CN117342007A

CN117342007A - Unmanned helicopter

Info

Publication number: CN117342007A
Application number: CN202311491316.0A
Authority: CN
Inventors: 刘焯; 王金林
Original assignee: Beijing Hangyi Technology Co ltd
Current assignee: Beijing Hangyi Technology Co ltd
Priority date: 2023-11-09
Filing date: 2023-11-09
Publication date: 2024-01-05

Abstract

The application discloses unmanned helicopter relates to unmanned aerial vehicle technical field. The engine assembly of the unmanned helicopter is arranged on a frame of a fuselage and comprises an engine and a plurality of shock absorbers arranged around the engine, and the shock absorbers are directly or indirectly connected with the engine and the frame of the fuselage. The at least two shock absorbers are respectively positioned at two sides of the gravity center of the engine in the front-rear direction of the unmanned helicopter; the at least two shock absorbers are respectively positioned at two sides of the gravity center of the engine in the upper and lower directions of the unmanned helicopter; at least two shock absorbers are respectively positioned at two sides of the center of gravity of the engine in the left-right direction of the unmanned helicopter. Because the front and back, the left and right and the upper and lower of the center of gravity of the engine are distributed with the shock absorbers, the center of gravity of the engine is surrounded by the shock absorbers, the periphery of the engine is uniformly supported and damped by the shock absorbers in a multi-point manner, and the engine is not easy to swing due to the lack of support and shock absorption on one side of the engine, so that the stability of the engine is better, and the unmanned helicopter also has better stability.

Description

Unmanned helicopter

Technical Field

The application relates to the technical field of unmanned aerial vehicles, in particular to an unmanned helicopter.

Background

The engine of unmanned helicopter is in vibration condition during operation, so that the shock absorber is often used during installation. In the related art, a plurality of dampers are provided on the same side of an engine, for example, each damper is provided on the lower side or the rear side of the engine. The shock absorber can cause uneven stress of the engine, is easy to swing in vibration and has poor stability.

Disclosure of Invention

The purpose of this application includes providing an unmanned helicopter, and it can make engine atress more even, and stability is better.

Embodiments of the present application may be implemented as follows:

the application provides an unmanned helicopter, comprising:

a fuselage frame;

the engine assembly is arranged on the frame and comprises an engine and a plurality of shock absorbers arranged around the engine, and the shock absorbers are directly or indirectly connected with the engine and the frame; the at least two shock absorbers are respectively positioned at two sides of the gravity center of the engine in the front-rear direction of the unmanned helicopter; the at least two shock absorbers are respectively positioned at two sides of the gravity center of the engine in the upper and lower directions of the unmanned helicopter; the at least two shock absorbers are respectively positioned at two sides of the gravity center of the engine in the left-right direction of the unmanned helicopter;

A rotor assembly;

the transmission mechanism comprises a transmission shaft, and the transmission shaft is used for connecting the rotor wing assembly with the engine in a transmission way.

In an alternative embodiment, the engine assembly includes an inner mounting bracket coupled to the engine and an outer mounting bracket coupled to the fuselage frame, and the shock absorber is coupled to the inner mounting bracket and the outer mounting bracket.

In an alternative embodiment, the inner mounting bracket comprises an upper inner bracket, the outer mounting bracket comprises an upper outer bracket, the upper inner bracket is connected to the engine, and the upper outer bracket is connected to the fuselage frame; along the up-down direction of the unmanned helicopter, the upper end of the shock absorber above the center of gravity of the engine is connected with the upper inner bracket, and the lower end is connected with the upper outer bracket.

In an alternative embodiment, the inner mounting bracket comprises a lower inner bracket, the outer mounting bracket comprises a lower outer bracket, the lower inner bracket is connected to the engine, and the lower outer bracket is connected to the fuselage frame; along the upper and lower direction of unmanned helicopter, the upper end of the shock absorber below the engine gravity center is connected with the lower inner support, and the lower end is connected with the lower outer support.

In an alternative embodiment, the transmission mechanism further comprises a fixing assembly, the fixing assembly comprises a fixing seat and connecting structures arranged at two opposite ends of the fixing seat, the two connecting structures are detachably connected with two beams of the frame, a shaft hole penetrating through the fixing seat is formed in the fixing seat, and the shaft hole is in plug-in fit with the transmission shaft and enables the transmission shaft to rotate relative to the fixing seat.

In an alternative embodiment, the rotor assembly comprises a rotor shaft and a propeller connected to one end of the rotor shaft, the transmission mechanism further comprises a gear box and a shaft supporting assembly, the gear box comprises a box body and a gear assembly arranged in the box body, and the propeller is in transmission connection with the gear assembly through the rotor shaft; the spindle support assembly includes:

the main shaft bracket is connected with a box body of the gear box;

the support seat is arranged on the main shaft support, the support seat is provided with a main shaft matching hole, the main shaft matching hole is in plug-in matching with the rotor shaft, and the rotor shaft can rotate relative to the support seat.

In an alternative embodiment, the spindle bracket comprises a first supporting frame and a second supporting frame, wherein the first supporting frame and the second supporting frame are both used for being connected with the box body of the gear box, are arranged at intervals in the radial direction of the spindle matching hole, and are respectively connected with two opposite sides of the supporting seat in the radial direction of the spindle matching hole.

The beneficial effects of the embodiment of the application are that:

the unmanned helicopter that this application provided includes fuselage frame, engine subassembly, rotor subassembly and drive mechanism, and engine subassembly includes the engine and sets up a plurality of shock absorbers around the engine, and the shock absorber is connected with the fuselage frame of engine and unmanned helicopter directly or indirectly. The at least two shock absorbers are respectively positioned at two sides of the gravity center of the engine in the front-rear direction of the unmanned helicopter; the at least two shock absorbers are respectively positioned at two sides of the gravity center of the engine in the upper and lower directions of the unmanned helicopter; at least two shock absorbers are respectively positioned at two sides of the center of gravity of the engine in the left-right direction of the unmanned helicopter. Because the front and back, the left and right and the upper and lower of the center of gravity of the engine are distributed with the shock absorbers, the center of gravity of the engine is surrounded by the shock absorbers, the periphery of the engine is uniformly supported and damped by the shock absorbers in a multi-point manner, and the engine is not easy to swing due to the lack of support and shock absorption on one side of the engine, so that the stability of the engine is better. Further, the application provides an unmanned helicopter still includes fixed subassembly, and fixed subassembly can fix the transmission shaft of unmanned helicopter between two roof beams of fuselage frame for the transmission shaft is difficult to swing in radial, consequently has better stability, is favorable to improving transmission efficiency, life, avoids abnormal sound. In addition, the fixing assembly can connect two beams of the fuselage frame, so that the structural stability of the fuselage frame can be further improved. Further, the application provides an unmanned helicopter still includes main shaft supporting component, and main shaft supporting component includes main shaft support and supporting seat, and main shaft support is used for connecting the box of gear box, and the supporting seat sets up in the support, and the supporting seat has main shaft mating hole, and main shaft mating hole is used for pegging graft the cooperation with the rotor main shaft to make the rotor main shaft can rotate for the supporting seat. Through setting up main shaft supporting component, the supporting seat passes through the box fixed connection of main shaft support and gear box to can support the rotor main shaft between screw and the gear box effectively, make even if rotor main shaft length is longer, also can keep better stability under the supporting action of the supporting seat of main shaft supporting component. In this case, too, the rigidity requirement for the rotor main shaft can be reduced to some extent.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered limiting the scope, and that other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic illustration of an assembly of a fuselage frame, engine assembly, and transmission mechanism in one embodiment of the present application;

FIG. 2 is a schematic diagram illustrating the assembly of an engine assembly according to one embodiment of the present disclosure;

FIG. 3 is an exploded view of an engine assembly in one embodiment of the present application;

FIG. 4 is a schematic illustration of an engine assembly with a cylinder block omitted in one embodiment of the present application;

FIG. 5 is a schematic view of an assembly of an upper inner bracket, an upper outer bracket, and a shock absorber according to one embodiment of the present application;

FIG. 6 is an exploded view of an upper inner bracket, an upper outer bracket, and a shock absorber in one embodiment of the present application;

FIG. 7 is a cross-sectional view of the upper outer bracket, shock absorber and upper inner bracket mating portion of an embodiment of the present application;

FIG. 8 is a schematic view of an assembly of a front lower inner bracket, a shock absorber, and a lower outer bracket in one embodiment of the present application;

FIG. 9 is a schematic view of an assembly of a rear lower inner bracket, a shock absorber, and a lower outer bracket in one embodiment of the present application;

FIG. 10 is a schematic illustration of the position distribution of six shock absorbers and an engine in accordance with another embodiment of the present application;

FIG. 11 is a schematic view of the position distribution of twelve shock absorbers and an engine in accordance with another embodiment of the present application;

FIG. 12 is a schematic view of an assembly of a fuselage frame and a transmission mechanism (gearbox not shown) in one embodiment of the present application;

FIG. 13 is a schematic illustration of the attachment of the drive mechanism to the header in one embodiment of the present application;

FIG. 14 is a schematic view of a fixation assembly (with various screws omitted) in one embodiment of the present application;

FIG. 15 is a schematic view of a fixing base and an upper half ring according to an embodiment of the present application;

FIG. 16 is a cross-sectional view of the bottom bracket, pulley and stationary assembly in an assembled state in one embodiment of the present application;

FIG. 17 is a schematic view of an assembly of a gearbox, rotor mast, and mast support assembly according to one embodiment of the present application;

FIG. 18 is a schematic view of a spindle support assembly (with the protective sleeve omitted) according to one embodiment of the present application;

FIG. 19 is a schematic view of a first support frame according to an embodiment of the present disclosure;

FIG. 20 is a schematic view of a second support frame according to an embodiment of the present disclosure;

FIG. 21 is a schematic view of a support base according to an embodiment of the present disclosure at a first view angle;

FIG. 22 is a schematic view of a support base according to an embodiment of the present disclosure at a second view angle;

FIG. 23 is a schematic view of a support bracket connection according to one embodiment of the present disclosure;

FIG. 24 is a schematic view of a rocker arm mount in one embodiment of the present application at a first view angle;

fig. 25 is a schematic view of a rocker arm mount in an embodiment of the present application at a second perspective.

