A rotating shaft assembly for a folding tail wing comprising a plurality of locking mechanisms

Abstract

The application discloses a rotating shaft assembly of a folding tail wing comprising a plurality of locking mechanisms and relates to the technical field of unmanned aerial vehicles. The rotating shaft assembly comprises a body connecting piece, an axial locking end cover, a driving rotating shaft, a wing connecting piece, a locking sleeve and a passive rotating shaft. The wing connecting piece rotates synchronously with the driving rotating shaft, the passive rotating shaft rotates synchronously with the wing connecting piece and can slide and move in the wing connecting piece, and the locking sleeve is fixedly connected with the body connecting piece and can be automatically slidably connected with the passive rotating shaft. A driving torsional spring between the driving rotating shaft and the body connecting piece drives the wing connecting piece to rotate. The axial locking end cover completes primary locking of the driving rotating shaft through a first conical pin, the driving rotating shaft completes secondary locking with the body connecting piece through a bidirectional elastic pin, and the passive rotating shaft and the body connecting piece complete tertiary locking through a fan-shaped boss. The application has a simple structure, improves the stability of locking after the wing is unfolded to a position through three times of locking, and makes the locking reliability index meet the requirements.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of unmanned aerial vehicle, more particularly, relates to a rotatable shaft assembly of a deployable folding tail wing containing multiple locking modes for aircraft or flight rudder. BACKGROUND

[0002] In the field of unmanned aerial vehicle, aircrafts containing foldable wings are widely used. The foldable wings change the wing shape under different flight environments to complete specific flight tasks. In order to improve the flight distance of the unmanned aerial vehicle, the stability of the folding wing deployment becomes a key influencing factor.

[0003] In addition, in the conventional unmanned aerial vehicle wing folding and unfolding mechanism, the locking of the wing after deployment is generally achieved by using axial or longitudinal locking pins, which has a complex structure. Due to high-frequency vibration 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 conventional unmanned aerial vehicle wing folding and unfolding mechanism, a single locking mechanism is generally provided. The continuous vibration during the flight of the aircraft will accelerate the fatigue and wear of the locking mechanism and the surrounding structure, shorten the service life of the aircraft, and even cause structural damage during flight.

[0005] The sudden failure of the locking mechanism during flight will cause the wing to be unexpectedly retracted or loose, which will affect the execution of the aircraft's mission, and in serious cases, the aircraft will lose lift and crash. SUMMARY

[0006] The technical problem to be solved by the present application is to provide a folding tail wing rotatable shaft assembly containing multiple locking mechanisms, which has a simple structure and improves the stability of the wing deployment after three times of locking, so that the locking reliability index meets the requirements.

[0007] To solve the above technical problems, the technical scheme adopted by the present application is: a rotating shaft assembly of a folding tail wing comprising a plurality of locking mechanisms, comprising a body connecting piece, an axial locking end cover, a driving rotating shaft, a wing connecting piece, a locking sleeve and a passive rotating shaft; the body connecting piece is fixedly connected to the main body of an aircraft, the wing connecting piece is fixedly connected to the wing of the aircraft, the wing connecting piece is sleeved outside the driving rotating shaft and rotates synchronously with the driving rotating shaft, the driving rotating shaft is rotationally connected to the body connecting piece, and the passive rotating shaft is further arranged in the wing connecting piece and rotates synchronously with the wing connecting piece and can axially slide in the wing connecting piece; the locking sleeve is fixedly connected to the body connecting piece and can be automatically slidably connected with the passive rotating shaft; a driving torsional spring is arranged between the driving rotating shaft and the body connecting piece, and when the wing is unfolded, the elastic force of the driving torsional spring drives the driving 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 by two first conical pins and pin holes of the driving rotating shaft, so that the driving rotating shaft cannot rotate relative to the body connecting piece; a bidirectional elastic pin is further arranged between the driving rotating shaft and the body connecting piece, and when the wing is unfolded, the bidirectional elastic pin automatically locks the driving rotating shaft and the body connecting piece, so that the driving rotating shaft cannot rotate relative to the body connecting piece; a third spring is arranged axially between the passive rotating shaft and the wing connecting piece, and when the wing is unfolded, the passive rotating shaft slides under the elastic force of the third spring and is connected and 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 piece comprises a first sleeve, a second sleeve and a third sleeve arranged at intervals and coaxially, and a plurality of through-hole bosses, the three sleeves and the through-hole bosses being fixedly connected to the two sides of the columnar structure, and the through-hole bosses being fixedly connected to the main body of the aircraft by bolts.

