be consistent with the normal direction of the curved surface at the loading point of the skin.

[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the embodiments and accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, and not all of the embodiments obtained. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model are within the protection scope of the present utility model.

[0028] like Figure 1As shown, the static loading test device for bomb skin consists of bomb skin 1, test truss 2, skin support fixing block 3, eye bolt 4, weight tray 5, fixed pulley 6, weight 7, wire rope 8, dial indicator 9, guide wheel 10, and guide wheel bracket 11. An eye bolt 4 is fixed to each load application point on the bomb skin 1. The wire rope 8 is secured to the ring of the eye bolt 4 using rope clamps. The wire rope 8 changes the direction of the load to vertically downward through the fixed pulley 6 and guide wheel 10. The other end of the wire rope 8 is connected to the weight tray 5. Weights 7, corresponding to the load application point, are placed on the tray 5 to simulate the test load at the loading point of the bomb skin 1.

[0029] Dial gauge 9 is installed at the static test displacement measuring point of bomb skin 1. The static test displacement measuring points are symmetrically distributed along the central axis of skin 1, so dial gauge 9 is symmetrically arranged at the two displacement measuring points.

[0030] The test truss 2 is used to fix the skin support fixing block 3, the fixed pulley 6, and the guide wheel bracket 11. For example... Figure 2 As shown, the guide wheel bracket 11 consists of two square tubes 14 and several long steel tubes 15. The guide wheel 10 is made of thin steel tube and is fitted onto the long steel tubes 15. The long steel tubes 15 and the two square tubes 14 are welded together. The fixed pulley 6 and the guide wheel 10 are used to change the direction of the wire rope 8.

[0031] like Figure 3 As shown, holes of a certain size are drilled on the bomb skin 1 at each load application point. The direction of the holes is the normal direction of the curved surface at the load application point of the bomb skin 1. The eye bolts 4 pass through the holes on the bomb skin 1 and are fixed on the other side by nuts 12.

[0032] To simulate the actual working conditions of the bomb skin 1, the bomb skin 1 is fixed to the skin support fixing block 3 by countersunk screws 13. The top arc surface of the skin support fixing block 3 is consistent with the inner surface of the contact part of the bomb skin 1.

[0033] Obviously, those skilled in the art can make various modifications and variations to the embodiments of this utility model without departing from the spirit and scope of the embodiments of this utility model. Therefore, if these modifications and variations of the embodiments of this utility model fall within the scope of the claims of this utility model and their equivalents, then this utility model also intends to include these modifications and variations. In the technical solution of this utility model, a soft rope of equivalent strength is used instead of a steel wire rope; and a heavy object of equivalent weight is used instead of a weight.

[0034] This invention is used for static testing of bomb skin, simulating the actual aerodynamic load on bomb skin. The deformation values ​​obtained in the test are close to the simulation results, proving the feasibility of this invention.

Claims

1. A loading device for static testing of bomb skin, characterized in that: The device consists of bomb skin (1), test truss (2), skin support fixing block (3), lifting eye screw (4), weight tray (5), fixed pulley (6), weight (7), steel wire rope (8), guide wheel (10), and guide wheel bracket (11). A lifting eye screw (4) is fixed on the bomb skin (1) at each force load position. The wire rope (8) is fixed to the ring of the lifting eye screw (4) by rope clamp. The wire rope (8) changes the direction of the force load to vertical downward through the fixed pulley (6) and the guide wheel (10). The other end of the wire rope (8) is connected to the weight tray (5), and the weight (7) corresponding to the force load loading point is placed on the tray (5) to simulate the test load of the bomb skin (1); The test truss (2) is used to fix the skin support fixing block (3), the fixed pulley (6) and the guide wheel bracket (11). The fixed pulley (6) and the guide wheel (10) are used to change the direction of the wire rope (8).

2. The loading device for static testing of bomb skin according to claim 1, characterized in that: The test device also includes a dial gauge (9), which is installed on the static test displacement measuring point of the bomb skin (1). The static test displacement measuring point is symmetrically distributed along the central axis of the skin (1), so the dial gauge (9) is symmetrically arranged at the two displacement measuring points.

3. The loading device for static testing of bomb skin according to claim 1, characterized in that: Holes of a certain size are drilled at each force load location on the bomb skin (1). The size of the holes is as small as possible to ensure the integrity of the skin structure.

4. The loading device for static testing of bomb skin according to claim 1, characterized in that: The guide wheel bracket (11) consists of two square tubes (14) and several long steel tubes (15).

5. The static load-bearing device for bomb skin testing according to claim 1, characterized in that: The guide wheel (10) is made of thin steel pipe and is fitted onto long steel pipe (15). The long steel pipe (15) and two square pipes (14) are welded together.

6. The static load-bearing device for bomb skin testing according to claim 1, characterized in that: The bomb skin (1) is fixed to the skin support fixing block (3) by countersunk screws (13). The top arc surface of the skin support fixing block (3) is consistent with the inner surface of the contact part of the bomb skin (1).

7. The static load-bearing device for bomb skin testing according to claim 1, characterized in that: Each force load on the bomb skin (1) is applied individually and does not affect each other.

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