Icon: 100-an engine assembly; 110-an engine; 111-cylinder; 112-an engine mount; 120-upper inner support; 121-front connector; 122-front connection; 123-front mounting; 124-rear connectors; 125-rear connection; 126-rear mount; 127-cross beam; 130-a shock absorber; 131-a threaded hole; 132-studs; 133-nut; 140-upper outer rack; 141-U-shaped frame; 142-supporting the bottom plate; 143-side plates; 144-through holes; 145-upper connection structure; 150-lower inner support; 151-front lower inner support; 152-front base; 153-front lower connection; 154-rear lower inner rack; 155-a rear base; 156-rear lower connection; 160-lower outer rack; 161-lower connection structure;

200-fuselage frames; 210-top beam; 220-bottom beams; 230-front beam; 240-rear beam; 250-connecting beams; 260-gearbox mount;

300-transmission mechanism; 310-a transmission shaft; 311-front axle; 312-middle axis; 313-rear axle; 314-a coupling; 320-pulleys; 321-a pulley body; 322-end plates; 323-a second bearing; 324-third bearing; 325-inner sleeve; 326-outer sleeve; 330-a fixed assembly; 331-fixing base; 332-shaft hole; 333-bearing mounting slots; 334-a weight reduction tank; 335-blocking screw mounting holes; 336-blocking screw; 337—a first bearing; 340-anchor ear structure; 341-an upper half ring; 342-reinforcing ribs; 343-a lower half ring;

400-gear box;

500-spindle support assembly; 510-a first support frame; 511-a first mounting hole; 512-a first positioning groove; 513-a first gap; 514-a second mounting hole; 515-a third assembly hole; 516-fourth mounting holes; 517-a third positioning slot; 518-a first lightening hole; 520-a second support frame; 521-fifth mounting holes; 522-a second detent; 523-a second gap; 524-sixth mounting hole; 525-seventh mounting holes; 526-eighth fitting hole; 527-fourth positioning slot; 528-second lightening holes; 529-steering engine hole; 5291-steering engine mounting holes; 530-a support base; 531-spindle mating holes; 532—a first screw hole; 533-second screw hole; 534-a first positioning boss; 535-a second positioning boss; 536-lower flange; 537-sheath mounting holes; 540-a support frame connection; 541-connecting the bodies; 542-external hole; 543-connecting bumps; 544-third screw holes; 550-rocker arm mount; 551-connecting arms; 5511-fourth positioning boss; 5512-fifth screw holes; 552-a connection; 5521-a third positioning boss; 5522-fourth screw holes; 553-a mounting portion; 5531-rocker arm mounting holes; 560-protective sleeve;

600-steering engine; 610-rocker arm;

700-rotor mast.

Detailed Description

For the purposes of making the objects, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments. The components of the embodiments of the present application, which are generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present application, as provided in the accompanying drawings, is not intended to limit the scope of the application, as claimed, but is merely representative of selected embodiments of the application. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.

It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.

In the description of the present application, it should be noted that, if the terms "upper," "lower," "inner," "outer," and the like indicate an azimuth or a positional relationship based on the azimuth or the positional relationship shown in the drawings, or the azimuth or the positional relationship in which the inventive product is conventionally put in use, it is merely for convenience of describing the present application and simplifying the description, and it is not indicated or implied that the apparatus or element referred to must have a specific azimuth, be configured and operated in a specific azimuth, and thus should not be construed as limiting the present application.

Furthermore, the terms "first," "second," and the like, if any, are used merely for distinguishing between descriptions and not for indicating or implying a relative importance.

It should be noted that, without conflict, features in embodiments of the present application may be combined with each other.

In the related art, an engine of an unmanned helicopter is connected to a fuselage frame through a plurality of dampers, which are disposed on the same side of the engine, such as each damper being disposed on a lower side or a rear side of the engine. This damper arrangement results in one side of the engine being supported by the damper and the opposite side being unsupported, the unsupported side of the engine being prone to wobble when the engine is running, resulting in unstable wobble of the engine output shaft and ultimately in unstable gears or pulleys mounted on the engine output shaft. Instability of the engine and associated transmission components may ultimately lead to transmission failure or transmission inefficiency.

In order to solve the problem of poor engine stability in the related art, the embodiment of the application provides an unmanned helicopter, which improves the uniformity of stress of an engine by distributing a plurality of shock absorbers around the center of gravity of the engine, thereby improving the stability.

Fig. 1 is a schematic diagram illustrating an assembly of a fuselage frame 200, an engine assembly 100, and a transmission 300 according to one embodiment of the present application. The unmanned helicopter provided by the embodiment of the application comprises a fuselage frame 200, an engine assembly 100, a rotor assembly and a transmission mechanism 300, wherein the engine assembly 100 is installed on the fuselage frame 200. In addition, the unmanned helicopter also comprises a control system, a shell and other components which are not shown in the figure. The unmanned helicopter provided by the embodiment of the application can be a tandem double-rotor unmanned helicopter.

In the present embodiment, the fuselage frame 200 includes two top beams 210 and two bottom beams 220 extending in the front-rear direction of the unmanned helicopter (the direction indicated by the arrow ab in the figure), the two top beams 210 being spaced apart in the left-right direction of the unmanned helicopter, and the two bottom beams 220 also being spaced apart in the left-right direction of the unmanned helicopter (the direction indicated by the arrow cd in the figure). The top beams 210 are spaced from the bottom beams 220 in the up-down direction (indicated by arrow ef) of the unmanned helicopter, with two top beams 210 up and two bottom beams 220 down. In this embodiment, the engine assembly 100 is coupled to two top beams 210 and two bottom beams 220.

FIG. 2 is a schematic diagram illustrating the assembly of engine assembly 100 in one embodiment of the present application; fig. 3 is an exploded view of engine assembly 100 in one embodiment of the present application. Referring to fig. 1-3, in an embodiment of the present application, an engine assembly 100 includes an engine 110 and a plurality of shock absorbers 130 disposed about the engine 110, the shock absorbers 130 being for direct or indirect connection with the engine 110 and a fuselage frame 200 of an unmanned helicopter. In order to enable the engine 110 to uniformly receive force, at least two dampers 130 are respectively located at both sides of the center of gravity of the engine 110 in the front-rear direction of the unmanned helicopter, at least two dampers 130 are respectively located at both sides of the center of gravity of the engine 110 in the up-down direction of the unmanned helicopter, and at least two dampers 130 are respectively located at both sides of the center of gravity of the engine 110 in the left-right direction of the unmanned helicopter. By the arrangement, the center of gravity of the engine 110 can be surrounded by the shock absorber 130, so that the problem that a plurality of positions around the engine 110 (around and up and down) are supported and damped by the shock absorber 130 in a multipoint manner, the stress is more uniform, and the swing problem of a certain side of the engine 110 due to lack of support and damping is not easy to occur.

Further, the engine assembly 100 includes an inner mounting bracket coupled to the engine 110 and an outer mounting bracket for coupling to the fuselage frame 200, to which the shock absorber 130 is coupled. In the present embodiment, the engine 110, the inner mounting bracket, the damper 130, the outer mounting bracket, and the body frame 200 are sequentially connected, thereby achieving the mounting and fixing of the engine 110 on the body frame 200. Since the engine 110 has an irregular shape, in the present embodiment, the damper 130 is disposed between the inner mounting bracket and the outer mounting bracket, and is connected with the engine 110 through the inner mounting bracket, and is connected with the fuselage frame 200 through the outer mounting bracket, so that the suitability of the engine 110 and the fuselage frame 200 can be increased by adding the inner mounting bracket and the outer mounting bracket, which is convenient for better mounting the engine 110 to the fuselage frame 200. In alternative other embodiments, the engine 110 may be coupled directly to the shock absorber 130 and/or the shock absorber 130 may be coupled directly to the fuselage frame 200.

In the present embodiment, the engine 110 includes a cylinder 111 and an engine bracket 112, the engine bracket 112 is connected to the rear end of the cylinder 111 in the front-rear direction of the unmanned helicopter (i.e., the outer surface of one end of the cylinder 111), an inner mounting bracket at one end remote from the engine bracket 112 is connected to the cylinder 111, and an inner mounting bracket at one end near the engine bracket 112 is connected to the engine bracket 112 to be connected to the cylinder 111 through the engine bracket 112. Because the cylinder 111 of the engine 110 is irregular in shape, the engine bracket 112 is additionally arranged, so that the inner mounting bracket is indirectly and fixedly connected with the cylinder 111 through the engine bracket 112 at a local position, the suitability of the cylinder 111 can be improved to a certain extent, and the engine 110 has an appearance convenient to mount. Alternatively, the cylinder 111 of the engine 110 and the engine bracket 112 may be detachably connected by using fasteners such as screws, or may be connected by welding. The cylinder 111 and the inner mounting bracket, and the inner mounting bracket and the engine bracket 112 can be detachably connected by fasteners such as screws. In the present embodiment, one end of the cylinder 111 is connected to the engine bracket 112 by screws (optionally, four screws) in the fore-and-aft direction of the unmanned helicopter to be connected to the inner mounting bracket by the engine bracket 112, and the other end of the cylinder 111 is directly connected to the inner mounting bracket. In alternative other embodiments, the engine 110 may not include an engine mount 112, with the inner mounting mount being directly coupled to the cylinder 111.

Fig. 4 is a schematic illustration of engine assembly 100 with cylinder 111 omitted in one embodiment of the present application. Referring to fig. 1 to 4, in the present embodiment, the inner mounting bracket includes an upper inner bracket 120, the outer mounting bracket includes an upper outer bracket 140, the upper inner bracket 120 is connected to the engine 110, and the upper outer bracket 140 is used to connect to the body frame 200; in the up-down direction of the unmanned helicopter, the upper end of the damper 130 located above the center of gravity of the engine 110 is connected to the upper inner bracket 120, and the lower end is connected to the upper outer bracket 140. By the arrangement, the shock absorber 130 above the center of gravity of the engine 110 still plays a role in supporting and absorbing shock to the engine 110, bears a part of the gravity of the engine 110, and avoids the other shock absorbers 130 from bearing excessive downward pressure. Further, the inner mounting bracket further comprises a lower inner bracket 150, the outer mounting bracket further comprises a lower outer bracket 160, the lower inner bracket 150 is connected to the engine 110, and the lower outer bracket 160 is used for connecting to the frame 200; in the up-down direction of the unmanned helicopter, the upper end of the damper 130 located below the center of gravity of the engine 110 is connected to the lower inner bracket 150, and the lower end is connected to the lower outer bracket 160.

