CN114906315A - Detachable mounting structure for propulsion propeller - Google Patents

Abstract

The invention discloses a detachable mounting structure for a propulsion propeller, wherein the propulsion propeller is arranged at the tail end of the tail part of a body of an airplane, the detachable mounting structure comprises a jaw mechanism fixedly connected with a propulsion motor for driving the propulsion propeller and a flange part fixedly connected with the body, and the jaw mechanism is clamped with the flange part through a plurality of jaws which are driven to open and close by a handle. The detachable mounting structure for the propulsion propeller is clamped with the flange piece in the machine body by the jaw mechanism, can realize tool-free disassembly and assembly, is convenient to operate, can meet the requirement of frequent inspection or replacement of the propulsion motor, and improves the safety of an airplane.

Description

Detachable mounting structure for propulsion propeller

Technical Field

The invention relates to an aircraft with an electric propulsion propeller, in particular to a detachable mounting structure for the propulsion propeller.

Background

With the increasing requirements on energy conservation and environmental protection, the electric airplane is gradually approved. Most of the existing electric propulsion airplanes are multi-rotor electric unmanned planes, and are widely applied to tasks of agricultural plant protection, forest fire monitoring, aerial photography, land measurement, post-disaster loss assessment and the like. But the ubiquitous load level of current many rotors electric unmanned aerial vehicle is low, and the unreasonable shortcoming of structural layout is difficult to exert unmanned aerial vehicle's control and safety advantage.

With the development of battery technology, electrically propelled screw aircraft increasingly have the ability to be applied to passenger aircraft. However, the requirement for the motor is further improved when the unmanned aerial vehicle is converted into the passenger aircraft, and particularly under the high reliability requirement of the passenger aircraft, the passenger aircraft needs to frequently test and overhaul the motor.

For example, CN 107672799 a discloses an electric unmanned aerial vehicle, which includes a body, two landing gears, and eight motors supported by eight cantilevers connected to the body. In order to reduce the transportation volume, the cantilever of the electric unmanned aerial vehicle in the prior art adopts a folding structure. Therefore, if the cantilever of the electric unmanned aerial vehicle and the motor supported on the cantilever are applied to a passenger traffic scene, the motor needs to be checked or replaced very frequently, and the whole cantilever is detached to be a troublesome thing. In addition, the aircraft adopts a non-conventional layout, has a complex aerodynamic structure and is very limited in reliability. Therefore, in the practical application process, further improvement and improvement are needed on the basis of the method, so that the method can be applied to real passenger traffic scenes.

Disclosure of Invention

The technical problem underlying the present invention is to provide a detachable mounting structure for a propulsion propeller that reduces or avoids the aforementioned problems.

In order to solve the technical problem, the invention provides a detachable mounting structure for a propulsion propeller, wherein the propulsion propeller is arranged at the tail end of the tail part of a body of an airplane, the detachable mounting structure comprises a jaw mechanism fixedly connected with a propulsion motor for driving the propulsion propeller and a flange piece fixedly connected with the body, and the jaw mechanism is clamped with the flange piece through a plurality of jaws driven by a handle to open and close.

Preferably, the flange member is fixed inside a hole at the tail end of the tail part of the body, the flange member is provided with a small-diameter part facing the inside of the hole and fixedly connected with the body, and a large-diameter part facing the outside of the hole, and a clamping space for accommodating the tail end of the clamping jaw is formed between the large-diameter part and the bottom and the side wall of the hole; the tail ends of the clamping jaws can be clamped on the inner side of the large-diameter part in an opening and closing mode.

Preferably, a locking part connected with the handle is formed on the body.

Preferably, a guide part is formed on the inner side wall of the hole, and a guide matching structure matched with the guide part is formed on the outer side wall of the jaw mechanism.

Preferably, the jaw mechanism comprises a cylindrical base and a cylindrical turntable arranged in the cylindrical base, and a hollow rotating shaft is arranged in the center of the cylindrical base; the handle is fixedly connected with the cylindrical turntable; the drive handle can drive the cylindrical turntable to rotate around the hollow rotating shaft.

