CN110949654A

CN110949654A - Aircraft

Info

Publication number: CN110949654A
Application number: CN201911354783.2A
Authority: CN
Inventors: 彭振根
Original assignee: Individual
Current assignee: Guangdong Fanya Technology Co ltd
Priority date: 2019-12-25
Filing date: 2019-12-25
Publication date: 2020-04-03
Anticipated expiration: 2039-12-25
Also published as: CN110949654B

Abstract

The invention discloses an aircraft, which belongs to a multifunctional unmanned aerial vehicle in the technical field of unmanned aerial vehicles, and adopts the technical scheme that the multifunctional unmanned aerial vehicle comprises a body and wing assemblies arranged on two sides of the body, wherein the body comprises a body front section, a body middle section and a body rear section which are detachably connected in sequence, each wing assembly comprises a wing and a tilting power assembly arranged on the wing, and the wing assemblies also comprise a V-shaped empennage arranged at the rear end of the body; the rear section of the machine body is provided with a detachable tail duct, and a tail duct motor is arranged in the tail duct; the invention provides an aircraft which is stronger in expansion space and wider in application and application range.

Description

Aircraft

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to an aircraft.

Background

Current VTOL power component unmanned aerial vehicle that verts adopts the combined type more or adopts the rotor formula that verts, realizes many rotor powers and the switching between the power component power that verts. In the existing tilting rotor type Y3 configuration vertical take-off and landing unmanned aerial vehicle, three motors are distributed in a Y shape, and 2 motors on the left and right in front of a wing can generate vector tension to fix the tail part by 1 motor or generate vector tension by 3 motors.

1. VTOL power component unmanned aerial vehicle that verts is the new trend of trade unmanned aerial vehicle in recent years. The flight form of the tilting power assembly is the most efficient flight mode mastered by human beings at present, but sliding takeoff or catapult takeoff is often needed. And many rotors class VTOL unmanned aerial vehicle, it is more nimble convenient, but flight efficiency, time of a flight all are limited relatively. VTOL power component unmanned aerial vehicle that verts can combine together both advantages, becomes one of the main research direction in order to trade level unmanned aerial vehicle in recent years.

2. In the existing tilting rotor type vertical take-off and landing tilting power assembly unmanned aerial vehicle, 3 motors are distributed in a Y shape in a Y3 configuration, 2 propeller motors can generate vector tension force in the left and right sides of the front of a wing, and 1 propeller motor at the tail is fixed. The wingspan of the airplane using the structure on the market is 1.5-2.5 m, the lowest takeoff weight is 3-6kg, and the endurance time is 30-90 min. The flight control system is based on closed-source commodity flight control or open-source flight control. The flight principle of the aircraft is that under the action of a vector steering engine, 2 motors on the front of the wings vertically upwards through a flight control instruction, and at the moment, 3 motors simultaneously generate upwards pulling force to enable the aircraft to vertically take off. When the aircraft reaches a certain altitude flight control indication steering engine (located below the propeller motor and controlling the motor to face) slowly tilts towards the direction of the aircraft nose to a horizontal position (completing the process of accelerating from 0 to a preset airspeed), the tail motor assists in maintaining the aircraft altitude through rotation in the tilting process until the aircraft stops working after reaching the preset airspeed, and at the moment, the conversion from a plurality of rotors to the tilting power assembly in the take-off process is completed. The descending process is then opposite, and vector steering wheel slowly upwards verts to vertical position (accomplishes current airspeed to 0 speed reduction process) by the aircraft nose direction promptly, and the tail motor is rotatory to be maintained the height, accomplishes the conversion of verting power component to many rotors. In the process of a multi-rotor state, the 2 steering engines deflect forward or backward at a certain angle and the rotating speed of the tail motor blade is increased or reduced to realize pitching motion of the airplane, yawing motion of the airplane is realized through opposite directions of the two steering engines, and rolling motion is realized through the rotating speed of the motors on the left side and the right side.

However, the above configuration arrangements all have the disadvantages of large occupied space of the rotor, additional air resistance, additional weight increase and the like. Meanwhile, most of the existing aircraft bodies with the same takeoff weight level are not replaceable, the volume in the cabin is limited, the aircraft is troublesome to transform and can only be used by one aircraft, and the modules cannot be flexibly replaced according to task types. From this the current design of the unmanned aerial vehicle of verting rotor formula Y3 configuration VTOL on the market has following apparent shortcoming:

1. the large torque produced by the blades results in a need for increased strength in the fuselage.

2. The paddle occupies a large space, the mounting position is lower than the ground, and the paddle is easy to hit sundries and be damaged in the vertical take-off and landing or field forced landing process.

