TWM552374U - Co-axial dual-rotor turbo transmission unmanned vehicle mechanism system - Google Patents

Description

Coaxial double-rotor turbine drive unmanned vehicle mechanism system

This creation is about a coaxial double-rotor turbine drive unmanned vehicle system, especially a coaxial double-rotor turbine drive unmanned vehicle with full evolution in terms of flight capability, safety, stability, manufacturing, and disassembly. Institutional system.

Remotely controlled unmanned helicopters are mainly distinguished by the number of rotor shafts: single rotor, double rotor and multi-rotor. Among them, the double-rotor RC helicopter can be subdivided into four types: coaxial, tandem, horizontal, and cross. The general coaxial double-rotor turbine-driven unmanned vehicle mechanism system includes three main mechanisms: a fuselage, a turbine engine, and a coaxial double-rotor mechanism.

Turbine engines, also known as turboshaft engines, use the airflow generated by the combustion chamber to drive the free turbine output shaft power, rather than the jet thrust. It is similar in structure to a turboprop engine, but the main difference is that the exhaust from the turboprop engine also produces some residual propulsion. In addition to the turboprop engine, the final drive of the drive train is integrated on the engine, while for the turboshaft engine it is split.

The transmission output structure of the conventional turbine engine is manufactured in one piece, and due to its integral structure, it is complicated when the output gear is damaged and the like, and when the gear ratio needs to be replaced. The disassembly and assembly method needs to be disassembled and assembled as a whole, and the process is complicated. In addition, it is very difficult to process the transmission output structure.

The coaxial double-rotor mechanism comprises a large main shaft, a small main shaft, an upper main rotor group, a lower main rotor group, a plurality of upper rotor blades, a plurality of lower rotor blades, an upper coaxial double-rotor swash plate phase control fixed seat structure and a lower coaxial double Rotor Phillips disc phase control mount structure, its structure is different from the general large helicopter. The large spindle is rotatably disposed in the body, extends through the top of the body, and has a shaft hole. The small spindle is rotatably disposed in the body and extends through the shaft bore of the large spindle. The upper main rotor group is set on the small main shaft, and the lower main rotor group is set on the large main shaft. The upper rotor blades are disposed on the upper main rotor group, and the lower rotor blades are disposed in the lower main rotor group. The upper coaxial double-rotor swash plate phase control fixing seat structure is arranged on the small main shaft, and the plurality of connecting rods are connected between the upper main rotor group and the upper coaxial double-rotor swash plate phase control fixing seat structure. The lower coaxial double-rotor swash plate phase control fixing seat structure is arranged on the large main shaft, and the plurality of connecting rods are connected between the lower main rotor group and the lower coaxial double-rotor swash plate phase control fixing seat structure. The upper and lower main rotor groups are arranged up and down and are respectively rotated in opposite directions on the same axis by the coaxial small and large spindle drives (that is, the small and large spindles respectively drive the upper and lower main rotor groups to rotate in different directions) And the coaxial twin-rotor RC helicopter can stably take off and land by the lift generated by the upper and lower rotor blades when rotating. Among them, the rotor is a circular motion. Due to the radius, when the linear velocity of the wing tip of the upper and lower rotor blades is close to the speed of sound, the linear velocity at the center of the circle is zero, so the maximum lift is generated near the circumference of the rotor, and close to the center of the circle. The place only produces negligible lift. The small and large main shafts are used to synchronously drive the upper and lower main rotor groups to tilt relative to the fuselage by means of the upper and lower coaxial double-rotor swashplate phase control fixed seat structure and the combination of the connecting rods to change the flight angle of the coaxial double-rotor remote control helicopter. (for example, forward, backward, left turn, right turn).

The upper main rotor group includes an upper main rotor mount and a coaxial double rotor direction control mount structure. The upper main rotor fixing base comprises a body, a plurality of extension arms and a plurality of paddle chucks. The seat body of the upper main rotor fixing seat is disposed on the small main shaft, and the extension arms protrude from the outer ring wall of the seat body at intervals, the paddles Chucks are respectively provided at the ends of the extension arms. The coaxial double-rotor direction control fixing seat structure is disposed above the seat body of the upper main rotor fixing seat.

However, the aforementioned coaxial double-rotor directional control fixed seat structure is only connected by a shaft to the seat body of the upper main rotor mount and the three links are connected with the extension arms of the upper main rotor mount, so that the upper The main rotor group has poor stability and is easy to sway relative to the small spindle, resulting in an offset, which in turn causes the small and large spindles to drive the upper and lower mains by the upper and lower coaxial double-rotor swashplate phase control fixed seat structure and the connecting rods. When the rotor group is tilted relative to the fuselage to change the flight angle of the coaxial dual-rotor RC helicopter and tilted relative to the fuselage, the tilt angle of the upper rotor blades cannot be consistent, resulting in the coaxial double-rotor turbine drive unmanned vehicle mechanism system being inaccurate. The ground maintains flying at a preset angle.

Another conventional coaxial dual-rotor directional control mount structure includes a body and two sliding pins, and the two sliding pins are disposed between the body of the coaxial double-rotor direction control fixed seat structure and the base of the upper main rotor fixed seat, thereby The stability of the upper main rotor group makes the upper main rotor group less sway relative to the small main shaft.

However, the coaxial double-rotor directional control mount structure of the double-slide pin can only reduce the error of the inclination angle of the three upper rotor blades, and the coaxial double-rotor turbine-driven unmanned vehicle mechanism system can be approached by a preset angle. However, it is still impossible to keep the inclination angles of the three upper rotor blades consistent, so the coaxial double-rotor turbine-driven unmanned vehicle mechanism system with the coaxial double-rotor directional control fixed seat structure loaded with such double sliding pins is still unable to accurately maintain Flying at a preset angle cannot completely solve the problems caused by the aforementioned coaxial double-rotor direction control mount structure without slip.

Furthermore, the two sliding pins are easily deformed by force. When one of the sliding pins is deformed or bent by the collision, the coaxial double-rotor direction control fixed seat structure of the double sliding pin "lifts the stability of the upper main rotor group. The effect of "land" is immediately lost, even if the other slippery is as good as ever, it will not help.

Please refer to FIG. 1. FIG. 1 is a top view of a conventional rotor blade. The structure of the upper and lower rotor blades is identical, so the upper and lower rotor blades will be represented by "rotor blades" below. A typical rotor blade A includes a blade body A1, a joint portion A2, and a wing tip portion A3. The blade body A1 is linear, and the two ends of the longitudinal direction are defined as a first end and a second end, and the two sides in the width direction are defined as a first side A13 and a second side A14. The joint portion A2 is provided at the first end of the blade body A1 and is provided to the paddle chucks of the upper and lower main rotor groups. The wing tip portion A3 is disposed at the second end of the blade body A1, is located on the same plane as the blade body A1, extends linearly away from the direction of the joint portion A2, and is tapered such that its longitudinal direction is opposite to the blade body A1. The length direction is the same and is parallel to the longitudinal direction of the blade body A1. In short, the general configuration of the general rotor blade A is linear. The vortex line of such a linear rotor blade A is kept perpendicular to the lift line, resulting in a very limited lift generated.

Further, the wing tip portion A3 of the linear rotor blade A is highly likely to generate a regional vibration wave when it is rotated at a high speed, thereby improving the resistance.

Please refer to FIG. 2. FIG. 2 is a cross-sectional view of a conventional rotor blade. The blade body A1 has a top surface A15 and a bottom surface A16. The top surface A15 and the bottom surface A16 of the blade body A1 are from the first side A13 of the blade body A1 to the second side of the blade body A1. The curvature of the side A14 is equal; the top surface A15 of the blade body A1 is first bent upward from the first side A13 of the blade body A1, and then bent downward to the second side A14 of the blade body A1; the blade body A1 The bottom surface A16 is first bent downward from the first side A13 of the blade body A1 and then bent upward to the second side A14 of the blade body A1. In other words, the arc lengths of the top surface A15 and the bottom surface A16 of the blade body A1 from the first side A13 to the second side A14 are equal, and the bending manners of the top surface A15 and the bottom surface A16 of the blade body A1 correspond to each other. Therefore, the height and the undulation are quite uniform, so that the overall structure of the blade body A1 is symmetrical. However, the lift generated by such a symmetrical blade body A1 is very limited.

The conventional upper coaxial double-rotor swashplate phase control mount structure includes an upper inner ring set, an upper outer ring set, an upper inner ring phase fixed seat set, and an upper outer ring phase fixed seat set. The upper inner ring set is sleeved on the small main shaft and has a plurality of upper inner globes, and the plurality of first connecting rods are connected between the upper inner globe and the upper main rotor group. The upper outer ring set is disposed in the upper inner ring group and has a plurality of upper outer ring heads. The upper inner ring phase fixing seat set comprises an upper inner ring phase fixing seat body, an upper inner ring latch and an upper inner ring handle. The upper inner ring phase fixing seat body is sleeved on the small main shaft. The upper inner ring is pivoted on the upper inner ring phase fixing seat. One end of the upper inner ring handle is disposed on one of the upper inner ring heads, and the upper inner ring latch rotatably fastens the other end of the upper inner ring handle. The upper outer ring phase fixing seat set comprises an upper outer ring phase fixing seat body, an upper outer ring latch and an upper outer ring connecting handle. The upper outer ring phase fixing seat body is sleeved on the small main shaft. The upper outer ring is pivoted to the upper outer ring phase fixing seat. One end of the upper outer ring handle is disposed on one of the upper and outer ring heads, and the upper outer ring pin rotatably buckles the other end of the upper outer ring handle.

The conventional lower coaxial double-rotor swashplate phase control fixing seat structure comprises a lower inner ring group, a lower outer ring group, a lower inner ring phase fixed seat group and a lower outer ring phase fixed seat group. In other words, the structure of the lower coaxial double-rotor swashplate phase control fixed seat structure is identical to that of the upper coaxial double-rotor symmetrical disk phase control fixed seat structure, and the connection relationship between the components is also the same, the difference is: the lower inner ring set Located on the main spindle, a plurality of second connecting rods are connected between the upper outer globe head and the lower inner globe head, and the plurality of third connecting rods are connected between the lower inner globe head and the lower main rotor group ball head, and the fourth joint is connected. The rod is connected between the lower outer head and the ball head inside the remote control helicopter.

When the first and second inner ring links of the upper inner ring link rotate outward, the first and second inner ring links of the lower inner ring link rotate inward. When the first and second inner ring links of the upper inner ring link rotate inward, the first and second inner ring links of the lower inner ring link rotate outward. By controlling the combination of the inner ring group and the lower outer ring group relative to the large main axis, and the combination of the upper inner ring group and the upper outer ring group is relatively small spindle skew, thereby controlling the upper and lower main rotor groups to synchronize relative to the fuselage Deflection to change the flight angle of the coaxial dual-rotor RC helicopter.

However, there is a gap between the upper inner ring latch and the upper inner ring handle, and there is a gap between the lower inner ring latch and the lower inner ring handle, and there is a gap between the upper outer ring latch and the upper outer ring handle. There is a gap between the lower outer ring catch and the lower outer ring handle. Therefore, when the upper and lower main rotor groups are respectively rotated in opposite directions on the same axis by the coaxial small and large spindle drives, the coaxial double-rotor mechanism will generate vibration as a whole, resulting in the upper inner ring handles from above. The inner ring latch is gradually loosened, the upper outer ring handle is gradually loosened from the upper outer ring latch, the lower outer ring handle is gradually loosened from the lower outer ring latch, and the lower inner ring is attached from the lower inner ring. The cassette is gradually loosened, so that the upper and lower coaxial double-rotor swashplate phase control mount structure loses its effectiveness and cannot change the flight angle of the coaxial dual-rotor remote control helicopter.

Furthermore, the materials of the upper inner ring, the upper outer ring, the lower inner ring and the lower outer ring are all plastic, and the structural strength is poor. In the long-term use, the upper inner ring latch, the upper outer ring latch, the lower inner ring latch and the lower outer ring latch are easily worn by vibration, so that the upper inner ring handle, the upper outer ring handle, and the lower inner ring The adapter and the lower outer ring handle are more easily released from the upper inner ring latch, the upper outer ring latch, the lower inner ring latch, and the lower outer ring latch, thereby allowing the upper and lower coaxial double-rotor swashplate phases Controlling the structure of the fixed seat loses its effectiveness and cannot change the flight angle of the coaxial dual-rotor RC helicopter.

In addition, the distance between the upper inner ring link and the small main shaft is smaller than the distance between the lower inner ring link and the large main shaft, so that the first and second inner ring links of the upper inner ring link rotate outward to the limit, the lower inner The first and second inner ring links of the ring link have a little space with the large main axis and continue to rotate inward to simultaneously touch the large main axis, resulting in a combination of the lower inner ring group and the lower outer ring group. The skew angle is greater than the skew angle of the combination of the upper inner ring group and the upper outer ring group relative to the small main shaft, thereby causing the upper and lower main rotor groups to be unable to synchronize relative to the fuselage deflection, thereby causing the coaxial double-rotor RC helicopter to change the flight angle. Out of control in the process.

