Testing device and method for aircraft hinge

Abstract

The invention provides a testing device and method for an aircraft hinge, and relates to the technical field of aircraft hinge testing, and the device comprises a pedestal, the upper side of the pedestal is provided with a hinge support, and the hinge support is used for connecting one end of a to-be-tested hinge; the rotation driving component is connected with the base, and the output end of the rotation driving component is connected with a driving rocker arm; the aileron is connected with the other end of the detected hinge, and the aileron is connected with a control surface rocker arm; two ends of the connecting rod are rotationally connected with the driving rocker arm and the control surface rocker arm respectively; the loading rocker arm is detachably connected with the aileron; the problems of large test scale, complex test process, single function of test equipment and poor applicability of unmanned aerial vehicle hinge tests in the prior art are solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft hinge testing, and more specifically, relates to a testing device and method for aircraft hinges. Background Art

[0002] A hinge is a structure that enables two parts to rotate relative to each other. For drones, it is mainly used to achieve relative movement between the fixed wing and the rudder. With the rapid development of drones, the performance requirements for hinge structures are gradually increasing, and their static strength, rotation durability and environmental adaptability all need to be verified.

[0003] Traditional hinge tests are usually included in UAV component tests, and the test scale is large, which is not conducive to the rapid verification and design iteration of hinge structures. In other fields such as automobiles, actuators and other equipment are usually used to design dedicated durability test benches, which also have the disadvantages of large test scale, poor versatility of test systems, and difficulty in conducting environmental tests. Summary of the invention

[0004] The purpose of the present invention is to provide a test device and method for aircraft hinges in view of the shortcomings of the prior art, so as to solve the problems in the prior art of testing of drone hinges, such as large test scale, complex test process, single function of test equipment and poor applicability.

[0005] In order to achieve the above object, the present invention provides a test device for aircraft hinges, comprising:

[0006] A base, wherein a hinge support is disposed on the upper side of the base, and the hinge support is used to connect one end of the hinge to be tested;

[0007] A rotation driving component, the rotation driving component is connected to the base, and an output end of the rotation driving component is connected to a driving rocker arm;

[0008] an aileron beam, the aileron beam being connected to the other end of the hinge to be measured, the aileron beam being connected to a rudder rocker arm;

[0009] A connecting rod, both ends of which are rotatably connected to the driving rocker arm and the rudder rocker arm respectively;

[0010] A loading rocker arm is detachably connected to the aileron beam.

[0011] Optionally, the rotation driving component includes a driving motor capable of bidirectional rotation.

[0012] Optionally, a connecting hole is provided at one end of the driving rocker arm, and is connected to the rotating shaft of the rotating driving component through the connecting hole. The driving rocker arm is provided with a plurality of first hinge holes spaced apart along its length direction, and one end of the connecting rod can be hinged to any of the first hinge holes.

[0013] Optionally, a joint bearing is respectively provided at both ends of the connecting rod, and the connecting rod is rotatably connected to the driving rocker arm and the rudder surface rocker arm through the joint bearing.

[0014] Optionally, the spherical bearing is detachably connected to the rod body of the connecting rod via a locking nut.

[0015] Optionally, a bonding portion is provided at one end of the rudder rocker arm, the shape of the bonding portion matches the outer shape of the aileron beam and is bonded to the aileron beam, and a second hinge hole is provided at the other end of the rudder rocker arm, and the other end of the connecting rod is hinged to the second hinge hole.

[0016] Optionally, a clamp structure is provided at one end of the loading rocker arm, a clamp hole is formed inside the clamp structure, the loading rocker arm is connected to the aileron beam through the clamp structure, and the loading rocker arm is provided with a plurality of loading holes spaced apart along its length direction, and the loading holes are used to connect the loading components.

[0017] The present invention also provides a test method for aircraft hinges, using the above-mentioned test device for aircraft hinges, comprising:

[0018] Connect the two ends of the hinge to be tested to the hinge support and the aileron beam respectively;

[0019] Determine whether to connect the loading rocker arm to the aileron beam according to the test requirements;

[0020] Start the rotating drive component, and drive the hinge to open and close through the cooperation of the rotating drive component with the driving rocker arm, connecting rod and rudder rocker arm to carry out a durability test.

[0021] Optionally, it also includes:

[0022] Provide environmental test chambers;

[0023] The test device for aircraft hinges connected with the hinge to be tested is placed in an environmental test chamber to carry out a composite test of environment and durability.

[0024] Optionally, it also includes:

[0025] Keep the rotating drive components stationary;

[0026] Installing a loading rocker arm on the aileron beam and setting a set load on the loading rocker arm;

[0027] Maintain the set time and observe the hinge under test to perform a static test.

