Aircraft test loading lever non-collinear connecting device and design method thereof

Abstract

The invention relates to the technical field of aircraft structure fatigue tests, and discloses an aircraft test loading lever non-collinear connecting device and a design method thereof.A connecting joint is designed to be of a structure with a U-shaped cross section, so that a dowel bar can be vertically inserted into a force transmission hole of a force transmission single lug; therefore, a force transmission path between a lever connection point and an airplane test loading point is changed, test force load application in a narrow space is realized, and the device has the characteristics of simple structural form, reliable connection mode, convenience in installation and the like; in the design process of the loading lever of the non-collinear connecting device, the lower limit value of the diameter of a dowel bar, the lower limit value of the diameter of a bolt hole and the minimum distance from the center of the bolt hole to the edge of a U-shaped supporting plate are analyzed in advance, and then the structural design of the loading lever, a force transmission single lug and a connecting joint is conducted according to the key parameters. The aircraft test loading lever non-collinear connecting device which is reasonable in structure and excellent in performance can be designed, and the requirement of an aircraft structure fatigue test is met.

Description

Technical Field

[0001] This invention relates to the field of aircraft structural fatigue testing technology, and discloses a non-collinear connection device for aircraft test loading levers and its design method. Background Technology

[0002] To more realistically simulate aircraft loading conditions, aerodynamic forces are typically represented as several concentrated forces in aircraft structural fatigue tests. The point of application of these concentrated forces is referred to as the aircraft loading point. Due to limitations such as the aircraft's structural load-bearing capacity and the number of testing loading devices, the concentrated forces at various nodes on the aircraft must be connected using loading levers and applied by hydraulic actuators. Normally, each level of the lever system uses joints or pull plates for connection, characterized by the load direction being parallel to the direction of the joint bolts. However, in certain special scenarios, such as fuselage doors, the limited space at the connection frame restricts the installation of the lever system, making it difficult to ensure that the lever connection point and the aircraft loading point are on the same straight line. Therefore, the above connection methods are limited and cannot meet the testing requirements. Summary of the Invention

[0003] The purpose of this invention is to provide a non-collinear connection device for aircraft test loading levers and its design method. It changes the force transmission path from the lever connection point to the aircraft test loading point, realizing the application of test force load in a confined space. It has the characteristics of simple structure, reliable connection method, and convenient installation, and can meet the requirements of aircraft structural fatigue testing.

[0004] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows: A non-collinear connection device for loading levers in aircraft testing includes: A loading lever, wherein the fulcrum of the loading lever is hinged to the reaction seat; A force-transmitting single ear includes a fixing plate and an ear piece mounted on the fixing plate. The fixing plate is used to fix and connect to the test loading point of the aircraft to be tested. The ear piece of the force-transmitting single ear is provided with a force-transmitting hole. The connecting joint has a U-shaped cross-section and is provided with a force transmission rod that is perpendicular to the cross-section of the U-shaped structure and can be inserted into the force transmission hole; the two U-shaped support plates of the connecting joint are fixed to the resistance point of the loading lever by at least two bolts.

[0005] Furthermore, the U-shaped structure of the connecting joint is provided with a mounting block, and the mounting block is provided with a mounting hole, and the force transmission rod is detachably fixed in the mounting hole.

[0006] Furthermore, the mounting hole is a threaded hole, and the force transmission rod is fixed in the mounting hole by cooperating with the threaded hole.

[0007] Furthermore, two nuts are installed on the outer wall of the force transmission rod through external thread engagement. The two nuts are used to limit and fix the force transmission rod on the mounting block on both sides of the mounting hole after the force transmission rod passes through the mounting hole.

[0008] Furthermore, a spherical bearing is provided inside the force transmission hole, and the force transmission rod is inserted into the inner ring of the spherical bearing.

[0009] Furthermore, a polyurethane block is provided between the fixing plate of the force transmission single ear and the test loading point, and the fixing plate and the test loading point are respectively bonded and fixed to the polyurethane block.

