Aircraft connecting assembly and aircraft

Abstract

The invention discloses an aircraft connecting assembly and an aircraft, and relates to the technical field of aircrafts, the aircraft connecting assembly comprises a fixing shell, the fixing shell is connected with a pair of connecting rods, one side of each connecting rod is slidably connected with an inserting block, the bottom end of each connecting rod is provided with an inserting groove, and one connecting rod is internally and rotatably connected with a wind shielding cloth roll; the aircraft connecting assembly comprises a fixing shell, two pairs of connecting rods are slidably connected to the fixing shell, the connecting rods are slidably connected to a fixing frame through sliding grooves, a supporting rod is slidably connected to the fixing shell, a sliding block is slidably connected to the supporting rod, and a pull rod is rotatably connected between the sliding block and the fixing frame. The sliding block pushes the fixing frame through the pull rod, so that the two pairs of connecting rods rotate oppositely and are aligned and closed together, the two pairs of connecting rods are pulled to be slowly retracted into the two fixing shells through rotation of the lead screw, fixation is firm, looseness is not likely to happen, the wind blocking cloth roll is pulled out and unfolded during landing, and therefore wind resistance is increased and the sliding distance is reduced during landing of the unmanned aerial vehicle.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to an aircraft connection component and an aircraft. Background Art

[0002] A multi-body combined UAV is composed of multiple UAVs. The wings of two adjacent UAVs can be docked and separated through a detachable structure. Compared with a single UAV, a multi-body combined UAV has a larger aspect ratio and a greater lift-to-drag ratio, so it has better aerodynamic performance and increases its range.

[0003] Referring to the existing Chinese invention patent, the publication number is: CN 116552785 A, and the name of the invention is: An aircraft connection assembly and an aircraft. The invention performs magnetic connection through a first magnetic docking member and a second magnetic docking member. The allowable error of the magnetic connection is relatively high, and high-precision control of the aircraft is not required. The connection efficiency during the connection process can be improved. When connected, the two aircraft are connected by magnetic attraction to each other, and there is no rigid connection, which can reduce the impact on the flight of the aircraft during the connection process.

[0004] However, in actual use, the above technical solutions and similar technical solutions still have some problems:

[0005] 1. In the process of docking aircraft using magnetic connection technology, the wings of the two aircraft must be close to each other before they touch. During this process, multiple blades on the connector need to be unfolded to form a bowl-shaped structure. Although the docking system has a certain fault tolerance, the effective range of its blades is relatively limited. When the docking component is inserted into this structure in the horizontal direction, it is necessary to ensure that the flight altitude and speed of the two aircraft are completely consistent, and then docking is achieved by gradually approaching. If the docking fails, the aircraft needs to separate and try to approach again. This process places high demands on the control of flight speed. Once the speed of the two aircraft deviates, it is very easy to cause docking failure, which increases the complexity of the operation;

[0006] 2. When the wings are docked, a staggered bite design is adopted. The bite depth of this method is relatively small. When the lift of the aircraft on both sides is uneven, it is easy to produce a leverage effect, thereby increasing the risk of fracture in the bite area. Therefore, this docking method puts higher requirements on the strength, toughness and other properties of the wing material;

[0007] 3. The connection components play a key role in the docking of aircraft, but their functions are relatively simple and they occupy a certain space on the wing. These components mainly play a connecting role and fail to realize other additional functions, such as flight speed adjustment. This leads to a decrease in the utilization rate of the wing space and limits the further improvement of the aircraft performance. Summary of the invention

[0008] The purpose of the present invention is to provide an aircraft connection assembly and an aircraft, which adopts longitudinal docking, has low requirements on flight speed, has a small leverage effect when directly inserted into the wing, has diverse functions, and can also assist in landing.