3. After the vertical takeoff of the blades is finished and the operation is stopped, the blades can generate resistance and moment due to the rotation of the wind resistance to influence the maneuvering of the aircraft.

4. Cannot or is not beneficial to the running takeoff and the short-distance take-off and landing of the airplane. Resulting in reduced applicability and flexibility.

5. When the emergency treatment machine is encountered, the tail propeller has low response speed and the aircraft can be disassembled by suddenly rotating at high speed.

6. The fuselage integration is difficult for changing other loads, and the diversity of expansibility is not enough.

Disclosure of Invention

Aiming at the defects in the prior art, the invention provides an aircraft, wherein a tail duct motor is adopted at the tail part of the aircraft, the aircraft has the advantages of small volume, high response speed, small torque, high safety and difficult damage, can be fused into an aircraft body to reduce the influence on flight resistance and aircraft maneuverability, a task cabin section can be flexibly replaced at the front section of the aircraft body according to a task, and a cabin section containing a tail duct and an aircraft tail wing of different models can also be replaced at the rear section of the aircraft body. The airplane can perform diversified tasks to the maximum benefit by utilizing the airplane platform, and meanwhile, the airplane can further increase the takeoff weight by adopting the rolloff takeoff and landing and the short-distance takeoff and landing due to the fact that the airplane is not blocked by the tail propeller. Therefore, the aircraft has stronger expansion space and wider application and application range.

An aircraft comprises a fuselage and wing assemblies arranged on two sides of the fuselage, wherein the fuselage comprises a front fuselage section, a middle fuselage section and a rear fuselage section which are detachably connected in sequence, each wing assembly comprises a wing and a tilting power assembly arranged on the wing, and the wing assemblies further comprise a V-shaped empennage arranged at the rear end of the fuselage; the fuselage back end is provided with detachable afterbody duct, afterbody duct inside is provided with afterbody duct motor.

Preferably, fuselage anterior segment, fuselage middle section and fuselage back end can dismantle the connection through mortise and tenon bolt tube hole structure, mortise and tenon bolt tube hole structure is including setting up the connecting pipe in the fuselage middle section, the connecting pipe is provided with a plurality ofly along the fillet department in fuselage middle section, the one end that fuselage anterior segment and fuselage middle section are connected is provided with a plurality of through-holes, the one end that fuselage back end and fuselage middle section are connected is provided with a plurality of through-holes, and the through-hole on the fuselage anterior segment and the through-hole on the fuselage back end are connected with the connecting pipe in fuselage middle section in proper.

Preferably, mortise and tenon bolt tube hole structure is still including setting up the mortise in fuselage middle section, sets up the tenon at fuselage anterior segment and fuselage back end, the mortise is provided with a plurality ofly along the both ends in fuselage middle section, the tenon passes through bolt fixed connection at the junction of fuselage anterior segment and the junction of fuselage back end, tenon and mortise.

Preferably, the inside fuselage inner wall bracing that is provided with of fuselage middle section, fuselage inner wall bracing is the triangle-shaped and fixed the setting inside the fuselage middle section.

Preferably, the fuselage back end both sides be provided with V type tailstock, V type fin fixed mounting is on V type tailstock, the contained angle of V type fin is: 100 degrees.

Preferably, the fuselage middle section is provided with the wing mounting hole, the wing mounting hole includes 10mm carbon-tube jack and 16mm carbon-tube jack, the tip that the wing is connected with the fuselage is provided with the connection carbon pipe with 10mm carbon-tube jack and 16mm carbon-tube jack adaptation, and the connection carbon pipe is arranged in 10mm carbon-tube jack and 16mm carbon-tube jack and is carried out fixed connection.

Preferably, the power component that verts includes the power component brushless motor that verts that sets up on the wing, with the screw that verts power component brushless motor axis of rotation fixed connection.

Preferably, the fixed steering wheel that verts that is provided with in power component brushless motor's the bottom verts, the steering wheel that verts is fixed to be set up on the motor support pole, the other end of motor support pole sets up the antenna, the motor support pole with the connection can be dismantled to the wing.

Preferably, the through hole direction of the tail duct is arranged along the height direction of the rear section of the fuselage.

Preferably, an airspeed meter is arranged on the wing.