[0010] To achieve the above-mentioned technical effects, the present invention also provides a design method for a non-collinear connection device for aircraft test loading levers, used to obtain the aforementioned non-collinear connection device, comprising: Based on the input load applied to the loading lever, and the positional relationship between the fulcrum, the force application point, and the test loading point on the loading lever, the output load of the loading lever at the test loading point under the input load condition is analyzed and obtained. Based on the output load obtained from the analysis, and the material property parameters of the force transmission rod or bolt, the lower limit value of the diameter of the force transmission rod and the lower limit value of the diameter of the bolt are obtained respectively. Based on the output load obtained from the analysis, the thickness of the U-shaped support plate of the connecting joint, and the size parameters, performance parameters, and quantity of the bolts installed at the resistance point, the minimum distance from the center of the bolt hole to the edge of the U-shaped support plate at the corresponding position of the bolt is obtained. Based on the lower limit of the diameter of the force transmission rod and the minimum distance from the center of the bolt hole to the edge of the U-shaped support plate, the structural design of the loading lever, the force transmission lug, and the connecting joint is completed.

[0011] Furthermore, the lower limit of the diameter of the force transmission rod is based on... Analysis yielded, among which This is the lower limit of the diameter of the force transmission rod. The tensile strength of the force transmission rod material. The load is the output load of the loading lever at the test loading point under the input load condition. The safety factor for the force transmission rod ranges from 2.5 to 4.

[0012] Furthermore, the lower limit value of the bolt diameter is based on... Analysis yielded, among which This is the lower limit value for the bolt diameter. This represents the number of bolts at the resistance point. The tensile strength of the bolt material. The load is the output load of the loading lever at the test loading point under the input load condition. The safety factor for the bolt is 2.5 to 4; the minimum distance from the center of the bolt hole at the corresponding position on the U-shaped support plate to the edge of the U-shaped support plate is based on... , The minimum distance from the center of the bolt hole at the corresponding position on the U-shaped support plate to the edge of the U-shaped support plate. Where is the diameter of the bolt. , The thickness of the U-shaped support plate.

[0013] Compared with the prior art, the beneficial effects of this invention are: 1. The present invention designs the connecting joint with a U-shaped cross-section, so that the force transmission rod can be inserted vertically into the force transmission hole of the force transmission ear. The force transmission rod of the connecting joint is changed from being perpendicular to the lever arm direction to being horizontal to the lever arm direction, which changes the force transmission path from the lever connection point to the aircraft test loading point. This enables the application of test force load in a confined space and has the characteristics of simple structure, reliable connection method and convenient installation.

[0014] 2. In the design process of the loading lever of the non-collinear connection device of the present invention, the lower limit of the diameter of the force transmission rod, the lower limit of the diameter of the bolt hole, and the minimum distance from the center of the bolt hole to the edge of the U-shaped support plate are analyzed in advance. Then, based on these key parameters, the structural design of the loading lever, the force transmission lug, and the connecting joint is carried out to ensure that a non-collinear connection device for aircraft test loading lever with reasonable structure and excellent performance can be designed to meet the requirements of aircraft structural fatigue test. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the non-collinear connection device of the aircraft test loading lever in Example 1 or 2; Figure 2 This is a schematic diagram of the connecting joint in Example 1 or 2; Figure 3 This is a schematic diagram of the force-transmitting single ear in Example 1 or 2; Among them, 1. Loading lever; 2. Force transmission single ear; 201. Fixing plate; 202. Ear plate; 203. Joint bearing; 3. Connecting joint; 301. Force transmission rod; 302. U-shaped support plate; 303. Bolt; 4. Polyurethane block. Detailed Implementation

[0016] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0017] Example 1 See Figures 1 to 3A non-collinear connection device for loading levers in aircraft testing, comprising: Loading lever 1, wherein the fulcrum of loading lever 1 is hinged to the reaction seat; The force-transmitting single ear 2 includes a fixing plate 201 and an ear piece 202 mounted on the fixing plate 201. The fixing plate 201 is used to fix and connect to the test loading point of the aircraft to be tested. The ear piece 202 of the force-transmitting single ear 2 is provided with a force-transmitting hole. The connecting joint 3 has a U-shaped cross-section and is provided with a force transmission rod 301 that is perpendicular to the cross-section of the U-shaped structure and can be inserted into the force transmission hole; the two U-shaped support plates 302 of the connecting joint 3 are fixed to the resistance point of the loading lever 1 by at least two bolts 303.

