A detachable installation structure for propulsion propeller

Abstract

The present invention discloses a detachable installation structure for a propulsion propeller, wherein the propulsion propeller is arranged at the end of the tail of the fuselage of an aircraft, wherein the detachable installation structure comprises a claw mechanism fixedly connected to a propulsion motor driving the propulsion propeller and a flange member fixedly connected to the fuselage, wherein the claw mechanism is engaged with the flange member by a plurality of claws driven to open and close by a handle. The detachable installation structure for a propulsion propeller of the present invention utilizes the claw mechanism to engage with the flange member in the fuselage, can realize tool-free disassembly and assembly, is easy to operate, can meet the needs of frequent inspection or replacement of the propulsion motor, and improves the safety of the aircraft.

Description

Technical Field

[0001] This invention relates to an aircraft with an electric propulsion propeller, and more particularly to a detachable mounting structure for the propeller. Background Technology

[0002] With increasingly stringent requirements for energy conservation and environmental protection, electric aircraft are gradually gaining acceptance. Most existing electric-propelled aircraft are multi-rotor electric unmanned aerial vehicles (UAVs), widely used for tasks such as agricultural protection, forest fire monitoring, aerial photography, land surveying, and disaster loss assessment. However, existing multi-rotor electric UAVs generally suffer from low payload capacity and unreasonable structural layout, making it difficult to fully utilize the control and safety advantages of UAVs.

[0003] With the development of battery technology, electric propeller aircraft are gradually becoming capable of being used in passenger aircraft. However, the transition from drones to passenger aircraft will further increase the requirements for motors, especially given the high reliability requirements of passenger aircraft, which necessitate frequent testing and maintenance of motors.

[0004] For example, CN 107672799 A discloses an electric unmanned aerial vehicle (UAV) including a fuselage, two landing gears, and eight motors supported by eight cantilever arms connected to the fuselage. To reduce transport volume, the cantilever arms of this prior art electric UAV employ a folding structure. Therefore, if the cantilever arms and the motors supported by them were used in passenger transport scenarios, the motors would require very frequent inspections or replacements, and disassembling the entire cantilever arm would be cumbersome. Furthermore, this aircraft uses an unconventional layout, resulting in a complex aerodynamic structure and very limited reliability. Therefore, further improvements and refinements are needed in practical applications to make it suitable for real-world passenger transport scenarios. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a detachable mounting structure for propulsion propellers in order to reduce or avoid the problems mentioned above.

[0006] To solve the above-mentioned technical problems, the present invention proposes a detachable mounting structure for a propulsion propeller, wherein the propulsion propeller is located at the tail end of the fuselage of an aircraft. The detachable mounting structure includes a claw mechanism fixedly connected to a propulsion motor that drives the propulsion propeller and a flange fixedly connected to the fuselage. The claw mechanism engages with the flange by multiple claws that are driven to open and close by a handle.

[0007] Preferably, the flange is fixed inside a hole at the end of the tail section of the fuselage. The flange has a small-diameter portion that is fixedly connected to the fuselage facing the inside of the hole, and a large-diameter portion facing the outside of the hole. The large-diameter portion forms a locking space with the bottom and sidewall of the hole to accommodate the end of the claw. The end of the claw can be locked into the inside of the large-diameter portion.

[0008] Preferably, a locking part connected to the handle is formed on the body.

[0009] Preferably, a guide portion is formed on the inner wall of the hole, and a guide engagement structure that cooperates with the guide portion is formed on the outer wall of the claw mechanism.

[0010] Preferably, the claw mechanism includes a cylindrical base and a cylindrical turntable disposed inside the cylindrical base, with a hollow rotating shaft disposed at the center of the cylindrical base; the handle is fixedly connected to the cylindrical turntable; the cylindrical turntable can be driven to rotate around the hollow rotating shaft by driving the handle.

[0011] Preferably, a plurality of guide strips are formed at equal intervals on the inner sidewall of the cylindrical base, and a first elongated slot is formed on the guide strip along the radial direction toward the central axis of the cylindrical base. A second elongated slot is formed at the bottom of the cylindrical base corresponding to the first elongated slot. A connecting rod through hole is formed on the sidewall of the cylindrical base between the first elongated slot and the second elongated slot, corresponding to each claw, for a claw connecting rod hinged to the bottom of the claw to pass through. A handle through hole is formed on the sidewall of the cylindrical base for a handle to pass through. A claw lug is formed on the outer sidewall of the cylindrical base above the connecting rod through hole, and the middle part of the claw is rotatably hinged to the claw lug.

