Aircraft folding mechanism and aircraft

Abstract

The utility model discloses an aircraft folding mechanism and an aircraft. The aircraft folding mechanism comprises an aircraft body connector, aircraft arms, adapter connectors and connecting pieces. One end, close to the fuselage joint, of each arm is connected with an adapter which is connected with the fuselage joint; the connecting pieces are arranged on the vehicle arms in a sleeving manner, and are detachably connected with the vehicle body joints; the adapter joint is of a conical structure, and the diameter of the conical structure is gradually reduced in the direction of the fuselage joint; in an unfolded state, the adapter joint is coaxial with the fuselage joint, and the adapter joint is fixedly connected with the fuselage joint through a connecting piece; and in a folding state, the adapter joint is vertically connected to the fuselage joint. According to the aircraft, the problem that in the prior art, when the aircraft is idle on the ground, the arms of the aircraft are too long and suspended and are prone to being damaged by external force impact is solved, the occupied space of the aircraft is reduced on the premise that the flight requirement of the aircraft is met, and therefore the damage risk caused by suspension of the arms of the aircraft when the aircraft is idle is avoided.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft, and in particular to an aircraft folding mechanism and an aircraft. Background Art

[0002] In recent years, aircraft technology has developed rapidly, among which drones have been widely used in various industries and fields. For example, multi-rotor drones have attracted widespread attention due to their advantages of vertical take-off and landing and hovering in the air. Among them, the packaging and transfer transportation of multi-rotor drones have always been issues that must be considered when designing drones.

[0003] At present, most multi-rotor drones on the market have an integrated structure of arms and fuselage, which is costly to pack and transport, and the motor and blades are easily damaged during placement. This patent designs a quick folding and locking mechanism for drone arms, which enables the drone to be quickly folded down when not in operation, reducing the space occupied by the aircraft and reducing the risk of the arms being broken by external impact. Utility Model Content

[0004] The embodiments of the present application provide an aircraft folding and locking mechanism to solve the problems in the prior art that when the aircraft is idle on the ground, the aircraft's arms are too long and suspended in the air, making them susceptible to damage from external impacts, and that when the aircraft's arms are in an unfolded state, they occupy a large area, causing inconvenience in packaging and transfer transportation. This achieves the goal of reducing the space occupied by the aircraft while meeting the flight requirements of the aircraft, thereby avoiding the risk of damage caused by the aircraft's arms being suspended in the air when idle.

[0005] In the first aspect, an embodiment of the utility model provides an aircraft folding mechanism, comprising a fuselage joint, an arm, an adapter joint and a connecting piece; the adapter joint is connected to one end of the arm close to the fuselage joint, and the adapter joint is connected to the fuselage joint; the connecting piece is sleeved on the arm, and the connecting piece is detachably connected to the fuselage joint; the adapter joint is a conical structure, and the diameter of the conical structure gradually decreases along the direction of the fuselage joint; in the unfolded state, the adapter joint is coaxial with the fuselage joint, and the adapter joint is fixedly connected to the fuselage joint through the connecting piece; in the folded state, the adapter joint is vertically connected to the fuselage joint.

[0006] In combination with the first aspect, in a possible implementation, it also includes a locking joint; the locking joint is connected to one end of the fuselage joint close to the arm, and the adapter joint is connected to the locking joint; the connecting piece is detachably connected to the locking joint.

[0007] In combination with the first aspect, in a possible implementation, it also includes a latch, a shell and an elastic member; the shell is connected to the outer side of the locking joint, the latch passes through the shell and abuts against the connecting member; a groove is provided on the side of the connecting member close to the fuselage joint, and an end of the latch close to the connecting member is inserted into the groove; the elastic member is sleeved on the latch and arranged inside the shell, and when the latch is in an unlocked state, the latch as a whole moves in a direction away from the machine arm, so that the elastic member is compressed; when the latch is in a locked state, the latch as a whole moves in a direction close to the machine arm under the action of the elastic member, and the end of the latch is inserted into the groove.

