CN114013641A - Slow-cruise unmanned aerial vehicle - Google Patents

Abstract

The invention discloses a slow cruise unmanned aerial vehicle, which is a fixed wing unmanned aerial vehicle for vertical take-off and landing, and comprises: the fuselage, the lower extreme of fuselage sets up the ventral fin, and the upper end of fuselage can be dismantled and set up the middle wing, and the middle wing can be dismantled at the both ends of keeping away from the fuselage and set up the power arm, and the one end that the middle wing was kept away from to the power arm can be dismantled and set up the outer wing, and the rear end of power arm can be dismantled and set up the fin, and the upper end of fin sets up the tail fin, can dismantle between two tail fins and set up the wake board, and the lower extreme of fin is provided with down the tail fin, sets up the propulsion rotor mechanism on the fuselage, and the upper end of power arm sets up a plurality of lifting rotor mechanisms. Wherein, two last tail fins incline towards the direction of keeping away from the fuselage, and incline towards the direction of drawing close each other, and the one end that the fuselage was kept away from to last tail fin sets up and turns to the aileron, and the one end that the fuselage was kept away from to the wake board sets up assists and rises the aileron, and the wake board is the straight plate. Compared with the traditional vertical take-off and landing fixed wing unmanned aerial vehicle, the unmanned aerial vehicle can be horizontally arranged on the ground without a landing gear, and the flying state is more stable.

Description

Slow-cruise unmanned aerial vehicle

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a slow cruise unmanned aerial vehicle.

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:

1. 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.

2. The tail fin is difficult to set. If need to improve unmanned aerial vehicle and receive the interference of air current at the flight in-process and diminish, then need set up high horizontal tail, and high horizontal tail will cause the aircraft to descend the opportunity head and sink, and the jet flow of screw slipstream or engine also can change the change, if sets up the low horizontal tail fin of type of falling T, then needs will impel the screw setting in aircraft nose department. According to the classical momentum theory, the speed of the airflow brought by the propeller is increased by half before and half after the speed is increased, namely the speed of the slip flow behind the propeller is higher than that of the slip flow in front of the propeller, the dynamic pressure loss is larger when the air blows through the machine body, and the thrust loss is more. The propeller of the nose arrangement can also have a negative effect on the static stability of the aircraft.

Conventional vertical take-off and landing fixed wing drones therefore typically use a V-tail in imitation of the tail of a passenger aircraft. However, the inside of the unmanned aerial vehicle is different from that of the manned aircraft, the V-shaped tail wing is arranged to easily cause the integral gravity center of the unmanned aerial vehicle to be deviated, and the undercarriage is installed at the part, close to the tail wing, of the fuselage to ensure that the unmanned aerial vehicle is stably placed on the ground. After too many landing gears are installed, more turbulence is brought to the unmanned aerial vehicle in the flying process; be unfavorable for flight steadily, if set up the undercarriage that can retract, will improve unmanned aerial vehicle's manufacturing cost, need increase the volume of fuselage, volume simultaneously to there is sufficient space to hold the undercarriage, further improve unmanned aerial vehicle's manufacturing cost.

Disclosure of Invention

In order to solve the problems, the invention provides a slow cruise unmanned aerial vehicle, which is realized as follows:

a slow cruise drone, being a fixed wing drone for vertical take-off and landing, comprising:

the aircraft comprises an aircraft body, wherein ventral fins are arranged at the lower end of the aircraft body, a middle wing is detachably arranged at the upper end of the aircraft body, power arms are detachably arranged at two ends of the middle wing, which are far away from the aircraft body, an outer wing is detachably arranged at one end of each power arm, which is far away from the middle wing, an empennage is detachably arranged at the rear end of each power arm, an upper tail fin is arranged at the upper end of each empennage, a tail flow plate is detachably arranged between the two upper tail fins, a lower tail fin is arranged at the lower end of each empennage, a propulsion rotor wing mechanism is arranged on the aircraft body, and a plurality of lifting rotor wing mechanisms are arranged at the upper end of each power arm;

the tail fin is far away from the direction slope of fuselage, and the direction slope of drawing close each other, it keeps away from to go up the tail fin the one end of fuselage sets up and turns to the aileron, the spoiler is kept away from the one end of fuselage sets up assists and rises the aileron, the spoiler is the straight plate.