[0012] Preferably, the cylindrical turntable has multiple pairs of outwardly extending rotating arms corresponding to each claw, each pair of rotating arms is spaced vertically apart, and each pair has a vertically aligned third long slot. The length direction of the third long slot has an angle greater than 0 degrees and less than 90 degrees with the radial direction toward the central axis of the cylindrical base.

[0013] Preferably, a sleeve is provided between a pair of rotating arms spaced apart vertically, and a mandrel is inserted through the center of the sleeve, which is inserted into the corresponding third long slot, first long slot and second long slot; the end of the pawl connecting rod is hinged to the outside of the sleeve.

[0014] Preferably, a return spring is provided between the claw and the outer wall of the cylindrical base, and the return spring holds the end of the claw against the middle and closes it.

[0015] Preferably, a retaining ring is provided above the hollow rotating shaft to press down the cylindrical turntable; the claw mechanism is fixedly connected to the propulsion motor through an adapter plate.

[0016] The detachable mounting structure for propulsion propellers of the present invention uses a claw mechanism to engage with the flange in the fuselage, enabling tool-free assembly and disassembly, which is convenient and allows for frequent inspection or replacement of the propulsion motor, thereby improving the safety of the aircraft. Attached Figure Description

[0017] The accompanying drawings are intended only to illustrate and explain the present invention and do not limit the scope of the invention.

[0018] Figure 1 The diagram shown is a three-dimensional structural schematic of a vertical takeoff and landing aircraft according to a specific embodiment of the present invention.

[0019] Figure 2 The diagram shown is an exploded view of a detachable mounting structure for a propeller according to a specific embodiment of the present invention.

[0020] Figure 3 The diagram shown is an exploded perspective view of the fuselage and flange according to a specific embodiment of the present invention.

[0021] Figure 4 The diagram shows an anatomical view of the claw mechanism and the fuselage according to a specific embodiment of the present invention.

[0022] Figure 5 The diagram shown is an exploded view of a detachable mounting structure for propulsion propellers according to another specific embodiment of the present invention.

[0023] Figure 6 The diagram shown is a three-dimensional structural schematic of the chuck mechanism in a disassembled state according to yet another specific embodiment of the present invention.

[0024] Figure 7 The diagram shown is a three-dimensional structural schematic of the chuck mechanism in a disassembled state according to another specific embodiment of the present invention. Detailed Implementation

[0025] To provide a clearer understanding of the technical features, objectives, and effects of the present invention, specific embodiments are now described with reference to the accompanying drawings. Identical components are denoted by the same reference numerals.

[0026] like Figure 1As shown, this invention provides a vertical takeoff and landing (VTOL) aircraft, employing a conventional high-wing configuration. It includes a wing 2 positioned above the fuselage 1, a propeller 3 located at the rear of the fuselage 1, horizontal stabilizers 4 on either side of the rear of the fuselage 1, and landing gear 5 located below the fuselage 1. This aircraft utilizes a conventional layout, allowing for takeoff and taxiing like a conventional aircraft. The advantages of this design are its simple structure and mature, reliable technology. The rear-mounted propeller provides low noise and a comfortable ride, making it suitable for passenger transport.

[0027] To achieve short takeoff and landing (STOVL), the aircraft of this invention has a support beam 6 extending parallel to the axis of the fuselage 1, connected below each of the wings 2 on both sides of the fuselage 1. Each end of the support beam 6 has a motor nacelle 7, and a pair of coaxial counter-rotating lift propellers 8 are mounted on the motor nacelles 7. Although the invention has eight lift propellers, only four motor nacelles 7 are needed, meaning only four lift motors are required. Compared to a single motor driving one propeller, this design results in lighter weight and higher takeoff and landing efficiency. Similarly, because the aircraft of this invention adopts a conventional structural layout, the lift propellers 8 only function during takeoff and landing; they are inactive during level flight, avoiding wingtip stall.

[0028] It should be noted that electric motors have advantages over internal combustion engines in terms of light weight, smooth operation, and ease of control. However, this is contingent on minimizing the number of motors while maintaining the same lift. Simply increasing the number of motors indefinitely does not achieve the same technical effect as internal combustion engines. Therefore, for aircraft with higher requirements for economy and reliability, this invention offers a more optimized design for the number, layout, and structural weight of lift motors. Compared to the unrealistic ideas of existing technologies, this invention achieves greater economic benefits and reliability suitable for passenger transport.