[0008] In combination with the first aspect, in a possible implementation, it also includes a rotating shaft; the locking joint is provided with a sliding groove, and the rotating shaft is arranged in the sliding groove; the adapter joint is rotatably connected to the rotating shaft; when in the unfolded state, the adapter joint is inserted into the interior of the locking joint, and the adapter joint is configured to drive the rotating shaft to move in the sliding groove.

[0009] In combination with the first aspect, in a possible implementation manner, the locking joint is provided with a track; and the adapter joint is configured to slide within the track.

[0010] In combination with the first aspect, in a possible implementation, it further includes a limiter; the limiter is connected to the outer side of the arm, and the limiter is configured to limit the range of movement of the connecting member in the length direction of the arm.

[0011] In combination with the first aspect, in a possible implementation, a sunken groove is provided on the outer side of the sliding slot, and when the arm is folded downward, the rotating shaft is inserted into the sunken groove; the sunken groove is configured to limit the forward and backward movement of the arm when folded.

[0012] In combination with the first aspect, in a possible implementation, the adapter joint includes a slider and a conical block; the side of the conical block close to the slider is a first plane, and the slider is connected to the first plane; the slider cooperates with the track; the conical block is connected to the inside of the locking joint; the inside of the locking joint close to the track is a second plane, the second plane cooperates with the first plane, and the first plane and the second plane are configured to limit the rotation of the arm.

[0013] In a second aspect, an embodiment of the utility model provides an aircraft, characterized in that the aircraft comprises the aircraft folding mechanism described in the first aspect or any possible implementation of the first aspect.

[0014] One or more technical solutions provided by this application have at least the following technical effects:

[0015] The embodiment of the utility model adopts a fuselage joint, an arm, an adapter joint and a connecting piece; an adapter joint is connected to one end of the arm close to the fuselage joint, and the adapter joint is rotatably connected to the fuselage joint; the adapter joint can rotate around the fuselage joint, thereby driving the arm to rotate around the fuselage joint; the connecting piece is sleeved on the arm, and the connecting piece is detachably connected to the fuselage joint; the adapter joint is a conical structure, and the diameter of the conical structure gradually decreases along the direction of the fuselage joint, so that when the arm is pulled out, it is convenient for the adapter joint to be rotated out of the fuselage; in the unfolded state, the adapter joint is coaxial with the fuselage joint, and the adapter joint is fixedly connected to the fuselage joint through the connecting piece, that is, in the unfolded state, the arm is horizontally arranged, at this time , the fuselage joint and the adapter joint are connected by a connecting piece to ensure the normal flight of the aircraft; in the folded state, the adapter joint is vertically arranged on the fuselage joint, and the adapter joint rotates relative to the fuselage joint, thereby realizing the folding of the arm relative to the fuselage joint; the present application solves the problem in the prior art that when the aircraft is idle on the ground, the aircraft arm is too long and the arm is suspended in the air, which is easily damaged by external force impact, and the aircraft arm is in the unfolded state. The occupied area is large, which makes packaging and transfer transportation inconvenient, and the occupied space of the aircraft is reduced while meeting the flight requirements of the aircraft, thereby avoiding the risk of damage caused by the aircraft arm being suspended in the air when idle. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the description of the embodiments of the utility model will be briefly introduced below. Obviously, the drawings described below are some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 A front view of an aircraft folding mechanism provided in an embodiment of the present application;

[0018] Figure 2 A schematic diagram of a latch, a housing and an elastic member provided in an embodiment of the present application;

[0019] Figure 3 A schematic diagram of a connecting member and a limiting member provided in an embodiment of the present application;

[0020] Figure 4 A right side view of the folded state provided by the embodiment of the present application;

[0021] Figure 5 A schematic diagram of an adapter joint and a rotating shaft provided in an embodiment of the present application;

[0022] Figure 6 An axonometric view of the adapter provided in an embodiment of the present application.

[0023] Icons: 1-body joint; 2-arm; 3-adapter joint; 31-slider; 32-conical block; 321-first plane; 4-connector; 41-groove; 5-locking joint; 51-sliding groove; 52-track; 53-sunk groove; 54-second plane; 6-latch pin; 7-housing; 8-elastic part; 9-spindle; 10-limiting part; 11-cotter pin; 12-hexagonal slot nut; 13-gasket. DETAILED DESCRIPTION

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

[0025] In the description of the embodiments of the present utility model, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "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 utility model 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 utility model. The terms "first", "second", and "third" are only used for descriptive purposes 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 ordinary technicians in this field, the specific meanings of the above terms in the embodiments of the present utility model can be understood according to specific circumstances.