As a further improvement, the upper end of the upper tail fin is bent towards the direction close to the other upper tail fin to form a flow filtering part, and the cross section of the flow filtering part is in a sector arc shape.

As a further improvement, the thickness of the upper tail fin gradually shrinks towards the direction close to the fuselage.

As a further improvement, the end of the secondary lift aileron remote from the wake plate is contracted away from the adjacent upper tail fin.

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, the lower end of the machine body is provided with a camera which is positioned in front of the ventral fin.

The invention has the beneficial effects that:

1. 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.

2. Through setting up tail fin and two last tail fins under two, be equivalent to having set up a pair of perpendicular fin, can effectually offset turning moment each other, possess great vertical fin area simultaneously, course stability when flight of unmanned aerial vehicle can effectual improvement.

3. Set up straight platelike wake board between last tail fin, flight stability and the straightness of course when can effectively improve unmanned aerial vehicle meets with bad weather such as strong wind, strong air current in the flight process.

4. Through setting up two last tail fins to the direction slope of drawing close to each other towards to set up at the rear end of last tail fin and turn to the aileron, set up at the rear end of wake board and assist and rise the aileron, can effectually utilize behind the oar slipstream that impels rotor mechanism to produce and guarantee the stationarity of aircraft flight in-process, can control simultaneously and assist and rise the aileron and avoid unmanned aerial vehicle landing in-process because of the too big aircraft nose that leads to sinks and the crash of lift that the tail receives.

Drawings

Fig. 1 is a schematic view of the overall structure of a slow cruise unmanned aerial vehicle after a vertical takeoff and landing propeller is exploded.

Fig. 2 is a side view of a slow cruise drone provided by the present invention.

Fig. 3 is a top view of a slow cruise drone provided by the present invention.

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

Fig. 5 is a schematic overall structure diagram of the power arm in another view angle according to the present invention.

Fig. 6 is a schematic view showing the overall structure of the connector of the present invention.

FIG. 7 is a schematic view of the overall structure of the receiving flange and the inserting flange in the connected state.

FIG. 8 is a schematic cross-sectional view of the outer wing of the present invention with a chamfered edge sealing structure.

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 showing a bolt fastener of the present invention in an installed state.

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

Fig. 12 is a diagram illustrating the state of airflow generated by the lift rotor mechanism at the rear end of the slow cruise drone during vertical take-off and landing.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings of the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention. Thus, the following detailed description of the embodiments of the present invention, presented in the figures, 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. 1-12, the present invention provides a slow cruise drone, which is a vertical take-off and landing fixed wing drone.

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.

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 to be located in the inner wall of first mounting hole. Wherein the fixed platform is made of metal material or alloy, and is preferably made of aluminum alloy material in the embodiment, and the middle wing 201 is formed by thermoplastic molding of high polymer material and covers the fixed platform. 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. In the traditional vertical take-off and landing fixed-wing unmanned aerial vehicle, the lifting rotor wing mechanism 502 close to the aircraft nose is directly arranged at the front end of the power arm 301, and the lifting rotor wing mechanism 502 directly arranged at the front end of the power arm 301 is easy to cause that the propeller of the lifting rotor wing mechanism 502 close to the aircraft nose is damaged or an output shaft of a motor is damaged due to overlarge influence of air resistance.