It can be seen from the above that the conventional coaxial double-rotor turbine-driven unmanned vehicle mechanism system has many unsatisfactory aspects in the coaxial double-rotor and the turbine engine, and these undesired points affect each other's flight capacity, Safety, stability, manufacturing, and disassembly, there is an urgent need to develop a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system that can improve the above problems in all aspects.

The main purpose of this creation is to provide a coaxial double-rotor turbine drive unmanned vehicle mechanism system. The transmission output structure of the turbine engine is more convenient and quicker in processing, such as replacement, disassembly and assembly, and facilitates processing and manufacturing, saving replacement and maintenance time; The sliding stability of the rotor group is good, and the degree of swaying relative to the small spindle is small; the lift generated by the aerodynamic configuration of the upper and lower rotor blades and the effect of reducing the resistance are good; maintaining the structure of the upper and lower coaxial double-rotor swash plate phase control fixed seat The function of the created flight angle, and precise control of the upper and lower main rotor groups synchronized relative to the fuselage deflection, enables the creation to stably change the flight angle.

In order to achieve the foregoing objectives, the present application will provide a coaxial dual-rotor turbine driven unmanned vehicle mechanism system including a fuselage, a turbine engine and a coaxial twin-rotor mechanism.

The turbine engine is disposed in the fuselage and includes a transmission output structure. The transmission output structure includes a turbine engine, an adapter and an output gear. The turbine engine includes an engine body, a turbine drive shaft and a fixed ring. The turbine drive shaft can be Rotatingly disposed on the engine body and having one side protruding from one side of the engine body, the fixing ring is disposed at one end of the turbine drive shaft, the adapter seat is disposed on the fixing ring, and the output gear is disposed on the adapter seat.

The coaxial double-rotor mechanism includes a large main shaft, a small main shaft, an upper main rotor group, a lower main rotor group, a plurality of upper rotor blade aerodynamic configurations, a plurality of lower rotor blade aerodynamic configurations, and an upper coaxial double-rotor swash plate phase control fixed The seat structure and the structure of the coaxial coaxial double-rotor swash plate phase control fixed seat.

The large spindle is rotatably disposed in the body, extends through the top of the body, and has a shaft hole.

The small spindle is rotatably disposed in the body and extends through the shaft bore of the large spindle.

The upper main rotor group comprises an upper main rotor fixing seat and a coaxial double rotor direction control fixing seat structure, the upper main rotor fixing seat is arranged on the small main shaft and comprises a plurality of upper paddle chucks, and the coaxial double rotor direction control fixing seat structure is arranged on the upper main rotor The main rotor fixing base comprises a body, a shaft rod, a plurality of connecting rods and at least three supporting structures. The body is located above the upper main rotor fixing seat and coaxial with the upper main rotor fixing seat, and the shaft rod is disposed on the main body and the upper main rotor fixing seat. And extending on an axis of the main body and an axis of the upper main rotor fixing seat, the connecting rods are respectively disposed between the outer side of the main body and the outer side of the upper main rotor fixing seat, and the supporting structures are respectively disposed around the shaft Between the bottom of the body and the top of the upper main rotor mount.

The lower main rotor group includes a lower main rotor mount, and the lower main rotor mount is disposed on the main spindle and includes a plurality of lower paddles.

The aerodynamic configurations of the upper rotor blades each include an upper blade body, an upper joint portion and an upper wing tip portion. The upper blade body is linear, and the two ends of the longitudinal direction are respectively defined as a first end and a first end. a second end, the two sides of the width direction are respectively defined as a first side and a second side, and have a top surface and a bottom surface, and the upper joint portion is disposed at the first end of the upper blade body and is disposed at An upper paddle, the upper wing tip being disposed at the second end of the upper blade body, extending in the same plane as the upper blade body, and away from the upper joint and the first side of the upper blade body The extension is such that the longitudinal direction of the upper wing tip is different from the longitudinal direction of the upper blade body and at an angle to the longitudinal direction of the upper blade body.

The aerodynamic configurations of the lower rotor blades each include a lower blade body, a lower joint portion and a lower wing tip portion. The lower blade body is linear, and the two ends of the longitudinal direction are respectively defined as a first end and a second end. The two sides of the width direction are respectively defined as a first side and a second side, and have a top surface and a bottom surface, and the lower joint portion is disposed at the first end of the lower blade body and is disposed on the lower paddle a head, a lower wing tip disposed at a second end of the lower blade body, extending in the same plane as the lower blade body, and extending away from the lower joint and the first side of the lower blade body, such that The longitudinal direction of the lower wing tip is different from the longitudinal direction of the lower blade body and has an angle with the longitudinal direction of the lower blade body.

The upper coaxial double-rotor swash plate phase control fixing seat structure comprises an upper inner ring group, an upper outer ring group, an upper inner ring phase fixing seat group and an upper outer ring phase fixing seat group, and the upper inner ring group is sleeved in a small The main shaft has an upper inner ring head, the upper outer ring set ring is disposed on the upper inner ring group and has an upper outer ring head, and the upper inner ring phase fixed seat set includes an upper inner ring phase fixing seat body and an upper inner ring link The upper inner ring phase fixing seat body is sleeved on the small main shaft, and the upper inner ring connecting piece has a first end and a second end, at least one upper inner ring, a top inner ring connecting handle and a plurality of upper inner ring fixing members The fixing member is screwed on the first end of the upper inner ring connecting member and the upper inner ring phase fixing seat body, so that the first end of the upper inner ring connecting member is fixed to the upper inner ring phase fixing seat body by the upper inner ring fixing member. The inner ring shank has a first end and a second end, and at least one upper inner ring fixing member is screwed on the first end of the upper inner ring shank and the second end of the upper inner ring connecting member, so that the upper inner ring is connected The first end of the handle is fixed to the second end of the upper inner ring connecting piece by the upper inner ring fixing member, and the upper inner ring is connected to the handle The second end is disposed on the upper inner ring head, and the upper outer ring phase fixing seat set comprises an upper outer ring phase fixing seat body, an upper outer ring connecting piece, an upper outer ring connecting handle and a plurality of upper outer ring fixing members, the upper outer part The ring-shaped fixing base body is sleeved on the small main shaft, the upper outer ring connecting member has a first end and a second end, and at least one upper outer ring fixing member is screwed on the first end and the upper outer ring of the upper outer ring connecting member The phase fixing base body is such that the first end of the upper outer ring connecting member is fixed to the upper outer ring phase fixing seat body by the upper outer ring fixing member, and the upper outer ring connecting handle has a first end and a second end, at least one The outer ring fixing member is screwed on the first end of the upper outer ring connecting handle and the second end of the upper outer ring connecting piece, so that the first end of the upper outer ring connecting handle is fixed to the upper outer ring connecting piece by the upper outer ring fixing member The second end of the upper outer ring is provided at the upper outer head.

The lower coaxial double-rotor swash plate phase control fixing seat structure comprises a lower inner ring group, a lower outer ring group, a lower inner ring phase fixed seat group and a lower outer ring phase fixed seat group, and the lower inner ring group is sleeved on the lower inner ring group a large main shaft and having a lower inner ring head, the lower outer ring set ring is disposed in the lower inner ring group and has a lower outer ring head, and the lower inner ring phase fixing seat group limiting the rotation angle includes a lower inner ring phase fixing seat body and a lower inner ring a ring connecting member, a lower inner ring connecting handle, a plurality of lower inner ring fixing members and a limiting device, the lower inner ring phase fixing seat body is sleeved on the large main shaft, and the lower inner ring connecting member comprises a first lower inner ring connecting rod and a second lower inner ring link, the first lower inner ring link has a first end and a second end, and the second lower inner ring link has a first end and a second end, at least the inner ring is fixed a screw is disposed on the first end of the first lower inner ring link and the lower inner ring phase fixing seat body, such that the first end of the first lower inner ring link is fixed to the lower inner ring phase fixing seat by the lower inner ring fixing member The body, at least the inner ring fixing member is screwed to the second lower inner ring a first end and a second end of the first lower inner ring link such that the first end of the second lower inner ring link is fixed to the second end of the first lower inner ring link by the lower inner ring fixing member, The inner ring shank has a first end and a second end, and at least the lower inner ring fixing member is screwed on the first end of the lower inner ring shank and the second end of the second lower inner ring link, so that the lower inner ring The first end of the shank is fixed to the second end of the second lower inner ring link by the lower inner ring fixing member, the second end of the lower inner ring shank is disposed at the lower inner ring head, and at least a part of the limiting device is located in the lower end Between the inner side of the ring link and the outer side of the large spindle, wherein when the lower inner ring link is rotated outward to a first position, the lower inner ring link is away from the major axis; when the lower inner ring link is rotated inwardly to In the second position, the limiting device limits the angle at which the first lower inner ring link and the second lower inner ring link rotate inwardly so that the inner side of the lower inner ring link is spaced apart from the outer side of the large main axis, The outer ring phase fixing seat set includes a lower outer ring phase fixing seat body, a lower outer ring connecting piece, a lower outer ring connecting handle and a plurality of The ring fixing member, the lower outer ring phase fixing seat body is sleeved on the large main shaft, and the lower outer ring connecting member has a first end and a second end, and at least the lower outer ring fixing member is screwed on the first outer ring connecting member The end and the lower outer ring phase fix the seat body such that the first end of the lower outer ring connecting member is fixed to the lower outer ring phase fixing seat body by the lower outer ring fixing member, and the lower outer ring connecting handle has a first end and a second end And at least a lower outer ring fixing member is screwed on the first end of the lower outer ring connecting handle and the second end of the lower outer ring connecting member, so that the first end of the lower outer ring connecting handle is fixed to the lower end by the lower outer ring fixing member The second end of the outer ring link and the second end of the lower outer ring handle are disposed on the lower outer globe.

The effect of this creation is that the transmission output structure of the turbine engine is more convenient and quicker in processing, such as replacement, disassembly and assembly, and is advantageous for processing and manufacturing, saving replacement and maintenance time; the sliding stability of the upper main rotor group is good, and the relatively small spindle is swaying. The degree is small; the lift of the aerodynamic configuration of the upper and lower rotor blades and the effect of reducing the resistance are good; maintaining the upper and lower coaxial double-rotor swash plate phase control fixed seat structure changes the function of the flight angle of the creation, and precisely controls the upper, The lower main rotor group is synchronously deflected relative to the fuselage, enabling the creation to stably change the angle of flight. In this way, the performance of this creation has evolved in all aspects of flight capability, safety, stability, manufacturing and disassembly.

The implementation of the present invention will be described in more detail below with reference to the drawings and component symbols, so that those skilled in the art can implement the present specification after studying the present specification.

Please refer to FIG. 3 , which is a schematic diagram of the coaxial double-rotor turbine driven unmanned vehicle mechanism system of the present invention. The present invention provides a coaxial double-rotor turbine driven unmanned vehicle mechanism system, including a fuselage 10 and a turbine engine 20 . And a coaxial double rotor mechanism 30.

Please refer to FIG. 4a to FIG. 4d. FIG. 4a is a perspective view of the transmission output structure of the turbine engine of the present invention, FIG. 4b is an exploded view of the transmission output structure of the turbine engine of the present invention, and FIG. 4c is the transmission output of the turbine engine of the present creation. A side view of the structure, Figure 4d is a cross-sectional view of the transmission output structure of the turbine engine of the present invention. The turbine engine 20 is disposed on the fuselage 10 and includes a transmission output structure 21 including a turbine engine 22, an adapter 23, a plurality of adapter screws 24, an output gear 25, a plurality of gear screws 26, and a transmission. Gear 27. The rest of the structure of the turbine engine 20 is conventional and will not be described herein.

The turbine engine 22 includes an engine body 221, a turbine drive shaft 222, a stationary ring 223, and a protruding tube 224. The turbine drive shaft 222 is rotatably provided to the engine body 221 and has one side protruding from one side of the engine body 221. The retaining ring 223 is disposed on an axis of the turbine drive shaft 222 that protrudes from one side of the engine body 221. The fixing ring 223 defines a plurality of fixing screw holes 2231. The protruding tube 224 protrudes from the axis of the side of the fixing ring 223 away from the engine body 221.

The adapter seat 23 includes an adapter ring 231, an adapter tube 232, and a shaft hole 233. The adapter ring 231 defines a plurality of adapter screw holes 2311. The transfer tube 232 protrudes from the axis of the side of the adapter ring 231 away from the engine body 221 and opens a plurality of output screw holes 2321. The shaft hole 233 of the adapter 23 penetrates the axis of the adapter ring 231 and the transfer tube 232. The adapter ring 231 is attached to the fixing ring 223. The adapter screw holes 2311 are correspondingly fixed to the screw holes 2231. The adapter screws 24 are respectively screwed to the adapter screw holes 2311 and the fixing screw holes 2231. . However, the fixing manner of the adapter ring 231 and the fixing ring 223 is not limited thereto. In other embodiments, the adapter ring 231 may be fixed to the fixing ring 223 by snapping, rotating, fixing, or other fixing manner. , first and foremost. The protruding tube 224 is butted from the side of the fixing ring 223 and is engaged with the shaft hole 233 of the adapter seat 23 . Thereby, when the turbine engine 22 is started, the turbine drive shaft 222 begins to rotate relative to the engine body 221 and drives the adapter 23 to rotate synchronously.