Preferably, a plurality of guide strips facing the central axis of the cylindrical base are formed on the inner side wall of the cylindrical base at equal intervals, a first long slot hole extending along the radiation direction facing the central axis of the cylindrical base is formed on each guide strip, and a second long slot hole corresponding to the first long slot hole is formed at the bottom of the cylindrical base; a connecting rod through hole for a claw connecting rod hinged at the bottom of each claw to pass through is formed on the side wall of the cylindrical base between the first long slotted hole and the second long slotted hole and corresponds to each claw; a handle through hole for the handle to pass through is formed on the side wall of the cylindrical base; the outer side wall of the cylindrical base above the connecting rod through hole is provided with a jaw lug, and the middle part of the jaw is rotatably hinged on the jaw lug.

Preferably, a plurality of pairs of outwardly extending rotating arms are formed on the cylindrical turntable corresponding to each clamping jaw, each pair of rotating arms is arranged at intervals up and down and is provided with a third long slotted hole which is vertically aligned, and the length direction of the third long slotted hole has an included angle which is larger than 0 degree and smaller than 90 degrees with the radial direction of the central shaft facing the cylindrical base.

Preferably, a sleeve is arranged between a pair of rotating arms arranged at intervals up and down, a core shaft penetrates through the center of the sleeve, and the core shaft penetrates through the corresponding third long slotted hole, the first long slotted hole and the second long slotted hole; the tail end of the claw connecting rod is hinged to the outer side of the sleeve.

Preferably, a return spring is arranged between the clamping jaw and the outer side wall of the cylindrical base, and the return spring enables the tail end of the clamping jaw to be propped against the middle to be folded.

Preferably, a snap ring for pressing the cylindrical turntable is arranged above the hollow rotating shaft; the claw mechanism is fixedly connected with the propelling motor through a switching disk.

The detachable mounting structure for the propulsion propeller is clamped with the flange piece in the machine body by the jaw mechanism, can realize tool-free disassembly and assembly, is convenient to operate, can meet the requirement of frequent inspection or replacement of the propulsion motor, and improves the safety of an airplane.

Drawings

The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention.

Fig. 1 is a perspective view of a vertical takeoff and landing aircraft according to an embodiment of the present invention.

Fig. 2 shows an exploded view of a detachable mounting arrangement for a propulsion propeller according to an embodiment of the invention.

Figure 3 shows an exploded perspective view of a fuselage and flange member according to an embodiment of the invention.

Figure 4 shows an exploded cross-sectional view of a jaw mechanism and body according to one embodiment of the present invention.

Fig. 5 is an exploded view schematically showing a detachable mounting structure for a propulsion propeller according to another embodiment of the present invention.

Figure 6 is a perspective view of a jaw mechanism according to yet another embodiment of the present invention in an exploded configuration.

Fig. 7 is a perspective view of a jaw mechanism according to yet another embodiment of the present invention in an exploded state.

Detailed Description

In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.

As shown in fig. 1, the present invention provides a vertical take-off and landing aircraft using a conventional upper single wing layout, including wings 2 disposed above a fuselage 1, a propeller 3 located at the tail end of the fuselage 1, horizontal stabilizers 4 disposed at both sides of the tail of the fuselage 1, and a landing gear 5 located below the fuselage 1. The airplane of the invention adopts the conventional layout, can take off in a sliding way like a common airplane, and has the advantages of simple structure and mature and reliable technology. The rear propulsion propeller has low noise and good riding experience, and is suitable for the passenger transport field.

In order to realize short-distance or vertical take-off and landing, the lower parts of wings 2 positioned at two sides of a fuselage 1 of the airplane are respectively connected with a supporting beam 6 extending parallel to the axial direction of the fuselage 1, the front end and the rear end of the supporting beam 6 are respectively provided with an electric engine room 7, and a pair of coaxial counter-propeller lift propellers 8 are arranged on the electric engine rooms 7. Although the lift force propeller has more than eight, only four electric engine rooms 7 are needed, namely only four lift force motors are needed, and compared with a structure that one propeller is driven by a single motor, the lift force propeller is lighter in weight and higher in take-off and landing efficiency. Similarly, because the aircraft of the invention adopts a conventional structural layout, the lift propellers 8 only play a role in taking off and landing, and the eight lift propellers 8 do not work in flat flight, thereby avoiding the problem of wing tip stall.

It should be noted that the motors have the advantages of light weight, smooth operation and easy control compared with the fuel engine, but the precondition is to reduce the number of the motors as much as possible under the condition of equivalent lift force, and the technical effect of the fuel engine can be achieved without infinitely overlapping the number of the motors. Therefore, as for the airplane with higher requirements on economy and reliability, the design of the invention for optimizing the number, the layout and the light weight of the lift motors is more optimized, and compared with the unexpected idea in the prior art, the invention can obtain economic benefit and reliability more suitable for passenger transportation.

