Rotating shaft assembly of folding empennage comprising multiple locking mechanisms

Abstract

The invention discloses a rotating shaft assembly of a folding empennage comprising multiple locking mechanisms, and relates to the technical field of unmanned aerial vehicles. Comprising a machine body connecting piece, an axial locking end cover, a driving rotating shaft, a wing connecting piece, a locking sleeve and a driven rotating shaft, the wing connecting piece and the driving rotating shaft rotate synchronously, the driven rotating shaft and the wing connecting piece rotate synchronously and can slide in the wing connecting piece, and the locking sleeve is fixedly connected with the machine body connecting piece and can be clamped with the driven rotating shaft in an automatic sliding manner; a driving torsion spring between the driving rotating shaft and the machine body connecting piece drives the wing connecting piece to rotate; the axial locking end cover completes primary locking on the driving rotating shaft through the first conical pin, the driving rotating shaft completes secondary locking with the machine body connecting piece through the two-way elastic pin, and the driven rotating shaft and the machine body connecting piece complete tertiary locking through the fan-shaped boss. The wing locking device is simple in structure, the locking stability after the wing is unfolded in place is improved through three times of locking, and the locking reliability index meets the requirement.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles, and more specifically, relates to a rotating shaft assembly of a deployable and foldable tail wing with multiple locking modes suitable for an aircraft or a flight servo. Background Art

[0002] In the field of drones, aircraft with foldable wings are widely used. Foldable wings can change the shape of the wings in different flight environments to complete specific flight missions. In order to increase the flight distance of drones, the stability of the folding wings becomes a key factor.

[0003] In addition, in the conventional UAV wing folding and unfolding mechanism, the wing is usually locked by axial or longitudinal locking pins after it is fully unfolded, which has a complex structure. Due to the high-frequency vibration generated during flight, the position of the pin and the pin hole will deviate, and the reliability of the pin cannot be guaranteed.

[0004] In the wing folding and unfolding mechanism of conventional UAVs, a single locking mechanism is generally set. The continuous vibration during the flight of the aircraft will accelerate the fatigue and wear of the locking mechanism and surrounding structures, shorten the life of the aircraft, and even cause structural damage during flight.

[0005] The locking mechanism suddenly fails during flight, causing the wings to accidentally retract or loosen. This situation will affect the mission execution of the aircraft. In severe cases, it will cause the aircraft to lose lift and crash. Summary of the invention

[0006] The technical problem to be solved by the present invention is to provide a rotating shaft assembly of a folding tail wing including a multi-locking mechanism, which has a simple structure and improves the locking stability of the wing after it is fully deployed through three lockings, so that the locking reliability index meets the requirements.

[0007] In order to solve the above technical problems, the technical scheme adopted by the present invention is: a rotating shaft assembly of a folding tail wing including a multi-locking mechanism, comprising a body connecting member, an axial locking end cover, an active rotating shaft, a wing connecting member, a locking sleeve, and a passive rotating shaft; the body connecting member is fixedly connected to the aircraft body, the wing connecting member is fixedly connected to the wing of the aircraft, the wing connecting member is sleeved and connected to the outside of the active rotating shaft and rotates synchronously with the active rotating shaft, the active rotating shaft is rotatably connected to the body connecting member, and a passive rotating shaft is also provided in the wing connecting member, the passive rotating shaft rotates synchronously with the wing connecting member and can axially slide and move in the wing connecting member, the locking sleeve is fixedly connected to the body connecting member and can automatically slide and engage with the passive rotating shaft; a driving torsion spring is provided between the active rotating shaft and the body connecting member, and when the wing is unfolded, the driving torsion spring The elastic force of the spring drives the active rotating shaft to rotate, thereby driving the wing connecting piece to rotate; the axial locking end cover is fixedly connected to the body connecting piece, and when the wing is unfolded, the axial locking end cover is locked through the two first conical pins and the active rotating shaft pin hole, so that the active rotating shaft cannot rotate relative to the body connecting piece; a two-way elastic pin is also provided between the active rotating shaft and the body connecting piece, and when the wing is unfolded, the two-way elastic pin automatically locks the active rotating shaft and the body connecting piece, so that the active rotating shaft cannot rotate relative to the body connecting piece; an axial third spring is provided between the passive rotating shaft and the wing connecting piece, and when the wing is unfolded, under the elastic force of the third spring, the passive rotating shaft slides and moves and is locked with the locking sleeve, so that the passive rotating shaft cannot rotate relative to the body connecting piece, thereby preventing the wing connecting piece from rotating relative to the body connecting piece.