[0018] In this embodiment, by improving the joint structure, the connecting joint 3 is designed with a U-shaped cross-section, allowing the force transmission rod 301 to be vertically inserted into the force transmission hole of the force transmission ear 2. During operation, the load can be applied vertically to the loading lever 1 and transmitted to the resistance point of the connecting joint 3 through the loading lever 1. The resistance point uses at least two bolts 303 under shear to transmit the load to the force transmission rod 301 of the connecting joint 3. The shear of the force transmission rod 301 converts the load into a tensile load on the force transmission ear 2, and finally transmits the load to the test loading point of the aircraft. The fulcrum of the lever can be equipped with a conventional joint as needed, transmitting the load from the lever to the conventional joint, and finally to the ground to provide a support reaction force. The non-collinear connection device of this embodiment changes the force transmission rod 301 of the connecting joint 3 from being perpendicular to the lever arm direction to being horizontal to the lever arm direction, changing the force transmission path from the lever connection point to the aircraft test loading point. This enables the application of test force loads in a confined space and features a simple structure, reliable connection method, and convenient installation.

[0019] In this embodiment, a mounting block is provided within the U-shaped structure of the connecting joint 3. The mounting block has mounting holes, and the force transmission rod 301 is detachably fixed within these mounting holes. By utilizing the positional relationship between the mounting holes and the bolts 303, the force transmission rod 301 is raised, ensuring that the loading lever 1 and the force transmission rod 301 are not collinear, thus avoiding interference with the test piece. Furthermore, the U-shaped structure of the connecting joint 3 ensures that the force transmission rod 301 will not shift or loosen during the test, guaranteeing its connection and force transmission reliability.

[0020] In this embodiment, the mounting hole is a threaded hole. The force transmission rod 301 is fixed in the mounting hole by engaging with the threaded hole, achieving a detachable connection between the force transmission rod 301 and the mounting block. When it is necessary to replace or maintain the force transmission rod 301, it can be removed from the mounting hole simply by loosening the force transmission rod 301, greatly facilitating the maintenance and replacement of components of the device and improving testing efficiency. At the same time, this detachable connection method also allows for the replacement of force transmission rods 301 of different specifications or materials according to different testing requirements.

[0021] It should be noted that other methods that enable detachable connection between the mounting hole and the force transmission rod 301 are also applicable to this invention. For example, in some other embodiments, two nuts can be installed on the outer wall of the force transmission rod 301 via external threads. After the force transmission rod 301 passes through the mounting hole, the two nuts are located on opposite sides of the mounting hole, firmly fixing the force transmission rod 301 to the mounting block. This double-nut fixing method not only enhances the stability of the force transmission rod 301, preventing it from loosening or shifting during testing, but also allows for fine-tuning of the elongation of the force transmission rod 301 by adjusting the relative positions of the two nuts, ensuring a reliable fit between the force transmission rod 301 and the force transmission hole of the force transmission lug 2, thereby guaranteeing the reliability of load transmission.

[0022] Furthermore, in this embodiment, a spherical bearing 203 is installed inside the force transmission hole, and the force transmission rod 301 is inserted into the inner ring of the spherical bearing 203. The installation of the spherical bearing 203 releases the degree of freedom in the position of the mating node between the force transmission rod 301 and the force transmission hole, and there is no additional load at the node, ensuring connection safety and testing accuracy.

[0023] Regarding the connection between the force transmission ear 2 and the test loading point, this embodiment employs a polyurethane block 4 placed between the fixing plate 201 of the force transmission ear 2 and the test loading point, and then bonding and fixing the fixing plate 201 and the test loading point to the polyurethane block 4 respectively. The polyurethane block 4 has good elasticity and shock absorption properties, effectively absorbing and dispersing the vibration and impact forces generated during the test, protecting the test loading point and the force transmission ear 2 from damage. Simultaneously, the bonding and fixing method of the polyurethane block 4 also ensures that the connection between the force transmission ear 2 and the test loading point is firm and reliable, and will not detach or loosen due to the test force.

[0024] Based on the same inventive concept, this embodiment also provides a design method for a non-collinear connection device for an aircraft test loading lever, used to obtain the connection device, comprising: Step 1: Based on the input load applied to the loading lever 1, and the positional relationship between the fulcrum, the force application point, and the test loading point on the loading lever 1, analyze and obtain the output load of the loading lever 1 at the test loading point under the input load condition; Step 2: Based on the output load obtained from the analysis, and the material performance parameters of the force transmission rod 301 or the bolt 303, analyze and obtain the lower limit value of the diameter of the force transmission rod 301 and the lower limit value of the diameter of the bolt 303 respectively. In this embodiment, the lower limit of the diameter of the force transmission rod 301 is based on... Analysis yielded, among which This is the lower limit of the diameter of the force transmission rod 301. The tensile strength of the force transmission rod 301 material. The load is the output load of the loading lever 1 at the test loading point under the input load condition. The safety factor for force transmission rod 301 ranges from 2.5 to 4.

