TWI627103B - Coaxial double-rotor turbine drive unmanned vehicle mechanism system - Google Patents

Abstract

A coaxial dual-rotor turbine-driven unmanned vehicle mechanism system includes a fuselage, a turbine engine, and a coaxial dual-rotor mechanism. The turbine engine contains a transmission output structure. The coaxial double-rotor mechanism includes large and small main shafts, upper and lower main rotor groups, upper and lower rotor blade aerodynamic configurations, and upper and lower coaxial double-rotor swashplate phase control fixed seat structures. The transmission output structure can be disassembled at external speeds and is convenient for processing, saving replacement and maintenance time. The upper main rotor group has good sliding stability and small sloshing; the lift and drag resistance generated by the aerodynamic configuration of the upper and lower rotor blades are good; The function of maintaining the upper and lower coaxial dual-rotor swashplate phase control fixed seat structure to change the flying angle of the present invention, and accurately controlling the upper and lower main rotor groups to synchronously deflect relative to the fuselage, so that the present invention can stably change the flying angle.

Description

Coaxial double-rotor turbine-driven unmanned vehicle mechanism system

The invention relates to a coaxial dual-rotor turbo-drive unmanned vehicle mechanism system, in particular to a coaxial dual-rotor turbo-drive unmanned vehicle that has comprehensively evolved in all aspects of flight capabilities, safety, stability, manufacturing and disassembly. Institutional system.

There are mainly three types of remotely controlled unmanned helicopters based on the number of rotor shafts: single rotor, double rotor, and multiple rotors. The double-rotor remote-control helicopter can be subdivided into four types: coaxial, tandem, horizontal, and cross. A common coaxial dual-rotor turbo-drive unmanned vehicle mechanism system includes three main mechanisms, such as a fuselage, a turbine engine, and a coaxial dual-rotor mechanism.

Turbine engines are also called turboshaft engines. The airflow generated by the combustion chamber drives the free turbine output shaft power instead of jet thrust. The structure is similar to the turboprop, but the main difference is that the exhaust from the turboprop also generates some residual propulsion. In addition, for turboprop engines, the main reduction gear of the transmission system is integrated on the engine, while for turboshaft engines, it is separated.

The conventional transmission output structure of the turbine engine is manufactured in an integrated manner. Due to its integrated structure, it is very complicated when the output gear is damaged and aging, and when the gear ratio needs to be replaced. The disassembly method requires disassembly of the whole, and the process is complicated. In addition, it is very difficult to process the transmission output structure.

The coaxial dual-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 blades, a plurality of lower rotor blades, an upper coaxial double rotor swash plate phase control fixed seat structure, and a lower coaxial double The structure of the rotor swashplate phase control fixed seat is different from that of a large helicopter. The main shaft is rotatably provided on the fuselage, extends through the top of the fuselage, and has a shaft hole. The small main shaft is rotatably provided on the fuselage and extends through the shaft hole of the large main shaft. The upper main rotor group is set on the small main axis, and the lower main rotor group is set on the main main axis. The upper rotor blades are provided in the upper main rotor group, and the lower rotor blades are provided in the lower main rotor group. The upper coaxial double-rotor swashplate phase control fixed seat structure is arranged on the small main shaft, and a plurality of connecting rods are connected between the upper main rotor group and the upper coaxial double-rotor swashplate phase control fixed seat structure. The lower coaxial double-rotor swashplate phase control fixed seat structure is arranged on the main shaft, and a plurality of connecting rods are connected between the lower main rotor group and the lower coaxial double-rotor swashplate phase control fixed seat structure. The upper and lower main rotor groups are arranged on top of each other and are driven by the coaxial small and large spindles to rotate in opposite directions on the same axis (that is, the small and large spindles respectively drive the upper and lower main rotor groups to rotate in different directions). And, with the lift generated by the upper and lower rotor blades during rotation, the coaxial dual-rotor remote-control helicopter can take off and land stably. 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. The place produces only negligible lift. The small and large spindles use the upper and lower coaxial dual-rotor swashplate phase control fixed seat structure and the combination of these connecting rods to synchronously drive the upper and lower main rotor groups to tilt relative to the fuselage to change the flight angle of the coaxial dual-rotor remote-control helicopter. (E.g. forward, backward, turn left, turn right).

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

However, the above-mentioned conventional coaxial double-rotor direction control fixing seat structure only uses one shaft to combine with the seat body of the upper main rotor fixing seat and three extension links to the extension arms of the upper main rotor fixing seat, so that the upper The main rotor group has poor stability and is prone to sway relative to the small main shaft, causing offsets, which in turn causes the small and large main shafts to use the upper and lower coaxial dual-rotor swashplate phase control fixed seat structures and these connecting rods to simultaneously drive the upper and lower main shafts. When the rotor group is tilted relative to the fuselage to change the flight angle of the coaxial dual-rotor remote-control helicopter and tilted relative to the fuselage, the tilt angles of the upper rotor blades cannot be consistent, resulting in the inaccuracy of the coaxial dual-rotor turbine-driven unmanned vehicle mechanism system. The ground is maintained to fly at a preset angle.

Another conventional coaxial double-rotor direction control fixing structure includes a body and two sliding pins. The two sliding pins are arranged between the body of the coaxial double-rotor direction control fixing structure and the seat of the upper main rotor fixing base, thereby improving The stability of the upper main rotor group makes the degree of sloshing of the upper main rotor group relative to the small main shaft smaller.

However, this type of dual-spin coaxial dual-rotor direction control fixed seat structure can only reduce the error of the tilt angles of the three upper rotor blades, and the coaxial dual-rotor turbine-driven unmanned vehicle mechanism system can fly closer to a preset angle. However, the inclination angles of the three upper rotor blades still cannot be kept the same, so the coaxial double rotor turbine-driven unmanned carrier mechanism system equipped with the coaxial double rotor direction control fixed seat structure of such a double sliding pin still cannot be accurately maintained at Flying at a predetermined angle cannot completely solve the problems caused by the structure of the above-mentioned coaxial double-rotor direction control fixing base without sliding pin.

In addition, the two sliding pins are easily deformed by force. When one of the sliding pins is deformed or bent due to collision, the coaxial double-rotor direction control fixing structure of this double-slide pin "improves the stability of the upper main rotor group. The "earthly" effect was immediately lost, and even if the other slip pin remained intact, it would not help.

Please refer to FIG. 1, which is a top view of a conventional rotor blade. The structure of the upper and lower rotor blades is exactly the same, so the "rotor blades" will be used to represent the upper and lower rotor blades. A general 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 two ends in the length direction are defined as a first end and a second end, and 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 at the paddle chuck of the upper and lower main rotor groups. The wing tip A3 is provided at the second end of the blade body A1, is located on the same plane as the blade body A1, and extends straight and tapered in a direction away from the joint A2, so that its length direction is in line with that of the blade body A1. The longitudinal direction is the same and parallel to the longitudinal direction of the blade body A1. In short, the general structure of a general rotor blade A is straight. The vortex of the linear rotor blade A and the lift line remain perpendicular, resulting in a very limited lift.

Furthermore, the wing tip A3 of such a linear rotor blade A is highly likely to generate a regional vibration wave when it rotates at a high speed, thereby increasing the resistance.

Please refer to FIG. 2, which is a cross-sectional view of a conventional rotor blade. The blade body A1 has a top surface A15 and a bottom surface A16. From a sectional view, 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 bent upward from the first side A13 of the blade body A1, and then bent down to the second side A14 of the blade body A1; the blade body A1 The bottom surface A16 of the blade body A1 is bent downward from the first side edge A13 of the blade body A1 and then bent upward to the second side edge 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 fluctuations are quite consistent, so that the overall structure of the blade body A1 is symmetrical. However, the lift generated by this symmetrical blade body A1 is very limited.

The conventional upper coaxial dual-rotor swashplate phase control fixed seat structure includes an upper inner ring group, an upper outer ring group, an upper inner ring phase fixed seat group, and an upper outer ring phase fixed seat group. The upper inner ring group is sleeved on the small main shaft and has a plurality of upper inner ring and ball heads. A plurality of first connecting rods are connected between the upper inner ring and ball heads and the upper main rotor group. The upper outer ring group ring is provided in the upper inner ring group and has a plurality of upper and outer ring heads. The upper inner ring phase fixing base group includes an upper inner ring phase fixing base body, an upper inner ring tongue and groove and an upper inner ring connecting handle. The upper inner ring phase fixing seat body is sleeved on the small spindle. The upper inner ring tongue is pivotally arranged on the upper inner ring phase fixing seat. One end of the upper inner ring connecting handle is provided on one of the upper inner ring heads, and the upper inner ring tongue can rotatably fasten the other end of the upper inner ring connecting handle. The upper outer ring phase fixing seat group includes an upper outer ring phase fixing seat body, an upper outer ring tongue and groove, and an upper outer ring connecting handle. The main body of the upper outer ring phase fixing seat is sleeved on the small spindle. The upper outer ring tongue is pivotally arranged on the upper outer ring phase fixing seat. One end of the upper outer ring connecting handle is arranged on one of the upper and outer ring heads, and the upper outer ring tenon is rotatably fastened to the other end of the upper outer ring connecting handle.

The conventional lower coaxial dual-rotor swashplate phase control fixed base structure includes a lower inner ring group, a lower outer ring group, a lower inner ring phase fixed block group, and a lower outer ring phase fixed block group. In other words, the structure of the lower coaxial dual-rotor swashplate phase control fixing structure is exactly the same as that of the upper coaxial dual-rotor swashplate phase control fixing structure, and the connection relationship between these components is also the same, the difference is: the lower inner ring set It is set on the main shaft. A plurality of second connecting rods are connected between the upper and outer globe heads and a lower inner and round head. The third connecting rods are connected between the lower inner globe head and the ball head of the lower main rotor group. The fourth connection is plural. The rod is connected between the lower outer globe 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. In this way, the deflection of the combination of the lower inner ring group and the lower outer ring group relative to the major axis is controlled, while the combination of the upper inner ring group and the upper outer ring group is deflected relative to the small main axis, and then the upper and lower main rotor groups are synchronized with respect to the fuselage. Deflection to change the flight angle of the coaxial twin-rotor remote control helicopter.

However, there is a gap between the upper inner ring tongue and the upper inner ring adapter, there is a gap between the lower inner ring tongue and the lower inner ring adapter, and there is a gap between the upper outer ring tongue and the upper outer ring adapter. There is a gap between the lower outer ring mortise and the lower outer ring shank. Therefore, when the upper and lower main rotor groups are driven by the coaxial small and large spindles to rotate in opposite directions on the same axis, the coaxial double rotor mechanism will generate vibration as a whole, resulting in the upper inner ring connecting handle from above. The inner ring tongue is gradually loosened, the upper outer ring adapter is gradually loosened from the upper outer ring tongue, the lower outer ring adapter is gradually released from the lower outer ring tongue, and the lower inner ring adapter is released from the lower inner ring. The tenon is gradually loosened, so that the structure of the upper and lower coaxial dual-rotor swashplate phase control mounts is ineffective and the flight angle of the coaxial dual-rotor remote-control helicopter cannot be changed.

