A single-input coaxial composite aircraft

Abstract

The present invention provides a single-input coaxial composite aircraft, comprising a coaxial three-stage reduction mechanism, a power conversion mechanism, a folding screw mechanism, and a swinging screw mechanism; the coaxial three-stage reduction mechanism comprises a first reduction mechanism and a second reduction mechanism arranged coaxially, the first reduction mechanism being connected to the second reduction mechanism via a bearing structure, the first reduction mechanism being connected to the folding screw mechanism via a first connecting rod mechanism, and the second reduction mechanism being connected to the swinging screw mechanism via a second connecting rod mechanism; the power conversion mechanism comprises a first transmission assembly and a second transmission assembly, the first transmission assembly being connected to an engine, the first transmission assembly being connected to the second transmission assembly, the first transmission assembly being connected to the first reduction mechanism, and the second transmission assembly being connected to the second reduction mechanism. Through the present application, a single-input power can be freely switched between two flight states, and a longitudinal twin-rotor and a transverse tilt-rotor can be effectively combined.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a single-input coaxial composite aircraft. Background Art

[0002] Conventional tiltrotors have both rotors and wings, and the rotors also need to transition between vertical and horizontal positions. Therefore, they not only share the technical characteristics of fixed-wing aircraft and helicopters, but are also significantly more complex in terms of structure, aerodynamics, and control. Rotor tilting is a highly complex, unsteady aerodynamic process, making it difficult to develop accurate mathematical models and select appropriate prediction algorithms. Furthermore, aerodynamic interference in tiltrotors is highly complex, involving multiple aspects, including rotor-wing, rotor-rotor, rotor-fuselage, and rotor-tail. Rotor-wing aerodynamic interference is most severe during vertical flight and hovering, significantly impacting the tiltrotor's payload. Transitioning from helicopter mode to fixed-wing mode requires reaching a relatively high level flight speed, which typically requires a period of acceleration in helicopter mode. When transitioning back from fixed-wing mode to helicopter mode for landing in a small area, a significant period of deceleration is required before the tiltrotor can be performed. These specific structural design forms and flight control mechanisms have extremely strict requirements on the flight and landing environment, making it difficult to meet complex and changing application needs.

[0003] Currently, existing patent CN116374167 A discloses a high-speed tilt-rotor helicopter with trapezoidal rotors. By controlling the nacelle angle, the aircraft can be placed in either helicopter or fixed-wing mode. The helicopter can take off in helicopter mode, take off in fixed-wing mode, perform transition flight, perform high-speed fixed-wing flight, switch from fixed-wing mode to helicopter mode for landing, and perform fixed-wing mode landing. Transitioning from hover mode to cruise mode requires tilting the wings, which results in severe aerodynamic interference, significantly impacting the tilt-rotor's payload, requiring high pilot skill, and reducing the safety margin during flight.

[0004] Existing patent CN109110105 A discloses a wing retraction and folding device for a deformable aircraft, which can change the wing span and wing sweep angle of the deformable aircraft. However, it cannot achieve the function of taking off in a small space, and the wing retraction and folding has certain limitations. Summary of the Invention

[0005] Based on this, the purpose of the present invention is to provide a single-input coaxial compound aircraft to solve the deficiencies in the prior art.

[0006] To achieve the above-mentioned object, the present invention provides a single-input coaxial compound aircraft, comprising an aircraft fuselage, a coaxial three-stage reduction mechanism provided on the aircraft fuselage, a power conversion mechanism, a folding screw mechanism, and a swinging screw mechanism;

[0007] The coaxial three-stage reduction mechanism includes a first reduction mechanism and a second reduction mechanism arranged coaxially, the first reduction mechanism being connected to the second reduction mechanism via a bearing structure, the first reduction mechanism being connected to the folding screw mechanism via a first connecting rod mechanism, and the second reduction mechanism being connected to the swinging screw mechanism via a second connecting rod mechanism, the first reduction mechanism and the second reduction mechanism being used to perform three-stage reduction on the folding screw mechanism and the swinging screw mechanism, respectively;

[0008] The power conversion mechanism includes a first transmission assembly and a second transmission assembly, wherein the first transmission assembly is connected to an engine, and the first transmission assembly is connected to the second transmission assembly, the first transmission assembly is connected to the first reduction mechanism, and the second transmission assembly is connected to the second reduction mechanism; the first transmission assembly is used to transmit the power provided by the engine to the first reduction mechanism or the second reduction mechanism;

[0009] The folding propeller mechanism includes a first planetary reduction assembly, a folding assembly, and a first propeller. The plane formed by the rotation of the first propeller is parallel to the horizontal plane. The first propeller is connected to the first connecting rod mechanism via the first planetary reduction assembly. The folding assembly is connected to the first propeller. The folding assembly is used to drive the first propeller to fold in a direction close to the top of the aircraft fuselage. The first planetary reduction assembly is connected to a spare engine.

[0010] The swinging screw mechanism includes a second planetary reduction assembly, a swinging assembly and a second propeller. The plane formed by the rotation of the second propeller is perpendicular to the horizontal plane. The second propeller is connected to the second connecting rod mechanism through the second planetary reduction assembly. The swinging assembly is connected to the second propeller. The swinging assembly is used to drive the second propeller to swing in a direction close to the tail of the aircraft fuselage.

[0011] The beneficial effects of the present invention are as follows: by connecting the first transmission assembly to the engine, connecting the second transmission assembly to the first transmission assembly, connecting the first transmission assembly to the first reduction mechanism, connecting the second transmission assembly to the second reduction mechanism, and arranging the first reduction mechanism and the second reduction mechanism coaxially, the maneuverability of the aircraft is improved, the first reduction mechanism and the second reduction mechanism are connected by a bearing structure so that the first reduction mechanism and the second reduction mechanism do not interfere with each other, and then connected to the folding screw mechanism through the first connecting rod mechanism, and connected to the swinging screw mechanism through the second connecting rod mechanism, through the above structure, the aircraft can be operated with a single input power. The free switching between the two flight states is conducive to achieving vertical take-off and long-distance cruising flight in the air, avoiding the danger caused by the tilting of the aircraft rotor, and using the backup engine to ensure the hovering posture of the aircraft during power switching. The first propeller is folded and retracted by the folding component, so that the first propeller can be folded and retracted when the aircraft is cruising, which is conducive to reducing the wind resistance of the aircraft during cruising to increase the flight speed. At the same time, the second propeller can be swung by the swinging component so that the aircraft can make any turn, thereby improving the maneuverability of the aircraft and realizing the effective combination of the longitudinal twin rotors and the transverse tilt rotors.

[0012] Preferably, the first transmission assembly includes a first flywheel, a first transmission shaft and a first movable connecting piece, one end of the first transmission shaft is movably connected to the first flywheel through the first movable connecting piece, the other end of the first transmission shaft is connected to the first reduction mechanism through a first engaging shaft, the first flywheel is connected to the engine, and the first movable connecting piece is used to disconnect or connect the first transmission shaft from or to the first flywheel.

[0013] Preferably, the first movable connecting member includes a first driving cylinder, a first pressure plate connecting ring, a first pressure plate and a first friction member, the first driving cylinder is connected to the first transmission shaft through a first connecting structure, the piston rod of the first driving cylinder is connected to the first pressure plate through the first pressure plate connecting ring, the first pressure plate is connected to the first friction member, and the first friction member is movably connected to the first flywheel disc.

[0014] Preferably, the second transmission assembly includes a second flywheel, a second transmission shaft and a second movable connecting piece, one end of the second transmission shaft is connected to the second flywheel through the second movable connecting piece, and the other end of the second transmission shaft is connected to the second reduction mechanism through a second meshing shaft, the first flywheel and the first transmission shaft are both hollow structures, the second flywheel is built into the first flywheel, and the second transmission shaft is built into the first transmission shaft.