[0009] Preferably, the wing connecting piece comprises a fourth sleeve and a fifth sleeve arranged at intervals and coaxially, and a plurality of connecting parts, the two sleeves and the connecting parts being fixedly connected to the two sides of the column, and the connecting parts being 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.

[0010] Preferably, the driving rotating shaft is provided with two connecting keys, one end of the driving rotating shaft extends into the fourth sleeve, the other end extends into the first sleeve through the fifth sleeve and is rotationally connected with the first sleeve, and the two connecting keys are connected with the fourth sleeve and the fifth sleeve respectively.

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

[0012] Preferably, the side surface of the passive rotating shaft is provided with a boss slider in the length direction, the boss slider is a fan-shaped protrusion, the angle of the fan shape is consistent with the rotation angle in the wing unfolding 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 with the body connector, the other end extends into the fourth sleeve and is provided with a fan-shaped groove at the end which is matched with the boss slider.

[0014] Preferably, the bidirectional elastic pin comprises a second spring and two second conical pins, the second conical pin is a closed cylindrical structure at one end, the opening ends of the two second conical pins are oppositely arranged, and the two ends of the second spring are respectively connected with the inner bottom surfaces of the two second conical pins.

[0015] Preferably, the first conical pin is a sleeve closed at one end, a guide hole is arranged on the end face of the axial locking end cover, the opening end of the first conical pin extends into the guide hole and can slide in the guide hole, a first spring is arranged in the guide hole, one end of the first spring is connected with the bottom surface of the guide hole, and the other end is connected with 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 hole, and when the conical pin is inserted into the corresponding pin hole, a self-locking effect can be generated.

[0017] The beneficial effects generated by the above technical scheme are that:

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

[0019] 2. The present application can modularize the shaft through the sleeve assembly shaft system, can be flexibly adjusted, and is convenient for use in different use scenarios.

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

[0021] Figure 1 is a structural schematic view when the wing is unfolded;

[0022] Figure 2 is a structural schematic view of the body connector;

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

[0024] Figure 4is the schematic diagram of the explosion structure of the bidirectional elastic pin;

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

[0026] Figure 6 is the schematic diagram of the structure of the wing connector;

[0027] Figure 7 is the schematic diagram of the explosion of the passive rotating shaft and the locking sleeve, the wing connector;

[0028] Figure 8 is the schematic diagram of the structure of the passive rotating shaft, the locking sleeve, the third spring assembled in the wing connector;

[0029] Figure 9 is the schematic diagram of the structure of the axial locking end cover;

[0030] Figure 10 is the schematic diagram of the structure when the wing is folded;

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

[0032] 2, the axial locking end cover, 2-1, the countersunk screw hole, 2-2, the first conical pin, 2-3, the first spring;

[0033] 3, the active rotating shaft, 3-1, the axial pin hole, 3-2, the connecting key, 3-3, the driving torsional spring, 3-4, the bidirectional elastic pin, 3-4-1, the second conical pin, 3-4-2, the second spring, 3-5, the torsional spring clamping groove;

[0034] 4, the wing connector, 4-1, the third threaded hole, 4-2, the third spring, 4-3, the connecting part, 4-4, the fan-shaped recess;

[0035] 5, the locking sleeve, 5-1 through hole boss;

[0036] 6, the passive rotating shaft, 6-1 boss slider;

[0037] 7, the plugging end cover; 8, the process cover. DETAILED DESCRIPTION

[0038] With reference to the drawings of the embodiments of the present application, the technical solutions in the embodiments of the present application will be clearly and completely described. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments of the present application, all the other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application.

[0039] As shown in Figures 1-8 , the rotating shaft assembly comprises a body connecting piece 1, an axial locking end cover 2, a driving rotating shaft 3, a wing connecting piece 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 piece 1 by bolts. The driving rotating shaft 3 is sleeved and connected in the wing connecting piece 4. One end of the locking sleeve 5 is sleeved and connected in the wing connecting piece 4, and the other end is sleeved and connected in the body connecting piece 1. The wing connecting piece 4 is fixedly connected to the upper surface of the wing of the aircraft. The blocking end cover 7 is fixedly connected to the bottom of the body connecting piece 1 by bolts.