Furthermore, the materials of the upper inner ring tenon, the upper outer ring tenon, the lower inner ring tenon, and the lower outer ring tenon are all made of plastic, which has poor structural strength. Under long-term use, the upper inner ring tenon, the upper outer ring tenon, the lower inner ring tenon, and the lower outer ring tenon are prone to wear due to vibration, making the upper inner ring joint, the upper outer ring joint, and the lower inner ring The adapter and the lower outer ring adapter are easier to release from the upper inner ring tongue, the upper outer ring tongue, the lower inner ring tongue, and the lower outer ring tongue, respectively, so that the upper and lower coaxial double rotor swashplates are phased. The control mount structure loses its effectiveness and cannot change the flight angle of the coaxial dual-rotor remote-control helicopter.

In addition, the distance between the upper inner ring connector and the small main shaft is smaller than the distance between the lower inner ring connector and the large main shaft. Therefore, when the first and second inner ring links of the upper inner ring connector rotate outward to the limit, the lower inner ring The first and second inner ring links of the ring link and the main spindle still have a little space and will continue to rotate inward until they touch the main spindle at the same time, resulting in the combination of the lower inner ring group and the lower outer ring group being relatively large. The angle of deflection is larger than the deflection angle of the combination of the upper inner ring group and the upper outer ring group with respect to the relatively small main axis. As a result, the upper and lower main rotor groups cannot synchronously deflect relative to the fuselage, which causes the coaxial dual-rotor remote control helicopter to change the flight angle Out of control.

It can be seen from the above that the conventional coaxial double-rotor turbo-drive unmanned vehicle mechanism system has many unsatisfactory aspects in terms of the coaxial double-rotor and the turbine engine, and these unsatisfactory aspects mutually affect the flight capability of the overall system, Safety, stability, manufacturing and disassembly, therefore, there is an urgent need to develop a coaxial dual-rotor turbo-drive unmanned vehicle mechanism system that can comprehensively improve the above problems.

The main purpose of the present invention is to provide a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system. The transmission output structure of the turbine engine is more convenient and fast in replacement, disassembly and other applications, and is conducive to processing and manufacturing, saving replacement and maintenance time. The rotor group has good sliding stability, and the degree of sloshing is relatively small. The aerodynamic configuration of the upper and lower rotor blades has good lift and lower drag effects. Maintaining the upper and lower coaxial dual-rotor swashplate phase control fixed structure changes the cost. The function of the invented flight angle, and the precise control of the upper and lower main rotor groups to synchronously deflect relative to the fuselage, enable the present invention to stably change the flight angle.

In order to achieve the foregoing object, the present invention provides a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system, including a fuselage, a turbine engine, and a coaxial dual-rotor mechanism.

The turbine engine is provided on 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 transmission shaft, and a fixed ring. It is rotatably arranged on the engine body and one side of the engine body protrudes from one side of the engine body. A fixed ring is provided on one end of the turbine transmission shaft. An adapter seat is provided on the fixed ring. An output gear is provided on the adapter seat.

The coaxial dual-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 dual rotor swashplate phase control and fixed Seat structure and lower coaxial double-rotor swashplate phase control fixed seat structure.

The main shaft is rotatably provided on the fuselage, extends through the top of the fuselage, and has a shaft hole.

The small main shaft is rotatably provided on the fuselage and extends through the shaft hole of the large main shaft.

The upper main rotor set includes an upper main rotor fixed base and a coaxial double rotor direction control fixed base structure. The upper main rotor fixed base is provided on the small main shaft and includes a plurality of upper paddle chucks. The coaxial double rotor direction controlled fixed base structure is provided on the upper side. The main rotor fixed base includes a body, a shaft, a plurality of links and at least three supporting structures. The main body is located above the upper main rotor fixed base and is coaxial with the upper main rotor fixed base. The shaft is provided on the main body and the upper main rotor fixed base. Between the axis of the main body and the axis of the upper main rotor fixed seat, the connecting rods are respectively arranged between the outer side of the main body and the outer side of the upper main rotor fixed seat, and the supporting structures are respectively arranged around the shaft Between the bottom of the body and the top of the upper main rotor fixed seat.

The lower main rotor set includes a lower main rotor fixing seat, the lower main rotor fixing seat is provided on the main shaft and includes a plurality of lower paddle chucks.

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 in the length direction are respectively defined as a first end and a The second end has two sides in the width direction defined as a first side and a second side, respectively, and has a top surface and a bottom surface. The upper joint portion is provided at the first end of the upper blade body and is provided at Upper paddle chuck, the upper wing tip is set on the second end of the upper blade body, extends on the same plane as the upper blade body, and is away from the upper joint and the first side of the upper blade body Extend so that the length direction of the tip of the upper wing is different from the length direction of the upper blade body and has an angle with the length 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 in the length direction are respectively defined as a first end and a second end. The two sides in the width direction are defined as a first side and a second side, respectively, and have a top surface and a bottom surface. The lower joint portion is provided on the first end of the lower blade body and on the lower blade clamp. The head and the lower wing tip are located on the second end of the lower blade body, and extend on the same plane as the lower blade body, and extend away from the lower joint portion and the first side of the lower blade body, so that The length direction of the lower wing tip is different from the length direction of the lower blade body and has an angle with the length direction of the lower blade body.

The upper coaxial double-rotor swashplate phase control fixed seat structure includes an upper inner ring group, an upper outer ring group, an upper inner ring phase fixed seat group and an upper outer ring phase fixed seat group. The upper inner ring group is set in a small The main shaft has an upper inner ring head, the upper outer ring ring is arranged on the upper inner ring ring and has an upper and outer ring ring head. The upper inner ring phase fixing seat group includes an upper inner ring phase fixing seat body and an upper inner ring connection. Pieces, an upper inner ring connecting handle and a plurality of upper inner ring fixing pieces, the upper inner ring phase fixing seat body is sleeved on the small spindle, and the upper inner ring connecting piece has a first end and a second end, at least one upper inner ring The fixing member is screwed on the first end of the upper inner ring connecting member and the upper inner ring phase fixing base body, so that the first end of the upper inner ring connecting member is fixed to the upper inner ring phase fixing base body by the upper inner ring fixing member. The inner ring connecting handle has a first end and a second end. At least one upper inner ring fixing member is screwed on the first end of the upper inner ring connecting handle 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 member by the upper inner ring fixing member, and the upper inner ring is connected to the handle The second end is located on the upper and inner ring heads. The upper and outer ring phase fixing base group includes an upper and outer ring phase fixing base body, an upper and outer ring connecting piece, an upper and outer ring connecting handle, and a plurality of upper and outer ring fixing pieces. The ring phase fixing body is sleeved on the small main shaft. The upper outer ring connecting member has a first end and a second end. 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, so that the first end of the upper outer ring connecting member is fixed to the upper outer ring phase fixing base 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 upper 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 member, so that the first end of the upper outer ring connecting handle is fixed to the upper outer ring connecting member by the upper outer ring fixing member. The second end of the upper outer ring connecting handle is provided on the upper and outer round heads.

The lower coaxial double-rotor swashplate phase control fixed seat structure includes 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 that limit the rotation angle. The lower inner ring group is set on The main shaft has a lower inner ring head, and a lower outer ring group ring is arranged on the lower inner ring group and has a lower outer ring head. The lower inner ring phase fixing seat group which restricts the rotation angle includes a lower inner ring phase fixing body, a lower inner ring A ring link, a lower inner ring connecting handle, a plurality of lower inner ring fixing members, and a limiting device. The lower inner ring phase fixing body is sleeved on the main shaft. The lower inner ring link includes a first lower inner ring link and A second lower inner ring link, 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 is fixed Pieces are 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 to the lower inner ring phase fixing seat by the lower inner ring fixing member Body, at least the lower inner ring fixing part is screwed on the second lower inner ring The first end and the second end of the first lower inner link are such that the first end of the second lower inner link is fixed to the second end of the first lower inner link by the lower inner ring fixing member. The inner ring connecting handle 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 connecting handle and the second end of the second lower inner ring connecting rod, so that the lower inner ring The first end of the connecting handle is fixed to the second end of the second lower inner ring connecting rod by the lower inner ring fixing member. The second end of the lower inner ring connecting handle is provided on the lower inner ring head. At least a part of the limiting device is located in the lower inner ring. Between the inside of the ring link and the outside of the major axis, when the lower inner ring link rotates outward to a first position, the lower inner ring link moves away from the main axis; when the lower inner ring link rotates inward to one In the second position, the limiting device limits the inward rotation angle of the first lower inner link and the second lower inner link so that the inside of the lower inner ring link is separated from the outside of the main shaft by a distance. Outer ring phase fixing block group includes lower outer phase fixing base body, lower outer ring connecting piece, lower outer ring connecting handle and a plurality of lower rings A ring fixing member, the lower outer ring phase fixing seat body is sleeved on the main shaft, 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 of the lower outer ring connecting member; The end and the lower outer ring phase fixing seat body, so 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, at least the 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 part by the lower outer ring fixing member. The second end of the outer ring connecting piece and the second end of the lower outer ring connecting handle are arranged on the lower outer ring head.

The effect of the present invention is that the transmission output structure of the turbine engine is more convenient and fast in replacement, disassembly and other applications, and is conducive to processing and manufacturing, saving time for replacement and maintenance. The sliding stability of the upper main rotor group is better, and the relatively small main shaft swayes. The degree is small; the lift and drag generated by the aerodynamic configuration of the upper and lower rotor blades are good; the function of maintaining the structure of the upper and lower coaxial dual-rotor swashplate phase control mounts to change the flight angle of the present invention and accurately control the upper and lower rotors The lower main rotor group is simultaneously deflected relative to the fuselage, so that the present invention can stably change the flight angle. With this, the present invention has comprehensively evolved in all aspects of flight capability, safety, stability, processing, manufacturing, disassembly and the like.

The following describes the embodiments of the present invention in more detail with reference to the drawings and element symbols, so that those skilled in the art can implement them after studying this specification.

Please refer to FIG. 3. FIG. 3 is a schematic diagram of a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system of the present invention. The present invention provides a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system, which includes 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 invention A side view of the structure. FIG. 4D is a cross-sectional view of a transmission output structure of a turbine engine of the present invention. The turbine engine 20 is disposed on the fuselage 10 and includes a transmission output structure 21. The transmission output structure 21 includes 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 known and will not be described in detail here.

The turbine engine 22 includes an engine body 221, a turbine transmission shaft 222, a fixing ring 223, and a protruding tube 224. The turbine transmission shaft 222 is rotatably provided on the engine body 221 and one side thereof protrudes from one side of the engine body 221. The fixing ring 223 is provided on a shaft center of the turbine transmission shaft 222 protruding 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 an axis of the fixing ring 223 on a side away from the engine body 221.