[0028] The present invention provides a test device and method for aircraft hinges, and the beneficial effects are as follows: the test device for aircraft hinges is provided with a hinge support for connecting one end of a hinge to be tested on a base, and the other end of the hinge to be tested is connected to an aileron beam, and the hinge to be tested can be driven to open and close by the rotating drive component through a rotating drive component, a driving rocker arm, a connecting rod and a rudder rocker arm, so that a durability test of the hinge to be tested can be performed, and at the same time, the setting of the loading rocker arm can flexibly load the test of the hinge to be tested, so that both a static test of the hinge to be tested and a durability test of the hinge to be tested can be performed. The durability test under the loading conditions of the chain is carried out, and the test device for aircraft hinges has a simple and compact structure, which can be conveniently placed in an environmental test box for environmental testing, and can realize a composite test of environment and durability; the test device for aircraft hinges has a small test scale, strong operability, a real and simple loading method, good economy, and can easily realize the structural design and rapid iteration of the hinge under test. It is suitable for static tests, durability tests, environmental tests, etc. of the hinge under test, and has strong versatility. By replacing local parts, such as hinge supports and rocker arms, etc., it is suitable for tests of different hinges under test.

[0029] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0031] Figure 1 The figure shows an overall structural schematic diagram of a test device for aircraft hinges according to an embodiment of the present invention.

[0032] Figure 2 A schematic structural diagram of a driving rocker arm of a test device for an aircraft hinge according to an embodiment of the present invention is shown.

[0033] Figure 3 A schematic structural diagram of a connecting rod of a test device for an aircraft hinge according to an embodiment of the present invention is shown.

[0034] Figure 4 A schematic structural diagram of a control surface rocker arm of a test device for aircraft hinges according to an embodiment of the present invention is shown.

[0035] Figure 5A schematic structural diagram of an aileron beam of a test device for an aircraft hinge according to an embodiment of the present invention is shown.

[0036] Figure 6 A schematic structural diagram of a loading rocker arm of a test device for aircraft hinges according to an embodiment of the present invention is shown.

[0037] Figure 7 A schematic structural diagram of a test device for aircraft hinges according to an embodiment of the present invention is shown, in which a hinge to be tested is installed on a hinge support.

[0038] Figure 8 A flow chart of a test method for an aircraft hinge according to an embodiment of the present invention is shown.

[0039] Fig. 9 A schematic diagram showing state changes of a test device for aircraft hinges according to an embodiment of the present invention during a durability test is shown.

[0040] Fig.10 A schematic structural diagram of a test device for aircraft hinges according to an embodiment of the present invention during a static test is shown.

[0041] Description of reference numerals:

[0042] 1. Rotating driving component; 2. Driving rocker arm; 3. Connecting rod; 4. Rudder rocker arm; 5. Aileron beam; 6. Loading rocker arm; 7. Hinge support; 8. Base; 9. Hinge to be tested; 2-1. Connecting hole; 2-2. First hinge hole; 3-1. Rod body; 3-2 Joint bearing; 3-3. Locking nut; 4-1. Adhesive part; 4-2. Second hinge hole; 6-1. Loading hole; 6-2. Hoop hole; 6-3. Second pin hole; 6-4. Fastening bolt hole. DETAILED DESCRIPTION

[0043] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0044] like Figure 1 As shown, the present invention provides a test device for aircraft hinges, comprising:

[0045] A base 8, a hinge support 7 is provided on the upper side of the base 8, and the hinge support 7 is used to connect one end of the hinge 9 to be tested;

[0046] A rotating driving component 1, the rotating driving component 1 is connected to a base 8, and an output end of the rotating driving component 1 is connected to a driving rocker arm 2;

[0047] Aileron beam 5, the aileron beam 5 is connected to the other end of the hinge 9 to be tested, and the aileron beam 5 is connected to the rudder rocker arm 4;

[0048] A connecting rod 3, both ends of which are rotatably connected to the driving rocker arm 2 and the rudder rocker arm 4 respectively;

[0049] The loading rocker arm 6 is detachably connected to the aileron beam 5 .

