CN216834272U

CN216834272U - Slow-cruise unmanned aerial vehicle

Info

Publication number: CN216834272U
Application number: CN202123059279.5U
Authority: CN
Inventors: 余新峰
Original assignee: Xiamen Yunlun Intelligent Technology Co ltd
Current assignee: Xiamen Yunlun Intelligent Technology Co ltd
Priority date: 2021-12-07
Filing date: 2021-12-07
Publication date: 2022-06-28
Anticipated expiration: 2031-12-07

Abstract

The utility model provides an unmanned aerial vehicle cruises slowly, for the unmanned aerial vehicle of many rotors of stationary vane combination, it includes: the lower end of the machine body is provided with a ventral fin; the fixed wing comprises a middle wing which is detachably arranged at the upper end of the machine body, power arms are detachably arranged at two ends, far away from the machine body, of the middle wing, one ends, far away from the middle wing, of the power arms are detachably provided with outer wings, the rear ends of the outer wings are provided with wing flaps and rolling ailerons, the rear end of each power arm is detachably provided with an empennage, the lower end of each empennage is provided with a lower tail fin, the upper end of each empennage is provided with an upper tail fin, and a tail flow plate is detachably arranged between the two tail fins; the rotor device, the screw including set up in the propulsion rotor mechanism of the rear end of fuselage still include a plurality of set up in lifting rotor mechanism on the power arm.

Description

Slow-cruise unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field especially relates to an unmanned aerial vehicle cruises at a slow speed.

Background

The unmanned plane is an unmanned plane for short, and is an unmanned aerial vehicle operated by utilizing a radio remote control device and a self-contained program control device.

From a technical perspective, drones are generally classified into fixed-wing drones and multi-rotor drones. The fixed-wing unmanned aerial vehicle is strong in carrying capacity, long in range, poor in steering capacity and hovering capacity; the flight status of a multi-rotor drone is more flexible, but the carrying capacity and stability are poor. Therefore, vertical take-off and landing fixed wing drones have begun to appear on the market at present.

However, the existing vertical take-off and landing fixed wing drones have the following disadvantages:

this kind of unmanned aerial vehicle belongs to small-size unmanned aerial vehicle, and the quality is between 116kg ~ 5700kg, and wholly forms by splicing each other between a plurality of structures, consequently still need set up the undercarriage in order to guarantee the steady of unmanned aerial vehicle when being located the ground at the lower extreme of fuselage usually. This has led to unmanned aerial vehicle's camera to shoot and has received the interference of undercarriage easily, and some unmanned aerial vehicle select to get rid of the ventral fin in order to vacate sufficient space installation undercarriage, and nevertheless lack the unmanned aerial vehicle stability of ventral fin poor, and the moment of torsion of vertical fin lateral force to the fuselage is difficult to eliminate in the flight process, causes the damage to the fuselage easily.

SUMMERY OF THE UTILITY MODEL

In order to solve the problem, the utility model provides a slow cruise unmanned aerial vehicle, the utility model discloses a realize like this:

the utility model provides a slow cruise unmanned aerial vehicle, for the unmanned aerial vehicle of stationary vane combination many rotors, it includes:

the lower end of the machine body is provided with a ventral fin;

the fixed wing comprises a middle wing detachably arranged at the upper end of the machine body, power arms are detachably arranged at two ends, far away from the machine body, of the middle wing, one end, far away from the middle wing, of each power arm is detachably provided with an outer wing, a wing flap and a rolling aileron are arranged at the rear end of each outer wing, an empennage is detachably arranged at the rear end of each power arm, a lower tail fin is arranged at the lower end of each empennage, an upper tail fin is arranged at the upper end of each empennage, and a tail flow plate is detachably arranged between the two tail fins;

the rotor wing device comprises a propeller, a propelling rotor wing mechanism arranged at the rear end of the fuselage and a plurality of lifting rotor wing mechanisms arranged on the power arm.

As a further improvement, the power arm includes a rod body, the upper end of the rod body is bulged upwards to form a streamlined wing butt joint portion, the wing butt joint portion is arranged between the middle wing and the outer wing, the front end of the power arm is provided with a streamlined bulb, the rear end of the power arm is provided with a receiving flange, and one end of the tail wing close to the power arm is provided with an inserting flange matched with the receiving flange.