The adapter seat 23 includes an adapter ring 231, a adapter tube 232 and a shaft hole 233. The adapter ring 231 defines a plurality of adapter screw holes 2311. The adapter pipe 232 protrudes from the shaft center of the side of the adapter ring 231 away from the engine body 221 and defines a plurality of output screw holes 2321. The shaft hole 233 of the adapter seat 23 passes through the shaft centers of the adapter ring 231 and the adapter tube 232. The adapter ring 231 is attached to the fixing ring 223, the adapter screw holes 2311 correspond to the fixing screw holes 2231, and the adapter screws 24 are screwed in the adapter screw holes 2311 and the fixing screw holes 2231, respectively. . However, the fixing manner of the adapter ring 231 and the fixing ring 223 is not limited to this. In other embodiments, the adapter ring 231 may be fixed to the fixing ring 223 by snap-fitting, rotation fixing, adhesive fixing, or other fixing methods. , He Xianxian. The protruding tube 224 is abutted from one side of the adapter ring 231 to the fixing ring 223 and engaged with the shaft hole 233 of the adapter seat 23. Thereby, when the turbine engine 22 is started, the turbine transmission shaft 222 starts to rotate relative to the engine body 221 and drives the adapter seat 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 on an outer circumferential surface of the gear tube 251. The shaft hole 252 penetrates the shaft center of the gear tube 251 and the front and rear ends of the gear tube 251. The output gear teeth 253 are provided on the outer ring surface of the gear tube 251. The transfer pipe 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 in the gear screw holes 2511 and the output screw holes 2321, respectively. However, the fixing manner of the transfer tube 232 and the gear tube 251 is not limited to this. In other embodiments, the transfer tube 232 can also be fixed to the gear tube 251 by snap fixing, rotation fixing, adhesive fixing, or other fixing methods. , He Xianxian. Thereby, when the adapter seat 23 rotates, the adapter seat 23 can drive the output gear 25 to rotate synchronously.

The transmission gear 27 includes a plurality of transmission gear teeth 271. The transmission gear teeth 271 mesh 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.

Because the components such as the turbine engine 22, the adapter 23, and the output gear 25 are fixed in sections (that is, they are connected and fixed to each other in sequence), when 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 after aging or damage, the connection relationship between the adapter seat 23 and the output gear 25 only needs to be released, that is, directly remove the gear screw 26, or the engagement of the adapter tube 232 and the gear tube 251 When it is fixedly opened, the gear ratio of the output gear 25 can be replaced. In addition, when selecting the output gears 25 of different calibers, the adapter 23 can be directly processed, and the adapter 23 corresponding to the caliber of the output gear 25 can be changed, so that the output gears 25 of different calibers can be replaced. Compared with the conventional technology, 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 replacement, disassembly and other applications, saving replacement and maintenance time.

Please refer to FIG. 3 and FIG. 5. FIG. 3 is a schematic diagram of the coaxial dual-rotor turbine-driven unmanned vehicle mechanism system of the present invention. FIG. 5 is a perspective view of the coaxial dual-rotor mechanism of the present invention. The coaxial dual-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 blade aerodynamic configurations 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 shaft 40 is rotatably disposed on the fuselage 10, extends through the top of the fuselage 10, and has a shaft hole (not shown).

The small main shaft 50 is rotatably provided in the fuselage 10 and extends through a shaft hole of the large main shaft 40.

Please refer to FIG. 3 and FIGS. 6 a to 6 d. FIG. 3 is a schematic diagram of a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system of the present invention. FIG. 6 a is a schematic diagram of an upper main rotor set of the present invention, and FIG. 6 b is a coaxial of the present invention. A perspective view of the structure of the dual-rotor direction control fixing base. FIG. 6C is an exploded view of the coaxial double-rotor direction-control fixing base structure according to the present invention, and FIG. The upper main rotor group 60 includes an upper main rotor fixing base 61 and a coaxial double rotor direction control fixing structure 62.

The upper main rotor fixing seat 61 is disposed on the small main shaft 50 and includes an upper seat body 611, at least three upper extension arms 612, and at least three upper paddle chucks 613. At least three upper extension arms 612 protrude from an outer ring wall of the upper base 611 at intervals, and each of the upper extension arms 612 and an adjacent two upper extension arms 612 are spaced apart at the same distance. At least three upper paddle chucks 613 are provided at the ends of the at least three upper extension arms 612 (that is, the end away from the upper seat body 611). Generally speaking, the number of the upper extension arms 612 and the number of the upper paddle chucks 613 are three and the angle between the adjacent two upper extension arms 612 is one hundred and twenty degrees. Therefore, the The overall appearance is herringbone-shaped, as shown in Figure 6a.

The coaxial double-rotor direction control fixing seat structure 62 includes a body 63, a shaft 64, a plurality of links 65, and at least three supporting structures 66, as shown in FIG. 6a.

The main body 63 is located above the upper main rotor fixing base 61 and is coaxial with the upper main rotor fixing base 61. In this embodiment, the main body 63 includes a base 631 and a plurality of pivot bases 632, and the pivot bases 632 are pivotally disposed outside the base 631. Specifically, an outer ring wall of the base 631 protrudes from a plurality of cantilever arms 6311 at intervals, and the pivot bases 632 are respectively pivoted on the cantilever 6311.

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

The connecting rods 65 are respectively provided between the outside of the main body 63 and the outside of the upper main rotor fixing base 61. More specifically, one end of the connecting rods 65 is respectively pivoted on the outer side of the pivot bases 632, and the other end is respectively pivoted on the outer sides of the at least three upper extension arms 612.

At least three supporting structures 66 are respectively arranged around the shaft 64 between the bottom of the body 63 and the top of the upper main rotor fixing base 61, as shown in FIG. 6a. Specifically, the outer ring wall of the base 631 protrudes at least three protrusions 6314 at intervals, and the distance between each protrusion 6314 and the adjacent two protrusions 6314 is equal, and each protrusion 6314 is provided on two cantilevers. 6311 and the length is shorter than the length of each cantilever 6311; at least three supporting structures 66 are rod-shaped, and are arranged around the shaft 64 at the bottom of at least three protrusions 6314 and the top of the upper main rotor fixing seat 61 respectively Among them, the number of the cantilever 6311, the projection 6314, the pivot base 632, the link 65 and the support structure 66 are all equal to the number of the upper extension arms 612. The number of the upper extension arms 612 in this embodiment is three, so the cantilever The number of 6311, the protruding portion 6314, the pivot base 632, the connecting rod 65 and the supporting structure 66 are all three. In this way, the supporting structures 66 can provide the effect of three-point support, so that the stability of the upper main rotor group 60 is better than that of the conventional technology. Therefore, the degree of shaking of the relatively small main shaft 50 is smaller than that of the conventional technology. The main spindle 40 and the main spindle 40 drive the upper main shaft synchronously by the upper coaxial double-rotor swashplate phase fixing base 100, the lower coaxial double-rotor swashplate phase fixing base 110, and a plurality of first connecting rods 121 and a plurality of third connecting rods 123 (see FIG. 8a). When the rotor group 60 and the lower main rotor group 70 are inclined with respect to the fuselage 10 to change the flight angle of the present invention and are inclined with respect to the fuselage 10, the tilt angles of the aerodynamic configurations 80 of the upper rotor blades are smaller than those of conventional techniques. Therefore, compared with the conventional technology, the present invention can be closer to flying at a preset angle.

Preferably, the support structures 66 respectively extend through and are 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 extending directions perpendicular to the upper extending arms 612 are shown in FIG. 6a; the distance between each supporting structure 66 and the adjacent two supporting structures 66 is equal. More specifically, the extending directions of the protruding portions 6314 are parallel to the extending directions of the upper extending arms 612, respectively. An axis 63141 of each protruding portion 6314 is directly above the axis 6121 of the corresponding upper extending arm 612. As shown in FIG. 6a; a hole 63142 is respectively opened at the bottom of the protrusions 6314, and the holes 63142 respectively extend through and are perpendicular to the axis 63141 of the protrusions 6314; that is, the holes 63142 They are respectively located on the axis 63141 of the protrusions 6314, and are perpendicular to the extension direction of the protrusions 6314, respectively, as shown in FIG. 6d; the top of the upper main rotor fixing base 61 is provided with three perforations 614, and the perforations 614 respectively extend through and are perpendicular to the axis 6121 of the upper extension arms 612, and are located directly below the holes 63142, as shown in FIG. 6a; that is, the perforations 614 are located at the upper extension arms 612, respectively. The axis 6121 is perpendicular to the extending direction of the upper extending arms 612. Preferably, the perforations 614 further extend through the bottom of the upper main rotor fixing base 61 (not shown). In this embodiment, the holes 63142 are respectively located directly above the junctions of the upper base 611 and the upper extension arms 612, and the perforations 614 are respectively located at the junctions of the upper base 611 and the upper extension arms 612. Up, as shown in Figure 6a. In other embodiments, the protrusions 6314 may extend longer than shown in the embodiment of FIG. 6a, so that the holes 63142 are located above the upper extension arms 612, and the perforations 614 are located at On the upper extending arms 612, nothing is impossible. Two ends of the supporting structures 66 are respectively inserted in the holes 63142 and the perforations 614. Preferably, the holes 63142 are screw holes, and the outer sides of the supporting structures 66 are screw-shaped near the top end and are screwed in the holes 63142, as shown in FIG. 6d. In this way, the support structures 66 can provide the most stable three-point support effect, and make the upper main rotor group 60 have the best stability, so it will not shake relative to the small main shaft 50, and then the small main shaft 50 and the large main shaft. 40 The upper main rotor group 60 is synchronously driven by the upper coaxial double-rotor swashplate phase fixing base 100 and the lower coaxial double-rotor swashplate phase fixing base 110 and a plurality of first links 121 and a plurality of third links 123 (see FIG. 8a). When tilting with the lower main rotor group 70 relative to the fuselage 10 to change the flight angle of the present invention and tilting relative to the fuselage 10, the tilt angles of the upper rotor blade aerodynamic configurations 80 reach the effect of zero error and truly remain consistent; With this, the present invention can accurately maintain the flight at a preset angle and completely solve the problems of the conventional technology.

It is worth mentioning that since the present invention has at least three support structures 66, the sliding and strength of the three support structures 66 are sufficient to improve the problem of easy deformation of the prior art, so that the stability of the upper main rotor group 60 can be maintained at a certain level. , At least retain the effect of "the tilt angle of the upper rotor blade aerodynamic configuration 80 is smaller than the conventional technology error"; thus, compared with the conventional technology, the present invention still maintains closer to the preset angle The effect of the upward flight will not cause the loss of the effect of "improving the stability of the upper main rotor group 60" due to the rotation deformation.

Please refer to FIG. 8a, which is an enlarged three-dimensional schematic diagram of the coaxial dual-rotor mechanism of the present invention. The lower main rotor set 70 includes a lower main rotor fixing base 71. The lower main rotor fixing base 71 is disposed on the main shaft 40 and includes a lower base body 711, at least three lower extension arms 712, and at least three lower paddle chucks 713. In fact, the structure of the lower base body 711 of the lower main rotor fixed seat 71, the lower extension arms 712, and the lower paddle chucks 713 and their connection relationship are substantially the same as those of the upper seat of the upper main rotor fixed seat 61. 611. The components such as the upper extension arms 612 and the upper paddle chucks 613 and their connection relationships are similar, so they are not described herein again. It is worth mentioning that the lower main rotor group 70 does not include a coaxial double rotor direction control fixed seat 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 dual-rotor turbine-driven unmanned vehicle mechanism system of the present invention. FIG. 7a is a first embodiment of the aerodynamic configuration of the upper and lower rotor blades of the present invention. In a top view, FIG. 7b is a 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 coupling portion 92, and a lower wing tip portion 93.

