Aircraft, power output apparatus, and tilting mechanism

Abstract

An aircraft, comprising a fuselage body, a power output apparatus, and a propeller assembly. The power output apparatus is arranged on the fuselage body; a driving mechanism of the power output apparatus comprises a first driving assembly and a second driving assembly; the first driving assembly comprises a first fixed member and a first movable member, and the first movable member is configured to be in transmission connection with the propeller assembly, so as to drive the propeller assembly to rotate; the first driving assembly is provided with an accommodating space; the second driving assembly is configured to drive blades of the propeller assembly to rotate so as to adjust a propeller pitch of the blades; the second driving assembly comprises a second fixed member and a second movable member, and the second movable member is configured to be in transmission connection with the blades; the second movable member comprises a pitch-variable pushing member capable of driving the blades to rotate, and the pitch-variable pushing member passes through the accommodating space to connect to the blades; and the accommodating space passes through the first driving assembly in the direction of a rotation axis of the propeller assembly, and the second fixed member and the propeller assembly close the accommodating space from two ends of the accommodating space, respectively. The present invention further relates to a power output apparatus and a tilting mechanism.

Description

Aircraft, power output device and tilting mechanism Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to an aircraft, a power output device, and a tilting mechanism. Background Art

[0002] Aircraft, with their strong adaptability to environmental conditions and ability to hover, hold broad application prospects. The power take-off (PTO) system of an aircraft, used to provide propulsion for flight, is a key component of the aircraft. However, the PTO structure of aircraft in related art is often poorly designed, requiring improvement and hindering the aircraft's operational capabilities.

[0003] Summary of the Invention

[0004] The present application provides an aircraft, a power output device and a tilt mechanism, wherein the structure of the power output device is reasonably designed.

[0005] In a first aspect, an embodiment of the present application provides an aircraft, comprising a fuselage body, a power output device, and a propeller assembly, wherein the power output device is provided on the fuselage body and is used to drive the propeller assembly; wherein the power output device includes a drive mechanism, and the drive mechanism includes:

[0006] a first drive assembly, configured to drive the propeller assembly to rotate, thereby providing flight power for the aircraft; the first drive assembly comprises a first fixed member and a first movable member that moves relative to the first fixed member, the first movable member being configured to be in transmission connection with the propeller assembly to drive the propeller assembly to rotate; the first drive assembly is provided with an accommodating space; and

[0007] a second drive assembly for driving the blades of the propeller assembly to rotate, thereby adjusting the pitch of the blades; the second drive assembly includes a second fixed member and a second movable member that moves relative to the second fixed member, the second movable member being in driving connection with the blades; the second movable member includes a pitch-changing push member capable of driving the blades to rotate, the pitch-changing push member passing through the accommodating space and connected to the blades;

[0008] The accommodating space passes through the first driving assembly in the direction of the rotation axis of the propeller assembly, and the second fixing member and the propeller assembly respectively close the accommodating space from both ends of the accommodating space.

[0009] In a second aspect, an embodiment of the present application provides an aircraft, comprising an airframe, a power output device, and a propeller assembly, wherein the power output device is disposed on the airframe and is configured to drive the propeller assembly; wherein the power output device includes a driving mechanism and a detecting mechanism, wherein the driving mechanism is configured to drive the propeller assembly to rotate to provide flight power for the aircraft and to drive blades of the propeller assembly to rotate to adjust the pitch of the blades of the propeller assembly, and the detecting mechanism is configured to detect pitch information of the blades;

[0010] Wherein, an accommodating space is provided inside the driving mechanism, and the detecting mechanism is at least partially provided in the accommodating space.

[0011] In a third aspect, an embodiment of the present application provides an aircraft, comprising a fuselage body, a power output device, and a propeller assembly, wherein the power output device is provided on the fuselage body and is used to drive the propeller assembly; wherein the power output device includes a drive mechanism, and the drive mechanism includes:

[0012] a first drive assembly, configured to drive the propeller assembly to rotate, thereby providing flight power for the aircraft; the first drive assembly comprises a first fixed member and a first movable member that moves relative to the first fixed member, the first movable member being configured to be in transmission connection with the propeller assembly to drive the propeller assembly to rotate; and

[0013] a second drive assembly for driving the blades of the propeller assembly to rotate, thereby adjusting the pitch of the blades; the second drive assembly includes a second fixed member and a second movable member that moves relative to the second fixed member, the second movable member being in driving connection with the blades;

[0014] The second fixing member is connected to the first fixing member, and when the first driving assembly drives the propeller assembly to rotate, the second fixing member is stationary relative to the first fixing member.

[0015] In a fourth aspect, an embodiment of the present application provides a power output device, including a drive mechanism, wherein the drive mechanism includes:

[0016] a first drive assembly, configured to drive the propeller assembly to rotate, thereby providing flight power for the aircraft; the first drive assembly comprises a first fixed member and a first movable member that moves relative to the first fixed member, the first movable member being configured to be in transmission connection with the propeller assembly to drive the propeller assembly to rotate; the first drive assembly is provided with an accommodating space; and

[0017] a second drive assembly for driving the blades of the propeller assembly to rotate, thereby adjusting the pitch of the blades; the second drive assembly includes a second fixed member and a second movable member that moves relative to the second fixed member, the second movable member being in driving connection with the blades; the second movable member includes a pitch-changing push member capable of driving the blades to rotate, the pitch-changing push member passing through the accommodating space and connected to the blades;

[0018] The accommodating space passes through the first driving assembly in the direction of the rotation axis of the propeller assembly, and the second fixing member and the propeller assembly respectively close the accommodating space from both ends of the accommodating space.

[0019] In a fifth aspect, an embodiment of the present application provides a power output device, comprising a drive mechanism and a detection mechanism, wherein the drive mechanism is configured to drive a propeller assembly of an aircraft to rotate to provide flight power for the aircraft and to drive blades of the propeller assembly to rotate to adjust the pitch of the blades, and the detection mechanism is configured to detect pitch information of the blades;

[0020] Wherein, an accommodating space is provided inside the driving mechanism, and the detecting mechanism is at least partially provided in the accommodating space.

[0021] In a sixth aspect, an embodiment of the present application provides a power output device, including a drive mechanism, wherein the drive mechanism includes:

[0022] a first drive assembly for driving the propeller assembly of the aircraft to rotate, thereby providing flight power for the aircraft; the first drive assembly includes a first fixed member and a first movable member that moves relative to the first fixed member, the first movable member being configured to be in transmission connection with the propeller assembly to drive the propeller assembly to rotate; and

[0023] a second drive assembly for driving the blades of the propeller assembly to rotate, thereby adjusting the pitch of the blades; the second drive assembly includes a second fixed member and a second movable member that moves relative to the second fixed member, the second movable member being in driving connection with the blades;

[0024] The second fixing member is connected to the first fixing member, and when the first driving assembly drives the propeller assembly to rotate, the second fixing member is stationary relative to the first fixing member.

[0025] In a seventh aspect, an embodiment of the present application provides a tilting mechanism, comprising:

[0026] A connecting seat, used for connecting to the fuselage of the aircraft;

[0027] a tilting connection member, configured to connect to a drive mechanism of a power output device of the aircraft, wherein the drive mechanism is configured to drive the propeller assembly to rotate and / or drive the blades to rotate to adjust the pitch;

[0028] a tilt drive assembly; and

[0029] A tilt transmission assembly is rotatably connected to the connecting seat; it cooperates with the tilt drive assembly in threaded transmission to convert the rotational motion of the tilt drive assembly into at least part of the linear motion of the tilt transmission assembly; the tilt transmission assembly is connected to the tilt connecting piece to drive the tilt connecting piece to rotate relative to the connecting seat, thereby driving the drive mechanism and the propeller assembly to tilt.

[0030] The embodiments of the present application provide an aircraft, a power output device and a tilting mechanism. Since the first drive assembly is provided with an accommodating space, the variable pitch pusher passes through the accommodating space and is connected to the blades, thereby being able to compress the overall size of the power output device to a certain extent, and the structural design of the power output device is reasonable and compact; in addition, since the second fixing member and the propeller assembly respectively close the accommodating space from both ends of the accommodating space, the protection performance of the power output device can be improved to a certain extent.

[0031] It should be understood that the above general description and the following detailed description are merely exemplary and explanatory and do not limit the disclosure of the embodiments of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0033] FIG1 is a schematic structural diagram of an aircraft provided in an embodiment of the present application;

[0034] FIG2 is a schematic diagram of a partial structure of an aircraft provided in an embodiment of the present application, showing a propeller assembly;

[0035] FIG3 is a partial cross-sectional view of an aircraft provided in an embodiment of the present application, showing a propeller assembly and a power output device;

[0036] FIG4 is a schematic structural diagram of an aircraft provided in an embodiment of the present application;

[0037] FIG5 is a partial cross-sectional view of an aircraft provided in an embodiment of the present application, showing a propeller assembly and a power output device;

[0038] FIG6 is a schematic diagram of a partial structure of an aircraft provided in an embodiment of the present application, showing a portion of a propeller assembly;

[0039] FIG7 is a partial enlarged schematic diagram of point A in FIG2;

[0040] FIG8 is a partial cross-sectional view of an aircraft provided in an embodiment of the present application, showing a propeller assembly and a power output device;

[0041] FIG9 is a schematic diagram of a partial structure of an aircraft provided in an embodiment of the present application, showing a propeller assembly and a power output device;

[0042] FIG10 is a partial cross-sectional view of an aircraft provided in an embodiment of the present application, showing a propeller assembly and a power output device;

[0043] FIG11 is a partial cross-sectional view of a power output device provided in an embodiment of the present application;

[0044] FIG12 is an exploded schematic diagram of a partial structure of a power output device provided in an embodiment of the present application, showing a second drive assembly and a detection mechanism;

[0045] FIG13 is a schematic structural diagram of a tilting mechanism provided in an embodiment of the present application;

[0046] FIG14 is a schematic diagram of a partial structure of an aircraft provided in an embodiment of the present application, showing a tilt mechanism, a drive mechanism, and a propeller assembly, wherein the propeller assembly is in a first state;

[0047] FIG15 is a schematic diagram of a partial structure of an aircraft provided in an embodiment of the present application, showing a tilt mechanism, a drive mechanism, and a propeller assembly, wherein the propeller assembly is in a second state;

[0048] FIG16 is an exploded schematic diagram of a tilting mechanism provided in an embodiment of the present application;

[0049] FIG17 is a schematic structural diagram of a tilting mechanism provided in an embodiment of the present application;

[0050] FIG18 is a schematic diagram of a partial structure of an aircraft provided in an embodiment of the present application, showing a tilt mechanism, a drive mechanism, and a propeller assembly, wherein the propeller assembly is in a first state;

[0051] FIG19 is a schematic diagram of a partial structure of an aircraft provided in an embodiment of the present application, showing a tilt mechanism, a drive mechanism, and a propeller assembly, wherein the propeller assembly is in a second state;

[0052] FIG20 is a schematic diagram of an exploded view of a tilting mechanism provided in an embodiment of the present application.

[0053] Description of reference numerals:

[0054] 1000, aircraft;

[0055] 101. Airframe; 1011. Center frame; 1012. Airframe arm; 102. Power take-off device; 103. Propeller assembly; 1031. Propeller base; 10311. Bearing seat; 10312. Guide rod; 1032. Propeller blade; 10321. Second mating portion; 104. Control module;

[0056] 10. Driving mechanism;

[0057] 11. First drive assembly; 111. First fixed member; 1111. First coil; 112. First movable member; 113. Accommodating space; 12. Second drive assembly; 121. Second fixed member; 1211. Second coil; 122. Second movable member; 1221. Variable-pitch push member; 12211. Second threaded portion; 1222. Variable-pitch push plate; 12221. First mating portion; 1223. Second bearing; 1224. Second rotor; 12241. First threaded portion; 1225. Threaded transmission mechanism; 12251. Screw; 12252. Nut; 13. Limiting structure;

[0058] 20. Detection mechanism; 21. Linkage member; 211. Rack; 212. Gear; 22. Signal acquisition member; 30. Detection sensor;

[0059] 40. Tilt mechanism; 41. Connecting seat; 42. Tilt connecting piece; 43. Tilt drive assembly; 431. Tilt drive piece; 432. Speed ​​regulator; 433. Tilt screw; 44. Tilt transmission assembly; 441. Tilt push rod; 4411. First transmission part; 4412. Second transmission part; 442. Transmission frame; 4421. First bracket; 4422. Second bracket; 4423. Third bracket; 443. First connecting shaft; 444. Second connecting shaft; 445. Third connecting shaft; 446. Fourth connecting shaft; 447. Fifth connecting shaft; 448. Sixth connecting shaft; 449. Seventh connecting shaft; 450. Eighth connecting shaft; 46. Detection sensor. DETAILED DESCRIPTION

[0060] The following will be combined with the drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the embodiments described are part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0061] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the said features. In the description of the present application, "multiple" means two or more, unless otherwise clearly and specifically defined.

[0062] It should also be understood that the terms used in this specification are only for the purpose of describing specific embodiments and are not intended to limit the present application. As used in this specification and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms unless the context clearly indicates otherwise.

[0063] It should be further understood that the term "and / or" used in this specification and the appended claims refers to and includes any and all possible combinations of one or more of the associated listed items.

[0064] Aircraft, with their strong adaptability to environmental conditions and ability to hover, hold broad application prospects. The power take-off (PTO) system of an aircraft, used to provide propulsion for flight, is a key component of the aircraft. However, the PTO structure of aircraft in related art is often poorly designed, requiring improvement and hindering the aircraft's operational capabilities.

[0065] The present application provides an aircraft, a power output device and a tilt mechanism, wherein the power output device has a reasonable structural design.

[0066] The following describes some embodiments of the present application in detail with reference to the accompanying drawings. In the absence of conflict, the following embodiments and features therein may be combined with each other.

[0067] The present invention provides a movable platform. Exemplarily, the movable platform includes at least one of the following: an aircraft, a mobile ship, an underwater mobile device, an above-water mobile device, etc.

[0068] In some embodiments, the movable platform includes a fuselage body, a power output device, and a propeller assembly. The power output device is provided on the fuselage body, and the power output device is used to drive the propeller assembly, thereby providing movement power for the movable platform.

[0069] Exemplarily, the movable platform includes at least one of the following: an aircraft, a mobile ship, an underwater mobile device, a mobile device on water, etc.

[0070] The following describes the embodiments of the present application using a movable platform as an aircraft as an example. It should be noted that, unless there is a conflict, this does not limit the scope of protection of the present application. The following embodiments can be applied individually or in combination as needed to a movable platform that is an underwater mobile device or other movable platform. All embodiments of the power output device and / or propeller assembly that apply the embodiments of the present application will fall within the scope of protection of the present application.

[0071] It is understandable that the aircraft may include a rotorcraft, a fixed-wing aircraft, a helicopter, or a fixed-wing-rotor hybrid aircraft, etc. The rotorcraft may be a single-rotor aircraft, a bi-rotor aircraft, a tri-rotor aircraft, a quad-rotor aircraft, a hexacopter aircraft, an octo-rotor aircraft, a deca-rotor aircraft, a dodeca-rotor aircraft, etc.

[0072] Please refer to Figure 1. In some embodiments, the aircraft 1000 includes a fuselage body 101, a power output device 102 and a propeller assembly 103. The power output device 102 is disposed on the fuselage body 101. The power output device 102 is used to drive the propeller assembly 103, thereby providing flight power for the aircraft 1000.

[0073] It is understood that the position, structure, and / or shape of the power output device 102 and propeller assembly 103 in FIG1 are merely exemplary. In actual applications, the position, structure, and / or shape of the power output device 102 and propeller assembly 103 may be modified according to actual needs and do not constitute a limitation to this application. For example, in actual applications, the power output device 102 may be at least partially located within the propeller assembly 103; alternatively, the power output device 102 may be located outside the propeller assembly 103.

[0074] Referring to Figure 1 , in some embodiments, the main body 101 includes a center frame 1011 and arms 1012. The arms 1012 are connected to the center frame 1011, and the power output device 102 is connected to the arms 1012. It is understood that the number of arms 1012 can be designed based on actual needs, such as one or more. For example, one or more arms 1012 extend radially from the center frame 1011.

[0075] 2 , in some embodiments, propeller assembly 103 includes a propeller base 1031 and a plurality of blades 1032. Blades 1032 are disposed on propeller base 1031. Propeller assembly 103 is configured to rotate to provide flight power for aircraft 1000. The number of blades 1032 can be set based on actual needs and is not limited herein.

[0076] In some embodiments, the aircraft further includes a payload mounting position (not shown), which is disposed on the fuselage body and is used to accommodate or connect a payload.

[0077] Exemplarily, the payload includes at least one of the following: a shooting component, a person, an animal, a cargo box, a winch, etc.

[0078] Referring to FIG. 3 , in some embodiments, the power output device 102 includes a drive mechanism 10, which includes a first drive assembly 11 and a second drive assembly 12. The first drive assembly 11 is configured to drive the propeller assembly 103 to rotate, thereby providing flight power for the aircraft 1000. The first drive assembly 11 includes a first fixed member 111 and a first movable member 112 that moves relative to the first fixed member 111. The first movable member 112 is configured to be in transmission connection with the propeller assembly 103 to drive the propeller assembly 103 to rotate, thereby providing flight power for the aircraft 1000. The first drive assembly 11 is provided with an accommodating space 113. Second drive assembly 12 is used to drive blades 1032 of propeller assembly 103 to rotate, thereby adjusting the pitch of blades 1032. Second drive assembly 12 includes a second fixed member 121 and a second movable member 122 that moves relative to second fixed member 121. Second movable member 122 is in driving connection with blades 1032. Second movable member 122 includes a pitch-changing push member 1221 that can drive blades 1032 to rotate. Pitch-changing push member 1221 passes through accommodating space 113 and is connected to blades 1032. Accommodating space 113 extends through first drive assembly 11 in the direction of the rotation axis of propeller assembly 103. Second fixed member 121 and propeller assembly 103 respectively enclose accommodating space 113 at both ends.

[0079] The power output device 102 of the above embodiment, since the first drive assembly 11 is provided with an accommodating space 113, the pitch-variable push piece 1221 passes through the accommodating space 113 and is connected to the blade 1032, can thus compress the overall size of the power output device 102 to a certain extent. The structural design of the power output device 102 is reasonable and compact. The power output device 102 can be flexibly arranged and has strong adaptability, which reduces the adverse effects of the power output device 102 on the overall design of the aircraft 1000, is conducive to making better optimization results for the overall design, and provides a guarantee for the normal use of the aircraft 1000.