As a further improvement, a first electric adjusting installation groove is formed in the lower end of the machine body and is located behind the ventral fin;

the power arm is characterized in that a front rotor mounting groove is formed in one side, close to the ball head, of the upper end of the power arm, a second electric tuning mounting groove is formed in the position, corresponding to the front rotor mounting groove, of the lower end of the power arm, the power arm is close to one side, close to the bearing flange, of the power arm, a rear rotor mounting groove is formed in the side, close to the bearing flange, of the lower end of the power arm, and a third electric tuning mounting groove is formed in the position, corresponding to the rear rotor mounting groove, of the lower end of the power arm.

As a further improvement, the propulsion rotor mechanism specifically comprises a propulsion electric controller arranged in the fuselage through a first electric controller mounting auxiliary, the propulsion electric controller is electrically connected with a propulsion propeller, the propulsion propeller is rotatably arranged at the rear end of the fuselage, the first electric controller mounting auxiliary is fixedly arranged in the first electric controller mounting groove, and a cooling fin of the propulsion electric controller extends out of the fuselage;

the lifting rotor mechanism specifically includes that installation auxiliary and third electricity are transferred through the second electricity and install the auxiliary set up in lifting electricity in the power arm is transferred, the lifting electricity is transferred and is connected with the lifting screw electricity, the lifting screw rotate set up in preceding rotor mounting groove and in the back rotor mounting groove, the second electricity is transferred installation auxiliary set firmly in the mounting groove is transferred to the second electricity, the third electricity is transferred installation auxiliary set firmly in the mounting groove is transferred to the third electricity, the fin that the lifting electricity was transferred stretches out the outside of power arm.

As a further improvement, a camera is arranged at the lower end of the machine body and is positioned in front of the ventral fin.

As a further improvement, the planes of the bottom ends of the ventral fins and the bottom ends of the two lower tail fins are parallel to the rotation plane of the propeller of the lifting rotor mechanism.

The beneficial effects of the utility model reside in that:

set up the ventral fin through the lower extreme at the fuselage, set up the power arm in the both sides of middle wing, the rear end of power arm sets up the fin, and the lower extreme of fin sets up down the tail fin, has realized through ventral fin and the effect of the supporting legs when down the tail fin can reach and park, is the setting that the triangle was arranged through three tail fin simultaneously, has improved unmanned aerial vehicle stability at the flight in-process, has also improved unmanned aerial vehicle's upset ability.

Drawings

Fig. 1 is the utility model provides a slow cruise unmanned aerial vehicle is at the overall structure schematic diagram after the explosion of VTOL screw.

Fig. 2 is a side view of the slow cruise unmanned aerial vehicle provided by the utility model.

Fig. 3 is a top view of the slow cruise unmanned aerial vehicle provided by the present invention.

Fig. 4 is a schematic view of the overall structure of the power arm of the present invention.

Fig. 5 is a schematic view of the overall structure of the power arm of the present invention at another viewing angle.

Fig. 6 is a schematic view of the overall structure of the connecting member of the present invention.

Fig. 7 is the overall structure diagram of the connection state of the receiving flange and the inserting flange of the present invention.

Fig. 8 is the utility model discloses the outer wing is provided with the section structure sketch map of banding chamfer structure department.

Fig. 9 is a schematic view of the overall structure of the rudder angle mounting base according to the present invention.

Fig. 10 is a schematic sectional view of the bolt fastener in an installed state.

Fig. 11 is a schematic view of the combination of the spoiler and the spoiler of the present invention.

Detailed Description

To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the drawings of the embodiments of the present invention are combined to clearly and completely describe the technical solutions of the embodiments of the present invention, and obviously, the described embodiments are some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention. Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention.

In the description of the present invention, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature.

Referring to fig. 1-11, the utility model provides a slow cruise unmanned aerial vehicle, the fixed wing unmanned aerial vehicle for VTOL.

Referring to fig. 1-3, it includes fuselage 101, the lower extreme of fuselage 101 sets up ventral fin 102, the upper end of fuselage 101 can be dismantled and set up middle wing 201, middle wing 201 is kept away from the both ends of fuselage 101 can be dismantled and set up power arm 301, power arm 301 is kept away from the one end of middle wing 201 can be dismantled and set up outer wing 202, the rear end of power arm 301 can be dismantled and set up the fin, the upper end of fin sets up skeg 402, two go up and to dismantle between the skeg 402 and set up wake board 404, the lower extreme of fin is provided with down skeg 401, set up on the fuselage 101 and impel rotor mechanism 501, the upper end of power arm 301 sets up a plurality of lifting rotor mechanisms 502.

