Power source test mechanism of folding wing

Abstract

The embodiment of the utility model provides a power source test mechanism of a folding wing. The base is mounted on a foundation; the fixed support is installed at the end, away from the foundation, of the base. The bearing folding platform is rotationally connected to the side wall of the base, a plurality of first connecting holes are formed in the length direction of the bearing folding platform, and the bearing folding platform is used for bearing a balance weight load; the first connecting piece is detachably connected to the bearing folding platform through the first connecting hole; a power source is arranged between the end, away from the base, of the fixed support and the first connecting piece. The locking assembly is arranged between the side wall of the base and the bearing folding platform and is configured to fix the bearing folding platform to the side wall of the base when the bearing folding platform is in a horizontal state. Therefore, the performance of the power source can be evaluated according to different balance weight loads, smooth unfolding and folding of the wings of the unmanned aerial vehicle are guaranteed, the operation process is simplified through flexible adjustment of the first connecting piece, and the flexibility and efficiency of the test mechanism are improved.

Description

Technical Field

[0001] The present application relates to the technical field of power source testing mechanisms, and in particular to a power source testing mechanism for folding wings. Background Art

[0002] A foldable drone is a drone with a foldable design, whose wings or arms can be folded up to reduce the overall size and weight, and improve portability and convenience of transportation.

[0003] However, in the existing technology, the folding and unfolding of the wings is an important factor affecting flight safety. In order to ensure the normal function of the wings of foldable drones in different operating modes, it is necessary to evaluate whether the wing folding and unfolding power source can ensure the stable control of the wings in different operating modes, and evaluate the tensile force of the power source in different operating modes to ensure the smooth unfolding and folding of the drone wings and meet the normal operation of the wings under different load conditions. This test often requires real machine testing. Although this method is direct and effective, its testing cost is correspondingly high. Utility Model Content

[0004] The embodiment of the present application proposes a power source testing mechanism for folding wings, which aims to solve the problem in the prior art of using a real machine to detect whether the wing deployment and folding functions of a folding UAV operate normally under different counterweight loads, and to evaluate the tensile force of the power source under these conditions, thereby effectively reducing the testing cost.

[0005] An embodiment of the present application provides a power source test mechanism for a folding wing, comprising a base, a load-bearing folding platform, a fixed support, a first connecting member and a locking assembly; the base is installed on a foundation; the fixed support is installed at one end of the base away from the foundation; the load-bearing folding platform is rotatably connected to the side wall of the base, and a plurality of first connecting holes are provided along its length direction, and the load-bearing folding platform is used to bear a counterweight load; the first connecting member is detachably connected to the load-bearing folding platform through the first connecting hole; a power source is provided between one end of the fixed support away from the base and the first connecting member; the locking assembly is provided between the side wall of the base and the load-bearing folding platform, and is configured to fix the load-bearing folding platform to the side wall of the base when the load-bearing folding platform is in a horizontal state.

[0006] In a possible implementation, the locking assembly includes a plurality of fixing members, a plurality of first latches and a plurality of first support members; the plurality of fixing members are all arranged on the side walls of the base, and are spaced apart along the width direction of the base, and are all provided with a second connecting hole; the plurality of first support members are all arranged on a side of the load-bearing folding platform close to the base, and are arranged toward a side of the foundation, and are all provided with a third connecting hole corresponding to the second connecting hole; the plurality of first latches are configured to be inserted into the corresponding second connecting holes and the third connecting holes to fix the corresponding fixing members and the first support members.

[0007] In a possible implementation, the locking assembly further includes a plurality of driving members; the plurality of driving members are respectively disposed in the corresponding first supporting members, and are used to drive the corresponding first latches to insert into or disengage from the corresponding third connecting holes.

[0008] In a possible implementation, the locking assembly also includes a plurality of second support members; the two ends of the plurality of second support members are respectively connected to the side of the corresponding first support member away from the load-bearing folding platform and the load-bearing folding platform, and the plurality of second support members form a triangular structure with the corresponding first support member and the load-bearing folding platform.

[0009] In a possible implementation, the power source test mechanism of the folding wing further includes a reinforcement member; the reinforcement member is disposed in the middle of the bottom of the load-bearing folding platform.