The output gear 25 includes a gear tube 251, a shaft hole 252, and a plurality of output gear teeth 253. A plurality of gear screw holes 2511 are formed in the outer ring surface of the gear tube 251. The shaft hole 252 penetrates the axial center of the gear tube 251 and the front and rear ends of the gear tube 251. The output teeth 253 are annularly disposed on the outer ring surface of the gear tube 251. The transfer tube 232 is inserted into the shaft hole 252 of the output gear 25. The gear screw holes 2511 correspond to the output screw holes 2321, and the gear screws 26 are screwed to the gear screw holes 2511 and the output screw holes 2321, respectively. However, the manner in which the adapter tube 232 and the gear tube 251 are fixed is not limited thereto. In other embodiments, the adapter tube 232 may be fixed to the gear tube 251 by snapping, rotating, fixing, or other fixing manner. , first and foremost. Thereby, when the adapter seat 23 is rotated, the adapter seat 23 can drive the output gear 25 to rotate synchronously.

The drive gear 27 includes a plurality of drive gear teeth 271. The drive gear teeth 271 are engaged with the output gear teeth 253. Thereby, when the output gear 25 rotates, the output gear 25 can drive the transmission gear 27 to rotate synchronously.

Since the components such as the turbine engine 22, the adapter 23, and the output gear 25 are segmented and fixed (that is, sequentially connected and fixed to each other), the gear ratio of the output gear 25 is changed, or the output gear 25 is caused by long-term use. When the output gear 25 needs to be replaced due to aging or damage, only the connection relationship between the adapter 23 and the output gear 25 needs to be released, that is, the gear screw 26 is directly removed, or the adapter tube 232 is engaged with the gear tube 251. The gear ratio of the output gear 25 can be replaced by fixed opening. Further, when the output gear 25 having a different diameter is selected, the adapter 23 can be directly processed, and the adapter 23 corresponding to the diameter of the output gear 25 can be changed, so that the output gear 25 having a different diameter can be replaced. Compared with the prior art, the transmission output structure 21 of the present invention does not need to be replaced as a whole, and the structure is more convenient and quicker in the application of replacement, disassembly and assembly, and saves replacement and maintenance time.

Please refer to FIG. 3 and FIG. 5. FIG. 3 is a schematic diagram of the coaxial double-rotor turbine driven unmanned vehicle mechanism system of the present invention, and FIG. 5 is a perspective view of the coaxial double-rotor mechanism of the present invention. The coaxial double-rotor mechanism 30 includes a large main shaft 40, a small main shaft 50, an upper main rotor group 60, a lower main rotor group 70, a plurality of upper rotor blade aerodynamic configurations 80, a plurality of lower rotor blades aerodynamic configuration 90, and an upper coaxial The dual-rotor swashplate phase control mount structure 100 and the lower coaxial dual-rotor swashplate phase control mount structure 110.

The main spindle 40 is rotatably disposed on the body 10, extends through the top of the body 10, and has a shaft hole (not shown).

The small spindle 50 is rotatably disposed in the body 10 and extends through the shaft hole of the large spindle 40.

Please refer to FIG. 3 and FIG. 6a to FIG. 6d. FIG. 3 is a schematic diagram of the coaxial double-rotor turbine driven unmanned vehicle mechanism system of the present invention. FIG. 6a is a schematic diagram of the upper main rotor group of the present invention, and FIG. The perspective view of the double-rotor direction control fixed seat structure, FIG. 6c is an exploded view of the coaxial double-rotor direction control fixed seat structure, and FIG. 6d is another angular exploded view of the coaxial double-rotor direction control fixed seat structure. The upper main rotor set 60 includes an upper main rotor mount 61 and a coaxial dual rotor directional control mount structure 62.

The upper main rotor mount 61 is disposed on the small spindle 50 and includes an upper body 611, at least three upper extension arms 612, and at least three upper paddle clamps 613. At least three upper extension arms 612 are spaced apart from one outer ring wall of the upper seat 611, and each upper extension arm 612 is equally spaced from the adjacent two upper extension arms 612. At least three upper paddles 613 are provided at the ends of at least three upper extension arms 612 (i.e., one end away from the upper body 611). Generally, the number of upper extension arms 612 and the number of upper paddles 613 are three and the angle between the adjacent upper extension arms 612 is one hundred and twenty degrees, so the upper main rotor mount 61 The overall appearance is herringbone, as shown in Figure 6a.

The coaxial dual-rotor directional control mount structure 62 includes a body 63, a shaft 64, a plurality of links 65, and at least three support structures 66, as shown in Figure 6a.

The body 63 is located above the upper main rotor mount 61 and is coaxial with the upper main rotor mount 61. In this embodiment, the body 63 includes a base 631 and a plurality of pivots 632 pivoted on the outer side of the base 631. Specifically, an outer ring wall of the base 631 is spaced apart from the plurality of cantilevers 6311, and the pivotal seats 632 are respectively pivotally mounted on the cantilever arms 6311.

The shaft 64 is disposed between the body 63 and the upper main rotor mount 61 and extends on an axis of the body 63 and an axis of the upper main rotor mount 61. Specifically, the base 631 defines a base shaft hole 6312 at the axial center, as shown in FIG. 6c and FIG. 6d; the upper base 611 defines a upper body shaft hole 6111 at the axial center, as shown in FIG. 6a; The rod 64 is disposed between the base 631 and the upper seat 611, and the two ends are respectively disposed on the base shaft hole 6312 and the upper seat shaft hole 6111, and extend on an axis 113 of the base 631 and an axis 6112 of the upper seat 611. , as shown in Figure 6a and Figure 6b.

The links 65 are respectively disposed between the outer side of the body 63 and the outer side of the upper main rotor mount 61. More specifically, one end of the connecting rods 65 is respectively disposed on the outer side of the pivoting seats 632, and the other ends are respectively pivotally disposed on the outer sides of the at least three upper extending arms 612.

At least three support structures 66 are disposed about the shaft 64 between the bottom of the body 63 and the top of the upper main rotor mount 61, as shown in Figure 6a. Specifically, the outer ring wall of the base 631 protrudes at least three protrusions 6314 at intervals, and each of the protrusions 6314 is equally spaced from the adjacent two protrusions 6314, and each protrusion 6314 is disposed on the second cantilever. Between 6311 and shorter than the length of each cantilever 6311; at least three support structures 66 are rod-shaped and are disposed around the shaft 64 at the bottom of at least three projections 6314 and the top of the upper main rotor mount 61, respectively. Wherein, the number of the cantilever 6311, the protruding portion 6314, the pivoting seat 632, the connecting rod 65 and the supporting structure 66 are equal to the number of the upper extending arms 612, and the number of the upper extending arms 612 of the present embodiment is three, so the cantilever 6311, the number of the projections 6314, the pivot seat 632, the link 65 and the support structure 66 are all three. Thereby, the support structures 66 can provide the effect of three-point support, so that the stability of the upper main rotor group 60 is better than the prior art, so the degree of sway relative to the small spindle 50 is smaller than that of the prior art, and thus the small spindle 50 And the main spindle 40 is driven synchronously by the upper coaxial double-rotor swashplate phase mount 100 and the lower coaxial double-rotor swashplate phase mount 110 and the plurality of first links 121 and the plurality of third links 123 (see FIG. 8a) When the rotor set 60 and the lower main rotor set 70 are inclined relative to the fuselage 10 to change the flight angle of the present invention and are inclined relative to the fuselage 10, the tilt angle of the upper rotor blade aerodynamic configuration 80 is smaller than the prior art error. Therefore, compared with the prior art, the creation can be closer to flying at a preset angle.

Preferably, the support structures 66 extend through and perpendicular to the axis 6121 of the upper extension arms 612; in other words, the support structures 66 are respectively located on the axis 6121 of the upper extension arms 612, and respectively The direction perpendicular to the extension of the upper extension arms 612 is as shown in FIG. 6a; the distance between the support structures 66 and the adjacent two support structures 66 is equal. More specifically, the extending directions of the protrusions 6314 are respectively parallel to the extending direction of the upper extending arms 612, and an axis 63141 of each of the protruding portions 6314 is located directly above the axis 6121 of the corresponding upper extending arm 612. As shown in FIG. 6a, the bottoms of the protrusions 6314 respectively define a hole 63142 extending through and perpendicular to the axis 63141 of the protrusions 6314; that is, the holes 63142 Positioned on the axis 63141 of the protrusions 6314, respectively, and perpendicular to the extending direction of the protrusions 6314, as shown in FIG. 6d; the top of the upper main rotor holder 61 is provided with three through holes 614, the perforations 614 extend through and perpendicular to the axis 6121 of the upper extension arms 612, respectively, and directly below the apertures 63142, as shown in Figure 6a; that is, the perforations 614 are located at each of the upper extension arms 612, respectively. On the axis 6121, and perpendicular to the direction in which the upper extension arms 612 extend, respectively. Preferably, the perforations 614 extend further through the bottom of the upper main rotor mount 61 (not shown). In the present embodiment, the holes 63142 are respectively located directly above the intersection of the upper body 611 and the upper extension arms 612, and the holes 614 are respectively located at the intersection of the upper body 611 and the upper extension arms 612. Above, as shown in Figure 6a. In other embodiments, the projections 6314 can extend longer than the embodiment of FIG. 6a such that the apertures 63142 are positioned above the upper extension arms 612, respectively. There is no such thing as the upper extension arm 612. The two ends of the supporting structures 66 are respectively inserted into the holes 63142 and the through holes 614. Preferably, the holes 63142 are screw holes, and the outer sides of the support structures 66 are screwed into the holes 63142 near the top end, as shown in FIG. 6d. Thereby, the support structures 66 can provide the most stable three-point support effect, so that the stability of the upper main rotor group 60 is optimized, so that it does not sway relatively with respect to the small spindle 50, and thus the small spindle 50 and the large spindle. The upper main rotor group 60 is synchronously driven by the upper coaxial double-rotor swashplate phase mount 100 and the lower coaxial double-rotor swashplate phase mount 110 and the plurality of first links 121 and the plurality of third links 123 (see FIG. 8a). When the lower main rotor group 70 is inclined with respect to the fuselage 10 to change the flying angle of the present invention and is inclined with respect to the fuselage 10, the tilt angle of the upper rotor blade aerodynamic configuration 80 achieves zero error effect and is truly consistent; In this way, the creation can accurately maintain the flight at a preset angle and thoroughly solve the problems of the prior art.

It is worth mentioning that, since the present invention has at least three supporting structures 66, the sliding and strength of the three supporting structures 66 are sufficient to improve the problem of the prior art being susceptible to deformation, so that the stability of the upper main rotor group 60 can be maintained at a certain level. At least, the effect of "the inclination angle of the aerodynamic configuration 80 of the upper rotor blade is smaller than the prior art" is maintained; thereby, compared with the prior art, the creation still maintains a closer angle to the preset angle. The effect of the flying up is not caused by the loss of the effect of "increasing the stability of the upper main rotor group 60" due to the rotational deformation.

Please refer to FIG. 8a. FIG. 8a is a perspective enlarged view of the coaxial double-rotor mechanism of the present invention. The lower main rotor set 70 includes a lower main rotor mount 71 that is disposed on the main spindle 40 and includes a lower base 711, at least three lower extension arms 712, and at least three lower paddle clamps 713. In fact, the structure of the lower base 711 of the lower main rotor mount 71, the lower extension arm 712, and the lower paddle 713 and the like are substantially the same as the upper seat of the upper main rotor mount 61. 611. The structures of the upper extension arm 612 and the upper paddle 613 and the connecting relationship thereof are similar, and thus will not be described herein. It is worth mentioning that the lower main rotor group 70 does not include a coaxial double rotor direction control mount structure, which is different from the upper main rotor group 60.

Please refer to FIG. 3, FIG. 7a and FIG. 7b. FIG. 3 is a schematic diagram of the coaxial double-rotor turbine driven unmanned vehicle mechanism system of the present invention, and FIG. 7a is a first embodiment of the aerodynamic configuration of the upper and lower rotor blades of the present invention. In plan view, Figure 7b is a cross-sectional view of the blade body of the first embodiment of the aerodynamic configuration of the upper and lower rotor blades of the present invention. The upper rotor blade aerodynamic configuration 80 includes an upper blade body 81, an upper joint portion 82, and an upper wing tip portion 83. The lower rotor blade aerodynamic configuration 90 includes a lower blade body 91, a lower joint portion 92, and a lower wing tip portion 93.