In the present embodiment, engine assembly 100 includes a total of eight shock absorbers 130, with four shock absorbers 130 located on the lower side of the center of gravity of engine 110 and four shock absorbers 130 located on the upper side of the center of gravity of engine 110. Thus, four dampers 130 are connected to the upper inner bracket 120 and the upper outer bracket 140, and the other four dampers 130 are connected to the lower inner bracket 150 and the lower outer bracket 160. Specifically, in the present embodiment, eight dampers 130 are provided around the engine 110, and four dampers 130 located on the lower side of the center of gravity of the engine 110 are respectively arranged at four positions of the lower left front, the lower right front, the lower left rear, and the lower right rear of the engine 110. Four dampers 130 located at the upper center of gravity of the engine 110 are respectively disposed at four positions of the upper left front, the upper right front, the upper left rear, and the upper right rear of the engine 110.

FIG. 5 is a schematic view of the assembly of the upper inner bracket 120, the upper outer bracket 140, and the shock absorber 130 in one embodiment of the present application; fig. 6 is an exploded view of upper inner leg 120, upper outer leg 140, and shock absorber 130 in one embodiment of the present application. As shown in fig. 5 and 6, in the present embodiment, the upper inner bracket 120 includes a front link 121, a rear link 124, and two cross members 127, the front link 121 and the rear link 124 are spaced apart in the front-rear direction of the unmanned helicopter, the two cross members 127 are spaced apart in the left-right direction of the unmanned helicopter and extend in the front-rear direction of the unmanned helicopter, both ends of the cross members 127 are respectively connected to the front link 121 and the rear link 124, the front link 121 and the rear link 124 are connected to the engine 110, the front link 121 and the rear link 124 are respectively connected to the shock absorbers 130, and the shock absorbers 130 connected to the front link 121 and the shock absorbers 130 connected to the rear link 124 are respectively located at both sides of the center of gravity of the engine 110 in the front-rear direction of the unmanned helicopter. Alternatively, the cross member 127 and the front connecting member 121, and the cross member 127 and the rear connecting member 124 may be connected by using a welding or a screw or the like. In the present embodiment, the front link 121, the rear link 124, and the two cross members 127 of the upper inner bracket 120 form a frame structure, and thus have superior stability.

Further, the beam 127 is provided with a plurality of lightening holes to reduce the weight of the upper inner bracket 120, which is beneficial to reducing the load of the unmanned helicopter.

Further, two dampers 130 are connected to each of the front link 121 and the rear link 124. Wherein, two dampers 130 connected with the front connection member 121 are respectively connected to both ends of the front connection member 121 in the left-right direction of the unmanned helicopter, so that the two dampers 130 connected with the front connection member 121 are respectively located at both sides of the center of gravity of the engine 110 in the left-right direction of the unmanned helicopter. The two dampers 130 connected to the rear link 124 are respectively connected to both ends of the rear link 124 in the left-right direction of the unmanned helicopter such that the two dampers 130 connected to the rear link 124 are respectively located at both sides of the center of gravity of the engine 110 in the left-right direction of the unmanned helicopter.

In the present embodiment, the front connection member 121 includes two front connection portions 122 and two front mounting portions 123, the two front connection portions 122 being connected to the cylinder 111 of the engine 110, the two front mounting portions 123 each being connected to one shock absorber 130, respectively; alternatively, the two front connection parts 122 are connected to the cylinder 111 of the engine 110 by two screws. The rear connecting member 124 includes a rear connecting portion 125 and two rear mounting portions 126, the rear connecting portion 125 being connected to the engine bracket 112, the two rear mounting portions 126 each being connected to one of the dampers 130; alternatively, the rear connection portion 125 is connected to the engine bracket 112 by two screws.

Further, the upper inner bracket 120 has a symmetrical structure in the left-right direction of the unmanned helicopter, which is beneficial to balancing the stress of the engine 110 and balancing the unmanned helicopter.

In the present embodiment, the outer mounting bracket of the engine assembly 100 includes a plurality of upper outer brackets 140, and the number of upper outer brackets 140 is the same as and corresponds to one with the number of shock absorbers 130 to which the upper inner brackets 120 are connected. Fig. 7 is a cross-sectional view of the upper outer bracket 140, the shock absorber 130, and the upper inner bracket 120 in one embodiment of the present application. As shown in fig. 7, the upper outer brackets 140 include a U-shaped frame 141 and an upper connection structure 145, the U-shaped frame 141 includes a supporting bottom plate 142 and side plates 143 connected to both ends of the supporting bottom plate 142, the supporting bottom plate 142 and the side plates 143 enclose an accommodating space, the dampers 130 connected to the upper inner brackets 120 are disposed in the accommodating space of each upper outer bracket 140 in a one-to-one correspondence and connected to the supporting bottom plate 142, the upper connection structure 145 is connected to both side plates 143, and the upper connection structure 145 is used to connect the body frame 200. The U-shaped frame 141 can be formed by bending a metal plate body, so that the structure stability is better; the U-shaped frame 141 and the upper connecting structure 145 can be connected by fasteners or by welding.

In the previous description of the connection manner of the connecting member 121 and the upper outer bracket 140, the lower end of the shock absorber 130 is provided with the threaded hole 131, and the supporting base plate 142 of the upper outer bracket 140 is provided with the through hole 144, so that the shock absorber 130 and the supporting base plate 142 can be connected by a screw (not shown). The upper end of the shock absorber 130 is provided with a stud 132, and the stud 132 is penetrated through a hole on the front mounting portion 123 and is engaged with a nut 133, thereby fixing the shock absorber 130 to the front connection member 121. The connection manner among the rear connection member 124, the shock absorber 130 and the upper outer bracket 140 is the same as that described above, and will not be repeated here.

Further, the upper connection structure 145 is a hoop structure. The upper outer support 140 and the top beam 210 can be stably connected through the hoop structure, so that the risk of welding cracking is avoided, and the assembly is convenient.

In this embodiment, the inner mounting bracket includes two lower inner brackets 150, and the two lower inner brackets 150 are disposed at intervals in the front-rear direction of the unmanned helicopter. The outer mounting brackets include two lower outer brackets 160, and the two lower outer brackets 160 are arranged at intervals in the front-rear direction of the unmanned helicopter and correspond to the two lower inner brackets 150 one by one. The lower outer bracket 160 is provided with lower connection structures 161 at both ends in the left-right direction of the unmanned helicopter, respectively, and the lower connection structures 161 are used to connect the fuselage frame 200. Optionally, the lower connection structure 161 is specifically configured to connect to the bottom beam 220 of the fuselage frame 200.

FIG. 8 is a schematic view illustrating the assembly of the front lower inner bracket 151, the shock absorber 130, and the lower outer bracket 160 according to an embodiment of the present application; fig. 9 is a schematic view illustrating an assembly of the rear lower inner bracket 154, the shock absorber 130, and the lower outer bracket 160 in one embodiment of the present application. Referring to fig. 8 and 9 in combination with fig. 1 to 4, in the present embodiment, the front and rear lower internal brackets 150 may have different structures. Of the two lower inner brackets 150, the lower inner bracket 150 forward in the front-rear direction of the unmanned helicopter is a front lower inner bracket 151, and the lower inner bracket 150 rearward in the front-rear direction of the unmanned helicopter is a rear lower inner bracket 154. The front lower inner bracket 151 is connected to the cylinder 111, and the rear lower inner bracket 154 is connected to the engine bracket 112 to be connected to the cylinder 111 through the engine bracket 112.

Specifically, in the present embodiment, the front lower inner bracket 151 includes a front base 152 extending in the left-right direction of the unmanned helicopter, and two front lower connection portions 153 connected to the upper sides of the front base 152, the front base 152 is respectively connected to one shock absorber 130 at the lower sides of both ends in the left-right direction of the unmanned helicopter, and the two front lower connection portions 153 are disposed at intervals in the left-right direction of the unmanned helicopter and connected to the cylinder 111. Specifically, the front lower connection portion 153 is connected to the cylinder 111 by a screw. The two front lower connecting portions 153 may be two parallel spaced plate bodies, and the two sides of the two front lower connecting portions 153 facing away from each other may be provided with reinforcing ribs to improve structural strength.

In the present embodiment, the rear lower inner bracket 154 includes a rear base 155 extending in the left-right direction of the unmanned helicopter and a rear lower connecting portion 156 connected to the upper side of the rear base 155, the rear base 155 being connected to one shock absorber 130 at each of the lower sides of both ends of the unmanned helicopter in the left-right direction, the rear lower connecting portion 156 being connected to the engine bracket 112. Specifically, the rear base 155 is a plate body horizontally disposed, the rear lower connecting portion 156 is a plate body perpendicular to the rear base 155, and the rear lower connecting portion 156 is connected to the engine bracket 112 by screws. A reinforcing rib may be provided between the rear chassis 155 and the rear lower connection portion 156 to improve the connection strength therebetween. Weight reducing holes may be provided on the rear chassis 155 and the rear lower connection part 156 to reduce weight.

In alternative other embodiments, the front and rear lower internal brackets 150 may be identical in structure.

As shown in fig. 1 to 4 and fig. 8 and 9, two dampers 130 are provided between each lower inner bracket 150 and its corresponding lower outer bracket 160, and two dampers 130 connected to the lower inner bracket 150 are located at both ends of the lower inner bracket 150 in the left-right direction of the unmanned helicopter, so that two dampers 130 connected to the lower inner bracket 150 are located at both sides of the center of gravity of the engine 110 in the left-right direction of the unmanned helicopter, respectively. The shock absorber 130 may be connected to the lower inner bracket 150 and the lower outer bracket 160 by screws. The upper end of the lower inner bracket 150 may be coupled to the cylinder 111 of the engine 110 or the engine bracket 112 by a screw.

In this embodiment, the lower connection structure 161 is a hoop structure, through which stable connection between the lower outer bracket 160 and the fuselage frame 200 can be achieved, specifically, the hoop structure achieves stable connection between the lower outer bracket 160 and the bottom beam 220, avoids the risk of welding cracking, and is convenient for assembly.