[0009] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: an aircraft connection component, comprising a fixed shell, the fixed shell is connected with a connection mechanism, the connection mechanism comprises a connecting rod, the fixed shell is connected with a pair of connecting rods, one side of the connecting rod is slidably connected with a plurality of embedded plug-in blocks, the outer edge of the plug-in block is provided with a card slot, a first spring is installed between the plug-in block and the connecting rod, the interior of the connecting rod is slidably connected with an ejection bar, the ejection bar is serrated, the serrated protruding end of the ejection bar abuts against the bottom end of the plug-in block, the bottom end of the connecting rod is provided with a slot, the plug-in block is used to extend into the slot and abut against the connecting rod, the connecting rod is slidably connected with a card strip, the card strip is serrated, the serrated protruding end of the card strip is used to extend into the inside of the card slot, and one end of the ejection bar and the card strip are both installed with a first pull rope;

[0010] A pair of connecting rods are rotatably connected to each other, and a speed reduction mechanism is connected to the connecting rods. The speed reduction mechanism includes a windshield cloth roll, one of the connecting rods is rotatably connected to a windshield cloth roll, and the free end of the windshield cloth roll extends out of the outer wall of the connecting rod, and a volute spring is installed between the rotating shaft of the windshield cloth roll and the connecting rod, a pin bar is fixedly connected to the free end of the windshield cloth roll, and a limiting component for limiting the pin bar is connected to the other connecting rod.

[0011] As a preferred technical solution of the present invention, the limiting assembly includes a docking groove, the connecting rod is provided with a docking groove, the connecting rod is located inside the docking groove and is slidably connected to a push bar, a fourth spring is installed between the push bar and the connecting rod, and a pin block is slidably connected to the connecting rod, the pin block is perpendicular to the push bar, one end of the pin block extends into the pin groove, the push bar is serrated, the serrated protruding end of the push bar is in contact with the other end of the push bar, and one end of the card bar and the ejection bar are respectively in contact with one side of the push bar.

[0012] As a preferred technical solution of the present invention, a second spring is installed between the ejection bar and the connecting rod, a second spring is also installed between the clamping bar and the connecting rod, and the first pull rope passes through the second spring.

[0013] As a preferred technical solution of the present invention, a concession mechanism is connected to the connecting rod, and the concession mechanism includes a slide groove. Slide grooves are provided on both sides of the connecting rod. The connecting rod is slidably connected to a fixed frame through the slide groove. A third spring is installed between the fixed frame and the connecting rod. A pair of the fixed frames are rotatably connected, and the pair of connecting rods rotate through a pair of fixed frames.

[0014] As a preferred technical solution of the present invention, a driving mechanism is connected to the fixed shell, and the driving mechanism includes a support rod, the fixed shell is slidably connected to the support rod, a pair of rotating shafts of the fixed frame are installed on the support rod, the fixed frame is rotatably connected to the support rod, a slider is slidably connected to the support rod, a pull rod is rotatably connected between the slider and the fixed frame, a fifth spring is installed between the slider and the support rod, and a second pull rope is installed on the slider.

[0015] As a preferred technical solution of the present invention, one end of the support rod is fixedly connected to a mounting plate, a plurality of electric push rods are installed on the mounting plate, a fixing plate is fixedly connected to the mounting plate, a sleeve is installed between the fixing plate and the connecting rod, the sleeve is movably sleeved on the outside of the first pull rope, and one end of the first pull rope and the second pull rope are both installed on different electric push rods.

[0016] As a preferred technical solution of the present invention, a storage mechanism is connected to the fixed shell, and the storage mechanism includes a motor. The motor is installed in the fixed shell, and a screw rod is installed on the output shaft of the motor. The screw rod is rotatably connected to the fixed shell, and the screw rod is threadedly connected to the support rod.

[0017] As a preferred technical solution of the present invention, the two pairs of connecting rods on the two pairs of the fixing shells are staggered, and the internal width of the fixing shells is twice that of the connecting rods.

[0018] An aircraft comprises an unmanned aerial vehicle body, both sides of the unmanned aerial vehicle body are equipped with wings, and the fixing shell is fixedly embedded in the inside of the wings.

[0019] As a preferred technical solution of the present invention, the end of the wing facing away from the drone body is planar, the end of the fixed shell close to the connecting rod is parallel to the end of the wing, the bottom end of the drone body is equipped with landing wheels, and the wing is equipped with an engine.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1. The present invention uses two pairs of connecting rods to approach and collide with each other by placing the wings of two UAVs one in front of the other. Since the connecting rods are unfolded into a "V"-shaped structure, the two pairs of connecting rods have a large fault tolerance when they collide with each other. When the two pairs of connecting rods collide with each other, one of the plug blocks on each connecting rod is inserted into the interior of the slot, and the card strip extends into the card slot and collides with the plug block, thereby limiting the detachment of the plug block extending into the interior of the slot, thereby limiting the detachment of the two pairs of connecting rods that collide with each other, so that the two UAVs are connected together. Compared with a single UAV, the multi-body combined UAV has a larger aspect ratio and an increased lift-to-drag ratio, so it has better aerodynamic performance and increases the range. By adopting the longitudinal docking method, only one of the aircraft needs to be accelerated when the horizontal heights are the same, and the docking is easy to operate.