[0026] An aircraft folding mechanism, such as Figure 1 and Figure 4As shown, it includes a fuselage joint 1, an arm 2, an adapter joint 3 and a connector 4; the adapter joint 3 is connected to one end of the arm 2 close to the fuselage joint 1, and the adapter joint 3 is connected to the fuselage joint 1; the connector 4 is sleeved on the arm 2, and the connector 4 is detachably connected to the fuselage joint 1; the adapter joint 3 is a conical structure, and the diameter of the conical structure gradually decreases along the direction of the fuselage joint 1; in the unfolded state, the adapter joint 3 is coaxial with the fuselage joint 1, and the adapter joint 3 is fixedly connected to the fuselage joint 1 through the connector 4; in the folded state, the adapter joint 3 is vertically connected to the fuselage joint 1.

[0027] Exemplarily, the adapter joint 3 can rotate around the fuselage joint 1, thereby driving the arm 2 to rotate around the fuselage joint 1; further, the adapter joint is a conical structure, so that when the arm 2 is pulled out, it is convenient for the adapter joint 3 to be rotated out of the fuselage.

[0028] Exemplarily, in the unfolded state, the adapter joint 3 is coaxial with the fuselage joint 1, and the adapter joint 3 is fixedly connected to the fuselage joint 1 through the connector 4, that is, in the unfolded state, the arm 2 is horizontally arranged. At this time, the fuselage joint 1 and the adapter joint 3 are connected by the connector 4 to ensure the normal flight of the aircraft; in the folded state, the adapter joint 3 is vertically connected to the fuselage joint 1, and the adapter joint 3 rotates relative to the fuselage joint 1, thereby realizing the folding of the arm 2 relative to the fuselage joint 1.

[0029] In the present application embodiment, Figure 1 and Figure 3 As shown, it also includes a locking joint 5; the locking joint 5 is connected to one end of the fuselage joint 1 close to the arm 2, the adapter joint 3 is connected to the locking joint 5; the connecting piece 4 is detachably connected to the locking joint 5.

[0030] Exemplarily, the locking joint 5 is connected to one end of the fuselage joint 1 close to the arm 2, and an interface matching the adapter joint 3 is provided in the locking joint 5, which can increase the stability of the connection of the adapter joint 3 and increase the reliability of the arm 2 in flight. In the unfolded state, the adapter joint 3 is coaxial with the locking joint 5, and one end of the adapter joint 3 is inserted into the adapter joint 3, and the adapter joint 3 is threadedly connected to the locking joint 5 through the connector 4; in the folded state, the adapter joint 3 is vertically arranged on the locking joint 5, and the adapter joint 3 rotates relative to the locking joint 5, so that the arm 2 can be folded relative to the locking joint 5.

[0031] In the present application embodiment, Figure 1 and Figure 2As shown, it also includes a latch 6, a shell 7 and an elastic member 8; the shell 7 is connected to the outer side of the locking joint 5, the latch 6 passes through the shell 7 and abuts against the connecting member 4; a groove 41 is provided on the side of the connecting member 4 close to the fuselage joint 1, and an end of the latch 6 close to the connecting member 4 is inserted into the groove 41; the elastic member 8 is sleeved on the latch 6 and arranged inside the shell 7. When the latch 6 is in the unlocked state, the latch 6 moves as a whole in the direction away from the machine arm 2, so that the elastic member 8 is compressed; when the latch 6 is in the locked state, the latch 6 moves as a whole in the direction close to the machine arm 2 under the action of the elastic member 8, and the end of the latch 6 is inserted into the groove 41.

[0032] Exemplarily, the latch 6 is L-shaped, and a part of the L-shaped latch 6 is arranged in the shell 7. Under the action of the elastic member 8, the end of the latch 6 can abut against the groove 41, wherein the elastic member 8 can use a spring or other elements with the same function. After the connector 4 completes the connection between the locking connector 5 and the adapter connector 3, the connector 4 can be limited by the latch 6, and the other part of the L-shaped latch 6 abuts against the shell 7, and this part can be used for manual operation.