[0029] Furthermore, to enable the aircraft to take off and land using conventional taxiing and to fly normally, the horizontal tail 4 of the aircraft of this invention is provided with a wingtip spade 41, and yaw surfaces 42 extending obliquely upward and downward are respectively provided on the outer side of the wingtip spade 41. At least one of the yaw surfaces 42 is a wing surface with a control surface or a fully movable wing surface, so as to facilitate the normal operation of the aircraft to change its heading.

[0030] As a conventionally laid-out aircraft, the horizontal tail 4 of this invention primarily provides stabilizing torque and pitch control torque. Therefore, the size of the horizontal tail 4 is much smaller than that of the wing 2, and it does not originally require much structural strength. In order to be able to set a yaw surface 42 at the wingtip of the horizontal tail 4 (since the propeller 3 is located at the end of the fuselage 1, it would be difficult to set a conventional vertical tail at the tail of the fuselage 1, and it would also affect the propulsion efficiency of the propeller 3. Therefore, this invention preferably sets a yaw surface 42 at the wingtip of the horizontal tail 4), this invention sets a wingtip sparb 41 at the wingtip of the horizontal tail 4 to structurally strengthen the relatively weak wingtip portion, so as to bear the additional structural stress of the yaw surface 42 after the position improvement.

[0031] As mentioned earlier, a pair of lift propellers 8 are installed at the front and rear of the support beam 6 connected to the lower part of the wing 2. Although the lift propellers 8 do not work during level flight, their protruding shape greatly disrupts the airflow during high-speed flight. Therefore, the end of the support beam 6 needs to withstand very large aerodynamic impacts, and the torsional amplitude is also large during level flight. In order to reduce the vibration of the support beam 6, in the specific embodiment shown in the figure, the end of the lift support beam 6 can be connected to the wingtip spars 41 of the horizontal tail 4, and the wingtip spars 41 of the reinforced yaw surface 42 can provide additional support for the lift support beam 6.

[0032] As mentioned above, the propeller 3, which is the main propulsion propeller, requires a high-power motor for driving. In order to improve the safety factor, the motor needs to be inspected or replaced very frequently. Therefore, this invention proposes a detachable mounting structure for the propeller 3, which is used to conveniently remove the propeller 3 and its motor from the fuselage 1 or install them on it.

[0033] Figure 2 An exploded view of a detachable mounting structure for a propeller according to a specific embodiment of the present invention is shown. As shown, the detachable mounting structure of the present invention includes a claw mechanism 60 fixedly connected to a propulsion motor 31 that drives the propeller 3 and a flange member 70 fixedly connected to the fuselage 1. The claw mechanism 60 engages with the flange member 70 through a plurality of claws 81 driven by a handle 80 to open and close, which will be described in further detail later.

[0034] Figure 3 An exploded perspective view of the fuselage and flange components is shown; Figure 4The figure shows an anatomical view of the claw mechanism and the fuselage. As shown, the flange 70 is fixed inside a hole 11 at the tail end of the fuselage 1. The flange 70 has a small-diameter portion 71 that is fixedly connected to the fuselage 1 facing the inside of the hole 11, and a large-diameter portion 72 facing the outside of the hole 11. The large-diameter portion 72 forms a locking space 73 between itself and the bottom and sidewall of the hole 11 to accommodate the end of the claw 81. The end of the claw 81 can be opened and closed to lock into the inside of the large-diameter portion 72.

[0035] Since the opening and closing of the pawl 81 is driven by the handle 80, it is best to fix the handle 80 in place to prevent accidental movement when the propeller 3 is normally installed on the fuselage 1. Therefore, in the illustrated embodiment, a locking part 74 connected to the handle 80 is formed on the fuselage 1. In a specific embodiment illustrated, the locking part 74 is a flange with a screw hole on the inner wall of the hole 11. Of course, this flange can also be provided on the outside of the fuselage 1. The handle 80 is provided with a small hole corresponding to the screw hole on the locking part 74, and the handle 80 and the fuselage 1 can be locked together by a locking mechanism such as a screw or pin.

[0036] Furthermore, for ease of installation, a guide portion 75 is formed on the inner wall of the hole 11, and a guide engagement structure 76 that mates with the guide portion 75 is formed on the outer wall of the claw mechanism 60. In the illustrated specific embodiment, the guide portion 75 is a guide groove, and the guide engagement structure 76 is a guide post. Those skilled in the art should understand that various suitable guide structures can be provided based on the structure of the present invention.