[0008] Preferably, the body connecting member includes a first sleeve, a second sleeve, and a third sleeve that are spaced apart and coaxially arranged, and also includes a plurality of through-hole bosses. The three sleeves and the through-hole bosses are fixedly connected to the two sides of the columnar structure, and the through-hole bosses are fixedly connected to the main body of the aircraft by bolts.

[0009] Preferably, the wing connector includes a fourth sleeve and a fifth sleeve that are spaced apart and coaxially arranged, and also includes a plurality of connecting parts. The two sleeves and the connecting parts are fixedly connected on both sides of the column, and the connecting parts are fixedly connected to the wings of the aircraft by bolts; the fourth sleeve is arranged in the gap between the second sleeve and the third sleeve, and the fifth sleeve is arranged in the gap between the first sleeve and the second sleeve.

[0010] Preferably, two connecting keys are provided on the active rotating shaft, one end of the active rotating shaft extends into the fourth sleeve, and the other end passes through the fifth sleeve and then extends into the first sleeve and is rotatably connected to the first sleeve, and the two connecting keys are respectively connected to the fourth sleeve and the fifth sleeve.

[0011] Preferably, the third spring is disposed in the fourth sleeve, one end of the third spring is connected to the fourth sleeve, and the other end of the third spring is in contact with the end surface of the passive rotating shaft.

[0012] Preferably, a boss slider is provided on the side of the passive rotating shaft along the length direction. The boss slider is a fan-shaped protrusion, and the fan-shaped angle is consistent with the rotation angle during the wing expansion process. The boss slider is clamped in the fan-shaped groove of the fourth sleeve and can slide along the fan-shaped groove.

[0013] Preferably, the outer side wall of one end of the locking sleeve is provided with a through hole boss, the through hole boss is fixedly connected to the body connecting piece, and the other end extends into the fourth sleeve and is provided with a fan-shaped groove adapted to the boss slider at the end.

[0014] Preferably, the bidirectional elastic pin includes a second spring and two second conical pins, the second conical pin is a cylindrical structure with one end closed, the open ends of the two second conical pins are arranged facing each other, and the two ends of the second spring are respectively connected to the inner bottom surfaces of the two second conical pins.

[0015] Preferably, the first conical pin is a sleeve with one end closed, and a guide hole is provided on the end face of the axial locking end cover, the open end of the first conical pin extends into the guide hole and can slide in the guide hole, a first spring is provided in the guide hole, one end of the first spring is connected to the bottom surface of the guide hole, and the other end is connected to the inner bottom surface of the first conical pin.

[0016] Preferably, the first conical pin and the second conical pin in the structure have a specific matching angle with the corresponding pin holes, and a self-locking effect can be generated when the conical pins are inserted into the corresponding pin holes.

[0017] The beneficial effects of adopting the above technical solution are:

[0018] 1. The active rotating shaft of the present invention is provided with two locking mechanisms, and the passive rotating shaft is provided with one locking structure, and a total of three locking mechanisms are provided as a whole, which greatly ensures the locking stability of the overall mechanism and enables the wing locking reliability index to meet the requirements.

[0019] 2. The present invention combines the shaft system through a kit, so that the shaft can be modularized and flexibly adjusted to facilitate use in different usage scenarios.

[0020] 3. The present invention can change the diameters of the active rotating shaft and the passive rotating shaft to adapt to tasks under different working conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the structure when the wing is unfolded;

[0022] Figure 2 It is a schematic diagram of the structure of the body connecting parts;

[0023] Figure 3 It is a structural schematic diagram of the active rotating shaft;

[0024] Figure 4It is a schematic diagram of the exploded structure of a bidirectional elastic pin;

[0025] Figure 5 is a schematic diagram of the structure when the locking sleeve and the wing connecting piece are assembled together;

[0026] Figure 6 It is a schematic diagram of the structure of the wing connection;

[0027] Figure 7 It is an exploded schematic diagram of the passive rotating shaft and locking sleeve and wing connection parts;

[0028] Figure 8 It is a schematic diagram of the structure in which the passive rotating shaft, the locking sleeve and the third spring are assembled in the wing connecting member;

[0029] Fig. 9 It is a schematic diagram of the structure of the axial locking end cover;

[0030] Fig.10 This is a schematic diagram of the structure when the wing is folded;