[0010] In a possible implementation, the fixed support includes a second pin, two second connecting members and two first connecting ears; the two second connecting members are installed at the end of the base away from the foundation, and are spaced apart along the width direction of the base; the two first connecting ears are respectively arranged on the side of the corresponding second connecting member away from the base, and are arranged on the inner side of the corresponding second connecting member, and are both provided with a ninth connecting hole; the end of the power source away from the first connecting member is arranged between the two first connecting ears, and is provided with a fourth connecting hole corresponding to the ninth connecting hole; one end of the second pin passes through one of the ninth connecting holes, the fourth connecting hole and the other ninth connecting hole, and the second pin is configured to connect the power source and the two first connecting ears.

[0011] In a possible implementation manner, the side walls of the two second connecting members are each provided with a plurality of weight-reducing holes.

[0012] In a possible implementation, the power source test mechanism of the folding wing further includes a plurality of rotating shafts, a plurality of second connecting ears and a plurality of third connecting ears; the plurality of second connecting ears are arranged on the side wall of the base, and are arranged along the width direction of the base, and are a first opening structure facing the side of the bearing folding platform; both side walls of the plurality of second connecting ears are symmetrically provided with fourth connecting holes; the plurality of third connecting ears are arranged on the side wall of the bearing folding platform, and are arranged at intervals along the width direction of the bearing folding platform, and are inserted into the first opening structure;

[0013] Each of the plurality of third connecting ears is provided with a fifth connecting hole corresponding to the fourth connecting hole;

[0014] One end of each of the rotating shafts passes through the corresponding fourth connecting hole and the corresponding fifth connecting hole, and is configured to connect the corresponding second connecting ear piece and the corresponding third connecting ear piece.

[0015] In a possible implementation, the first connecting member includes a third pin and a fourth connecting ear; the fourth connecting ear is detachably connected to the load-bearing folding platform through the first connecting hole, and its side away from the load-bearing folding platform is a second opening structure, and its two side walls are symmetrically provided with sixth connecting holes; the power source is provided with a seventh connecting hole corresponding to the two sixth connecting holes; one end of the third pin passes through one of the sixth connecting holes, the seventh connecting hole and the other sixth connecting hole in sequence, and is configured to connect the power source and the two fourth connecting ears.

[0016] In a possible implementation, the power source test mechanism of the folding wing also includes a plurality of fasteners; a plurality of eighth connection holes are provided at the bottom of the base; the plurality of eighth connection holes are arranged at intervals along the width direction of the base; and one end of the plurality of fasteners passes through the corresponding eighth connection holes and is connected to the base.

[0017] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects:

[0018] The power source test mechanism of the folding wing provided in the embodiment of the present application includes a base, a bearing folding platform, a fixed support, a first connecting member and a locking assembly. The bearing folding platform in the present application simulates the function of the wing. When the bearing folding platform is in a horizontal position, the bearing folding platform is connected to the side wall of the base by a locking assembly to ensure the stability of the test. At this time, the present application can flexibly adjust the position of the first connecting member on the bearing folding platform according to the actual specifications of the power source, and then connect the two ends of the power source to the fixed support and the first connecting member respectively, and apply a suitable counterweight load to simulate the actual flight conditions. When the bearing folding platform rotates counterclockwise, the process of wing folding is simulated, and the tension value of the power source in different states can be accurately measured at this time. Therefore, the present application can evaluate the performance of the power source according to different counterweight loads to ensure the smooth unfolding and folding of the drone wing, and through the flexible adjustment of the first connecting member, the operation process is simplified, and the flexibility and efficiency of the test mechanism are improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following is a brief introduction to the drawings required for use in the description of the embodiments of the present application. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0020] Figure 1 A schematic diagram of the structure of a power source test mechanism for a folding wing provided in an embodiment of the present application;

[0021] Figure 2 A schematic diagram of the structure of the load-bearing folding platform provided in an embodiment of the present application;

[0022] Figure 3 A schematic diagram of the structure of the base provided in an embodiment of the present application.