[0040] Specifically, as shown in Figure 2 , the main body of the body connecting piece 1 is a columnar structure. Four through-hole bosses 1-7 are arranged on one side of the columnar structure along the length direction at intervals. The through-hole bosses 1-7 are provided with through holes, and the through-hole bosses 1-7 are connected to the main body of the aircraft by bolts. A first sleeve, a second sleeve, and a third sleeve are arranged on the other side of the columnar structure along the length direction at intervals. The centers of the three sleeves are on the same straight line, and the connecting line of 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. As shown in Figure 9 , 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. After the countersunk screw passes through the countersunk screw hole 2-1, the flange is fixedly connected to the top surface of the first sleeve by rotating and connecting the first threaded hole 1-1, so that the axial locking end cover 2 is fixed on the first sleeve. Two round holes are arranged on the cylindrical end face of the axial locking end cover 2, and a first spring 2-3 is arranged in the round hole. A conical pin 2-2 is sleeved and connected in the round hole with one end sliding, and the other end protrudes from the cylinder and contacts the end face of the driving rotating shaft 3. The conical pin 2-2 is a cylindrical structure with one end closed, and the open end faces the round hole of the end face of the locking end cover 2. One end of the first spring 2-3 is connected to the bottom surface of the round hole, and the other end is connected to the inner bottom surface of the round hole of the conical pin 2-2. Two axial pin holes 3-1 are correspondingly arranged on the end face of the driving rotating shaft 3. When the driving rotating shaft 3 is rotated in place, the conical pin 2-2 is inserted into the axial pin hole 3-1 under the elastic force of the first spring 2-3 to lock the driving rotating shaft 3.

[0041] The second sleeve is provided with a radial pin hole 1-3 and a process hole 1-4 on both sides of the center, and 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 process hole 1-4. The process hole 1-4 is used to pop out the bidirectional elastic pin 3-4 through the fine needle after the driving rotation shaft 3 is locked, so as to realize the repeated use of multiple locking. The bidirectional elastic pin 3-4 is arranged in the pin hole on the driving rotation shaft 3 and can slide in the pin hole. Specifically, as shown in Figure 4 , the bidirectional elastic pin 3-4 includes two sleeve-shaped second conical pins 3-4-1 with one end closed and one second spring 3-4-2. The two ends of the second spring 3-4-2 are connected to the inner bottom surfaces of the two second conical pins 3-4-1 respectively. The third sleeve is provided with a second threaded hole 1-6 at the bottom end face, and the end cover 7 is fixedly connected to the bottom end face of the third sleeve by bolts.

[0042] The driving rotation shaft 3 passes through the second sleeve, and the bidirectional elastic pin 3-4 is arranged at the coincidence position of the driving rotation shaft 3 and the second sleeve. The driving rotation shaft 3 is provided with an axial pin hole 3-1 at one end, which extends into the first sleeve and is rotatably connected with the first sleeve.

[0043] As shown in Figures 5-6 , the wing connecting piece 4 includes a fourth sleeve, a fifth sleeve, and a connecting part 4-3. The fourth sleeve and the fifth sleeve are concentrically 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 parts 4-3. The connecting part 4-3 is fixedly connected to the wing of the aircraft by bolts, so that the wing connecting piece 4 is fixedly connected to the wing of the aircraft. The driving rotation shaft 3 is arranged in the wing connecting piece 4, one end of which is connected to the fourth sleeve, and the other end extends into the first sleeve through the fifth sleeve and contacts the first conical pin 2-2. As shown in Figure 3 , the driving rotation shaft 3 is provided with two connecting keys 3-2, which are clamped in the key grooves of the fourth sleeve and the fifth sleeve, so as to connect the driving rotation shaft 3 and the wing connecting piece 4 together, so that they can rotate synchronously. The driving torsional spring 3-3 is arranged on the driving rotation shaft 3, one end of the driving torsional spring 3-3 is connected to the torsional spring clamping groove 3-5 on the driving rotation shaft 3, and the other end is connected to the columnar structure of the body connecting piece 1. The driving torsional spring 3-3 can rotate the driving rotation shaft 3 relative to the body connecting piece 1, so as to drive the wing connecting piece 4 to rotate relative to the body connecting piece 1, thereby completing the rotating folding and unfolding action of the wing of the aircraft.

[0044] As shown in Figures 7-8As shown, the fourth sleeve of the wing connecting member 4 is further provided with a third spring 4-2, one end of the third spring 4-2 is connected to the fourth sleeve, and the other end is abutted against one end face of the passive rotating shaft 6 which is arranged in the fourth sleeve as a whole. The other end face of the passive rotating shaft 6 is abutted against one end face of the locking sleeve 5, the other end of the locking sleeve 5 extends into the third sleeve of the body connecting member 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 connecting member 4 and can rotate relative to the fourth sleeve, and the other end is in the third sleeve of the body connecting member 1 and is fixedly connected to the body connecting member 1.