[0037] Figure 5 An exploded view of a detachable mounting structure for a propeller according to another specific embodiment of the present invention is shown, wherein the propeller 3 is omitted from the diagram. In the illustrated embodiment, the gripper mechanism 60 is fixedly connected to the propeller motor 31 via an adapter plate 50. Of course, if the structural design allows, the gripper mechanism 60 can also be directly connected to the propeller motor 31, in which case the adapter plate 50 is not required.

[0038] Figure 6 and Figure 7The figures show three-dimensional structural diagrams of the gripper mechanism in two different disassembled states. As shown, the gripper mechanism 60 includes a cylindrical base 61 and a cylindrical turntable 62 disposed inside the cylindrical base 61. A hollow rotating shaft 611 is located at the center of the cylindrical base 61. A handle 80 is fixedly connected to the cylindrical turntable 62; the cylindrical turntable 62 can be rotated around the hollow rotating shaft 611 by driving the handle 80. The hollow rotating shaft 611 at the center of the cylindrical base 61 is designed to form a channel in the center of the gripper mechanism 60 through which cables (not shown) can pass, connecting the battery and control mechanism inside the fuselage 1 to the propulsion motor 31. Of course, those skilled in the art should understand that these cables need to be plugged in and disconnected during the installation and disassembly of the propulsion propeller 3. The connection and disconnection of these cables are not the subject of this invention and will not be described in detail here.

[0039] Multiple guide strips 612 are formed at equal intervals on the inner sidewall of the cylindrical base 61, facing the central axis of the cylindrical base 61. A first elongated slot 613 is formed on the guide strip 612, extending in a radial direction towards the central axis of the cylindrical base 61. A second elongated slot 614 corresponding to the first elongated slot 613 is formed on the bottom of the cylindrical base 61. A connecting rod through hole 83 is formed on the sidewall of the cylindrical base 61 between the first elongated slot 613 and the second elongated slot 614, corresponding to each claw 81, through which a claw connecting rod 82 hinged to the bottom of the claw 81 can pass. A handle through hole 84 is formed on the sidewall of the cylindrical base 61 for the handle 80 to pass through. A claw lug 85 is formed on the outer sidewall of the cylindrical base 61 above the connecting rod through hole 83, and the middle part of the claw 80 is rotatably hinged to the claw lug 85. In the specific embodiment shown in the figure, a total of three claws 81 are provided. These three claws 81 are hinged to the outer wall of the cylindrical base 61 at equal intervals through claw lugs 85. Each claw 81 is provided with a guide strip 612 and a connecting rod through hole 83. In order to avoid interference, the handle through hole 84 needs to avoid the connecting rod through hole 83. The figure shows that the handle through hole 84 is located between the two connecting rod through holes 83.

[0040] The cylindrical turntable 62 has multiple pairs of outwardly extending rotating arms 621 corresponding to each jaw 81. Each pair of rotating arms 621 is spaced vertically apart and has a vertically aligned third elongated slot 622. The length direction of the third elongated slot 622 has an angle α greater than 0 degrees and less than 90 degrees with the radial direction toward the central axis of the cylindrical base 61. Figure 5As shown in the specific embodiment, three pairs of rotating arms 621 are formed corresponding to the three jaws 81. Each pair of rotating arms 621 has a corresponding upper and lower third elongated slot 622. The length direction of the third elongated slot 622 cannot radiate outward from the central axis, but needs to have an angle α with the radiating direction towards the central axis. If this angle α is 0 degrees, the handle 80 will jam when operating. If this angle α is 90 degrees, the handle 80 will spin freely for a period of time when operating. That is, when rotating the handle 80, the jaws 81 will not produce an immediate action, but will have a large pause. Moreover, the operating stroke required by the handle 80 will become very long, and the space required for the handle through hole 84 will become difficult to set.

[0041] A sleeve 86 is positioned between a pair of vertically spaced rotating arms 621. A spindle 87 passes through the center of the sleeve 86, passing through the corresponding third elongated slot 622, first elongated slot 613, and second elongated slot 614. The end of the pawl connecting rod 82 is hinged to the outside of the sleeve 86. The spindle 87 can freely pass through the sleeve 86, allowing the sleeve 86 to rotate around the spindle 87 and move up and down along the length of the spindle 87. Since the spindle 87 also needs to be able to translate along the first elongated slot 613 and second elongated slot 614, a cover (not shown in the figure) can be provided above the cylindrical base 61 to restrict the upper end of the spindle 87 in order to prevent the spindle 87 from detaching from the top of the sleeve 86. Of course, the cover can also have an elongated slot similar to the second elongated slot 614. In another specific embodiment, the mandrel 87 can form a tight fit with the sleeve 86. When the sleeve 86 rotates or moves up and down, it will move the mandrel 87 along with it, thus preventing the mandrel 87 from disengaging. Of course, the tight fit between the mandrel 87 and the sleeve 86 requires high assembly standards, but the reliability after assembly is higher than that of the method of setting a cover.