[0025] The lower limit value of the diameter of the bolt 303 is based on Analysis yielded, among which This is the lower limit value for the diameter of bolt 303. The number of 303 bolts at the resistance point. The tensile strength of the 303 material used in the bolt. The load is the output load of the loading lever 1 at the test loading point under the input load condition. The safety factor for bolt 303 is 2.5 to 4.

[0026] In this embodiment, the design of the lower limit of the diameter of the force transmission rod 301 and the lower limit of the diameter of the bolt 303 fully considers factors such as the material properties of the force transmission rod 301, the input load, and the safety margin, ensuring that the force transmission rod 301 and the bolt 303 can withstand the corresponding loads without damage during actual operation, thus ensuring the reliability and safety of the connection device.

[0027] Step 3: Based on the output load obtained from the analysis, the thickness of the U-shaped support plate 302 of the connecting joint 3, and the size parameters, performance parameters, and quantity of the bolts 303 installed at the resistance point, analyze and obtain the minimum distance from the center of the bolt hole 303 to the edge of the U-shaped support plate 302 at the corresponding position of the bolt 303. In this embodiment, the minimum distance from the center of the bolt 303 hole at the corresponding position of the U-shaped support plate 302 to the edge of the U-shaped support plate 302 is based on... , This is the minimum distance from the center of the bolt 303 hole at the corresponding position on the U-shaped support plate 302 to the edge of the U-shaped support plate 302. The diameter of bolt 303 is... , The thickness of the U-shaped support plate 302 is defined. By fully considering the tensile force of the output load on the bolt 303, the influence of the thickness of the U-shaped support plate 302 on the bearing capacity of the bolt 303, and the dimensional and performance parameters of the bolt 303 itself, the minimum distance from the center of the bolt 303 hole to the edge of the U-shaped support plate 302 is reasonably determined. This can prevent the bolt 303 hole of the U-shaped support plate 302 from being damaged due to stress concentration during operation, thereby ensuring the connection strength and stability of the connection joint 3.

[0028] Step 4: Based on the lower limit of the diameter of the force transmission rod 301 and the minimum distance from the center of the bolt hole 303 to the edge of the U-shaped support plate 302, complete the structural design of the loading lever 1, the force transmission single ear 2 and the connecting joint 3. The design of the loading lever 1 in this embodiment needs to consider the positional relationship and load-bearing capacity of its fulcrum, force application point, and test loading point to ensure accurate transmission and distribution of load. The design of the force transmission lug 2 must ensure a reliable connection with the test loading point and be able to withstand the tensile load transmitted by the force transmission rod 301. The design of the connecting joint 3 must combine the arrangement of the U-shaped structure, the force transmission rod 301, and the bolt 303 to achieve a stable force transmission function. After analyzing the lower limit of the diameter of the force transmission rod 301, the lower limit of the diameter of the bolt 303 hole, and the minimum distance from the center of the bolt 303 hole to the edge of the U-shaped support plate 302, the structural design of the loading lever 1, the force transmission lug 2, and the connecting joint 3 is carried out based on these key parameters to ensure that a non-collinear connection device for the aircraft test loading lever 1 with reasonable structure and excellent performance can be designed to meet the requirements of aircraft structural fatigue testing.

[0029] Example 2 See Figures 1 to 3 This embodiment takes the design of a non-collinear connection device for a loading lever in a fatigue test of a certain type of aircraft structure as an example to describe in detail the design process of the non-collinear connection device for the aircraft test loading lever 1 of the present invention. The result of this non-collinear connection device is the same as the structure in Embodiment 1, mainly involving five parts: loading lever 1, connecting joint 3, aluminum plate force transmission single ear 2, joint bearing 203, and polyurethane block 4. Among them, loading lever 1 is the connection object, and its structure is as follows: Figure 1 As shown, no design is required; the selection and design process for connecting joint 3, force transmission single ear 2, spherical bearing 203, and polyurethane block 4 is as follows: 2.1 Design of connector 3: 2.1.1 Figure 1 In the middle, the load at point 2 of the single force transmission ear (i.e., the input load) Under the condition that the loading lever 1 is at the test loading point Output load )according to The calculation yielded, where Point of application of force for lever The input load at the point is perpendicular to the loading lever 1. For the fulcrum of lever 1 With the point of application of force The projection distance of the line connecting the load directions perpendicular to the load direction. Point of application of force With test loading point The projection distance of the line connecting the load directions perpendicular to the load direction.