Two, go up the skeg 402 towards keeping away from the direction slope of fuselage 101, and incline towards the direction that draws close each other, go up skeg 402 and keep away from the one end of fuselage 101 sets up turns to aileron 403, the spoiler 404 is kept away from the one end of fuselage 101 sets up and assists the liter aileron 405, the spoiler 404 is the straight plate. In this embodiment, the tail is a high flat tail.

As a further improvement, the plane of the bottom ends of the ventral fin 102 and the bottom ends of the two lower tail fins 401 is parallel to the propeller rotation plane of the lift rotor mechanism 502.

Referring to fig. 10, in the present embodiment, the middle wing 201 is fastened to the body 101 by a specific bolt fastening member 606, and the bolt fastening member 606 includes:

the fixed station is fixed to be inlayed and is located on the well wing 201, some internal thread holes are seted up at the middle part of fixed station, the fixed station is including stretching out the buffering portion on well wing 201 surface, the lower extreme court of buffering portion extend in the well wing 201 and form axle sleeve portion, the lower extreme of axle sleeve portion is provided with joint portion, joint portion outwards extends and inlays and locate in the inner wall of first mounting hole. Wherein, the fixed station is made by metal material or alloy, preferably with aluminium alloy material preparation in this embodiment, wing 201 is by polymer material thermoforming and cladding the fixed station. The fastening bolt is movably sleeved in the fixed table and comprises a screw head, the lower end of the screw head is integrally provided with a screw rod, and one end of the screw rod, far away from the screw head, is provided with a threaded part;

because the fastening bolt with middle wing 201 and fuselage 101 is through the nut cooperation tight both connected mode of clamp, the fastening bolt runs through middle wing 201 and fuselage 101, if the inside part of wing 201 or fuselage 101 is not closely laminated rather than inside in inserting of fastening bolt, then cause middle wing 201 and fuselage 101 two multi-direction offsets of taking place between in the use easily, this also can make fastening bolt can receive great shearing force and impulsive force in the laminating face department of middle wing 201 and fuselage 101, the easy fracture of taking place. Therefore, as a further improvement, wherein the outer diameter of the screw is not larger than the minor diameter of the internally threaded hole, the thread portion is fitted to the internally threaded hole.

Preferably, the buffer part is in a circular truncated cone shape, and the clamping part is in an inverted circular truncated cone shape. Compared with an annular sheet gasket, the buffer part is in a round table shape, so that the pressure of the screw head on the component can be uniformly dispersed to a large area at the lower end of the buffer part, and the pressure applied on the component is reduced.

As a further improvement, the screw head is a cylindrical screw head, and a circular through hole is formed in the screw head along the radial direction.

Referring to fig. 3, 4 and 7, in a conventional vertical take-off and landing fixed wing drone, in order to ensure a streamlined surface of a fixed wing, a power arm 301 is usually arranged at the lower end of a wing, so that the power arm 301 generates pressure on the wing firstly under the action of a plurality of vertical lifting rotors, and then the wing drives a fuselage 101 to take off and land, and a carbon rod is only used for preventing separation of various components and does not become a main stressed component. Therefore, as a further improvement, the power arm 301 includes a rod body, the upper end of the rod body is raised upwards to form a streamlined wing butt-joint portion 3013, the wing butt-joint portion 3013 is disposed between the middle wing 201 and the outer wing 202, the front end of the power arm 301 is provided with a streamlined ball head 3014, the rear end of the power arm 301 is provided with a receiving flange 602, and one end of the tail wing close to the power arm 301 is provided with an inserting flange 603 adapted to the receiving flange 602.

Referring to fig. 4-6, because unmanned aerial vehicle's casing adopts polymer material to make more, and need splice the equipment shaping each other by a plurality of structures, different with manned aircraft, this type of unmanned aerial vehicle need set up the carbon pole inside and make each part as the skeleton to assist with multiple part in order to accomplish the installation. And unmanned aerial vehicle's structural connection department is stress concentration point, takes place to damage easily. Therefore, as a further improvement, a plate surface mounting groove 3015 is opened at the connection point of the power arm 301, the middle wing 201 and the outer wing 202, and a connecting piece 601 is fixedly embedded in the plate surface mounting groove 3015, in this embodiment, the connecting piece 601 is integrally molded by an aluminum alloy material. The carbon pole runs through connecting piece 601 sets up, after the relative motion trend appears between the flight in-process structure, applys pressure each other between carbon pole and the connecting piece 601, can effectually disperse the pressure that the carbon pole was applyed by coupling mechanism through connecting piece 601, avoids the casing that the high polymer polymeric material made to produce the damage.