The upper and lower blade bodies 81 and 91 are linear, and the two ends in the length 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 The side edges 813, 913 and a second side edge 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 sides 813, 913 of the upper and lower blade bodies 81, 91 toward the second of the upper and lower blade bodies 81, 91. The curvature of the sides 814, 914 is larger than the top surfaces 815, 915 of the upper and lower blade bodies 81, 91. From the first sides 813, 913 of the upper and lower blade bodies 81, 91, the upper and lower blade bodies 81 are curved. The curved curvature of the second side edges 814 and 914 of the first and second blades 91 and 91 makes the heights of the top surfaces 815 and 915 and the bottom surfaces 816 and 916 of the upper and lower blade bodies 81 and 91 inconsistent and uneven. 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 larger than the top surfaces of the upper and lower blade bodies 81, 91. 815, 915 arc length from the first side 813, 913 to the second side 814, 914, that is, the top surfaces 815, 915 of the upper and lower blade bodies 81, 91 are longer than the upper and lower blade bodies 81 The bottom surfaces 816, 916 of 91 are also flat. More specifically, in this embodiment, the top surfaces 815, 915 of the upper and lower blade bodies 81, 91 are bent upward from the first sides 813, 913 of the upper and lower blade bodies 81, 91, and then flattened. Ground extends to the second sides 814, 914 of the upper and lower blade bodies 81, 91; the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 are from the first sides of the upper and lower blade bodies 81, 91 813 and 913 are bent down first, and then bent up to the second sides 814 and 914 of the upper and lower blade bodies 81 and 91. Generally, the first sides 813 and 913 of the upper and lower blade bodies 81 and 91 are front sides, and the second sides 814 and 914 of the upper and lower blade bodies 81 and 91 are rear sides. The upper and lower rotor blades are When the aerodynamic configuration 80, 90 rotates, it usually rotates in the backward direction; thereby, when the airflow passes through the upper and lower rotor blades aerodynamic configuration 80, 90, the bottom surfaces 816 of the upper and lower blade bodies 81, 91, The vortex generated by 916 is sufficient to make the lift produced by the present invention greater than that produced by conventional techniques.

The upper and lower coupling portions 82 and 92 are provided on the first ends 811 and 911 of the upper and lower blade bodies 81 and 91 and on the upper and lower blade chucks 613 and 713, as shown in FIGS. 7a and 5.

The upper and lower wing tips 83, 93 are provided on the second ends 812, 912 of the upper and lower blade bodies 81, 91, and extend on the same plane as the upper and lower blade bodies 81, 91, and away from the upper, The lower joint portions 82 and 92 and the first side edges 813 and 913 of the upper and lower blade bodies 81 and 91 extend in directions, so that the length directions of the upper and lower wing tip portions 83 and 93 are different from the upper and lower blade bodies 81 And 91 have 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 tip portions 83 and 93 are different from the extending directions of the upper and lower blade bodies 81 and 91. Since the first sides 813 and 913 of the upper and lower blade bodies 81 and 91 are front sides and the second sides 814 and 914 of the upper and lower blade bodies 81 and 91 are rear sides, the upper and lower wing tips 83 , 93 are essentially obliquely rearward of the upper and lower blade bodies 81 and 91 and present a "swept back" pattern. As a result, when the vortex line leaves the lift line, it will no longer remain perpendicular to the lift line, so the improved induction line analysis method can be used to correct the induction speed generated by the upward direction of the lift line, thereby improving the tip of the upper and lower wings. The eddy current characteristics of 83 and 93 make the lift generated by the present invention greater than that produced by the conventional technology, and at the same time can reduce the possibility of regional vibration waves generated by the upper and lower wing tips 83 and 93 under high-speed rotation. To achieve the effect of reducing resistance. The above effect can have significant effects when the angle of the included angle Θ1 is 20 to 45 degrees; especially when the angle of the included angle Θ1 is 35 degrees, the above effects can achieve the best. Among them, the widths of the upper and lower wing tip portions 83 and 93 are gradually tapered away from the upper and lower blade bodies 81 and 91 toward the second ends 812 and 912 of the upper and lower blade bodies 81 and 91, that is, The widths of the upper and lower wing tip portions 83 and 93 are gradually tapered to the oblique rear of the upper and lower blade bodies 81 and 91, so as to help enhance the above effects.

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

In the second embodiment, "the upper and lower wing tips 83, 93 and the upper and lower blade bodies 81, 91 extend on the same plane, and are away from the upper and lower joints 82," the first embodiment is omitted. , 92, and the first side edges 813, 913 of the upper and lower blade bodies 81, 91 extend so that the length direction of the upper and lower wing tip portions 83, 93 is different from the length of the upper and lower blade bodies 81, 91 It has technical characteristics such as an angle θ1 with the longitudinal direction of the upper and lower blade bodies 81 and 91, and retains the bottom surfaces 816 and 916 of the upper and lower blade bodies 81 and 91 from the upper and lower blades of the first embodiment. The first side edges 813, 913 of the blade bodies 81, 91 go up and down, and the second side edges 814, 914 of the blade bodies 81, 91 have a curved curvature greater than the top surfaces 815, 915 of the upper and lower blade bodies 81, 91. The curvature from the first sides 813, 913 of the upper and lower blade bodies 81, 91 to the second sides 814, 914 of the upper and lower blade bodies 81, 91 is curved, so that the upper and lower blade bodies 81, 91 The top and bottom surfaces 815 and 915 and the bottom surface 816 and 916 have different heights and inconsistencies and are asymmetrical "and other technical characteristics and their effects. As for the relationship between the upper and lower wing tip portions 83 and 93 and the upper and lower blade bodies 81 and 91 of the second embodiment, there is no particular limitation. For example, the upper and lower wing tip portions 83, 93 of the second embodiment may extend on a different plane from the upper and lower blade body 81, 91, that is, the upper and lower wing tip portions 83, 93 are relatively upward , The lower blade bodies 81, 91 are vertically upward, vertically downward, inclined upward, or inclined downward. Alternatively, the upper and lower wing tips 83, 93 and the upper and lower blade bodies 81, 91 extend on the same plane, and extend linearly in a direction away from the upper and lower joint portions 82, 92, so that the length direction is equal to the upper direction The longitudinal directions of the lower blade bodies 81 and 91 are the same and parallel to the longitudinal directions of the upper and lower blade bodies 81 and 91. In general, any of the implementation forms of the second embodiment can collectively capture the aerodynamic configurations 80 and 90 of the upper and lower rotor blades called "asymmetric airfoil rotor airfoil, without swept-back wing tip".

In the third embodiment, "the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 are omitted 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 a curved curvature greater than the top surfaces 815, 915 of the upper and lower blade bodies 81, 91, from the first side edges 813 of the upper and lower blade bodies 81, 91. The curved curvature of the second side edges 814 and 914 of the upper and lower blade bodies 81 and 91 is caused by the upward and downward movements of the upper and lower blade bodies 81 and 91, so that the top and bottom surfaces 815 and 915 of the upper and lower blade bodies 81 and 91 and the bottom surfaces 816 and 916 are inconsistent. "Asymmetrical" and other technical features, retaining the "upper and lower wing tips 83 and 93 and the upper and lower paddle bodies 81 and 91 on the same plane extending from the upper and lower blades of the first embodiment, and combined away from the upper and lower The sections 82, 92 and the first side edges 813, 913 of the upper and lower blade bodies 81, 91 extend in directions such that the length direction of the upper and lower wing tip portions 83, 93 is different from the upper and lower blade bodies 81, 91. It has technical characteristics such as an angle θ1 ″ with the longitudinal direction of the upper and lower blade bodies 81 and 91 and their effects. As for the relationship between the top surfaces 815 and 915 and the bottom surfaces 816 and 916 of the upper and lower blade bodies 81 and 91 of the third embodiment, there is no particular limitation. For example, the top surfaces 815 and 915 and the bottom surfaces 816 and 916 of the upper and lower blade bodies 81 and 91 of the third embodiment are upward from the first sides 813 and 913 of the upper and lower blade bodies 81 and 91, The second sides 814, 914 of the lower blade bodies 81, 91 have the same curvature, and the top surfaces 815, 915 of the upper and lower blade bodies 81, 91 are from the first sides of the upper and lower blade bodies 81, 91. 813, 913 bend upward first, then bend down 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 from the upper and lower blade bodies The first sides 813, 913 of 81, 91 are bent down first, and then bent up to the second sides 814, 914 of the upper and lower blade bodies 81, 91, so that the top surfaces of the upper and lower blade bodies 81, 91 The 815, 915 and the bottom surface 816, 916 have the same height fluctuations. The third embodiment of this embodiment can be referred to as the aerodynamic configuration of the upper and lower rotor blades of a "symmetry wing rotor airfoil with swept-back wing tips". 80, 90. Alternatively, the bottom surfaces 816, 916 of the upper and lower blade bodies 81, 91 go from the first sides 813, 913 of the upper and lower blade bodies 81, 91 toward the second sides 814 of the upper and lower blade bodies 81, 91. , 914 The curvature of the curvature is smaller than that of the top surfaces 815, 915 of the upper and lower blade bodies 81, 91 from the first sides 813, 913 of the upper and lower blade bodies 81, 91 toward the upper and lower blade bodies 81, 91. The curved curvature of the second side edges 814 and 914 makes the top and bottom surfaces 815 and 915 and bottom surfaces 816 and 916 of the upper and lower blade bodies 81 and 91 inconsistent and undulating and asymmetric. The third aspect of this embodiment The embodiment may be referred to as the aerodynamic configuration 80, 90 of the upper and lower rotor blades of the "second asymmetric airfoil with swept-back wing tips".

Please refer to FIG. 7c, Table 1 and Table 2. FIG. 7c is a lift comparison diagram of a conventional coaxial double-rotor turbine-driven unmanned vehicle mechanism system of the first embodiment and the second embodiment of the present invention. Lifting force comparison table of the known technology, the first embodiment and the second embodiment of the coaxial dual-rotor turbine-driven unmanned vehicle system at a pitch angle of 12 degrees and a rotation speed of 1000 RPM, 1200 RPM, and 1400 RPM, Table 2 Comparison of lift ratios of coaxial dual-rotor turbine-driven unmanned vehicle mechanism systems for conventional technology, the first embodiment and the second embodiment of the invention under the conditions of a pitch angle of 12 degrees and a rotation speed of 1000 RPM, 1200 RPM, and 1400 RPM form. Among them, 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> Know-how </ td> <td> Second Example </ td> <td> First example </ 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> Comparison of rotors </ td> <td> First embodiment / second embodiment </ td td> <td> First embodiment / known technology </ td> <td> Second embodiment / known technology </ td> </ tr> <tr> <td> Pitch angle 12 ˚ &amp; rotation speed 1000RPM Lift magnification difference at different times </ 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 magnification 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; RPM 1400RPM lift magnification difference </ td> <td> 1.040 times </ td> <td> 1.195 times </ td> <td> 1.149 times </ td> </ tr> </ TBODY > </ TABLE>

According to Fig. 7c, Tables 1 and 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 lift generated by the example is about 1.276 times the lift generated by the conventional technology. The lift generated by the second embodiment is about 1.128 times the lift generated by the conventional technology. At a pitch angle of 12 degrees and a rotation speed of 1200 RPM, etc. Under the conditions, the lift generated by the first embodiment is about 1.095 times the lift generated by the second embodiment, and the lift generated by the first embodiment is about 1.240 times the lift generated by the conventional technology. The lift generated by the example is about 1.132 times the lift generated by the conventional technology. Under the conditions of a pitch angle of 12 degrees and a rotation speed of 1400 RPM, the lift generated by the first embodiment is about the same as that produced by the second embodiment. 1.040 times the lift, the lift generated by the first embodiment is about 1.195 times the lift generated by the conventional technology, and the lift produced by the second embodiment is about 1.149 times the lift generated by the conventional technology. In general, under the conditions of a pitch angle of 12 degrees and a rotation speed of 1000 RPM, 1200 RPM, and 1400 RPM, the lift generated by the first embodiment is significantly greater than that produced by the second embodiment and the conventional technology. The lift generated by the example is greater than the lift generated by the conventional technology.