The outer mounting bracket in this embodiment includes a hoop structure for connecting the fuselage frame 200, and the connection of the outer mounting bracket and the fuselage frame 200 is realized through a plurality of hoop structures, so that the rapid assembly of the engine assembly 100 can be realized. In alternative embodiments, the outer mounting brackets may be attached to the airframe 200 by other means, such as by fasteners such as screws or by welding to the airframe 200.

In this embodiment, the lower outer bracket 160 is provided with a plurality of lightening holes, so that the weight of the lower outer bracket 160 is lightened, which is beneficial to reducing the load of the unmanned helicopter.

Optionally, the overall structure formed by the lower outer bracket 160, the lower inner bracket 150 and the shock absorber 130 connected with the two is symmetrical in the left-right direction of the unmanned helicopter, which is beneficial to the uniform stress of the engine 110 and the left-right balance of the unmanned helicopter.

In this embodiment, the main body of the shock absorber 130 has a certain flexibility (such as rubber material), and can provide a certain buffer when the engine 110 vibrates, so as to avoid the influence on the flight caused by the severe vibration of the engine 110 on the fuselage frame 200 or other parts of the unmanned helicopter. The engine assembly 100 in the present embodiment employs eight shock absorbers 130 to achieve multi-point support of the engine 110; in alternative embodiments, the number of shock absorbers 130 may be increased or decreased, such as providing six or twelve shock absorbers 130.

Fig. 10 is a schematic diagram illustrating a position distribution of six dampers 130 and an engine 110 according to another embodiment of the present application. In the embodiment shown in fig. 10, engine assembly 100 includes six shock absorbers 130, with four shock absorbers 130 located on the underside of the center of gravity of engine 110 and two shock absorbers 130 located on the upper side of the center of gravity of engine 110. Specifically, in this other embodiment, six dampers 130 are provided around the engine 110, four dampers 130 located on the lower side of the center of gravity of the engine 110 are respectively arranged at four positions of the lower left front, lower right front, lower left rear, lower right rear of the engine 110, and two dampers 130 located on the upper side of the center of gravity of the engine 110 are provided at intervals in the front-rear direction.

Fig. 11 is a schematic diagram illustrating a position distribution of twelve dampers 130 and an engine 110 according to another embodiment of the present application. In the embodiment shown in fig. 11, engine assembly 100 includes twelve shock absorbers 130, with six shock absorbers 130 located on the underside of the center of gravity of engine 110 and six shock absorbers 130 located on the upper side of the center of gravity of engine 110. Specifically, in this further embodiment, twelve dampers 130 are disposed around the engine 110, among six dampers 130 located on the lower side of the center of gravity of the engine 110, two dampers 130 are disposed at the lowest part of the engine 110 and at intervals front and rear, and four dampers 130 are disposed at four positions of the left front lower, the right front lower, the left rear lower, and the right rear lower of the engine 110, respectively. Of the six dampers 130 located on the upper side of the center of gravity of the engine 110, two dampers 130 are disposed at the uppermost side of the engine 110 and are disposed at intervals front and rear, and four dampers 130 are disposed at four positions of the upper left front, the upper right front, the upper left rear, and the upper right rear of the engine 110, respectively.

In the above embodiments of the present application, the plurality of dampers 130 on the same side of the engine 110 are optionally located on the same plane. Specifically, in the eight-damper 130 embodiment, four dampers 130 located on the upper side of the engine 110 are located on the same plane, and four dampers 130 located on the lower side of the center of gravity of the engine 110 are located on the same plane; in the six-damper 130 embodiment, two dampers 130 located on the upper side of the engine 110 are located on the same plane, and four dampers 130 located on the lower side of the center of gravity of the engine 110 are located on the same plane. The dampers 130 located on the same side of the engine 110 are disposed on the same plane so that the dampers 130 are uniformly stressed.

However, the present application is not limited thereto, and alternatively, the plurality of dampers 130 located on the same side of the engine 110 may not be in the same plane. For example, in the twelve damper 130 embodiment, a plurality of dampers 130 on the same side of the engine 110 are located in two planes, respectively; specifically, the two shock absorbers 130 located at the lowermost part of the engine 110 are located on the same plane, and the four shock absorbers 130 located at the four positions of the left front lower, the right front lower, the left rear lower, and the right rear lower of the engine 110 are located on the same plane; the two dampers 130 located at the uppermost of the engine 110 are located on the same plane, and the four dampers 130 located at the four positions of the left front upper, the right front upper, the left rear upper, and the right rear upper of the engine 110 are located on the same plane. Also, the present application is not limited thereto, and the plurality of shock absorbers 130 located on the same side of the engine 110 may be distributed in other forms as long as the plurality of shock absorbers 130 are disposed around the center of gravity of the engine 110.

It should be understood that the distribution position of each damper 130 in the present application may be adjusted according to needs, but it is required to ensure that the dampers 130 are distributed in front of and behind the center of gravity of the engine 110, in the left and right directions, and in the up and down directions, so that the center of gravity of the engine 110 is uniformly supported and damped by a plurality of dampers 130 at multiple points.

Fig. 12 is a schematic diagram illustrating an assembly of the frame 200 and a transmission 300 (gearbox not shown) according to an embodiment of the present application. As shown in fig. 12, the unmanned helicopter of the present embodiment includes two rotor assemblies arranged at intervals in the front-rear direction thereof (the direction indicated by arrow ab in the drawing), and a transmission mechanism 300 drivingly connects an engine 110 (see fig. 2) with the two rotor assemblies at the same time, so that the engine 110 can output power to the two rotor assemblies at the same time through one transmission mechanism 300.

In the embodiment of the present application, the fuselage frame 200 includes two beams spaced apart in the left-right direction of the unmanned helicopter (the direction indicated by the arrow cd in the figure), and the transmission mechanism 300 is connected to the two beams spaced apart in the left-right direction of the unmanned helicopter. Specifically, the fuselage frame 200 includes two side frames disposed at intervals in the left-right direction of the unmanned helicopter, and optionally, the two side frames are disposed symmetrically. The side frames include top beams 210 and bottom beams 220 spaced in the up-down direction (direction indicated by arrow ef in the figure) of the unmanned helicopter, and front beams 230 and rear beams 240 spaced in the front-rear direction of the unmanned helicopter, and the top beams 210, front beams 230, bottom beams 220 and rear beams 240 are sequentially connected to form a closed frame. A plurality of connecting beams 250 are arranged between the two side frames, a gear box mounting seat 260 is also respectively arranged between the front ends and the rear ends of the two top beams 210, and the two gear box mounting seats 260 are respectively used for mounting two gear boxes 400 (see fig. 17) corresponding to the two rotor wing assemblies. The plurality of connecting beams 250 connect the two side frames with the two gear box mounting seats 260, so that the relative positions of the two side frames are fixed, and the fuselage frame 200 has better stability. In the present embodiment, the shape and the connection manner of the connection beam 250 at different positions may be different as long as the connection of the two side frames can be performed to enhance the stability of the fuselage frame 200. For example, the connecting beam 250 may be a section bar or a pipe; the side frames can be connected through P-type hoops, and also can be connected through fasteners such as T-type hoops or bolts; can be horizontally arranged or obliquely arranged.

In this embodiment, the top beams 210 of the two side frames are spaced apart in parallel in the left-right direction of the unmanned helicopter, and the transmission mechanism 300 is connected to the two top beams 210. In other embodiments, the actuator 300 may be coupled to two other horizontally spaced beams on the fuselage frame 200.

Fig. 13 is a schematic diagram illustrating the connection of the transmission mechanism 300 to the top beam 210 in an embodiment of the present application. As shown in fig. 13, in the present embodiment, the transmission mechanism 300 includes a transmission shaft 310, a pulley 320, and a fixing assembly 330. Engine 110 is drivingly coupled to the rotor assembly via a drive shaft 310 of drive mechanism 300. The pulley 320 is connected to the drive shaft 310 and is disposed coaxially with the drive shaft 310, the pulley 320 being for driving connection with the engine 110. The transmission shaft 310 is disposed through the fixing assembly 330 and can rotate relative to the fixing assembly 330, and opposite ends of the fixing assembly 330 are respectively used for detachably connecting two beams (specifically, two top beams 210 in the embodiment) of the fuselage frame 200, which are disposed at intervals in the left-right direction of the unmanned helicopter. Because the unmanned helicopter in this embodiment is a tandem double-rotor unmanned helicopter, the transmission shaft 310 extends along the front-rear direction of the unmanned helicopter, the front and rear ends of the transmission shaft 310 are respectively in transmission connection with the rotor assembly, the belt pulley 320 is disposed between the front and rear ends of the transmission shaft 310, and the belt pulley 320 is in transmission connection with the engine 110 through a transmission belt (not shown in the figure).

Further, the transmission shaft 310 includes a front shaft 311, a middle shaft 312, and a rear shaft 313 sequentially connected in an axial direction, the pulley 320 is connected to the middle shaft 312, and the front shaft 311 and the rear shaft 313 are respectively used for transmission connection with one rotor assembly.

Further, the front axle 311, the middle axle 312 and the rear axle 313 are connected by a coupling 314, and keyways may be provided on the front axle 311, the middle axle 312 and the rear axle 313, and flat keys (not shown in the figure) may be provided in the keyways, and then are connected and matched with the coupling 314, so that synchronous rotation of the front axle 311, the middle axle 312 and the rear axle 313 may be achieved. Optionally, the front and rear ends of drive shaft 310 are also drivingly connected to the rotor assembly by a coupling 314.

The transmission mechanism 300 may include a plurality of fixing assemblies 330, and the front axle 311, the middle axle 312, and the rear axle 313 are rotatably connected to at least one fixing assembly 330, respectively. In the present embodiment, the front shaft 311, the middle shaft 312 and the rear shaft 313 are each mounted to the body frame 200 through two fixing assemblies 330, respectively, so that the stability of the entire transmission shaft 310 in the radial direction is ensured.

Alternatively, the bottom bracket 312 is rotatably connected to two fixing members 330, and the two fixing members 330 to which the bottom bracket 312 is connected are located on opposite sides of the pulley 320 in the axial direction.