[0033] Exemplarily, a knob or a marble may be used to replace the limiting mechanism composed of the latch 6 , the housing 7 and the elastic member 8 in the present application, so as to realize the limiting function for the connecting member 4 .

[0034] In the present application embodiment, Figure 4 and Figure 5 As shown, it also includes a rotating shaft 9; the locking joint 5 is provided with a sliding groove 51, and the rotating shaft 9 is arranged in the sliding groove 51; the adapter joint 3 is rotatably connected to the rotating shaft 9; when in the unfolded state, the adapter joint 3 is inserted into the interior of the locking joint 5, and the adapter joint 3 is configured to drive the rotating shaft 9 to move in the sliding groove 51.

[0035] In the present application embodiment, Figure 4 As shown, the locking joint 5 is provided with a track 52 ; the adapter joint 3 is configured to slide in the track 52 .

[0036] Exemplarily, the locking joint 5 and the adapter joint 3 can be connected by the rotating shaft 9. In the unfolded state, the adapter joint 3 slides into the locking joint 5 along the track 52, and the rotating shaft 9 slides in the sliding groove 51 along with the adapter joint 3. After reaching the target position, the adapter joint 3 and the locking joint 5 are connected by the connecting member 4 and then fixed by the latch 6. In the folded state, the latch 6 is pulled open and the connecting member 4 is released, the adapter joint 3 slides out of the locking joint 5 along the track 52, and the rotating shaft 9 slides in the sliding groove 51 along with the adapter joint 3. After reaching the target position, the machine arm 2 is flipped downward so that the angle between the machine arm 2 and the locking joint is 90°.

[0037] In the present application embodiment, Figure 1 and Figure 3 As shown, it also includes a limiter 10 ; the limiter 10 is connected to the outer side of the arm 2 , and the limiter 10 is configured to limit the range of motion of the connecting member 4 in the length direction of the arm 2 .

[0038] Exemplarily, when the connecting member 4 is not connected to the locking joint 5, the connecting member 4 can slide along the length direction on the machine arm 2, and the limiting member 10 can limit the range of movement of the connecting member 4 on the machine arm 2, so as to facilitate manual operation.

[0039] In the present application embodiment, Figure 1 As shown, a sunken groove 53 is provided on the outer side of the sliding groove 51. When the machine arm 2 is folded downward, the rotating shaft 9 is inserted into the sunken groove 53. The sunken groove 53 is configured to limit the forward and backward movement of the machine arm 2 when folding.

[0040] Exemplarily, when the arm 2 is folded downward, the rotating shaft 9 is inserted into the sunken groove 41 , and the sunken groove 41 can limit the forward and backward movement of the arm 2 , thereby increasing the stability of the structure.

[0041] In the present application embodiment, Figure 4 , Figure 5 and Figure 6 As shown, the adapter joint 3 includes a slider 31 and a conical block 32; the side of the conical block 32 close to the slider 31 is a first plane 321, and the slider 31 is connected to the first plane 321; the slider 31 cooperates with the track 52; the conical block 32 is connected to the inside of the locking joint 5; the side of the inside of the locking joint 5 close to the track 52 is a second plane 54, and the second plane 54 cooperates with the first plane 321, and the first plane 321 and the second plane 54 are configured to limit the rotation of the arm 2.

[0042] For example, in the unfolded state, the tapered butt joint surfaces of the locking joint 5 and the adapter joint 3 are tightly pressed, and the first plane 321 and the second plane 54 are in contact, which can limit the adapter joint 3 from rotating in the locking joint 5. Then, the locking joint 5 and the adapter joint 3 are locked by the connector 4, which limits the sliding of the adapter joint 3 in the locking joint 5, thereby increasing the structural stability of the aircraft during flight and improving the overall performance of the aircraft. At the same time, the arrangement of the latch 6 and the connector 4 has the advantage of quick disassembly and assembly, which can reduce the difficulty of operation for the staff.

[0043] An aircraft includes an aircraft folding mechanism. The aircraft folding mechanism of the present application is not limited to the folding of the aircraft arm 2, but also includes the folding of the landing gear and the mounting bracket.