It is worth mentioning that, under the condition of the same pitch angle, the larger the rotation 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 dual-rotor turbo-drive unmanned vehicle mechanism system of the present invention. FIG. FIG. 8b is a perspective view of the upper inner ring phase fixing seat group of the present invention, FIG. 8c is an exploded view of the upper inner ring phase fixing seat group of the present invention, and FIG. 8d is a perspective view of the upper outer ring phase fixing seat group of the present invention. 8e is an exploded view of the upper outer ring phase fixing block group of the present invention. The upper coaxial double-rotor swashplate phase control fixed seat structure 100 includes an upper inner ring group 101, an upper outer ring group 102, an upper inner ring phase fixed seat group 103, and an upper outer ring phase fixed seat group 104.

The upper inner ring group 101 is sleeved on the small spindle 50 and has an upper inner ring head 1011. Specifically, the upper inner ring group 101 includes an upper ball bearing 1012, an upper ball collar 1013, and an upper inner ring base 1014. The small spindle 50 passes through a shaft hole of the upper ball bearing 1012, and the upper ball A ring 1013 is provided on the outer side of the upper ball bearing 1012. An upper inner ring base 1014 is provided on the outer side of the upper ball collar 1013 and a plurality of upper and lower ring heads 1011 protrude from the outer peripheral side of the upper portion, as shown in Figs. 8a and 8a. Figure 8b.

The upper outer ring group 102 is arranged on the upper inner ring group 101 and has an upper and outer ring head 1021. In more detail, the upper outer ring group 102 includes an upper ring bearing 1022 and an upper outer ring base 1023. The upper ring bearing 1022 is ringed on the outer peripheral side of the lower portion of the upper inner ring base 1014, and the upper outer ring base 1023 A ring is provided on the outside of the upper ring bearing 1022 and a plurality of upper and outer ring heads 1021 protrude from the outer peripheral side thereof, as shown in FIGS. 8a and 8d.

The upper inner ring phase fixing block group 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 pieces 1034, as shown in Figs. 8a, 8b and Figure 8c. The upper inner ring phase fixing base body 1031 is sleeved on the small main shaft 50 and is located above the upper inner ring group 101. The upper inner ring connecting piece 1032 has a first end and a second end. At least one upper inner ring fixing piece 1034 is screwed on the first end of the upper inner ring connecting piece 1032 and the upper inner ring phase fixing base body 1031, so that the upper The first end of the inner ring connecting member 1032 is fixed to the upper inner ring phase fixing base body 1031 by the upper inner ring fixing member 1034. The upper inner ring connecting handle 1033 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 handle 1033 and the second end of the upper inner ring connecting member 1032. The first end of the upper inner ring connecting handle 1033 is fixed to the second end of the upper inner ring connecting member 1032 by the upper inner ring fixing member 1034. The second end of the upper inner ring connecting handle 1033 is set on one of the upper inner ring heads 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. At least one upper inner ring fixing member 1034 is screwed on the first end of the first upper inner ring link 1035 and the upper inner ring phase fixing seat body 1031, so that the first end of the first upper inner ring link 1035 is the upper inner 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 on the first end of the second upper inner ring link 1036 and the second end of the first upper inner ring link 1035, so 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 connecting handle 1033 and the second end of the second upper inner ring connecting rod 1036, so that the first end of the upper inner ring connecting handle 1033 is the upper inner The ring fixing member 1034 is fixed to the second end of the second upper inner ring link 1036.

More specifically, the first upper inner link 1035 includes a connecting arm 10351, two extension arms 10352, and a handle 10353. The two upper arms 10352 of the first upper inner link 1035 extend from the first upper inner link The two ends of the connecting arm 10351 of 1035 extend and are defined as the first end of the first upper inner ring link 1035 and respectively have a perforation 10354. The perforations 10354 of the two extending arms 10352 of the first upper inner ring link 1035 are respectively transverse. Through both sides of the two extending arms 10352 of the first upper inner link 1035, the handle 10353 of the first upper inner link 1035 is away from the center of the first upper inner link 1035 The two extension arms 10352 of the inner ring link 1035 extend in the direction and are defined as the second end of the first upper inner ring link 1035 and open a screw hole 10355 penetrating the two sides thereof; the upper inner ring phase fixing body 1031 is located at In the space surrounded by the connecting arm 10351 and the two extension arms 10352 of the first upper inner ring link 1035, a screw hole 10311 is formed through the two sides of the first upper inner link 1035, and the two upper inner ring fixing members 1034 respectively pass through the first upper The perforations 10354 of the two extension arms 10352 of the inner ring link 1035 are respectively from the upper inner The two ends of the screw holes 1011 of the phase fixing base body 1031 are screwed in the screw holes 10311, so that the two extension arms 10352 of the first upper inner ring link 1035 are fixed by the two upper inner ring fixing members 1034 respectively in the upper inside. 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 two ends of the connecting arm 10361 of the second upper inner ring link 1036. A perforation 10363 is defined as the first end of the second upper inner ring link 1036, and the perforations 10363 of the two extension arms 10362 of the second upper inner ring link 1036 respectively penetrate the second upper inner ring link 1036 laterally. On both sides of the two extension arms 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 two extension arms 10362 of the second upper inner ring link 1036. The second upper inner ring The connecting arm 10361 of the connecting rod 1036 is defined as the second end of the second upper inner ring link 1036 and a perforation 10364 is opened. The perforating 10364 of the connecting arm 10361 of the second upper inner ring link 1036 penetrates the second upper inner ring longitudinally. The top and bottom of the connecting arm 10361 of the connecting rod 1036; preferably, the perforation 10364 of the connecting arm 10361 of the second upper inner ring connecting rod 1036 is located in the center of the connecting arm 10361 of the second upper inner ring connecting rod 1036; The inner ring fixing member 1034 passes through the two extension arms 1036 of the second upper inner ring link 1036 respectively. Two perforations 10363 are screwed into the screw holes 10355 from both ends of the screw holes 10355 of the shank portion 10353 of the first upper inner ring link 1035, so that the two extension arms 10362 of the second upper inner ring link 1036 The two upper inner ring fixing members 1034 are respectively fixed to 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 is provided with a screw hole 10331, and one of the upper inner ring is fixed The piece 1034 passes longitudinally through the through hole 10364 of the connecting arm 10361 of the second upper inner ring link 1036 and is screwed in the screw hole 10331 of the first end of the upper inner ring connecting handle 1033, so that the first end of the upper inner ring connecting 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 group 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 pieces 1044, as shown in Figs. 8a, 8d and Figure 8e. The upper outer ring phase fixing base body 1041 is sleeved on the small main shaft 50 and is located below the upper outer ring group 102. The upper outer ring connecting piece 1042 has a first end and a second end. At least one upper outer ring fixing piece 1044 is screwed on the first end of the upper outer ring connecting piece 1042 and the upper outer ring phase fixing base body 1041, so that the upper The first end of the outer ring connecting member 1042 is fixed to the upper outer ring phase fixing base body 1041 by the upper outer ring fixing member 1044. The upper outer ring connecting handle 1043 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 handle 1043 and the second end of the upper outer ring connecting member 1042. The first end of the upper outer ring connecting handle 1043 is fixed to the second end of the upper outer ring connecting member 1042 by the upper outer ring fixing member 1044. The second end of the upper outer ring connecting handle 1043 is set on one of the upper and outer ring heads 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 on the first end of the first upper outer ring link 1045 and the upper outer ring phase fixing base body 1041, so that the first end of the first upper outer ring link 1045 is fixed by the upper and outer rings. 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 on the first end of the second upper outer ring link 1046 and the second end of the first upper outer ring link 1045, so 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 on the first end of the upper outer ring connecting handle 1043 and the second end of the second upper outer ring connecting rod 1046, so that the first end of the upper outer ring connecting handle 1043 is upper and outer. The ring fixing member 1044 is fixed 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 extension arms 10452, and a handle 10453. The two upper arms 10452 of the first upper outer ring link 1045 extend from the first upper outer ring link. The two ends of the connecting arm 10451 of 1045 extend and are defined as the first end of the first upper outer ring link 1045 and each have a perforation 10454, and the perforations 10454 of the two extending arms 10452 of the first upper outer ring link 1045 are respectively transverse. Through both sides of the two extension arms 10452 of the first upper outer ring link 1045, the handle portion 10453 of the first upper outer ring link 1045 is far from the center of the connecting arm 10451 of the first upper outer ring link 1045. The two extension arms 10452 of the outer ring link 1045 extend in the direction and are defined as the second end of the first upper outer ring link 1045 and two screw holes 10455 are respectively opened on the two sides thereof; the upper outer ring phase fixing body 1041 is located at the first Two screw holes 10411 are opened in the space surrounded by the connecting arm 10451 and the two extending arms 10452 of the upper outer ring link 1045. The two upper outer ring fixing members 1044 pass through the first upper outer ring link 1045 respectively. The two extension arms 10452 are perforated 10454 and are screwed on 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 extension arms 10462. The two extending arms 10462 of the second upper outer ring link 1046 extend from two ends of the connecting arm 10461 of the second upper outer ring link 1046. It is defined as the first end of the second upper outer link 1046 and a perforation 10463 is respectively opened. The perforations 10463 of the two extension arms 10462 of the second upper outer link 1046 penetrate the second upper outer link 1046 laterally. On both sides of the two extension arms 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 two extension arms 10462 of the second upper outer ring link 1046. The second upper outer ring The connecting arm 10461 of the link 1046 is defined as the second end of the second upper outer ring link 1046 and a perforation 10464 is opened. The perforation 10464 of the connecting arm 10461 of the second upper outer ring link 1046 penetrates the second upper outer ring longitudinally. The top and bottom of the connecting arm 10461 of the connecting rod 1046; preferably, the perforation 10464 of the connecting arm 10461 of the second upper outer ring link 1046 is located in the center of the connecting arm 10461 of the second upper outer ring link 1046; The outer ring fixing member 1044 passes through the two extension arms 1046 of the second upper outer ring link 1046, respectively. The two perforations 10463 are screwed in the two screw holes 10455 of the handle 10453 of the first upper outer ring link 1045, respectively, so that the two extension arms 10462 of the second upper outer ring link 1046 are fixed by the two upper outer rings, respectively. The member 1044 is fixed to both sides of the handle 10453 of the first upper outer ring link 1045; the first end of the upper outer ring connecting handle 1043 defines a screw hole 10431, and one of the upper outer ring fixing members 1044 passes longitudinally through the second upper The perforation 10464 of the connecting arm 10461 of the outer ring link 1046 is screwed into the screw hole 10431 of the first end of the upper outer ring connecting handle 1043, so that the first end of the upper outer ring connecting handle 1043 is fixed by the upper outer ring fixing member 1044. The top of the connecting arm 10461 of the second upper outer ring link 1046 is fixed.