[0080] It is understandable that in this embodiment, the second movable part 122 of the second drive assembly 12 can be connected to the blade 1032 through a transmission, thereby driving the blade 1032 to rotate to adjust the pitch of the blade 1032, and then adjusting the tension or lift of the propeller assembly 103 to adapt to at least two working states such as vertical take-off and landing and cruising, so that the propeller assembly 103 can operate efficiently in both the vertical take-off and landing working state and the cruising working state, thereby improving the endurance performance of the entire aircraft. When the tension or lift of the propeller assembly 103 changes, the tension or lift of the propeller assembly 103 can be adjusted by controlling the speed of the first drive assembly 11 according to actual needs; and / or, the pitch of the blade 1032 can be adjusted by the second drive assembly 12, thereby adjusting the tension or lift of the propeller assembly 103.

[0081] Furthermore, because the second fixing member 121 and the propeller assembly 103 seal both ends of the accommodating space 113 that extends through the first drive assembly 11, they prevent external media (such as at least one of liquid, gas, or dust) from entering the accommodating space 113 through both ends and affecting the performance of the components within the accommodating space 113, thereby improving the protection performance of the drive mechanism 10. Furthermore, the second fixing member 121 and the propeller assembly 103, respectively sealing the accommodating space 113 from both ends, fully utilize the space occupied by the first drive assembly 11, making the structure of the power output device 102 compact and facilitating better optimization of the overall design.

[0082] Illustratively, the rotation axis of propeller assembly 103 is shown as dashed line m in FIG3 . Illustratively, when second drive assembly 12 drives blade 1032 to rotate to adjust the pitch of blade 1032 , the rotation axis of blade 1032 is shown as dashed line n in FIG3 . Illustratively, the rotation axis of blade 1032 is perpendicular to the rotation axis of propeller assembly 103 .

[0083] For example, propeller base 1031 is connected to blades 1032. To adjust the pitch of blades 1032, second drive assembly 12 can be used to drive second movable member 122 to move relative to second fixed member 121, thereby causing second movable member 122 to drive blades 1032 to rotate relative to propeller base 1031. To provide flight power for aircraft 1000, blades 1032 can also rotate along with propeller base 1031. First drive assembly 11 can be used to drive first movable member 112 to move relative to first fixed member 111, thereby causing first movable member 112 to drive propeller base 1031 and blades 1032 to rotate.

[0084] Please refer to FIG. 3 , illustratively, the propeller base 1031 and the second fixing member 121 respectively close the accommodating space 113 from both ends of the accommodating space 113 .

[0085] In some embodiments, blades 1032 are configured to rotate relative to propeller base 1031 to change the pitch of blades 1032. When adjusting the pitch of blades 1032, second drive assembly 12 can drive blades 1032 to rotate relative to propeller base 1031. When first drive assembly 11 drives propeller assembly 103 to rotate, thereby providing flight power for aircraft 1000, propeller base 1031 and blades 1032 move synchronously.

[0086] Referring to FIG3 , in some embodiments, a first fixing member 111 is provided with an accommodation space 113 on its inner side, a first movable member 112 is provided on the outer side of the first fixing member 111, and a second fixing member 121 is provided on the outer side or the inner side of the accommodation space 113. This allows the power output device 102 to have a compact structure, facilitating a miniaturized design of the aircraft 1000.

[0087] Referring to FIG3 , illustratively, at least a portion of the second fixing member 121 is disposed outside the accommodating space 113. Thus, structural components of the power output device 102 (such as the detection mechanism 20 or other structural components shown in FIG3 ) can be installed within the accommodating space 113, thereby making the structure of the power output device 102 compact. Exemplarily, the second fixing member 121 is disposed inside the accommodating space 113 (as shown in FIG8 ) to minimize the size of the power output device 102, such as compressing the size of the power output device 102 in the direction of the rotation axis of the propeller assembly 103, thereby making the structure of the power output device 102 compact.

[0088] It is understood that the second movable member 122 is at least partially disposed within the accommodating space 113 to effectively reduce the size of the power output device 102 in the direction of the rotation axis of the propeller assembly 103. Referring to FIG. 3 , illustratively, a portion of the second movable member 122 is disposed outside the accommodating space 113, while a portion of the second movable member 122 is disposed within the accommodating space 113.

[0089] Referring to FIG. 3 , in some embodiments, the first drive assembly 11 includes a first motor, the first fixed member 111 includes a first coil 1111, the second drive assembly 12 includes a second motor, and the second fixed member 121 includes a second coil 1211. The first drive assembly 11 includes the first motor, and the second drive assembly 12 includes the second motor. This provides high drive efficiency, flexible control, and fast response speed, enabling high-precision applications. It does not require liquid or gaseous media, and is environmentally friendly, safe, and clean. As will be understood, when the first coil 1111 is energized, the first movable member 112 can move relative to the first fixed member 111, causing the first drive assembly 11 to rotate the propeller assembly 103, thereby providing flight power for the aircraft 1000. When the second coil 1211 is energized, the second movable member 122 can move relative to the second fixed member 121, causing the second drive assembly 12 to rotate the blades 1032 of the propeller assembly 103, thereby adjusting the pitch of the blades 1032.

[0090] It can be understood that if the second fixed part 121 is connected to the first movable part 112, when the first drive component 11 drives the propeller component 103 to rotate, the second fixed part 121 will move along with the first movable part 112, and a slip ring structure or a brush structure needs to be designed between the first drive component 11 and the second drive component 12. The power output device 102 with such a structure is not conducive to the routing of the second drive component 12. When the second fixed part 121 moves along with the first movable part 112, the routing of the second drive component 12 is prone to shaking, entanglement or damage, resulting in unreliable electrical connection and control failure.

[0091] Referring to FIG3 , in some embodiments, the second fixing member 121 is connected to the first fixing member 111. When the first drive assembly 11 drives the propeller assembly 103 to rotate, the second fixing member 121 remains stationary relative to the first fixing member 111. Thus, when the first drive assembly 11 drives the propeller assembly 103 to rotate, the second fixing member 121 of the second drive assembly 12 remains stationary relative to the first fixing member 111 of the first drive assembly 11. The connecting cable connecting the second drive assembly 12 and other components (such as the control module 104 in FIG4 ) does not need to move with the rotation of the first movable member 112 of the first drive assembly 11. This facilitates wiring, ensures stability and reliability, and is less likely to cause control failure. This improves the reliability and safety of the power output device 102 and reduces maintenance costs. In addition, since the second fixing member 121 is connected to the first fixing member 111, the first drive assembly 11 and the second drive assembly 12 are relatively less susceptible to wear when the power output device 102 is working, which is beneficial to extending the service life of the power output device 102 and reducing the number of times the power output device 102 is maintained or replaced; it is less likely to cause electric shock corrosion and has good corrosion resistance; the power output device 102 has a simple structure and is simple to control.

[0092] 3 , in some embodiments, the second fixing member 121 is fixedly connected to the first fixing member 111. For example, the second fixing member 121 and the first fixing member 111 are fixedly connected by at least one of the following methods: screw locking connection, snap connection, adhesive connection, etc.

[0093] In other embodiments, the second fixing member 121 may also be connected to the first movable member 112 .

[0094] Referring to Figure 3, in some embodiments, the power output device 102 further includes a detection mechanism 20 configured to detect the pitch information of the blades 1032. The detection mechanism 20 is at least partially located within the accommodation space 113 to detect the motion information of the pitch-changing pusher 1221, thereby determining the pitch information of the blades 1032. The provision of the detection mechanism 20 ensures that the aircraft 1000 can control the pitch of the blades 1032 in a closed manner. Furthermore, since the detection mechanism 20 is at least partially located within the accommodation space 113, it can fully utilize the space occupied by the first drive assembly 11, thus reducing the overall size of the power output device 102 and making it more compact. The detection mechanism 20 is also protected to a certain extent, making it less susceptible to external environmental factors (such as temperature and humidity). In other embodiments, the detection mechanism 20 can be omitted, and the aircraft 1000 can use open-loop control of the pitch of the blades 1032.

[0095] Please refer to Figure 3. It can be understood that the detection mechanism 20 is at least partially disposed in the accommodating space 113, including at least one of the following schemes: Scheme 1, the detection mechanism 20 is partially disposed in the accommodating space 113, and part of the detection mechanism 20 is disposed outside the accommodating space 113; Scheme 2, the detection mechanism 20 is disposed in the accommodating space 113.

[0096] Referring to Figure 4 , in some embodiments, aircraft 1000 further includes a control module 104, with power output device 102 being electrically connected to control module 104. Exemplarily, both first drive assembly 11 and second drive assembly 12 are electrically or signal-connected to control module 104. Control module 104 is capable of controlling the operation of at least one of first drive assembly 11 and second drive assembly 12 according to actual application requirements. Exemplarily, control module 104 is disposed in fuselage body 101. Exemplarily, control module 104 is disposed in at least one of drive mechanism 10 and detection mechanism 20.

[0097] Exemplarily, the control module 104 includes at least one of the following: a control circuit, a circuit board, etc.

[0098] In some embodiments, the control module 104 is configured to adjust the operating state or operating parameters of the aircraft 1000 based on the pitch information detected by the detection mechanism 20. In this way, the operating state or operating parameters of the aircraft 1000 can be controlled in a closed loop based on the pitch information, which facilitates more precise control of the operation of the aircraft 1000, allowing the aircraft 1000 to better meet environmental requirements or user needs.

[0099] In some embodiments, the operating state includes at least one of the operating state of fuselage body 101, the operating state of a load attached to fuselage body 101, the operating state of power take-off 102, and the operating state of propeller assembly 103. The operating parameters include at least one of the operating parameters of fuselage body 101, the operating parameters of a load attached to aircraft 1000, the operating parameters of power take-off 102, and the operating parameters of propeller assembly 103.

[0100] Exemplarily, the payload includes at least one of the following: a gimbal, a sensor, an imaging device, etc.

[0101] In some embodiments, the operating state of the power output device 102 includes at least one of the following: the operating state of the first drive assembly 11 and the operating state of the second drive assembly 12. The operating parameters of the power output device 102 include at least one of the following: the operating parameters of the first drive assembly 11 and the operating parameters of the second drive assembly 12. For example, the operating parameters of the first drive assembly 11 include at least one of the following: the rotational speed and rotational direction of the first drive assembly 11. The operating parameters of the second drive assembly 12 include at least one of the following: the rotational speed and rotational direction of the second drive assembly 12.

[0102] In some embodiments, the operating parameters of the propeller assembly 103 include at least one of the pitch of the blades 1032 , the rotation speed of the propeller assembly 103 , the rotation direction of the propeller assembly 103 , and the like.

[0103] In some embodiments, pitch-changing pusher 1221 is configured to reciprocate along the axis of rotation of propeller assembly 103 to drive blades 1032 to rotate. Detection mechanism 20 is used to detect the travel of pitch-changing pusher 1221 to determine the pitch information of blades 1032. This allows for a simple movement of pitch-changing pusher 1221 and a simple structure for second movable member 122. By detecting the travel of pitch-changing pusher 1221 by detection mechanism 20 to determine the pitch information of blades 1032, detection mechanism 20 is simple in structure, compact in size, and lightweight.

[0104] Exemplarily, the detection mechanism 20 includes a linear displacement sensor, which includes a linear variable differential transformer (LVDT) sensor.

[0105] Referring to Figure 3, in some embodiments, detection mechanism 20 includes a linkage member 21 and a signal acquisition member 22. Linkage member 21 is connected to pitch-changing push member 1221. Signal acquisition member 22 is disposed corresponding to linkage member 21 and is configured to detect the motion state information of linkage member 21 and determine the pitch information of blades 1032 based on the motion state information. The pitch information of blades 1032 is used to control the operation of second drive assembly 12 in a closed-loop manner, thereby controlling the pitch of blades 1032, thereby improving the operation of aircraft 1000.

[0106] Exemplarily, the fixed connection method between the linkage member 21 and the variable-distance push member 1221 includes at least one of the following: a snap connection, an adhesive connection, an interference fit connection, a screw-locked connection, etc.

[0107] Exemplarily, the motion state information of the linkage member 21 includes at least one of the following: movement displacement, movement speed, movement direction, etc. of the linkage member 21 .

[0108] In some embodiments, linkage member 21 moves synchronously with pitch-changing push member 1221, and signal acquisition member 22 is configured to acquire linear movement information of linkage member 21. Because linkage member 21 moves synchronously with pitch-changing push member 1221, pitch information of blade 1032 can be determined based on the linear movement information of linkage member 21 acquired by signal acquisition member 22.

[0109] Referring to Figure 3 , in some embodiments, the signal acquisition component 22 is connected to the first fixing component 111. Exemplarily, the signal acquisition component 22 and the first fixing component 111 are integrally formed, reducing the number of components and improving the assembly efficiency of the power output device 102. Exemplarily, the signal acquisition component 22 and the first fixing component 111 are separate components, and the connection between the two includes at least one of the following: a snap-fit ​​connection, an adhesive connection, an interference fit connection, a screw-lock connection, etc.

[0110] Referring to FIG. 3 , in some embodiments, the signal acquisition component 22 includes a hollow structure, and the linkage component 21 and the pitch-variable pusher 1221 are at least partially disposed within the signal acquisition component 22. Thus, after the drive mechanism 10 and the detection mechanism 20 are assembled, the assembled dimensions of the detection mechanism 20 and the pitch-variable pusher 1221 along the axis of rotation of the propeller assembly 103 are smaller than the sum of the dimensions of the linkage component 21 along the axis of rotation of the propeller assembly 103 and the dimensions of the pitch-variable pusher 1221 along the axis of rotation of the propeller assembly 103, effectively compressing the dimensions of the power output device 102 and making the structure of the power output device 102 as compact as possible. Furthermore, the signal acquisition component 22 including a hollow structure is beneficial for reducing the weight of the detection mechanism 20, thereby reducing the weight of the power output device 102, and further reducing the flight drag load of the aircraft 1000, thereby improving the performance of the aircraft 1000. When the driving mechanism 10 of the power output device 102 is connected to the tilt mechanism 40 (see FIG. 14 ), the power output device 102 of this embodiment can also reduce the load and power of the tilt mechanism 40 , thereby improving the performance of the aircraft 1000 .

[0111] Please refer to FIG. 3 , illustratively, the linkage member 21 is disposed in the signal collecting member 22 , and the variable distance pushing member 1221 is partially disposed in the signal collecting member 22 .

[0112] Exemplarily, the linkage component 21 and the variable-distance pushing component 1221 are both arranged in the signal collecting component 22 .

[0113] Exemplarily, the linkage component 21 and the variable-distance pushing component 1221 are both partially disposed in the signal collecting component 22 .

[0114] Please refer to Figure 3. For example, the signal acquisition component 22 is arranged in the accommodating space 113 to effectively compress the size of the power output device 102, and the structure of the power output device 102 is compact; in addition, it can also protect the detection mechanism 20 to a certain extent, reducing or avoiding the impact of the external environment on the detection mechanism 20.

[0115] Referring to FIG. 3 , in some embodiments, the linkage member 21 and the variable pitch push member 1221 at least partially overlap in the direction of the rotation axis of the propeller assembly 103, thereby effectively reducing the size of the power output device 102 and making the power output device 102 compact. It is understood that the projections of the variable pitch push member 1221 and the linkage member 21 on the rotation axis of the propeller assembly 103 at least partially overlap.

[0116] For example, the linkage member 21 and the variable pitch push member 1221 are coaxially arranged, and the structure of the power output device 102 is simple and compact.

[0117] In some embodiments, linkage member 21 is used to convert the linear motion of pitch-changing push member 1221 into rotational motion, and signal acquisition member 22 is used to detect the rotational state information of linkage member 21. By detecting the rotational motion information of linkage member 21, the linear movement information of pitch-changing push member 1221 can be determined, thereby determining the pitch information of blade 1032.

[0118] Referring to FIG. 5 , in some embodiments, the linkage 21 includes a rack 211 and a gear 212. The rack 211 is connected to the pitch-changing pusher 1221; the gear 212 meshes with the rack 211, and the signal acquisition unit 22 is configured to detect the rotational state of the gear 212. In this manner, the rack 211 and the pitch-changing pusher 1221 can move synchronously. The meshing transmission between the gear 212 and the rack 211 converts the linear motion of the pitch-changing pusher 1221 into the rotational motion of the gear 212. Therefore, the pitch information of the blade 1032 can be determined based on the rotational state information of the gear 212 detected by the signal acquisition unit 22.

[0119] 5 , in some embodiments, the rack 211 is fixedly connected to the variable pitch pusher 1221. For example, the rack 211 can be fixedly connected to any suitable position of the variable pitch pusher 1221, such as an end of the variable pitch pusher 1221 close to the second fixing member 121.

[0120] Exemplarily, the rotation state information of the linkage member 21 includes at least one of the following: a rotation angle of the gear 212 , a rotation acceleration of the gear 212 , a rotation direction of the gear 212 , and the like.

[0121] Exemplarily, the signal collecting component 22 includes an angle sensor (not shown), which detects the rotation state information of the linkage component 21 (such as the gear 212 ) through the angle sensor to determine the pitch of the blade 1032 .

[0122] Referring to FIG. 6 , in some embodiments, propeller base 1031 is provided with a bearing seat 10311, and blade 1032 is connected to bearing seat 10311 via a first bearing (not shown), so that blade 1032 can rotate relative to bearing seat 10311 or propeller base 1031, thereby adjusting the pitch of blade 1032. Exemplarily, the first bearing includes at least one of a needle bearing and a thrust bearing.

[0123] It is understood that the number of bearing seats 10311 provided on each propeller base 1031 can be designed based on actual needs, such as one, two, three, four, or more. Referring to FIG. 6 , for example, at least two bearing seats 10311 are spaced apart along the circumference of the propeller base 1031. Referring to FIG. 7 , for example, two adjacent bearing seats 10311 of the at least two bearing seats 10311 are connected to form a hollow structure, with the variable pitch push plate 1222 at least partially located within this hollow structure, thereby reducing the size and weight of the power output device 102.

[0124] Exemplarily, each bearing seat 10311 is connected to a corresponding blade 1032.