[0015] Preferably, the first friction member includes two first friction plates, a first reduction plate and a telescopic spring. The two friction plates are respectively glued to the opposite ends of the first reduction plate. A groove is provided on the first reduction plate. A cylindrical boss is respectively provided on the groove walls on both sides opposite to each other. The two ends of the telescopic spring are respectively connected to the two cylindrical bosses.

[0016] Preferably, the first reduction mechanism includes a primary reduction gear, a secondary reduction gear and a tertiary reduction gear, the primary reduction gear, the secondary reduction gear and the tertiary reduction gear are all clearance-matched with the first meshing shaft, the first reduction gear is synchronously transmitted with the first meshing shaft through a primary synchronization structure, and the second reduction gear and the third reduction gear are both synchronously transmitted with the first meshing shaft through a secondary synchronization structure.

[0017] Preferably, a first mating gear, a second mating gear and a third mating gear are provided on the first transmission shaft, and the first mating gear, the second mating gear and the third mating gear are respectively meshed with the first-stage reduction gear, the second-stage reduction gear and the third-stage reduction gear for transmission.

[0018] Preferably, the first connecting rod mechanism includes a first connecting rod member, a second connecting rod member and a third connecting rod member connected in sequence, the first connecting rod member is connected to the first meshing shaft through a first single-curved gear, the second connecting rod member is connected to the third connecting rod member through a first double-curved gear, and the third connecting rod member is connected to the first planetary reduction assembly through a second single-curved gear.

[0019] Preferably, the second connecting rod mechanism includes a fourth connecting rod, a fifth connecting rod and a sixth connecting rod connected in sequence, the fourth connecting rod is connected to the second meshing shaft through a third single-curved gear, the fifth connecting rod is connected to the sixth connecting rod through the first double-curved gear, and the sixth connecting rod is connected to the second planetary reduction assembly through a fourth single-curved gear.

[0020] Preferably, the sixth transmission rod is a hollow structure, one end of the third transmission rod is built into the sixth transmission rod, and the sixth transmission rod is connected to the third transmission rod through a second bearing structure, and the third transmission rod and the sixth transmission rod are respectively connected to the inner tooth surface and the outer tooth surface of the first hypoid gear.

[0021] Additional aspects and advantages of the present invention will be set forth in part in the description which follows and, in part, will be obvious from the description which follows, or may be learned by practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1A schematic diagram of the overall structure of a single-input coaxial compound aircraft provided in an embodiment of the present invention;

[0023] Figure 2 A schematic diagram of the coordination of a coaxial three-stage reduction mechanism and a power conversion mechanism provided in an embodiment of the present invention;

[0024] Figure 3 A schematic structural diagram of a first connecting rod mechanism and a second connecting rod mechanism provided in an embodiment of the present invention;

[0025] Figure 4 Schematic diagram of the structure of the coaxial three-stage reduction mechanism provided by the embodiment of the present invention

[0026] Figure 5 A schematic structural diagram of a power conversion mechanism provided by an embodiment of the present invention;

[0027] Figure 6 A schematic structural diagram of a foldable spiral mechanism provided in an embodiment of the present invention;

[0028] Figure 7 A schematic structural diagram of a two-stage reducer provided in an embodiment of the present invention;

[0029] Figure 8 A schematic structural diagram of a folding assembly and a first propeller provided in an embodiment of the present invention;

[0030] Figure 9 A schematic structural diagram of the swing assembly and the second propeller provided in an embodiment of the present invention;

[0031] Figure 10 A cross-sectional view of a swing assembly provided in an embodiment of the present invention.

[0032] Description of main component symbols:

[0033] 11. Cabin; 12. Wing; 13. Landing wheel; 21. First reduction gear; 211. First reduction gear; 212. Second reduction gear; 213. Third reduction gear; 22. Second reduction gear; 231. First friction synchronizer ring; 234. First shift cylinder; 235. Mounting plate; 236. First timing belt housing; 30. Power conversion mechanism; 311. First flywheel; 312. First transmission shaft; 312a. First mating gear; 312b. Second mating gear; 312c. Third mating gear; 313. First meshing shaft; 314. First drive cylinder; 317a. First friction plate; 317b. First reduction gear; 3 17c, telescopic spring; 321, second transmission shaft; 322, second meshing shaft; 324, second pressure plate connecting plate; 325, second pressure plate; 326a, second friction plate; 326b, second reduction plate; 327, second connecting ring bearing; 328, second driving cylinder; 411, first input shaft; 412, first-stage planetary reducer; 413, second-stage planetary reducer; 413a, first sun gear; 413b, first reduction planetary gear; 413c, second-stage planetary reducer housing; 413d, first deep groove ball bearing; 413e, second-stage planetary gear retainer; 413f, second-stage planetary reducer ring gear; 413g, second-stage planet carrier; 413i, second Deep groove ball bearing; 413j, planetary gear gasket; 420, folding cylinder; 421, fixed annular base; 422, first guide rod; 423, first displacement ring seat; 424, first mounting base; 425, first mounting block; 426, first fixed rod; 427, second displacement ring seat; 428, second mounting base; 429, second guide rod; 430, second fixed rod; 43, first propeller; 44, propeller input shaft; 51, second planetary reduction assembly; 521, fixed base; 522, swing motor; 523a, transmission crank; 523b, chuck connecting rod; 523c, chuck crank; 523d, first support rod; 524a, first A chuck; 524b, a second chuck; 524c, a friction ring; 524d, a chuck gasket; 525, a second crank member; 526, a second support rod; 527, a ball shaft; 53, a second propeller; 54, an oscillating propeller input shaft; 55, a propeller root adapter sleeve; 56, a propeller hub; 61, a first connecting rod; 62, a second connecting rod; 63, a third connecting rod; 64, a first single-curved gear; 65, a second single-curved gear; 66, a first hyperboloid gear; 67, a first mounting seat; 68, a fourth connecting rod; 69, a fifth connecting rod; 691, a sixth connecting rod; 692, a third single-curved gear; 693, a fourth single-curved gear; 80, an engine; 90, a spare engine.

[0034] The following specific embodiments will further illustrate the present invention in conjunction with the above-mentioned drawings. DETAILED DESCRIPTION

[0035] To facilitate understanding of the present invention, the present invention will be described more fully below with reference to the accompanying drawings. The drawings illustrate several embodiments of the present invention. However, the present invention may be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to provide a more thorough and comprehensive understanding of the present invention.

[0036] It should be noted that when an element is referred to as being "fixed to" another element, it may be directly on the other element or there may be an intermediate element. When an element is referred to as being "connected to" another element, it may be directly connected to the other element or there may be an intermediate element. The terms "vertical," "horizontal," "left," "right," and similar expressions used herein are for illustrative purposes only.

[0037] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which this invention pertains. The terms used in this specification of the present invention are for the purpose of describing specific embodiments only and are not intended to limit the present invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0038] See also Figures 1 to 10 , is a single-input coaxial compound aircraft in an embodiment of the present invention, including an aircraft fuselage, a coaxial three-stage reduction mechanism, a power conversion mechanism 30, a folding screw mechanism and a swinging screw mechanism.

[0039] The coaxial three-stage reduction mechanism, the power conversion mechanism 30, the folding screw mechanism, and the swinging screw mechanism are all arranged in the aircraft fuselage. The aircraft fuselage includes a cabin 11, wings 12, and landing wheels 13. The cabin 11 and the wings 12 are welded, and the cabin 11 and the landing wheels 13 are welded. The coaxial three-stage reduction mechanism is fixedly connected to the wings 12 by a bolt structure.

[0040] The coaxial three-stage reduction mechanism includes a coaxially arranged first reduction mechanism 21 and a second reduction mechanism 22. The first reduction mechanism 21 is connected to the second reduction mechanism 22 via a bearing structure. The first reduction mechanism 21 is connected to the folding screw mechanism via a first connecting rod 61 mechanism, and the second reduction mechanism 22 is connected to the swinging screw mechanism via a second connecting rod 62 mechanism. The first reduction mechanism 21 is used to perform three-stage reduction on the folding screw mechanism, and the second reduction mechanism 22 is used to perform three-stage reduction on the swinging screw mechanism.