[0042] Additionally, to prevent the cylindrical turntable 62 from detaching from the hollow shaft 611, a retaining ring 89 can be provided above the hollow shaft 611 to hold the cylindrical turntable 62 in place. Replacing the retaining ring 89 with the aforementioned cover will also achieve the same effect of holding the cylindrical turntable 62 in place. Alternatively, if the spindle 87 and sleeve 86 form a tight fit, the cylindrical turntable 62 is restricted by the sleeve 86, eliminating the need for the retaining ring 89. Of course, for safety, providing the retaining ring 89 on the hollow shaft 611 is a safe structural design, and retaining the retaining ring 89 is also feasible.

[0043] Furthermore, a return spring 88 is provided between the pawl 81 and the outer wall of the cylindrical base 61. The return spring 88 holds the end of the pawl 81 in a closed position against the center. In the illustrated embodiment, the return spring 88 is located below the hinge axis between the pawl 81 and the pawl lug 85. A recess 881 is formed on the outer wall of both the pawl 81 and the cylindrical base 61 to accommodate the end of the return spring 88, thus preventing the return spring 88 from shifting or disengaging. In the free state, the return spring 88 abuts against the lower end of the pawl 81, causing the pawl 81 to tend to rotate along the hinge axis, and the end of the pawl 81 closes towards the center. This ensures that, under normal conditions, the end of the pawl 81 can be securely engaged with the inner side of the large-diameter portion 72 of the flange member 70.

[0044] When it is necessary to install the propeller 3 onto the fuselage 1, firstly, the claw mechanism 60 is fixedly connected to the propeller motor 31 of the propeller 3 via the adapter plate 50. A flange 70 is pre-embedded in the hole 11 at the tail end of the fuselage 1. Then, as... Figure 5-7 As shown, turning the handle 80 clockwise causes the cylindrical turntable 62 to rotate, which in turn causes the rotating arm 621 on the cylindrical turntable 62 to rotate. The third elongated slot 622 of the rotating arm 621 presses against the side of the spindle 87, causing it to move along the third elongated slot 622 towards the central axis of the cylindrical base 61. Since the spindle 87 is also restricted by the first elongated slot 613 and the second elongated slot 614, the spindle 87 can only move inward under the synchronous restriction of the three elongated slots. At the same time as the spindle 87 moves inward, the sleeve 86 on the spindle 87 also moves inward synchronously, further driving the pawl connecting rod 82 to retract inward. The pawl connecting rod 82 drives the lower end of the pawl 81 inward, overcoming the elastic force of the return spring 88, and causing the end of the pawl 81 to open. Next, align the guide engagement structure 76 of the claw mechanism 60 with the guide portion 75 on the inner wall of the hole 11, push the claw mechanism 60 into the bottom of the hole 11, so that the end of the claw 81 enters the engagement space 73, and then release the handle 80. Under the elastic force of the return spring 88, the end of the claw 81 returns to its inward closing state, thus engaging with the inner side of the large diameter portion 72 of the flange 70. Finally, lock the handle 80 to the body 1 to prevent the handle 80 from moving accidentally.

[0045] When it is necessary to remove the propeller 3 from the fuselage 1, first release the lock between the handle 80 and the fuselage 1. Then, turn the handle 1 clockwise. As mentioned before, the clockwise rotation of the handle 1 will eventually cause the end of the pawl 81 to open, thereby disengaging from the engagement with the inner side of the large diameter part 72 of the flange 70. Then, simply pull the entire propeller 3 outward together.

[0046] The detachable mounting structure for propulsion propellers of the present invention uses a claw mechanism to engage with the flange in the fuselage, enabling tool-free assembly and disassembly, which is convenient and allows for frequent inspection or replacement of the propulsion motor, thereby improving the safety of the aircraft.

[0047] Those skilled in the art should understand that although the present invention has been described with reference to multiple embodiments, not every embodiment contains only one independent technical solution. This description is provided merely for clarity; those skilled in the art should understand the specification as a whole and consider the technical solutions involved in each embodiment as being able to be combined with each other to form different embodiments to understand the scope of protection of the present invention.