[0125] 5 and 6 , in some embodiments, pitch-changing push member 1221 is connected to blade 1032 via pitch-changing push plate 1222, which is rotatably mounted on pitch-changing push member 1221. For example, second movable member 122 or pitch-changing push plate 1222 is drivingly connected to blade 1032, so that second drive assembly 12 can drive blade 1032 to rotate relative to propeller base 1031, thereby changing the pitch of blade 1032.

[0126] Referring to Figures 5 and 6, in some embodiments, the pitch-changing push plate 1222 is provided with a first mating portion 12221, and the base of the blade 1032 is provided with a second mating portion 10321. The first mating portion 12221 slidably engages with the second mating portion 10321. When the pitch-changing push member 1221 moves, the pitch-changing push plate 1222 can follow the movement of the pitch-changing push member 1221. Through the sliding engagement between the first mating portion 12221 and the second mating portion 10321, the movement of the pitch-changing push plate 1222 is converted into rotation of the blade 1032, thereby adjusting the pitch of the blade 1032. It is understood that the pitch of the blade 1032 can be determined by detecting the movement information of the pitch-changing push member 1221.

[0127] Exemplarily, when adjusting the pitch of the blade 1032 , the linear movement direction of the pitch-changing push plate 1222 is the same as the linear movement direction of the pitch-changing push member 1221 .

[0128] Exemplarily, one of the first mating portion 12221 and the second mating portion 10321 includes at least one of the following: a mating pin, a slider, a guide rod, etc., and the other of the first mating portion 12221 and the second mating portion 10321 includes a sliding groove.

[0129] In some embodiments, the variable pitch push plate 1222 can be movably connected to the propeller base 1031. When the second drive assembly 12 is in operation, the variable pitch push member 1221 can drive the variable pitch push plate 1222 to move relative to the propeller base 1031 along the rotation axis of the propeller assembly 103, thereby causing the variable pitch push plate 1222 to drive the blades 1032 to rotate relative to the propeller base 1031, thereby adjusting the pitch of the blades 1032.

[0130] Referring to Figures 6 or 7 , in some embodiments, propeller base 1031 is provided with a guide rod 10312. Guide rod 10312 is used to limit the rotation of variable pitch push plate 1222 and guide the linear movement of variable pitch push plate 1222. When first drive assembly 11 is in operation, first movable member 112 can drive propeller base 1031 to rotate, and variable pitch push plate 1222 and blades 1032 can rotate in conjunction with propeller base 1031, thereby providing flight propulsion for aircraft 1000. When second drive assembly 12 is in operation, variable pitch push plate 1222 can move linearly relative to propeller base 1031 along the rotation axis of propeller assembly 103, driving blades 1032 to rotate, thereby adjusting the pitch of blades 1032 and, in turn, the thrust or lift of propeller assembly 103. For example, when the first drive assembly 11 is working, the first movable part 112 can drive the propeller base 1031 to rotate, and the variable pitch push plate 1222 and the blades 1032 can rotate along with the rotation of the propeller base 1031. The pull or lift of the propeller assembly 103 can be adjusted by controlling the rotation speed of the first drive assembly 11.

[0131] 8 and 9 , illustratively, pitch-changing push plate 1222 is connected to pitch-changing push member 1221 via a second bearing 1223 and a fixing nut 12252 (not shown). Pitch-changing push member 1221 can drive linear movement of pitch-changing push plate 1222. Thus, when first drive assembly 11 is operating, first movable member 112 can drive propeller base 1031 to rotate, which in turn drives pitch-changing push plate 1222 and blades 1032 to rotate relative to pitch-changing push member 1221. When second drive assembly 11 is operating, pitch-changing push member 1221 can drive pitch-changing push plate 1222 to move linearly relative to propeller base 1031 along the rotation axis of propeller assembly 103, thereby causing pitch-changing push plate 1222 to rotate blades 1032 and thereby adjust the pitch of blades 1032.

[0132] Referring to FIG. 8 , in some embodiments, the second movable member 122 includes a second rotor 1224, which is provided with a first threaded portion 12241. The variable pitch pusher 1221 is provided with a second threaded portion 12211. The first threaded portion 12241 and the second threaded portion 12211 are threadedly engaged with each other, resulting in a simple and reliable transmission structure and convenient and quick assembly of the second drive assembly 12. Furthermore, the threaded engagement between the first threaded portion 12241 and the second threaded portion 12211 can reduce the performance requirements of the second drive assembly 12 to a certain extent, thereby reducing the risk of failure of the second drive assembly 12. In other embodiments, the second rotor 1224 can also be connected to the variable pitch pusher 1221 via other connection methods, such as by integrally forming the second rotor 1224 and the variable pitch pusher 1221. Alternatively, the second rotor 1224 and the variable pitch pusher 1221 can be adhesively bonded.

[0133] Exemplarily, the second rotor 1224 is at least partially disposed outside the accommodating space. Referring to FIG. 8 , exemplary, the second rotor 1224 is disposed within the accommodating space 113 .

[0134] In some embodiments, the first threaded portion 12241 is an internal threaded portion, and the second threaded portion 12211 is an external threaded portion, as shown in FIG8 ; or the first threaded portion 12241 is an external threaded portion, and the second threaded portion 12211 is an internal threaded portion.

[0135] Referring to FIG. 10 , in some embodiments, the second movable member 122 includes a second rotor 1224 and a threaded transmission mechanism 1225. The threaded transmission mechanism 1225 is connected to the second rotor 1224, which is in turn connected to the variable-pitch pusher 1221, for converting the rotational motion of the second rotor 1224 into linear motion of the variable-pitch pusher 1221. The threaded transmission mechanism 1225 has a simple structure, occupies a small space, operates smoothly, has a large load capacity, and offers high transmission precision. The second rotor 1224 is connected to the variable-pitch pusher 1221 via the threaded transmission mechanism 1225, enabling self-locking at any position. This reduces the performance requirements for the second drive assembly 12, minimizes the risk of failure of the second drive assembly 12, and even in the event of failure, can reduce or avoid catastrophic accidents. This effectively improves the reliability of the second drive assembly 12 and the power output device 102, extending maintenance cycles and, to a certain extent, reducing maintenance costs.

[0136] For example, the linear movement direction of the variable pitch pusher 1221 is parallel to or coincides with the rotation axis of the propeller assembly 103. The movement stroke of the variable pitch pusher 1221 is simple, which facilitates full utilization of the space of the first drive assembly 11 in the direction of the rotation axis of the propeller assembly 103, and the structure of the power output device 102 is compact.

[0137] In some embodiments, the length extension direction of the pitch-changing push member 1221 is parallel to or coincides with the rotation axis of the propeller assembly 103 .

[0138] Referring to Figures 11 and 12, in some embodiments, the threaded transmission mechanism 1225 includes a screw 12251 and a nut 12252. The nut 12252 is threadedly engaged with the screw 12251, which is connected to the second rotor 1224. The nut 12252 is fixedly connected to the variable pitch pusher 1221. This eliminates the need to machine a threaded structure on the variable pitch pusher 1221, reducing the difficulty of machining the variable pitch pusher 1221. Furthermore, the threaded transmission mechanism 1225 of this structure is simple, and the nut 12252 can be fixedly connected to the variable pitch pusher 1221 at an appropriate position according to actual needs, thereby increasing the assembly flexibility of the second drive assembly 12 and reducing the difficulty of assembling the second drive assembly 12.

[0139] In some embodiments, the variable pitch pusher 1221 is coaxially disposed with the screw 12251, and the projections of the variable pitch pusher 1221 and the screw 12251 on the rotation axis of the propeller assembly 103 at least partially overlap. This allows the second drive assembly 12 to have a simple and compact structure, minimizing the size of the power output device 102 along the rotation axis of the propeller assembly 103. For example, the screw 12251 at least partially penetrates the variable pitch pusher 1221. In another example, the variable pitch pusher 1221 at least partially penetrates the screw 12251.

[0140] Referring to FIG. 11 , in some embodiments, the nut 12252 is passed through the detection mechanism 20. Exemplarily, the positional relationship of the different components of the power output device 102 includes at least one of the following: the nut 12252 is sleeved on the outside of the screw 12251; the linkage member 21 is sleeved on the outside of the screw 12251, and the linkage member 21 is sleeved on the outside of the nut 12252; the variable pitch push member 1221 is sleeved on the outside of the linkage member 21; and the signal collection member 22 is sleeved on the outside of the variable pitch push member 1221, thereby effectively reducing the space occupied by the power output device 102, making the structure of the power output device 102 more compact and effectively reducing the weight of the power output device 102.

[0141] Please refer to Figure 11. For example, the screw 12251 and the variable pitch push piece 1221 are respectively passed through the signal acquisition component 22, and the screw 12251 is passed through the variable pitch push piece 1221. After the detection mechanism 20 and the second drive component 12 are assembled, the assembly size of the structure composed of the detection mechanism 20 and the second drive component 12 along the rotation axis direction of the propeller assembly 103 is significantly smaller than the sum of the sizes of the detection mechanism 20 and the second drive component 12 along the rotation axis direction of the propeller assembly 103, thereby effectively compressing the size of the power output device 102, making the structure of the power output device 102 more compact.

[0142] Exemplarily, the fixed connection method between the nut 12252 and the variable pitch push piece 1221 includes at least one of the following: a snap connection, an adhesive connection, an interference fit connection, a screw locking connection, etc.

[0143] In other embodiments, the nut 12252 may also be fixedly connected to the linkage member 21 of the detection mechanism 20. In other embodiments, the screw 12251 may also be connected to the variable pitch pusher 1221 by other connection methods, such as the screw 12251 and the variable pitch pusher 1221 being integrally formed.

[0144] Please refer to Figures 11 and 12. For example, during assembly, at least part of the nut 12252 enters the linkage member 21 from the end of the linkage member 21 away from the second fixing member 121, part of the screw 12251 extends into the linkage member 21 from the end of the linkage member 21 close to the second fixing member 121, and at least part of the linkage member 21 extends into the variable-distance pushing member 1221 from the end of the variable-distance pushing member 1221 close to the second fixing member 121.

[0145] Please refer to FIG. 11 , illustratively, the nut 12252 is at least partially disposed in the linkage 21 , for example, most or all of the nut 12252 is disposed in the linkage 21 , so as to minimize the size of the power output device 102 .

[0146] For example, the structure and / or shape of the variable pitch push member 1221 in the various figures of this application are only exemplary and can be configured according to actual needs in actual applications. For example, the variable pitch push member 1221 includes a variable pitch push rod.

[0147] Exemplarily, the variable pitch push piece 1221 includes a hollow rod body, which on the one hand provides space for the screw 12251 to pass through the variable pitch push piece 1221, which is conducive to compressing the size of the power output device 102 along the rotation axis direction of the propeller assembly 103, so that the structure of the power output device 102 is compact; on the other hand, it can also reduce the weight of the power output device 102, reduce the flight resistance load of the aircraft 1000, and improve the performance of the aircraft 1000.

[0148] Please refer to FIG. 5 . In some embodiments, the driving mechanism 10 further includes a limiting structure 13 . The limiting structure 13 is used to limit the rotational movement of the nut 12252 and / or the variable-pitch pusher 1221 to achieve linear movement of the variable-pitch pusher 1221 .

[0149] Please refer to Figure 5. For example, the limiting structure 13 is mounted outside the variable pitch pusher 1221 to compress the size of the power output device 102 along the rotation axis of the propeller assembly 103, which is conducive to achieving a miniaturized design of the power output device 102 and the aircraft 1000.

[0150] Exemplarily, the limiting structure 13 is in position-limiting cooperation with the variable distance pusher 1221. Exemplarily, the limiting structure 13 can limit the rotational movement of the variable distance pusher 1221 and guide the linear movement of the variable distance pusher 1221 to a certain extent, so that the linear movement of the variable distance pusher 1221 is smoother.

[0151] Referring to Figure 5 , in some embodiments, the limiting structure 13 is provided separately from the signal acquisition component 22, and the limiting structure 13 is connected to the first fixing component 111 of the drive mechanism 10. This allows the structural layout and assembly position of the detection mechanism 20 to be flexibly configured according to actual needs. For example, the limiting structure 13 is spaced apart from the signal acquisition component 22. For example, both the limiting structure 13 and the signal acquisition component 22 are connected to the first fixing component 11.

[0152] Exemplarily, the limiting structure 13 is fixedly connected to the first fixing member 111 , and the connection method between the two includes at least one of the following: a snap connection, an adhesive connection, an interference fit connection, a screw locking connection, etc.

[0153] Illustratively, a limiting surface (not labeled) of the limiting structure 13 and a mating surface (not labeled) of the variable pitch pusher 1221 are in a limiting engagement with each other to limit the rotational movement of the nut 12252 and / or the variable pitch pusher 1221, thereby achieving linear movement of the variable pitch pusher 1221. Illustratively, the cross-section of the limiting structure 13 includes a non-circular shape, the cross-section of the outer contour of the variable pitch pusher 1221 includes a non-circular shape, and the limiting surface of the limiting structure 13 and the mating surface of the variable pitch pusher 1221 are in a limiting engagement with each other.

[0154] Exemplarily, one of the position-limiting structure 13 and the pitch-changing push member 1221 includes a guide groove (not shown) or a guide rod, and the other includes a sliding block or a sliding protrusion. Exemplarily, the length of the guide groove or the guide rod extends parallel to the rotation axis of the propeller assembly 103.

[0155] Referring to FIG. 10 , in some embodiments, the position-limiting structure 13 is integrally formed with the signal acquisition component 22. This integrally formed structure not only serves as a position limiter but also detects the motion state information of the linkage component 21, thereby reducing the number of components required and improving the assembly efficiency of the power output device 102. Furthermore, this integrally formed structure can also, to a certain extent, reduce the space occupied by the power output device 102 and reduce the weight of the power output device 102 to reduce flight drag loads. When the drive mechanism 10 is connected to the tilt mechanism 40 (see FIG. 14 ), the power output device 102 of this embodiment can also reduce the load and power of the tilt mechanism 40.

[0156] 5 , in some embodiments, the power output device 102 further includes a detection sensor 30 disposed on the second movable member 122 for detecting rotational state information of the second movable member 122. Exemplarily, the rotational state information of the second movable member 122 includes at least one of the following: a rotational angle, a rotational acceleration, and a rotational direction of the second movable member 122.

[0157] Exemplarily, the detection sensor 30 is provided on the second rotor 1224 and / or the screw 12251 .

[0158] Exemplarily, the detection sensor 30 includes a giant magnetoresistive (GMR) sensor.

[0159] Referring to FIG. 13 , in some embodiments, the power output device 102 further includes a tilt mechanism 40, which includes a connection base 41, a tilt connector 42, a tilt drive assembly 43, and a tilt transmission assembly 44. The connection base 41 is configured to connect to the fuselage body 101; the drive mechanism 10 is connected to the tilt connector 42. The tilt transmission assembly 44 is threadedly engaged with the tilt drive assembly 43 to convert at least a portion of the rotational motion of the tilt drive assembly 43 into linear motion of the tilt transmission assembly 44. The tilt transmission assembly 44 is connected to the tilt connector 42, which is rotatably connected to the connection base 41. The tilt transmission assembly 44 is configured to drive the tilt connector 42 to rotate relative to the connection base 41, thereby driving the drive mechanism 10 and the propeller assembly 103 to tilt. This allows the aircraft 1000 to meet the requirements of vertical takeoff and landing (VTOL) operations while also providing directional thrust for cruising in cruise mode. This effectively improves cruise efficiency and reduces cruise resistance, enabling the aircraft 1000 to perform a variety of flight missions.

[0160] Furthermore, because the tilt transmission assembly 44 and the tilt drive assembly 43 are threadedly coupled to each other to convert the rotational motion of the tilt drive assembly 43 into at least a portion of the linear motion of the tilt transmission assembly 44, the tilt transmission assembly 44 and the tilt drive assembly 43 can achieve self-locking at any position, reducing the impact of failure of the tilt drive assembly 43. Furthermore, the threaded connection method reduces the performance requirements of the tilt drive assembly 43 and reduces the risk of failure. Even if the tilt drive assembly 43 fails, catastrophic accidents can be avoided, significantly improving reliability, providing a longer maintenance cycle, and to a certain extent reducing maintenance costs.

[0161] Exemplarily, the tilting mechanism 40 can drive the driving mechanism 10 to tilt so that the propeller assembly 103 can switch between a first state and a second state, wherein the first state corresponds to the vertical take-off and landing working state of the aircraft 1000, and the second state corresponds to the cruising working state of the aircraft 1000.

[0162] Exemplarily, the propeller assembly 103 in the first state is shown in FIG14 , and the propeller assembly 103 in the second state is shown in FIG15 .

[0163] Exemplarily, the first state is a horizontal state, and the second state is a vertical state.

[0164] For example, when propeller assembly 103 is in the first state, the rotation axis of propeller assembly 103 is parallel to or coincides with the yaw axis of aircraft 1000. When propeller assembly 103 is in the second state, the rotation axis of propeller assembly 103 is perpendicular to the yaw axis of aircraft 1000.

[0165] For example, when the propeller assembly 103 is in the first state, if the aircraft 1000 needs to take off, the propeller assembly 103 in the first state can be driven by the drive mechanism 10 to rotate to generate a vertical upward pulling force or lift, thereby driving the aircraft 1000 to take off vertically. When the aircraft 1000 reaches a certain altitude, the tilt mechanism 40 can be used to drive the drive mechanism 10 to tilt until the propeller assembly 103 switches from the first state to the second state, thereby placing the aircraft 1000 in a cruising state.

[0166] In some embodiments, the connection base 41 is configured to be detachably connected to the fuselage body 101. This allows for a detachable connection between the tilt mechanism 40 and the fuselage body 101, thereby facilitating modularization of the aircraft 1000, facilitating assembly and disassembly of the power take-off device 102, and enhancing the maintainability and interchangeability of the power take-off device 102. If the power take-off device 102 or the tilt mechanism 40 malfunctions, is damaged, or requires maintenance, they can be promptly disassembled, replaced, or maintained without requiring the entire aircraft 1000 to be repaired or replaced, thereby reducing overall maintenance costs.

[0167] Exemplarily, the connection base 41 is used to connect to the arm 1012 of the aircraft 1000. Exemplarily, the connection base 41 is used to be detachably connected to the arm 1012, and the detachable connection between the two includes at least one of the following: screw connection, magnetic connection, snap connection, quick release locking connection, etc.