[0041] The power conversion mechanism 30 includes a first transmission component and a second transmission component. The first transmission component is connected to the engine 80, and the first transmission component is connected to the second transmission component. The first transmission component is movably connected to the first reduction mechanism 21, and the second transmission component is connected to the second reduction mechanism 22. The first transmission component is used to transmit the power provided by the engine 80 to the first reduction mechanism 21 or the second reduction mechanism 22.

[0042] In this embodiment, the folding screw mechanism includes a first planetary reduction assembly, a folding assembly and a first propeller 43. The first propeller 43 is connected to the first connecting rod 61 mechanism through the first planetary reduction assembly, and the folding assembly is connected to the first propeller 43. The folding assembly is used to drive the first propeller 43 to fold in a direction close to the top of the aircraft fuselage. It should be noted that the plane formed by the rotation of the first propeller 43 is parallel to the horizontal plane. There are multiple first propellers 43, and the multiple first propellers 43 are distributed at equal angles along the circumference of the central axis of the first planetary reduction assembly.

[0043] In this embodiment, the swinging screw mechanism includes a second planetary reduction assembly 51, a swinging assembly and a second propeller 53. The second propeller 53 is connected to the second connecting rod 62 through the second planetary reduction assembly 51, and the swinging assembly is connected to the second propeller 53. The swinging assembly is used to drive the second propeller 53 to swing in the direction close to the tail of the aircraft fuselage. The parallel formed by the rotation of the second propeller 53 is perpendicular to the horizontal plane. There are multiple second propellers 53, and the multiple second propellers 53 are distributed at equal angles along the circumference of the central axis of the second planetary reduction assembly 51.

[0044] In this embodiment, the first transmission assembly includes a first flywheel disc 311, a first transmission shaft 312 and a first movable connecting member. One end of the first transmission shaft 312 is movably connected to the first flywheel disc 311 through the first movable connecting member, that is, the first transmission shaft 312 is connected to the first movable connecting member, the first movable connecting member is movably connected to the first flywheel disc 311, the other end of the first transmission shaft 312 is connected to the first reduction mechanism 21 through the first meshing shaft 313, the first flywheel disc 311 is connected to the engine 80 through the engine diaphragm coupling, and the first movable connecting member is used to The first transmission shaft 312 is disconnected from or connected to the first flywheel disc 311. It should be noted that when the first transmission shaft 312 is connected to the first flywheel disc 311 through the first movable connecting piece, the power provided by the engine 80 is transmitted to the first reduction mechanism 21 through the first transmission assembly, and then transmitted to the folding spiral mechanism. When the first transmission shaft 312 is disconnected from the first flywheel disc 311 through the first movable connecting piece, the power provided by the engine 80 is transmitted to the swinging spiral mechanism through the first transmission assembly, the second transmission assembly and the second reduction mechanism 22 in sequence.

[0045] In this embodiment, the first movable connecting member includes a first driving cylinder 314, a first pressing plate 316 connecting ring 315, a first pressing plate 316 and a first friction member. The first driving cylinder 314 is connected to the first transmission shaft 312 through a first connecting structure. The piston rod of the first driving cylinder 314 is connected to the first pressing plate 316 through the first pressing plate 316 connecting ring 315. The first pressing plate 316 is connected to the first friction member. The first friction member is movably connected to the first flywheel disc 311. It should be noted that the first friction member includes two A first friction plate 317a and a first reduction plate 317b are respectively glued to the opposite ends of the first reduction plate 317b. A first square groove is opened on the first reduction plate 317b. First cylindrical bosses are respectively provided on the groove walls on both sides of the opposite sides of the first square groove. A telescopic spring 317c is provided in the first square groove. The two ends of the telescopic spring 317c are respectively connected to the two first cylindrical bosses, and the two first cylindrical bosses are respectively inserted into the corresponding ends of the telescopic spring 317c.

[0046] In this embodiment, the end of the first friction member away from the engine 80 is connected to the first pressure plate 316 connecting plate, and the first friction member is connected to the first pressure plate 316 through the first pressure plate 316 connecting plate. Specifically, the first pressure plate 316 connecting plate is provided with an annular boss, and the annular boss is provided with a threaded line. The first pressure plate 316 is provided with an annular through hole, and the annular boss passes through the annular through hole and cooperates with a nut thread to fix the first pressure plate 316 to the first pressure plate 316 connecting plate.

[0047] In this embodiment, the first pressing plate 316 is connected to the first pressing plate 316 connecting ring 315 through a first connecting ring bearing. Specifically, a cylindrical hollow boss is provided at the end of the first pressing plate 316 away from the engine 80, and the first connecting ring bearing is interference fit with the cylindrical hollow boss, and the first pressing plate 316 connecting ring 315 is interference fit with the first connecting ring bearing. It should be noted that the first transmission shaft 312 is connected to the first flywheel disc 311 through the first extension shaft, the first pressure plate 316 connecting ring 315 is a hollow structure, the first extension shaft passes through the first pressure plate 316 connecting ring 315, the first friction member and the first pressure plate 316 connecting plate, the first extension shaft passes through the first pressure plate 316 connecting ring 315 with a clearance fit, and the first extension shaft is interference fit with the first friction member and the first pressure plate 316 connecting plate, a first connecting boss is provided on the outer side of the first extension shaft, an annular through hole is provided on the first connecting boss, a second connecting boss is provided on the outer side of the first transmission shaft 312, an annular through hole is provided on the second connecting boss, a bolt is passed through the annular through holes on the first connecting boss and the second connecting boss, and is threadedly connected with a nut to fix the first extension shaft to the first transmission shaft 312.

[0048] It should be noted that the two first friction plates 317 a , the first reduction plate 317 b , the connecting plate of the first pressing plate 316 , and the first pressing plate 316 in the first friction member are all clearance-fitted with the first flywheel disc 311 .

[0049] In this embodiment, the first connecting structure includes a first cylinder connecting ring and a first cylinder fixing block. The first cylinder connecting ring is a hollow structure. The first cylinder connecting ring and the first transmission shaft 312 are clearance-fitted. The interior of the first connecting ring is fixedly connected to the first transmission shaft 312 by a bolt structure. The first cylinder connecting ring is connected to the first cylinder fixing block. The bottom of the first driving cylinder 314 is connected to a first connecting base plate, and the first connecting base plate is connected to the first cylinder fixing block to realize the connection between the first driving cylinder 314 and the first transmission shaft 312. The piston rod of the first driving cylinder 314 is inserted into the interior of the first pressing plate 316 connecting ring 315 and is connected to the first pressing plate 316 connecting ring 315 by a bolt structure.

[0050] In this embodiment, a first pressing plate 316 shell is provided on the outer side of the first pressing plate 316, a first extension boss is provided on the outer side of the first flywheel disc 311, an annular blind hole is provided on the first extension boss, a second extension boss is provided on the outer side of the first pressing plate 316 shell, an annular through hole is provided on the second extension boss, a bolt passes through the annular through hole and is connected to the annular blind hole to fix the first pressing plate 316 shell to the first flywheel disc 311.

[0051] In this embodiment, the structure of the second transmission assembly is basically the same as that of the first transmission assembly. The second transmission assembly includes a second flywheel, a second transmission shaft 321 and a second movable connecting member. One end of the second transmission shaft 321 is connected to the second flywheel through the second movable connecting member, and the other end of the second transmission shaft 321 is connected to the second reduction mechanism 22 through the second meshing shaft 322. The second meshing shaft 322 is connected to the first meshing shaft 313 through a bearing structure. It should be noted that the first flywheel 311 and the second transmission shaft 321 are both hollow structures, the second flywheel and the second movable connecting member are both built into the second flywheel, and the second transmission shaft 321 is built into the first transmission shaft 312.