Accordingly, the connector 601 is preset inside the upper tail fin 402 and the tail flow plate 404.

As a further improvement, an opening penetrating through the substrate 6011 is formed in the middle of the substrate 6011, the size and shape of the opening are adapted to the size and shape of the joint of the quick-release aviation plug or the quick-release aviation socket, and may be circular or rectangular, and the like, in this embodiment, the plug of the square housing is preferably provided with a rectangular opening, the edge of the opening protrudes toward the bottom of the panel mounting groove 3015 to form a quick-release aviation plug fixing seat 6012 adapted to the quick-release aviation plug, an accommodating space is provided inside the quick-release aviation plug fixing seat 6012, and can accommodate and fix the head of the quick-release aviation plug, and only the contact pin or other part of the protruding head of the plug 6011 is left to extend out of the quick-release aviation plug fixing seat 6012. The plug and the socket are firmly arranged on the aluminum plate connecting piece 601 through the quick-release aviation plug fixing seat 6012, and the plug is prevented from falling off to influence butt joint of wings.

The base plate 6011 is further provided with a carbon rod mounting hole 6013 for a carbon rod to pass through.

Referring to fig. 4 and 5, as a further improvement, a first electric adjustment installation groove is formed in the lower end of the fuselage 101, and the first electric adjustment installation groove is located behind the ventral fin 102;

a front rotor wing installation groove 3011 is formed in one side, close to the ball head 3014, of the upper end of the power arm 301, a second electric tuning installation groove 3016 is formed in a position, corresponding to the front rotor wing installation groove 3011, of the lower end of the power arm 301, a rear rotor wing installation groove 3012 is formed in one side, close to the bearing flange 602, of the upper end of the power arm 301, and a third electric tuning installation groove 3017 is formed in a position, corresponding to the rear rotor wing installation groove 3012, of the lower end of the power arm 301. Among traditional VTOL fixed wing unmanned aerial vehicle, lifting rotor mechanism 502 that is close to the aircraft nose position directly sets up at the front end of power arm 301, directly sets up and makes the screw that is close to lifting rotor mechanism 502 of aircraft nose position receive air resistance influence too big and impaired or cause the damage to the output shaft of motor easily in the front end of power arm 301, the utility model discloses in set up streamlined bulb 3014 at the front end of power arm 301 to rotor mechanism with the front end moves backward slightly, makes the air current of vertical flow to the screw become the incline direction, is favorable to the rotation of screw, reduces the output consumption of motor in the high altitude flight.

Wherein, the distance from the front rotor installation slot 3011 to the front end of the connection between the power arm 301 and the middle wing 201/outer wing 202 is defined, that is, the moment arm of the lifting rotor mechanism 502 arranged at the front end of the power arm 301 is D; the distance from the rear rotor installation slot 3012 to the power arm 301 and the rear end of the connection of the middle wing 201/outer wing 202, that is, the force arm of the lifting rotor mechanism 502 arranged at the rear end of the power arm 301 is D, and then there is D: d is 1.15 to 1.25. Because the utility model provides an unmanned aerial vehicle that cruises at a slow speed's fin is high flat tail, and the ratio undersize of D and D then causes unmanned aerial vehicle when descending or fly fast the opportunity head to sink easily, leads to unmanned aerial vehicle to crash. If the ratio of D to D is too large, it will cause too much work load to the tail, and further increase the area of the wake plate 404 on the tail to maintain balance.

As a further improvement, the propulsion rotor mechanism 501 specifically includes a propulsion electric governor arranged in the airframe 101 through a first electric governor mounting accessory, the propulsion electric governor is electrically connected with a propulsion propeller, the propulsion propeller is rotatably arranged at the rear end of the airframe 101, the first electric governor mounting accessory is fixedly arranged in the first electric governor mounting groove, and a heat sink of the propulsion electric governor extends out of the airframe 101;

lifting rotor mechanism 502 specifically includes that installation auxiliary and third electricity are transferred through the second electricity install auxiliary set up in lifting electricity in power arm 301 is transferred, the lifting electricity is transferred and is connected with the lifting screw electricity, the lifting screw rotate set up in preceding rotor mounting groove 3011 and in the back rotor mounting groove 3012, the second electricity is transferred installation auxiliary set firmly in second electricity is transferred in mounting groove 3016, the third electricity is transferred installation auxiliary set firmly in third electricity is transferred in mounting groove 3017, the fin that the lifting electricity was transferred stretches out power arm 301's outside.