[0023] Icons: 1-base; 101-eighth connecting hole; 2-bearing folding platform; 21-first connecting hole; 3-fixed support; 31-second connecting member; 32-first connecting ear; 321-ninth connecting hole; 33-weight reduction hole; 4-first connecting member; 41-fourth connecting ear; 42-sixth connecting hole; 5-locking assembly; 51-fixing member; 52-first latch; 53-first support member; 531-third connecting hole; 54-second support member; 6-counterweight load; 7-reinforcement member; 8-rotating shaft; 9-second connecting ear; 10-third connecting ear; 102-fifth connecting hole; 11-power source; 12-fastener. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0025] In the description of the embodiments of the present application, it should be noted that the orientation or positional relationship indicated by the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the embodiments of the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. The terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance. In addition, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0026] The present application embodiment provides a folding wing power source test mechanism, such as Figures 1 to 3 As shown. The power source test mechanism of the folding wing includes a base 1, a load-bearing folding platform 2, a fixed support 3, a first connecting member 4 and a locking assembly 5. The base 1 is installed on a foundation. The fixed support 3 is installed at one end of the base 1 away from the foundation. The load-bearing folding platform 2 is rotatably connected to the side wall of the base 1, and a plurality of first connecting holes 21 are provided along its length direction, and the load-bearing folding platform 2 is used to carry a counterweight load 6. The first connecting member 4 is detachably connected to the load-bearing folding platform 2 through the first connecting hole 21. A power source 11 is provided between one end of the fixed support 3 away from the base 1 and the first connecting member 4. The locking assembly 5 is provided between the side wall of the base 1 and the load-bearing folding platform 2, and is configured to fix the load-bearing folding platform 2 to the side wall of the base 1 when the load-bearing folding platform 2 is in a horizontal state.

[0027] It should be noted that the load-bearing folding platform 2 in the present application simulates the function of the wing. When the load-bearing folding platform 2 is in a horizontal position, the load-bearing folding platform 2 is connected to the side wall of the base 1 by a locking assembly 5 to ensure the stability of the test. At this time, the present application can flexibly adjust the position of the first connecting member 4 on the load-bearing folding platform 2 according to the actual specifications of the power source 11, and then connect the two ends of the power source 11 to the fixed support 3 and the first connecting member 4 respectively, and apply a suitable counterweight load 6 to simulate actual flight conditions. When the load-bearing folding platform 2 rotates counterclockwise, the process of wing folding is simulated, and the tension value of the power source 11 in different states can be accurately measured at this time. Therefore, the present application can evaluate the performance of the power source 11 according to different counterweight loads 6 to ensure the smooth unfolding and folding of the drone wings, and through the flexible adjustment of the first connecting member 4, the operation process is simplified, and the flexibility and efficiency of the test mechanism are improved.

[0028] In the embodiment of the present application, the locking assembly 5 includes a plurality of fixing members 51, a plurality of first latches 52 and a plurality of first support members 53. The plurality of fixing members 51 are all arranged on the side wall of the base 1, and are arranged at intervals along the width direction of the base 1, and are all provided with a second connection hole. The plurality of first support members 53 are all arranged on a side of the folding platform 2 close to the base 1, and are arranged toward a side of the foundation, and are all provided with a third connection hole 531 corresponding to the second connection hole. The plurality of first latches 52 are configured to be inserted into the corresponding second connection holes and third connection holes 531 to fix the corresponding fixing members 51 and first support members 53.

[0029] It should be noted that the present application ensures that the load-bearing folding platform 2 can be uniformly stressed when in a horizontal state by arranging a plurality of fixing members 51 at intervals along the width direction on the side wall of the base 1, and arranging a plurality of first supporting members 53 at corresponding positions on one side of the load-bearing folding platform 2 close to the base 1, thereby significantly enhancing its stability. When the load-bearing folding platform 2 needs to be fixed in a horizontal state, the operator only needs to insert the first latch 52 into the corresponding second connecting hole and the third connecting hole 531 to achieve a quick and stable locking. On the contrary, when it is necessary to test the tensile value of the power source 11, the operator can easily pull out the first latch 52 to unlock it, so that the load-bearing folding platform 2 can rotate freely. Therefore, the present application not only improves the efficiency and accuracy of the test, but also simplifies the operation process, making the entire test process smoother and more controllable.