[0168] 13 and 16 , in some embodiments, the tilt drive assembly 43 includes a tilt drive member 431 and a speed regulator 432. The tilt drive member 431 is connected to the speed regulator 432, which is in turn connected to the tilt transmission assembly 44. The speed regulator 432 can adjust the speed of movement output by the tilt drive assembly 43.

[0169] Illustratively, the speed regulator 432 includes a speed reducer, which can reduce the output speed of the tilt drive 431 and increase the torque output by the tilt drive 431. Illustratively, the tilt drive 431 includes a motor or a servo. The speed regulator 432 includes a gear reduction structure, etc.

[0170] In other embodiments, the speed regulator 432 may also be omitted.

[0171] Exemplarily, the connection between the tilting connection member 42 and the driving mechanism 10 includes: the tilting connection member 42 is connected to the first driving component 11; or, the tilting connection member 42 is connected to the second driving component 12; or, both the first driving component 11 and the second driving component 12 are connected to the tilting connection member 42.

[0172] Referring to Figures 13 and 16 , in some embodiments, the tilt transmission assembly 44 includes a tilt push rod 441 and a transmission frame 442. The tilt push rod 441 is in transmission connection with the tilt drive assembly 43. The tilt push rod 441 and the tilt drive assembly 43 utilize a threaded transmission to convert the rotational motion of the tilt drive assembly 43 into linear motion of the tilt push rod 441. The transmission frame 442 is rotatably mounted on the connecting seat 41. The tilt push rod 441 is connected to the transmission frame 442 to drive the transmission frame 442 to rotate. The transmission frame 442 is connected to the tilt connector 42 to drive the rotation of the tilt connector 42. This structure of the tilt transmission assembly 44 enables smooth and reliable tilting of the tilt connector 42. The threaded transmission method can achieve self-locking at any position.

[0173] For example, when the propeller assembly 103 needs to switch from the first state to the second state, the tilt drive assembly 43 can drive at least a portion of the tilt push rod 441 to move linearly, so that the tilt push rod 441 drives the transmission frame 442 to move, thereby causing the transmission frame 442 to drive the tilt connection 42 to rotate relative to the connection seat 41, thereby driving the drive mechanism 10 and the propeller assembly 103 to rotate in the first rotation direction until the propeller assembly 103 is in the second state. When the propeller assembly 103 needs to switch from the second state to the first state, the tilt drive assembly 43 can drive at least a portion of the tilt push rod 441 to move linearly, so that the tilt push rod 441 drives the transmission frame 442 to move, thereby causing the transmission frame 442 to drive the tilt connection 42 to rotate relative to the connection seat 41, thereby driving the drive mechanism 10 and the propeller assembly 103 to rotate in the second rotation direction until the propeller assembly 103 is in the first state, the second rotation direction being opposite to the first rotation direction.

[0174] Exemplarily, the first rotation direction is shown as the direction of the dotted arrow W in FIG. 14 .

[0175] Referring to Figure 16 , the tilt actuator 441 illustratively includes a first transmission portion 4411 and a second transmission portion 4412. The first transmission portion 4411 is in driving connection with the tilt drive assembly 43, while the second transmission portion 4412 is threadedly engaged with the first transmission portion 4411, which is then connected to the transmission frame 442. The threaded transmission within the tilt actuator 441 converts the rotational motion of the tilt drive assembly 43 into linear motion of the second transmission portion 4412, resulting in a simple and compact structure.

[0176] Referring to Figures 13 and 16 , in some embodiments, the transmission frame 442 includes a first bracket 4421, a second bracket 4422, and a third bracket 4423. One end of the first bracket 4421 is hingedly connected to the tilt connector 42, and the other end of the first bracket 4421 is hingedly connected to the connecting base 41. One end of the second bracket 4422 is hingedly connected to the connecting base 41, and the other end of the second bracket 4422 is hingedly connected to the third bracket 4423. The end of the third bracket 4423, which is remote from the second bracket 4422, is hingedly connected to the tilt connector 42. This structure of the transmission frame 442 can maximize the tilting range of the tilt connector 42.

[0177] 13 and 16 , in some embodiments, one end of a first bracket 4421 is hingedly connected to the tilt connector 42 via a first connecting shaft 443, the other end of the first bracket 4421 is hingedly connected to the connecting base 41 via a second connecting shaft 444, one end of a second bracket 4422 is hingedly connected to the connecting base 41 via a third connecting shaft 445, the other end of the second bracket 4422 is hingedly connected to the third bracket 4423 via a fourth connecting shaft 446, and the end of the third bracket 4423 away from the second bracket 4422 is hingedly connected to the tilt connector 42 via a fifth connecting shaft 447. Exemplarily, the second bracket 4422 is connected to the tilt push rod 441 via a sixth connecting shaft 448, so that the tilt push rod 441 can push the second bracket 4422 to move, thereby driving the tilt connector 42 to rotate.

[0178] Exemplarily, the first bracket 4421 , the second bracket 4422 , the third bracket 4423 , the tilting connector 42 and the connecting seat 41 cooperate to form a five-bar linkage.

[0179] In some embodiments, the transmission frame 442 includes a first bracket 4421, a second bracket 4422 and a third bracket 4423 connected in sequence, one end of the first bracket 4421 is hinged to the tilt connection 42, the other end of the first bracket 4421 is hinged to the second bracket 4422, the end of the second bracket 4422 away from the first bracket 4421 is hinged to the third bracket 4423, and the end of the third bracket 4423 away from the second bracket 4422 is hinged to the tilt connection 42. The structure of the transmission frame 442 is simple, the movement of the tilt connection 42 is controllable, and the tilt mechanism 40 can reliably control the tilting of the driving mechanism 10.

[0180] Exemplarily, the first bracket 4421 , the second bracket 4422 , the third bracket 4423 and the tilting connection member 42 cooperate to form a four-bar linkage.

[0181] In some embodiments, the tilt transmission assembly 44 is threadedly engaged with the tilt drive assembly 43. Referring to Figure 17, illustratively, the tilt drive assembly 43 includes a tilt screw 433, and the tilt transmission assembly 44 includes a tilt nut (not shown), and the tilt screw 433 is threadedly engaged with the tilt nut. Through the threaded transmission of the tilt screw 433 and the tilt nut, the rotational motion of the tilt drive assembly 43 is converted into linear motion of the tilt nut, and the tilt screw 433 and the tilt nut can be self-locked at any position, reducing the impact caused by the failure of the tilt drive assembly 43, lowering the performance requirements of the tilt drive assembly 43, and reducing the risk of failure. Even if the tilt drive assembly 43 fails, catastrophic accidents can be avoided, and reliability is significantly improved. Exemplarily, the propeller assembly 103 connected to the tilt mechanism 40 of this embodiment is in the first state as shown in Figure 18, and in the second state as shown in Figure 19.

[0182] Referring to Figure 17 , in some embodiments, the tilt transmission assembly 44 is connected to the tilt connector 42 via a seventh connecting shaft 449, and the tilt connector 42 is hinged to the connecting base 41 via an eighth connecting shaft 450. As will be appreciated, the connection point between the tilt transmission assembly 44 and the tilt connector 42 (e.g., the seventh connecting shaft 449) is located away from the rotation point of the tilt connector 42 relative to the connecting base 41 (e.g., the eighth connecting shaft 450). This results in a relatively small load on the tilt drive assembly 43 and improved rigidity. This reduces the risk of abnormal wear or vibration, thereby reducing maintenance costs and safety risks associated with vibration.

[0183] Referring to Figures 13 or 20 , in some embodiments, the tilt mechanism 40 further includes a detection sensor 46 for detecting the rotation angle of the tilt connection 42. Referring to Figure 13 , illustratively, the detection sensor 46 is disposed on at least one of the tilt connection 42 or the transmission frame 442. The detection sensor 46 is capable of detecting motion information of the tilt connection 42 or the transmission frame 442, thereby detecting the rotation angle of the tilt connection 42. Exemplarily, the detection sensor 46 is disposed on the tilt connection 42 or at the connection between the tilt connection 42 and the transmission frame 442.

[0184] Please refer to FIG. 20 , illustratively, the detection sensor 46 is used to detect the movement displacement of the tilt nut, thereby indirectly detecting the rotation angle of the tilt connection 42 .

[0185] An embodiment of the present application also provides an aircraft 1000, including a fuselage body 101, a power output device 102 and a propeller assembly 103. The power output device 102 is arranged on the fuselage body 101, and the power output device 102 is used to drive the propeller assembly 103; wherein, the power output device 102 includes a driving mechanism 10 and a detection mechanism 20, the driving mechanism 10 is used to drive the propeller assembly 103 to rotate to provide flight power for the aircraft 1000 and drive the blades 1032 of the propeller assembly 103 to rotate to adjust the pitch of the blades 1032, and the detection mechanism 20 is configured to be able to detect the pitch information of the blades 1032; wherein, an accommodating space 113 is provided on the inner side of the driving mechanism 10, and the detection mechanism 20 is at least partially arranged in the accommodating space 113.

[0186] In the aircraft 1000 of the above embodiment, since an accommodating space 113 is provided on the inner side of the driving mechanism 10, and the detection mechanism 20 is at least partially provided in the accommodating space 113, the overall size of the power output device 102 can be compressed to a certain extent. The structural design of the power output device 102 is reasonable and compact. The power output device 102 can be flexibly arranged and has strong adaptability, which reduces the adverse effects of the power output device 102 on the overall design of the aircraft 1000, is conducive to making better optimization results for the overall design, and provides a guarantee for the normal use of the aircraft.

[0187] Illustratively, aircraft 1000 comprises the aircraft 1000 of any of the aforementioned embodiments. Airframe 101 comprises the airframe 101 of any of the aforementioned embodiments. Power output device 102 comprises the power output device 102 of any of the aforementioned embodiments. Propeller assembly 103 comprises the propeller assembly 103 of any of the aforementioned embodiments. Drive mechanism 10 comprises the drive mechanism 10 of any of the aforementioned embodiments. Detection mechanism 20 comprises the detection mechanism 20 of any of the aforementioned embodiments.

[0188] In some embodiments, the drive mechanism 10 includes:

[0189] The first driving assembly 11 is used to drive the propeller assembly 103 to rotate, thereby providing flight power for the aircraft 1000; and

[0190] The second driving assembly 12 is used to drive the blade 1032 to rotate, thereby adjusting the pitch of the blade 1032;

[0191] The first driving assembly 11 or the second driving assembly 12 defines an accommodating space 113 .

[0192] It is understandable that in this embodiment, the second movable part 122 of the second drive assembly 12 can be connected to the blade 1032 through a transmission, thereby driving the blade 1032 to rotate to adjust the pitch of the blade 1032, and then adjusting the tension or lift of the propeller assembly 103 to adapt to at least two working states such as vertical take-off and landing and cruising, so that the propeller assembly 103 can operate efficiently in both the vertical take-off and landing working state and the cruising working state, thereby improving the endurance performance of the entire aircraft. When the tension or lift of the propeller assembly 103 changes, the tension or lift of the propeller assembly 103 can be adjusted by controlling the speed of the first drive assembly 11 according to actual needs; and / or, the pitch of the blade 1032 can be adjusted by the second drive assembly 12, thereby adjusting the tension or lift of the propeller assembly 103.

[0193] In some embodiments, the first drive component 11 is provided with a accommodating space 113, the second drive component 12 includes a variable pitch pusher 1221 capable of driving the blade 1032 to rotate, the variable pitch pusher 1221 passes through the accommodating space 113 and is connected to the blade 1032, and the detection mechanism 20 is at least partially provided in the accommodating space 113 to detect the movement information of the variable pitch pusher 1221.

[0194] In some embodiments, the pitch-changing push piece 1221 is configured to be able to move back and forth along the rotation axis of the propeller assembly 103 to drive the blade 1032 to rotate; the detection mechanism 20 is used to detect the movement stroke of the pitch-changing push piece 1221 to determine the pitch information of the blade 1032.

[0195] In some embodiments, the detection mechanism 20 includes:

[0196] The linkage member 21 is connected to the variable pitch push member 1221;

[0197] The signal collecting component 22 is provided corresponding to the linkage component 21 , and is used to detect the motion state information of the linkage component 21 and determine the pitch information of the blade 1032 according to the motion state information.

[0198] In some embodiments, the linkage member 21 moves synchronously with the variable-distance push member 1221 , and the signal acquisition member 22 is configured to acquire linear movement information of the linkage member 21 .

[0199] In some embodiments, the signal collecting component 22 includes a hollow structure, and the linkage component 21 and the variable distance pushing component 1221 are at least partially disposed in the signal collecting component 22 .

[0200] In some embodiments, the linkage member 21 and the pitch-changing push member 1221 at least partially overlap in the direction of the rotation axis of the propeller assembly 103 .

[0201] In some embodiments, the linkage member 21 is used to convert the linear motion of the variable-pitch push member 1221 into rotational motion, and the signal acquisition member 22 is used to detect the rotational state information of the linkage member 21 .

[0202] In some embodiments, the linkage 21 includes:

[0203] The rack 211 is connected to the pitch-variable push member 1221;

[0204] The gear 212 is meshed with the rack 211 , and the signal collecting component 22 is used to detect the rotation state information of the gear 212 .

[0205] In some embodiments, the pitch-varying push member 1221 is connected to the blade 1032 through the pitch-varying push plate 1222. The pitch-varying push plate 1222 is rotatably mounted on the pitch-varying push member 1221. The pitch-varying push plate 1222 is provided with a first matching portion 12221, and the root of the blade 1032 is provided with a second matching portion 10321. The first matching portion 12221 and the second matching portion 10321 are slidably matched; when the pitch-varying push member 1221 moves, the pitch-varying push plate 1222 moves with the pitch-varying push member 1221, and through the sliding fit between the first matching portion 12221 and the second matching portion 10321, the movement of the pitch-varying push plate 1222 is converted into the rotation of the blade 1032.

[0206] In some embodiments, the first drive assembly 11 includes a first fixed member 111 and a first movable member 112 that moves relative to the first fixed member 111, and the first movable member 112 is used to be connected to the propeller assembly 103 in a transmission manner; the second drive assembly 12 includes a second fixed member 121 connected to the first fixed member 111 and a second movable member 122 that moves relative to the second fixed member 121, and the second movable member 122 is used to be connected to the blade 1032 in a transmission manner; when the first drive assembly 11 drives the propeller assembly 103 to rotate, the second fixed member 121 is stationary relative to the first fixed member 111.

[0207] In some embodiments, the first driving assembly 11 includes a first motor, the first fixing member 111 includes a first coil 1111 , the second driving assembly 12 includes a second motor, and the second fixing member 121 includes a second coil 1211 .

[0208] In some embodiments, the first drive assembly 11 includes a first fixed member 111 and a first movable member 112 that moves relative to the first fixed member 111, and the first movable member 112 is used for transmission connection with the propeller assembly 103; the second drive assembly 12 includes a second fixed member 121 connected to the first fixed member 111 and a second movable member 122 that moves relative to the second fixed member 121, and the second movable member 122 is used for transmission connection with the blade 1032;

[0209] The accommodating space 113 passes through the first driving assembly 11 in the direction of the rotation axis of the propeller assembly 103 . The second fixing member 121 and the propeller assembly 103 respectively close the accommodating space 113 from both ends thereof.

[0210] In some embodiments, an accommodating space 113 is defined inside the first fixing member 111 , the first movable member 112 is disposed outside the first fixing member 111 , and the second fixing member 121 is disposed outside or inside the accommodating space 113 .

[0211] In some embodiments, the second drive assembly 12 includes a second fixed member 121 and a second movable member 122 that moves relative to the second fixed member 121. The second movable member 122 includes a second rotor 1224, a threaded transmission mechanism 1225, and a variable pitch push member 1221 that can drive the blades 1032 to rotate. The second rotor 1224 is connected to the threaded transmission mechanism 1225, and the threaded transmission mechanism 1225 is connected to the variable pitch push member 1221, which is used to convert the rotational motion of the second rotor 1224 into linear movement of the variable pitch push member 1221.

[0212] In some embodiments, the threaded transmission mechanism 1225 includes a screw 12251 and a nut 12252 threadedly engaged with the screw 12251 . The screw 12251 is connected to the second rotor 1224 , and the nut 12252 is fixedly connected to the variable pitch pusher 1221 .

[0213] In some embodiments, a limiting structure 13 is further included, and the limiting structure 13 is used to limit the rotational movement of the nut 12252 and / or the variable-distance pusher 1221 to achieve linear movement of the variable-distance pusher 1221.

[0214] In some embodiments, the power output device 102 further includes a tilting mechanism 40, which includes:

[0215] A connecting seat 41 is used to connect to the fuselage body 101;

[0216] The tilting connecting member 42 is rotatably connected to the connecting seat 41, and the driving mechanism 10 is connected to the tilting connecting member 42;

[0217] Tilt drive assembly 43; and

[0218] The tilt transmission assembly 44 is rotatably connected to the connecting seat 41; it cooperates with the tilt drive assembly 43 in threaded transmission to convert the rotational motion of the tilt drive assembly 43 into at least part of the linear motion of the tilt transmission assembly 44; the tilt transmission assembly 44 is connected to the tilt connection member 42, and is used to drive the tilt connection member 42 to rotate relative to the connecting seat 41, thereby driving the drive mechanism 10 and the propeller assembly 103 to tilt.

[0219] In some embodiments, the tilt transmission assembly 44 includes:

[0220] The tilt push rod 441 is in transmission connection with the tilt drive assembly 43. The tilt push rod 441 and the tilt drive assembly 43 are threadedly connected to convert the rotational motion of the tilt drive assembly 43 into linear motion of the tilt push rod 441; and

[0221] The transmission frame 442 is rotatably disposed on the connecting seat 41 . The tilt push rod 441 is connected to the transmission frame 442 to drive the transmission frame 442 to rotate. The transmission frame 442 is connected to the tilt connecting member 42 to drive the tilt connecting member 42 to rotate.

[0222] In some embodiments, the transmission frame 442 includes a first bracket 4421, a second bracket 4422 and a third bracket 4423 connected in sequence, one end of the first bracket 4421 is hinged to the tilt connection 42, and the other end is hinged to the second bracket 4422, the end of the second bracket 4422 away from the first bracket 4421 is hinged to the third bracket 4423, and the end of the third bracket 4423 away from the second bracket 4422 is hinged to the tilt connection 42.

[0223] In some embodiments, the connection base 41 is used for detachable connection with the fuselage body 101 .

[0224] In some embodiments, a control module 104 is further included, and the power output device 102 is electrically connected to the control module 104 .