[0022] 2. The present invention separates the ejection bar from the plug-in block by pulling the ejection bar, and the first spring contracts, thereby pulling the unrestricted plug-in block to hide, releasing the second pull rope, and the compressed fifth spring will extend. The slider pushes the fixed frame through the pull rod, so that the two pairs of fixed frames drive the two pairs of connecting rods to rotate toward each other and align and close together. When the distances between the two plug-ins and the ends of the two connecting rods are unequal, the two pairs of connecting rods will approach each other, and the plug-in blocks will push the two connecting rods to slide along the slide groove. The third spring will extend or compress, so that the two pairs of connecting rods can be aligned and close together, thereby playing a concession role. The screw rotates and pulls the two pairs of connecting rods to slowly retract into the interior of the two fixed shells. The leverage effect is small, and the two drones are pulled closer to each other. The ends of the two wings are parallel, so that they are in conflict with each other and docked, firmly fixed, and not easy to loosen.

[0023] 3. The present invention limits the position of the pin bar. When each pair of connecting rods is unfolded, the pin bar will follow the movement of the connecting rod, so that the windshield cloth roll is pulled out and unfolded. The windshield cloth roll rotates, and the scroll spring contracts, so as to increase the wind resistance when the UAV lands, thereby slowing down the UAV. By controlling the distance between each pair of connecting rods, the length of the windshield cloth roll that is pulled out can be controlled, thereby controlling the size of the wind resistance, which is convenient for rapid landing through the landing wheels. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention;

[0025] Figure 2 It is a partial structural schematic diagram of the connecting rod of the present invention;

[0026] Figure 3 It is a partial structural schematic diagram of the fixed shell of the present invention;

[0027] Figure 4 It is a partial structural schematic diagram of the windshield cloth roll of the present invention;

[0028] Figure 5 It is a partial structural schematic diagram of the fixing frame of the present invention;

[0029] Figure 6 It is a partial structural schematic diagram of the mounting plate of the present invention;

[0030] Figure 7 It is a partial structural schematic diagram of the electric push rod of the present invention;

[0031] Figure 8 It is a partial structural schematic diagram of the support rod of the present invention;

[0032] Fig. 9 It is a partial structural schematic diagram of the third spring of the present invention;

[0033] Fig.10 It is a partial structural schematic diagram of the ejector strip of the present invention;

[0034] Fig.11 It is a partial structural schematic diagram of the card strip of the present invention;

[0035] Fig.12 It is a partial structural schematic diagram of the slot of the present invention;

[0036] Fig.13 It is a partial structural schematic diagram of the volute spring of the present invention;

[0037] Fig.14 It is a partial structural schematic diagram of the docking groove of the present invention;

[0038] Fig.15 It is a partial structural schematic diagram of the push bar of the present invention;

[0039] Fig.16 It is a partial structural schematic diagram of the pin block of the present invention.

[0040] In the figure: 1. UAV body; 2. Wing; 3. Landing wheel; 4. Engine; 5. Connecting mechanism; 51. Connecting rod; 52. Insert block; 53. Slot; 54. First pull rope; 55. First spring; 56. Second spring; 57. Ejector bar; 58. Card bar; 59. Card slot; 6. Concession mechanism; 61. Fixed frame; 62. Third spring; 63. Slide; 7. Speed ​​reduction mechanism; 71. Windshield cloth roll; 72 , pin bar; 73, pin groove; 74, scroll spring; 75, push bar; 76, pin block; 77, fourth spring; 78, docking groove; 8, driving mechanism; 81, sleeve; 82, fixing plate; 83, electric push rod; 84, pull rod; 85, slider; 86, second pull rope; 87, fifth spring; 88, support rod; 9, storage mechanism; 91, fixing shell; 92, motor; 93, screw rod; 94, mounting plate. DETAILED DESCRIPTION

[0041] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0042] See also Figure 1-Figure 16 , the present invention provides an aircraft connection assembly and an aircraft:

[0043] Embodiment 1:

[0044] according to Figure 1 , Figure 2 , Figure 3 , Figure 5 , Fig.10 and Fig.11 As shown, an aircraft connection assembly includes a fixed shell 91, a connection mechanism 5 is connected to the fixed shell 91, and the connection mechanism 5 includes a connection rod 51. A pair of connection rods 51 are connected to the fixed shell 91. The two pairs of connection rods 51 cross and interfere with each other, thereby facilitating docking, increasing the contact area, and improving the fault tolerance rate. A plurality of embedded plug-in blocks 52 are slidably connected to one side of the connection rod 51. A card slot 59 is provided on the outer edge of the plug-in block 52. A first spring 55 is installed between the plug-in block 52 and the connection rod 51. The interior of the connection rod 51 is slidably connected to a push-out strip 57. The push-out strip 57 is saw-shaped. The sawtooth protruding end of the ejection strip 57 abuts against the bottom end of the plug block 52. A slot 53 is provided at the bottom end of the connecting rod 51. The plug block 52 is used to extend into the slot 53 and abut against the connecting rod 51. A clamping strip 58 is slidably connected to the connecting rod 51. The clamping strip 58 has a sawtooth structure. The sawtooth protruding end of the clamping strip 58 is used to extend into the interior of the clamping slot 59, thereby limiting the detachment of the plug block 52, so that the two pairs of connecting rods 51 that abut each other are firmly abutted. A first pull rope 54 is installed at one end of the ejection strip 57 and the clamping strip 58, and the movement of the ejection strip 57 and the clamping strip 58 can be controlled by the first pull rope 54.

[0045] In the present invention, a second spring 56 is installed between the ejection bar 57 and the connecting rod 51, and a second spring 56 is also installed between the clamping bar 58 and the connecting rod 51. The first pull rope 54 passes through the second spring 56, so that when the first pull rope 54 is released, the ejection bar 57 and the clamping bar 58 can be pushed to reset.

[0046] In the present invention, the two pairs of connecting rods 51 on the two pairs of fixed shells 91 are staggered, and the internal width of the fixed shells 91 is twice that of the connecting rods 51 , so that the two pairs of connecting rods 51 can be inserted into the two connected fixed shells 91 .

[0047] The present invention includes a drone body 1, with wings 2 installed on both sides of the drone body 1, a fixed shell 91 fixedly embedded in the inside of the wing 2, the end of the wing 2 facing away from the drone body 1 is flat, and one end of the fixed shell 91 close to the connecting rod 51 is parallel to the end of the wing 2, a landing wheel 3 is installed at the bottom of the drone body 1, and an engine 4 is installed on the wing 2, so as to facilitate the drone to take off and land.

[0048] Embodiment 2:

[0049] Based on Example 1, Figure 4 , Fig.12 , Fig.13 , Fig.14 , Fig.15 and Fig.16 As shown, an aircraft is rotatably connected between a pair of connecting rods 51, and a deceleration mechanism 7 is connected to the connecting rod 51. The deceleration mechanism 7 includes a windshield cloth roll 71, wherein the windshield cloth roll 71 is rotatably connected in one of the connecting rods 51, and the free end of the windshield cloth roll 71 extends out of the outer wall of the connecting rod 51, and a volute spring 74 is installed between the rotating shaft of the windshield cloth roll 71 and the connecting rod 51, so as to automatically retract the windshield cloth roll 71 when the pair of connecting rods 51 are brought together, and a pin bar 72 is fixedly connected to the free end of the windshield cloth roll 71, and a limiting component for limiting the pin bar 72 is connected to the other connecting rod 51, so that when controlling the distance between each pair of connecting rods 51, the length of the windshield cloth roll 71 being pulled out can be controlled, thereby controlling the size of the wind resistance, and facilitating rapid landing through the landing wheel 3.

[0050] In the present invention, the limiting assembly includes a docking groove 78, a docking groove 78 is provided on the connecting rod 51, the connecting rod 51 is located inside the docking groove 78 and is slidably connected to a push bar 75, a fourth spring 77 is installed between the push bar 75 and the connecting rod 51, a pin block 76 is slidably connected to the connecting rod 51, the pin block 76 is perpendicular to the push bar 75, one end of the pin block 76 extends into the pin groove 73, the push bar 75 is serrated, and the serrated protruding end of the push bar 75 is in conflict with the other end of the push bar 75, and one end of the locking strip 58 and the ejection strip 57 are respectively in conflict with one side of the push bar 75, so as to facilitate the limiting and fixing of the pin bar 72, so as to facilitate the pulling out of the windshield cloth roll 71 when a pair of connecting rods 51 are unfolded.