[0030] In the embodiment of the present application, the locking assembly 5 further includes a plurality of driving members, which are respectively disposed in the corresponding first supporting members 53 and are used to drive the corresponding first latch 52 to be inserted into or separated from the corresponding third connecting hole 531 .

[0031] It should be noted that the driving member of the present application can accurately control the extension and retraction distance of the first latch 52 to ensure that the first latch 52 can be accurately inserted into or disengaged from the corresponding third connection hole 531. Therefore, the present application not only improves the convenience and efficiency of operation, but also reduces the errors and risks caused by human operation, provides a strong guarantee for the smooth progress of the test, and at the same time, can also play a protective role in the process of installing the counterweight load 6.

[0032] In the embodiment of the present application, the locking assembly 5 further includes a plurality of second support members 54. Both ends of the plurality of second support members 54 are respectively connected to the side of the corresponding first support member 53 away from the carrying folding platform 2 and the carrying folding platform 2, and the plurality of second support members 54, the corresponding first support member 53, and the carrying folding platform 2 form a triangular structure.

[0033] It should be noted that the present application can significantly enhance the structural stability of the load-bearing folding platform 2 in a horizontal state. Even under the action of external forces, this triangular structure can effectively resist deformation and displacement, ensuring the smooth progress of the test process.

[0034] In the embodiment of the present application, the power source test mechanism of the folding wing further includes a reinforcement member 7. The reinforcement member 7 is arranged in the middle of the bottom of the folding platform 2.

[0035] It should be noted that the reinforcement member 7 of the present application can enhance the structural strength of the bottom of the load-bearing folding platform 2, so that it can withstand a larger load.

[0036] In the embodiment of the present application, the fixed support 3 includes a second latch, two second connecting members 31 and two first connecting ears 32. The two second connecting members 31 are installed at one end of the base 1 away from the foundation, and are spaced apart along the width direction of the base 1. The two first connecting ears 32 are respectively arranged on the side of the corresponding second connecting member 31 away from the base 1, and are arranged on the inner side of the corresponding second connecting member 31, and are both provided with a ninth connecting hole 321. The end of the power source 11 away from the first connecting member 4 is arranged between the two first connecting ears 32, and is provided with a fourth connecting hole corresponding to the ninth connecting hole 321. One end of the second latch passes through one of the ninth connecting holes 321, the fourth connecting hole and the other ninth connecting hole 321, and the second latch is configured to connect the power source 11 and the two first connecting ears 32.

[0037] It should be noted that the present application realizes the rapid installation and stable connection between the power source 11 and the two first connection ears 32. During installation, the power source 11 is placed between the two first connection ears 32, and then the second latch passes through the ninth connection hole 321 on one of the first connection ears 32, the fourth connection hole on the power source 11, and the ninth connection hole 321 on the other first connection ear 32, thereby completing the fixation. Similarly, the disassembly process is also extremely simple, and the power source 11 can be quickly separated from the fixed support 3 by simply pulling out the second latch.

[0038] The two first connecting ears 32 in the present application are fixedly connected on the sides facing each other. This design not only ensures the stability of the connection, but also effectively saves space, making the entire test mechanism more compact and efficient.

[0039] In the embodiment of the present application, the side walls of the two second connecting members 31 are each provided with a plurality of weight-reducing holes 33 .

[0040] In the embodiment of the present application, the power source test mechanism of the folding wing also includes a plurality of rotating shafts 8, a plurality of second connecting ears 9 and a plurality of third connecting ears 10. The plurality of second connecting ears 9 are arranged on the side wall of the base 1 and arranged along the width direction of the base 1, and the first opening structure is formed on the side facing the folding platform 2. The fourth connecting holes are symmetrically arranged on both side walls of the plurality of second connecting ears 9. The plurality of third connecting ears 10 are arranged on the side wall of the folding platform 2 and are arranged at intervals along the width direction of the folding platform 2 and inserted into the first opening structure. The plurality of third connecting ears 10 are all provided with a fifth connecting hole 102 corresponding to the fourth connecting hole. One end of the plurality of rotating shafts 8 passes through the corresponding fourth connecting hole and the fifth connecting hole 102, respectively, and is configured to connect the corresponding second connecting ears 9 and the third connecting ears 10.