[0225] In some embodiments, the control module 104 is configured to adjust the operating state or operating parameters of the aircraft 1000 according to the pitch information detected by the detection mechanism.

[0226] In some embodiments, the operating status includes at least one of the operating status of the fuselage body 101, the operating status of the load attached to the fuselage body 101, the operating status of the power output device 102, and the operating status of the propeller assembly 103, and the operating parameters include at least one of the operating parameters of the fuselage body 101, the operating parameters of the load attached to the aircraft 1000, the operating parameters of the power output device 102, and the operating parameters of the propeller assembly 103.

[0227] In some embodiments, the operating parameter of the propeller assembly 103 includes at least one of the pitch of the blades 1032 , the rotation speed of the propeller assembly 103 , and the rotation direction of the propeller assembly 103 .

[0228] In some embodiments, the propeller assembly 103 includes a propeller base 1031 and a plurality of blades 1032 disposed on the propeller base 1031. The propeller assembly 103 is configured to be able to rotate to provide flight power for the aircraft 1000, and the blades 1032 are configured to be able to rotate relative to the propeller base 1031 to change the pitch of the blades 1032.

[0229] It is understandable that if the second fixed member 121 of the second drive assembly 12 is connected to the first movable member 112 of the first drive assembly 11, when the first drive assembly 11 drives the propeller assembly 103 to rotate, the second fixed member 121 will follow the rotation of the first movable member 112 and move. It is necessary to design a slip ring structure or a brush structure between the first drive assembly 11 and the second drive assembly 12. The power output device 102 of this structure is not conducive to the routing of the second drive assembly 12. When the second fixed member 121 follows the movement of the first movable member 112, the routing of the second drive assembly 12 is prone to shaking, entanglement or damage, resulting in unreliable electrical connection and control failure. In addition, this structure may also have at least one of the following shortcomings: easy wear and tear, short life, and frequent maintenance or replacement is required; poor corrosion resistance, and electric shock corrosion leads to control failure; the volume and reliability of the slip ring structure or brush structure lead to insufficient reliability and safety of the power output device 102, limiting the application of the power output device 102.

[0230] To this end, an embodiment of the present application further provides an aircraft 1000, comprising a fuselage body 101, a power output device 102, and a propeller assembly 103. The power output device 102 is disposed on the fuselage body 101 and is used to drive the propeller assembly 103. The power output device 102 includes a drive mechanism 10, which includes:

[0231] A first drive assembly 11 is configured to drive the propeller assembly 103 to rotate, thereby providing flight power for the aircraft 1000. The first drive assembly 11 includes a first fixed member 111 and a first movable member 112 that moves relative to the first fixed member 111. The first movable member 112 is configured to be in transmission connection with the propeller assembly 103 to drive the propeller assembly 103 to rotate.

[0232] The second drive assembly 12 is used to drive the blades 1032 of the propeller assembly 103 to rotate, thereby adjusting the pitch of the blades 1032. The second drive assembly 12 includes a second fixed member 121 and a second movable member 122 that moves relative to the second fixed member 121. The second movable member 122 is in driving connection with the blades 1032.

[0233] The second fixing member 121 is connected to the first fixing member 111 . When the first driving assembly 11 drives the propeller assembly 103 to rotate, the second fixing member 121 remains stationary relative to the first fixing member 111 .

[0234] In the aircraft 1000 of the above embodiment, when the first drive assembly 11 drives the propeller assembly 103 to rotate, the second fixed member 121 of the second drive assembly 12 remains stationary relative to the first fixed member 111 of the first drive assembly 11. The connecting cable connecting the second drive assembly 12 (e.g., the second fixed member 121) and other components (e.g., the control module 104 in FIG4 ) does not need to move with the rotation of the first movable member 112 of the first drive assembly 11. This facilitates wiring, ensures stable and reliable routing, and is less likely to cause control failure, thereby improving the reliability and safety of the power output device 102 and reducing maintenance costs. Furthermore, because the second fixed member 121 is connected to the first fixed member 111, the first drive assembly 11 and the second drive assembly 12 are relatively less susceptible to wear when the power output device 102 is operating, which helps extend the service life of the power output device 102 and reduce the number of times the power output device 102 is maintained or replaced. Furthermore, the power output device 102 is less susceptible to electric shock corrosion and has good corrosion resistance. Furthermore, the power output device 102 has a simple structure and is easy to control.

[0235] Illustratively, the aircraft 1000 includes the aircraft 1000 of any of the aforementioned embodiments. The fuselage body 101 includes the fuselage body 101 of any of the aforementioned embodiments. The power output device 102 includes the power output device 102 of any of the aforementioned embodiments. The propeller assembly 103 includes the propeller assembly 103 of any of the aforementioned embodiments.

[0236] In some embodiments, the power output device 102 further includes:

[0237] The detection mechanism 20 is configured to detect the pitch information of the blade 1032;

[0238] An accommodating space 113 is defined inside the first fixing member 111 , and the detection mechanism 20 is at least partially disposed in the accommodating space 113 .

[0239] In some embodiments, the second movable member 122 includes a variable pitch pusher 1221 capable of driving the blade 1032 to rotate. The variable pitch pusher 1221 passes through the accommodating space 113 and is connected to the blade 1032. The detection mechanism 20 is at least partially disposed in the accommodating space 113 to detect movement information of the variable pitch pusher 1221.

[0240] In some embodiments, the pitch-changing push piece 1221 is configured to be able to move back and forth along the rotation axis of the propeller assembly 103 to drive the blade 1032 to rotate; the detection mechanism 20 is used to detect the movement stroke of the pitch-changing push piece 1221 to determine the pitch information of the blade 1032.

[0241] In some embodiments, the detection mechanism 20 includes:

[0242] The linkage member 21 is connected to the variable pitch push member 1221;

[0243] The signal collecting component 22 is provided corresponding to the linkage component 21 , and is used to detect the motion state information of the linkage component 21 and determine the pitch information of the blade 1032 according to the motion state information.

[0244] In some embodiments, the linkage member 21 moves synchronously with the variable-distance push member 1221 , and the signal acquisition member 22 is configured to acquire linear movement information of the linkage member 21 .

[0245] In some embodiments, the signal collecting component 22 includes a hollow structure, and the linkage component 21 and the variable distance pushing component 1221 are at least partially disposed in the signal collecting component 22 .

[0246] In some embodiments, the linkage member 21 and the pitch-changing push member 1221 at least partially overlap in the direction of the rotation axis of the propeller assembly 103 .

[0247] In some embodiments, the linkage member 21 is used to convert the linear motion of the variable-pitch push member 1221 into rotational motion, and the signal acquisition member 22 is used to detect the rotational state information of the linkage member 21 .

[0248] In some embodiments, the linkage 21 includes:

[0249] The rack 211 is connected to the pitch-variable push member 1221;

[0250] The gear 212 is meshed with the rack 211 , and the signal collecting component 22 is used to detect the rotation state information of the gear 212 .

[0251] In some embodiments, the pitch-changing push member 1221 is connected to the blade 1032 via a pitch-changing push plate 1222. The pitch-changing push plate 1222 is rotatably mounted on the pitch-changing push member 1221. The pitch-changing push plate 1222 has a first mating portion 12221. The root of the blade 1032 has a second mating portion 10321. The first mating portion 12221 and the second mating portion 10321 are slidably engaged with each other.

[0252] When the pitch-changing push piece 1221 moves, the pitch-changing push plate 1222 moves along with the pitch-changing push piece 1221 , and the movement of the pitch-changing push plate 1222 is converted into the rotation of the blade 1032 through the sliding fit of the first matching portion 12221 and the second matching portion 10321 .

[0253] In some embodiments, the second movable member 122 includes a second rotor 1224 and a threaded transmission mechanism 1225 connected to the second rotor 1224 . The threaded transmission mechanism 1225 is connected to the variable pitch pusher 1221 for converting the rotational motion of the second rotor 1224 into linear movement of the variable pitch pusher 1221 .

[0254] In some embodiments, the threaded transmission mechanism 1225 includes a screw 12251 and a nut 12252 threadedly engaged with the screw 12251 . The screw 12251 is connected to the second rotor 1224 , and the nut 12252 is fixedly connected to the variable pitch pusher 1221 .

[0255] In some embodiments, a limiting structure 13 is further included, and the limiting structure 13 is used to limit the rotational movement of the nut 12252 and / or the variable-distance pusher 1221 to achieve linear movement of the variable-distance pusher 1221.

[0256] In some embodiments, the accommodating space 113 passes through the first driving assembly 11 in the direction of the rotation axis of the propeller assembly 103 , and the second fixing member 121 and the propeller assembly 103 respectively close the accommodating space 113 from both ends thereof.

[0257] In some embodiments, an accommodating space 113 is defined inside the first fixing member 111 , the first movable member 112 is disposed outside the first fixing member 111 , and the second fixing member 121 is disposed outside or inside the accommodating space 113 .

[0258] In some embodiments, the first driving assembly 11 includes a first motor, the first fixing member 111 includes a first coil 1111 , the second driving assembly 12 includes a second motor, and the second fixing member 121 includes a second coil 1211 .

[0259] In some embodiments, the power output device 102 further includes a tilting mechanism 40, which includes:

[0260] A connecting seat 41 is used to connect to the fuselage body 101;

[0261] A tilting connection member 42, wherein the driving mechanism 10 is connected to the tilting connection member 42;

[0262] Tilt drive assembly 43; and

[0263] The tilt transmission assembly 44 is rotatably connected to the connecting seat 41; it cooperates with the tilt drive assembly 43 in threaded transmission to convert the rotational motion of the tilt drive assembly 43 into at least part of the linear motion of the tilt transmission assembly 44; the tilt transmission assembly 44 is connected to the tilt connection member 42, and is used to drive the tilt connection member 42 to rotate relative to the connecting seat 41, thereby driving the drive mechanism 10 and the propeller assembly 103 to tilt.

[0264] In some embodiments, the tilt transmission assembly 44 includes:

[0265] The tilt push rod 441 is in transmission connection with the tilt drive assembly 43. The tilt push rod 441 and the tilt drive assembly 43 are threadedly connected to convert the rotational motion of the tilt drive assembly 43 into linear motion of the tilt push rod 441; and

[0266] The transmission frame 442 is rotatably disposed on the connecting seat 41 . The tilt push rod 441 is connected to the transmission frame 442 to drive the transmission frame 442 to rotate. The transmission frame 442 is connected to the tilt connecting member 42 to drive the tilt connecting member 42 to rotate.

[0267] In some embodiments, the transmission frame 442 includes a first bracket 4421, a second bracket 4422 and a third bracket 4423 connected in sequence, one end of the first bracket 4421 is hinged to the tilt connection 42, and the other end is hinged to the second bracket 4422, the end of the second bracket 4422 away from the first bracket 4421 is hinged to the third bracket 4423, and the end of the third bracket 4423 away from the second bracket 4422 is hinged to the tilt connection 42.

[0268] In some embodiments, the connection base 41 is used for detachable connection with the fuselage body 101 .

[0269] In some embodiments, a control module 104 is further included, and the power output device 102 is electrically connected to the control module 104 .

[0270] In some embodiments, the control module 104 is configured to adjust the operating state or operating parameters of the aircraft 1000 according to the pitch information detected by the detection mechanism.

[0271] In some embodiments, the operating status includes at least one of the operating status of the fuselage body 101, the operating status of the load attached to the fuselage body 101, the operating status of the power output device 102, and the operating status of the propeller assembly 103, and the operating parameters include at least one of the operating parameters of the fuselage body 101, the operating parameters of the load attached to the aircraft 1000, the operating parameters of the power output device 102, and the operating parameters of the propeller assembly 103.

[0272] In some embodiments, the operating parameter of the propeller assembly 103 includes at least one of the pitch of the blades 1032 , the rotation speed of the propeller assembly 103 , and the rotation direction of the propeller assembly 103 .

[0273] In some embodiments, the propeller assembly 103 includes a propeller base 1031 and a plurality of blades 1032 disposed on the propeller base 1031. The propeller assembly 103 is configured to be able to rotate to provide flight power for the aircraft 1000, and the blades 1032 are configured to be able to rotate relative to the propeller base 1031 to change the pitch of the blades 1032.

[0274] The embodiment of the present application provides a power output device 102, including a drive mechanism 10, which includes:

[0275] A first drive assembly 11 is configured to drive the propeller assembly 103 to rotate, thereby providing flight power for the aircraft 1000. The first drive assembly 11 includes a first fixed member 111 and a first movable member 112 that moves relative to the first fixed member 111. The first movable member 112 is configured to be in transmission connection with the propeller assembly 103 to drive the propeller assembly 103 to rotate. The first drive assembly 11 is provided with an accommodating space 113.

[0276] The second drive assembly 12 is used to drive the blades 1032 of the propeller assembly 103 to rotate, thereby adjusting the pitch of the blades 1032. The second drive assembly 12 includes a second fixed member 121 and a second movable member 122 that moves relative to the second fixed member 121. The second movable member 122 is configured to be in driving connection with the blades 1032. The second movable member 122 includes a pitch-changing push member 1221 that can drive the blades 1032 to rotate. The pitch-changing push member 1221 passes through the accommodating space 113 and is connected to the blades 1032.

[0277] The accommodating space 113 passes through the first driving assembly 11 in the direction of the rotation axis of the propeller assembly 103 . The second fixing member 121 and the propeller assembly 103 respectively close the accommodating space 113 from both ends thereof.

[0278] The power output device 102 of the above embodiment, since the first drive assembly 11 is provided with an accommodating space 113, the pitch-variable push piece 1221 passes through the accommodating space 113 and is connected to the blade 1032, can thus compress the overall size of the power output device 102 to a certain extent. The structural design of the power output device 102 is reasonable and compact. The power output device 102 can be flexibly arranged and has strong adaptability, which reduces the adverse effects of the power output device 102 on the overall design of the aircraft 1000, is conducive to making better optimization results for the overall design, and provides a guarantee for the normal use of the aircraft 1000.

[0279] It is understandable that in this embodiment, the second movable part 122 of the second drive assembly 12 can be connected to the blade 1032 through a transmission, thereby driving the blade 1032 to rotate to adjust the pitch of the blade 1032, and then adjusting the tension or lift of the propeller assembly 103 to adapt to at least two working states such as vertical take-off and landing and cruising, so that the propeller assembly 103 can operate efficiently in both the vertical take-off and landing working state and the cruising working state, thereby improving the endurance performance of the entire aircraft. When the tension or lift of the propeller assembly 103 changes, the tension or lift of the propeller assembly 103 can be adjusted by controlling the speed of the first drive assembly 11 according to actual needs; and / or, the pitch of the blade 1032 can be adjusted by the second drive assembly 12, thereby adjusting the tension or lift of the propeller assembly 103.

[0280] Furthermore, because the second fixing member 121 of the first drive assembly 11 and the propeller assembly 103 of the aircraft 1000 seal both ends of the accommodating space 113 that extends through the first drive assembly 11, external media (such as at least one of liquid, gas, or dust) are prevented from entering the accommodating space 113 through both ends and affecting the performance of the components within the accommodating space 113, thereby improving the protection performance of the drive mechanism 10. Furthermore, the second fixing member 121 and the propeller assembly 103, respectively sealing the accommodating space 113 from both ends, fully utilize the space occupied by the first drive assembly 11, making the structure of the power output device 102 compact and facilitating better optimization of the overall design.

[0281] Exemplarily, the power output device 102 includes the power output device 102 of any one of the above embodiments. The drive mechanism 10 includes the drive mechanism 10 of any one of the above embodiments. The propeller assembly 103 includes the propeller assembly 103 of any one of the above embodiments.

[0282] In some embodiments, further comprising:

[0283] The detection mechanism 20 is configured to detect the pitch information of the blade 1032;

[0284] The detection mechanism 20 is at least partially disposed in the accommodating space 113 to detect movement information of the variable-distance pushing member 1221 .

[0285] In some embodiments, the pitch-changing push member 1221 is configured to be able to reciprocate along the rotation axis of the propeller assembly 103 to drive the blades 1032 to rotate;

[0286] The detection mechanism 20 is used to detect the movement stroke of the pitch-changing push member 1221 to determine the pitch information of the blade 1032 .

[0287] In some embodiments, the detection mechanism 20 includes:

[0288] The linkage member 21 is connected to the variable pitch push member 1221;

[0289] The signal collecting component 22 is provided corresponding to the linkage component 21 , and is used to detect the motion state information of the linkage component 21 and determine the pitch information of the blade 1032 according to the motion state information.

[0290] In some embodiments, the linkage member 21 moves synchronously with the variable-distance push member 1221 , and the signal acquisition member 22 is configured to acquire linear movement information of the linkage member 21 .

[0291] In some embodiments, the linkage member 21 is used to convert the linear motion of the variable-pitch push member 1221 into rotational motion, and the signal acquisition member 22 is used to detect the rotational state information of the linkage member 21 .

[0292] In some embodiments, the second fixing member 121 is connected to the first fixing member 111 . When the first driving assembly 11 drives the propeller assembly 103 to rotate, the second fixing member 121 remains stationary relative to the first fixing member 111 .

[0293] In some embodiments, an accommodating space 113 is defined inside the first fixing member 111 , the first movable member 112 is disposed outside the first fixing member 111 , and the second fixing member 121 is disposed outside or inside the accommodating space 113 .

[0294] In some embodiments, the second movable member 122 includes a second rotor 1224 and a threaded transmission mechanism 1225 connected to the second rotor 1224 . The threaded transmission mechanism 1225 is connected to the variable pitch pusher 1221 for converting the rotational motion of the second rotor 1224 into linear movement of the variable pitch pusher 1221 .

[0295] In some embodiments, the threaded transmission mechanism 1225 includes a screw 12251 and a nut 12252 threadedly engaged with the screw 12251 . The screw 12251 is connected to the second rotor 1224 , and the nut 12252 is fixedly connected to the variable pitch pusher 1221 .

[0296] In some embodiments, the power output device 102 further includes a tilting mechanism 40, which includes:

[0297] A connecting seat 41 is used to connect to the fuselage body 101;

[0298] A tilting connection member 42, wherein the driving mechanism 10 is connected to the tilting connection member 42;

[0299] Tilt drive assembly 43; and

[0300] The tilt transmission assembly 44 is rotatably connected to the connecting seat 41; it cooperates with the tilt drive assembly 43 in threaded transmission to convert the rotational motion of the tilt drive assembly 43 into at least part of the linear motion of the tilt transmission assembly 44; the tilt transmission assembly 44 is connected to the tilt connection member 42, and is used to drive the tilt connection member 42 to rotate relative to the connecting seat 41, thereby driving the drive mechanism 10 and the propeller assembly 103 to tilt.