Please refer to FIG. 9a to FIG. 9f. FIG. 9a is a perspective enlarged schematic view of the coaxial double rotor mechanism of the present invention from another perspective. FIG. 9b is another perspective perspective view of the upper inner ring phase fixing block of the present invention. A perspective view of the lower inner ring phase fixed seat group with limited rotation angle. FIG. 9d is an exploded view of the lower inner ring phase fixed seat group with limited rotation angle. FIG. 9e is a lower inner ring phase with limited rotation angle of the invention. 9f is a cross-sectional view of the lower inner ring link rotating inwardly to the second position, and FIG. 9g is a view of the upper inner ring link rotating outward to the extreme limit and the lower inner ring link of the present invention. A perspective view that rotates inward to the second position. The lower coaxial double-rotor swashplate phase control fixed structure 110 includes a lower inner ring group 111, a lower outer ring group 112, a lower inner ring phase fixed seat group 113 that restricts a rotation angle, and a lower outer ring phase fixed seat group. A lower inner ring phase fixing block group 113 with a restricted rotation angle is provided between the main spindle 40 and the lower inner ring group 111 and includes a lower inner ring phase fixing block body 114, a lower inner ring connecting member 115, a lower inner ring connecting handle 116, and A limiting device 117. Basically, the main structure of the lower coaxial dual-rotor swashplate phase control mount structure 110 and the upper coaxial dual-rotor swashplate phase control mount structure 100 are substantially the same, and the difference between the two lies in: first, the upper coaxial dual-rotor swashplate phase control The phase control fixed structure 100 is arranged on the small main shaft 50 and is connected to the upper main rotor group 60 through a plurality of first links 121. Second, the upper and lower coaxial double-rotor swashplate phase control fixed structures 100 and 110 are provided by The plurality of second connecting rods 122 are connected; third, the lower coaxial double-rotor swashplate phase control fixing structure 110 is provided on the main shaft 40 and is connected to the lower main rotor group 70 through a plurality of third connecting rods 123 and is connected through a plurality of The fourth link 124 is connected to the fuselage 10; fourthly, the lower inner ring phase fixed seat group 113 of the lower coaxial double-rotor swashplate phase control fixed seat structure 110 that restricts the rotation angle includes a limiting device 117.

With this, the present invention improves the tightness of the combination of the upper inner ring phase fixing base body 1031, the upper inner ring connecting piece 1032, and the upper inner ring connecting handle 1033 by means of the upper inner ring fixing member 1034 in a screwing manner. The tightness of the upper outer ring phase fixing base body 1041, the upper outer ring connecting piece 1042, and the upper outer ring connecting handle 1043 is improved by the upper outer ring fixing part 1044 in a screwing manner, so that the upper inner ring phase fixing seat group The overall tightness of the overall structure of the 103 and the upper and outer ring phase fixing base groups 104 is improved; moreover, the lower inner ring phase fixing base body 114 and the lower inner ring connecting piece are screwed up by the lower inner ring fixing members. The tightness of the combination of 115 and the lower inner ring connecting handle 116, and at the same time, the lower outer ring phase fixing seat body, the lower outer ring connecting piece and the lower outer ring connecting handle are screwed up by the lower outer ring fixing member. The tightness of the combination makes the tightness of the overall structure of the lower inner ring phase fixed seat group 113 and the lower outer ring phase fixed seat group limited to the rotation angle. Therefore, when the upper and lower main rotor groups 60 and 70 are driven by the coaxial small and large main shafts 50 and 40 to rotate in opposite directions on the same axis, the coaxial double rotor mechanism 30 will generate vibration as a whole. At this time, the upper and lower inner ring connecting members will not loosen from the upper and lower inner ring phase fixing bases, and the upper and lower inner ring connecting handles will never loosen from the upper and lower inner ring connecting members. The outer ring connecting piece will not be loosened from the upper and lower outer ring phase fixing base body, and the upper and lower outer ring connecting handles will not be loosened from the upper and lower outer ring connecting piece at all, thereby maintaining the upper and lower coaxial double The function of the rotor swashplate phase control mount structure 100, 110 to change the flight angle of the present invention.

It is worth mentioning that when the materials of the upper inner ring fixing members 32 and the upper outer ring fixing members 42 are metal, the upper inner ring phase fixing base body 1031, the upper inner ring connecting member 1032, and the upper inner ring The three joints 1033 can be screwed together tighter by the upper inner ring fixing member 1034, while the upper outer ring phase fixing base body 1041, the upper outer ring connecting member 1042, and the upper outer ring connecting rod 1043 are also tightly connected. The upper and outer ring fixing members 1044 can be combined tighter by screwing, and the overall tightness and structural strength of the overall structure of the upper inner ring phase fixing base group 103 and the upper and outer ring phase fixing base group 104 can be further improved; more In addition, when the materials of the lower inner ring fixing members and the lower outer ring fixing members are 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 be all three. The lower inner ring fixing member is screwed tighter, and the lower outer ring phase fixing base 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 combines tighter 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. Accordingly, the upper and lower coaxial dual-rotor swashplate phase control fixed seat structures 100 and 110 of the present invention are less prone to wear, more durable, and have a longer life.

Differences between the lower inner ring phase fixing seat group 113 and the upper inner ring phase fixing seat group 103 that limit the rotation angle will be further described below.

The lower inner ring phase fixing base body 114 is sleeved on the main 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 connecting handle 116 is disposed between the second lower inner ring link 1152 of the lower inner ring link 115 and the lower inner ring group 111. At least a part of the limiting device 117 is located between the inner side of the lower inner ring link 115 and the outer side of the main shaft 40. Among them, when the lower inner ring link 115 is rotated outward to a first position, the lower inner ring link 115 is far away from the main shaft 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 rotates inward to a second position, the limiting device 117 restricts the angle of the first lower inner ring link 1151 and the second lower inner ring link 1152 of the lower inner ring link 115 to rotate inward. So that the inside of the lower inner ring link 115 is separated from the outside of the major spindle 40 by a distance, as shown in Figures 9f and 9g; at this time, the lower inner ring link 115 is rotated inward to the maximum while the upper inner ring The connecting member 1032 is rotated outward to the maximum limit, so that the deflection angle of the combination of the lower inner ring group 111 and the lower outer ring group 112 with respect to the major axis 40 is equal to the combination of the upper inner ring group 101 and the upper outer ring group 102. The state of the deflection angle of the small main shaft 50 accurately controls the upper main rotor group 60 and the lower main rotor group 70 to deflect relative to the fuselage synchronously, so that the present invention 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 is provided with a perforation 11511. The limiting device 117 is provided in the perforation 11511 and one end thereof extends beyond the perforation 11511 and protrudes from the lower inside. The inside of the first lower inner ring link 1151 of the ring link 115 is shown in FIGS. 9c and 9e. When the lower inner ring link 115 rotates inward to the second position, the portion of the stop 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 main shaft 40, such as 9f and 9g. 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 One end 11521 and one second end 11522. The first end 11512 of the first lower inner ring link 1151 of the lower inner ring link 115 is pivoted to the lower inner ring phase fixing base body 114, and the first The second end 11513 of the lower inner ring link 1151 is pivoted on the first end 11521 of the second lower inner ring link 1152 of the lower inner ring link 115, and the lower inner ring connecting handle 116 is provided on the lower inner ring link 115 The second end 11522 of the second lower inner ring link 1152, the perforation 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 is close to the lower inner ring The first end 11512 of the first lower inner ring link 1151 of the link 115 is shown in Figs. 9d and 9e.

In a preferred embodiment, the position-limiting device 117 can adjust the degree that it protrudes from the inside of the first lower inner ring link 1151 of the lower inner ring link 115. Therefore, the user can adjust the angle between the first lower inner ring link 1151 and the second lower inner ring link 1152 when the lower inner ring link 115 is rotated inward to the second position. Preferably, the perforation 11511 of the first lower inner ring link 1151 of the lower inner ring connecting member 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 11712; the screw 11711 of the bolt 1171 has an external thread, and the screw is provided in the perforation 11511, and an end thereof near the main shaft 40 extends beyond the perforation 11511 and protrudes from the first lower inner ring link 1151 of the lower inner ring link 115 Inside; the head 11712 of the bolt 1171 is provided on the end of the screw 11711 away from the main spindle 40, and the nut 1172 is screwed on the end of the screw 11711 of the bolt 1171 near the main spindle 40. Thereby, the user can directly adjust the extent to which the bolt protrudes inside the first lower inner ring link 1151 of the lower inner ring link 115, or by adjusting the nut 1172 and the first lower inner ring of the lower inner ring link 115 The distance of the inner side of the ring link 1151 controls the extent to which the limiter 117 protrudes from the inside of the first lower inner ring link 1151 of the lower inner ring link 115. In other embodiments, the nut 1172 may be omitted, so that the limiting device 117 includes only the bolt 1171. In other embodiments, the limiting device 117 may also be a latch.

In another preferred embodiment, the limiting device 117 is integrally formed on the inside of the first lower inner ring link 1151 of the lower inner ring link 115, so that the limiting device 117 protrudes from the first link of the lower inner ring link 115. The degree of the inner side of the lower inner ring link 1151 remains fixed (that is, permanent and cannot be adjusted), so that when the lower inner ring link 115 rotates inward to the second position, the first of the lower inner ring link 115 The angle of the included angle Θ3 between the lower inner ring link 1151 and the second lower inner ring link 1152 is kept constant, which can ensure that the limit device 117 will not be adjusted to the wrong degree of protrusion (for example: too much protrusion, too short protrusion, completely shrinking Into the perforation without protruding or even being completely removed), to avoid the deflection angle of the combination of the lower inner ring group 111 and the lower outer ring group 112 relative to the major axis 40 compared to the combination of the upper inner ring group 101 and the upper outer ring group 102 The minor spindle 50 is inconsistent. Furthermore, the limiting device 117 in this embodiment has the advantages of not being easy to wear and having good durability.

In other embodiments, the limiting device 117 may also be provided on the major axis 40 and at least a part is located between the inner side of the lower inner ring link 115 and the outer side of the major axis 40, which can also achieve the above-mentioned preferred embodiment. efficacy.

It is worth mentioning that when the lower inner ring link 115 is rotated inward to the first position, the angle between the first lower inner ring link 1151 and the second lower inner ring link 1152 of the lower inner ring link 115 is an angle Θ2 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 link of the lower inner ring link 115 The angle of the included angle Θ3 of the ring link 1152 is less than or equal to 170 °; within the above-mentioned angle range (that is, within the range of the included angle Θ2 and the included angle Θ3 between 110 ° and 170 °), the present invention can more reliably reduce the following The deflection angle of the combination of the inner ring group 111 and the lower outer ring group 112 with respect to the large main shaft 40 is maintained at a state equal to the deflection angle of the combination of the upper inner ring group 101 and the upper outer ring group 102 with respect to the small main shaft 50, which is more accurate. The upper main rotor group 60 and the lower main rotor group 70 are controlled to deflect synchronously with respect to the fuselage, so that the present invention can change the flight angle more stably without losing control.