FIG. 14 is a schematic view of a fixing assembly 330 (with various screws omitted) according to one embodiment of the present application; FIG. 15 is a schematic view of the fixing base 331 and the upper half ring 341 according to an embodiment of the present disclosure; fig. 16 is a cross-sectional view of the bottom bracket 312, the pulley 320, and the securing assembly 330 in an assembled state in one embodiment of the present application. As shown in fig. 14 to 16, the fixing assembly 330 in this embodiment includes a fixing base 331 and connection structures disposed at opposite ends of the fixing base 331, and the two connection structures are respectively used for detachably connecting with two beams (specifically, two top beams 210 in this embodiment) of the frame 200. The fixing base 331 is provided with a shaft hole 332 penetrating through the fixing base 331, and the shaft hole 332 is used for being in plug-in fit with the transmission shaft 310 and enabling the transmission shaft 310 to rotate relative to the fixing base 331. The fixing assembly 330 in this embodiment further includes a first bearing 337, where the first bearing 337 is embedded in the shaft hole 332, and the transmission shaft 310 is rotatably connected to the fixing base 331 through the first bearing 337. In this embodiment, the shaft hole 332 is located at the center of the connecting line between the two opposite ends of the fixed seat 331, so that the transmission shaft 310 can be centered when the fixed seat 331 is used for supporting the transmission shaft 310, which is beneficial to balancing the unmanned helicopter. Alternatively, the fixing base 331 is symmetrically disposed about the axis of the shaft hole 332.

In this embodiment, the two connection structures are two anchor ear structures 340, and two ends of the fixing seat 331 can be connected to the frame 200 through the anchor ear structures 340 respectively. Specifically, two anchor ear structures 340 are respectively connected to opposite ends of the fixing base 331 and are used for connecting the top beam 210 of the frame 200. Compared to welding, the hoop structure 340 can reduce the risk of welding cracking and improve the assembly efficiency of the transmission mechanism 300.

Specifically, the anchor ear structure 340 includes an upper half ring 341 and a lower half ring 343, the upper half ring 341 is integrally formed with the fixing seat 331, and the lower half ring 343 is detachably connected with the upper half ring 341. Alternatively, the lower half ring 343 is detachably connected to the upper half ring 341 by screws. The upper half ring 341 is fixed on the fixed seat 331, and the opening of the upper half ring 341 faces downwards, so that when the fixing component 330 is installed, the fixed seat 331 can be placed on the two top beams 210 by using the two upper half rings 341, and the fixed seat 331 is not required to be supported by hands; the lower half ring 343 is then buckled with the upper half ring 341 from bottom to top, and the fixing assembly 330 is mounted to the frame 200. The present application is not limited in sequence, and the upper half ring 341 and the lower half ring 343 may also adopt other connection manners, including but not limited to clamping, plugging, etc.

In this embodiment, the outer side of the upper half ring 341 is provided with a reinforcing rib 342, so as to increase the connection strength between the anchor ear structure 340 and the fixing seat 331. Optionally, the fixing base 331 is further provided with a weight-reducing groove 334, and in this embodiment, the weight-reducing grooves 334 are distributed on two opposite sides of the fixing base 331 along the axial direction of the shaft hole 332.

In this embodiment, two bearing mounting slots 333 are disposed at two ends of the shaft hole 332 in the axial direction, the fixing assembly 330 includes two first bearings 337, and the two first bearings 337 are disposed in the two bearing mounting slots 333, respectively. Specifically, the inner wall of the shaft hole 332 is provided with a boss extending along the circumferential direction of the shaft hole 332, two bearing mounting slots 333 are formed on two sides of the boss, and two first bearings 337 are respectively disposed in the two bearing mounting slots 333 and are abutted to two opposite sides of the boss. In the present embodiment, the boss is of an annular structure coaxial with the shaft hole 332 and is located at the middle of the shaft hole 332 in the axial direction, so that the boss partitions the shaft hole 332 into two bearing mounting grooves 333 spaced in the axial direction for mounting the two first bearings 337, respectively. By providing two first bearings 337, the supporting effect of the fixing base 331 on the driving shaft 310 can be enhanced, and the driving shaft 310 is ensured to have a small rotation resistance, thereby reducing power attenuation.

In this embodiment, a plurality of blocking screws 336 are disposed on the fixing base 331 around the shaft hole 332, and the blocking screws 336 are used for blocking the first bearing 337 from falling off the shaft hole 332. As shown in fig. 14 and 15, four blocking screw mounting holes 335 are provided on the fixing base 331, and the four blocking screw mounting holes 335 are uniformly spaced around the shaft hole 332 for cooperation with the blocking screw 336. When the blocking screw 336 is mounted to the blocking screw mounting hole 335, the head of the blocking screw 336 may abut the first bearing 337 in the axial direction of the first bearing 337, thereby preventing it from being removed from the shaft hole 332; specifically, the first bearing 337 is disposed within the bearing mounting groove 333, and the blocking screw 336 is used to block the first bearing 337 from falling off the bearing mounting groove 333. In other embodiments, the head of blocking screw 336 may not directly abut first bearing 337, but indirectly abut first bearing 337 through a spacer between the head of blocking screw 336 and fixed seat 331.

In this embodiment, the fixing base 331 is made of aluminum alloy, which has both higher strength and lower density, and is beneficial to light weight. Optionally, the fixing base 331 is made of 7075 high-strength aluminum alloy.

In this embodiment, the pulley 320 includes a pulley body 321 sleeved outside the transmission shaft 310 and two end plates 322, and the two end plates 322 are respectively connected to two ends of the pulley body 321 in the axial direction, and the outer peripheral side of the pulley body 321 is used for being sleeved with a transmission belt (not shown in the figure), and is in transmission connection with the engine 110 through the transmission belt. End plate 322 is connected to drive shaft 310 by a second bearing 323, and pulley body 321 is connected to drive shaft 310 by a third bearing 324. In this embodiment, the end plates 322 may be fixedly coupled to both ends of the pulley body 321 by fasteners. The outer edge of the end plate 322 protrudes from the outer peripheral surface of the pulley body 321, that is, the outer diameter of the end plate 322 is larger than the outer diameter of the pulley body 321, so that the driving belt is limited by the end plate 322 and is not easy to slip from the pulley body 321 after being sleeved on the pulley body 321. The third bearing 324 acts to transmit torque and ensures that the pulley 320 remains coaxial with the drive shaft 310 (in this embodiment, the central shaft 312). The third bearing 324 may be keyed to the bottom bracket 312 and the pulley body 321 to achieve torque transfer. The second bearing 323 may be a ball bearing for maintaining the end plate 322 and the bottom bracket 312 coaxial and reducing rotational friction therebetween.

In the present embodiment, an inner sleeve 325 is provided between the second bearing 323 and the third bearing 324, and both ends of the inner sleeve 325 in the axial direction abut against the second bearing 323 and the third bearing 324, respectively. The inner sleeves 325 are sleeved on the center shaft 312, and the two inner sleeves 325 clamp the third bearing 324 in the axial direction, so that the relative positions of the second bearing 323 and the third bearing 324 can be maintained. Further, an outer sleeve 326 is disposed between the second bearing 323 and the fixing component 330 on the middle shaft 312, the outer sleeve 326 is sleeved on the middle shaft 312, and two ends in the axial direction of the outer sleeve 326 respectively abut against the second bearing 323 and the first bearing 337. The outer sleeve 326 can function to maintain the relative position of the second bearing 323 and the first bearing 337, i.e., to maintain a fixed distance between the stationary assembly 330 and the pulley 320.

In this embodiment, the two fixing assemblies 330 respectively disposed on the front axle 311 and the rear axle 313 are identical in structure and installation manner to the fixing assemblies 330 on the middle axle 312, and will not be described herein. In alternative other embodiments, the number of securing assemblies 330 on front axle 311, center axle 312, and rear axle 313 may be adjusted as desired. For example, in order to adapt to the installation position of the engine 110, the length of the rear axle 313 is longer than that of the front axle 311 in the present embodiment, and in order to ensure the stability of the rear axle 313, more fixing assemblies 330 may be added to the rear axle 313.

It should be understood that, in this embodiment, the unmanned helicopter is taken as a tandem type double-rotor unmanned helicopter, and thus, two opposite ends of the transmission shaft 310 are connected to rotor assemblies; in alternative embodiments, the unmanned helicopter may be a single rotor unmanned helicopter, wherein one end of the drive shaft 310 is drivingly connected to the rotor assembly, and the pulley 320 may be disposed at the other end or between the ends of the drive shaft 310. By providing the fixing assembly 330 to fix the driving shaft 310, not only the stability of the driving shaft 310 can be improved, but also the structural stability of the fuselage frame 200 can be enhanced.

The fixing assembly 330 can fix the transmission shaft 310 of the unmanned helicopter between two beams of the fuselage frame 200, so that the transmission shaft 310 is not easy to swing in the radial direction, thereby having better stability, being beneficial to improving transmission efficiency and service life and avoiding abnormal sound. In addition, the fixing assembly 330 can connect two beams of the body frame 200, and thus structural stability of the body frame 200 can be further improved.

Figure 17 is a schematic diagram illustrating the assembly of gearbox 400, rotor mast 700, and mast support assembly 500 in one embodiment of the present application. As shown in fig. 17, the rotor assembly includes a rotor shaft 700 and a propeller (not shown) connected to one end of the rotor shaft 700, and the transmission mechanism 300 further includes a gear box 400 and a shaft support assembly 500, wherein the gear box 400 includes a box body and a gear assembly disposed in the box body, and the propeller is in transmission connection with the gear assembly through the rotor shaft 700. The bracket of the main shaft supporting assembly 500 is connected to the box body of the gear box 400, and the rotor shaft 700 is in plug-in fit with the main shaft matching hole 531 on the supporting base 530 and can rotate relative to the supporting base 530. The main shaft support assembly 500 is fixed relative to the gear case 400, and simultaneously, the main shaft 700 between the propeller and the gear case 400 is effectively supported and limited by the support base 530, so that the main shaft 700 can be prevented from swinging in the radial direction, and the stability of the main shaft 700 can be improved. By improving the structural stability of rotor head 700, the transmission stability of transmission mechanism 300 can be improved, and the transmission efficiency and the stable flight of the unmanned helicopter can be ensured.

Further, the unmanned helicopter further comprises steering gears 600, the steering gears 600 are arranged on the main shaft support assemblies 500, and in the embodiment, two steering gears 600 are arranged on each main shaft support assembly 500. The two steering engines 600 are arranged at intervals in a direction perpendicular to the axis of the main shaft fitting hole 531.