[0050] Specifically, in order to solve the problems in the prior art of the test of the hinge of the unmanned aerial vehicle, the test scale is large, the test process is complicated, the test equipment has a single function and poor applicability; the test device for the hinge of the aircraft provided by the present invention is provided with a hinge support 7 for connecting one end of the hinge 9 to be tested on the base 8, and the other end of the hinge 9 to be tested is connected to the aileron beam 5. By rotating the driving component 1, the driving rocker arm 2, the connecting rod 3 and the rudder rocker arm 4, the driving component 1 can be used to drive the hinge 9 to open and close, and the durability test of the hinge 9 to be tested can be carried out. At the same time, the setting of the loading rocker arm 6 can flexibly load the test of the hinge 9 to be tested, which can not only realize The static test of the hinge 9 under test can also realize the durability test of the hinge 9 under loading conditions, and the test device for aircraft hinges has a simple and compact structure, which can be conveniently placed in an environmental test box for environmental testing, and can realize a composite test of environment and durability; the test device for aircraft hinges has a small test scale, strong operability, a real and simple loading method, good economy, and can easily realize the structural design and rapid iteration of the hinge 9 under test. It is suitable for static tests, durability tests, environmental tests, etc. of the hinge 9 under test, and has strong versatility. By replacing local parts, such as the hinge support 7 and the rocker arm, it is suitable for tests of different hinges 9 under test.

[0051] Optionally, the rotation driving component 1 includes a driving motor capable of bidirectional rotation.

[0052] Specifically, the driving motor can adopt a bidirectional servo motor, which drives the driving rocker arm 2 to swing by rotating its rotating shaft. According to the test requirements, the driving motor can rotate from the 0 position to one side and reset to the 0 position and reciprocate, or it can rotate from the 0 position of the driving motor to both sides and reciprocate.

[0053] Optionally, a connecting hole 2-1 is provided at one end of the driving rocker arm 2, and is connected to the rotating shaft of the rotating driving component 1 through the connecting hole 2-1. The driving rocker arm 2 is provided with a plurality of first hinge holes 2-2 spaced apart along its length direction, and one end of the connecting rod 3 can be hinged to any first hinge hole 2-2.

[0054] Specifically, Figure 2 The driving rocker arm 2 shown can be connected to the rotating shaft of the rotating driving component 1 through the connecting hole 2-1. The provision of multiple first hinge holes 2-2 allows the connection position of the connecting rod 3 on the driving rocker arm 2 to be adjusted according to test needs during use.

[0055] Optionally, a joint bearing 3 - 2 is respectively provided at both ends of the connecting rod 3 , and is rotatably connected to the driving rocker arm 2 and the rudder rocker arm 4 through the joint bearing 3 - 2 .

[0056] Specifically, Figure 3 The connecting rod 3 shown includes a rod body 3-1 and a spherical bearing 3-2 detachably connected to both ends of the rod body 3-1, and is used to connect the driving rocker arm 2 and the rudder surface rocker arm 4, and transmit the load output by the rotating driving component 1 to the aileron beam 5, that is, to the rudder surface.

[0057] In this embodiment, the rod body 3 - 1 is made of metal material.

[0058] Optionally, the spherical bearing 3 - 2 is detachably connected to the rod body 3 - 1 of the connecting rod 3 via a locking nut 3 - 3 .

[0059] Specifically, the spherical bearing 3-2 can be directly purchased from outside and installed on the end of the rod body 3-1 through its locking nut 3-3.

[0060] Optionally, one end of the rudder rocker arm 4 is provided with a bonding portion 4-1, the shape of the bonding portion 4-1 matches the outer shape of the aileron beam 5, and is bonded to the aileron beam 5, and the other end of the rudder rocker arm 4 is provided with a second hinge hole 4-2, and the other end of the connecting rod 3 is hinged to the second hinge hole 4-2.

[0061] Specifically, Figure 4 As shown, the rudder rocker arm 4 is made of metal material, and its bonding portion 4 - 1 is bonded to the aileron beam 5 . Its structure can be set according to the shape of the aileron beam 5 , and the second hinge hole 4 - 2 is rotatably connected to the connecting rod 3 .

[0062] In this embodiment, the bonding portion 4-1 is bonded to the middle of the auxiliary wing beam 5, and the auxiliary wing beam 5 is as follows: Figure 5 The cylindrical aileron beam 5 shown is made of lightweight composite materials and is used to simulate the support structure of the rudder surface of a UAV. The use of lightweight composite materials can avoid excessive test loads caused by gravity, which affects the accuracy of the test. A first pin hole is provided on it.

[0063] Optionally, a clamp structure is provided at one end of the loading rocker arm 6, and a clamp hole 6-2 is formed inside the clamp structure. The loading rocker arm 6 is connected to the aileron beam 5 through the clamp structure. The loading rocker arm 6 is provided with a plurality of loading holes 6-1 spaced apart along its length direction, and the loading holes 6-1 are used to connect the loading components.