[0030] 2.1.2 Based on the output load Calculate the lower limit of the diameter of the force transmission rod 301 of the connecting joint 3. ,in This is the lower limit of the diameter of the force transmission rod 301. The tensile strength of the force transmission rod 301 material. The load is the output load of the loading lever 1 at the test loading point under the input load condition. The safety factor for force transmission rod 301 ranges from 2.5 to 4.

[0031] 2.1.3 In this embodiment, the force transmission rod 301 adopts a large screw structure. First, a nut is screwed into the large screw at the connecting joint 3, then the large screw is passed through the spherical bearing 203, and finally another nut is screwed into the other side, and the nuts on both sides are tightened. To ensure that the large screw does not experience fatigue fracture at its root, the smooth length of the large screw is set. If the diameter is 20-30mm, then the external thread length of the force transmission rod 301 is... , Test loading point Distance to the center of connector 3. Height between the large screw and the central axis of loading lever 1. The value should be as small as possible while avoiding interference to ensure stability.

[0032] 2.1.4 The resistance point between the connecting joint 3 and the loading lever 1 is connected by small bolts 303. The two bolts 303 can withstand both shear force and bending moment. The diameter of the bolts 303 is limited to a certain extent. Calculations show that, considering connection reliability, an additional bolt (303) can be added to make the connection more secure and less prone to loosening. The U-shaped support plate (302) at the bolt (303) hole is [thickness missing]. The distance is generally around 20mm. The formula for determining the distance from the center of the 303 bolt hole to the edge is as follows: , This is the minimum distance from the center of the bolt 303 hole at the corresponding position on the U-shaped support plate 302 to the edge of the U-shaped support plate 302. The diameter of bolt 303 is... , The thickness of the U-shaped support plate 302 is given. This formula takes into account both strength and economy at the bolt 303, ensuring sufficient strength near the bolt 303 hole while also preventing the distance between the hole center and the edge from being too large, thus avoiding excessive weight of the parts and increased material costs.

[0033] 2.1.5 A "gate" shaped groove is used to reduce the weight of connector 3, with a groove depth of 0.67 mm. .

[0034] 2.1.6 To ensure the overall strength and fatigue resistance of the parts and the threads, the connecting joint 3, the force transmission rod 301 and the bolt 303 are made of 30CrMnSiA material.

[0035] 2.2 Selection of Spherical Plain Bearing 203 Inner diameter of spherical plain bearing 203 , The selected force transmission rod 301 has a diameter; the outer diameter of the spherical bearing 203 needs to be coordinated according to the loading space, and the material of the spherical bearing 203 is 30CrMnSiA.

[0036] 2.3 Design of the single earbud with power transmission The force transmission lug 2 connects to the aircraft reinforcing frame, and its outer contour should fit the frame shape as closely as possible. The height of the mounting hole for the spherical bearing 203 should be chosen to ensure sufficient space for the wrench without interference. The diameter of the force transmission hole is consistent with the outer diameter of the spherical bearing 203, with a thickness of 20mm. For ease of machining, the force transmission lug 2 is made of high-strength aluminum alloy.

[0037] 2.4 Polyurethane Block 4 Design The polyurethane block 4 has the same shape as the fixing piece 201 of the force transmission single ear 2 to ensure a tight fit during bonding. The thickness is 20mm and the hardness is selected as D40~D50.

[0038] After the design of each component in this embodiment is completed, the final installation effect is as follows: Figure 1 As shown, the installation steps are as follows: 1) Press the spherical bearing 203 into the force transmission single ear 2, and use a small hammer to tap the edge of the force transmission hole of the ear piece 202 several times in a point-punching manner to make the edge of the hole slightly deformed until the spherical bearing 203 will not slip off. 2) After wiping the bonding surface of the test loading point of the aircraft test piece with gauze, sand the bonding area with sandpaper and remove the dust after sanding. 3) Roughen both the top and bottom surfaces of polyurethane block 4; 4) Apply FN305 adhesive to the bonding area of ​​the test piece and the lower surface of polyurethane block 4 and then bond them together. After bonding, press for more than 5 minutes. 5) Apply FN305 adhesive to the upper surface of polyurethane block 4 and the lower surface of aluminum block and then bond them together. After bonding, press for more than 5 minutes. 6) First, screw a nut into the large bolt 303 of the connecting joint 3, then insert the bolt 303 into the spherical bearing 203, and finally screw in another nut to the other side and tighten the nuts on both sides. 7) Insert the resistance point of the loading lever 1 into the connector, and install the three small bolts 303 in sequence, tighten the nut, and the assembly is complete.