[0301] The embodiment of the present application provides a power output device 102, including a driving mechanism 10 and a detection mechanism 20. The driving mechanism 10 is used to drive a propeller assembly 103 of an aircraft 1000 to rotate to provide flight power for the aircraft 1000 and to drive blades 1032 of the propeller assembly 103 to rotate to adjust the pitch of the blades 1032. The detection mechanism 20 is configured to detect pitch information of the blades 1032.

[0302] An accommodating space 113 is defined inside the driving mechanism 10 , and the detecting mechanism 20 is at least partially disposed in the accommodating space 113 .

[0303] The power output device 102 of the above embodiment, since an accommodating space 113 is provided on the inner side of the driving mechanism 10, and the detection mechanism 20 is at least partially provided in the accommodating space 113, can compress the overall size of the power output device 102 to a certain extent. The structural design of the power output device 102 is reasonable and compact. The power output device 102 can be flexibly arranged and has strong adaptability, which reduces the adverse effects of the power output device 102 on the overall design of the aircraft 1000, is conducive to making better optimization results for the overall design, and provides a guarantee for the normal use of the aircraft.

[0304] Illustratively, the power output device 102 includes the power output device 102 of any of the above embodiments. The drive mechanism 10 includes the drive mechanism 10 of any of the above embodiments. The detection mechanism 20 includes the detection mechanism 20 of any of the above embodiments. The propeller assembly 103 includes the propeller assembly 103 of any of the above embodiments.

[0305] In some embodiments, the drive mechanism 10 includes:

[0306] A first driving assembly 11, configured to drive the propeller assembly 103 to rotate; and

[0307] The second driving assembly 12 is used to drive the blade 1032 to rotate;

[0308] The first driving assembly 11 or the second driving assembly 12 defines an accommodating space 113 .

[0309] In some embodiments, the first drive component 11 is provided with a accommodating space 113, the second drive component 12 includes a variable pitch pusher 1221 capable of driving the blade 1032 to rotate, the variable pitch pusher 1221 passes through the accommodating space 113 and is connected to the blade 1032, and the detection mechanism 20 is at least partially provided in the accommodating space 113 to detect the movement information of the variable pitch pusher 1221.

[0310] In some embodiments, the pitch-changing push member 1221 is configured to be able to reciprocate along the rotation axis of the propeller assembly 103 to drive the blades 1032 to rotate;

[0311] The detection mechanism 20 is used to detect the movement stroke of the pitch-changing push member 1221 to determine the pitch information of the blade 1032 .

[0312] In some embodiments, the detection mechanism 20 includes:

[0313] The linkage member 21 is connected to the variable pitch push member 1221;

[0314] The signal collecting component 22 is provided corresponding to the linkage component 21 , and is used to detect the motion state information of the linkage component 21 and determine the pitch information of the blade 1032 according to the motion state information.

[0315] In some embodiments, the linkage member 21 moves synchronously with the variable-distance push member 1221 , and the signal acquisition member 22 is configured to acquire linear movement information of the linkage member 21 .

[0316] In some embodiments, the linkage member 21 is used to convert the linear motion of the variable-pitch push member 1221 into rotational motion, and the signal acquisition member 22 is used to detect the rotational state information of the linkage member 21 .

[0317] In some embodiments, the first drive assembly 11 includes a first fixed member 111 and a first movable member 112 that moves relative to the first fixed member 111, and the first movable member 112 is used for transmission connection with the propeller assembly 103; the second drive assembly 12 includes a second fixed member 121 connected to the first fixed member 111 and a second movable member 122 that moves relative to the second fixed member 121, and the second movable member 122 is used for transmission connection with the blade 1032;

[0318] When the first driving assembly 11 drives the propeller assembly 103 to rotate, the second fixing member 121 is stationary relative to the first fixing member 111 .

[0319] In some embodiments, the first drive assembly 11 includes a first fixed member 111 and a first movable member 112 that moves relative to the first fixed member 111, and the first movable member 112 is used for transmission connection with the propeller assembly 103; the second drive assembly 12 includes a second fixed member 121 connected to the first fixed member 111 and a second movable member 122 that moves relative to the second fixed member 121, and the second movable member 122 is used for transmission connection with the blade 1032;

[0320] The accommodating space 113 passes through the first driving assembly 11 in the direction of the rotation axis of the propeller assembly 103 . The second fixing member 121 and the propeller assembly 103 respectively close the accommodating space 113 from both ends thereof.

[0321] In some embodiments, an accommodating space 113 is defined inside the first fixing member 111 , the first movable member 112 is disposed outside the first fixing member 111 , and the second fixing member 121 is disposed outside or inside the accommodating space 113 .

[0322] In some embodiments, the second drive assembly 12 includes a second fixed member 121 and a second movable member 122 that moves relative to the second fixed member 121. The second movable member 122 includes a second rotor 1224 and a threaded transmission mechanism 1225 connected to the second rotor 1224. The threaded transmission mechanism 1225 is connected to the variable pitch push member 1221 and is used to convert the rotational motion of the second rotor 1224 into linear movement of the variable pitch push member 1221.

[0323] In some embodiments, the threaded transmission mechanism 1225 includes a screw 12251 and a nut 12252 threadedly engaged with the screw 12251 . The screw 12251 is connected to the second rotor 1224 , and the nut 12252 is fixedly connected to the variable pitch pusher 1221 .

[0324] In some embodiments, the power output device 102 further includes a tilting mechanism 40, which includes:

[0325] A connecting seat 41 is used to connect to the fuselage body 101 of the aircraft 1000;

[0326] A tilting connection member 42, wherein the driving mechanism 10 is connected to the tilting connection member 42;

[0327] Tilt drive assembly 43; and

[0328] The tilt transmission assembly 44 is rotatably connected to the connecting seat 41; it cooperates with the tilt drive assembly 43 in threaded transmission to convert the rotational motion of the tilt drive assembly 43 into at least part of the linear motion of the tilt transmission assembly 44; the tilt transmission assembly 44 is connected to the tilt connection member 42, and is used to drive the tilt connection member 42 to rotate relative to the connecting seat 41, thereby driving the drive mechanism 10 and the propeller assembly 103 to tilt.

[0329] The embodiment of the present application provides a power output device 102, including a drive mechanism 10, which includes:

[0330] A first drive assembly 11 is configured to drive the propeller assembly 103 of the aircraft 1000 to rotate, thereby providing flight power for the aircraft 1000. The first drive assembly 11 includes a first fixed member 111 and a first movable member 112 that moves relative to the first fixed member 111. The first movable member 112 is configured to be in transmission connection with the propeller assembly 103 to drive the propeller assembly 103 to rotate.

[0331] The second drive assembly 12 is used to drive the blades 1032 of the propeller assembly 103 to rotate, thereby adjusting the pitch of the blades 1032. The second drive assembly 12 includes a second fixed member 121 and a second movable member 122 that moves relative to the second fixed member 121. The second movable member 122 is in driving connection with the blades 1032.

[0332] The second fixing member 121 is connected to the first fixing member 111 . When the first driving assembly 11 drives the propeller assembly 103 to rotate, the second fixing member 121 remains stationary relative to the first fixing member 111 .

[0333] The power output device 102 of the above embodiment has a reasonable structural design. When the first drive component 11 drives the propeller component 103 to rotate, the second fixed member 121 is stationary relative to the first fixed member 111. The connecting cable used to connect the second drive component 12 and other components (such as the control module 104 in Figure 4) does not need to move with the rotation of the first movable member 112 of the first drive component 11. The wiring is convenient, stable and reliable, and is not prone to control failure, thereby improving the reliability and safety of the power output device 102 and reducing maintenance costs. In addition, because the second fixed member 121 is connected to the first fixed member 111, the first drive component 11 and the second drive component 12 are relatively less prone to wear when the power output device 102 is working, which is beneficial to extending the service life of the power output device 102 and reducing the number of times the power output device 102 is maintained or replaced; it is not prone to electric shock corrosion and has good corrosion resistance; the power output device 102 has a simple structure and is simple to control.

[0334] Exemplarily, the power output device 102 includes the power output device 102 of any one of the above embodiments. The drive mechanism 10 includes the drive mechanism 10 of any one of the above embodiments. The propeller assembly 103 includes the propeller assembly 103 of any one of the above embodiments.

[0335] In some embodiments, the power output device 102 further includes:

[0336] The detection mechanism 20 is configured to detect the pitch information of the blade 1032;

[0337] An accommodating space 113 is defined inside the first fixing member 111 , and the detection mechanism 20 is at least partially disposed in the accommodating space 113 .

[0338] In some embodiments, the second movable member 122 includes a variable pitch pusher 1221 capable of driving the blade 1032 to rotate. The variable pitch pusher 1221 passes through the accommodating space 113 and is connected to the blade 1032. The detection mechanism 20 is at least partially disposed in the accommodating space 113 to detect movement information of the variable pitch pusher 1221.

[0339] In some embodiments, the pitch-changing push member 1221 is configured to be able to reciprocate along the rotation axis of the propeller assembly 103 to drive the blades 1032 to rotate;

[0340] The detection mechanism 20 is used to detect the movement stroke of the pitch-changing push member 1221 to determine the pitch information of the blade 1032 .

[0341] In some embodiments, the detection mechanism 20 includes:

[0342] The linkage member 21 is connected to the variable pitch push member 1221;

[0343] The signal collecting component 22 is provided corresponding to the linkage component 21 , and is used to detect the motion state information of the linkage component 21 and determine the pitch information of the blade 1032 according to the motion state information.

[0344] In some embodiments, the linkage member 21 moves synchronously with the variable-distance push member 1221 , and the signal acquisition member 22 is configured to acquire linear movement information of the linkage member 21 .

[0345] In some embodiments, the linkage member 21 is used to convert the linear motion of the variable-pitch push member 1221 into rotational motion, and the signal acquisition member 22 is used to detect the rotational state information of the linkage member 21 .

[0346] In some embodiments, the second movable member 122 includes a second rotor 1224 and a threaded transmission mechanism 1225 connected to the second rotor 1224 . The threaded transmission mechanism 1225 is connected to the variable pitch pusher 1221 for converting the rotational motion of the second rotor 1224 into linear movement of the variable pitch pusher 1221 .

[0347] In some embodiments, the threaded transmission mechanism 1225 includes a screw 12251 and a nut 12252 threadedly engaged with the screw 12251 . The screw 12251 is connected to the second rotor 1224 , and the nut 12252 is fixedly connected to the variable pitch pusher 1221 .

[0348] In some embodiments, the accommodating space 113 passes through the first driving assembly 11 in the direction of the rotation axis of the propeller assembly 103 , and the second fixing member 121 and the propeller assembly 103 respectively close the accommodating space 113 from both ends thereof.

[0349] In some embodiments, an accommodating space 113 is defined inside the first fixing member 111 , the first movable member 112 is disposed outside the first fixing member 111 , and the second fixing member 121 is disposed outside or inside the accommodating space 113 .

[0350] In some embodiments, the first driving component 11 includes a first motor, the first fixing member 111 includes a first coil 1111 , the second driving component 12 includes a second motor, and the second fixing member 121 includes a second coil 1211 .

[0351] In some embodiments, the power output device 102 further includes a tilting mechanism 40, which includes:

[0352] A connecting seat 41 is used to connect to the fuselage body 101 of the aircraft 1000;

[0353] A tilting connection member 42, wherein the driving mechanism 10 is connected to the tilting connection member 42;

[0354] Tilt drive assembly 43; and

[0355] The tilt transmission assembly 44 is rotatably connected to the connecting seat 41; it cooperates with the tilt drive assembly 43 in threaded transmission to convert the rotational motion of the tilt drive assembly 43 into at least part of the linear motion of the tilt transmission assembly 44; the tilt transmission assembly 44 is connected to the tilt connection member 42, and is used to drive the tilt connection member 42 to rotate relative to the connecting seat 41, thereby driving the drive mechanism 10 and the propeller assembly 103 to tilt.

[0356] The embodiment of the present application further provides a tilting mechanism 40, comprising:

[0357] A connecting seat 41 is used to connect to the fuselage body 101 of the aircraft 1000;

[0358] The tilt connector 42 is used to connect to the drive mechanism 10 of the power output device 102 of the aircraft 1000, and the drive mechanism 10 is used to drive the propeller assembly 103 to rotate and / or drive the blades 1032 to rotate to adjust the pitch;

[0359] Tilt drive assembly 43; and

[0360] The tilt transmission assembly 44 is rotatably connected to the connecting seat 41; it cooperates with the tilt drive assembly 43 in threaded transmission to convert the rotational motion of the tilt drive assembly 43 into at least part of the linear motion of the tilt transmission assembly 44; the tilt transmission assembly 44 is connected to the tilt connection member 42, and is used to drive the tilt connection member 42 to rotate relative to the connecting seat 41, thereby driving the drive mechanism 10 and the propeller assembly 103 to tilt.

[0361] The tilt mechanism 40 of the above embodiment has a reasonable structural design. The tilt transmission assembly 44, driven by the tilt drive assembly 43, can drive the tilt connector 42 to rotate relative to the connecting seat 41, thereby driving the drive mechanism 10 and the propeller assembly 103 to tilt, so that the aircraft 1000 can not only meet the use requirements of the vertical take-off and landing working state, but also provide heading thrust for cruising in the cruising working state, effectively improving the cruising efficiency and reducing the cruising resistance, so that the aircraft 1000 can have more flight missions.

[0362] Furthermore, because the tilt transmission assembly 44 and the tilt drive assembly 43 are threadedly coupled to each other to convert the rotational motion of the tilt drive assembly 43 into at least a portion of the linear motion of the tilt transmission assembly 44, the tilt transmission assembly 44 and the tilt drive assembly 43 can achieve self-locking at any position, reducing the impact of failure of the tilt drive assembly 43. Furthermore, the threaded connection method reduces the performance requirements of the tilt drive assembly 43 and reduces the risk of failure. Even if the tilt drive assembly 43 fails, catastrophic accidents can be avoided, significantly improving reliability, providing a longer maintenance cycle, and to a certain extent reducing maintenance costs.

[0363] Illustratively, the tilting mechanism 40 includes the tilting mechanism 40 of any one of the above embodiments. The driving mechanism 10 includes the driving mechanism 10 of any one of the above embodiments. The fuselage body 101 includes the fuselage body 101 of any one of the above embodiments.

[0364] In some embodiments, the tilt transmission assembly 44 includes:

[0365] The tilt push rod 441 is in transmission connection with the tilt drive assembly 43. The tilt push rod 441 and the tilt drive assembly 43 are threadedly connected to convert the rotational motion of the tilt drive assembly 43 into linear motion of the tilt push rod 441; and

[0366] The transmission frame 442 is rotatably disposed on the connecting seat 41 . The tilt push rod 441 is connected to the transmission frame 442 to drive the transmission frame 442 to rotate. The transmission frame 442 is connected to the tilt connecting member 42 to drive the tilt connecting member 42 to rotate.

[0367] In some embodiments, the transmission frame 442 includes a first bracket 4421, a second bracket 4422 and a third bracket 4423 connected in sequence, one end of the first bracket 4421 is hinged to the tilt connection 42, and the other end is hinged to the second bracket 4422, the end of the second bracket 4422 away from the first bracket 4421 is hinged to the third bracket 4423, and the end of the third bracket 4423 away from the second bracket 4422 is hinged to the tilt connection 42.

[0368] In some embodiments, the connection base 41 is used for detachable connection with the fuselage body 101 .

[0369] An embodiment of the present application provides a movable platform, including a fuselage body 101 , a power output device 102 and a propeller assembly 103 . The power output device 102 is disposed on the fuselage body 101 and is used to drive the propeller assembly 103 .

[0370] In some embodiments, the power output device 102 includes a drive mechanism 10, and the drive mechanism 10 includes:

[0371] A first drive assembly 11 is configured to drive the propeller assembly 103 to rotate, thereby providing flight power for the aircraft 1000. The first drive assembly 11 includes a first fixed member 111 and a first movable member 112 that moves relative to the first fixed member 111. The first movable member 112 is configured to be in transmission connection with the propeller assembly 103 to drive the propeller assembly 103 to rotate. The first drive assembly 11 is provided with an accommodating space 113.

[0372] The second drive assembly 12 is used to drive the blades 1032 of the propeller assembly 103 to rotate, thereby adjusting the pitch of the blades 1032. The second drive assembly 12 includes a second fixed member 121 and a second movable member 122 that moves relative to the second fixed member 121. The second movable member 122 is configured to be in driving connection with the blades 1032. The second movable member 122 includes a pitch-changing push member 1221 that can drive the blades 1032 to rotate. The pitch-changing push member 1221 passes through the accommodating space 113 and is connected to the blades 1032.

[0373] The accommodating space 113 passes through the first driving assembly 11 in the direction of the rotation axis of the propeller assembly 103 . The second fixing member 121 and the propeller assembly 103 respectively close the accommodating space 113 from both ends thereof.

[0374] Exemplarily, the movable platform includes at least one of the following: an aircraft 1000, an underwater mobile body, an above-water mobile body, etc.

[0375] Exemplarily, the movable platform includes the aircraft 1000 of any of the above embodiments. The fuselage body 101 includes the fuselage body 101 of any of the above embodiments. The power output device 102 includes the power output device 102 of any of the above embodiments. The propeller assembly 103 includes the propeller assembly 103 of any of the above embodiments.

[0376] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "mechanically coupled", and "coupled" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection. It can be a mechanical connection or an electrical connection. It can be directly connected or indirectly connected through an intermediate medium. It can be the internal connection of two elements or the interaction relationship between two elements. The mechanical coupling or coupling of two components includes direct coupling and indirect coupling, for example, direct fixed connection, connection through a transmission mechanism, etc. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to the specific circumstances.

[0377] In this application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0378] The disclosure above provides many different embodiments or examples for realizing the different structures of the present application. In order to simplify the disclosure of the present application, the components and settings of specific examples are described above. Of course, they are merely examples and are not intended to limit the present application. In addition, the present application may repeat reference numerals and / or reference letters in different examples, and such repetition is for the purpose of simplicity and clarity, and does not itself indicate the relationship between the various embodiments and / or settings discussed. In addition, the present application provides examples of various specific processes and materials, but those of ordinary skill in the art will appreciate the application of other processes and / or the use of other materials.