[0051] Embodiment 3:

[0052] Based on Example 2, Figure 6 , Figure 7 , Figure 8 and Fig. 9As shown, an aircraft is shown, a connecting rod 51 is connected to a concession mechanism 6, the concession mechanism 6 includes a slide groove 63, slide grooves 63 are provided on both sides of the connecting rod 51, the connecting rod 51 is slidably connected to a fixed frame 61 through the slide groove 63, a third spring 62 is installed between the fixed frame 61 and the connecting rod 51, a pair of fixed frames 61 are rotationally connected, a pair of connecting rods 51 rotate through a pair of fixed frames 61, when the distances between the two plug blocks 52 reaching the ends of the two connecting rods 51 are unequal, the two pairs of connecting rods 51 are brought together, and the two connecting rods 51 are pushed by the plug blocks 52 to slide along the slide groove 63. The third spring 62 will be stretched or compressed, so that the two pairs of connecting rods 51 can be aligned and brought together.

[0053] In the present invention, a driving mechanism 8 is connected to the fixed shell 91, and the driving mechanism 8 includes a support rod 88. The fixed shell 91 is slidably connected to the support rod 88, and a pair of rotating axes of the fixed frame 61 are installed on the support rod 88. The fixed frame 61 is rotatably connected to the support rod 88. A slider 85 is slidably connected to the support rod 88. A pull rod 84 is rotatably connected between the slider 85 and the fixed frame 61. A fifth spring 87 is installed between the slider 85 and the support rod 88, and a second pull rope 86 is installed on the slider 85, so that it is convenient to control the expansion or closing of a pair of connecting rods 51 by pulling the second pull rope 86.

[0054] In the present invention, one end of the support rod 88 is fixedly connected to a mounting plate 94, a plurality of electric push rods 83 are installed on the mounting plate 94, a fixing plate 82 is fixedly connected to the mounting plate 94, a sleeve 81 is installed between the fixing plate 82 and the connecting rod 51, the sleeve 81 is movably sleeved on the outside of the first pull rope 54, one end of the first pull rope 54 and the second pull rope 86 are installed on different electric push rods 83, so as to facilitate the control of the operation of the first pull rope 54 and the second pull rope 86.

[0055] In the present invention, a storage mechanism 9 is connected to the fixed shell 91, and the storage mechanism 9 includes a motor 92. The motor 92 is installed in the fixed shell 91, and a screw rod 93 is installed on the output shaft of the motor 92. The screw rod 93 is rotatably connected to the fixed shell 91, and the screw rod 93 is threadedly connected to the support rod 88, so as to facilitate pulling a pair of connecting rods 51 into the interior of the fixed shell 91.

[0056] Working principle:

[0057] The engine 4 provides power, and the wing 2 generates lift to drive the drone body 1 to fly. When the two drones are docked in the air, the positions of the drones are determined, and the wings 2 of the two drones are arranged one in front of the other, so that the two pairs of connecting rods 51 are close to each other and collide with each other. Since the connecting rods 51 are unfolded into a "V" shape structure, the two pairs of connecting rods 51 have a large tolerance when they collide with each other. When the two pairs of connecting rods 51 collide with each other, one of the plugs 52 on each connecting rod 51 is inserted into the inside of the slot 53, and the electric push rod 83 of the control card strip 58 is started, and the first pull rope 54 is pulled through the sleeve 81, thereby pulling the card strip 58, and the card strip 58 is pulled. The sawtooth end extends into the slot 53, and the card strip 58 contacts the plug block 52 by extending into the card slot 59. The second spring 56 at one end of the card strip 58 is compressed, thereby limiting the disengagement of the plug block 52 extending into the slot 53, thereby limiting the disengagement of the two pairs of connecting rods 51 that conflict with each other, so that the two drones are connected together. Compared with a single drone, the multi-body combined drone has a larger aspect ratio and an increased lift-to-drag ratio, so it has better aerodynamic performance and increases the range. The electric push rod 83 is reversely driven, and the card strip 58 is reset under the action of the second spring 56, thereby releasing the plug block 52, and the two pairs of connecting rods 51 can be separated from each other, thereby completing the separation of docking;