Further, in order to allow the airplane to take off and land in a conventional taxi and fly in a normal plane, the horizontal rear wing 4 of the airplane of the present invention is provided with a wing tip beam 41, and the outer side of the wing tip beam 41 is provided with a yawing wing surface 42 extending obliquely upward and obliquely downward, respectively. At least one of the yaw airfoils 42 is an airfoil or a full motion airfoil having a control surface for facilitating normal operation of the aircraft for yaw heading.

The horizontal rear wing 4 of the present invention, as a conventional layout type of airplane, mainly provides a stabilizing moment and a pitching moment, so that the size of the horizontal rear wing 4 is much smaller than that of the wing 2, and a great structural strength is not originally required. In order to be able to provide the yawing surfaces 42 at the tip part of the horizontal rear wing 4 (since the propulsion propeller 3 is provided at the end of the tail part of the fuselage 1, it is difficult to provide a conventional vertical rear wing at the tail part of the fuselage 1, and it affects the propulsion efficiency of the propulsion propeller 3, and therefore, it is preferable to provide the yawing surfaces 42 at the tip part of the horizontal rear wing 4, the present invention provides a tip beam 41 at the tip part of the horizontal rear wing 4 for structural reinforcement of the relatively weak tip part to take over the additional structural stress of the yawing surfaces 42 after the position improvement.

As described above, the pair of lift propellers 8 are provided in front and behind the support beam 6 connected to the lower part of the wing 2, and the lift propellers 8 are not operated during the flat flight, but the profile of the lift propellers 8 protruding during the high-speed flight is greatly damaged to the flow field, so that the tip of the support beam 6 is required to receive a very large aerodynamic shock, and the amplitude of twist during the flat flight is also large. In order to reduce the vibration of the support beams 6, in the illustrated embodiment, it is possible to attach the ends of the lift support beams 6 to the tip beams 41 of the horizontal rear wing 4, with the tip beams 41 reinforcing the yawing airfoils 42 providing additional support to the lift support beams 6.

As described above, in the case of the propulsion propeller 3 having a main propulsion function, which requires a relatively large power motor for driving, it is necessary to frequently check or replace the motor in order to increase the safety factor, and thus the present invention provides a detachable mounting structure for the propulsion propeller 3 for conveniently detaching or mounting the propulsion propeller 3 and the motor thereof from or on the body 1.

Fig. 2 shows an exploded view of a detachable mounting structure for a propulsion propeller according to an embodiment of the present invention, as shown, the detachable mounting structure of the present invention includes a jaw mechanism 60 fixedly connected to a propulsion motor 31 driving a propulsion propeller 3 and a flange member 70 fixedly connected to a body 1, and the jaw mechanism 60 is engaged with the flange member 70 by a plurality of jaws 81 driven to open and close by a handle 80, which will be described in further detail later.

FIG. 3 shows an exploded perspective view of the fuselage and flange member; figure 4 shows an exploded cross-sectional view of the jaw mechanism and body. As shown in the figures, the flange member 70 is fixed inside a hole 11 at the tail end of the fuselage 1, the flange member 70 has a small diameter part 71 facing the inside of the hole 11 and fixedly connected with the fuselage 1, and a large diameter part 72 facing the outside of the hole 11, and a clamping space 73 for accommodating the tail end of the claw 81 is formed between the large diameter part 72 and the bottom and the side wall of the hole 11; the end of the claw 81 is connected to the inside of the large diameter portion 72 in an openable and closable manner.

Since the opening and closing of the jaws 81 is driven by the handle 80, the handle 80 is preferably fixed against a malfunction in the case where the propeller 3 is normally mounted on the main body 1, and therefore, in the illustrated embodiment, the main body 1 is formed with a locking portion 74 connected to the handle 80. In the illustrated embodiment, the locking portion 74 is a flange with a screw hole provided on the inner side wall of the hole 11, but it is also possible to provide the flange on the outside of the body 1, and the handle 80 is provided with a small hole corresponding to the screw hole of the locking portion 74, and the handle 80 and the body 1 can be locked together by a locking mechanism such as a screw or a pin.

Further, for the convenience of installation, a guide portion 75 is formed on the inner side wall of the hole 11, and a guide engagement structure 76 engaged with the guide portion 75 is formed on the outer side wall of the latch mechanism 60. In the illustrated embodiment, the guide portion 75 is a guide slot and the guide engagement structure 76 is a guide post. It will be appreciated by those skilled in the art that various suitable guide arrangements may be provided in addition to the arrangement of the present invention.