[0041] It should be noted that the rotating shaft 8, the second connecting ear piece 9 and the third connecting ear piece 10 of the present application are usually made of wear-resistant and corrosion-resistant materials.

[0042] The second connecting lug 9 and the third connecting lug 10 are respectively arranged on the side walls of the base 1 and the folding platform 2, and are connected by the rotating shaft 8. This design allows the folding platform 2 to be flexibly folded and unfolded relative to the base 1, thereby simulating the actual working state of the folding wing. The rotating shaft 8, as a connection point, provides the necessary rotational freedom, making the folding process smoother.

[0043] In the embodiment of the present application, the first connecting member 4 includes a third latch and a fourth connecting ear piece 41. The fourth connecting ear piece 41 is detachably connected to the load-bearing folding platform 2 through the first connecting hole 21, and the side away from the load-bearing folding platform 2 is a second opening structure, and the two side walls thereof are symmetrically provided with sixth connecting holes 42. The power source 11 is provided with a seventh connecting hole corresponding to the two sixth connecting holes 42. One end of the third latch passes through one of the sixth connecting holes 42, the seventh connecting hole and the other sixth connecting hole 42 in sequence, and is configured to connect the power source 11 and the two fourth connecting ear pieces 41.

[0044] It should be noted that, through the design of the third latch, the power source 11 can be quickly installed between the two fourth connecting ears 41 and achieve a stable connection by passing through the sixth connecting hole 42 and the seventh connecting hole.

[0045] In the embodiment of the present application, the power source test mechanism of the folding wing further includes a plurality of fasteners 12. A plurality of eighth connection holes 101 are provided at the bottom of the base 1. The plurality of eighth connection holes 101 are arranged at intervals along the width direction of the base 1. One end of the plurality of fasteners 12 passes through the corresponding eighth connection hole 101 and is connected to the foundation.

[0046] It should be noted that the plurality of fasteners 12 are tightly connected to the foundation after passing through the eighth connection hole 101 at the bottom of the base 1. The embodiment of the present application not only ensures the stability of the test mechanism during the test, but also enhances its ability to resist external interference and vibration.

[0047] The various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referenced to each other. Each embodiment focuses on the differences from other embodiments.

[0048] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit the present application. Although the present application has been described in detail with reference to the aforementioned embodiments, a person of ordinary skill in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some or all of the technical features thereof may be replaced by equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present application.

Claims

1. A power source test mechanism for folding wings, characterized in that: It comprises a base (1), a load-bearing folding platform (2), a fixed support (3), a first connecting member (4) and a locking assembly (5); The base (1) is installed on a foundation; The fixed support (3) is installed on an end of the base (1) away from the foundation; The load-bearing folding platform (2) is rotatably connected to the side wall of the base (1), and is provided with a plurality of first connection holes (21) along its length direction. The load-bearing folding platform (2) is used to bear a counterweight load (6); The first connecting member (4) is detachably connected to the load-bearing folding platform (2) via the first connecting hole (21); A power source (11) is provided between an end of the fixed support (3) away from the base (1) and the first connecting member (4); The locking assembly (5) is arranged between the side wall of the base (1) and the carrying folding platform (2), and is configured to fix the carrying folding platform (2) to the side wall of the base (1) when the carrying folding platform (2) is in a horizontal state.

2. The power source test mechanism for folding wings according to claim 1, characterized in that: The locking assembly (5) comprises a plurality of fixing members (51), a plurality of first latches (52) and a plurality of first supporting members (53); The plurality of fixing members (51) are all arranged on the side wall of the base (1), and are arranged at intervals along the width direction of the base (1), and are all provided with a second connection hole; A plurality of the first support members (53) are all arranged on a side of the load-bearing folding platform (2) close to the base (1) and facing a side of the foundation, and are all provided with a third connection hole (531) corresponding to the second connection hole; The plurality of first latches (52) are configured to be inserted into the corresponding second connection holes and the third connection holes (531) to fix the corresponding fixing members (51) and the first supporting members (53).