[0379] Throughout this specification, reference to terms such as "one embodiment," "some embodiments," "illustrative embodiments," "examples," "specific examples," or "some examples" means that the specific method steps, features, structures, materials, or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific method steps, features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0380] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present application, and such modifications or substitutions should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. An aircraft, characterized in that: The invention comprises a fuselage body, a power output device and a propeller assembly, wherein the power output device is arranged on the fuselage body and is used to drive the propeller assembly; wherein the power output device comprises a driving mechanism, and the driving mechanism comprises: a first driving assembly, used for driving the propeller assembly to rotate, so as to provide flying power for the aircraft; the first driving assembly comprises a first fixed member and a first movable member moving relative to the first fixed member, the first movable member being used for transmission connection with the propeller assembly to drive the propeller assembly to rotate; the first driving assembly is provided with an accommodating space; and A second driving assembly is used to drive the blades of the propeller assembly to rotate, so as to adjust the pitch of the blades; the second driving assembly includes a second fixed member and a second movable member that moves relative to the second fixed member, the second movable member is used to be connected to the blades in a transmission manner; the second movable member includes a variable pitch push member that can drive the blades to rotate, the variable pitch push member passes through the accommodating space and is connected to the blades; The accommodating space passes through the first driving assembly in the direction of the rotation axis of the propeller assembly, and the second fixing member and the propeller assembly respectively close the accommodating space from both ends of the accommodating space.

2. The aircraft according to claim 1, characterized in that The power output device further comprises: A detection mechanism, configured to detect pitch information of the blade; Wherein, the detection mechanism is at least partially disposed in the accommodating space to detect movement information of the variable-distance pushing member.

3. The aircraft according to claim 2, characterized in that: The pitch-changing push piece is configured to be able to reciprocate along the rotation axis direction of the propeller assembly to drive the blade to rotate; The detection mechanism is used to detect the moving stroke of the pitch-changing push member to determine the pitch information of the blade.

4. The aircraft according to claim 3, characterized in that The detection mechanism includes: A linkage member connected to the variable pitch push member; The signal collecting component is arranged corresponding to the linkage component, and is used for detecting the motion state information of the linkage component and determining the pitch information of the blade according to the motion state information.

5. The aircraft according to claim 4, characterized in that The linkage member moves synchronously with the variable-distance pushing member, and the signal collecting member is configured to collect linear movement information of the linkage member.

6. The aircraft according to claim 4, characterized in that The signal collecting component comprises a hollow structure, and the linkage component and the variable distance pushing component are at least partially arranged in the signal collecting component.

7. The aircraft according to claim 4, characterized in that: The linkage member and the pitch-changing push member at least partially overlap in the direction of the rotation axis of the propeller assembly.

8. The aircraft according to claim 4, characterized in that The linkage member is used to convert the linear motion of the variable-distance push member into rotational motion, and the signal acquisition member is used to detect the rotation state information of the linkage member.

9. The aircraft according to claim 8, characterized in that The linkage comprises: A rack connected to the variable pitch push piece; A gear is meshed with the rack, and the signal acquisition component is used to detect the rotation state information of the gear.

10. An aircraft according to any one of claims 1 to 9, characterized in that The pitch-changing push piece is connected to the blade via a pitch-changing push plate, the pitch-changing push plate is rotatably sleeved on the pitch-changing push piece, the pitch-changing push plate is provided with a first matching portion, the root of the blade is provided with a second matching portion, and the first matching portion is slidably matched with the second matching portion; When the pitch-changing push piece moves, the pitch-changing push plate moves along with the pitch-changing push piece, and the movement of the pitch-changing push plate is converted into the rotation of the blade through the sliding cooperation of the first matching portion and the second matching portion.

11. The aircraft according to claim 1, characterized in that: The second fixing member is connected to the first fixing member, and when the first driving assembly drives the propeller assembly to rotate, the second fixing member is stationary relative to the first fixing member.

12. The aircraft according to claim 11, characterized in that The first driving component includes a first motor, the first fixing component includes a first coil, the second driving component includes a second motor, and the second fixing component includes a second coil.

13. The aircraft according to claim 1 or 11, characterized in that: The accommodating space is provided on the inner side of the first fixing member, the first movable member is provided on the outer side of the first fixing member, and the second fixing member is provided on the outer side or the inner side of the accommodating space.

14. The aircraft according to claim 1, characterized in that The second movable member includes a second rotor and a threaded transmission mechanism connected to the second rotor. The threaded transmission mechanism is connected to the variable pitch push member and is used for converting the rotational motion of the second rotor into the linear motion of the variable pitch push member.

15. The aircraft according to claim 14, characterized in that The thread transmission mechanism comprises a screw rod and a nut matched with the screw rod thread, the screw rod is connected to the second rotor, and the nut is fixedly connected to the variable pitch push piece.

16. The aircraft according to claim 15, characterized in that It also includes a limiting structure, which is used to limit the rotational movement of the nut and / or the variable-distance push piece to achieve linear movement of the variable-distance push piece.

17. The aircraft according to claim 1, characterized in that: The power output device further includes a tilting mechanism, and the tilting mechanism includes: A connecting seat, used for connecting with the fuselage body; A tilting connection member, the driving mechanism being connected to the tilting connection member; a tilt drive assembly; and A tilt transmission assembly is rotatably connected to the connecting seat; it cooperates with the tilt drive assembly in threaded transmission to convert the rotational motion of the tilt drive assembly into at least part of the linear motion of the tilt transmission assembly; the tilt transmission assembly is connected to the tilt connecting piece to drive the tilt connecting piece to rotate relative to the connecting seat, thereby driving the drive mechanism and the propeller assembly to tilt.

18. The aircraft according to claim 17, characterized in that The tilt transmission assembly comprises: A tilt push rod, which is in driving connection with the tilt drive assembly, wherein the tilt push rod and the tilt drive assembly are threadedly driven to convert the rotational motion of the tilt drive assembly into the linear motion of the tilt push rod; and The transmission frame is rotatably arranged on the connecting seat, the tilt push rod is connected to the transmission frame to push the transmission frame to rotate, and the transmission frame is connected to the tilt connecting member to drive the tilt connecting member to rotate.

19. The aircraft according to claim 18, characterized in that The transmission frame comprises: A first bracket, one end of which is hinged to the tilting connector, and the other end of which is hinged to the connecting seat; A second bracket, one end of which is hinged to the connecting seat; The third bracket is hinged to the other end of the second bracket, and one end of the third bracket away from the second bracket is hinged to the tilting connection piece.

20. The aircraft according to claim 17, characterized in that The connecting seat is used for detachable connection with the fuselage body.

21. The aircraft according to claim 2, characterized in that It also includes a control module, and the power output device is electrically connected to the control module.

22. The aircraft according to claim 21, characterized in that The control module is configured to adjust the operating state or operating parameters of the aircraft according to the pitch information detected by the detection mechanism.

23. The aircraft according to claim 22, characterized in that The operating state includes at least one of the operating state of the fuselage body, the operating state of the load attached to the fuselage body, the operating state of the power output device, and the operating state of the propeller assembly; and the operating parameters include at least one of the operating parameters of the fuselage body, the operating parameters of the load attached to the aircraft, the operating parameters of the power output device, and the operating parameters of the propeller assembly.

24. The aircraft according to claim 23, characterized in that The operating parameters of the propeller assembly include at least one of the pitch of the blades, the rotation speed of the propeller assembly, and the rotation direction of the propeller assembly.

25. The aircraft according to claim 1, characterized in that The propeller assembly includes a propeller base and a plurality of blades arranged on the propeller base. The propeller assembly is configured to be rotatable to provide flight power for the aircraft, and the blades are configured to be rotatable relative to the propeller base to change the pitch of the blades.

26. An aircraft, characterized in that: The invention comprises a fuselage body, a power output device and a propeller assembly, wherein the power output device is arranged on the fuselage body and is used to drive the propeller assembly; wherein the power output device comprises a driving mechanism and a detecting mechanism, wherein the driving mechanism is used to drive the propeller assembly to rotate so as to provide the flight power of the aircraft and to drive the blades of the propeller assembly to rotate so as to adjust the pitch of the blades, and the detecting mechanism is configured to detect the pitch information of the blades; Wherein, an accommodating space is provided inside the driving mechanism, and the detecting mechanism is at least partially provided in the accommodating space.

27. The aircraft according to claim 26, characterized in that The driving mechanism comprises: A first driving assembly, configured to drive the propeller assembly to rotate; and A second driving assembly, used for driving the blades to rotate; The first driving assembly or the second driving assembly is provided with the accommodating space.

28. The aircraft according to claim 27, characterized in that The first driving assembly is provided with the accommodating space, the second driving assembly includes a variable pitch push piece capable of driving the blade to rotate, the variable pitch push piece passes through the accommodating space and is connected to the blade, and the detection mechanism is at least partially arranged in the accommodating space to detect movement information of the variable pitch push piece.

29. The aircraft according to claim 28, characterized in that The pitch-changing push piece is configured to be able to reciprocate along the rotation axis direction of the propeller assembly to drive the blade to rotate; The detection mechanism is used to detect the moving stroke of the pitch-changing push member to determine the pitch information of the blade.

30. The aircraft according to claim 29, characterized in that The detection mechanism includes: A linkage member connected to the variable pitch push member; The signal collecting component is arranged corresponding to the linkage component, and is used for detecting the motion state information of the linkage component and determining the pitch information of the blade according to the motion state information.

31. The aircraft according to claim 30, characterized in that The linkage member moves synchronously with the variable-distance pushing member, and the signal collecting member is configured to collect linear movement information of the linkage member.

32. The aircraft according to claim 30, characterized in that The signal collecting component comprises a hollow structure, and the linkage component and the variable distance pushing component are at least partially arranged in the signal collecting component; and / or, The linkage member and the pitch-changing push member at least partially overlap in the direction of the rotation axis of the propeller assembly.

33. The aircraft according to claim 30, characterized in that The linkage member is used to convert the linear motion of the variable-distance push member into rotational motion, and the signal acquisition member is used to detect the rotation state information of the linkage member.

34. The aircraft according to claim 33, characterized in that The linkage comprises: A rack connected to the variable pitch push piece; A gear is meshed with the rack, and the signal acquisition component is used to detect the rotation state information of the gear.

35. An aircraft according to any one of claims 27 to 34, characterised in that The pitch-changing push piece is connected to the blade via a pitch-changing push plate, the pitch-changing push plate is rotatably sleeved on the pitch-changing push piece, the pitch-changing push plate is provided with a first matching portion, the root of the blade is provided with a second matching portion, and the first matching portion is slidably matched with the second matching portion; When the pitch-changing push piece moves, the pitch-changing push plate moves along with the pitch-changing push piece, and the movement of the pitch-changing push plate is converted into the rotation of the blade through the sliding cooperation of the first matching portion and the second matching portion.

36. The aircraft according to claim 27, characterized in that The first driving assembly includes a first fixed member and a first movable member that moves relative to the first fixed member, and the first movable member is used for driving connection with the propeller assembly; the second driving assembly includes a second fixed member connected to the first fixed member and a second movable member that moves relative to the second fixed member, and the second movable member is used for driving connection with the blade; When the first driving assembly drives the propeller assembly to rotate, the second fixing member is stationary relative to the first fixing member.

37. The aircraft according to claim 36, characterized in that The first driving component includes a first motor, the first fixing component includes a first coil, the second driving component includes a second motor, and the second fixing component includes a second coil.

38. The aircraft according to claim 27, characterized in that The first driving assembly includes a first fixed member and a first movable member that moves relative to the first fixed member, and the first movable member is used for driving connection with the propeller assembly; the second driving assembly includes a second fixed member connected to the first fixed member and a second movable member that moves relative to the second fixed member, and the second movable member is used for driving connection with the blade; The accommodating space passes through the first driving assembly in the direction of the rotation axis of the propeller assembly, and the second fixing member and the propeller assembly respectively close the accommodating space from both ends of the accommodating space.

39. The aircraft according to claim 38, characterized in that The accommodating space is provided on the inner side of the first fixing member, the first movable member is provided on the outer side of the first fixing member, and the second fixing member is provided on the outer side or the inner side of the accommodating space.

40. The aircraft according to claim 28, characterized in that The second driving assembly includes a second fixed member and a second movable member that moves relative to the second fixed member, the second movable member includes a second rotor and a threaded transmission mechanism connected to the second rotor, the threaded transmission mechanism is connected to the variable pitch push member, and is used to convert the rotational motion of the second rotor into linear movement of the variable pitch push member.

41. The aircraft according to claim 40, characterized in that The thread transmission mechanism comprises a screw rod and a nut matched with the screw rod thread, the screw rod is connected to the second rotor, and the nut is fixedly connected to the variable pitch push piece.

42. The aircraft according to claim 41, characterized in that It also includes a limiting structure, which is used to limit the rotational movement of the nut and / or the variable-distance push piece to achieve linear movement of the variable-distance push piece.

43. The aircraft according to claim 26, characterized in that The power output device further includes a tilting mechanism, and the tilting mechanism includes: A connecting seat, used for connecting with the fuselage body; A tilting connection member, the driving mechanism being connected to the tilting connection member; a tilt drive assembly; and A tilt transmission assembly is rotatably connected to the connecting seat; it cooperates with the tilt drive assembly in threaded transmission to convert the rotational motion of the tilt drive assembly into at least part of the linear motion of the tilt transmission assembly; the tilt transmission assembly is connected to the tilt connecting piece to drive the tilt connecting piece to rotate relative to the connecting seat, thereby driving the drive mechanism and the propeller assembly to tilt.

44. The aircraft according to claim 43, characterized in that The tilt transmission assembly comprises: A tilt push rod, which is in driving connection with the tilt drive assembly, wherein the tilt push rod and the tilt drive assembly are threadedly driven to convert the rotational motion of the tilt drive assembly into the linear motion of the tilt push rod; and The transmission frame is rotatably arranged on the connecting seat, the tilt push rod is connected to the transmission frame to push the transmission frame to rotate, and the transmission frame is connected to the tilt connecting member to drive the tilt connecting member to rotate.

45. The aircraft according to claim 44, characterized in that: The transmission frame comprises: A first bracket, one end of which is hinged to the tilting connector, and the other end of which is hinged to the connecting seat; A second bracket, one end of which is hinged to the connecting seat; The third bracket is hinged to the other end of the second bracket, and one end of the third bracket away from the second bracket is hinged to the tilting connection piece.

46. ​​The aircraft according to claim 43, characterized in that The connecting seat is used for detachable connection with the fuselage body.

47. The aircraft according to claim 26, characterized in that It also includes a control module, and the power output device is electrically connected to the control module.

48. The aircraft according to claim 47, characterized in that The control module is configured to adjust the operating state or operating parameters of the aircraft according to the pitch information detected by the detection mechanism.

49. The aircraft according to claim 48, characterized in that The operating state includes at least one of the operating state of the fuselage body, the operating state of the load attached to the fuselage body, the operating state of the power output device, and the operating state of the propeller assembly; and the operating parameters include at least one of the operating parameters of the fuselage body, the operating parameters of the load attached to the aircraft, the operating parameters of the power output device, and the operating parameters of the propeller assembly.

50. The aircraft according to claim 49, characterized in that The operating parameters of the propeller assembly include at least one of the pitch of the blades, the rotation speed of the propeller assembly, and the rotation direction of the propeller assembly.

51. The aircraft according to claim 26, characterized in that The propeller assembly includes a propeller base and a plurality of blades arranged on the propeller base. The propeller assembly is configured to be rotatable to provide flight power for the aircraft, and the blades are configured to be rotatable relative to the propeller base to change the pitch of the blades.

52. An aircraft, characterized in that: The invention comprises a fuselage body, a power output device and a propeller assembly, wherein the power output device is arranged on the fuselage body and is used to drive the propeller assembly; wherein the power output device comprises a driving mechanism, and the driving mechanism comprises: a first driving assembly, used for driving the propeller assembly to rotate, so as to provide flight power for the aircraft; the first driving assembly comprises a first fixed member and a first movable member moving relative to the first fixed member, the first movable member being used for transmission connection with the propeller assembly to drive the propeller assembly to rotate; and a second driving assembly, used for driving the blades of the propeller assembly to rotate, so as to adjust the pitch of the blades; the second driving assembly comprises a second fixed member and a second movable member moving relative to the second fixed member, the second movable member being used for driving connection with the blades; The second fixing member is connected to the first fixing member, and when the first driving assembly drives the propeller assembly to rotate, the second fixing member is stationary relative to the first fixing member.

53. The aircraft according to claim 52, characterized in that The power output device further comprises: A detection mechanism, configured to detect pitch information of the blade; An accommodating space is disposed inside the first fixing member, and the detection mechanism is at least partially disposed in the accommodating space.

54. The aircraft according to claim 53, characterized in that The second movable member includes a variable pitch push member capable of driving the blade to rotate, the variable pitch push member passes through the accommodating space and is connected to the blade, and the detection mechanism is at least partially disposed in the accommodating space to detect movement information of the variable pitch push member.

55. The aircraft according to claim 54, characterized in that The pitch-changing push piece is configured to be able to reciprocate along the rotation axis direction of the propeller assembly to drive the blade to rotate; The detection mechanism is used to detect the moving stroke of the pitch-changing push member to determine the pitch information of the blade.

56. The aircraft according to claim 54, characterized in that The detection mechanism includes: A linkage member connected to the variable pitch push member; The signal collecting component is arranged corresponding to the linkage component, and is used for detecting the motion state information of the linkage component and determining the pitch information of the blade according to the motion state information.

57. The aircraft according to claim 56, characterized in that The linkage member moves synchronously with the variable-distance pushing member, and the signal collecting member is configured to collect linear movement information of the linkage member.

58. The aircraft according to claim 56, characterized in that The signal collecting component comprises a hollow structure, and the linkage component and the variable distance pushing component are at least partially arranged in the signal collecting component.

59. The aircraft according to claim 56, characterized in that The linkage member and the pitch-changing push member at least partially overlap in the direction of the rotation axis of the propeller assembly.

60. The flying machine according to claim 56, characterized in that The linkage member is used to convert the linear motion of the variable-distance push member into rotational motion, and the signal acquisition member is used to detect the rotation state information of the linkage member.