[0031] In the figure: 1 body connecting part, 1-1, first threaded hole, 1-2, keyway, 1-3, radial pin hole, 1-4, process hole, 1-5, threaded through hole, 1-6, second threaded hole, 1-7, through hole boss;

[0032] 2. Axial locking end cover, 2-1. Countersunk screw hole, 2-2. First conical pin, 2-3. First spring;

[0033] 3. Active rotating shaft, 3-1. Axial pin hole, 3-2. Connecting key, 3-3. Driving torsion spring, 3-4. Bidirectional elastic pin, 3-4-1. Second conical pin, 3-4-2. Second spring, 3-5. Torsion spring slot;

[0034] 4. Wing connector, 4-1. third threaded hole, 4-2. third spring, 4-3. connecting portion, 4-4. fan-shaped groove;

[0035] 5. Locking sleeve, 5-1 through hole boss;

[0036] 6. Passive rotating shaft, 6-1 boss slider;

[0037] 7. Sealing end cap; 8. Process cap. DETAILED DESCRIPTION

[0038] 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 only 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.

[0039] like Figure 1-8 As shown, the rotating shaft assembly includes a body connecting member 1, an axial locking end cover 2, an active rotating shaft 3, a wing connecting member 4, a locking sleeve 5, a passive rotating shaft 6, and a blocking end cover 7. The axial locking end cover 2 is fixedly connected to the top of the body connecting member 1 by bolts, the active rotating shaft 3 is sleeved and connected in the wing connecting member 4, one end of the locking sleeve 5 is sleeved and connected in the wing connecting member 4, and the other end is sleeved and connected in the body connecting member 1, and the wing connecting member 4 is fixedly connected to the wing of the aircraft. The blocking end cover 7 is fixedly connected to the bottom of the body connecting member 1 by bolts.

[0040] Specifically, Figure 2 As shown, the main body of the body connector 1 is a columnar structure. Four through-hole bosses 1-7 are arranged at intervals along the length direction on one side of the columnar structure. Through holes are arranged on the through-hole bosses 1-7. The through-hole bosses 1-7 are connected to the main body of the aircraft through bolts. A first sleeve, a second sleeve, and a third sleeve are arranged at intervals along the length direction on the other side of the columnar structure. The centers of the three sleeves are in the same straight line, and the line connecting the three centers is parallel to the columnar structure. A first threaded hole 1-1 is arranged on the top end face of the first sleeve. Fig. 9 As shown, the axial locking end cover 2 is a flange structure as a whole. The cylindrical sleeve of the flange structure is connected in the first sleeve. The countersunk screw passes through the countersunk screw hole 2-1 and then is screwed into the first threaded hole 1-1 to fix the flange plate to the top surface of the first sleeve. Thus, the axial locking end cover 2 is fixed to the first sleeve. Two circular holes are provided on the cylindrical end surface of the axial locking end cover 2, and the first spring 2-3 is provided in the circular hole. One end of the conical pin 2-2 is slidably sleeved and connected in the circular hole, and the other end extends out of the cylinder to contact one end surface of the active rotating shaft 3. The conical pin 2-2 is a cylindrical structure with one end closed, and the open end faces the circular hole on the end surface of the locking end cover 2. One end of the first spring 2-3 is connected to the bottom surface of the circular hole, and the other end is connected to the inner bottom surface of the circular hole of the conical pin 2-2. Two axial pin holes 3-1 are correspondingly provided on the end surface of the active rotating shaft 3. When the active rotating shaft 3 is rotated to the right position, under the elastic force of the first spring 2-3, the conical pin 2-2 extends into the axial pin hole 3-1 to lock the active rotating shaft 3.

[0041] A radial pin hole 1-3 and a process hole 1-4 are provided on both sides of the center of the second sleeve. The process hole 1-4 is located outside the radial pin hole 1-3, and the axis of the radial pin hole 1-3 coincides with the axis of the process hole 1-4. The process hole 1-4 is provided to eject the bidirectional elastic pin 3-4 through a fine needle after the active rotating main shaft 3 is locked, so as to realize repeated use of multiple locking. The bidirectional elastic pin 3-4 is provided in the pin hole on the active rotating shaft 3 and can slide and move in the pin hole. Specifically, as Figure 4 As shown, the bidirectional elastic pin 3-4 includes two sleeve-shaped second conical pins 3-4-1 with one end closed and a second spring 3-4-2. The two ends of the second spring 3-4-2 are respectively connected to the inner bottom surfaces of the two second conical pins 3-4-1. A second threaded hole 1-6 is provided on the bottom end surface of the third sleeve, and a blocking end cover 7 is fixedly connected to the bottom end surface of the third sleeve by bolts.