[0052] In this embodiment, the structure of the second movable connecting member is basically the same as that of the first movable connecting member. The second movable connecting member includes a second driving cylinder 328, a second pressing plate 325 connecting ring, a second pressing plate 325 and a second friction plate 326a. The second driving cylinder 328 is connected to the second transmission shaft 321 through a second connecting structure. The piston rod of the second driving cylinder 328 is connected to the second pressing plate 325 through a second pressing plate 325 connecting ring. The second pressing plate 325 is connected to the second friction member, and the second friction member is movably connected to the second flywheel disc. It should be noted that The second friction member includes two second friction plates 326a and a second reduction plate 326b. The two second friction plates 326a are glued to the opposite ends of the second reduction plate 326b respectively. A second square groove is opened on the second reduction plate 326b. Second cylindrical bosses are respectively provided on the opposite side groove walls of the second square groove. A telescopic spring 317c is provided in the second square groove. The two ends of the telescopic spring 317c are respectively connected to the two second cylindrical bosses, and the two second cylindrical bosses are respectively inserted into the corresponding ends of the telescopic spring 317c.

[0053] In this embodiment, the first connecting rod 61 mechanism includes a first connecting rod 61, a second connecting rod 62 and a third connecting rod 63 connected in sequence. The first connecting rod 61 is connected to the first meshing shaft 313 through a first single-curved gear 64, the second connecting rod 62 is connected to the third connecting rod 63 through a first double-curved gear 66, and the third connecting rod 63 is connected to the first planetary reduction assembly through a second single-curved gear 65.

[0054] Specifically, the end of the first meshing shaft 313 facing the engine 80 is a disc shaft, and the end of the first meshing shaft 313 facing the engine 80 is connected to the first single-curved gear 64. The first connecting rod 61 includes a first connecting rod 61, a first mounting seat 67, a first transmission gear and a second transmission gear. The first connecting rod 61 is perpendicular to the second connecting rod 62, and the second connecting rod 62 is parallel to the first transmission shaft 312. The first transmission gear and the second transmission gear are respectively connected to the opposite end portions of the first connecting rod 61. The middle part of the first connecting rod 61 is connected to the aircraft fuselage through the first mounting seat 67, wherein the first connecting rod 61 is connected to the first mounting seat 67 through a first bearing, and the first connecting rod 61 is fixedly connected to the inside of the first bearing. A mounting seat 67 has an interference fit with the outside of the first bearing, the first transmission gear is meshed with the first single-curved gear 64 for transmission, the second connecting rod 62 includes a second connecting rod 62, a second mounting seat, a third transmission gear and a fourth transmission gear, the third transmission gear and the fourth transmission gear are respectively connected to the opposite end portions of the second connecting rod 62, the middle part of the second connecting rod 62 is connected to the aircraft fuselage through the second mounting seat, wherein the second connecting rod 62 is connected to the second mounting seat through the second bearing, the second connecting rod 62 is fixedly connected to the inside of the second bearing, the second mounting seat has an interference fit with the outside of the second bearing, the third transmission gear is meshed with the second transmission gear for transmission, and the fourth transmission gear is meshed with the inner tooth surface of the first hypoid gear 66 for transmission.

[0055] In addition, the third connecting rod 63 includes a third connecting rod 63, a third mounting seat and a fifth transmission gear. The third connecting rod 63 is perpendicular to the second connecting rod 62. The middle part of the third connecting rod 63 is connected to the aircraft fuselage through the third mounting seat, wherein the third connecting rod 63 is connected to the third mounting seat through a third bearing, the third connecting rod 63 is fixedly connected to the inside of the third bearing, and the third mounting seat is interference fit with the outside of the third bearing. One end of the third connecting rod 63 is connected to the center of the inner tooth surface of the first hypoid gear 66, and the other end of the third connecting rod 63 is connected to the fifth transmission gear. The fifth transmission gear is meshed with the second single-curved gear 65 for transmission, and the center of the second single-curved gear 65 is connected to the center of the first planetary reduction assembly. It should be noted that the inner tooth surface of the first hypoid gear 66 and its outer tooth surface can rotate with each other, and do not interfere with each other during movement.

[0056] In this embodiment, the second connecting rod 62 mechanism includes a fourth connecting rod 68, a fifth connecting rod 69 and a sixth connecting rod 691 connected in sequence. The fourth connecting rod 68 is connected to the second meshing shaft 322 through the third single-curved gear 692, the fifth connecting rod 69 is connected to the sixth connecting rod 691 through the outer tooth surface of the first double-curved gear 66, and the sixth connecting rod 691 is connected to the second planetary reduction assembly 51 through the fourth single-curved gear 693.

[0057] Specifically, the fourth connecting rod 68 includes a fourth connecting rod 68, a fourth mounting seat, a sixth transmission gear and a seventh transmission gear. The fourth connecting rod 68 is parallel to the first connecting rod 61 and is connected to the aircraft fuselage through the fourth mounting seat. The fourth connecting rod 68 is connected to the fourth mounting seat through a fourth bearing. The fourth connecting rod 68 is fixedly connected to the inside of the fourth bearing, and the fourth mounting seat is interference fit with the outside of the fourth bearing. The sixth transmission gear and the seventh transmission gear are respectively connected to the opposite end portions of the fourth connecting rod 68. The sixth transmission gear is meshed with the third single-curved gear 692 for transmission. The fifth connecting rod 69 includes the fifth connecting rod 69, the fourth mounting seat, the sixth transmission gear and the seventh transmission gear. The fifth mounting seat, the eighth transmission gear and the ninth transmission gear, the fifth connecting rod 69 are perpendicular to the fourth connecting rod 68, the fifth connecting rod 69 is parallel to the second connecting rod 62, and the fifth connecting rod 69 is connected to the aircraft fuselage through the fifth mounting seat, wherein the fifth connecting rod 69 is connected to the fifth mounting seat through the fifth bearing, the fifth connecting rod 69 is fixedly connected to the inside of the fifth bearing, the fifth mounting seat is interference fit with the outside of the fifth bearing, the eighth transmission gear and the ninth transmission gear are respectively connected to the opposite end portions of the fifth connecting rod 69, the eighth transmission gear is meshed with the sixth transmission gear for transmission, and the ninth transmission gear is meshed with the outer tooth surface of the first hypoid gear 66 for transmission.

[0058] In addition, the sixth connecting rod 691 includes a sixth connecting rod 691, a sixth mounting seat and a tenth transmission gear. The sixth connecting rod 691 is perpendicular to the fifth connecting rod 69. The middle part of the sixth connecting rod 691 is connected to the aircraft fuselage through the sixth mounting seat, wherein the sixth connecting rod 691 is connected to the sixth mounting seat through the sixth bearing, the sixth connecting rod 691 is fixedly connected to the inside of the sixth bearing, the sixth mounting seat is interference fit with the outside of the sixth bearing, one end of the sixth connecting rod 691 is connected to the center of the outer tooth surface of the first hypoid gear 66, and the other end of the sixth connecting rod 691 is meshed with the tenth transmission gear for transmission, and the center of the tenth transmission gear is connected to the center of the second planetary reduction assembly 51.

[0059] It should be noted that the sixth connecting rod 691 is a hollow structure, one end of the third connecting rod 63 is built into the sixth connecting rod 691, and the sixth connecting rod 691 is connected to the third connecting rod 63 through a bearing structure to ensure that the sixth connecting rod 691 and the third connecting rod 63 do not interfere with each other when they rotate relative to each other.

[0060] In this embodiment, the first reduction mechanism 21 includes a first-stage reduction gear 211, a second-stage reduction gear 212 and a third-stage reduction gear 213. Three first mating gears 312a are provided on the first transmission shaft 312, and from the end close to the engine 80 to the end away from the engine 80, they are the first mating gear 312a, the second mating gear 312b and the third mating gear 312c, respectively. The first-stage reduction gear 211 is meshed with the first mating gear 312a, the second-stage reduction gear 212 is meshed with the second mating gear 312b, and the third-stage reduction gear 213 is meshed with the third mating gear 312c. The first-stage reduction gear 211, the second-stage reduction gear 212 and the third-stage reduction gear 213 are all clearance-fitted with the first meshing shaft 313.