The upper and lower blade bodies 81 and 91 are linear, and the two ends of the longitudinal direction are respectively defined as a first end 811, 911 and a second end 812, 912, and the two sides in the width direction are respectively defined as a first Sides 813, 913 and a second side 814, 914 have a top surface 815, 915 and a bottom surface 816, 916. Referring to FIG. 7b, the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 are from the first side edges 813, 913 of the upper and lower blade bodies 81, 91 to the second of the upper and lower blade bodies 81, 91. The curvature of the sides 814, 914 is greater than the top surfaces 815, 915 of the upper and lower blade bodies 81, 91 from the first side 813, 913 of the upper and lower blade bodies 81, 91 to the upper and lower blade body 81. The curved curvature of the second side edges 814, 914 of 91 causes the top and bottom surfaces 815, 915 and the bottom surfaces 816, 916 of the upper and lower blade body bodies 81, 91 to be inconsistent and asymmetrical. In other words, the arc lengths of the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 from the first side edges 813, 913 to the second side edges 814, 914 are greater than the top surfaces of the upper and lower blade body bodies 81, 91. 815, 915 are arc lengths from the first side edges 813, 913 to the second side edges 814, 914, that is, the top surfaces 815, 915 of the upper and lower blade body 81, 91 are compared to the upper and lower blade body 81. The bottom surfaces 816, 916 of 91 are also flat. More specifically, in the present embodiment, the top faces 815, 915 of the upper and lower blade bodies 81, 91 are bent upward from the first side edges 813, 913 of the upper and lower blade bodies 81, 91, and then flattened. The second sides 814, 914 of the upper and lower blade bodies 81, 91 extend; the bottom faces 816, 916 of the upper and lower blade bodies 81, 91 are from the first side of the upper and lower blade bodies 81, 91 813, 913 are first bent downward and then bent upward to the second sides 814, 914 of the upper and lower blade bodies 81, 91. Generally, the first side edges 813, 913 of the upper and lower blade bodies 81, 91 are the front side, and the second side edges 814, 914 of the upper and lower blade body 81, 91 are the rear side; the upper and lower rotor blades When the aerodynamic configurations 80, 90 are rotated, they are generally rotated in the rearward direction; whereby the airflow passes through the upper and lower rotor blade aerodynamic configurations 80, 90, the bottom surfaces 816 of the upper and lower blade bodies 81, 91, The vortex generated by 916 is sufficient for the creation of the lift to be greater than the lift generated by conventional techniques.

The upper and lower joint portions 82, 92 are provided at the first ends 811, 911 of the upper and lower blade bodies 81, 91 and are provided to the upper and lower paddles 613, 713, as shown in Figs. 7a and 5.

The upper and lower wing tips 83, 93 are disposed at the second ends 812, 912 of the upper and lower blade bodies 81, 91, extending in the same plane as the upper and lower blade bodies 81, 91, and away from the top, The lower joint portions 82, 92 and the first side edges 813, 913 of the upper and lower blade bodies 81, 91 extend in a direction such that the longitudinal directions of the upper and lower wing tips 83, 93 are different from the upper and lower blade bodies 81. The longitudinal direction of 91 has an angle Θ1 with the longitudinal direction of the upper and lower blade bodies 81 and 91. In other words, the extending directions of the upper and lower wing tips 83, 93 are different from the extending directions of the upper and lower blade bodies 81, 91. Since the first side edges 813, 913 of the upper and lower blade bodies 81, 91 are the front side, and the second side edges 814, 914 of the upper and lower blade bodies 81, 91 are the rear side, the upper and lower wing tips 83 are provided. The 93 is substantially in the form of a "swept back" extending obliquely rearward of the upper and lower blade bodies 81, 91. Thereby, the vortex line will no longer be perpendicular to the lift line when leaving the lift line, so the improvement of the induced speed along the lift line can be corrected by improving the lift line analysis method, thereby improving the upper and lower wing tips. The eddy current characteristics of 83 and 93 make the lift generated by the creation larger than the lift generated by the prior art, and at the same time, the possibility of regional vibration waves generated by the upper and lower wing tips 83, 93 at high speed rotation can be reduced. Sex to achieve the effect of reducing drag. The above effect can be achieved at an angle of 20 to 45 degrees at an angle of Θ1; especially when the angle of the angle Θ1 is 35 degrees, the above effect can be optimal. Wherein, the widths of the upper and lower wing tips 83, 93 are tapered from the second ends 812, 912 of the upper and lower blade bodies 81, 91 away from the upper and lower blade bodies 81, 91, that is, The widths of the upper and lower wing tips 83, 93 are tapered toward the rear of the upper and lower blade bodies 81, 91 to assist in enhancing the above effects.

It is worth mentioning that the asymmetric upper and lower blade bodies 81, 91 of the first embodiment cooperate with the swept upper and lower wing tips 83, 93 so that the overall structural form can be called " The first type of asymmetrical wing rotor airfoil has a swept wing tip with upper and lower rotor blade aerodynamic configurations 80, 90.

In the second embodiment, the "upper and lower wing tips 83, 93 of the first embodiment are omitted from the upper and lower blade bodies 81, 91 in the same plane, and are moved away from the upper and lower joint portions 82. And 92 extend in the direction of the first side edges 813, 913 of the upper and lower blade bodies 81, 91 such that the longitudinal directions of the upper and lower wing tips 83, 93 are different from the lengths of the upper and lower blade bodies 81, 91 The direction has an angle Θ1" with the longitudinal direction of the upper and lower blade bodies 81, 91, and the bottom faces 816, 916 of the upper and lower blade bodies 81, 91 of the first embodiment are retained from the upper and lower paddles. The first sides 813, 913 of the leaf bodies 81, 91 have curvatures that are curved toward the second sides 814, 914 of the upper and lower blade bodies 81, 91 that are greater than the top faces 815, 915 of the upper and lower blade bodies 81, 91. The curvature of the second side edges 814, 914 of the upper and lower blade bodies 81, 91 from the first side edges 813, 913 of the upper and lower blade bodies 81, 91 is such that the upper and lower blade bodies 81, 91 The technical features and functions of the top surfaces 815, 915 and the bottom surfaces 816, 916 are inconsistent with each other and are asymmetric. As for the relationship between the upper and lower wing tips 83, 93 of the second embodiment and the upper and lower blade bodies 81, 91, there is no particular limitation. For example, the upper and lower wing tips 83, 93 of the second embodiment may extend in different planes from the upper and lower blade bodies 81, 91, that is, the upper and lower wing tips 83, 93 are opposite. The lower blade body 81, 91 is vertically upward, vertically downward, inclined upward or obliquely downward. Alternatively, the upper and lower wing tips 83, 93 extend in the same plane as the upper and lower blade bodies 81, 91, and extend straight away from the direction of the upper and lower joint portions 82, 92 such that their length direction and upper The lower blade bodies 81 and 91 have the same longitudinal direction and are parallel to the longitudinal directions of the upper and lower blade bodies 81 and 91. In general, any of the embodiments of the second embodiment can collectively refer to the aerodynamic configurations 80, 90 of the upper and lower rotor blades, which are referred to as "asymmetric wing rotor airfoil, no swept wing tip".

In the third embodiment, the bottom faces 816, 916 of the upper and lower blade bodies 81, 91 of the first embodiment are omitted from the first side edges 813, 913 of the upper and lower blade bodies 81, 91, The curvature of the second side edges 814, 914 of the lower blade bodies 81, 91 is greater than the top sides 815, 915 of the upper and lower blade bodies 81, 91 from the first side 813 of the upper and lower blade bodies 81, 91. The curved curvature of the second side edges 814, 914 of the upper and lower blade bodies 81, 91 is such that the heights and undulations of the top surfaces 815, 915 and the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 are inconsistent. The technical features of the asymmetrical shape, etc., retain the "upper and lower wing tips 83, 93 of the first embodiment and the upper and lower blade bodies 81, 91 extend in the same plane, and are joined away from the upper and lower sides. The portions 82, 92 and the first side edges 813, 913 of the upper and lower blade bodies 81, 91 extend in a direction such that the longitudinal directions of the upper and lower wing tips 83, 93 are different from the upper and lower blade bodies 81, 91. The longitudinal direction has an angle of Θ1" with the longitudinal direction of the upper and lower blade bodies 81, 91 and the like. As for the relationship between the top faces 815, 915 and the bottom faces 816, 916 of the upper and lower blade bodies 81, 91 of the third embodiment, there is no particular limitation. For example, the top surfaces 815, 915 and the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 of the third embodiment are upward from the first side edges 813, 913 of the upper and lower blade bodies 81, 91, The second side edges 814, 914 of the lower blade bodies 81, 91 have the same curvature, and the top faces 815, 915 of the upper and lower blade bodies 81, 91 are from the first side of the upper and lower blade bodies 81, 91. 813, 913 are first bent upwards and then bent downward to the second sides 814, 914 of the upper and lower blade bodies 81, 91, and the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 are from the upper and lower blade bodies The first side edges 813, 913 of 81, 91 are first bent downward and then bent upward to the second side edges 814, 914 of the upper and lower blade bodies 81, 91 such that the top surfaces of the upper and lower blade bodies 81, 91 The heights and undulations of the 815, 915 and the bottom surfaces 816, 916 are the same. The third embodiment of this embodiment can be called the "symmetrical wing rotor type, with the swept wing tip" upper and lower rotor blade aerodynamic configuration. 80, 90. Alternatively, the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 extend from the first side 813, 913 of the upper and lower blade bodies 81, 91 to the second side 814 of the upper and lower blade bodies 81, 91. The curvature of the curved portion 914 is smaller than the top surfaces 815, 915 of the upper and lower blade bodies 81, 91 from the first side edges 813, 913 of the upper and lower blade bodies 81, 91 to the upper and lower blade bodies 81, 91. The curved curvature of the second side edges 814, 914 is such that the top and bottom surfaces 815, 915 and the bottom surfaces 816, 916 of the upper and lower blade body bodies 81, 91 are inconsistent with each other and are asymmetric, and the third aspect of the embodiment The embodiment may be referred to as a "second asymmetric airfoil with a swept wing tip" for the upper and lower rotor blade aerodynamic configurations 80, 90.

Referring to FIG. 7c, Table 1 and Table 2, FIG. 7c is a comparison diagram of the lift of the coaxial double-rotor turbine driven unmanned vehicle mechanism system of the prior art, the first embodiment and the second embodiment of the present invention. The lift comparison table of the coaxial double-rotor turbine driven unmanned vehicle mechanism system of the first embodiment and the second embodiment of the present invention at a pitch angle of 12 degrees and a rotational speed of 1000 RPM, 1200 RPM and 1400 RPM, Table 2 Comparison of the lift ratios of the coaxial double-rotor turbine-driven unmanned vehicle system of the prior art, the first embodiment and the second embodiment of the present invention at a pitch angle of 12 degrees and rotation speeds of 1000 RPM, 1200 RPM and 1400 RPM. form. Where N is Newton and the lift coefficient is CT=lift/ρπR2U2tip.

Table I         <TABLE border="1" borderColor="#000000" width="85%"><TBODY><tr><td> rotor name</td><td> conventional technology</td><td> second Embodiment </td><td> First Embodiment </td></tr><tr><td> Pitch Angle </td><td> 12° </td></tr><tr>< Td> Speed (RPM) </td><td> 1000 </td><td> 1200 </td><td> 1400 </td><td> 1000 </td><td> 1200 </td> <td> 1400 </td><td> 1000 </td><td> 1200 </td><td> 1400 </td></tr><tr><td> Lift (N) </td> <td> 284.3 </td><td> 372.2 </td><td> 467 </td><td> 320.91 </td><td> 421.45 </td><td> 536.87 </td><td > 362.81 </td><td> 461.57 </td><td> 558.37 </td></tr><tr height="0"><td></td><td></td><td ></td><td></td><td></td><td></td><td></td><td></td><td></td><td> </td><td></td><td></td></tr></TBODY></TABLE>

Table II         <TABLE border="1" borderColor="#000000" width="85%"><TBODY><tr><td> Rotor comparison combination</td><td> First embodiment / Second embodiment </ Td><td> First Embodiment / Conventional Technology</td><td> Second Embodiment / Conventional Technology</td></tr><tr><td> Pitch Angle 12 ̊&amp;Speed 1000RPM Difference in lift rate</td><td> 1.131 times</td><td> 1.276 times</td><td> 1.128 times</td></tr><tr><td> pitch angle 12 ̊ &amp; difference in lift rate at 1200 RPM</td><td> 1.095 times</td><td> 1.240 times</td><td> 1.132 times</td></tr><tr><td> Pitch angle 12 ̊ &amp; speed 1400RPM lift rate difference</td><td> 1.040 times</td><td> 1.195 times</td><td> 1.149 times</td></tr></TBODY ></TABLE>

According to FIG. 7c, Table 1 and Table 2, under the conditions of a pitch angle of 12 degrees and a rotation speed of 1000 RPM, the lift generated by the first embodiment is about 1.131 times the lift generated by the second embodiment, the first implementation The lift generated by the example is about 1.276 times the lift generated by the prior art, and the lift generated by the second embodiment is about 1.128 times the lift generated by the prior art; the pitch angle is 12 degrees and the rotational speed is 1200 RPM, etc. Under the condition, the lift generated by the first embodiment is about 1.095 times of the lift generated by the second embodiment, and the lift generated by the first embodiment is about 1.240 times of the lift generated by the prior art. The second implementation The lift generated by the example is about 1.132 times of the lift generated by the prior art; under the conditions of the pitch angle of 12 degrees and the rotational speed of 1400 RPM, the lift generated by the first embodiment is about the same as that produced by the second embodiment. With a lift of 1.040 times, the lift generated in the first embodiment is about 1.195 times the lift generated by the prior art, and the lift generated in the second embodiment is about 1.149 times the lift generated by the prior art. In general, under the conditions of a pitch angle of 12 degrees and a rotational speed of 1000 RPM, 1200 RPM, and 1400 RPM, the lift generated by the first embodiment is significantly greater than that of the second embodiment and the prior art, and the second embodiment The lift generated by the example is greater than the lift generated by conventional techniques.