[0064] Specifically, Figure 6 As shown, the loading rocker arm 6 can be connected to the aileron beam 5 through a clamp structure, the clamp structure is adapted to the structure of the aileron beam 5, and the loading hole 6-1 is used to connect loading components such as weights or sandbags. The setting of multiple loading holes 6-1 can flexibly change the loading lever arm.

[0065] In this embodiment, two loading rocker arms 6 are provided, and the two loading rocker arms 6 are respectively installed at both ends of the aileron beam 5. A second pin hole 6-3 is provided on the side wall of the clamp structure. The second pin hole 6-3 cooperates with the first pin hole and is used to penetrate the pin to prevent the loading rocker arm 6 and the aileron beam 5 from relative rotation. The clamp structure is provided with a pair of connecting ears, and the connecting ears are provided with fastening bolt holes 6-4. The clamp structure can be clamped by the fastening bolt assembly to clamp the aileron beam 5.

[0066] Furthermore, the loading rocker arm 6 and the aileron beam 5 can be quickly disassembled and assembled, and can be removed when the hinge 9 under test is subjected to environmental testing.

[0067] In this embodiment, if Figure 7 As shown, the hinge support 7 is used to connect the hinge 9 to be tested and the base 8 to fix the hinge 9 to be tested. The hinge support 7 can be designed according to the structural form and connection method of the hinge to achieve flexible replacement. The hinge support 7 is connected and fastened to the hinge 9 to be tested and the base 8 by bolts; the hinge support 7 and the base 8 are made of metal materials and need to have a certain weight. The base 8 is used to fix one end of the hinge 9 to be tested through the hinge support 7 and to fix the rotating drive component 1.

[0068] In summary, the test device for aircraft hinges provided by the present invention is designed as follows:

[0069] 1) Design the hinge support 7 and the aileron beam 5 according to the structural forms at both ends of the hinge 9 to be tested. It should be noted that the hinge support 7 must have sufficient strength to fix the hinge. It is recommended to use metal materials such as high-strength steel. The aileron beam 5 must have sufficient strength to ensure the transmission of the load, but it should not be too heavy to cause additional test loads. It is recommended to use carbon fiber composite materials;

[0070] 2) Design the relevant structural dimensions of the driving rocker arm 2, the connecting rod 3 and the rudder rocker arm 4 according to the structure of the output shaft of the bidirectional servo motor and its relative position relationship with the hinge 9 to be tested. It is recommended to use metal materials;

[0071] 3) Design the structural features of the loading rocker arm 6 according to the structure of the aileron beam 5, and design the hole distribution of the loading hole 6-1 according to the static load of the hinge 9 to be tested.

[0072] 4) The base 8 must be able to accommodate the installation of the rotating drive component 1 and the hinge support 7, and have sufficient strength to support and fix the entire test device. It is recommended to use metal materials such as high-strength steel.

[0073] like Figure 8 As shown, the present invention also provides a test method for aircraft hinges, using the above-mentioned test device for aircraft hinges, comprising:

[0074] Connect the two ends of the hinge 9 to be tested to the hinge support 7 and the aileron beam 5 respectively;

[0075] Determine whether to connect the loading rocker arm 6 to the aileron beam 5 according to the test requirements;

[0076] The rotating driving component 1 is started, and the hinge is driven to open and close through the cooperation of the rotating driving component 1 with the driving rocker arm 2, the connecting rod 3 and the rudder rocker arm 4, and a durability test is carried out.

[0077] Specifically, when performing a durability test on the hinge 9 to be tested, first assemble the above-mentioned test device for aircraft hinges to ensure that each connection position is tight and not loose; if only the durability test of the hinge function is to be performed, the loading rocker arm 6 may not be installed. If a load durability test is to be performed, the loading rocker arm 6 is installed and a weight is fixed at the designed position to achieve the application of the load weight; the bidirectional servo motor is powered on, and the rotational reciprocating motion of the hinge 9 to be tested is driven by the bidirectional servo motor. During the rotation process, the state changes of the hinge 9 to be tested and the aileron beam 5 are as follows: Fig. 9 As shown, the durability test under the set load can be realized, and attention should be paid to the influence of the transmission ratio on the movement angle; if the hinge 9 under test is not damaged during the overall test process, it can be determined that the hinge 9 under test meets the durability test requirements.

[0078] In this embodiment, it also includes:

[0079] Provide environmental test chambers;

[0080] The test device for aircraft hinges connected with the hinge 9 to be tested is placed in an environmental test chamber to perform a composite test of environment and durability.

[0081] Specifically, the test device for the aircraft hinge connected to the hinge 9 to be tested can also be placed in an environmental test chamber. The environmental test chamber applies environmental load conditions such as temperature, humidity, and air pressure according to the environmental test requirements. After the test is completed, the test system can be restored, and inspections and subsequent static or durability tests can be carried out according to the test requirements. At the same time, durability tests can still be carried out at the same time when conducting environmental tests, so as to achieve environmental and durability composite tests.