[0061] In this embodiment, the first reduction gear is synchronously transmitted with the first meshing shaft 313 through a primary synchronization structure. Specifically, the primary synchronization structure includes a primary gear friction synchronization ring, a primary synchronizer, a primary synchronization belt and a primary shift cylinder 234. The primary reduction gear 211 is fixedly connected to the primary gear friction synchronization ring. The primary gear friction synchronization ring is clearance-matched with the first meshing shaft 313. The primary synchronization belt is sleeved on the primary gear friction synchronization ring. The primary synchronization belt is transmission-matched with the primary gear friction synchronization ring. The length of the primary synchronization belt is greater than the length of the primary gear friction synchronization ring. The first meshing shaft 313 is welded to the primary synchronizer. A rectangular boss is provided on the primary synchronizer, and a rectangular groove is provided on the primary synchronization belt. The primary synchronizer is clearance-matched with the primary synchronization belt, and the rectangular groove is matched with the rectangular boss, so that the primary synchronizer is connected to the primary synchronization belt. The outer side of the primary synchronization belt is sleeved with a primary synchronization belt housing. The primary timing belt is rotatably connected to the primary timing belt housing. The primary timing belt housing is connected to the piston rod of the primary shift cylinder 234, which is connected to the aircraft fuselage via a mounting plate 235. It should be noted that due to the clearance fit between the primary reduction gear 211 and the first meshing shaft 313, when the first transmission shaft 312 rotates, the primary reduction gear 211 idles and cannot achieve deceleration. To achieve primary deceleration, the primary shift cylinder 234 pushes the primary timing belt through the primary timing belt housing. The primary timing belt moves toward the primary synchronizer, causing the rectangular boss on the primary synchronizer to fit into the rectangular groove on the primary timing belt. The primary reduction gear 211 then drives the primary gear friction synchronizer ring to rotate, which in turn drives the primary timing belt, which in turn drives the primary synchronizer and the first meshing shaft 313 to rotate, achieving deceleration. When the primary shift cylinder 234 pushes the primary timing belt back to a neutral position, the primary reduction gear 211 begins to idle again.

[0062] In this embodiment, the second reduction gear and the third reduction gear are both synchronously transmitted with the first meshing shaft 313 through a secondary synchronous structure. Specifically, the secondary synchronous structure is arranged between the second reduction gear and the third reduction gear. The secondary synchronous structure includes a secondary gear friction synchronizer ring, a secondary synchronizer, a secondary synchronous belt and a secondary shift cylinder. The secondary synchronizer is welded to the first meshing shaft 313. A rectangular boss is provided on the secondary synchronizer. There is a clearance fit between the secondary synchronizer and the secondary synchronous belt. A rectangular groove is provided on the outer side of the secondary synchronous belt. The secondary synchronous belt is sleeved on the secondary gear friction synchronizer ring. The length of the secondary synchronous belt is greater than that of the secondary gear friction synchronizer ring. The secondary gear friction synchronizer ring is clearance fit with the first meshing shaft 313. The secondary gear friction synchronizer ring is fixedly connected to the secondary reduction gear 212. A secondary synchronous belt housing is sleeved on the secondary synchronous belt. The secondary synchronous belt housing is rotatably connected to the secondary synchronous belt. The secondary synchronous belt housing is connected to the piston rod of the secondary shift cylinder. The secondary shift cylinder is connected to the aircraft fuselage through the mounting plate 235.

[0063] The secondary synchronization structure also includes a third-stage gear friction synchronization ring, which is connected to the third-stage reduction gear 213 and has a clearance fit with the first meshing shaft 313. The length of the secondary synchronization belt is greater than that of the third-stage gear friction synchronization ring.

[0064] It should be noted that when the secondary shift cylinder pushes the secondary synchronous belt through the secondary synchronous belt housing, the secondary synchronous belt cooperates with the secondary synchronous belt and the secondary synchronizer and the secondary reduction gear 212 to achieve the purpose of secondary deceleration. When the secondary shift cylinder pushes the secondary synchronous belt, the secondary synchronous belt cooperates with the secondary synchronizer and the tertiary reduction gear 213 at the same time to achieve the purpose of tertiary deceleration. When the secondary shift cylinder pushes the secondary synchronous belt to cooperate with different gears, different reduction ratios are achieved. When the secondary shift cylinder pushes the secondary synchronous belt back to the neutral position, the secondary reduction gear 212 and the tertiary reduction gear 213 start to idle again.

[0065] In this embodiment, the first planetary reduction assembly includes a first input shaft 411, a secondary planetary reducer 413 and a primary planetary reducer 412. One end of the first input shaft 411 is connected to the second single-curved gear 65, and the other end of the first input shaft 411 is connected to the center of the secondary planetary reducer 413. The secondary planetary reducer 413 is connected to the primary planetary reducer 412 through a coupling. The primary planetary reducer 412 is connected to the first propeller 43 through a coupling. The first propeller 43 is connected to the coupling through the propeller input shaft 44. The primary planetary reducer 412 and the secondary planetary reducer 413 are both used to reduce the speed of the first propeller 43.

[0066] Specifically, the two-stage planetary reducer 413 includes a first sun gear 413a, three first reduction planetary gears 413b and a two-stage planetary reducer housing. The middle part of the first input shaft 411 is fixedly connected to the center of the first sun gear 413a. The first sun gear 413a is sleeved on the first input shaft 411. The first input shaft 411 is sleeved with a first deep groove ball shaft 527 bearing 413d. The first sun gear 413a is located between the first deep groove ball shaft 527 bearing 413d and the second single-curved gear 65. The first input shaft 411 and the first deep groove ball shaft 527 bearing 413d have an internal interference fit. The outer side of the first deep groove ball shaft 527 bearing 413d is sleeved with a two-stage planetary gear retainer 413e. The wheel holder 413e is interference fit with the outer side of the first deep groove ball shaft 527 bearing 413d. The secondary planetary gear holder 413e is a hollow structure. The first sun gear 413a and the three first reduction planetary gears 413b are all located inside the secondary planetary gear holder 413e. The first sun gear 413a is located at the center of the secondary planetary gear holder 413e. The three first reduction planetary gears 413b are distributed at equal angles along the circumference of the first input shaft 411 and are arranged around the sun gear. The secondary planetary reducer 413 is fixedly connected to the ring gear of the secondary planetary reducer 413 in the outer casing. Each first reduction planetary gear 413b is meshed with the first sun gear 413a for transmission, and is also meshed with the ring gear of the secondary planetary reducer 413 for transmission.

[0067] It should be noted that a rectangular boss is provided on the first input shaft 411, and a rectangular groove is provided inside the first sun gear 413a. The rectangular boss and the rectangular groove are interference fit so that the first input shaft 411 is fixedly connected to the first sun gear 413a. An annular boss is provided on the outer casing of the secondary planetary reducer 413. The annular boss of the outer casing of the secondary planetary reducer 413 is fixedly connected to the aircraft fuselage by a bolt structure. A rectangular groove is provided inside the outer casing of the secondary planetary reducer 413. A rectangular boss is provided on the ring gear of the secondary planetary reducer 413. The rectangular boss on the ring gear of the secondary planetary reducer 413 is embedded in the rectangular groove of the outer casing of the secondary planetary reducer 413. The ring gear of the secondary planetary reducer 413 is fixed to the inner casing of the secondary planetary reducer 413 by a bolt structure. The first input shaft 411, the first sun gear 413a, and the ring gear of the secondary planetary reducer 413 are arranged on a common central axis.