[0042] The active rotating main shaft 3 passes through the second sleeve, and the bidirectional elastic pin 3-4 is arranged at the overlapped position of the active rotating main shaft 3 and the second sleeve. One end of the active rotating main shaft 3 with the axial pin hole 3-1 extends into the first sleeve and is rotatably connected with the first sleeve.

[0043] like Figure 5-6 As shown, the wing connector 4 includes a fourth sleeve, a fifth sleeve, and a connecting portion 4-3. The fourth sleeve and the fifth sleeve are concentric and spaced apart, and both sleeves are connected to one side of the columnar structure, and the other side of the columnar structure is connected to four connecting portions 4-3. The connecting portion 4-3 is fixedly connected to the wing of the aircraft by bolts, whereby the wing connector 4 is fixedly connected to the wing of the aircraft. The active rotating shaft 3 is integrally arranged in the wing connector 4, one end of which is connected to the fourth sleeve, and the other end passes through the fifth sleeve and then extends into the first sleeve to contact the first conical pin 2-2. As shown Figure 3 As shown, the active rotating shaft 3 is provided with two connecting keys 3-2, which are engaged in the key slots of the fourth sleeve and the fifth sleeve, connecting the active rotating shaft 3 and the wing connecting member 4 together so that the two can rotate synchronously. Two driving torsion springs 3-3 are also provided on the active rotating shaft 3, one end of the driving torsion spring 3-3 is connected to the torsion spring engaging slot 3-5 on the active rotating shaft 3, and the other end is connected to the column structure of the body connecting member 1. The driving torsion spring 3-3 can make the active rotating shaft 3 rotate relative to the body connecting member 1, thereby driving the wing connecting member 4 to rotate relative to the body connecting member 1, completing the rotation, folding and unfolding action of the wing of the aircraft.

[0044] like Figure 7-8As shown, a third spring 4-2 is also provided in the fourth sleeve of the wing connector 4, one end of the third spring 4-2 is connected to the fourth sleeve, and the other end is pressed against one end face of the passive rotating shaft 6, and the passive rotating shaft 6 is entirely arranged in the fourth sleeve. The other end face of the passive rotating shaft 6 is pressed against one end face of the locking sleeve 5, and the other end of the locking sleeve 5 extends into the third sleeve of the body connector 1, and the bottom end face of the third sleeve is provided with a second threaded hole 1-6, and the blocking end cover 7 is fixedly connected to the bottom end of the third sleeve by bolts to block the locking sleeve 5. Thus, one end of the locking sleeve 5 is in the fourth sleeve of the wing connector 4 and can rotate relative to the fourth sleeve, and the other end is in the third sleeve of the body connector 1 and is fixedly connected to the body connector 1.

[0045] A boss slider 6-1 is provided along the length direction of the passive rotating shaft 6, and the boss slider 6-1 is a fan-shaped boss protruding from the side of the passive rotating shaft 6. The fourth sleeve is also provided with a fan-shaped groove 4-4 along the length direction of the axis. When the passive rotating shaft 6 is placed in the fourth sleeve, the boss slider 6-1 is clamped in the fan-shaped groove 4-4. Therefore, the passive rotating shaft 6 can rotate synchronously with the wing connecting member 4. A through-hole boss 5-1 is provided on the outer side of the locking sleeve 5. After the bolt passes through the through-hole boss 5-1, it is screwed with the threaded through hole 1-5 on the body connecting member 1, so that the locking sleeve 5 is fixedly connected to the body connecting member 1. A fan-shaped groove is also provided at the end of the locking sleeve 5 that contacts the passive rotating shaft 6, and the boss slider 6-1 can be clamped in the fan-shaped groove of the locking sleeve 5.

[0046] When the wing is in the initial folding state, the entire mechanism is in the cabin or the initial locking structure cannot be freely unfolded, the wing connector 4 and the body connector 1 are at an angle of 90°, and the third spring 4-2 is in a compressed state. At this time, the end face of the passive rotating shaft 6 is pressed against the end face of the locking sleeve 5, the second spring 3-4-2 is in a compressed state, the bidirectional elastic pin 3-4 is compressed in the active rotating shaft 3, the first spring 2-3 is in a compressed state, the first conical pin 2-2 is compressed in the axial locking end cover 2, and the driving torsion spring 3-3 is in a torsion state.