[0082] In another embodiment, the environmental test can also be carried out separately. If only the hinge 9 to be tested is subjected to the environmental test, the connecting rod 3 and the rudder rocker arm 4 can be disassembled, the hinge support 7 and the base 8 can be disassembled, the aileron beam 5 and the loading rocker arm 6 can be disassembled, and only the hinge support 7, the hinge 9 to be tested, the aileron beam 5 and the rudder rocker arm 4 are placed in the test environmental test box for environmental testing.

[0083] Optionally, it also includes:

[0084] Keep the rotating drive component 1 stationary;

[0085] A loading rocker arm 6 is installed on the aileron beam 5, and a set load is set on the loading rocker arm 6;

[0086] Maintain the set time and observe the hinge 9 under test to perform a static test.

[0087] Specifically, Fig.10 As shown, when the hinge 9 under test is subjected to a static test, the bidirectional servo motor is energized and kept at position 0. According to the test load, a weight or sandbag is hung at a loading hole 6-1 of the loading rocker arm 6 for loading. Gradual loading can be achieved by replacing the loading hole 6-1 or the weight of the weight or sandbag. The loading is maintained for 1 minute, and the test phenomenon is observed. If there is no abnormal sound or damage during the entire loading process, it can be determined that the hinge 9 under test meets the static strength requirements.

[0088] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A test device for aircraft hinges, characterized in that: include: A base, wherein a hinge support is disposed on the upper side of the base, and the hinge support is used to connect one end of the hinge to be tested; A rotation driving component, the rotation driving component is connected to the base, and an output end of the rotation driving component is connected to a driving rocker arm; an aileron beam, the aileron beam being connected to the other end of the hinge to be measured, the aileron beam being connected to a rudder rocker arm; A connecting rod, both ends of which are rotatably connected to the driving rocker arm and the rudder rocker arm respectively; A loading rocker arm is detachably connected to the aileron beam.

2. The test device for aircraft hinges according to claim 1, characterized in that: The rotation driving component includes a driving motor capable of bidirectional rotation.

3. The test device for aircraft hinges according to claim 1, characterized in that: One end of the driving rocker arm is provided with a connecting hole, and is connected to the rotating shaft of the rotating driving component through the connecting hole. The driving rocker arm is provided with a plurality of first hinge holes spaced apart along its length direction, and one end of the connecting rod can be hinged to any of the first hinge holes.

4. The test device for aircraft hinges according to claim 1, characterized in that: A joint bearing is respectively arranged at both ends of the connecting rod, and the connecting rod is rotatably connected with the driving rocker arm and the rudder surface rocker arm through the joint bearing.

5. The test device for aircraft hinges according to claim 4, characterized in that: The spherical bearing is detachably connected to the rod body of the connecting rod via a locking nut.

6. The test device for aircraft hinges according to claim 1, characterized in that: One end of the rudder rocker arm is provided with a bonding portion, the shape of the bonding portion matches the outer shape of the aileron beam and is bonded to the aileron beam, and the other end of the rudder rocker arm is provided with a second hinge hole, and the other end of the connecting rod is hinged to the second hinge hole.

7. The test device for aircraft hinges according to claim 1, characterized in that: A clamping hoop structure is provided at one end of the loading rocker arm, a clamping hoop hole is formed inside the clamping hoop structure, the loading rocker arm is connected to the aileron beam through the clamping hoop structure, and the loading rocker arm is provided with a plurality of loading holes spaced apart along its length direction, and the loading holes are used to connect the loading components.

8. A test method for aircraft hinges, using the test device for aircraft hinges according to any one of claims 1 to 7, characterized in that: include: Connect the two ends of the hinge to be tested to the hinge support and the aileron beam respectively; Determine whether to connect the loading rocker arm to the aileron beam according to the test requirements; Start the rotating drive component, and drive the hinge to open and close through the cooperation of the rotating drive component with the driving rocker arm, connecting rod and rudder rocker arm to carry out a durability test.

9. The test method for aircraft hinges according to claim 8, characterized in that: Also includes: Provide environmental test chambers; The test device for aircraft hinges connected with the hinge to be tested is placed in an environmental test chamber to carry out a composite test of environment and durability.

10. The test method for aircraft hinges according to claim 8, characterized in that: Also includes: Keep the rotating drive components stationary; Installing a loading rocker arm on the aileron beam and setting a set load on the loading rocker arm; Maintain the set time and observe the hinge under test to perform a static test.

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