[0058] Before docking, align the connecting rod 51 with the rear of the empty end of the fixed shell 91 of the other UAV. After docking, start the electric push rod 83 corresponding to the first pull rope 54 on the ejection bar 57, pull the first pull rope 54, thereby pulling the ejection bar 57, compressing the second spring 56, separating the serrated protruding end of the ejection bar 57 from the plug block 52, and contracting the stretched first spring 55, thereby pulling the unrestricted plug block 52 to slide inside the connecting rod 51, thereby hiding the plug block 52, and start the electric push rod 83 corresponding to the second pull rope 86 to release the second pull rope 86, so that the compressed fifth spring 87 will extend, thereby pushing the slider 85, and the slider 85 pushes the fixed frame 61 through the pull rod 84 , so that the two pairs of fixed frames 61 drive the two pairs of connecting rods 51 to rotate toward each other and align and close together. When the distances between the two plug blocks 52 and the ends of the two connecting rods 51 are unequal, the two pairs of connecting rods 51 are brought together, and the plug blocks 52 push the two connecting rods 51 to slide along the slide grooves 63. The third spring 62 will be stretched or compressed, so that the two pairs of connecting rods 51 can be aligned and close together, and the motor 92 is started to drive the screw rod 93 to rotate, drive the support rod 88 and the mounting plate 94 to slide, and thus pull the two pairs of connecting rods 51 slowly into the inside of the two fixed shells 91, thereby pulling the two drones closer to each other, and the ends of the two wings 2 are parallel, so that they are mutually opposed and docked, fixed firmly, and not easy to loosen;

[0059] During the landing of the drone, when the runway is short, the two pairs of connecting rods 51 on the outer wing 2 are extended. When each pair of connecting rods 51 is brought together, the pin bar 72 is inserted into the docking groove 78, and the electric push rod 83 corresponding to the ejection bar 57 or the clamping bar 58 is controlled to release the first pull rope 54. The compressed second spring 56 will continue to extend, thereby pushing the ejection bar 57 or the clamping bar 58. The end of the ejection bar 57 or the clamping bar 58 contacts the push bar 75, pushing the push bar 75, compressing the fourth spring 77, and the serrations of the push bar 75 protrude. The end will push the pin block 76, and the pin block 76 will enter the pin groove 73, thereby limiting the pin bar 72. When each pair of connecting rods 51 is unfolded, the pin bar 72 will follow the movement of the connecting rod 51, thereby pulling out the windshield cloth roll 71 and unfolding it. The windshield cloth roll 71 rotates, and the volute spring 74 contracts, so as to increase the wind resistance when the UAV lands, thereby slowing down the UAV. By controlling the distance between each pair of connecting rods 51, the length of the windshield cloth roll 71 that is pulled out can be controlled, thereby controlling the size of the wind resistance, and facilitating rapid landing through the landing wheel 3.

[0060] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. An aircraft connection assembly, comprising a fixing shell (91), to which a connecting mechanism (5) is connected, characterized in that: The connecting mechanism (5) comprises a connecting rod (51), a pair of connecting rods (51) are connected to the fixed shell (91), a plurality of embedded plug-in blocks (52) are slidably connected to one side of the connecting rod (51), a slot (59) is provided on the outer edge of the plug-in block (52), a first spring (55) is installed between the plug-in block (52) and the connecting rod (51), the interior of the connecting rod (51) is slidably connected to an ejection bar (57), the ejection bar (57) is serrated, and the ejection bar (57) is ) is in contact with the bottom end of the plug block (52), a slot (53) is provided at the bottom end of the connecting rod (51), the plug block (52) is used to extend into the slot (53) and contact the connecting rod (51), a clamping strip (58) is slidably connected to the connecting rod (51), the clamping strip (58) is in a sawtooth structure, the sawtooth protruding end of the clamping strip (58) is used to extend into the interior of the clamping slot (59), and one end of each of the ejection strip (57) and the clamping strip (58) is installed with a first pull rope (54); A pair of connecting rods (51) are rotatably connected to each other, and a deceleration mechanism (7) is connected to the connecting rod (51). The deceleration mechanism (7) includes a windshield cloth roll (71), one of the connecting rods (51) is rotatably connected to a windshield cloth roll (71), and the free end of the windshield cloth roll (71) extends out of the outer wall of the connecting rod (51). A volute spring (74) is installed between the rotating shaft of the windshield cloth roll (71) and the connecting rod (51), and a pin bar (72) is fixedly connected to the free end of the windshield cloth roll (71), and a limiting component for limiting the pin bar (72) is connected to the other connecting rod (51).