[0047] When the wing is unfolded, the active rotating shaft 3 rotates automatically under the elastic force of the driving torsion spring 3-3, and the active rotating shaft 3 drives the wing connecting member 4 to rotate, and the wing connecting member 4 drives the passive rotating shaft 6 to rotate, and of course, it also drives the wing to rotate and unfold. When the active rotating shaft 3 rotates to a suitable angle, the first conical pin 2-2 is aligned with the axial pin hole 3-1, and the first spring 2-3 pushes the first conical pin 2-2 into the axial pin hole 3-1, and the active rotating shaft 3 and the body connecting member 1 complete the first locking, that is, the wing connecting member 4 and the body connecting member 1 complete the first locking; at the same time, the bidirectional elastic pin 3-4 is aligned with the radial pin hole 1-3, and under the elastic force of the second spring 3-4-3, the bidirectional elastic pin 3-4 extends into the radial pin hole 1-3, and the active rotating shaft 3 and the body connecting member 1 complete the second locking, that is, the wing connecting member 4 completes the second locking with the body connecting member 1; at the same time, the boss slider 6-1 is aligned with the fan-shaped groove at the end of the locking sleeve 5, the third spring 4-2 is extended, pushing the passive rotating shaft 6 to move, and the boss slider 6-1 slides along the fan-shaped groove of the fourth sleeve, and a part of the boss slider 6-1 is stuck in the fan-shaped groove at the end of the locking sleeve 5, completing the clamping and locking of the passive rotating shaft 6 and the locking sleeve 5. Because a part of the boss slider 6-1 is also stuck in the fan-shaped groove of the fourth sleeve of the wing connecting member 4, the third locking of the wing connecting member 4 and the body connecting member 1 is also completed. In this embodiment, when the wing is folded, the angle between the wing connecting member 4 and the body connecting member 1 is 90°. Figure 1 When the wing is unfolded, the angle between the wing connector 4 and the fuselage connector 1 is 180°. Fig.10 To ensure the angle after unfolding, a stopper can be set on the wing connector 4, and when the wing connector 4 is rotated into place, the stopper abuts against the body connector 1 to complete the limit.

[0048] In addition, in order to facilitate the connection of the drive torsion spring 3-3 during the assembly process, a portion of the fourth sleeve and the fifth sleeve is cut off, and after the drive torsion spring 3-3 is installed, the missing portion is sealed with a process cover 8. In order to facilitate the installation of the locking sleeve 5, a notch needs to be cut in the third sleeve to facilitate the connection between the through-hole boss 5-1 and the threaded through hole 1-5. The rotating spindle 3 is assembled from the first sleeve. In order to facilitate the assembly of the rotating spindle 3, the inner walls of the first sleeve and the second sleeve need to be machined with a keyway 1-2 to facilitate the passage of the connection key 3-2.

[0049] The above are only preferred specific implementation modes 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 solutions and inventive concepts 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. A rotating shaft assembly of a folding tail wing including a multi-locking mechanism, characterized in that: The invention comprises a body connecting member (1), an axial locking end cover (2), an active rotating shaft (3), a wing connecting member (4), a locking sleeve (5), and a passive rotating shaft (6); the body connecting member (1) is fixedly connected to the aircraft body, the wing connecting member (4) is fixedly connected to the wing of the aircraft, the wing connecting member (4) is sleeved and connected to the outside of the active rotating shaft (3) and rotates synchronously with the active rotating shaft (3), the active rotating shaft (3) is rotatably connected to the body connecting member (1), and the wing connecting member (4) is locked to the passive rotating shaft (6). ) is also provided with a passive rotating shaft (6), which rotates synchronously with the wing connecting member (4) and can slide and move in the wing connecting member (4), and the locking sleeve (5) is fixedly connected to the body connecting member (1) and can automatically slide and engage with the passive rotating shaft (6); a driving torsion spring (3-3) is provided between the active rotating shaft (3) and the body connecting member (1), and when the wing is unfolded, the elastic force of the driving torsion spring (3-3) drives the active rotating shaft (3) to rotate, thereby driving the wing connecting member ( 4) rotation; the axial locking end cover (2) is fixedly connected to the body connecting piece (1); when the wing is unfolded, the axial locking end cover (2) is automatically locked with the active rotating shaft (3) through two first conical pins (2-2), so that the active rotating shaft (3) cannot rotate relative to the body connecting piece (1); a bidirectional elastic pin (3-4) is also provided between the active rotating shaft (3) and the body connecting piece (1); when the wing is unfolded, the bidirectional elastic pin (3-4) locks the active rotating shaft (3) and the body connecting piece (1) is automatically locked, so that the active rotating shaft (3) cannot rotate relative to the body connecting member (1); a third spring (4-2) is provided between the passive rotating shaft (6) and the wing connecting member (4); when the wing is unfolded, under the elastic force of the third spring (4-2), the passive rotating shaft (6) slides and moves and is locked with the locking sleeve (5), so that the passive rotating shaft (6) cannot rotate relative to the body connecting member (1), thereby preventing the wing connecting member (4) from rotating relative to the body connecting member (1).