[0068] In this embodiment, the secondary planetary reducer 413 also includes a secondary planetary carrier 413g, which is interference fit with the secondary planetary gear retainer 413e. The secondary planetary carrier 413g is rotatably connected to the end of the first input shaft 411 away from the second single-curved gear 65. A receiving shaft is provided on the secondary planetary carrier 413g, and a second deep groove ball shaft 527 bearing 413i is sleeved on the middle part of the receiving shaft. The receiving shaft is fixedly connected to the inside of the second deep groove ball shaft 527 bearing 413i, and the end of the receiving shaft away from the secondary planetary carrier 413g is connected to the second input shaft of the primary planetary reducer 412 through a coupling to transmit the power processed by the secondary planetary reducer 413 to the primary planetary reducer 412.

[0069] However, it should be noted that the upper end shell of the secondary reducer housing is connected to the lower end shell thereof by a bolt structure, and the upper end shell of the secondary reducer housing is interference fit with the outer side of the second deep groove ball shaft 527 bearing 413i, and the lower end shell of the secondary reducer housing is sleeved on the first input shaft 411 and is rotatably connected to the first input shaft 411. In order to protect the first reduction planetary gear 413b, a planetary gear gasket 413j is provided between the first reduction planetary gear 413b and the secondary planetary gear retainer 413e, and the planetary gear gasket 413j is clearance-matched with the corresponding inner wall of the secondary planetary gear retainer 413e.

[0070] It should be noted that the structure of the first-stage planetary reducer 412 is consistent with that of the second-stage planetary reducer 413, so they will not be described in detail. Both of them input power through the sun gear, and then achieve deceleration through the engagement between the sun gear and the deceleration planetary gear. Then, the decelerated power is output to the first propeller 43 through the first-stage planetary carrier in the first-stage planetary reducer 412 to achieve the purpose of decelerating the first propeller 43.

[0071] In this embodiment, the first stage reduction calculation is as follows: the mating gear on the first transmission shaft 312 is used as input, the reduction gear on the first meshing shaft 313 is used as output, the first stage reduction gear 211 on the first meshing shaft 313 is meshed with the first mating gear 312a on the first transmission shaft 312, and the reduction ratio between the two is i 11 The secondary reduction gear 212 on the first meshing shaft 313 is meshed with the second matching gear 312b on the first transmission shaft 312, and the reduction ratio between the two is i 12 The third-stage reduction gear 213 on the first meshing shaft 313 is meshed with the third matching gear 312c on the first transmission shaft 312, and the reduction ratio between the two is i 13 .

[0072] Second stage reduction calculation: the first single curved gear 64 is used as input, the first transmission gear is used as output, the first single curved gear 64 and the first transmission gear are meshed, and the cone angle is α1 * The reduction ratio is i14 ;

[0073] The second transmission gear is used as input, and the third transmission gear is used as output. The second transmission gear and the third transmission gear are meshed, and the cone angle is α2 * , the reduction ratio is i 15 ;

[0074] The fourth transmission gear is used as input, and the inner tooth surface of the first hypoid gear 66 is used as output. The fourth transmission gear and the inner tooth surface of the first hypoid gear are meshed, and the cone angle is α3 * , the reduction ratio is i 16 ;

[0075] The fifth transmission gear is used as input, and the second single-curved gear 65 is used as output. The fifth transmission gear and the second single-curved gear 65 are meshed with each other, and the cone angle is α4 * , the reduction ratio is i 17 ;

[0076] Calculation of the third stage reduction: The ring gear 413f of the secondary planetary reducer is fixed, the first sun gear 413a is used as input, and the three first reduction planetary gears 413b drive the secondary planet carrier 413g as output. The reduction ratio is i 18 ;

[0077] The ring gear of the first-stage planetary reducer in the first-stage planetary reducer is fixed, the second sun gear in the first-stage planetary reducer is used as input, and the three first-stage reducer planetary gears in the first-stage planetary reducer drive the first-stage planet carrier in the first-stage planetary reducer as output. The reduction ratio is i 19 .

[0078] There are three final deceleration ratios when the aircraft is hovering: 总 choose:

[0079] i 总 =i 11 +i 14 +i 15 +i 16 +i 17 +i 18 +i 19

[0080] i 总 =i 12 +i 14 +i 15 +i 16 +i 17 +i 18 +i 19

[0081] i 总 =i 13 +i 14 +i15 +i 16 +i 17 +i 18 +i 19

[0082] In this embodiment, the first stage reduction calculation is: the matching gear on the second transmission shaft 321 is used as the input, the reduction gear on the second meshing shaft 322 is used as the output, the first stage reduction gear 211 on the second meshing shaft 322 is meshed with the first matching gear 312a on the second transmission shaft 321, and the reduction ratio between the two is i 21 The secondary reduction gear 212 on the second meshing shaft 322 is meshed with the second matching gear 312b on the second transmission shaft 321, and the reduction ratio between the two is i 22 The third-stage reduction gear 213 on the second meshing shaft 322 is meshed with the third matching gear 312c on the second transmission shaft 321, and the reduction ratio between the two is i 23 .

[0083] Second stage reduction calculation: the third single-curved gear 692 is used as input, the sixth transmission gear is used as output, the third single-curved gear 692 and the sixth transmission gear are meshed, and the cone angle is α5 * , the reduction ratio is i 24 ;

[0084] The seventh transmission gear is used as input, the eighth transmission gear is used as output, the seventh transmission gear and the eighth transmission gear are meshed, and the cone angle is α6 * , the reduction ratio is i 25 ;

[0085] The ninth transmission gear is used as input, and the outer tooth surface of the first hypoid gear 66 is used as output. The ninth transmission gear and the outer tooth surface of the first hypoid gear 66 are meshed with each other, and the cone angle is α7 * , the reduction ratio is i 26 ;

[0086] The tenth transmission gear is used as input, and the fourth single-curved gear 693 is used as output. The tenth transmission gear and the fourth single-curved gear 693 are meshed with each other, and the cone angle is Δ8 * , the reduction ratio is i 27 ;

[0087] Calculation of the third stage reduction: The ring gear 413f of the secondary planetary reducer is fixed, the first sun gear 413a is used as input, and the three first reduction planetary gears 413b drive the secondary planet carrier 413g as output. The reduction ratio is i 18 ;

[0088] The ring gear of the first-stage planetary reducer in the first-stage planetary reducer is fixed, the second sun gear in the first-stage planetary reducer is used as input, and the three first-stage reducer planetary gears in the first-stage planetary reducer drive the first-stage planet carrier in the first-stage planetary reducer as output. The reduction ratio is i 19 .

[0089] There are three final reduction ratios i when the aircraft is cruising 总 choose:

[0090] i 总 =i 21 +i 24 +i 25 +i 26 +i 27 +i 18 +i 19

[0091] i 总 =i 22 +i 24 +i 25 +i 26 +i 27 +i 18 +i 19

[0092] i 总 =i 23 +i 24 +i 25 +i 26 +i 27 +i 18 +i 19

[0093] In this embodiment, the folding assembly includes a fixed annular base 421, a first guide rod 422, a first displacement ring seat 423, a first mounting base 424 and a folding cylinder 420. The fixed annular base 421, the first displacement ring seat 423 and the first mounting base 424 are sequentially sleeved on the propeller input shaft 44 from bottom to top. The fixed annular base 421 is welded to the propeller input shaft 44. The first mounting base 424 is connected to the fixed annular base 421 through the first guide rod 422, that is, one end of the first guide rod 422 is connected to the first mounting base 424, and the other end thereof is connected to the fixed annular base 421. The first guide rod 422 is parallel to the propeller input shaft 44. The first displacement ring seat 423 is fixedly connected to the fixed annular base 421 through the first fixing rod 426. The first propeller 43 is hinged to the first mounting base 424 through the first mounting block 425, that is, the first mounting block 425 is fixedly connected to the first propeller 43 through a bolt structure. The block 425 is hinged to the first mounting base 424, and a cylinder fixing ring seat is provided between the first displacement ring seat 423 and the fixed annular base 421. The cylinder fixing ring seat is sleeved on the propeller input shaft 44, and the cylinder fixing ring seat is welded to the propeller input shaft 44. A through groove is provided on the cylinder fixing ring seat for the first guide rod 422 to pass through the through groove and extend to be connected to the bottom of the first displacement ring seat 423. The folding cylinder 420 is fixedly mounted on the cylinder fixing ring seat, and the piston rod of the folding cylinder 420 is connected to the bottom of the first displacement ring seat 423. The first displacement ring seat 423 is connected to the first mounting block 425 through a first connecting rod, that is, one end of the first connecting rod is hinged to the top of the first displacement ring seat 423, and the other end is hinged to the first mounting block 425 through a first rotating shaft. A first displacement groove is provided on the first mounting block 425, and a first through groove is provided at the end of the first connecting rod. The first rotating shaft passes through the first through groove and is movably connected to the groove wall of the first displacement groove.