In summary, the transmission output structure 21 of the turbo engine 20 of the coaxial dual-rotor turbo-drive unmanned vehicle mechanism system of the present invention is more convenient and quicker for replacement, disassembly, and other applications, and is conducive to manufacturing, saving replacement and maintenance time; The coaxial dual-rotor turbodrive unmanned vehicle mechanism system of the present invention has good sliding stability of the upper main rotor group 60 of the coaxial dual-rotor mechanism 30, and the degree of shaking with respect to the small main shaft 50 of the coaxial dual-rotor mechanism 30 is small; the coaxial of the present invention The upper and lower rotor blade aerodynamic configurations 80 and 90 of the coaxial double-rotor mechanism 30 of the dual-rotor turbine-driven unmanned vehicle mechanism system have good lift and drag reduction effects; the coaxial double-rotor turbine-driven unmanned vehicle mechanism system of the present invention The function of changing the flight angle of the present invention by maintaining the upper and lower coaxial double rotor swashplate phase control mount structures 100 and 110 of the coaxial double rotor mechanism 30 and accurately controlling the upper and lower main rotor groups 60 of the coaxial double rotor mechanism 30 The 70 and 70 are deflected synchronously with respect to the fuselage 10, so that the present invention can stably change the flight angle. With this, the present invention has comprehensively evolved in all aspects of flight capability, safety, stability, processing, manufacturing, disassembly and the like.

The above are only used to explain the preferred embodiments of the present invention, and are not intended to limit the present invention in any form. Therefore, any modification or change related to the present invention made under the same creative spirit Should still be included in the scope of the present invention.

A‧‧‧ Upper and lower rotor blade aerodynamic configuration
A1‧‧‧ Paddle Body
A13‧‧‧First side
A14‧‧‧Second side
A15‧‧‧Top
A16‧‧‧ Underside
A2‧‧‧Combination
A3‧‧‧wing tip
10‧‧‧Airframe
20‧‧‧Turbine engine
21‧‧‧Drive output structure
22‧‧‧Turbine engine
221‧‧‧Engine body
222‧‧‧Turbine drive shaft
223‧‧‧Fixed ring
2231‧‧‧Fixing screw holes
224‧‧‧ tube
23‧‧‧ adapter
231‧‧‧Adapter ring
2311‧‧‧Adapter screw hole
232‧‧‧Adapter
2321‧‧‧Output screw hole
233‧‧‧shaft hole
24‧‧‧ Adapter Screw
25‧‧‧output gear
251‧‧‧ Gear tube
2511‧‧‧Gear screw hole
252‧‧‧shaft hole
253‧‧‧Output Gear
26‧‧‧Gear Screw
27‧‧‧Drive gear
271‧‧‧ transmission gear
30‧‧‧ Coaxial Double Rotor Mechanism
40‧‧‧ Major Spindle
50‧‧‧ small spindle
60‧‧‧ Upper main rotor group
61‧‧‧Upper main rotor mount
611‧‧‧ Upper seat
6111‧‧‧ Upper body shaft hole
6112‧‧‧ axis
612‧‧‧ Upper extension arm
6121‧‧‧ axis
613‧‧‧Upper paddle chuck
614‧‧‧perforation
62‧‧‧Coaxial double-rotor direction control fixing structure
63‧‧‧ Ontology
631‧‧‧ base
6311‧‧‧ cantilever
6312‧‧‧Base shaft hole
6313‧‧‧ axis
6314‧‧‧ protrusion
63141‧‧‧ axis
63142‧‧‧hole
632‧‧‧ Pivot
64‧‧‧ shaft
65‧‧‧ connecting rod
66‧‧‧ support structure
70‧‧‧ lower main rotor group
71‧‧‧ Lower Main Rotor Mount
711‧‧‧lower body
712‧‧‧ Lower extension arm
713‧‧‧ Lower Paddle Chuck
80‧‧‧ Upper rotor blade aerodynamic configuration
81‧‧‧Upper blade body
811‧‧‧ the first end
812‧‧‧second end
813‧‧‧first side
814‧‧‧second side
815‧‧‧Top
816‧‧‧ Underside
82‧‧‧ Upper Joint
83‧‧‧ Upper wing tip
90‧‧‧ lower rotor blade aerodynamic configuration
91‧‧‧ lower blade body
911‧‧‧ the first end
912‧‧‧second end
913‧‧‧first side
914‧‧‧second side
915‧‧‧Top
916‧‧‧underside
92‧‧‧ lower joint
93‧‧‧ lower wing tip
100‧‧‧ Upper coaxial double rotor swashplate phase control fixed seat
101‧‧‧ Upper Inner Ring
1011‧‧‧ Upper Inner Globe Head
1012‧‧‧up ball bearing
1013‧‧‧up ball collar
1014‧‧‧ Upper inner ring base
102‧‧‧Sheung Wai Wan Group
1021‧‧‧Shangwai Global Head
1022‧‧‧Upper ring bearing
1023‧‧‧ Upper outer ring base
103‧‧‧ Upper inner ring phase fixing block group
1031‧‧‧ Upper inner ring phase fixing base body
10311‧‧‧Thread hole
1032‧‧‧ Upper inner ring connector
1033‧‧‧ Upper inner ring adapter
10331‧‧‧Thread hole
1034‧‧‧ Upper inner ring fastener
1035‧‧‧First upper inner link
10351‧‧‧Connecting arm
10352‧‧‧Extended arm
10353‧‧‧Handle
10354‧‧‧perforation
10355‧‧‧Thread hole
1036‧‧‧Second upper inner link
10361‧‧‧Connecting arm
10362‧‧‧Extended arm
10363‧‧‧perforation
10364‧‧‧perforation
104‧‧‧ Upper Outer Ring Phase Fixed Block Set
1041‧‧‧Upper outer ring phase fixing base body
10411‧‧‧Thread hole
1042‧‧‧ Upper outer ring connector
1043‧‧‧ Upper outer ring adapter
10431‧‧‧Thread hole
1044‧‧‧ Upper outer ring fixings
1045‧‧‧First upper outer link
10451‧‧‧Connecting arm
10452‧‧‧Extended arm
10453‧‧‧Handle
10454‧‧‧perforation
10455‧‧‧Thread hole
1046‧‧‧Second upper outer link
10461‧‧‧Connecting arm
10462‧‧‧Extended arm
10463‧‧‧perforation
10464‧‧‧perforation
110‧‧‧ lower coaxial dual-rotor swashplate phase control fixed seat structure
111‧‧‧ Lower inner ring group
112‧‧‧Lower outer ring group
113‧‧‧Lower inner ring phase fixed seat group with limited rotation angle
114‧‧‧ Lower inner ring phase fixing base body
115‧‧‧ Lower inner ring connector
1151‧‧‧First lower inner link
11511‧‧‧perforation
11512‧‧‧ the first end
11513‧‧‧ second end
1152‧‧‧Second lower inner link
11521‧‧‧ the first end
11522‧‧‧second end
116‧‧‧ Lower inner ring adapter
117‧‧‧ limit device
1171‧‧‧Bolt
11711‧‧‧Screw
11712‧‧‧Head
1172‧‧‧nut
121‧‧‧ First connecting rod
122‧‧‧Second Link
123‧‧‧Third Link
124‧‧‧ Fourth link Θ1 ~ 3‧‧‧ included angle

FIG. 1 is a plan view of a conventional rotor blade. Fig. 2 is a sectional view of a conventional rotor blade. FIG. 3 is a schematic diagram of a coaxial dual-rotor turbine-driven unmanned vehicle mechanism system of the present invention. 4a is a perspective view of a transmission output structure of a turbine engine according to the present invention. Fig. 4b is an exploded view of the transmission output structure of the turbine engine of the present invention. 4c is a side view of a transmission output structure of a turbine engine according to the present invention. 4d is a sectional view of a transmission output structure of a turbine engine according to the present invention. FIG. 5 is a perspective view of a coaxial double-rotor mechanism of the present invention. Fig. 6a is a schematic diagram of the upper main rotor group of the present invention. Fig. 6b is a perspective view of the coaxial double-rotor direction control fixing base structure of the present invention. FIG. 6c is an exploded view of the coaxial double-rotor direction control fixing base structure of the present invention. Fig. 6d is another angle exploded view of the coaxial double-rotor direction control fixing base structure of the present invention. 7a is a top view of a first embodiment of the aerodynamic configuration of the upper and lower rotor blades of the present invention. 7b is a cross-sectional view of a 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 lift comparison diagram of a coaxial twin-rotor turbo-drive unmanned vehicle mechanism system of the conventional technology, the first embodiment and the second embodiment of the present invention. FIG. 8a is an enlarged perspective view of the coaxial double-rotor mechanism of the present invention. FIG. 8b is a perspective view of an upper inner ring phase fixing seat group according to the present invention. FIG. 8c is an exploded view of the upper inner ring phase fixing block group of the present invention. FIG. 8d is a perspective view of an upper outer ring phase fixing seat group according to the present invention. FIG. 8e is an exploded view of the upper outer ring phase fixing seat group of the present invention. FIG. 9a is another perspective enlarged schematic 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 group according to the present invention. FIG. 9c is a perspective view of a lower inner ring phase fixing seat group with a restricted rotation angle according to the present invention. FIG. 9d is an exploded view of the lower inner ring phase fixing seat group with limited rotation angle according to the present invention. 9e is a cross-sectional view of a lower inner ring phase fixing seat group with a restricted rotation angle according to the present invention. FIG. 9f is a cross-sectional view of the lower inner ring link of the present invention rotated inward to a second position. 9g is a perspective view of the upper inner ring link rotating outward to the extreme limit and the lower inner ring link rotating inward to a second position according to the present invention.

Claims (10)