With reference to fig. 8, 9 and 11, as a further improvement, a sealing fillet 604 is provided at the flap 203 and at the connection between the aileron 204 and the outer wing 202. The edge sealing chamfer 604 is arranged at the joint of the wing flap 204 and the outer wing 202 of the wing flap 203, so that a gap is not generated between the wing flap 203 and the wing flap 204 during swinging in the flying process and the outer wing 202, the phenomenon that external airflow is poured into the wing is avoided, the internal air tightness of the unmanned aerial vehicle is ensured, the internal pressure of the unmanned aerial vehicle is also ensured to be constant, and the electronic instrument and the like are prevented from being damaged.

As a further improvement, the edge sealing chamfer 604 is made of an aluminum alloy material, the edge sealing chamfer 604 is a round chamfer, the edge sealing chamfer 604 is fixedly connected to the flap 203 or the wing aileron 204 close to one side surface of the outer wing 202, and the edge sealing chamfer 604 is close to one side surface of the outer wing 202 and provided with a sealing rubber strip.

During the flight, the aircraft may encounter the situation of high-altitude precipitation, or as the altitude rises, the temperature is reduced to cause a large amount of water drops to adhere to the surface, and the water drops are converged and enter the wing or the fuselage 101, so that the internal electronic instruments are easily damaged. In addition, during flight, the flap 203 and the aileron 204 swing due to airflow disturbance and motor control, and after long-time operation, wear is generated due to reciprocating swing, so that a gap is generated between the flap 203 or the aileron 204 and the outer wing 202. Therefore, as a further improvement, a wing chamfer corresponding to the edge sealing chamfer 604 is arranged at the joint of the shell and the flap 203 or the wing aileron 204, and a layer of sealant is fixedly arranged on the surface of the edge sealing chamfer 604.

The utility model provides a slow cruise unmanned aerial vehicle, span 4600mm, the long 2180mm of fuselage 101, the long 1585mm of outer wing, this slow cruise unmanned aerial vehicle's the speed of cruising is 20m/s, the biggest navigational speed 30m/s, minimum navigational speed 16m/s, the biggest weight of taking off of whole machine is 35 kg. This unmanned aerial vehicle is whole at the flight in-process and is in the flight at a slow speed, and the weight of complete machine is great, and the turn angle degree is great when consequently its turns, if the swing of flap 203 or wing aileron 204 is through the connecting axle drive then the pivot need provide very big moment of torsion and just can accomplish, causes the damage to the motor easily. Therefore, as a further improvement, a through hole is formed in the lower end surface of the housing, a pair of rudder angle mounting bases 605 is arranged in the through hole, a rudder angle motor is arranged in the rudder angle mounting bases 605, an output shaft of the rudder angle motor is hinged with a connecting rod, and one end of the connecting rod, which is far away from the rudder angle mounting bases 605, is hinged with the lower end surface of the flap 203 or the wing aileron 204.

Because this unmanned aerial vehicle is the unmanned aerial vehicle of endurance at a slow speed, set up rudder angle mount pad 605 after the lower extreme surface of outer wing 202, lead to the flight effect to reduce or cause the damage to the wing because of air resistance easily. Therefore, as a further improvement, the rudder angle mounting base 605 specifically includes:

rudder angle board 6051, the rigid coupling in the lower extreme surface of casing, the downward integrated into one piece in lower extreme surface of rudder angle board 6051 sets up installation cabin 6052, installation cabin 6052 keeps away from one side of flap 203 or wing aileron 204 is streamlined, installation cabin 6052 is close to the opening that supplies the connecting rod to pass through is seted up to one side of flap 203 or wing aileron 204, installation cabin 6052 intercommunication the inside and external world of outer wing 202.

The mounting cabin 6052 is streamlined, so that the air flow generated in the flight process can be prevented from directly impacting the connecting rod, and the service life of the connecting rod is ensured; meanwhile, the resistance on the wings in the flying process can be reduced, so that the flying process is more stable.

In order to facilitate the installation and heat dissipation of the motor, as a further improvement, the installation compartment 6052 is disposed in the rudder angle plate 6051 is close to the lower end surface on the side of the body 101, the rudder angle plate 6051 is kept away from the support 6053 integrally formed on the upper end surface on the side of the installation compartment 6052, the motor is disposed between the supports 6053, and the rudder angle plate 6051 is disposed with a plurality of heat dissipation holes 6054 between the supports 6053.