[0044] The present application can reduce the space occupied by the aircraft while meeting the flight requirements of the aircraft, facilitate the packaging and transfer transportation of the aircraft, and avoid the risk of human damage caused by the aircraft arms being suspended in the air when idle.

[0045] 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.

[0046] 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. An aircraft folding mechanism, characterized in that: It comprises a body joint (1), a machine arm (2), a transfer joint (3) and a connecting piece (4); One end of the machine arm (2) close to the machine body joint (1) is connected to the adapter joint (3), and the adapter joint (3) is connected to the machine body joint (1); The connecting piece (4) is sleeved on the machine arm (2), and the connecting piece (4) is detachably connected to the machine body joint (1); The adapter joint (3) is a conical structure, and the diameter of the conical structure gradually decreases along the direction of the fuselage joint (1); When in the unfolded state, the adapter joint (3) is coaxial with the fuselage joint (1), and the adapter joint (3) is fixedly connected to the fuselage joint (1) via the connecting piece (4); when in the folded state, the adapter joint (3) is vertically connected to the fuselage joint (1).

2. The aircraft folding mechanism according to claim 1, characterized in that: Also includes a locking connector (5); The locking joint (5) is connected to one end of the fuselage joint (1) close to the machine arm (2), and the adapter joint (3) is connected to the locking joint (5); The connecting piece (4) is detachably connected to the locking joint (5).

3. The aircraft folding mechanism according to claim 2, characterized in that: It also includes a latch (6), a housing (7) and an elastic member (8); The housing (7) is connected to the outer side of the locking joint (5); the latch (6) passes through the housing (7) and abuts against the connecting member (4); A groove (41) is provided on a side of the connecting piece (4) close to the fuselage joint (1), and an end of the latch (6) close to the connecting piece (4) is inserted into the groove (41); The elastic member (8) is sleeved on the latch (6) and is arranged inside the housing (7); when the latch (6) is in an unlocked state, the latch (6) as a whole moves in a direction away from the machine arm (2), so that the elastic member (8) is compressed; When the latch (6) is in a locked state, the latch (6) as a whole moves in a direction close to the machine arm (2) under the action of the elastic member (8), and the end of the latch (6) is inserted into the groove (41).

4. The aircraft folding mechanism according to claim 2, characterized in that: Also includes a rotating shaft (9); The locking joint (5) is provided with a sliding groove (51), and the rotating shaft (9) is arranged in the sliding groove (51); The adapter joint (3) is rotatably connected to the rotating shaft (9); In the unfolded state, the adapter joint (3) is inserted into the interior of the locking joint (5), and the adapter joint (3) is configured to drive the rotating shaft (9) to move in the sliding groove (51).

5. The aircraft folding mechanism according to claim 4, characterized in that: The locking joint (5) is provided with a track (52); the adapter joint (3) is configured to slide in the track (52).

6. The aircraft folding mechanism according to claim 1, characterized in that: It also includes a limiting member (10); The limiting member (10) is connected to the outer side of the machine arm (2), and the limiting member (10) is configured to limit the range of movement of the connecting member (4) in the length direction of the machine arm (2).

7. The aircraft folding mechanism according to claim 4, characterized in that: A sunken groove (53) is provided on the outer side of the sliding groove (51); when the machine arm (2) is folded downward, the rotating shaft (9) is inserted into the sunken groove (53); the sunken groove (53) is configured to limit the forward and backward movement of the machine arm (2) when folded.

8. The aircraft folding mechanism according to claim 5, characterized in that: The adapter joint (3) comprises a slider (31) and a tapered block (32); A side of the conical block (32) close to the sliding block (31) is a first plane (321), and the sliding block (31) is connected to the first plane (321); The slider (31) cooperates with the track (52); the conical block (32) is connected to the inside of the locking joint (5); A second plane (54) is provided on one side of the locking joint (5) close to the track (52). The second plane (54) cooperates with the first plane (321). The first plane (321) and the second plane (54) are configured to limit the rotation of the machine arm (2).

9. An aircraft, characterized in that: The aircraft comprises an aircraft folding mechanism as claimed in any one of claims 1-8.

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