Fig. 5 shows an exploded view of a detachable mounting structure for a propulsion propeller according to another embodiment of the present invention, wherein the propulsion propeller 3 is omitted and not shown. In the illustrated embodiment, the jaw mechanism 60 is fixedly connected to the propulsion motor 31 through an adapter plate 50, but the latch mechanism 60 may be directly connected to the propulsion motor 31 if the structure design allows, and the adapter plate 50 may not be used.

Fig. 6 and 7 are schematic perspective views of the jaw mechanism in two different exploded states, respectively. As shown in the figure, the jaw mechanism 60 includes a cylindrical base 61 and a cylindrical turntable 62 disposed inside the cylindrical base 61, and a hollow rotating shaft 611 is disposed in the center of the cylindrical base 61; the handle 80 is fixedly connected with the cylindrical turntable 62; the drive handle 80 can drive the cylindrical turntable 62 to rotate around the hollow rotating shaft 611. A hollow shaft 611 is provided in the center of the cylindrical base 61, the purpose of which is to form a passage in the center of the jaw mechanism 60 through which cables (not shown) can pass, for connecting the battery and control mechanism inside the body 1 to the propulsion motor 31. Of course, it should be understood by those skilled in the art that these cables need to be plugged and disconnected when the propeller 3 is mounted and dismounted, and the connection and disconnection of the cables is not a matter of protection of the present invention and will not be described in detail herein.

A plurality of guide bars 612 facing the central axis of the cylindrical base 61 are formed at equal intervals on the inner side wall of the cylindrical base 61, first long slots 613 extending in the radiation direction facing the central axis of the cylindrical base 61 are formed in the guide bars 612, and second long slots 614 corresponding to the first long slots 613 are formed in the bottom of the cylindrical base 61; a link through hole 83 through which a jaw link 82 hinged at the bottom of the jaw 81 passes is formed on the side wall of the cylindrical base 61 between the first long slot hole 613 and the second long slot hole 614 in correspondence to each jaw 80; a handle through hole 84 for the handle 80 to pass through is formed on the side wall of the cylindrical base 61; a jaw tab 85 is formed on an outer sidewall of the cylindrical base 61 above the link through hole 83, and a middle portion of the jaw 80 is rotatably hinged on the jaw tab 85. In the illustrated embodiment, a total of three jaws 81 are provided, the three jaws 81 are hinged on the outer side wall of the cylindrical base 61 at equal intervals by means of jaw tabs 85, each jaw 81 is provided with a guide strip 612 and a link through hole 83, and in order to avoid interference, the handle through hole 84 needs to avoid the link through hole 83, and the handle through hole 84 is shown to be provided between the two link through holes 83.

A plurality of pairs of outwardly extending rotating arms 621 are formed on the cylindrical turntable 62 corresponding to each jaw 80, each pair of rotating arms 621 is spaced up and down, and a third long slot 622 is formed thereon, wherein the third long slot 622 is vertically aligned, and an included angle α between the length direction of the third long slot 622 and the radial direction of the central axis of the cylindrical base 61 is greater than 0 degree and smaller than 90 degrees, as shown in fig. 5. In the illustrated embodiment, three pairs of rotating arms 621 are formed corresponding to the three claws 80, and each pair of rotating arms 621 is formed with a third elongated slot 622 corresponding to the upper and lower portions thereof. The length direction of the third slot 622 cannot radiate from the central axis, but needs to form an included angle α with the radiation direction facing the central axis, the included angle α is 0 degrees, the handle 80 is locked, if the included angle α is 90 degrees, the handle 80 is operated to idle, that is, the claw 81 does not move instantly when the handle 80 is rotated, but stops greatly, the operation stroke needed by the handle 80 becomes very long, and the space needed by the handle through hole 84 becomes difficult to set.