Further, the corresponding positions of the spoiler 404 and the upper tail fin 402 are also provided with rudder angle mounting seats 605 with the same structure.

As a further improvement, a camera 103 is arranged at the lower end of the body 101, and the camera 103 is positioned in front of the ventral fin 102.

As a further improvement, the thickness of the upper tail fin 402 gradually shrinks toward the fuselage 101.

In the conventional vertical lift fixed wing drone, a right-angle turn exists between the wake plate 404 and the vertical tail in the tail wing of the high horizontal tail, and the tail wing is usually formed by integral molding, so that it is difficult to arrange an adjustable aileron on the tail wing. Meanwhile, during the flight, the wake plate 404 is always subjected to a large lifting force, so that a large shearing force always exists between the wake plate 404 and the vertical tail, and the wake plate 404 may fall off after the flight for a period of time. In addition, the rear slip flow of the propeller and the rear slip flow of the fuselage 101 and the wings are easy to form turbulent masses at the corners after contacting with the vertical tail wings and the tail flow plates 404, and the material is easy to generate material fatigue phenomena after having irregular reciprocating motion tendency to crack, which is more adverse to the service life of the empennage. Further, the rotation of the lift propeller creates a vortex at the distal end of the blade, which impacts the wake plate 404, increasing the shear force between the wake plate 404 and the vertical tail.

Therefore, as a further improvement, the upper end of the upper tail fin 402 is bent toward the other upper tail fin 402 to form a flow filtering portion 406, the cross section of the flow filtering portion 406 is shaped like a sector, one end of the auxiliary lifting aileron 405 away from the flow baffle 404 is contracted toward the direction away from the adjacent upper tail fin 402, and a gap 407 is formed between the flow filtering portion 406, the turning aileron 403 and the auxiliary lifting aileron 405. Because two go up tail fin 402 towards keeping away from the direction slope of fuselage 101, and incline towards the direction that draws close each other for the breach 407 position corresponds the blade marginal position of lifting screw, can effectually make the vortex pass through. Meanwhile, the flow filtering portion 406 having a sector-shaped cross section, i.e., an arch shape as a whole, is provided. Compare traditional unmanned aerial vehicle's right angle corner, the dome structure can be more effective dispersion wake flow board 404 and the stress that exists between the vertical fin.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides a slow cruise unmanned aerial vehicle which characterized in that, for the unmanned aerial vehicle of stationary vane combination many rotors, it includes:

the lower end of the machine body is provided with a ventral fin;

2. The slow cruise unmanned aerial vehicle as claimed in claim 1, wherein the power arm comprises a rod body, the upper end of the rod body is bulged upwards to form a streamlined wing butt joint portion, the wing butt joint portion is arranged between the middle wing and the outer wing, a streamlined ball head is arranged at the front end of the power arm, a receiving flange is arranged at the rear end of the power arm, and an inserting flange matched with the receiving flange is arranged at one end, close to the power arm, of the empennage.

3. The slow cruise unmanned aerial vehicle as claimed in claim 2, wherein a first electrically-adjusting mounting groove is formed in a lower end of the main body, and the first electrically-adjusting mounting groove is located behind the ventral fin;

the upper end of power arm is close to preceding rotor mounting groove is seted up to one side of bulb, the lower extreme of power arm with the mounting groove is transferred to the second electricity is seted up to the corresponding position of preceding rotor mounting groove, the upper end of power arm is close to one side of accepting the flange is seted up the back rotor mounting groove, the lower extreme of power arm with the mounting groove is transferred to the third electricity is seted up to the corresponding position of back rotor mounting groove.

4. The slow cruise unmanned aerial vehicle of claim 3, wherein the propulsion rotor mechanism comprises a propulsion electric governor disposed in the fuselage through a first electric governor mounting accessory, the propulsion electric governor being electrically connected to a propulsion propeller, the propulsion propeller being rotatably disposed at a rear end of the fuselage, the first electric governor mounting accessory being fixedly disposed in the first electric governor mounting groove, a heat sink of the propulsion electric governor extending outside the fuselage;

5. A slow cruise drone according to claim 1 wherein the lower end of the fuselage is provided with a camera, said camera being located in front of the ventral fin.

6. A slow cruise drone according to claim 1, characterised in that the plane of the bottom ends of said ventral fins and of the two lower tail fins is parallel to the rotation plane of the propellers of said lift rotor mechanism.