It is worth mentioning that under the same pitch angle condition, the greater the rotational speed, the closer the lift of the second embodiment is to the lift of the first embodiment.

Please refer to FIG. 3 and FIG. 8a to FIG. 8e. FIG. 3 is a schematic diagram of the coaxial double-rotor turbine driven unmanned vehicle mechanism system of the present invention, and FIG. 8a is a perspective view of the structure of the upper coaxial double-rotor yaw phase control fixed seat. 8b is a perspective view of the upper inner ring phase fixing seat set of the present invention, FIG. 8c is an exploded view of the upper inner ring phase fixing seat set of the present invention, and FIG. 8d is a perspective view of the upper outer ring phase fixing seat set of the present invention. 8e is an exploded view of the upper outer ring phase fixing block set of the creation. The upper coaxial double-rotor swashplate phase control mount structure 100 includes an upper inner ring set 101, an upper outer ring set 102, an upper inner ring phase mount set 103, and an upper outer ring phase mount set 104.

The upper inner ring set 101 is sleeved on the small spindle 50 and has an upper inner globe 1011. Specifically, the upper inner ring group 101 includes an upper ball type bearing 1012, an upper ball type collar 1013 and an upper inner ring base 1014. The small main shaft 50 is disposed through a shaft hole of the upper ball type bearing 1012. The collar 1013 is annularly disposed on the outer side of the upper ball bearing 1012, and the upper inner ring base 1014 is disposed on the outer side of the upper ball type collar 1013 and the outer peripheral side of the upper portion protrudes from the upper inner ring head 1011, as shown in FIG. 8a. Figure 8b shows.

The upper outer ring set 102 is looped on the upper inner ring set 101 and has an upper outer globe head 1021. More specifically, the upper outer ring set 102 includes an upper ring type bearing 1022 and an upper outer ring base 1023. The upper ring type bearing 1022 is disposed on the outer peripheral side of the lower portion of the upper inner ring base 1014, and the upper outer ring base 1023. The ring is disposed on the outer side of the upper ring type bearing 1022 and protrudes from the outer peripheral side of the plurality of upper outer ring heads 1021 as shown in FIGS. 8a and 8d.

The upper inner ring phase fixing base set 103 includes an upper inner ring phase fixing base body 1031, an upper inner ring connecting piece 1032, an upper inner ring connecting handle 1033 and a plurality of upper inner ring fixing members 1034, as shown in FIG. 8a and FIG. 8b. Figure 8c shows. The upper inner ring phase fixing base body 1031 is sleeved on the small main shaft 50 and located above the upper inner ring group 101. The upper inner ring connecting member 1032 has a first end and a second end. At least one upper inner ring fixing member 1034 is screwed on the first end of the upper inner ring connecting member 1032 and the upper inner ring phase fixing base body 1031. The first end of the inner ring link 1032 is fixed to the upper inner ring phase mount body 1031 by the upper inner ring mount 1034. The upper inner ring shank 1033 has a first end and a second end, and at least one upper inner ring fixing member 1034 is screwed on the first end of the upper inner ring shank 1033 and the second end of the upper inner ring connecting member 1032. The first end of the upper inner ring shank 1033 is secured to the second end of the upper inner ring link 1032 by the upper inner ring retainer 1034. The second end of the upper inner ring handle 1033 is disposed on one of the upper inner globes 1011.

In a preferred embodiment, the upper inner ring link 1032 includes a first upper inner ring link 1035 and a second upper inner ring link 1036. The first upper inner ring link 1035 has a first end and a second end, and the second upper inner ring link 1036 has a first end and a second end. The at least one upper inner ring fixing member 1034 is screwed to the first end of the first upper inner ring link 1035 and the upper inner ring phase fixing seat body 1031 such that the first end of the first upper inner ring link 1035 is received by the upper inner ring The ring fixing member 1034 is fixed to the upper inner ring phase fixing base body 1031. At least one upper inner ring fixing member 1034 is screwed to the first end of the second upper inner ring link 1036 and the second end of the first upper inner ring link 1035 such that the first end of the second upper inner ring link 1036 The upper inner ring fixing member 1034 is fixed to the second end of the first upper inner ring link 1035. At least one upper inner ring fixing member 1034 is screwed on the first end of the upper inner ring shank 1033 and the second end of the second upper inner ring link 1036 such that the first end of the upper inner ring shank 1033 is received by the upper end The ring fixture 1034 is secured to the second end of the second upper inner ring link 1036.

More specifically, the first upper inner ring link 1035 includes a connecting arm 10351, two extending arms 10352 and a handle 10353. The two upper extending arms 10352 of the first upper inner ring link 1035 are connected from the first upper inner ring link. The two ends of the connecting arm 10351 of the 1035 extend and are defined as the first ends of the first upper inner ring links 1035 and respectively define a through hole 10354, and the through holes 10354 of the two extending arms 10352 of the first upper inner ring link 1035 are respectively laterally Through the two sides of the two extension arms 10352 of the first upper inner ring link 1035, the shank 10353 of the first upper inner ring link 1035 is away from the center of the connecting arm 10351 of the first upper inner ring link 1035. The two extension arms 10352 of the inner ring link 1035 extend in a direction and are defined as a second end of the first upper inner ring link 1035 and define a screw hole 10355 extending through the two sides thereof; the upper inner ring phase mount body 1031 is located a connecting hole 10351 of the first upper inner ring link 1035 and a space surrounded by the two extending arms 10352 and opening a screw hole 10311 extending through the two sides thereof, wherein the upper inner ring fixing members 1034 are transversely passed through the first upper portion The perforations 10354 of the two extension arms 10352 of the inner ring link 1035 are respectively from the upper inner Two ends of the screw holes 10311 of the phase fixing base body 1031 are screwed into the screw holes 10311, so that the two extension arms 10352 of the first upper inner ring link 1035 are respectively fixed by the upper inner ring fixing members 1034. The two sides of the ring phase fixing base body 1031. The second upper inner ring link 1036 includes a connecting arm 10361 and two extending arms 10362. The two extending arms 10362 of the second upper inner ring link 1036 extend from the two ends of the connecting arm 10361 of the second upper inner ring link 1036 and The first end of the second upper inner ring link 1036 is defined as a perforation 10363, and the perforations 10363 of the two extension arms 10362 of the second upper inner ring link 1036 extend transversely through the second upper inner ring link 1036, respectively. Two sides of the extension arm 10362, the handle 10353 of the first upper inner ring link 1035 is located in the space surrounded by the connecting arm 10361 and the second extension arm 10362 of the second upper inner ring link 1036, and the second upper inner ring The connecting arm 10361 of the connecting rod 1036 is defined as a second end of the second upper inner ring link 1036 and defines a through hole 10364. The through hole 10364 of the connecting arm 10361 of the second upper inner ring link 1036 extends longitudinally through the second upper inner ring. The top and bottom of the connecting arm 10361 of the connecting rod 1036; preferably, the through hole 10364 of the connecting arm 10361 of the second upper inner ring link 1036 is located at the center of the connecting arm 10361 of the second upper inner ring link 1036; The inner ring fixtures 1034 extend transversely through the two extension arms 1036 of the second upper inner ring link 1036, respectively. The through hole 10363 of the second upper inner ring link 1035 is screwed into the screw hole 10355 from the two ends of the screw hole 10355 of the handle portion 10353 of the first upper inner ring link 1035, so that the second extension arm 10362 of the second upper inner ring link 1036 is provided. The two upper inner ring fixing members 1034 are respectively fixed to the two sides of the handle portion 10353 of the first upper inner ring link 1035; the first end of the upper inner ring connecting handle 1033 defines a screw hole 10331, wherein an upper inner ring is fixed The member 1034 extends longitudinally through the through hole 10364 of the connecting arm 10361 of the second upper inner ring link 1036 and is screwed to the screw hole 10331 of the first end of the upper inner ring connecting handle 1033 such that the first end of the upper inner ring is connected to the handle 1033. The upper inner ring fixing member 1034 is fixed to the bottom of the connecting arm 10361 of the second upper inner ring link 1036.

The upper outer ring phase fixing base set 104 includes an upper outer ring phase fixing base body 1041, an upper outer ring connecting piece 1042, an upper outer ring connecting handle 1043 and a plurality of upper outer ring fixing members 1044, as shown in FIG. 8a and FIG. 8d. Figure 8e shows. The upper outer ring phase fixing base body 1041 is sleeved on the small main shaft 50 and located below the upper outer ring group 102. The upper outer ring connecting member 1042 has a first end and a second end. At least one upper outer ring fixing member 1044 is screwed on the first end of the upper outer ring connecting member 1042 and the upper outer ring phase fixing base body 1041. The first end of the outer ring link 1042 is fixed to the upper outer ring phase mount body 1041 by the upper outer ring fixing member 1044. The upper outer ring connecting ring 1043 has a first end and a second end, and at least one upper outer ring fixing member 1044 is screwed on the first end of the upper outer ring connecting handle 1043 and the second end of the upper outer ring connecting member 1042. The first end of the upper outer ring adapter 1043 is secured to the second end of the upper outer ring link 1042 by the upper outer ring fastener 1044. The second end of the upper outer ring handle 1043 is disposed on one of the upper outer globes 1021.

In a preferred embodiment, the upper outer ring link 1042 includes a first upper outer ring link 1045 and a second upper outer ring link 1046. The first upper outer ring link 1045 has a first end and a second end, and the second upper outer ring link 1046 has a first end and a second end. At least one upper outer ring fixing member 1044 is screwed to the first end of the first upper outer ring link 1045 and the upper outer ring phase fixing seat body 1041 such that the first end of the first upper outer ring link 1045 is received by the upper outer The ring fixing member 1044 is fixed to the upper outer ring phase fixing base body 1041. At least one upper outer ring fixing member 1044 is screwed to the first end of the second upper outer ring link 1046 and the second end of the first upper outer ring link 1045 such that the first end of the second upper outer ring link 1046 The upper outer ring fixing member 1044 is fixed to the second end of the first upper outer ring link 1045. At least one upper outer ring fixing member 1044 is screwed to the first end of the upper outer ring shank 1043 and the second end of the second upper outer ring link 1046, such that the first end of the upper outer ring shank 1043 is externally The ring fixture 1044 is secured to the second end of the second upper outer ring link 1046.

More specifically, the first upper outer ring link 1045 includes a connecting arm 10451, two extending arms 10452 and a handle 10453. The two upper extending arms 10452 of the first upper outer ring link 1045 are connected from the first upper outer ring link. The two ends of the connecting arm 10451 of 1045 extend and are defined as first ends of the first upper outer ring link 1045 and respectively define a through hole 10454, and the through holes 10454 of the two extending arms 10452 of the first upper outer ring link 1045 are respectively laterally Through the two sides of the two extension arms 10452 of the first upper outer ring link 1045, the shank 10453 of the first upper outer ring link 1045 is away from the center of the connecting arm 10451 of the first upper outer ring link 1045. The second extension arm 10452 of the outer ring link 1045 extends in a direction and is defined as a second end of the first upper outer ring link 1045 and defines a screw hole 10455 on each of the two sides; the upper outer ring phase mount body 1041 is located at the second end a connecting arm 10451 of the upper outer ring link 1045 and a space surrounded by the two extending arms 10452 and opening a second screw hole 10411, wherein the two upper outer ring fixing members 1044 are transversely passed through the first upper outer ring link 1045, respectively. The perforations 10454 of the extension arms 10452 are respectively screwed to the upper outer ring and fixed in phase 10411 two screw holes 1041 in the body, such that the first upper outer link two extending arms 1045 are two of the 10452 on the outer ring fixing member 1044 is fixed to the outer sides of the holder body 1041 phase. The second upper outer ring link 1046 includes a connecting arm 10461 and two extending arms 10462. The two extending arms 10462 of the second upper outer ring link 1046 extend from the two ends of the connecting arm 10461 of the second upper outer ring link 1046 and The first end of the second upper outer ring link 1046 is defined as a perforation 10463, and the perforations 10463 of the two extension arms 10462 of the second upper outer ring link 1046 extend transversely through the second upper outer ring link 1046, respectively. Two sides of the extension arm 10462, the handle 10453 of the first upper outer ring link 1045 is located in the space surrounded by the connecting arm 10461 and the second extension arm 10462 of the second upper outer ring link 1046, and the second upper outer ring The connecting arm 10461 of the connecting rod 1046 is defined as the second end of the second upper outer ring link 1046 and defines a through hole 10464. The through hole 10464 of the connecting arm 10461 of the second upper outer ring link 1046 extends longitudinally through the second upper outer ring. The top and bottom of the connecting arm 10461 of the connecting rod 1046; preferably, the through hole 10464 of the connecting arm 10461 of the second upper outer ring link 1046 is located at the center of the connecting arm 10461 of the second upper outer ring link 1046; The outer ring fixing members 1044 extend transversely through the two extension arms 1046 of the second upper outer ring link 1046, respectively. The through holes 10463 of the second upper outer ring link 1045 are respectively screwed into the two screw holes 10455 of the first upper outer ring link 1045, so that the two extension arms 10462 of the second upper outer ring link 1046 are respectively fixed by the two upper outer rings. The first end of the upper outer ring link 1043 is fixed to the two sides of the shank 10453 of the first upper outer ring link 1045; the first end of the upper outer ring shank 1043 defines a screw hole 10431, wherein an upper outer ring fixing member 1044 longitudinally passes through the second upper portion The through hole 10464 of the connecting arm 10461 of the outer ring link 1046 is screwed to the screw hole 1031 of the first end of the upper outer ring connecting ring 1043, so that the first end of the upper outer ring connecting handle 1043 is the upper outer ring fixing member 1044. Fixed to the top of the connecting arm 10461 of the second upper outer ring link 1046.