[0045] A boss slider 6-1 is arranged 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 face of the passive rotating shaft 6. The fourth sleeve is further provided with a fan-shaped groove 4-4 along the length direction of the axis, and 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. Thus, the passive rotating shaft 6 can rotate synchronously with the wing connecting member 4. The outer side face of the locking sleeve 5 is provided with a through-hole boss 5-1, and the bolt is screwed with the threaded through-hole 1-5 on the body connecting member 1 after passing through the through-hole boss 5-1, so that the locking sleeve 5 is fixedly connected to the body connecting member 1. The end of the locking sleeve 5 in contact with the passive rotating shaft 6 is also provided with a fan-shaped groove, 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 cannot be freely unfolded in the cabin or in the initial locking structure, the wing connecting member 4 and the body connecting member 1 form a 90° angle, the third spring 4-2 is in a compressed state, the end face of the passive rotating shaft 6 is abutted together with 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 driving 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 torsional spring 3-3 is in a torsional state.

[0047] When the wing is unfolded, the main rotating shaft 3 is automatically rotated under the elastic force of the driving torsion spring 3-3, the main rotating shaft 3 drives the wing connecting piece 4 to rotate, the wing connecting piece 4 drives the passive rotating shaft 6 to rotate, of course, the wing is also rotated and unfolded. When the main rotating shaft 3 rotates to a proper angle, the first conical pin 2-2 is aligned with the axial pin hole 3-1, the first spring 2-3 pushes the first conical pin 2-2 into the axial pin hole 3-1, the main rotating shaft 3 and the body connecting piece 1 complete the first locking, that is, the wing connecting piece 4 and the body connecting piece 1 complete the first locking; at the same time, the bidirectional elastic pin 3-4 is aligned with the radial pin hole 1-3, 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, the main rotating shaft 3 and the body connecting piece 1 complete the second locking, that is, the wing connecting piece 4 and the body connecting piece 1 complete the second locking; 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 elongated, the passive rotating shaft 6 is driven to move, the boss slider 6-1 slides along the fan-shaped groove of the fourth sleeve, a part of the boss slider 6-1 is clamped into the fan-shaped groove at the end of the locking sleeve 5, the clamping and locking of the passive rotating shaft 6 and the locking sleeve 5 is completed, because a part of the boss slider 6-1 is also clamped in the fan-shaped groove of the fourth sleeve of the wing connecting piece 4, so the third locking of the wing connecting piece 4 and the body connecting piece 1 is also completed. In the embodiment, the angle between the wing connecting piece 4 and the body connecting piece 1 is 90° when the wing is folded, as shown in Figure 1 The angle between the wing connecting piece 4 and the body connecting piece 1 is 180° when the wing is unfolded, as shown in Figure 10 To ensure the angle after unfolding, a stopper can be arranged on the wing connecting piece 4, and the stopper is abutted against the body connecting piece 1 to complete the limiting when the wing connecting piece 4 rotates to the position.

[0048] In addition, in order to facilitate the connection of the driving torsion spring 3-3 in the assembly process, the fourth sleeve and the fifth sleeve are both cut by a part, and the missing part is blocked by the process cover 8 after the driving torsion spring 3-3 is installed. In order to facilitate the installation of the locking sleeve 5, the third sleeve needs to be cut a notch to facilitate the connection of the through-hole boss 5-1 and the threaded through-hole 1-5. When the rotating shaft 3 is assembled, it is inserted from the first sleeve, and in order to facilitate the assembly of the rotating shaft 3, the inner walls of the first sleeve and the second sleeve are both processed with key grooves 1-2 to facilitate the connection of the key 3-2.