[0094] In this embodiment, the folding assembly also includes a second guide rod 429, a second displacement ring seat 427 and a second mounting base 428, one end of the second guide rod 429 is connected to the top of the first mounting base, and the other end thereof is connected to the bottom of the second displacement ring seat 427, the first displacement ring seat 423 is fixedly connected to the second displacement ring seat 427 through a second fixing rod 430, the second guide rod 429 is parallel to the first guide rod 422, the second mounting base 428 is hinged to the first propeller 43 through a second mounting block, that is, the second mounting base 428 is hinged to the second mounting block, the second mounting block is connected to the first propeller 43, the second mounting block is connected to the second displacement ring seat 427 through a second connecting rod, that is, one end of the second connecting rod is hinged to the top of the second displacement ring seat 427, and the other end thereof is hinged to the bottom of the second mounting block through a second rotating shaft, a second displacement groove is provided on the second mounting block, a second through-groove is provided at the end of the second connecting rod, the second rotating shaft passes through the second through-groove and is movably connected to the groove wall of the second displacement groove.

[0095] It should be noted that the multiple first propellers 43 are divided into two groups, each group of first propellers 43 includes three first propellers 43, one group of first propellers 43 is installed on the first mounting base 424, and the other group of first propellers 43 is installed on the second mounting base 428, wherein the second mounting base 428 is higher than the first mounting base 424.

[0096] In this embodiment, the structure of the second planetary reduction assembly 51 is substantially the same as that of the first planetary reduction assembly, and therefore will not be described in detail herein.

[0097] In this embodiment, the center of the second planetary reduction assembly 51 is connected to a swinging propeller input shaft 5444 through a coupling, the second propeller 53 is connected to the swinging propeller input shaft 5444 through a hub 56, and the second propeller 53 is connected to the hub 56 through a propeller root adapter sleeve 55. Specifically, the second propeller 53 is connected to the propeller root adapter sleeve 55, and the propeller root adapter sleeve 55 is movably connected to the hub 56 through a universal structure.

[0098] In this embodiment, the swing assembly includes a fixed base 521, a swing motor 522, a first crank member, a movable chuck and a second crank member 525. The swing propeller input shaft 5444 is connected to the fixed base 521 through a base bearing, that is, the swing propeller input shaft 5444 passes through the inside of the base bearing and has an interference fit with the base bearing. The fixed base 521 has an interference fit with the outside of the base bearing. The swing motor 522 is installed on the fixed base 521. A ball shaft 527 is sleeved on the swing propeller input shaft 5444. The movable chuck The movable chuck is connected to the ball shaft 527 through a movable bearing so that the movable chuck can rotate relative to the surface of the ball shaft 527. The movable chuck is connected to the drive shaft of the telescopic motor through a first crank member. The movable chuck is connected to the propeller root adapter sleeve 55 through a second crank member 525. When the drive shaft of the swing motor 522 rotates, the movable chuck is driven to rotate relative to the surface of the ball shaft 527 through the first crank member, so that the corresponding second propeller 53 can be tilted by the second crank member 525, thereby realizing the steering function of the aircraft in the air.

[0099] In this embodiment, the first crank member includes a transmission crank 523a, a chuck connecting rod 523b, and a chuck crank 523c. One end of the transmission crank 523a is fixedly connected to the drive shaft of the telescopic motor. The other end of the transmission crank 523a is connected to one end of the chuck connecting rod 523b via a universal ball joint. The other end of the chuck connecting rod 523b is connected to one end of the chuck crank 523c. The other end of the chuck crank 523c is interference fit with the movable chuck via a support shaft. It should be noted that the first crank member also includes a first support rod 523d. One end of the first support rod 523d ​​is hinged to the fixed base 521, and the other end is connected to the movable chuck via a universal ball joint.

[0100] In this embodiment, the second crank member 525 includes a conversion sleeve connecting rod and a second support rod 526. One end of the conversion sleeve connecting rod is connected to the movable chuck through a universal ball joint, and the other end thereof is connected to the propeller root conversion sleeve through a universal ball joint. One end of the second support rod 526 is hinged to the swing propeller input shaft 5444, and the other end thereof is connected to the movable chuck through a universal ball joint.

[0101] In this embodiment, the movable chuck includes a first chuck 524a, a second chuck 524b and a friction ring 524c. The first chuck 524a is located below the second chuck 524b. The second chuck 524b is connected to the second support rod 526 through a universal ball joint. The first chuck 524a is connected to the first support rod 523d ​​through a universal ball joint. The first chuck 524a is interference fit with the outside of the movable bearing. A chuck gasket 524d is connected below the first chuck 524a. The chuck gasket 524d is sleeved on the swing On the propeller input shaft 5444, the ball shaft 527 is rotatably connected to the friction ring 524c, the first chuck 524a and the second chuck 524b are both located on the friction ring 524c, and the first chuck 524a and the second chuck 524b are both clamped with the friction ring 524c, and the first chuck 524a is connected to the second chuck 524b by a bolt structure so that the friction ring 524c is limited to the inside of the first chuck 524a and the second chuck 524b, so that the movable chuck can rotate relative to the surface of the ball shaft 527.

[0102] In this embodiment, the number of the second propellers 53 is four, and the four second propellers 53 are evenly distributed at equal angles along the circumference of the swing propeller input shaft 5444. Each second propeller 53 is matched with a swing component to achieve tilting operation of each second propeller 53.

[0103] In this embodiment, since the aircraft has a symmetrical structure, the above content is all described based on one side of the aircraft.

[0104] In this embodiment, the working process of the single-input coaxial compound aircraft is as follows: when the aircraft needs to take off on the spot, the power provided by the engine 80 to the swinging screw mechanism is cut off, and the engine 80 only provides power to the folding screw mechanism. The folding screw mechanism works, and the aircraft rises to achieve a hovering attitude; after the aircraft reaches the specified altitude and the aircraft needs to cruise in the air, the power provided by the engine 80 to the folding screw mechanism is cut off, but the backup engine 90 can still provide power to the folding screw mechanism for a certain period of time. The engine 80 only provides power to the swinging screw mechanism. When the speed of the swinging screw mechanism reaches a predetermined speed, the backup engine 90 stops outputting power to the folding screw mechanism, and the first propeller 43 in the folding screw mechanism folds and contracts, and the aircraft achieves a stable cruising attitude.

[0105] When the aircraft needs to move away from takeoff, the second movable connecting member is activated, specifically the second driving cylinder 328 pushes the second pressing plate 325 connecting ring, and the second pressing plate 325 connecting ring pushes the second pressing plate 325. When the second pressing plate 325 is squeezed, its edge will lift up, so that there is no contact and friction between the second friction member and the second flywheel disc, the power connection between the second transmission shaft 321 and the engine 80 is disconnected, the second meshing shaft 322 no longer rotates, and the power of the swinging screw mechanism is cut off, that is, the engine no longer provides power output for the swinging rotating mechanism. At this time, the first driving cylinder 314 does not work, the first friction member contacts the first flywheel disc 311, and the first flywheel disc 311 is connected to the engine 80. The power of the engine 80 is transmitted to the first meshing shaft 313 through the first transmission shaft 312, and is transmitted to the folding screw mechanism in turn through the first reduction assembly and the first connecting rod 61 mechanism. The folding screw mechanism works, the aircraft rises, and achieves a hovering attitude.