Fig. 18 is a schematic view of a spindle support assembly 500 (omitting a protective sleeve 560) according to one embodiment of the present application. As shown in fig. 18, in the embodiment of the present application, the main shaft support assembly 500 includes a main shaft bracket and a support base 530, wherein the main shaft bracket is used to connect with the box body of the gear box 400, the support base 530 is disposed on the main shaft bracket, the support base 530 has a main shaft mating hole 531, and the main shaft mating hole 531 is used to be mated with the rotor shaft 700 in a plugging manner, and enables the rotor shaft 700 to rotate relative to the support base 530. Alternatively, the connection between the spindle carrier and the housing of the gearbox 400 and between the spindle carrier and the support base 530 may be removable, such as by screws.

In this embodiment, the spindle bracket includes a first support frame 510 and a second support frame 520, and the first support frame 510 and the second support frame 520 are both used to connect with the box body of the gear box 400. The first support frame 510 and the second support frame 520 are arranged at intervals in the radial direction of the main shaft matching hole 531, and are respectively connected with two opposite sides of the support base 530 in the radial direction of the main shaft matching hole 531; that is, opposite sides of the support base 530 are respectively connected to the first support frame 510 and the second support frame 520; alternatively, opposite sides of the support base 530 are connected to the first support frame 510 and the second support frame 520 by screws, respectively. For convenience of illustration, in fig. 17 and 18, the axis extending direction of the spindle engagement hole 531 is defined as the z-axis direction, and the first support 510 and the second support 520 are spaced apart in the x-axis direction. By arranging the first support frame 510 and the second support frame 520 at intervals in the x-axis direction, a certain space is formed between the first support frame 510 and the second support frame 520 for the rotor head 700 to pass through.

In this embodiment, the first support frame 510 and the second support frame 520 are plate-shaped structures, and the first support frame 510 and/or the second support frame 520 are provided with weight-reducing holes, that is, at least one of the first support frame 510 and the second support frame 520 is provided with weight-reducing holes. The plate is adopted, so that the forming process is simpler, the weight of the main shaft bracket can be reduced by arranging the lightening holes, and the flying load of the unmanned helicopter can be reduced.

In the present embodiment, the support base 530 is disposed at one end of the spindle bracket in the z-axis direction, and the other end of the spindle bracket in the z-axis direction is used to connect with the housing of the gear case 400. This allows the support base 530 to be positioned as close as possible to one end of the propeller to the rotor head 700, thereby improving the support effect and better preventing the rotor head 700 from swinging radially.

Further, the spindle bracket in this embodiment further includes a bracket connecting member 540 disposed between the first bracket 510 and the second bracket 520, and opposite ends of the bracket connecting member 540 are respectively connected to the first bracket 510 and the second bracket 520. In this embodiment, the spindle bracket includes two supporting frame connectors 540 disposed at intervals, and the two supporting frame connectors 540 are disposed at two sides of the axis of the spindle mating hole 531; that is, the two support frame connectors 540 are spaced apart in the y-axis direction, and the axis of the spindle engagement hole 531 is located between the two support frame connectors 540. By providing the support frame connecting member 540, the first support frame 510 and the second support frame 520 can be prevented from being deformed in a direction approaching or separating from each other, so that the stability of the spindle support can be improved, and the supporting effect of the spindle supporting assembly 500 on the rotor spindle 700 can be improved.

Further, the spindle bracket further includes a swing arm mounting member 550, where the swing arm mounting member 550 is disposed between the first support frame 510 and the second support frame 520 and is connected to the first support frame 510 and the second support frame 520. The rocker arm mount 550 is provided with a rocker arm mounting hole 5531 (see fig. 24), and the rocker arm mounting hole 5531 is used for mounting the rocker arm 610 of the steering engine 600 and enabling the rocker arm 610 to rotate relative to the rocker arm mount 550. By providing the rocker arm mounting 550, the rocker arm 610 of the steering engine 600 can be positioned, and the structural strength of the main shaft bracket can be improved to some extent.

Further, the spindle supporting assembly 500 further includes a protective sleeve 560, one end of the protective sleeve 560 in the axial direction is connected to the supporting base 530, the protective sleeve 560 is coaxially disposed with the spindle mating hole 531 and axially communicates with the spindle mating hole 531, and the other end of the protective sleeve 560 is used for connecting to a housing of the gear housing 400. In this embodiment, protective sleeve 560 is used to cover the outside of rotor shaft 700 and protect rotor shaft 700. On the other hand, the support base 530 is connected to the casing of the gear case 400 through the protective sleeve 560, so that the stability of the support base 530 can be further improved, and the stability of the rotor head 700 can be further improved. Alternatively, both ends of the protective sleeve 560 may be detachably coupled with the supporting base 530 and the case of the gear case 400 by screws.

The following describes the respective components of the spindle support assembly 500 separately.

Fig. 19 is a schematic view of a first support frame 510 according to an embodiment of the present application. As shown in fig. 18 and 19, the first support 510 is a plate, and further, the first support 510 has a symmetrical structure. The upper end (end near the propeller) of the first support frame 510 is provided with four first assembly holes 511, the first assembly holes 511 are for connection with the support base 530 through screws, and the first assembly holes 511 may be through holes.

The first support frame 510 is provided with a first positioning groove 512, and the first positioning groove 512 is used for being matched with a first positioning boss 534 on the support base 530, so that the relative positions of the first support frame 510 and the support base 530 are conveniently pre-fixed during assembly, and then the first support frame 510 and the support base 530 are fixed by installing screws.

The lower end of the first supporting frame 510 forms a first notch 513 for avoiding the box body of the gear box 400. Two second assembly holes 514 are respectively arranged at two sides of the first notch 513 at the lower end of the first support frame 510, and the second assembly holes 514 are used for being connected with the box body of the gear box 400 through screws. The second fitting hole 514 may be a through hole.

Further, the first supporting frame 510 is further provided with four third assembling holes 515, the third assembling holes 515 are used for being connected with the supporting frame connecting piece 540 through screws, and the third assembling holes 515 can be through holes. In the present embodiment, four third assembly holes 515 are divided into two groups, each group of two third assembly holes 515, and the two groups of third assembly holes 515 are symmetrically disposed at the left and right sides of the first support frame 510. Each set of third mounting holes 515 is configured to receive a support bracket attachment 540.

Further, the first supporting frame 510 is further provided with two fourth assembling holes 516, and the two fourth assembling holes 516 are used for being connected with the rocker arm mounting member 550 through screws. The fourth fitting hole 516 may be a through hole. In this embodiment, two third positioning grooves 517 are disposed on the first support frame 510 and are configured to cooperate with the third positioning boss 5521 on the rocker arm mounting member 550, so as to pre-fix the relative positions of the first support frame 510 and the rocker arm mounting member 550 during assembly, and then fix the two by mounting screws. In this embodiment, the fourth assembling holes 516 are correspondingly formed in the third positioning slots 517.

The first supporting frame 510 is provided with two first lightening holes 518 for lightening the weight. Alternatively, the shapes of the two first lightening holes 518 may be the same or different, and the number of the first lightening holes 518 may be increased or decreased as needed.

Fig. 20 is a schematic view of a second support frame 520 according to an embodiment of the present application. As shown in fig. 18 and 20, the second supporting frame 520 is a plate, and further, the second supporting frame 520 has a symmetrical structure. The upper end of the second supporting frame 520 is provided with four fifth assembly holes 521 for connection with the supporting base 530 by screws, and the fifth assembly holes 521 may be through holes. The second supporting frame 520 is provided with a second positioning groove 522, and the second positioning groove 522 is used for being matched with a second positioning boss 535 on the supporting seat 530, so that the relative positions of the second supporting frame 520 and the supporting seat 530 are conveniently pre-fixed during assembly, and then the second supporting frame 520 and the supporting seat 530 are fixed by installing screws.

The lower end of the second supporting frame 520 forms a second notch 523 for avoiding the case of the gear case 400. The lower end of the second supporting frame 520 is provided with two sixth assembling holes 524 at both sides of the second gap 523, respectively, and the sixth assembling holes 524 are used for being connected with the box body of the gear box 400 through screws. The sixth fitting hole 524 may be a through hole.

Further, the second supporting frame 520 is further provided with four seventh assembling holes 525, the seventh assembling holes 525 are used for connecting with the supporting frame connecting member 540 by screws, and the seventh assembling holes 525 may be through holes. In the present embodiment, the four seventh mounting holes 525 are divided into two groups, each group of two seventh mounting holes 525, and the two groups of seventh mounting holes 525 are symmetrically disposed at the left and right sides of the second supporting frame 520. Each set of seventh mounting holes 525 is configured to couple to a support bracket coupling 540.

Further, two eighth assembly holes 526 are further provided on the second supporting frame 520, and the two eighth assembly holes 526 are used for being connected with the swing arm mounting piece 550 through screws. The eighth fitting hole 526 may be a through hole. In this embodiment, two fourth positioning grooves 527 are disposed on the second support frame 520 and are used for matching with the fourth positioning boss 5511 on the rocker arm mounting member 550, so as to conveniently pre-fix the relative positions of the second support frame 520 and the rocker arm mounting member 550 during assembly, and then fix the two by mounting screws. In this embodiment, the eighth assembling holes 526 are correspondingly formed in the fourth positioning grooves 527 one by one.

The second supporting frame 520 is provided with two second lightening holes 528 for lightening the weight. Alternatively, the shapes of the two second lightening holes 528 may be the same or different, and the number of the second lightening holes 528 may be increased or decreased as needed.

In addition, the second support frame 520 is further provided with a steering engine hole 529 and a steering engine mounting hole 5291, the steering engine hole 529 is used for local insertion of the steering engine 600, and the steering engine mounting hole 5291 is used for fixing the steering engine 600 to the second support frame 520. Specifically, the second support frame 520 is provided with two steering engine holes 529 for cooperating with the two steering engines 600, and the two steering engine holes 529 are arranged at intervals in a direction perpendicular to the axis of the main shaft cooperating hole 531 (y-axis direction in fig. 17). Steering engine mounting hole 5291 may be through hole 144. Optionally, the steering engine mounting hole 5291 is used to fix the steering engine 600 to the second support frame 520 by a screw. In this embodiment, two sets of steering engine mounting holes 5291 are provided on the second support frame 520, and each set of steering engine mounting holes 5291 includes four steering engine mounting holes 5291 for mounting a steering engine 600. Four steering engine mounting holes 5291 in the same set are disposed about corresponding steering engine holes 529.