2. A rotating shaft assembly of a folding tail wing comprising a multi-locking mechanism according to claim 1, characterized in that: The body connecting member (1) comprises a first sleeve, a second sleeve, and a third sleeve which are spaced apart and coaxially arranged, and also comprises a plurality of through-hole bosses (1-7); the three sleeves and the through-hole bosses (1-7) are fixedly connected to the two sides of the columnar structure; the through-hole bosses (1-7) are fixedly connected to the main body of the aircraft by bolts.

3. A rotating shaft assembly of a folding tail wing comprising a multi-locking mechanism according to claim 2, characterized in that: The wing connecting member (4) comprises a fourth sleeve and a fifth sleeve which are spaced apart and coaxially arranged, and also comprises a plurality of connecting parts (4-3). The two sleeves and the connecting parts (4-3) are fixedly connected to the two sides of the column, and the connecting parts (4-3) are fixedly connected to the wing of the aircraft by bolts; the fourth sleeve is arranged in the gap between the second sleeve and the third sleeve, and the fifth sleeve is arranged in the gap between the first sleeve and the second sleeve.

4. The rotating shaft assembly of a folding tail wing comprising a multi-locking mechanism according to claim 3, characterized in that: Two connecting keys (3-2) are provided on the active rotating shaft (3); one end of the active rotating shaft (3) extends into the fourth sleeve, and the other end passes through the fifth sleeve and then extends into the first sleeve and is rotatably connected to the first sleeve; the two connecting keys (3-2) are respectively connected to the fourth sleeve and the fifth sleeve.

5. The rotating shaft assembly of a folding tail wing comprising a multi-locking mechanism according to claim 3, characterized in that: The third spring (4-2) is arranged in the fourth sleeve, one end of which is connected to the fourth sleeve and the other end of which is in contact with the end surface of the passive rotating shaft (6).

6. The rotating shaft assembly of a folding tail wing comprising a multi-locking mechanism according to claim 3, characterized in that: A boss slide block (6-1) is provided on the side surface of the passive rotating shaft (6) along the length direction. The boss slide block (6-1) is a fan-shaped protrusion. The fan-shaped angle is consistent with the rotation angle during the wing expansion process. The boss slide block (6-1) is clamped in the fan-shaped groove (4-4) of the fourth sleeve and can slide and move along the fan-shaped groove (4-4).

7. A rotating shaft assembly of a folding tail wing comprising a multi-locking mechanism according to claim 6, characterized in that: The outer wall of one end of the locking sleeve (5) is provided with a through hole boss (5-1), the through hole boss (5-1) is fixedly connected to the machine body connecting piece (1), and the other end extends into the fourth sleeve and is provided with a fan-shaped groove matched with the boss slider (6-1) at the end.

8. The rotating shaft assembly of a folding tail wing comprising a multi-locking mechanism according to claim 3, characterized in that: The bidirectional elastic pin (3-4) comprises a second spring (3-4-2) and two second conical pins (3-4-1); the second conical pin (3-4-1) is a cylindrical structure with one end closed; the open ends of the two second conical pins (3-4-1) are arranged facing each other; and the two ends of the second spring (3-4-2) are respectively connected to the inner bottom surfaces of the two second conical pins (3-4-1).

9. The rotating shaft assembly of a folding tail wing comprising a multi-locking mechanism according to claim 1, characterized in that: The first conical pin (2-2) is a sleeve with one end closed. A guide hole is provided on the end surface of the axial locking end cover (2). The open end of the first conical pin (2-2) extends into the guide hole and can slide in the guide hole. A first spring (2-3) is provided in the guide hole. One end of the first spring (2-3) is connected to the bottom surface of the guide hole, and the other end is connected to the inner bottom surface of the first conical pin (2-2).

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