[0106] When the aircraft reaches the specified altitude and needs to cruise in the air, the first movable connecting member is activated. The specific process of the second movable connecting member is referred to, so that the first friction member and the first flywheel disc 311 no longer contact and rub, the power connection between the first transmission shaft 312 and the engine 80 is disconnected, the first meshing shaft 313 no longer rotates, and the power connection between the folding screw mechanism and the engine 80 is cut off. The backup engine 90 still provides power to the folding screw mechanism for a certain period of time. At this time, the second driving cylinder 328 does not work, the second friction member contacts the second flywheel disc, and the second drive cylinder 328 is not in operation. The first flywheel disc 311 is fixedly connected to the second flywheel disc. The power of the engine 80 is transmitted to the second flywheel disc through the first flywheel disc 311. The power of the engine 80 is transmitted to the second meshing shaft 322 through the second flywheel disc and the second transmission shaft 321. The power is then transmitted to the swinging screw mechanism through the second reduction assembly and the second connecting rod 62 mechanism. After the swinging screw mechanism reaches a predetermined speed, the backup engine 90 stops providing power output to the folding screw mechanism. The folding mechanism in the folding screw mechanism folds and retracts the first propeller 43, and the aircraft achieves a stable cruising attitude.

[0107] When the aircraft needs to turn, the swinging assembly in the swinging screw mechanism drives the second screw member to tilt, so as to realize the turning work of the aircraft in the air.

[0108] It should be noted that the above implementation process is only for illustrating the feasibility of the present application, but it does not mean that the single-input coaxial compound aircraft of the present application has only the above-mentioned implementation process. On the contrary, as long as the single-input coaxial compound aircraft of the present application can be implemented, it can be included in the feasible implementation plan of the present application.

[0109] Throughout this specification, reference to terms such as "one embodiment," "some embodiments," "examples," "specific examples," or "some examples" means that a specific feature, structure, material, or characteristic described in conjunction with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0110] The above-described embodiments merely represent several implementation methods of the present invention. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that a person skilled in the art would be able to make various modifications and improvements without departing from the spirit of the present invention, all of which fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be determined by the appended claims.

Claims

1. A single-input coaxial compound aircraft, characterized in that: It includes an aircraft fuselage, a coaxial three-stage reduction mechanism, a power conversion mechanism, a folding screw mechanism, and a swinging screw mechanism provided on the aircraft fuselage; The coaxial three-stage reduction mechanism includes a first reduction mechanism and a second reduction mechanism arranged coaxially, the first reduction mechanism being connected to the second reduction mechanism via a bearing structure, the first reduction mechanism being connected to the folding screw mechanism via a first connecting rod mechanism, and the second reduction mechanism being connected to the swinging screw mechanism via a second connecting rod mechanism, the first reduction mechanism and the second reduction mechanism being used to perform three-stage reduction on the folding screw mechanism and the swinging screw mechanism, respectively; The power conversion mechanism includes a first transmission assembly and a second transmission assembly, wherein the first transmission assembly is connected to an engine, and the first transmission assembly is connected to the second transmission assembly, the first transmission assembly is connected to the first reduction mechanism, and the second transmission assembly is connected to the second reduction mechanism; the first transmission assembly is used to transmit the power provided by the engine to the first reduction mechanism or the second reduction mechanism; The folding propeller mechanism includes a first planetary reduction assembly, a folding assembly, and a first propeller. The plane formed by the rotation of the first propeller is parallel to the horizontal plane. The first propeller is connected to the first connecting rod mechanism via the first planetary reduction assembly. The folding assembly is connected to the first propeller. The folding assembly is used to drive the first propeller to fold in a direction close to the top of the aircraft fuselage. The first planetary reduction assembly is connected to a spare engine. The swinging screw mechanism includes a second planetary reduction assembly, a swinging assembly and a second propeller. The plane formed by the rotation of the second propeller is perpendicular to the horizontal plane. The second propeller is connected to the second connecting rod mechanism through the second planetary reduction assembly. The swinging assembly is connected to the second propeller. The swinging assembly is used to drive the second propeller to swing in a direction close to the tail of the aircraft fuselage.

2. The single-input coaxial compound aircraft according to claim 1, characterized in that: The first transmission assembly includes a first flywheel, a first transmission shaft and a first movable connecting piece. One end of the first transmission shaft is movably connected to the first flywheel through the first movable connecting piece. The other end of the first transmission shaft is connected to the first reduction mechanism through a first engaging shaft. The first flywheel is connected to the engine. The first movable connecting piece is used to disconnect or connect the first transmission shaft from or to the first flywheel.

3. The single-input coaxial compound aircraft according to claim 2, characterized in that: The first movable connecting part includes a first driving cylinder, a first pressure plate connecting ring, a first pressure plate and a first friction part. The first driving cylinder is connected to the first transmission shaft through a first connecting structure. The piston rod of the first driving cylinder is connected to the first pressure plate through the first pressure plate connecting ring. The first pressure plate is connected to the first friction part, and the first friction part is movably connected to the first flywheel disc.

4. The single-input coaxial compound aircraft according to claim 2, characterized in that: The second transmission assembly includes a second flywheel, a second transmission shaft and a second movable connecting piece. One end of the second transmission shaft is connected to the second flywheel through the second movable connecting piece, and the other end of the second transmission shaft is connected to the second reduction mechanism through a second meshing shaft. The first flywheel and the first transmission shaft are both hollow structures. The second flywheel is built into the first flywheel, and the second transmission shaft is built into the first transmission shaft.

5. The single-input coaxial compound aircraft according to claim 3, characterized in that: The first friction member includes two first friction plates, a first reduction plate and a telescopic spring. The two friction plates are respectively glued to the opposite ends of the first reduction plate. A groove is provided on the first reduction plate. A cylindrical boss is respectively provided on the groove walls on both sides of the opposite sides of the groove. The two ends of the telescopic spring are respectively connected to the two cylindrical bosses.

6. The single-input coaxial compound aircraft according to claim 2, characterized in that: The first reduction mechanism includes a primary reduction gear, a secondary reduction gear and a tertiary reduction gear. The primary reduction gear, the secondary reduction gear and the tertiary reduction gear are all clearance-matched with the first meshing shaft. The primary reduction gear is synchronously transmitted with the first meshing shaft through a primary synchronization structure. The secondary reduction gear and the tertiary reduction gear are both synchronously transmitted with the first meshing shaft through a secondary synchronization structure.

7. The single-input coaxial compound aircraft according to claim 6, characterized in that: The first transmission shaft is provided with a first mating gear, a second mating gear and a third mating gear, and the first mating gear, the second mating gear and the third mating gear are respectively meshed with the first-stage reduction gear, the second-stage reduction gear and the third-stage reduction gear for transmission.

8. The single-input coaxial compound aircraft according to claim 4, characterized in that: The first connecting rod mechanism includes a first connecting rod member, a second connecting rod member and a third connecting rod member connected in sequence, the first connecting rod member is connected to the first meshing shaft through a first single-curved gear, the second connecting rod member is connected to the third connecting rod member through a first double-curved gear, and the third connecting rod member is connected to the first planetary reduction assembly through a second single-curved gear.

9. The single-input coaxial compound aircraft according to claim 8, characterized in that: The second connecting rod mechanism includes a fourth connecting rod, a fifth connecting rod and a sixth connecting rod connected in sequence, the fourth connecting rod is connected to the second meshing shaft through a third single-curved gear, the fifth connecting rod is connected to the sixth connecting rod through the first double-curved gear, and the sixth connecting rod is connected to the second planetary reduction assembly through a fourth single-curved gear.

10. The single-input coaxial compound aircraft according to claim 9, characterized in that: The sixth connecting rod is a hollow structure, one end of the third connecting rod is built into the sixth connecting rod, and the sixth connecting rod is connected to the third connecting rod through a second bearing structure. The third connecting rod and the sixth connecting rod are respectively connected to the inner tooth surface and the outer tooth surface of the first hypoid gear.

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