Fig. 21 is a schematic view of a support base 530 in the embodiment of the present application at a first view angle; fig. 22 is a schematic view of the support base 530 in the embodiment of the present application under the second view angle. Referring to fig. 17 to 22, in the present embodiment, the support base 530 is generally rectangular, and the support base 530 is provided with a spindle engagement hole 531 penetrating the support base 530 for mating with the rotor shaft 700 in a plugging manner, and enabling the rotor shaft 700 to rotate relative to the support base 530. Optionally, bearings (not shown) are provided in main shaft mating hole 531, so that support base 530 is connected to main rotor shaft 700 through the bearings, thereby reducing frictional resistance when main rotor shaft 700 rotates.

The opposite sides (along the x-axis direction) of the support base 530 are respectively provided with a first screw hole 532 and a second screw hole 533, the first screw hole 532 is used for connecting the first support frame 510 by being matched with a screw, and the second screw hole 533 is used for connecting the second support frame 520 by being matched with the screw. In the present embodiment, the number of the first screw holes 532 and the second screw holes 533 is four, and the number and the arrangement positions of the first screw holes 532 and the second screw holes 533 correspond to the first fitting holes 511 on the first support frame 510 and the fifth fitting holes 521 on the second support frame 520, respectively.

The opposite sides (along the x-axis direction) of the support base 530 are further provided with a first positioning boss 534 and a second positioning boss 535, respectively, the first positioning boss 534 is used for being matched with the first positioning groove 512 on the first support frame 510, and the second positioning boss 535 is used for being matched with the second positioning groove 522 on the second support frame 520. Wherein, the first positioning boss 534 and the first screw hole 532 are located at the same side of the supporting seat 530, and the second positioning boss 535 and the second screw hole 533 are located at the same side of the supporting seat 530.

As shown in fig. 21, in the present embodiment, the support base 530 is provided with a lower flange 536 at one end in the axial direction of the spindle engagement hole 531, the lower flange 536 is disposed around the edge of the spindle engagement hole 531 to form a ring-shaped structure, and one end in the axial direction of the protection sleeve 560 is sleeved on the lower flange 536. Optionally, the protective sleeve 560 is secured to the lower flange 536 by screws. Specifically, a plurality of jacket mounting holes 537 (only one shown in fig. 21) are circumferentially disposed on the lower flange 536 for engagement with the screws.

In alternative embodiments, the first screw hole 532 and the second screw hole 533 may be replaced by a through hole penetrating the support base 530, and a screw may sequentially penetrate the first support frame 510, the support base 530 and the second support frame 520 and then cooperate with a nut to achieve connection and fixation of the first support frame 510, the second support frame 520 and the support base 530.

Fig. 23 is a schematic view of a support frame connector 540 according to an embodiment of the present application. As shown in fig. 23, the support frame connecting member 540 includes a connecting body 541 and two connecting protrusions 543 spaced apart from the connecting body 541, and the two connecting protrusions 543 are detachably connected to the first support frame 510 and the second support frame 520, respectively. The two connection bumps 543 and one connection body 541 form a Y-shaped structure together. Optionally, the two connection protrusions 543 are detachably connected with the first support 510 and the second support 520 through screws respectively; specifically, two third screw holes 544 are disposed on each connection bump 543, and the third screw holes 544 are used for connecting the first support frame 510 or the second support frame 520 by matching with screws.

In alternative other embodiments, the third screw hole 544 may be replaced by a through hole, and a screw may sequentially pass through the first support frame 510, the support frame connecting member 540 and the second support frame 520, and then cooperate with a nut to achieve connection and fixation of the first support frame 510, the second support frame 520 and the support frame connecting member 540.

Further, an external hole 542 is provided in the connection body 541, and the external hole 542 is used for connection with the fuselage frame 200 of the unmanned helicopter. In this embodiment, the number of the external holes 542 is two, and the external holes 542 may be screw holes or through holes.

FIG. 24 is a schematic view of a rocker arm mount 550 in one embodiment of the present application, at a first perspective; fig. 25 is a schematic view of a rocker arm mount 550 in an embodiment of the present application at a second perspective. In this embodiment, in combination with fig. 17 to 20 and fig. 24 and 25, two rocker arm mounting holes 5531 are provided on the rocker arm mounting member 550, and the two rocker arm mounting holes 5531 are used to mount the rocker arms 610 of the two steering engines 600 correspondingly. The rocker arm mounting piece 550 comprises two connecting arms 551 and a connecting part 552 connected with one end of the two connecting arms 551, the two connecting arms 551 and the connecting part 552 form a U-shaped piece together, the bottom end and the opening end of the U-shaped piece are respectively connected with the first supporting frame 510 and the second supporting frame 520, and the rotor main shaft 700 penetrates between the two connecting arms 551. The U-shaped piece is provided with mounting portions 553 protruding from both sides of the two connecting arms 551 in the direction of the interval (y-axis direction in fig. 17), and two rocker arm mounting holes 5531 are provided on the two mounting portions 553, respectively.

Specifically, the two mounting portions 553 are symmetrically arranged; a bearing may be disposed within the rocker arm mounting bore 5531 such that the rocker arm mount 550 is rotatably coupled to the rocker arm 610 via the bearing.

The two connecting arms 551 extend along the x-axis direction and are arranged at intervals in parallel in the y-axis direction, and one side of the connecting portion 552 away from the two connecting arms 551 (i.e. the bottom of the U-shaped piece) is provided with two fourth screw holes 5522 and two third positioning bosses 5521. The positions of the two fourth screw holes 5522 correspond to the positions of the two fourth assembly holes 516 on the first support frame 510, and are used for connecting the first support frame 510 through screws. The two fourth screw holes 5522 are respectively formed on the two third positioning bosses 5521. The two third positioning bosses 5521 correspond to the two third positioning slots 517 on the first support frame 510, and the third positioning bosses 5521 are configured to cooperate with the third positioning slots 517.

One end of the two connecting arms 551 away from the connecting portion 552 is provided with a fourth positioning boss 5511 and a fifth screw hole 5512 respectively, the fifth screw hole 5512 is arranged on the fourth positioning boss 5511, and the positions of the two fourth screw holes 5522 correspond to the two eighth assembly holes 526 on the second supporting frame 520 and are used for being connected with the second supporting frame 520 through screws. The two fourth positioning bosses 5511 correspond to the two fourth positioning slots 527 on the second support frame 520, and the fourth positioning bosses 5511 are configured to cooperate with the fourth positioning slots 527.

In alternative other embodiments, the fourth screw hole 5522 and the fifth screw hole 5512 may be replaced by a through hole penetrating the rocker arm mounting member 550, and a screw may sequentially penetrate the first support frame 510, the rocker arm mounting member 550 and the second support frame 520, and then cooperate with a nut to achieve connection and fixation of the first support frame 510, the second support frame 520 and the rocker arm mounting member 550.

Through setting up main shaft supporting component 500, supporting seat 530 passes through the box fixed connection of support and gear box 400 to can support rotor main shaft 700 between screw and the gear box 400 effectively, make even if rotor main shaft 700 length is longer, also can keep better stability under the supporting action of supporting seat 530 of main shaft supporting component 500. In this case, the rigidity requirement for the rotor main shaft 700 can be reduced to some extent.

The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An unmanned helicopter, comprising:

a fuselage frame;

an engine assembly mounted to the fuselage frame, the engine assembly comprising an engine and a plurality of shock absorbers disposed about the engine, the shock absorbers being directly or indirectly connected with the engine and the fuselage frame; at least two shock absorbers are respectively positioned at two sides of the gravity center of the engine in the front-rear direction of the unmanned helicopter; at least two shock absorbers are respectively positioned at two sides of the gravity center of the engine in the up-down direction of the unmanned helicopter; at least two shock absorbers are respectively positioned at two sides of the gravity center of the engine in the left-right direction of the unmanned helicopter;

a rotor assembly;

2. The unmanned helicopter of claim 1, wherein the engine assembly comprises an inner mounting bracket and an outer mounting bracket, the inner mounting bracket being connected to the engine, the outer mounting bracket being connected to the fuselage frame, the shock absorber being connected to the inner mounting bracket and the outer mounting bracket;

The inner mounting bracket comprises an upper inner bracket, the outer mounting bracket comprises an upper outer bracket, the upper inner bracket is connected with the engine, and the upper outer bracket is connected with the frame of the machine body; the upper end of the shock absorber located above the gravity center of the engine is connected with the upper inner bracket along the up-down direction of the unmanned helicopter, and the lower end of the shock absorber is connected with the upper outer bracket;

the upper inner bracket comprises a front connecting piece, a rear connecting piece and two cross beams, wherein the front connecting piece and the rear connecting piece are spaced in the front-rear direction of the unmanned helicopter, the two cross beams are spaced in the left-right direction of the unmanned helicopter and extend along the front-rear direction of the unmanned helicopter, the two ends of the cross beams are respectively connected with the front connecting piece and the rear connecting piece, the front connecting piece and the rear connecting piece are connected with the engine, the front connecting piece and the rear connecting piece are respectively connected with the shock absorber, and the shock absorber connected with the front connecting piece and the shock absorber connected with the rear connecting piece are respectively positioned at the two sides of the center of gravity of the engine in the front-rear direction of the unmanned helicopter;

the two shock absorbers connected with the front connecting piece are respectively connected to the two ends of the front connecting piece in the left-right direction of the unmanned helicopter, so that the two shock absorbers connected with the front connecting piece are respectively positioned on the two sides of the center of gravity of the engine in the left-right direction of the unmanned helicopter;

The two shock absorbers connected with the rear connecting piece are respectively connected to the two ends of the rear connecting piece in the left-right direction of the unmanned helicopter, so that the two shock absorbers connected with the rear connecting piece are respectively positioned on the two sides of the center of gravity of the engine in the left-right direction of the unmanned helicopter;

the outer mounting brackets comprise a plurality of upper outer brackets, and the number of the upper outer brackets is the same as that of the shock absorbers connected with the upper inner brackets and corresponds to the number of the shock absorbers one by one; the upper outer support comprises a U-shaped frame and an upper connecting structure, the U-shaped frame comprises a supporting bottom plate and side plates connected to two ends of the supporting bottom plate, the supporting bottom plate and the side plates enclose an accommodating space, the shock absorbers connected with the upper inner support are arranged in the accommodating spaces of the upper outer supports in a one-to-one correspondence manner and are connected with the supporting bottom plate, the upper connecting structure is connected with the two side plates, and the upper connecting structure is connected with the frame of the machine body;

the upper connecting structure is a hoop structure;

the inner mounting bracket comprises a lower inner bracket, the outer mounting bracket comprises a lower outer bracket, the lower inner bracket is connected with the engine, and the lower outer bracket is connected with the frame of the machine body; along the up-down direction of the unmanned helicopter, the upper end of the shock absorber below the gravity center of the engine is connected with the lower inner bracket, and the lower end of the shock absorber is connected with the lower outer bracket;

The inner mounting brackets comprise two lower inner brackets which are arranged at intervals in the front-rear direction of the unmanned helicopter; the outer mounting brackets comprise two lower outer brackets, the two lower outer brackets are arranged at intervals in the front-rear direction of the unmanned helicopter and correspond to the two lower inner brackets one by one, lower connecting structures are respectively arranged at two ends of the lower outer brackets in the left-right direction of the unmanned helicopter, and the lower connecting structures are connected with the frame of the helicopter;

the lower connecting structure is a hoop structure;

two shock absorbers are arranged between each lower inner support and the corresponding lower outer support, the two shock absorbers connected with the lower inner support are located at two ends of the lower inner support in the left-right direction of the unmanned helicopter, and the two shock absorbers connected with the lower inner support are located at two sides of the center of gravity of the engine in the left-right direction of the unmanned helicopter respectively.