[0039] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A non-collinear connection device for loading levers in aircraft testing, characterized in that, include: A loading lever, wherein the fulcrum of the loading lever is hinged to the reaction seat; A force-transmitting single ear includes a fixing plate and an ear piece mounted on the fixing plate. The fixing plate is used to fix and connect to the test loading point of the aircraft to be tested. The ear piece of the force-transmitting single ear is provided with a force-transmitting hole. The connecting joint has a U-shaped cross-section and is provided with a force transmission rod that is perpendicular to the cross-section of the U-shaped structure and can be inserted into the force transmission hole; the two U-shaped support plates of the connecting joint are fixed to the resistance point of the loading lever by at least two bolts.

2. The non-collinear connection device according to claim 1, characterized in that, The U-shaped structure of the connector has a mounting block, and the mounting block has a mounting hole. The force transmission rod can be detachably fixed in the mounting hole.

3. The non-collinear connection device according to claim 2, characterized in that, The mounting hole is a threaded hole, and the force transmission rod is fixed in the mounting hole by cooperating with the threaded hole.

4. The non-collinear connection device according to claim 2, characterized in that, Two nuts are installed on the outer wall of the force transmission rod through external thread engagement. The two nuts are used to limit and fix the force transmission rod on the mounting block on both sides of the mounting hole after the force transmission rod passes through the mounting hole.

5. The non-collinear connection device according to claim 1, characterized in that, A spherical bearing is provided inside the force transmission hole, and the force transmission rod is inserted into the inner ring of the spherical bearing.

6. The non-collinear connection device according to claim 1, characterized in that, A polyurethane block is provided between the fixing plate of the force transmission single ear and the test loading point, and the fixing plate and the test loading point are respectively bonded and fixed to the polyurethane block.

7. A design method for a non-collinear connection device for aircraft test loading levers, used to obtain the non-collinear connection device as described in any one of claims 1-6, characterized in that, include: Based on the input load applied to the loading lever, and the positional relationship between the fulcrum, the force application point, and the test loading point on the loading lever, the output load of the loading lever at the test loading point under the input load condition is analyzed and obtained. Based on the output load obtained from the analysis, and the material property parameters of the force transmission rod or bolt, the lower limit value of the diameter of the force transmission rod and the lower limit value of the diameter of the bolt are obtained respectively. Based on the output load obtained from the analysis, the thickness of the U-shaped support plate of the connecting joint, and the size parameters, performance parameters, and quantity of the bolts installed at the resistance point, the minimum distance from the center of the bolt hole to the edge of the U-shaped support plate at the corresponding position of the bolt is obtained. Based on the lower limit of the diameter of the force transmission rod and the minimum distance from the center of the bolt hole to the edge of the U-shaped support plate, the structural design of the loading lever, the force transmission lug, and the connecting joint is completed.

8. The design method for a non-collinear connection device according to claim 7, characterized in that, The lower limit of the diameter of the force transmission rod is based on Analysis yielded, among which This is the lower limit of the diameter of the force transmission rod. The tensile strength of the force transmission rod material. The load is the output load of the loading lever at the test loading point under the input load condition. The safety factor for the force transmission rod ranges from 2.5 to 4.

9. The design method for a non-collinear connection device according to claim 7, characterized in that, The lower limit value of the bolt diameter is based on Analysis yielded, among which This is the lower limit value for the bolt diameter. This represents the number of bolts at the resistance point. The tensile strength of the bolt material. The load is the output load of the loading lever at the test loading point under the input load condition. The safety factor for the bolt is 2.5 to 4; the minimum distance from the center of the bolt hole at the corresponding position on the U-shaped support plate to the edge of the U-shaped support plate is based on... , The minimum distance from the center of the bolt hole at the corresponding position on the U-shaped support plate to the edge of the U-shaped support plate. Where is the diameter of the bolt. , The thickness of the U-shaped support plate.

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