Please refer to FIG. 9a to FIG. 9f. FIG. 9a is a perspective view of another perspective view of the coaxial double-rotor mechanism of the present invention. FIG. 9b is another perspective view of the upper inner ring phase fixing seat set of the present invention, and FIG. 9c is a creation view. FIG. 9d is an exploded view of the lower inner ring phase fixing seat set of the limited rotation angle of the present invention, and FIG. 9e is an exploded lower inner phase phase of the created rotation angle. A cross-sectional view of the fixed seat set, FIG. 9f is a cross-sectional view of the lower inner ring link of the present invention rotated inwardly to a second position, and FIG. 9g is an outer ring link of the present invention rotated outward to the extreme limit and the lower inner ring link A perspective view that is rotated inward to the second position. The lower coaxial double-rotor swashplate phase control mount structure 110 includes a lower inner ring set 111, a lower outer ring set 112, a lower inner ring phase fixed seat set 113 that limits the rotation angle, and a lower outer ring phase fixed block set. The lower inner ring phase fixing seat set 113 for limiting the rotation angle is disposed between the large main shaft 40 and the lower inner ring group 111 and includes a lower inner ring phase fixing seat body 114, a lower inner ring connecting piece 115, a lower inner ring connecting piece 116, and A limiting device 117. Basically, the lower coaxial double-rotor swashplate phase control mount structure 110 and the upper coaxial double-rotor swashplate phase control mount structure 100 have substantially the same main structure, and the difference is that; the first coaxial double-rotor swashplate The phase control mount structure 100 is disposed on the small spindle 50 and is connected to the upper main rotor group 60 by a plurality of first links 121; second, the upper and lower coaxial double-rotor swash plate phase control mount structures 100, 110 are The plurality of second connecting rods 122 are connected to each other; third, the lower coaxial double-rotor swash plate phase control fixed seat structure 110 is disposed on the large main shaft 40 and is connected to the lower main rotor group 70 by the plurality of third connecting rods 123 and by a plurality The fourth link 124 is in contact with the fuselage 10; fourth, the lower inner ring phase fixed seat set 113 of the lower coaxial double-rotor swashplate phase control mount structure 110 includes a limiting device 117.

Thereby, the present invention enhances the tightness of the combination of the upper inner ring phase fixing base body 1031, the upper inner ring connecting member 1032 and the upper inner ring connecting handle 1033 by means of the upper inner ring fixing member 1034. The upper outer ring phase fixing member 1044 is screwed to improve the tightness of the upper outer ring phase fixing base body 1041, the upper outer ring connecting member 1042 and the upper outer ring connecting handle 1043, so that the upper inner ring phase fixing seat group The combination tightness of the overall structure of the upper outer ring phase fixing base set 104 is improved; and the lower inner ring phase fixing seat body 114 and the lower inner ring connecting piece are screwed up by the lower inner ring fixing member. 115 and the lower inner ring handle 116 are combined tightly, and the lower outer ring phase fixing seat body, the lower outer ring connecting piece and the lower outer ring connecting handle are screwed by the lower outer ring fixing member. The tightness of the combination makes the tightness of the combination of the lower inner ring phase fixing block group 113 and the lower outer ring phase fixing block group which limit the rotation angle to be improved. Thereby, when the upper and lower main rotor groups 60, 70 are respectively driven to rotate in opposite directions on the same axis by the coaxial small and large main shafts 50, 40, the coaxial double-rotor mechanism 30 generates vibration as a whole. When the upper and lower inner ring connecting members are not loosened from the upper and lower inner ring phase fixing seat bodies, the upper and lower inner ring connecting handles are not loosened from the upper and lower inner ring connecting members at all, up and down. The outer ring connecting piece will not be loosened from the upper and lower outer ring phase fixing seat body, and the upper and lower outer ring connecting handles will not be loosened from the upper and lower outer ring connecting members, thereby maintaining the upper and lower coaxial doubles. The rotor swashplate phase control mount structure 100, 110 changes the function of the flight angle of the present creation.

It is worth mentioning that when the materials of the upper inner ring fixing member 32 and the upper outer ring fixing members 42 are all metal, the upper inner ring phase fixing seat body 1031, the upper inner ring connecting member 1032 and the upper inner ring. The adapter 1033 can be more tightly coupled by the upper inner ring fixing member 1034 in a screw-fast manner, and the upper outer ring phase fixing base body 1041, the upper outer ring connecting member 1042 and the upper outer ring connecting handle 1043 are also The combination of the upper outer ring fixing member 1044 and the upper outer ring phase fixing base group 104 can be further improved by the screwing of the upper outer ring fixing member 1044, and the structural strength and structural strength of the upper inner ring phase fixing base group 103 and the upper outer ring phase fixing base group 104 can be further improved; Moreover, when the materials of the lower inner ring fixing member and the lower outer ring fixing members are all metal, the lower inner ring phase fixing seat body 114, the lower inner ring connecting member 115 and the lower inner ring connecting handle 116 can The lower inner ring fixing member is more tightly coupled by screwing, and the lower outer ring phase fixing seat body, the lower outer ring connecting member and the lower outer ring connecting handle can also be screwed by the lower outer ring fixing member. The solid way is combined more closely and more Binding tightness and overall configuration of the outer group of fixed base phase angle of the high-limit rotational phase of the inner holder groups and structural strength. Thereby, the upper and lower coaxial double-rotor swash plate phase control fixing seat structures 100 and 110 of the present invention are less prone to wear, more durable and longer lasting.

The difference between the lower inner ring phase fixing block group 113 and the upper inner ring phase fixing block group 103 for limiting the rotation angle will be further described below.

The lower inner ring phase mount body 114 is sleeved on the large spindle 40. The lower inner ring link 115 includes a first lower inner ring link 1151 and a second lower inner ring link 1152. The first lower inner ring link 1151 of the lower inner ring link 115 is pivotally fixed to the lower inner ring. The seat body 114 and the second lower inner ring link 1152 of the lower inner ring link 115 are pivotally disposed on the first lower inner ring link 1151 of the lower inner ring link 115. The lower inner ring shank 116 is disposed between the second lower inner ring link 1152 of the lower inner ring link 115 and the lower inner ring set 111. At least a portion of the retaining device 117 is located between the inner side of the lower inner ring link 115 and the outer side of the major spindle 40. Wherein, when the lower inner ring link 115 is rotated outward to a first position, the lower inner ring link 115 is away from the large spindle 40, as shown in FIGS. 9c and 9e; at this time, the lower inner ring link 115 is rotated outward to The most extreme. When the lower inner ring link 115 is rotated inwardly to a second position, the limiting device 117 limits the angle at which the first lower inner ring link 1151 and the second lower inner ring link 1152 of the lower inner ring link 115 rotate inwardly. So that the inner side of the lower inner ring link 115 is spaced apart from the outer side of the large spindle 40, as shown in Figures 9f and 9g; at this time, the lower inner ring link 115 is rotated inward to the extreme limit, while the inner ring The link 1032 is rotated outwardly to the extreme limit whereby the combination of the lower inner ring set 111 and the lower outer ring set 112 relative to the major axis 40 is maintained at a level equal to the combination of the upper inner ring set 101 and the upper outer ring set 102. The state of the skew angle of the small spindle 50 precisely controls the vertical deflection of the upper main rotor group 60 and the lower main rotor group 70 relative to the fuselage, so that the creation can stably change the flight angle without losing control.

In a preferred embodiment, the first lower inner ring link 1151 of the lower inner ring link 115 defines a through hole 11511. The limiting device 117 is disposed on the through hole 11511 and one end thereof extends beyond the through hole 11511 to protrude from the lower side. The inside of the first lower inner ring link 1151 of the ring link 115 is as shown in Figs. 9c and 9e. When the lower inner ring link 115 is rotated inwardly to the second position, the portion of the limiting device 117 protruding from the inner side of the first lower inner ring link 1151 of the lower inner ring link 115 abuts against the outer side of the large spindle 40, such as Figure 9f and Figure 9g show. Preferably, the first lower inner ring link 1151 of the lower inner ring link 115 has a first end 11512 and a second end 11513, and the second lower inner ring link 1152 of the lower inner ring link 115 has a first The first end 11512 and the second end 11522, the first end 11512 of the lower inner ring link 1151 of the lower inner ring link 115 is pivoted to the lower inner ring phase mount body 114, and the lower inner ring link 115 is The second end 11513 of the inner ring link 1151 is pivotally disposed at the first end 11521 of the second lower inner ring link 1152 of the lower inner ring link 115, and the lower inner ring handle 116 is disposed at the lower inner ring link 115. The second end 11522 of the second lower inner ring link 1152, the through hole 11511 is located between the first end 11512 and the second end 11513 of the first lower inner ring link 1151 of the lower inner ring link 115 and near the lower inner ring The first end 11512 of the first lower inner ring link 1151 of the link 115 is as shown in Figures 9d and 9e.

In a preferred embodiment, the stop means 117 can be adjusted to the extent that it protrudes inside the first lower inner ring link 1151 of the lower inner ring link 115. Therefore, the user can adjust the angle of the angle Θ3 between the first lower inner ring link 1151 and the second lower inner ring link 1152 when the inner ring link 115 is rotated inward to the second position according to the demand. Preferably, the through hole 11511 of the first lower inner ring link 1151 of the lower inner ring link 115 has an internal thread, and the limiting device 117 includes a bolt 1171 and a nut 1172; the bolt 1171 has a screw 11711 and a head. 11711; the screw 11711 of the bolt 1171 has an external thread, is screwed to the through hole 11511, and extends near the end of the large main shaft 40 to the outside of the through hole 11511 and protrudes from the first lower inner ring link 1151 of the lower inner ring link 115. The inner side; the head portion 11712 of the bolt 1171 is disposed at one end of the screw 11711 away from the large main shaft 40, and the nut 1172 is screwed to one end of the screw 11711 of the bolt 1171 near the large main shaft 40. Thereby, the user can directly adjust the extent to which the bolt protrudes from the inner side of the first lower inner ring link 1151 of the lower inner ring link 115, or by adjusting the first lower inner portion of the nut 1172 and the lower inner ring link 115. The distance of the inner side of the ring link 1151 controls the extent to which the stopper 117 protrudes from the inner side of the first lower inner ring link 1151 of the lower inner ring link 115. In other embodiments, the nut 1172 may also be omitted such that the limiting device 117 includes only the bolt 1171. In other embodiments, the limiting device 117 can also be a latch.

In another preferred embodiment, the limiting device 117 is integrally formed on the inner side of the first lower inner ring link 1151 of the lower inner ring link 115, so that the limiting device 117 protrudes from the lower inner ring link 115. The extent of the inner side of the inner ring link 1151 remains fixed (i.e., permanent, non-adjustable) such that when the lower inner ring link 115 is rotated inwardly to the second position, the first inner ring link 115 is first The angle of the angle Θ3 between the lower inner ring link 1151 and the second lower inner ring link 1152 is kept constant, which ensures that the limiting device 117 is not adjusted to the wrong degree of protrusion (for example: too prominent, too short, completely reduced) The indentation is not protruded or even completely removed. The avoidance of the combination of the lower inner ring set 111 and the lower outer ring set 112 relative to the large main axis 40 is opposite to the combination of the upper inner ring set 101 and the upper outer ring set 102. The small spindle 50 is inconsistent. Moreover, the limiting device 117 of this embodiment has the advantages of being less prone to wear and excellent durability.