[0048] The above description is merely an illustrative embodiment of the present invention and is not intended to limit the scope of the invention. Any equivalent changes, modifications, and combinations made by those skilled in the art without departing from the concept and principles of the present invention should fall within the scope of protection of the present invention.

Claims

1. A detachable mounting structure for a propulsion propeller, wherein the propulsion propeller (3) is arranged at the end of the tail of the fuselage (1) of an aircraft, characterized in that: The detachable mounting structure comprises a claw mechanism (60) fixedly connected to a propulsion motor (31) driving the propulsion propeller (3) and a flange member (70) fixedly connected to the fuselage (1), wherein the claw mechanism (60) is engaged with the flange member (70) by a plurality of claws (81) driven to open and close by a handle (80); the claw mechanism (60) comprises a cylindrical base (61) and a cylindrical rotating disk (62) arranged inside the cylindrical base (61); a plurality of guide strips (612) are formed at equal intervals on the inner side wall of the cylindrical base (61) and are oriented toward the central axis of the cylindrical base (61); a first long slot hole is formed on the guide strip (612) and extends in a radial direction toward the central axis of the cylindrical base (61). (613), a second long slot hole (614) corresponding to the first long slot hole (613) is formed at the bottom of the cylindrical base (61); a plurality of pairs of rotating arms (621) extending outward are formed on the cylindrical turntable (62) corresponding to each claw (81), each pair of rotating arms (621) is arranged at intervals up and down, and a third long slot hole (622) aligned vertically is formed thereon; a sleeve (86) is arranged between the pair of rotating arms (621) arranged at intervals up and down, a core shaft (87) is passed through the center of the sleeve (86), and the core shaft (87) is passed through the corresponding third long slot hole (622), the first long slot hole (613) and the second long slot hole (614), and the end of the claw connecting rod (82) is hinged to the outside of the sleeve (86).

2. The detachable installation structure for a propulsion propeller according to claim 1, characterized in that: The flange member (70) is fixed inside a hole (11) at the end of the tail portion of the fuselage (1). The flange member (70) comprises a small diameter portion (71) facing the inside of the hole (11) and fixedly connected to the fuselage (1), and a large diameter portion (72) facing the outside of the hole (11). A clamping space (73) for accommodating the end of the clamping claw (81) is formed between the large diameter portion (72) and the bottom and side wall of the hole (11); the end of the clamping claw (81) is clamped to the inner side of the large diameter portion (72) in an openable and closable manner.

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

4. The detachable installation structure for a propulsion propeller according to claim 3, characterized in that: A guide portion (75) is formed on the inner side wall of the hole (11), and a guide matching structure (76) matching with the guide portion (75) is formed on the outer side wall of the claw mechanism (60).

5. The detachable installation structure for a propulsion propeller according to any one of claims 1 to 4, characterized in that: A hollow rotating shaft (611) is arranged at the center of the cylindrical base (61); the handle (80) is fixedly connected to the cylindrical rotating disk (62); and the cylindrical rotating disk (62) can be driven to rotate around the hollow rotating shaft (611) by driving the handle (80).

6. The detachable installation structure for a propulsion propeller according to claim 5, characterized in that: A connecting rod through hole (83) 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 claw (81), through which a claw connecting rod (82) hinged to the bottom of the claw (81) passes; a handle through hole (84) is formed on the side wall of the cylindrical base (61), through which a handle (80) passes; and a claw ear piece (85) is formed on the outer side wall of the cylindrical base (61) above the connecting rod through hole (83), and the middle part of the claw (81) is rotatably hinged to the claw ear piece (85).

7. The detachable installation structure for a propulsion propeller according to claim 6, characterized in that: There is an angle between the length direction of the third long slot hole (622) and the radiation direction toward the central axis of the cylindrical base (61) that is greater than 0 degrees and less than 90 degrees.

8. The detachable installation structure for a propulsion propeller according to claim 7, characterized in that: A return spring (88) is provided between the clamping claw (81) and the outer side wall of the cylindrical base (61), and the return spring (88) pushes the end of the clamping claw (81) toward the middle to close.

9. The detachable installation structure for a propulsion propeller according to claim 8, characterized in that: A clamping ring (89) for pressing the cylindrical rotating disk (62) is arranged above the hollow rotating shaft (611); the clamping claw mechanism (60) is fixedly connected to the propulsion motor (31) via an adapter disk (50).

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