3. The power source testing mechanism for folding wings according to claim 2, characterized in that: The locking assembly (5) further comprises a plurality of driving members; The plurality of driving members are respectively arranged in the corresponding first supporting members (53) and are used to drive the corresponding first latch pins (52) to be inserted into or separated from the corresponding third connecting holes (531).

4. The power source testing mechanism for folding wings according to claim 2, characterized in that: The locking assembly (5) further comprises a plurality of second support members (54); The two ends of the plurality of second support members (54) are respectively connected to a side of the corresponding first support member (53) away from the carrying folding platform (2) and the carrying folding platform (2), and the plurality of second support members (54) form a triangular structure with the corresponding first support member (53) and the carrying folding platform (2).

5. The power source testing mechanism for folding wings according to claim 1, characterized in that: Also includes a reinforcement member (7); The reinforcement member (7) is arranged at the middle part of the bottom of the load-bearing folding platform (2).

6. The power source testing mechanism for folding wings according to claim 1, characterized in that: The fixed support (3) comprises a second latch, two second connecting members (31) and two first connecting ears (32); Two second connecting members (31) are mounted on an end of the base (1) away from the foundation, and are spaced apart along the width direction of the base (1); The two first connecting ears (32) are respectively arranged on a side of the corresponding second connecting member (31) away from the base (1), and are arranged on the inner side of the corresponding second connecting member (31), and are both provided with a ninth connecting hole (321); One end of the power source (11) away from the first connecting member (4) is arranged between the two first connecting lugs (32), and is provided with a fourth connecting hole corresponding to the ninth connecting hole (321); One end of the second latch passes through one of the ninth connection holes (321), the fourth connection hole and another of the ninth connection holes (321), and the second latch is configured to connect the power source (11) and the two first connection ear pieces (32).

7. The power source testing mechanism for folding wings according to claim 6, characterized in that: The side walls of the two second connecting members (31) are each provided with a plurality of weight-reducing holes (33).

8. The power source testing mechanism for folding wings according to claim 1, characterized in that: It also includes a plurality of rotating shafts (8), a plurality of second connecting ear pieces (9) and a plurality of third connecting ear pieces (10); A plurality of the second connecting ear pieces (9) are arranged on the side wall of the base (1) and are arranged along the width direction of the base (1), and the side facing the folding bearing platform (2) is a first opening structure; Both side walls of the plurality of second connecting ear pieces (9) are symmetrically provided with fourth connecting holes; A plurality of the third connecting ear pieces (10) are arranged on the side wall of the load-bearing folding platform (2), are arranged at intervals along the width direction of the load-bearing folding platform (2), and are inserted into the first opening structure; The plurality of third connecting ear pieces (10) are each provided with a fifth connecting hole (102) corresponding to the fourth connecting hole; One end of each of the plurality of rotating shafts (8) passes through the corresponding fourth connecting hole and the fifth connecting hole (102), respectively, and is configured to connect the corresponding second connecting ear piece (9) and the third connecting ear piece (10).

9. The power source testing mechanism for folding wings according to claim 1, characterized in that: The first connecting member (4) comprises a third latch and a fourth connecting ear piece (41); The fourth connecting ear piece (41) is detachably connected to the load-bearing folding platform (2) through the first connecting hole (21), and the side thereof away from the load-bearing folding platform (2) is a second opening structure, and the two side walls thereof are symmetrically provided with sixth connecting holes (42); The power source (11) is provided with a seventh connection hole corresponding to the two sixth connection holes (42); One end of the third plug passes through one of the sixth connection holes (42), the seventh connection hole and another of the sixth connection holes (42) in sequence, and is configured to connect the power source (11) and the two fourth connection ear pieces (41).

10. The power source testing mechanism for folding wings according to claim 1, characterized in that: Also included are a plurality of fasteners (12); The bottom of the base (1) is provided with a plurality of eighth connection holes (101); A plurality of the eighth connection holes (101) are arranged at intervals along the width direction of the base (1); One end of each of the plurality of fasteners (12) passes through the corresponding eighth connection hole (101) and is connected to the foundation.

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