A sleeve 86 is arranged between a pair of rotating arms 621 which are arranged at intervals up and down, a mandrel 87 is arranged in the center of the sleeve 86 in a penetrating manner, and the mandrel 87 is arranged in the corresponding third long slot 622, the first long slot 613 and the second long slot 614 in a penetrating manner; the end of the pawl link 82 is hinged outside of the sleeve 86. The mandrel 87 is freely inserted into the sleeve 86, so that the sleeve 86 can rotate around the mandrel 87 and also move up and down along the length of the mandrel 87. Since the stem 87 also needs to be able to translate along the first and second slots 613 and 614, in order to prevent the stem 87 from being disengaged from the sleeve 86, a cover (not shown) may be provided above the cylindrical base 61 to restrain the upper end of the stem 87 by the cover, and of course, a slot similar to the second slot 614 may be formed in the cover. In another embodiment, the mandrel 87 may form a tight fit with the sleeve 86, which may carry the mandrel 87 as soon as the sleeve 86 is rotated or moved up and down, thus preventing the mandrel 87 from disengaging. Of course, the tight fit of the mandrel 87 and sleeve 86 requires a higher assembly, but the reliability after assembly is higher than the way the cover is provided.

In addition, in order to prevent the cylindrical turntable 62 from being disengaged from above the hollow rotating shaft 611, a snap ring 89 that presses the cylindrical turntable 62 may be provided above the hollow rotating shaft 611. The technical effect of pressing against the cylindrical turntable 62 can also be obtained if the snap ring 89 is replaced by the aforementioned cover. In addition, if the spindle 87 is tightly fitted to the sleeve 86, the cylindrical turntable 62 is restricted by the sleeve 86, and the snap ring 89 may not be required. Of course, it is safe to provide the snap ring 89 on the hollow rotating shaft 611, and it is also feasible to retain the snap ring 89.

Further, a return spring 88 is arranged between the claw 81 and the outer side wall of the cylindrical base 61, and the return spring 88 pushes the tail end of the claw 81 to the middle closed state. In the illustrated embodiment, the return spring 88 is disposed below the hinge axis of the latch 81 and the latch tab 85, and the latch 81 and the outer side wall of the cylindrical base 61 are each formed with a recess 881 for receiving the end of the return spring 88 to prevent the return spring 88 from being positionally displaced or disengaged. In the free state, the return spring 88 abuts against the lower end of the claw 81, so that the claw 81 tends to rotate along the hinge shaft, and the end of the claw 81 is folded toward the middle, thereby ensuring that the end of the claw 81 can be firmly clamped on the inner side of the large-diameter portion 72 of the flange member 70 in the normal state.

When the propulsion propeller 3 needs to be installed on the fuselage 1, the jaw mechanism 60 is first fixedly connected with the propulsion motor 31 of the propulsion propeller 3 through the adapter plate 50, and the flange 70 is already embedded in the hole 11 at the tail end of the fuselage 1. Then, as shown in fig. 5-7, the handle 80 is pulled clockwise, the handle 80 drives the cylindrical turntable 62 to rotate, and further drives the rotating arm 621 on the cylindrical turntable 62 to rotate, and the third long slot 622 of the rotating arm 621 presses the side surface of the core shaft 87 to move along the third long slot 622 toward the direction close to the central axis of the cylindrical base 61. Because the mandrel 87 is also constrained by both the first slot 613 and the second slot 614, the mandrel 87 can only translate inwardly under the simultaneous constraint of the three slots. When the mandrel 87 translates inwards, the sleeve 86 on the mandrel 87 also translates inwards synchronously, the jaw connecting rod 82 is further driven to be folded inwards, the jaw connecting rod 82 drives the lower end of the jaw 81 to move inwards, and the elastic action of the return spring 88 is overcome, so that the tail end of the jaw 81 is opened. Thereafter, the guide engagement structure 76 of the latch mechanism 60 is aligned with the guide portion 75 on the inner side wall of the hole 11, the latch mechanism 60 is pushed into the bottom of the hole 11 so that the distal ends of the latches 81 enter the engaging space 73, and then the handle 80 is released, and the distal ends of the latches 81 are restored to the inwardly folded state by the elastic force of the return spring 88, thereby being engaged with the inner side of the large diameter portion 72 of the flange member 70. Finally, the handle 80 is locked with the body 1, thereby avoiding the handle 80 from being mistakenly moved.

When the propeller 3 needs to be detached from the body 1, the handle 80 is firstly unlocked from the body 1, the handle 1 is also pulled clockwise, and as before, the clockwise rotation of the handle 1 finally drives the tail ends of the claws 81 to open, so that the claws are separated from the clamping relation with the inner side of the large-diameter part 72 of the flange part 70, and then the whole propeller 3 is pulled out together.