3. The unmanned helicopter according to claim 2, wherein the engine includes a cylinder block and an engine bracket connected to a rear end of the cylinder block in a front-rear direction of the unmanned helicopter, the lower inner bracket forward in the front-rear direction of the unmanned helicopter being a front lower inner bracket, the lower inner bracket rearward in the front-rear direction of the unmanned helicopter being a rear lower inner bracket connected to the cylinder block, the rear lower inner bracket being connected to the engine bracket to be connected to the cylinder block through the engine bracket;

The front lower inner bracket comprises a front base extending along the left-right direction of the unmanned helicopter and two front lower connecting parts connected to the upper sides of the front base, wherein the lower sides of the two ends of the front base in the left-right direction of the unmanned helicopter are respectively connected with one shock absorber, and the two front lower connecting parts are arranged at intervals in the left-right direction of the unmanned helicopter and are connected with the cylinder body;

the rear lower inner bracket comprises a rear base extending along the left-right direction of the unmanned helicopter and a rear lower connecting part connected to the upper side of the rear base, wherein the lower sides of the two ends of the rear base in the left-right direction of the unmanned helicopter are respectively connected with one shock absorber, and the rear lower connecting part is connected with the engine bracket;

the outer mounting bracket includes a hoop structure for connecting to the fuselage frame.

4. The unmanned helicopter of claim 2, wherein the engine comprises a cylinder block and an engine bracket connected to a rear end of the cylinder block in a front-rear direction of the unmanned helicopter, the inner mounting bracket remote from one end of the engine bracket being connected to the cylinder block, the inner mounting bracket near one end of the engine bracket being connected to the engine bracket to be connected to the cylinder block through the engine bracket.

5. An unmanned helicopter according to any of claims 1-3 wherein the engine assembly comprises six of the shock absorbers, four of which are located on the underside of the centre of gravity of the engine and two of which are located on the upper side of the centre of gravity of the engine;

alternatively, the engine assembly includes eight of the shock absorbers, four of which are located on the lower side of the center of gravity of the engine, and four of which are located on the upper side of the center of gravity of the engine;

alternatively, the engine assembly includes twelve of the dampers, six of which are located on the lower side of the center of gravity of the engine, and six of which are located on the upper side of the center of gravity of the engine.

6. The unmanned helicopter of claim 1, wherein the transmission mechanism further comprises a fixing assembly, the fixing assembly comprises a fixing seat and connecting structures arranged at two opposite ends of the fixing seat, the two connecting structures are detachably connected with two beams of the fuselage frame, the fixing seat is provided with a shaft hole penetrating through the fixing seat, and the shaft hole is in plug-in fit with the transmission shaft and enables the transmission shaft to rotate relative to the fixing seat.

7. The unmanned helicopter of claim 6, wherein the stationary assembly further comprises a first bearing embedded within the shaft bore, the drive shaft being rotatably coupled to the stationary mount via the first bearing;

the connecting structure is a hoop structure;

the anchor ear structure comprises an upper semi-ring and a lower semi-ring, wherein the upper semi-ring and the fixing seat are integrally formed, and the lower semi-ring is detachably connected with the upper semi-ring;

the outer side of the upper semi-ring is provided with a reinforcing rib;

two bearing mounting grooves are formed in two ends of the shaft hole along the axial direction, the fixing assembly comprises two first bearings, and the two first bearings are respectively arranged in the two bearing mounting grooves;

a plurality of blocking screws are arranged on the fixing seat around the shaft hole, and the blocking screws are used for blocking the first bearing from falling off from the shaft hole;

the fixed seat is provided with a weight reduction groove.

8. The unmanned helicopter of claim 6, wherein the drive mechanism further comprises a pulley connected to and coaxially disposed with the drive shaft, the pulley for driving connection with the engine;

The unmanned helicopter comprises two rotor wing assemblies which are arranged at intervals in the front-rear direction of the unmanned helicopter, the transmission shaft comprises a front shaft, a middle shaft and a rear shaft which are sequentially connected along the axial direction, the belt wheel is connected with the middle shaft, and the front shaft and the rear shaft are respectively used for being in transmission connection with one rotor wing assembly;

the transmission mechanism comprises a plurality of fixing assemblies, and the front shaft, the middle shaft and the rear shaft are respectively and rotatably connected with at least one fixing assembly;

the middle shaft is rotationally connected with the two fixing assemblies, and the two fixing assemblies connected with the middle shaft are respectively positioned at two opposite sides of the belt wheel in the axial direction;

the front shaft, the middle shaft and the rear shaft are connected through a coupler;

the belt pulley comprises a belt pulley main body sleeved on the outer side of the transmission shaft and two end plates, the two end plates are respectively connected to two ends of the belt pulley main body in the axial direction, the outer peripheral side of the belt pulley main body is used for being sleeved with a transmission belt, the belt pulley is in transmission connection with the engine through the transmission belt, the end plates are connected with the transmission shaft through second bearings, and the belt pulley main body is connected with the transmission shaft through third bearings;

An inner shaft sleeve is arranged between the second bearing and the third bearing, and two ends of the inner shaft sleeve in the axial direction are respectively abutted against the second bearing and the third bearing.

9. The unmanned helicopter of claim 1 wherein the rotor assembly comprises a rotor mast and a propeller connected to one end of the rotor mast, the transmission further comprising a gearbox and a mast support assembly, the gearbox comprising a housing and a gear assembly disposed within the housing, the propeller being drivingly connected to the gear assembly by the rotor mast; the spindle support assembly includes:

the main shaft bracket is connected with the box body of the gear box;

10. The unmanned helicopter of claim 9, wherein the main shaft bracket comprises a first support frame and a second support frame, the first support frame and the second support frame are both used for being connected with a box body of the gear box, the first support frame and the second support frame are arranged at intervals in the radial direction of the main shaft matching hole and are respectively connected with two opposite sides of the support seat in the radial direction of the main shaft matching hole;

The main shaft support further comprises a support frame connecting piece arranged between the first support frame and the second support frame, and two opposite ends of the support frame connecting piece are respectively connected with the first support frame and the second support frame;

the main shaft bracket comprises two support frame connecting pieces which are arranged at intervals, and the two support frame connecting pieces are oppositely arranged at two sides of the axis of the main shaft matching hole;

the support frame connecting piece comprises a connecting main body and two connecting convex blocks which are arranged on the connecting main body at intervals, and the two connecting convex blocks are detachably connected with the first support frame and the second support frame respectively;

the connecting main body is provided with an external hole which is used for being connected with a frame of the unmanned helicopter;

the two opposite sides of the supporting seat are respectively provided with a first positioning boss and a second positioning boss, the first supporting frame is provided with a first positioning groove, the second supporting frame is provided with a second positioning groove, the first positioning boss is used for being matched with the first positioning groove, and the second positioning boss is used for being matched with the second positioning groove;

the unmanned helicopter comprises a steering engine, a steering engine hole and a steering engine mounting hole are formed in the second supporting frame, the steering engine hole is used for partial insertion of the steering engine, and the steering engine mounting hole is used for fixing the steering engine to the second supporting frame;

The main shaft support further comprises a rocker arm mounting piece, wherein the rocker arm mounting piece is arranged between the first support frame and the second support frame and is connected with the first support frame and the second support frame; the rocker arm mounting piece is provided with a rocker arm mounting hole, and the rocker arm mounting hole is used for mounting a rocker arm of the steering engine and enabling the rocker arm to rotate relative to the rocker arm mounting piece;

the second support frame is provided with two steering engine holes which are used for being matched with the two steering engines, the two steering engine holes are arranged at intervals in the direction perpendicular to the axis of the main shaft matching hole, and the rocker arm mounting piece is provided with two rocker arm mounting holes;

the rocker arm mounting piece comprises two connecting arms and a connecting part connected with one end of the two connecting arms, the two connecting arms and the connecting part form a U-shaped piece together, the bottom end and the opening end of the U-shaped piece are respectively connected with the first supporting frame and the second supporting frame, and the rotor main shaft penetrates between the two connecting arms;

the U-shaped piece is provided with mounting parts in a protruding mode on two sides of the connecting arms in the interval direction, and the two rocker arm mounting holes are formed in the two mounting parts respectively;

The first support frame and/or the second support frame are/is provided with a lightening hole;

the first support frame and/or the second support frame are of symmetrical structures;

the main shaft supporting assembly further comprises a protective sleeve, one end of the protective sleeve in the axial direction is connected to the supporting seat, the protective sleeve is coaxially arranged with the main shaft matching hole and is axially communicated with the main shaft matching hole, and the other end of the protective sleeve is connected with a box body of the gear box;

the support seat is provided with a lower flange at one axial end of the main shaft matching hole, the lower flange surrounds the edge of the main shaft matching hole to form a ring-shaped structure, and one axial end of the protective sleeve is sleeved on the lower flange.