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 tail wing of the slow-cruise unmanned aerial vehicle provided by the invention is a high horizontal tail, and the ratio of D to D is too small, the head of the unmanned aerial vehicle is easy to sink when the unmanned aerial vehicle lands or flies quickly, so that the unmanned aerial vehicle is crashed. 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 control disposed in the airframe 101 through a first electric control mounting accessory, the propulsion electric control is electrically connected to a propulsion propeller, the propulsion propeller is rotatably disposed at the rear end of the airframe 101, the first electric control mounting accessory is fixedly disposed in the first electric control mounting groove, and a heat sink of the propulsion electric control 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 slow-cruise unmanned aerial vehicle provided by the invention has a wing span of 4600mm, a length of the body 101 of 2180mm and a length of an outer wing of 1585mm, and has a cruising speed of 20m/s, a maximum cruising speed of 30m/s, a minimum cruising speed of 16m/s and a maximum takeoff weight of 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 seats 605 is arranged in the through hole, a rudder angle motor is arranged in the rudder angle mounting seats 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 seats 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 the heat dissipation of the motor, as a further improvement, the installation cabin 6052 is arranged in the rudder angle plate 6051 is close to on the lower end surface of one side of the fuselage 101, the rudder angle plate 6051 is far away from the support 6053 is arranged on the upper end surface of one side of the installation cabin 6052 in an integrated forming mode, the motor is arranged between the supports 6053, and the rudder angle plate 6051 is arranged between the supports 6053 and provided with a plurality of heat dissipation holes 6054.

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 of the high horizontal tail, and the tail is usually formed by integral molding, so that it is difficult to arrange an adjustable aileron on the tail. 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 fan creates a vortex at the distal end of the blade, which impacts the spoiler 404, increasing the shear force between the spoiler 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 (8)

1. The utility model provides a slow cruise unmanned aerial vehicle which characterized in that, for the fixed wing unmanned aerial vehicle of VTOL, it includes:

the aircraft comprises an aircraft body, wherein ventral fins are arranged at the lower end of the aircraft body, a middle wing is detachably arranged at the upper end of the aircraft body, power arms are detachably arranged at two ends of the middle wing, which are far away from the aircraft body, an outer wing is detachably arranged at one end of each power arm, which is far away from the middle wing, an empennage is detachably arranged at the rear end of each power arm, an upper tail fin is arranged at the upper end of each empennage, a tail flow plate is detachably arranged between the two upper tail fins, a lower tail fin is arranged at the lower end of each empennage, a propulsion rotor wing mechanism is arranged on the aircraft body, and a plurality of lifting rotor wing mechanisms are arranged at the upper end of each power arm;

the tail fin is far away from the direction slope of fuselage, and the direction slope of drawing close each other, it keeps away from to go up the tail fin the one end of fuselage sets up and turns to the aileron, the spoiler is kept away from the one end of fuselage sets up assists and rises the aileron, the spoiler is the straight plate.

2. The slow cruise drone of claim 1, wherein the upper end of said upper tail fin is curved towards the direction close to the other upper tail fin to form a flow filtering portion, the cross section of said flow filtering portion being sector-shaped.

3. A slow cruise drone according to claim 2, characterised in that said upper tail fin tapers in thickness towards said fuselage.

4. A slow cruise drone according to claim 3, wherein the end of said secondary lift ailerons remote from said spoilers is convergent in a direction away from the adjacent said upper skegs.

5. 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.

6. The slow cruise unmanned aerial vehicle of claim 5, wherein a first electrically-tunable mounting groove is formed in a lower end of the main body, and the first electrically-tunable mounting groove 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.

7. The slow cruise unmanned aerial vehicle of claim 6, wherein the propulsion rotor mechanism comprises a propulsion electronic governor disposed in the fuselage through a first electronic governor mounting accessory, the propulsion electronic governor being electrically connected to a propulsion propeller, the propulsion propeller being rotatably disposed at a rear end of the fuselage, the first electronic governor mounting accessory being fixedly disposed in the first electronic governor mounting groove, a heat sink of the propulsion electronic governor extending outside 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.

8. A slow cruise drone according to claim 1, characterised in that the lower end of the fuselage is provided with a camera, which is located in front of the ventral fin.

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