A coaxial dual-rotor turbine-driven unmanned vehicle mechanism system includes: a fuselage; a turbine engine disposed on the fuselage and including a transmission output structure, the transmission output structure including a turbine engine, an adapter and an output Gear, the turbine engine includes an engine body, a turbine transmission shaft, and a fixing ring, the turbine transmission shaft is rotatably disposed on the engine body and one side thereof protrudes from one side of the engine body, and the fixing ring is disposed on the One end of the turbine transmission shaft, the adapter seat is provided on the fixed ring, the output gear is provided on the adapter seat, and a coaxial double rotor mechanism includes: a large main shaft rotatably provided on the fuselage, extending through It passes through the top of the fuselage and has a shaft hole; a small main shaft is rotatably provided in the fuselage and extends through the shaft hole of the large main shaft; an upper main rotor group includes an upper main rotor fixing seat and a A coaxial double-rotor direction control fixed seat structure. The upper main rotor fixed seat is provided on the small main shaft and includes a plurality of upper paddle chucks. The seat structure is provided on the upper main rotor fixing seat and includes a body, a shaft, a plurality of links and at least three supporting structures. The body is located above the upper main rotor fixing seat and is coaxial with the upper main rotor fixing seat. A rod is provided between the body and the upper main rotor fixed seat and extends on an axis of the body and an upper axis of the upper main rotor fixed seat, and the links are respectively provided on the outer side of the body and fixed to the upper main rotor. Between the outer sides of the seats, the supporting structures are respectively arranged around the shaft between the bottom of the body and the top of the upper main rotor fixed seat; the lower main rotor group includes the lower main rotor fixed seat, and the lower main rotor The fixed seat is arranged on the main shaft and includes a plurality of lower paddle chucks; a plurality of upper rotor blade aerodynamic configurations, each including an upper paddle body, an upper joint portion and an upper wing tip portion, the upper paddle body is linear , The two ends in the length direction are respectively defined as a first end and a second end, and the two sides in the width direction are defined as a first side and a second side, respectively, and have a top surface and a bottom surface, The The joint portion is provided on the first end of the upper blade body and on the upper paddle chuck, the upper wing tip portion is provided on the second end of the upper blade body, and is on the same plane as the upper blade body Extending, and extending away from the upper joint portion and the first side of the upper blade body, so that the length direction of the upper wing tip is different from the length direction of the upper blade body and the upper blade body There is an included angle in the length direction; the aerodynamic configuration of a plurality of lower rotor blades each includes a lower blade body, a lower joint portion and a lower wing tip portion, the lower blade body is linear, and the two ends in the length direction are respectively defined as one The first end and the second end, 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, and the lower joint portion is provided on the lower blade body The first end of the lower blade is provided on the lower paddle chuck, the lower wing tip portion is provided on the second end of the lower blade body, extends on the same plane as the lower blade body, and away from the lower joint portion And the direction of the first side of the lower blade body extends so that It is obtained that the length direction of the lower wing tip is different from the length direction of the lower blade body and has an angle with the length direction of the lower blade body; an upper coaxial double-rotor swashplate phase control fixed seat structure, including an upper inner Ring group, an upper outer ring group, an upper inner ring phase fixing block group and an upper outer ring phase fixing block group, the upper inner ring group is sleeved on the small main shaft and has an upper inner ring head, and the upper outer ring The group ring is arranged on the upper inner ring group and has an upper and outer ring head. The upper inner ring phase fixing seat group includes an upper inner ring phase fixing body, an upper inner ring connecting piece, an upper inner ring connecting handle and a plurality of rings. An upper inner ring fixing member, the upper inner ring phase fixing seat body 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 on the upper main ring fixing member; The first end of the inner ring link member and the upper inner ring phase fixing base body, so that the first end of the upper inner ring link member is fixed to the upper inner ring phase fixing base body by the upper inner ring fixing member, and the upper inner ring The ring joint has a first end and a second end, and at least one of the inner ring is fixed. A screw is provided on the first end of the upper inner ring connecting handle and the second end of the upper inner ring connecting piece, so that the first end of the upper inner ring connecting handle is fixed to the upper inner ring by the upper inner ring fixing member. The second end of the connecting piece, the second end of the upper inner ring connecting handle is provided on the upper inner ring head, and the upper outer ring phase fixing seat group includes 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 outer A ring fixing member is screwed on the first end of the upper outer ring connecting member and the upper outer ring phase fixing base body, so 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. The phase fixing base body, the upper outer ring connecting handle has a first end and a second end, at least one upper outer ring fixing piece is screwed on the first end of the upper outer ring connecting piece and the upper outer ring connecting piece The second end, so that the first end of the upper outer ring connecting handle is fixed to the second end of the upper outer ring connecting member by the upper outer ring fixing member, and the upper outer ring connecting handle The second end is located on the upper and outer globe heads; and the lower coaxial double-rotor swashplate phase control fixed seat structure, including a lower inner ring group, a lower outer ring group, a lower inner ring phase fixed seat group with limited rotation angle and a lower Outer ring phase fixed seat group, the lower inner ring group is sleeved on the main shaft and has a lower inner ring head, the lower outer ring group ring is provided on the lower inner ring group and has a lower outer ring head, The lower inner ring phase fixing base group includes a lower inner ring phase fixing base body, a lower inner ring connecting piece, a lower inner ring connecting handle, a plurality of lower inner ring fixing pieces, and a limiting device. The lower inner ring phase fixing base body is sleeved. At the main spindle, the lower inner ring link includes a first lower inner ring link and a second lower inner ring link. 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 base body, so that The first end of the first lower inner ring link is fixed by the lower inner ring Fixed to the lower inner ring phase fixing base 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 The first end of the 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 lower inner ring connecting handle has a first end and a second end. An inner ring fixing member is screwed on the first end of the lower inner ring connecting handle and the second end of the second lower inner ring connecting rod, so that the first end of the lower inner ring connecting handle is fixed by the lower inner ring fixing member. At the second end of the second lower inner ring connecting rod, the second end of the lower inner ring connecting handle is provided at the lower inner ring head, and the limiting device is at least partly located inside the lower inner ring connecting member and the large Between the outer sides of the main shaft, wherein when the lower inner ring link rotates outward to a first position, the lower inner ring link moves away from the large main shaft; when the lower inner ring link rotates inward to a second position When in position, the limiting device limits the angle in which the first lower inner ring link and the second lower inner ring link rotate inward, so that the inner of the lower inner ring link The lower side is separated from the outside of the main shaft by a distance. The lower outer ring phase fixing seat group 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 pieces. The outer ring phase fixing base body is sleeved on the main shaft, the lower outer ring connecting piece has a first end and a second end, and at least the lower outer ring fixing piece is screwed on the first end of the lower outer ring connecting piece and The lower outer ring phase fixing base body, so that the first end of the lower outer ring connecting piece is fixed to the lower outer ring phase fixing base body by the lower outer ring fixing piece, and the lower outer ring connecting handle has a first end and A second end, at least the 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 The outer ring fixing member is fixed on the second end of the lower outer ring connecting member, and the second end of the lower outer ring connecting handle is provided on the lower outer ring. According to the coaxial double-rotor turbine-driven unmanned vehicle mechanism system described in the first patent application scope, wherein the fixed ring is provided with a fixed screw hole, the adapter seat is provided with an adapter screw hole, and the transmission output structure of the turbine engine Including an adapter screw, the adapter screw is screwed in the adapter screw hole and the fixing screw hole. According to the coaxial double-rotor turbine-driven unmanned vehicle mechanism system described in the first patent application scope, wherein the adapter seat is provided with an output screw hole, the output gear is provided with a gear screw hole, and the transmission output structure of the turbine engine includes A gear screw is screwed in the output screw hole and the gear screw hole. The coaxial dual-rotor turbo-drive unmanned vehicle mechanism system according to item 1 of the scope of the patent application, wherein the body includes a base and a plurality of pivot bases, and the pivot bases are pivotally arranged outside the base; the shaft It is located between the base and the upper main rotor fixed base and extends on the axis of the base and the axis of the upper main rotor fixed base; one end of the connecting rods is respectively pivoted on the outside of the pivot bases, The other ends are respectively pivoted outside the upper main rotor fixed base; the at least three supporting structures are rod-shaped and are respectively arranged between the bottom of the base and the top of the upper main rotor fixed base around the shaft. The coaxial dual-rotor turbine-driven unmanned vehicle mechanism system according to item 4 of the scope of the patent application, wherein the upper main rotor fixed base includes an upper base body and at least three upper extension arms, and the at least three upper extension arms protrude at intervals. An outer ring wall of the upper base body, the upper paddle chucks are respectively disposed at the ends of the at least three upper extension arms; the shaft is provided between the base and the upper base body and extends along the axis of the base and On the axis of the upper base body; the other ends of the connecting rods are respectively pivoted on the outside of the at least three upper extension arms; the at least three support structures respectively extend through and are perpendicular to the axis of the at least three upper extension arms, and each support structure The distance from the two adjacent supporting structures is equal. The coaxial dual-rotor turbine-driven unmanned vehicle mechanism system according to item 1 of the scope of patent application, wherein the bottom surface of the upper blade body is from the first side of the upper blade body to the second side of the upper blade body The curvature of the side curve 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, so that the top surface of the upper blade body and The height of the bottom surface is inconsistent and asymmetric; the curvature of the bottom surface of the lower blade body from the first side edge of the lower blade body to the second side edge of the lower blade body is greater than that of the lower blade body. The curvature of the top surface of the body is curved from the first side of the lower blade body to the second side of the lower blade body, so that the height fluctuations of the top and bottom surfaces of the lower blade body are inconsistent and asymmetric. . According to the coaxial dual-rotor turbine-driven unmanned vehicle mechanism system described in item 6 of the patent application scope, wherein the included angle is 20 to 45 degrees. The coaxial dual-rotor turbo-driven unmanned vehicle mechanism system according to item 1 of the scope of the patent application, wherein the upper outer ring link includes a first upper outer ring link and a second upper outer ring link. 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 phase fixing base body, so that the first end of the first upper outer ring link is fixed to the upper outer ring phase fixing base body by the upper outer ring fixing member, at least An upper outer ring fixing member is screwed on the first end of the second upper outer ring link and the second end of the first upper outer ring link, so that the first end of the second upper outer ring link is The upper outer ring fixing member is fixed to the second end of the first upper outer ring link, and at least one upper outer ring fixing member is screwed to the first end of the upper outer ring connecting handle and the second upper outer ring link. The second end, so that the first end of the upper outer ring connecting handle is fixed to the second end of the second upper outer ring connecting rod by the upper outer ring fixing member; wherein the lower outer ring connecting piece package Containing 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, and the lower second outer ring link has a first And a second end, at least the lower outer ring fixing member is screwed on the first end of the first lower outer ring link and the lower outer ring phase fixing seat body, so that the first of the first lower outer ring link The end is fixed to the lower outer ring phase fixing base body by the lower outer ring fixing member, and at least the lower outer ring fixing member is screwed to the first end of the second lower outer ring link and the first lower outer ring link. The second end, so that the first end of the second lower outer ring link 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 on the lower end The first end of the outer ring connecting handle and the second end of the second lower outer ring connecting rod, so that the first end of the lower outer ring connecting handle is fixed to the second lower outer ring connecting rod by the lower outer ring fixing member. The second end. The coaxial dual-rotor turbo-drive unmanned vehicle mechanism system according to item 1 of the scope of patent application, wherein the upper inner ring link includes a first upper inner ring link, and the first upper inner ring link includes a connection An arm and two extension arms, the two extension arms of the first upper inner ring link extending from two ends of the connecting arm of the first upper inner ring link and defined as the first end of the first upper inner ring link A perforation is respectively opened, and the perforations of the two extension arms of the first upper inner link are respectively penetrated laterally through the two sides of the two extension arms of the first upper inner link. The upper inner ring phase fixing seat body is located at the first A screw hole is formed in the space surrounded by the connecting arm of the upper inner ring link and the two extending arms, and two screw holes are formed through the two sides of the upper inner ring link. The perforations of the two extension arms are screwed into the screw holes from the two ends of the screw holes of the upper inner ring phase fixing base body, so that the two extension arms of the first upper inner ring link are respectively received by the two upper and inner rings. The ring fixing members are fixed on two sides of the upper inner ring phase fixing seat body; wherein, the first lower The inner ring link includes a connecting arm and two extension arms. Two extension arms of the first lower inner ring link extend from two ends of the connecting arm of the first lower inner ring link and are defined as the first lower inner link. The first ends of the ring links are respectively provided with a perforation, and the perforations of the two extension arms of the first lower inner ring link respectively penetrate the two sides of the two extension arms of the first lower inner ring link. The phase fixing seat body is located in the space surrounded by the connecting arm of the first lower inner ring link and the two extension arms and has a screw hole penetrating through the two sides thereof, wherein the two lower inner ring fixing pieces pass through the first and second transversely. The perforations of the two extension arms of the lower inner link are screwed into the screw holes from the two ends of the screw holes of the lower inner ring phase fixing base body, so that the two extensions of the first lower inner link The arms are respectively fixed to the two sides of the lower inner ring phase fixing seat body by the two lower inner ring fixing members. The coaxial dual-rotor turbo-drive unmanned vehicle mechanism system according to item 1 of the scope of patent application, wherein the first lower inner ring link is provided with a perforation, the limiting device is disposed at the perforation and one end thereof extends to the perforation. Outside, it protrudes from the inside of the first lower inner ring link, and when the lower inner ring link rotates inward to the second position, the limit device protrudes from the inside of the first lower inner ring link Partially abuts against the outside of the major axis.