The detachable mounting structure for the propulsion propeller is clamped with the flange piece in the machine body by the jaw mechanism, can realize tool-free disassembly and assembly, is convenient to operate, can meet the requirement of frequent inspection or replacement of the propulsion motor, and improves the safety of an airplane.

It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.

The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.

Claims (10)

1. The utility model provides a demountable installation structure for propelling screw, propelling screw (3) set up the end that is located the afterbody of fuselage (1) of aircraft, its characterized in that, demountable installation structure include with the drive propelling motor (31) fixed connection's of propelling screw (3) jack catch mechanism (60) and with fuselage (1) fixed connection's flange spare (70), jack catch mechanism (60) through drive its a plurality of jack catches (81) that open and shut by handle (80) with flange spare (70) joint.

2. The detachable mounting structure for a propeller according to claim 1, wherein the flange member (70) is fixed inside a hole (11) at the end of the tail portion of the body (1), the flange member (70) has a small diameter portion (71) fixedly connected to the body (1) toward the inside of the hole (11), and a large diameter portion (72) toward the outside of the hole (11), and a catching space (73) for receiving the end of the claw (81) is formed between the large diameter portion (72) and the bottom and side wall of the hole (11); the tail end of the claw (81) can be clamped on the inner side of the large-diameter part (72) in an opening and closing manner.

3. The detachable mounting structure for a propulsion propeller according to claim 2, characterized in that the body (1) is formed with a locking portion (74) connected to a handle (80).

4. A detachable mounting structure for a propulsion propeller according to claim 2 or 3, characterised in that a guide portion (75) is formed on the inner side wall of the hole (11), and a guide engagement structure (76) engaged with the guide portion (75) is formed on the outer side wall of the jaw mechanism (60).

5. A demountable installation structure for a propulsion propeller as claimed in any one of claims 1 to 4, wherein said jaw mechanism (60) comprises a cylindrical base (61) and a cylindrical turntable (62) disposed inside the cylindrical base (61), the center of the cylindrical base (61) being provided with a hollow rotating shaft (611); the handle (80) is fixedly connected with the cylindrical turntable (62); the drive handle (80) can drive the cylindrical turntable (62) to rotate around the hollow rotating shaft (611).

6. The detachable mounting structure for a propulsion propeller according to claim 5, characterized in that a plurality of guide strips (612) are formed at equal intervals on the inner side wall of the cylindrical base (61) toward the central axis of the cylindrical base (61), the guide strips (612) are formed with first long slot holes (613) extending in a radial direction toward the central axis of the cylindrical base 61, and the bottom of the cylindrical base (61) is formed with second long slot holes (614) corresponding to the first long slot holes (613); a link through hole (83) through which a jaw link (82) hinged to the bottom of the jaw (81) passes is formed on the side wall of the cylindrical base (61) between the first long slot hole (613) and the second long slot hole (614) corresponding to each jaw (80); a handle through hole (84) for the handle (80) to pass through is formed on the side wall of the cylindrical base (61); the outer side wall of the cylindrical base (61) above the connecting rod through hole (83) is provided with a claw lug (85), and the middle part of the claw (80) is rotatably hinged on the claw lug (85).

7. A detachable mounting structure for a propeller according to claim 6, wherein the cylindrical turntable (62) is formed with a plurality of pairs of outwardly extending swivel arms (621) corresponding to each jaw (80), each pair of swivel arms (621) being spaced apart from each other and having a third elongated slot (622) formed therein in vertical alignment, the third elongated slot (622) having a length direction which forms an angle greater than 0 degrees and smaller than 90 degrees with a radial direction toward the central axis of the cylindrical base (61).

8. The removable mounting structure for a propulsion propeller as claimed in claim 7, wherein a sleeve (86) is provided between a pair of rotating arms (621) spaced up and down, a spindle (87) is provided centrally through the sleeve (86), the spindle (87) is provided through the corresponding third slot (622), first slot (613) and second slot (614); the end of the jaw link (82) is hinged outside the sleeve (86).

9. The detachable mounting structure for a propulsion propeller according to claim 8, characterized in that a return spring (88) is arranged between the jaw (81) and the outer side wall of the cylindrical base (61), the return spring (88) urging the end of the jaw (81) to a state of being folded towards the middle.

10. The detachable mounting structure for a propulsion propeller according to claim 9, characterized in that a snap ring (89) pressing the cylindrical turntable (62) is provided above the hollow rotating shaft (611); the claw mechanism (60) is fixedly connected with the propelling motor (31) through an adapter plate (50).

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