2. An aircraft connection assembly according to claim 1, characterized in that: The limiting assembly comprises a docking groove (78), a docking groove (78) is provided on the connecting rod (51), a push bar (75) is slidably connected to the connecting rod (51) inside the docking groove (78), a fourth spring (77) is installed between the push bar (75) and the connecting rod (51), a pin block (76) is slidably connected to the connecting rod (51), the pin block (76) is perpendicular to the push bar (75), one end of the pin block (76) extends into the pin groove (73), the push bar (75) is serrated, the serrated protruding end of the push bar (75) abuts against the other end of the push bar (75), and one end of the clamping bar (58) and the ejecting bar (57) respectively abuts against one side of the push bar (75).

3. An aircraft connection assembly according to claim 2, characterized in that: A second spring (56) is installed between the ejection strip (57) and the connecting rod (51), and a second spring (56) is also installed between the clamping strip (58) and the connecting rod (51), and the first pull rope (54) passes through the second spring (56).

4. An aircraft connection assembly according to claim 2, characterized in that: The connecting rod (51) is connected to a concession mechanism (6), the concession mechanism (6) comprises a slide groove (63), both sides of the connecting rod (51) are provided with a slide groove (63), the connecting rod (51) is slidably connected to a fixed frame (61) through the slide groove (63), a third spring (62) is installed between the fixed frame (61) and the connecting rod (51), a pair of the fixed frames (61) are rotationally connected, and the pair of the connecting rods (51) rotate through the pair of fixed frames (61).

5. An aircraft connection assembly according to claim 4, characterized in that: The fixed shell (91) is connected to a driving mechanism (8), and the driving mechanism (8) includes a support rod (88). The fixed shell (91) is slidably connected to the support rod (88), a pair of rotating shafts of the fixed frame (61) are installed on the support rod (88), the fixed frame (61) is rotatably connected to the support rod (88), a slider (85) is slidably connected to the support rod (88), a pull rod (84) is rotatably connected between the slider (85) and the fixed frame (61), a fifth spring (87) is installed between the slider (85) and the support rod (88), and a second pull rope (86) is installed on the slider (85).

6. An aircraft connection assembly according to claim 5, characterized in that: One end of the support rod (88) is fixedly connected to a mounting plate (94), a plurality of electric push rods (83) are mounted on the mounting plate (94), a fixing plate (82) is fixedly connected to the mounting plate (94), a sleeve (81) is mounted between the fixing plate (82) and the connecting rod (51), the sleeve (81) is movably sleeved on the outside of the first pull rope (54), and one end of the first pull rope (54) and the second pull rope (86) are both mounted on different electric push rods (83).

7. An aircraft connection assembly according to claim 5, characterized in that: The fixed shell (91) is connected to a storage mechanism (9), the storage mechanism (9) comprises a motor (92), the motor (92) is installed in the fixed shell (91), a screw rod (93) is installed on the output shaft of the motor (92), the screw rod (93) is rotatably connected to the fixed shell (91), and the screw rod (93) is threadedly connected to the support rod (88).

8. An aircraft connection assembly according to claim 1, characterized in that: The two pairs of connecting rods (51) on the two pairs of fixed shells (91) are distributed in a staggered manner, and the internal width of the fixed shells (91) is twice that of the connecting rods (51).

9. An aircraft, comprising the aircraft connection assembly according to claim 1, characterized in that: It comprises an unmanned aerial vehicle body (1), with wings (2) installed on both sides of the unmanned aerial vehicle body (1), and the fixed shell (91) is fixedly embedded in the interior of the wings (2).

10. An aircraft according to claim 9, characterized in that: The end of the wing (2) facing away from the drone body (1) is in a planar shape, one end of the fixed shell (91) close to the connecting rod (51) is parallel to the end of the wing (2), the bottom end of the drone body (1) is equipped with a landing wheel (3), and the wing (2) is equipped with an engine (4).

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