In other embodiments, the limiting device 117 can also be disposed on the large main shaft 40 and at least a portion is located between the inner side of the lower inner ring connecting member 115 and the outer side of the large main shaft 40, which can also be achieved by the above preferred embodiment. efficacy.

It is worth mentioning that the angle of the angle Θ 2 between the first lower inner ring link 1151 and the second lower inner ring link 1152 of the lower inner ring link 115 when the inner ring link 115 is rotated inward to the first position Less than or equal to 110°, as shown in FIGS. 9c and 9e; when the lower inner ring link 115 is rotated inward to the second position, the first lower inner ring link 1151 and the second lower inner portion of the lower inner ring link 115 The angle 夹3 of the ring link 1152 is less than or equal to 170°; within the above range of angles (that is, within the range of angles Θ2 and Θ3 from 110° to 170°), the creation can more reliably The combination of the inner ring set 111 and the lower outer ring set 112 with respect to the large main axis 40 is maintained at a state equal to the skew angle of the combination of the upper inner ring set 101 and the upper outer ring set 102 relative to the small main axis 50, more precisely The upper main rotor group 60 and the lower main rotor group 70 are controlled to be synchronously deflected relative to the body, so that the creation can change the flight angle more stably without losing control.

In summary, the transmission output structure 21 of the turbine engine 20 of the coaxial double-rotor turbine driven unmanned vehicle mechanism system of the present invention is more convenient and quicker in processing, such as replacement, disassembly and assembly, and is advantageous for processing and manufacturing, saving replacement and maintenance time; The upper main rotor group 60 of the coaxial double-rotor mechanism 30 of the coaxial double-rotor turbine-driven unmanned vehicle mechanism system of the present invention has good sliding stability, and the small spindle 50 of the coaxial double-rotor mechanism 30 is less swaying; The twin-rotor turbine-driven unmanned vehicle mechanism system has a good effect of lifting and lowering the drag generated by the aerodynamic configuration 80, 90 of the upper and lower rotor blades of the coaxial double-rotor mechanism 30; the coaxial double-rotor turbine drive unmanned vehicle mechanism system of the present invention The upper and lower coaxial double-rotor swashplate phase control mount structures 100, 110 capable of maintaining the coaxial double-rotor mechanism 30 can change the function of the present flight angle and accurately control the upper and lower main rotor groups 60 of the coaxial double-rotor mechanism 30. 70 is synchronized with the body 10 to deflect, so that the creation can stably change the flight angle. In this way, the performance of this creation has evolved in all aspects of flight capability, safety, stability, manufacturing and disassembly.

The above description is only a preferred embodiment for explaining the present creation, and is not intended to impose any form of restriction on the creation, so that any modification or change related to the creation under the same creative spirit is provided. , should still be included in the scope of this creative intent.

A‧‧‧Aerodynamic configuration of upper and lower rotor blades

A1‧‧‧blade body

A13‧‧‧ first side

A14‧‧‧ second side

A15‧‧‧ top surface

A16‧‧‧ bottom

A2‧‧‧ Joint Department

A3‧‧‧ wing tip

10‧‧‧ body

20‧‧‧ Turbine engine

21‧‧‧Transmission output structure

22‧‧‧ Turbine engine

221‧‧‧ Engine body

222‧‧‧Turbo drive shaft

223‧‧‧Fixed ring

2231‧‧‧Fixed screw holes

224‧‧‧Stub

23‧‧‧Transfer seat

231‧‧‧Adapter ring

2311‧‧‧Transfer screw hole

232‧‧‧Transfer tube

2321‧‧‧Output screw hole

233‧‧‧Axis hole

24‧‧‧Replacement screw

25‧‧‧ Output gear

251‧‧‧ Gear tube

2511‧‧‧Gear screw hole

252‧‧‧Axis hole

253‧‧‧ Output gear teeth

26‧‧‧ Gear Screws

27‧‧‧Transmission gear

271‧‧‧ drive gear teeth

30‧‧‧Coaxial double-rotor mechanism

40‧‧‧large spindle

50‧‧‧Small spindle

60‧‧‧Upper main rotor group

61‧‧‧Upper main rotor mount

611‧‧‧The upper body

6111‧‧‧Upper body shaft hole

6112‧‧‧ axis

612‧‧‧Upper extension arm

6121‧‧‧ axis

613‧‧‧Upper paddle

614‧‧‧Perforation

62‧‧‧Coaxial double-rotor direction control fixed seat structure

63‧‧‧Ontology

631‧‧‧Base

6311‧‧‧cantilever

6312‧‧‧Base shaft hole

6313‧‧‧ axis

6314‧‧‧Protruding

63141‧‧‧ axis

63142‧‧‧ Hole

632‧‧‧ squat

64‧‧‧ shaft

65‧‧‧ Connecting rod

66‧‧‧Support structure

70‧‧‧The main rotor group

71‧‧‧Lower main rotor mount

71 1‧‧‧ lower body

712‧‧‧lower extension arm

713‧‧‧ lower paddle

80‧‧‧Aerodynamic configuration of upper rotor blades

81‧‧‧Upper blade body

811‧‧‧ first end

812‧‧‧ second end

813‧‧‧ first side

814‧‧‧ second side

815‧‧‧ top surface

816‧‧‧ bottom

82‧‧‧Upper joint

83‧‧‧Upper wing tip

90‧‧‧Lower rotor blade aerodynamic configuration

91‧‧‧ Lower blade body

911‧‧‧ first end

912‧‧‧ second end

913‧‧‧ first side

914‧‧‧ second side

915‧‧‧ top surface

916‧‧‧ bottom

92‧‧‧Under the junction

93‧‧‧ Lower wing tip

100‧‧‧Upper coaxial double-rotor swashplate phase control mount structure

101‧‧‧Upper Ring Group

1011‧‧‧上上环球头

1012‧‧‧Upper ball bearings

1013‧‧‧Upper shaft collar

1014‧‧‧Upper inner base

102‧‧‧Upper Ring Group

1021‧‧‧Shangwai Global Head

1022‧‧‧Upper ring bearing

1023‧‧‧Upper outer ring base

103‧‧‧Upper inner ring phase mount

1031‧‧‧Upper inner ring phase mount body

10311‧‧‧ screw hole

1032‧‧‧Upper inner ring joint

1033‧‧‧Upper inner ring handle

10331‧‧‧ screw hole

1034‧‧‧Upper inner ring fasteners

1035‧‧‧First upper inner ring link

10351‧‧‧Connecting arm

10352‧‧‧Extension arm

10353‧‧‧ handle

10354‧‧‧Perforation

10355‧‧‧ screw hole

1036‧‧‧Second upper inner ring link

10361‧‧‧Connecting arm

10362‧‧‧Extension arm

10363‧‧‧Perforation

10364‧‧‧Perforation

104‧‧‧Upper outer ring phase mount

1041‧‧‧Upper outer ring phase mount body

10411‧‧‧ screw hole

1042‧‧‧Upper outer ring joint

1043‧‧‧Upper outer ring handle

10431‧‧‧ screw hole

1044‧‧‧Upper outer ring fasteners

1045‧‧‧First upper outer ring link

10451‧‧‧Connecting arm

10452‧‧‧Extension arm

10453‧‧‧Handle

10454‧‧‧Perforation

10455‧‧‧ screw hole

1046‧‧‧Second upper outer ring link

10461‧‧‧Connecting arm

10462‧‧‧Extension arm

10463‧‧‧Perforation

10464‧‧‧Perforation

110‧‧‧Under coaxial double-rotor swashplate phase control fixed seat structure

111‧‧‧ Lower Inner Ring Group

112‧‧‧ Lower outer ring group

113‧‧‧ Lower inner ring phase mount block with limited rotation angle

114‧‧‧ Lower inner ring phase mount body

115‧‧‧ Lower inner ring joint

1151‧‧‧First lower inner ring link

11511‧‧‧Perforation

11512‧‧‧ first end

11513‧‧‧ second end

1152‧‧‧Second lower inner ring link

11521‧‧‧ first end

11522‧‧‧second end

116‧‧‧ Lower inner ring handle

117‧‧‧Limited device

1171‧‧‧ bolt

11711‧‧‧ screw

11712‧‧‧ head

1172‧‧‧ nuts

121‧‧‧First Link

122‧‧‧second connecting rod

123‧‧‧third link

124‧‧‧fourth link

Θ1~3‧‧‧ angle

Figure 1 is a top plan view of a conventional rotor blade. 2 is a cross-sectional view of a conventional rotor blade. 3 is a schematic diagram of the coaxial double-rotor turbine driven unmanned vehicle mechanism system of the present invention. 4a is a perspective view of the transmission output structure of the turbine engine of the present invention. Figure 4b is an exploded view of the transmission output structure of the inventive turbine engine. Figure 4c is a side elevational view of the transmission output structure of the inventive turbine engine. Figure 4d is a cross-sectional view of the transmission output structure of the inventive turbine engine. Figure 5 is a perspective view of the coaxial double-rotor mechanism of the present invention. Figure 6a is a schematic illustration of the upper main rotor set of the present invention. Figure 6b is a perspective view of the coaxial double-rotor direction control mount structure of the present invention. Figure 6c is an exploded view of the coaxial double-rotor directional control mount structure of the present invention. Fig. 6d is another angular exploded view of the coaxial double-rotor direction control mount structure of the present invention. Figure 7a is a top plan view of a first embodiment of the aerodynamic configuration of the upper and lower rotor blades of the present invention. Figure 7b is a cross-sectional view of the blade body of the first embodiment of the aerodynamic configuration of the upper and lower rotor blades of the present invention. Fig. 7c is a comparison diagram of the lift of the coaxial double-rotor turbine driven unmanned vehicle mechanism system of the prior art, the first embodiment and the second embodiment of the present invention. Fig. 8a is a perspective enlarged view of the coaxial double-rotor mechanism of the present invention. Figure 8b is a perspective view of the upper inner ring phase fixing base set of the present invention. Figure 8c is an exploded view of the upper inner ring phase mount block of the present invention. Figure 8d is a perspective view of the upper outer ring phase fixing base set of the present invention. Figure 8e is an exploded view of the upper outer ring phase mount block of the present invention. FIG. 9a is a perspective enlarged view of another perspective view of the coaxial double-rotor mechanism of the present invention. FIG. 9b is another perspective view of the upper inner ring phase fixing base set of the present invention. Figure 9c is a perspective view of the lower inner ring phase mount base set of the limited rotation angle of the present invention. Figure 9d is an exploded view of the lower inner ring phase mount block of the present invention for limiting the angle of rotation. Figure 9e is a cross-sectional view of the lower inner ring phase mount block of the created limited rotation angle. Figure 9f is a cross-sectional view of the lower inner ring link of the present invention rotated inwardly to a second position. Figure 9g is a perspective view of the upper inner ring link of the present invention rotated outward to the extreme limit and the lower inner ring link rotated inwardly to the second position.

10‧‧‧ body

20‧‧‧ Turbine engine

21‧‧‧Transmission output structure

30‧‧‧Coaxial double-rotor mechanism

40‧‧‧large spindle

50‧‧‧Small spindle

60‧‧‧Upper main rotor group

80‧‧‧Aerodynamic configuration of upper rotor blades

90‧‧‧Lower rotor blade aerodynamic configuration

100‧‧‧Upper coaxial double-rotor swashplate phase control mount structure

110‧‧‧Under coaxial double-rotor swashplate phase control fixed seat structure

121‧‧‧First Link

122‧‧‧second connecting rod

123‧‧‧third link

70‧‧‧The main rotor group

124‧‧‧fourth link

Claims (10)