[0049] The above is only a preferred specific embodiment of the present application, but the protection scope of the present application is not limited to this, any person skilled in the art can make equivalent replacement or change according to the technical scheme and the inventive concept of the present application within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

Claims

1. A rotating shaft assembly for a folding tail fin including multiple locking mechanisms, characterized in that, The components include a fuselage connector (1), an axial locking end cap (2), an active rotating shaft (3), a wing connector (4), a locking sleeve (5), and a passive rotating shaft (6). The fuselage connector (1) is fixedly connected to the main body of the aircraft, and the wing connector (4) is fixedly connected to the wings of the aircraft. The wing connector (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 fuselage connector (1), and the wing connector (4) is connected to the wing connector (6). The interior is also equipped with a passive rotating shaft (6), which rotates synchronously with the wing connector (4) and can slide within the wing connector (4). The locking sleeve (5) is fixedly connected to the fuselage connector (1) and can automatically slide and engage with the passive rotating shaft (6). A drive torsion spring (3-3) is provided between the active rotating shaft (3) and the fuselage connector (1). When the wing is deployed, the elastic force of the drive torsion spring (3-3) drives the active rotating shaft (3) to rotate, thereby driving the wing connector (4) to rotate. 4) Rotation; The axial locking end cap (2) is fixedly connected to the fuselage connector (1). When the wing is deployed, the axial locking end cap (2) is automatically locked to the active rotating shaft (3) by two first conical pins (2-2), so that the active rotating shaft (3) cannot rotate relative to the fuselage connector (1); A bidirectional elastic pin (3-4) is also provided between the active rotating shaft (3) and the fuselage connector (1). When the wing is deployed, the bidirectional elastic pin (3-4) will connect the active rotating shaft (3) to the fuselage connector. (1) Automatic locking prevents the active rotating shaft (3) from rotating relative to the fuselage connector (1); a third spring (4-2) is provided between the passive rotating shaft (6) and the wing connector (4). When the wing is deployed, the passive rotating shaft (6) slides and moves under the elastic force of the third spring (4-2) and locks with the locking sleeve (5), preventing the passive rotating shaft (6) from rotating relative to the fuselage connector (1), thereby preventing the wing connector (4) from rotating relative to the fuselage connector (1).

2. The rotating shaft assembly of a folding tail fin including multiple locking mechanisms according to claim 1, characterized in that, The body connector (1) includes a first sleeve, a second sleeve, and a third sleeve arranged at intervals and coaxially, and also includes several through-hole bosses (1-7). The three sleeves and the through-hole bosses (1-7) are fixedly connected to both sides of the columnar structure, and the through-hole bosses (1-7) are fixedly connected to the main body of the aircraft by bolts.

3. A rotating shaft assembly for a folding tail fin including multiple locking mechanisms according to claim 2, characterized in that, The wing connector (4) includes a fourth sleeve and a fifth sleeve arranged at intervals and coaxially, and also includes several connecting parts (4-3). The two sleeves and the connecting parts (4-3) are fixedly connected to both sides of the column. The connecting parts (4-3) are fixedly connected to the wing of the aircraft by bolts. The fourth sleeve is located in the gap between the second sleeve and the third sleeve, and the fifth sleeve is located in the gap between the first sleeve and the second sleeve.

4. A rotating shaft assembly for a folding tail fin including multiple locking mechanisms according to claim 3, characterized in that, The active rotating shaft (3) is provided with two connecting keys (3-2). One end of the active rotating shaft (3) extends into the fourth sleeve, and the other end passes through the fifth sleeve and extends into the first sleeve and is rotatably connected to the first sleeve. The two connecting keys (3-2) are connected to the fourth sleeve and the fifth sleeve respectively.

5. A rotating shaft assembly for a folding tail fin including multiple locking mechanisms according to claim 3, characterized in that, The third spring (4-2) is located inside the fourth sleeve, with one end connected to the fourth sleeve and the other end in contact with the end face of the passive rotating shaft (6).

6. A rotating shaft assembly for a folding tail fin including multiple locking mechanisms according to claim 3, characterized in that, The passive rotating shaft (6) has a boss slider (6-1) on its side along the length direction. The boss slider (6-1) is a fan-shaped protrusion. The angle of the fan shape is consistent with the rotation angle during the wing deployment process. The boss slider (6-1) is engaged in the fan-shaped groove (4-4) of the fourth sleeve and can slide along the fan-shaped groove (4-4).

7. A rotating shaft assembly for a folding tail fin including multiple locking mechanisms according to claim 6, characterized in that, The outer side wall of one end of the locking sleeve (5) is provided with a through hole boss (5-1), which is fixedly connected to the body connector (1). The other end extends into the fourth sleeve and is provided with a fan-shaped groove at the end that is compatible with the boss slider (6-1).

8. A rotating shaft assembly for a folding tail fin including multiple locking mechanisms according to claim 3, characterized in that, The bidirectional elastic pin (3-4) includes 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. 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. A rotating shaft assembly for a folding tail fin including multiple locking mechanisms 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 face 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 within 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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