61. The aircraft according to claim 60, characterized in that The linkage comprises: A rack connected to the variable pitch push piece; A gear is meshed with the rack, and the signal acquisition component is used to detect the rotation state information of the gear.

62. An aircraft according to any one of claims 54 to 61, characterized in that The pitch-changing push piece is connected to the blade via a pitch-changing push plate, the pitch-changing push plate is rotatably sleeved on the pitch-changing push piece, the pitch-changing push plate is provided with a first matching portion, the root of the blade is provided with a second matching portion, and the first matching portion is slidably matched with the second matching portion; When the pitch-changing push piece moves, the pitch-changing push plate moves along with the pitch-changing push piece, and the movement of the pitch-changing push plate is converted into the rotation of the blade through the sliding cooperation of the first matching portion and the second matching portion.

63. An aircraft according to any one of claims 54 to 61, characterised in that The second movable member includes a second rotor and a threaded transmission mechanism connected to the second rotor. The threaded transmission mechanism is connected to the variable pitch push member and is used for converting the rotational motion of the second rotor into the linear motion of the variable pitch push member.

64. The aircraft according to claim 63, characterized in that The thread transmission mechanism comprises a screw rod and a nut matched with the screw rod thread, the screw rod is connected to the second rotor, and the nut is fixedly connected to the variable pitch push piece.

65. The flying machine according to claim 64, characterized in that It also includes a limiting structure, which is used to limit the rotational movement of the nut and / or the variable-distance push piece to achieve linear movement of the variable-distance push piece.

66. The flying machine according to claim 53, characterized in that The accommodating space passes through the first driving assembly in the direction of the rotation axis of the propeller assembly, and the second fixing member and the propeller assembly respectively close the accommodating space from both ends of the accommodating space.

67. The flying machine according to claim 66, characterized in that The accommodating space is provided on the inner side of the first fixing member, the first movable member is provided on the outer side of the first fixing member, and the second fixing member is provided on the outer side or the inner side of the accommodating space.

68. The aircraft according to claim 52, characterized in that The first driving component includes a first motor, the first fixing component includes a first coil, the second driving component includes a second motor, and the second fixing component includes a second coil.

69. The aircraft according to claim 52, characterized in that The power output device further includes a tilting mechanism, and the tilting mechanism includes: A connecting seat, used for connecting with the fuselage body; A tilting connection member, the driving mechanism being connected to the tilting connection member; a tilt drive assembly; and A tilt transmission assembly is rotatably connected to the connecting seat; it cooperates with the tilt drive assembly in threaded transmission to convert the rotational motion of the tilt drive assembly into at least part of the linear motion of the tilt transmission assembly; the tilt transmission assembly is connected to the tilt connecting piece to drive the tilt connecting piece to rotate relative to the connecting seat, thereby driving the drive mechanism and the propeller assembly to tilt.

70. The aircraft according to claim 69, characterized in that The tilt transmission assembly comprises: A tilt push rod, which is in driving connection with the tilt drive assembly, wherein the tilt push rod and the tilt drive assembly are threadedly driven to convert the rotational motion of the tilt drive assembly into the linear motion of the tilt push rod; and The transmission frame is rotatably arranged on the connecting seat, the tilt push rod is connected to the transmission frame to push the transmission frame to rotate, and the transmission frame is connected to the tilt connecting member to drive the tilt connecting member to rotate.

71. The aircraft according to claim 70, characterized in that: The transmission frame comprises: A first bracket, one end of which is hinged to the tilting connector, and the other end of which is hinged to the connecting seat; A second bracket, one end of which is hinged to the connecting seat; The third bracket is hinged to the other end of the second bracket, and one end of the third bracket away from the second bracket is hinged to the tilting connection piece.

72. The aircraft according to claim 69, characterized in that The connecting seat is used for detachable connection with the fuselage body.

73. The aircraft according to claim 53, characterized in that It also includes a control module, and the power output device is electrically connected to the control module.

74. The aircraft according to claim 73, characterized in that The control module is configured to adjust the operating state or operating parameters of the aircraft according to the pitch information detected by the detection mechanism.

75. The flying machine according to claim 74, characterized in that The operating state includes at least one of the operating state of the fuselage body, the operating state of the load attached to the fuselage body, the operating state of the power output device, and the operating state of the propeller assembly; and the operating parameters include at least one of the operating parameters of the fuselage body, the operating parameters of the load attached to the aircraft, the operating parameters of the power output device, and the operating parameters of the propeller assembly.

76. The flying machine according to claim 75, characterized in that The operating parameters of the propeller assembly include at least one of the pitch of the blades, the rotation speed of the propeller assembly, and the rotation direction of the propeller assembly.

77. The aircraft according to claim 52, characterized in that The propeller assembly includes a propeller base and a plurality of blades arranged on the propeller base. The propeller assembly is configured to be rotatable to provide flight power for the aircraft, and the blades are configured to be rotatable relative to the propeller base to change the pitch of the blades.

78. A power output device, characterized in that: The invention comprises a driving mechanism, wherein the driving mechanism comprises: a first driving assembly, used for driving the propeller assembly of the aircraft to rotate, so as to provide the aircraft with flight power; the first driving assembly comprises a first fixed member and a first movable member moving relative to the first fixed member, the first movable member being used for transmission connection with the propeller assembly to drive the propeller assembly to rotate; the first driving assembly is provided with an accommodating space; and A second driving assembly is used to drive the blades of the propeller assembly to rotate, so as to adjust the pitch of the blades; the second driving assembly includes a second fixed member and a second movable member that moves relative to the second fixed member, the second movable member is used to be connected to the blades in a transmission manner; the second movable member includes a variable pitch push member that can drive the blades to rotate, the variable pitch push member passes through the accommodating space and is connected to the blades; The accommodating space passes through the first driving assembly in the direction of the rotation axis of the propeller assembly, and the second fixing member and the propeller assembly respectively close the accommodating space from both ends of the accommodating space.

79. The power output device according to claim 78, characterized in that Also includes: A detection mechanism, configured to detect pitch information of the blade; Wherein, the detection mechanism is at least partially disposed in the accommodating space to detect movement information of the variable-distance pushing member.

80. The power output device according to claim 79, characterized in that: The pitch-changing push piece is configured to be able to reciprocate along the rotation axis direction of the propeller assembly to drive the blade to rotate; The detection mechanism is used to detect the moving stroke of the pitch-changing push member to determine the pitch information of the blade.

81. The power output device according to claim 80, characterized in that: The detection mechanism includes: A linkage member connected to the variable pitch push member; The signal collecting component is arranged corresponding to the linkage component, and is used for detecting the motion state information of the linkage component and determining the pitch information of the blade according to the motion state information.

82. The power output device according to claim 81, characterized in that: The linkage member moves synchronously with the variable-distance pushing member, and the signal collecting member is configured to collect linear movement information of the linkage member.

83. The power output device according to claim 81, characterized in that: The linkage member is used to convert the linear motion of the variable-distance push member into rotational motion, and the signal acquisition member is used to detect the rotation state information of the linkage member.

84. The power output device according to claim 78, characterized in that: The second fixing member is connected to the first fixing member, and when the first driving assembly drives the propeller assembly to rotate, the second fixing member is stationary relative to the first fixing member.

85. The power output device according to claim 78 or 84, characterized in that: The accommodating space is provided on the inner side of the first fixing member, the first movable member is provided on the outer side of the first fixing member, and the second fixing member is provided on the outer side or the inner side of the accommodating space.

86. The power output device according to claim 78, characterized in that The second movable member includes a second rotor and a threaded transmission mechanism connected to the second rotor. The threaded transmission mechanism is connected to the variable pitch push member and is used for converting the rotational motion of the second rotor into the linear motion of the variable pitch push member.

87. The power output device according to claim 86, characterized in that: The thread transmission mechanism comprises a screw rod and a nut matched with the screw rod thread, the screw rod is connected to the second rotor, and the nut is fixedly connected to the variable pitch push piece.

88. The power output device according to claim 78, characterized in that The power output device further includes a tilting mechanism, and the tilting mechanism includes: A connecting seat, used for connecting to the fuselage body of the aircraft; A tilting connection member, the driving mechanism being connected to the tilting connection member; a tilt drive assembly; and A tilt transmission assembly is rotatably connected to the connecting seat; it cooperates with the tilt drive assembly in threaded transmission to convert the rotational motion of the tilt drive assembly into at least part of the linear motion of the tilt transmission assembly; the tilt transmission assembly is connected to the tilt connecting piece to drive the tilt connecting piece to rotate relative to the connecting seat, thereby driving the drive mechanism and the propeller assembly to tilt.

89. A power output device, characterized in that: The invention comprises a driving mechanism and a detection mechanism, wherein the driving mechanism is used to drive a propeller assembly of an aircraft to rotate so as to provide flight power for the aircraft and to drive blades of the propeller assembly to rotate so as to adjust the pitch of the blades, and the detection mechanism is configured to detect pitch information of the blades; Wherein, an accommodating space is provided inside the driving mechanism, and the detecting mechanism is at least partially provided in the accommodating space.

90. The power output device according to claim 89, characterized in that: The driving mechanism comprises: A first driving assembly, configured to drive the propeller assembly to rotate; and A second driving assembly, used for driving the blades to rotate; The first driving assembly or the second driving assembly is provided with the accommodating space.

91. The power output device according to claim 90, characterized in that: The first driving assembly is provided with the accommodating space, the second driving assembly includes a variable pitch push piece capable of driving the blade to rotate, the variable pitch push piece passes through the accommodating space and is connected to the blade, and the detection mechanism is at least partially arranged in the accommodating space to detect movement information of the variable pitch push piece.

92. The power output device according to claim 91, characterized in that: The pitch-changing push piece is configured to be able to reciprocate along the rotation axis direction of the propeller assembly to drive the blade to rotate; The detection mechanism is used to detect the moving stroke of the pitch-changing push member to determine the pitch information of the blade.

93. The power output device according to claim 92, characterized in that: The detection mechanism includes: A linkage member connected to the variable pitch push member; The signal collecting component is arranged corresponding to the linkage component, and is used for detecting the motion state information of the linkage component and determining the pitch information of the blade according to the motion state information.

94. The power output device according to claim 93, characterized in that: The linkage member moves synchronously with the variable-distance pushing member, and the signal collecting member is configured to collect linear movement information of the linkage member.

95. The power output device according to claim 93, characterized in that: The linkage member is used to convert the linear motion of the variable-distance push member into rotational motion, and the signal acquisition member is used to detect the rotation state information of the linkage member.

96. The power output device according to claim 90, characterized in that: The first driving assembly includes a first fixed member and a first movable member that moves relative to the first fixed member, and the first movable member is used for driving connection with the propeller assembly; the second driving assembly includes a second fixed member connected to the first fixed member and a second movable member that moves relative to the second fixed member, and the second movable member is used for driving connection with the blade; When the first driving assembly drives the propeller assembly to rotate, the second fixing member is stationary relative to the first fixing member.

97. The power output device according to claim 90, characterized in that: The first driving assembly includes a first fixed member and a first movable member that moves relative to the first fixed member, and the first movable member is used for driving connection with the propeller assembly; the second driving assembly includes a second fixed member connected to the first fixed member and a second movable member that moves relative to the second fixed member, and the second movable member is used for driving connection with the blade; The accommodating space passes through the first driving assembly in the direction of the rotation axis of the propeller assembly, and the second fixing member and the propeller assembly respectively close the accommodating space from both ends of the accommodating space.

98. The power output device according to claim 97, characterized in that: The accommodating space is provided on the inner side of the first fixing member, the first movable member is provided on the outer side of the first fixing member, and the second fixing member is provided on the outer side or the inner side of the accommodating space.

99. The power output device according to claim 91, characterized in that: The second driving assembly includes a second fixed member and a second movable member that moves relative to the second fixed member, the second movable member includes a second rotor and a threaded transmission mechanism connected to the second rotor, the threaded transmission mechanism is connected to the variable pitch push member, and is used to convert the rotational motion of the second rotor into linear movement of the variable pitch push member.

100. The power output device according to claim 99, characterized in that: The thread transmission mechanism comprises a screw rod and a nut matched with the screw rod thread, the screw rod is connected to the second rotor, and the nut is fixedly connected to the variable pitch push piece.

101. The power output device according to claim 89, characterized in that: The power output device further includes a tilting mechanism, and the tilting mechanism includes: A connecting seat, used for connecting to the fuselage body of the aircraft; A tilting connection member, the driving mechanism being connected to the tilting connection member; a tilt drive assembly; and A tilt transmission assembly is rotatably connected to the connecting seat; it cooperates with the tilt drive assembly in threaded transmission to convert the rotational motion of the tilt drive assembly into at least part of the linear motion of the tilt transmission assembly; the tilt transmission assembly is connected to the tilt connecting piece to drive the tilt connecting piece to rotate relative to the connecting seat, thereby driving the drive mechanism and the propeller assembly to tilt.

102. A power output device, characterized in that: The invention comprises a driving mechanism, wherein the driving mechanism comprises: a first driving assembly, used for driving a propeller assembly of the aircraft to rotate, thereby providing flight power for the aircraft; the first driving assembly comprises a first fixed member and a first movable member that moves relative to the first fixed member, the first movable member being used for transmission connection with the propeller assembly to drive the propeller assembly to rotate; and a second driving assembly, used for driving the blades of the propeller assembly to rotate, so as to adjust the pitch of the blades; the second driving assembly comprises a second fixed member and a second movable member moving relative to the second fixed member, the second movable member being used for driving connection with the blades; The second fixing member is connected to the first fixing member, and when the first driving assembly drives the propeller assembly to rotate, the second fixing member is stationary relative to the first fixing member.

103. The power output device according to claim 102, characterized in that: The power output device further comprises: A detection mechanism, configured to detect pitch information of the blade; An accommodating space is disposed inside the first fixing member, and the detection mechanism is at least partially disposed in the accommodating space.

104. The power output device according to claim 103, characterized in that: The second movable member includes a variable pitch push member capable of driving the blade to rotate, the variable pitch push member passes through the accommodating space and is connected to the blade, and the detection mechanism is at least partially disposed in the accommodating space to detect movement information of the variable pitch push member.

105. The power output device according to claim 104, characterized in that: The pitch-changing push piece is configured to be able to reciprocate along the rotation axis direction of the propeller assembly to drive the blade to rotate; The detection mechanism is used to detect the moving stroke of the pitch-changing push member to determine the pitch information of the blade.

106. The power output device according to claim 104, characterized in that: The detection mechanism includes: A linkage member connected to the variable pitch push member; The signal collecting component is arranged corresponding to the linkage component, and is used for detecting the motion state information of the linkage component and determining the pitch information of the blade according to the motion state information.

107. The power output device according to claim 106, characterized in that: The linkage member moves synchronously with the variable-distance pushing member, and the signal collecting member is configured to collect linear movement information of the linkage member.

108. The power output device according to claim 106, characterized in that: The linkage member is used to convert the linear motion of the variable-distance push member into rotational motion, and the signal acquisition member is used to detect the rotation state information of the linkage member.

109. A power output device according to any one of claims 104 to 108, characterized in that: The second movable member includes a second rotor and a threaded transmission mechanism connected to the second rotor. The threaded transmission mechanism is connected to the variable pitch push member and is used for converting the rotational motion of the second rotor into the linear motion of the variable pitch push member.

110. The power output device according to claim 109, characterized in that: The thread transmission mechanism comprises a screw rod and a nut matched with the screw rod thread, the screw rod is connected to the second rotor, and the nut is fixedly connected to the variable pitch push piece.

111. The power output device according to claim 103, characterized in that: The accommodating space passes through the first driving assembly in the direction of the rotation axis of the propeller assembly, and the second fixing member and the propeller assembly respectively close the accommodating space from both ends of the accommodating space.

112. The power output device according to claim 103, characterized in that: The accommodating space is provided on the inner side of the first fixing member, the first movable member is provided on the outer side of the first fixing member, and the second fixing member is provided on the outer side or the inner side of the accommodating space.

113. The power output device according to claim 102, characterized in that: The first driving component includes a first motor, the first fixing component includes a first coil, the second driving component includes a second motor, and the second fixing component includes a second coil.

114. The power output device according to claim 102, characterized in that: The power output device further includes a tilting mechanism, and the tilting mechanism includes: A connecting seat, used for connecting to the fuselage body of the aircraft; A tilting connection member, the driving mechanism being connected to the tilting connection member; a tilt drive assembly; and A tilt transmission assembly is rotatably connected to the connecting seat; it cooperates with the tilt drive assembly in threaded transmission to convert the rotational motion of the tilt drive assembly into at least part of the linear motion of the tilt transmission assembly; the tilt transmission assembly is connected to the tilt connecting piece to drive the tilt connecting piece to rotate relative to the connecting seat, thereby driving the drive mechanism and the propeller assembly to tilt.

115. A tilting mechanism, characterized in that: include: A connecting seat, used for connecting with the fuselage of the aircraft; A tilting connection member, used to connect to a driving mechanism of a power output device of the aircraft, wherein the driving mechanism is used to drive the propeller assembly to rotate and / or drive the blades to rotate to adjust the pitch; a tilt drive assembly; and A tilt transmission assembly is rotatably connected to the connecting seat; it cooperates with the tilt drive assembly in threaded transmission to convert the rotational motion of the tilt drive assembly into at least part of the linear motion of the tilt transmission assembly; the tilt transmission assembly is connected to the tilt connecting piece to drive the tilt connecting piece to rotate relative to the connecting seat, thereby driving the drive mechanism and the propeller assembly to tilt.

116. The tilting mechanism according to claim 115, characterized in that: The tilt transmission assembly comprises: A tilt push rod, which is in driving connection with the tilt drive assembly, wherein the tilt push rod and the tilt drive assembly are threadedly driven to convert the rotational motion of the tilt drive assembly into the linear motion of the tilt push rod; and The transmission frame is rotatably arranged on the connecting seat, the tilt push rod is connected to the transmission frame to push the transmission frame to rotate, and the transmission frame is connected to the tilt connecting member to drive the tilt connecting member to rotate.

117. The tilting mechanism according to claim 116, characterized in that: The transmission frame comprises: A first bracket, one end of which is hinged to the tilting connector, and the other end of which is hinged to the connecting seat; A second bracket, one end of which is hinged to the connecting seat; The third bracket is hinged to the other end of the second bracket, and one end of the third bracket away from the second bracket is hinged to the tilting connection piece.

118. The tilting mechanism according to claim 115, characterized in that: The connecting seat is used for detachable connection with the fuselage body.

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