A coaxial twin-rotor turbine driven unmanned vehicle mechanism system includes: a fuselage; a turbine engine disposed in the body and including a transmission output structure including a turbine engine, an adapter, and an output a gear, the turbine engine includes an engine body, a turbine drive shaft, and a retaining ring, the turbine drive shaft is rotatably disposed on the engine body and has a side protruding from a side of the engine body, the retaining ring being disposed at the One end of the turbine drive shaft, the adapter is disposed on the fixing ring, the output gear is disposed on the adapter; and a coaxial double-rotor mechanism includes: a large spindle rotatably disposed on the body and extending through Passing over the top of the fuselage and having a shaft hole; a small spindle rotatably disposed on the body and extending through the shaft hole of the large spindle; an upper main rotor group including an upper main rotor mount and a The coaxial double-rotor direction control fixed seat structure, the upper main rotor fixed seat is disposed on the small main shaft and includes a plurality of upper paddles, and the coaxial double-rotor direction is fixed The seat structure is disposed on the upper main rotor mount and includes a body, a shaft, a plurality of links and at least three support structures, the body being located above the upper main rotor mount and coaxial with the upper main rotor mount, the shaft a rod is disposed between the body and the upper main rotor mount and extends on an axis of the main body and an axis of the upper main rotor mount, and the links are respectively disposed on the outer side of the body and fixed to the upper main rotor Between the outer sides of the seat, the support structures are respectively disposed between the bottom of the body and the top of the upper main rotor mount around the shaft; the main rotor group includes a lower main rotor mount, the lower main rotor The fixed seat is disposed on the large main shaft and includes a plurality of lower paddle chucks; the plurality of upper rotor blade aerodynamic configurations each include an upper blade body, an upper joint portion and an upper wing tip portion, wherein the upper blade body is linear The two ends of the length direction are respectively defined as a first end and a second end, and the two sides in the width direction are respectively defined as a first side and a second side, and have a top surface and a bottom surface. The upper a joint portion is disposed at the first end of the upper blade body and disposed on the upper paddle head, the upper wing tip portion is disposed at the second end of the upper blade body, and is in the same plane as the upper blade body Extending and extending away from the upper joint and the first side of the upper blade body such that the length of the upper wing tip is different from the length direction of the upper blade body and the upper blade body The length direction has an angle; the plurality of lower rotor blade aerodynamic configurations each include a lower blade body, a lower joint portion and a lower wing tip portion, the lower blade body is linear, and the two ends of the longitudinal direction are respectively defined as one The first end and the second end are respectively defined as a first side and a second side, and have a top surface and a bottom surface, and the lower joint is disposed on the lower blade body The first end is disposed on the lower paddle, and the lower wing tip is disposed at the second end of the lower blade body, extends in the same plane as the lower blade body, and moves away from the lower joint And extending in a direction of the first side of the lower blade body such that The longitudinal direction of the lower wing tip is different from the longitudinal direction of the lower blade body and has an angle with the longitudinal direction of the lower blade body; an upper coaxial double-rotor swash plate phase control fixing seat structure, including an upper inner portion a ring set, an upper outer ring set, an upper inner ring phase fixed seat set and an upper outer ring phase fixed seat set, the upper inner ring set is sleeved on the small main axis and has an upper inner ring head, the upper outer ring The set ring is disposed on the upper inner ring group and has an upper outer ring head, the upper inner ring phase fixing seat set includes an upper inner ring phase fixing seat body, an upper inner ring connecting piece, an upper inner ring connecting piece and a plurality The upper inner ring fixing member is sleeved on the small main shaft, the upper inner ring connecting member has a first end and a second end, and at least one upper inner ring fixing member is screwed thereon The first end of the inner ring link and the upper inner ring are fixed to the base body such that the first end of the upper inner ring link is fixed to the upper inner ring phase mount body by the upper inner ring fixing member. The ring handle has a first end and a second end, and at least one upper inner ring is fixed a screw is disposed on the first end of the upper inner ring shank and the second end of the upper inner ring connecting member, such that the first end of the upper inner ring shank is fixed to the upper inner ring by the upper inner ring fixing member a second end of the connecting member, the second end of the upper inner ring shank is disposed on the upper inner ring head, and the upper outer ring phase fixing seat set comprises an upper outer ring phase fixing seat body, an upper outer ring connecting piece, An upper outer ring connecting handle and a plurality of upper outer ring fixing members, the upper outer ring phase fixing seat body is sleeved on the small main shaft, and the upper outer ring connecting member has a first end and a second end, at least one upper and outer The ring fixing member is screwed to the first end of the upper outer ring connecting member and the upper outer ring phase fixing seat body, such that the first end of the upper outer ring connecting member is fixed to the upper outer ring by the upper outer ring fixing member a phase fixing base body having a first end and a second end, wherein at least one upper outer ring fixing member is screwed on the first end of the upper outer ring connecting handle and the upper outer ring connecting piece a second end, the first end of the upper outer ring shank being fixed to the second end of the upper outer ring connecting piece by the upper outer ring fixing member, the upper outer ring connecting handle The second end is disposed on the upper outer head; and the coaxial double-rotor swash plate phase control fixed seat structure includes a lower inner ring group, a lower outer ring group, a lower inner ring phase fixed seat group for limiting the rotation angle, and An outer ring phase fixing seat set, the lower inner ring set is sleeved on the large main axis and has a lower inner ring head, the lower outer ring set ring is disposed in the lower inner ring set and has a lower outer ring head, the limit rotation angle The lower inner ring phase fixing seat set comprises a lower inner ring phase fixing seat body, a lower inner ring connecting piece, a lower inner ring connecting handle, a plurality of lower inner ring fixing members and a limiting device, and the lower inner ring phase fixing seat body sleeve is set The lower inner ring link includes a first lower inner ring link and a second lower inner ring link, and the first lower inner ring link has a first end and a second end. The second lower inner ring link has a first end and a second end, and at least the lower inner ring fixing member is screwed on the first end of the first lower inner ring link and the lower inner ring phase fixing seat body, so that The first end of the first lower inner ring link is fixed by the lower inner ring fixing member The lower inner ring phase fixing seat body, at least the lower inner ring fixing member is screwed on the first end of the second lower inner ring link and the second end of the first lower inner ring link, so that the second lower inner The first end of the ring link is fixed to the second end of the first lower inner ring link by the lower inner ring fixing member, the lower inner ring handle has a first end and a second end, at least the inner ring The fixing member is screwed to the first end of the lower inner ring shank and the second end of the second lower inner ring link such that the first end of the lower inner ring shank is fixed to the lower inner ring fixing member a second end of the second lower inner ring link, the second end of the lower inner ring shank is disposed on the lower inner ball head, and at least a portion of the limiting device is located at an inner side of the lower inner ring link and the major axis Between the outer sides, wherein the lower inner ring link is rotated away from the major axis when the lower inner ring link is rotated outward; when the lower inner ring link is rotated inwardly to a second position The limiting device limits an angle at which the first lower inner ring link and the second lower inner ring link rotate inwardly to inner side of the lower inner ring link The outer side of the large main shaft is separated by a distance, and the lower outer ring phase fixing seat set includes a lower outer ring phase fixing seat body, a lower outer ring connecting piece, a lower outer ring connecting handle and a plurality of lower outer ring fixing members, and the lower outer ring phase The fixing base body is sleeved on the large main shaft, and the lower outer ring connecting member has a first end and a second end, and at least the lower outer ring fixing member is screwed on the first end and the lower end of the lower outer ring connecting member The ring-shaped fixing base body is such that the first end of the lower outer ring connecting member is fixed to the lower outer ring phase fixing seat body by the lower outer ring fixing member, the lower outer ring connecting handle has a first end and a second end And at least a lower outer ring fixing member is screwed on the first end of the lower outer ring connecting handle and the second end of the lower outer ring connecting piece, so that the first end of the lower outer ring connecting handle is fixed by the lower outer ring The piece is fixed to the second end of the lower outer ring connecting piece, and the second end of the lower outer ring connecting piece is disposed on the lower outer ring head. The coaxial double-rotor turbine-driven unmanned vehicle mechanism system according to the first aspect of the invention, wherein the fixing ring defines a fixing screw hole, the adapter seat defines an adapter screw hole, and the transmission output structure of the turbine engine An adapter screw is disposed, and the adapter screw is screwed into the adapter screw hole and the fixing screw hole. The coaxial double-rotor turbine-driven unmanned vehicle mechanism system according to claim 1, wherein the adapter has an output screw hole, the output gear defines a gear screw hole, and the transmission output structure of the turbine engine includes a gear screw, the gear screw is screwed in the output screw hole and the gear screw hole. The coaxial double-rotor turbine-driven unmanned vehicle mechanism system of claim 1, wherein the body comprises a base and a plurality of pivots, the pivots being pivoted on an outer side of the base; the shaft The axis is disposed between the base and the upper main rotor mount and extends on an axis of the base and an axis of the upper main rotor mount; one ends of the links are respectively disposed outside the pivot seat The other ends are respectively pivoted on the outer side of the upper main rotor mount; the at least three support structures are all rod-shaped and are disposed around the shaft between the bottom of the base and the top of the upper main rotor mount. The coaxial double-rotor turbine-driven unmanned vehicle mechanism system of claim 4, wherein the upper main rotor mount includes an upper body and at least three upper extension arms, the at least three upper extension arms are spaced apart from each other An outer ring wall of the upper body, the upper paddles are respectively disposed at ends of the at least three upper extending arms; the shaft is disposed between the base and the upper body and extends along an axis of the base The other end of the connecting rod is respectively disposed on an outer side of the at least three upper extending arms; the at least three supporting structures respectively extend through and perpendicular to an axis of the at least three upper extending arms, each supporting structure The distance from the adjacent two support structures is equal. The coaxial double-rotor turbine-driven unmanned vehicle mechanism system of claim 1, wherein the bottom surface of the upper blade body is from a first side of the upper blade body to a second side of the upper blade body. The curvature of the side bend is greater than the curvature of the top surface of the upper blade body from the first side of the upper blade body to the second side of the upper blade body such that the top surface of the upper blade body and The height of the bottom surface is inconsistent and asymmetric; wherein the bottom surface of the lower blade body has a curvature curved from the first side of the lower blade body to the second side of the lower blade body is larger than the lower blade The curvature of the top surface of the body from the first side of the lower blade body to the second side of the lower blade body is such that the top and bottom surfaces of the lower blade body are inconsistent and asymmetric. . The coaxial double-rotor turbine-driven unmanned vehicle mechanism system according to claim 6, wherein the angle of the angle is 20 to 45 degrees. The coaxial double-rotor turbine-driven unmanned vehicle mechanism system according to claim 1, wherein the upper outer ring connecting member comprises a first upper outer ring link and a second upper outer ring link, the first An upper outer ring link has a first end and a second end, the second upper outer ring link has a first end and a second end, and at least one upper outer ring fixing member is screwed on the first The first end of the outer ring link and the upper outer ring are fixed to the base body such that the first end of the first upper outer ring link is fixed to the upper outer ring phase fixing seat body by the upper outer ring fixing member, at least Upper outer ring a fixing screw is disposed on the first end of the second upper outer ring link and the second end of the first upper outer ring link such that the first end of the second upper outer ring link is fixed by the upper outer ring The second end of the first upper outer ring link is fixed to the first end of the upper outer ring connecting rod and the second end of the second upper outer ring link. The first end of the upper outer ring shank is fixed to the second end of the second upper outer ring link by the upper outer ring fixing member; wherein the lower outer ring connecting member comprises a first lower outer ring link And a second lower outer ring link, the first lower outer ring link has a first end and a second end, the lower second outer ring link has a first end and a second end, at least The outer ring fixing member is screwed to the first end of the first lower outer ring link and the lower outer ring phase fixing seat body, such that the first end of the first lower outer ring link is fixed by the lower outer ring fixing member In the lower outer ring phase fixing seat body, at least the lower outer ring fixing member is screwed on the first end of the second lower outer ring link and the second end of the first lower outer ring link, so that the second lower Outer ring link The first end is fixed to the second end of the first lower outer ring link by the lower outer ring fixing member, and at least the lower outer ring fixing member is screwed to the first end of the lower outer ring connecting handle and the second lower outer The second end of the ring link is such that the first end of the lower outer ring shank is fixed to the second end of the second lower outer ring link by the lower outer ring fixing member. The coaxial double-rotor turbine-driven unmanned vehicle mechanism system of claim 1, wherein the upper inner ring link comprises a first upper inner ring link, and the first upper inner ring link comprises a connection An arm and two extension arms, wherein the two extension arms of the first upper inner ring link extend from two ends of the connecting arm of the first upper inner ring link and And defined as a first end of the first upper inner ring link and respectively forming a through hole, the through holes of the two extending arms of the first upper inner ring link respectively extend transversely through the two extensions of the first upper inner ring link Two sides of the arm, the upper inner ring phase fixing seat body is located in a space surrounded by the connecting arm of the first upper inner ring link and the two extending arms and defines a screw hole extending through the two sides thereof The ring fixing members respectively pass through the through holes of the two extending arms of the first upper inner ring link and are respectively screwed into the screw holes from the two ends of the screw holes of the upper inner ring phase fixing seat body, so that the first The two extension arms of the upper inner ring link are respectively fixed to the two sides of the upper inner ring phase fixing body by the two upper inner ring fixing members; wherein the first lower inner ring link comprises a connecting arm and two extensions An arm extending from two ends of the connecting arm of the first lower inner ring link and defined as a first end of the first lower inner ring link and respectively opening one a perforation, the through holes of the two extension arms of the first lower inner ring link respectively extend transversely through the first lower inner ring Two sides of the two extension arms of the rod, the lower inner ring phase fixing seat body is located in a space surrounded by the connecting arm of the first lower inner ring link and the two extending arms and defines a screw hole extending through the two sides thereof The two lower inner ring fixing members respectively pass through the through holes of the two extending arms of the first lower inner ring link and are respectively screwed into the screw holes from the two ends of the screw holes of the lower inner ring phase fixing seat body. The two extension arms of the first lower inner ring link are respectively fixed to the two sides of the lower inner ring phase fixing base body by the two lower inner ring fixing members. The coaxial double-rotor turbine-driven unmanned vehicle mechanism system of claim 1, wherein the first lower inner ring link defines a perforation, the limit The device is disposed on the through hole and has one end extending outside the through hole and protruding from the inner side of the first lower inner ring link. When the lower inner ring link is rotated inward to the second position, the limiting device protrudes A portion of the inner side of the first lower inner ring link abuts against an outer side of the large main shaft.