The invention has the beneficial effects that:

1. according to the invention, the fuselage is divided into the fuselage front section, the fuselage middle section and the fuselage rear section which can be detachably connected, the fuselage is spliced in sections, the manufacturing is facilitated, the equipment is conveniently added and replaced in the fuselage, the fuselage front section can be replaced by different mission cabin sections, and the fuselage rear section can also be replaced by a cabin section containing tail ducts and airplane empennages of different types. Wherein, owing to set up the afterbody duct at the fuselage back end to install afterbody duct motor and can realize reducing air resistance inside the fuselage, afterbody duct motor moment of torsion is little moreover can reduce fuselage structural strength and reduce weight, saves space, has reduced the requirement in the place of taking off, because do not have blockking of afterbody screw to be favorable to the race, short distance to rise and fall and lack the huge screw of afterbody, safer.

2. In the invention, the bolt in the mortise and tenon structure enters the interior of the machine body through the front cover and the rear cover of the machine body and is inserted into the mortise and tenon structure, so that the sections of the three sections of the machine body form interference fit, and the three sections of the machine body form a closed, firm, smooth and integrated machine body. Mortise and tenon bolt tube hole structure has avoided the slip of fuselage front and back section, and the carbon pipe that the fuselage middle section stretches out has shared the stress of fuselage front and back section and has transmitted the wing through the fuselage middle section and make fuselage anterior segment, fuselage middle section and fuselage back section satisfy easy installation and install more stable convenient effect in the prerequisite that possesses demountable installation.

3. In the invention, the joints of the front section of the fuselage, the rear section of the fuselage and the middle section of the fuselage are respectively in the matching action of a plurality of mortises and tenons and are fixedly connected through bolts, and the stability of the whole fuselage is reinforced by the connection of the plurality of tenons and the mortises.

4. According to the invention, the inner wall inclined strut of the machine body is arranged in the middle section of the machine body, so that the integral stability of the middle section of the machine body with a cavity structure is enhanced, the middle section of the machine body has strong rigidity, and the deformation of the machine body is prevented.

5. In the invention, the V-shaped tail bases are arranged on the two sides of the rear section of the airplane body, and the detachable V-shaped tail wings are arranged on the V-shaped tail bases, so that the interference resistance between the tail wings and the airplane body can be effectively reduced, and the flying speed and the flying stability of the airplane driven by the propeller can be improved.

6. According to the invention, the tilting steering engine is fixedly arranged at the bottom of the brushless motor of the tilting power assembly, so that the adjustment of the inclination angle of the brushless motor of the tilting power assembly can be realized on the premise that the brushless motor of the tilting power assembly drives the blade to rotate on the horizontal plane, and thus the adjustment of the whole unmanned aerial vehicle in the flying state can be realized.

Drawings

In order to more clearly illustrate the detailed description of the invention or the technical solutions in the prior art, the drawings that are needed in the detailed description of the invention or the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.

FIG. 1 is a schematic view of the overall structure of the unmanned aerial vehicle of the present invention;

FIG. 2 is a schematic view of the connection of the middle fuselage section, the front fuselage section and the rear fuselage section of the present invention;

FIG. 3 is an exploded view of the overall structure of the unmanned aerial vehicle of the present invention;

FIG. 4 is a schematic view of the bottom structure of the unmanned aerial vehicle of the present invention;

FIG. 5 is a schematic diagram of a middle section of the unmanned aerial vehicle body of the present invention;

FIG. 6 is a schematic structural diagram of a rear section of a body of the unmanned aerial vehicle according to the present invention;

fig. 7 is a schematic view of a rear section of the unmanned aerial vehicle body of the present invention;

fig. 8 is a schematic view of a rear-section three-dimensional structure of the unmanned aerial vehicle body.

In the attached drawings, 1-middle fuselage section, 2-front fuselage section, 3-rear fuselage section, 4-wing rib, 5-wing, 6-V type empennage, 7-motor support rod fixing part, 8-upper fuselage side R5 carbon tube slide tube, 9-bottom fuselage side R5 carbon tube slide tube, 10-rear fuselage cover, 11-front fuselage cover, 12-airspeed meter, 13-tail duct, 14-motor support rod, 15-tilt steering engine, 17-tilt steering engine bracket, 18-tilt power assembly brushless motor, 19-propeller, 20 antenna, 21-6s10000mah lithium ion battery, 22-16mm carbon tube, 23-10mm carbon tube, 24-tenon, 25-mortise, 26-R5 carbon tube through hole, 27-mortise bolt, 28-R5 carbon tube fixing screw, 29-R5 carbon tube fixing screw hole site, 30-fuselage inner wall bracing, 31-cable through hole, 32-10mm carbon tube jack, 33-16mm carbon tube jack, 34-tail duct fixing hole, 36-V tail base, 37-V tail 5mm carbon tube jack, 38-tail duct chute, 39-tilting power component.

Detailed Description

Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only examples, and the protection scope of the present invention is not limited thereby.

It is to be noted that, unless otherwise specified, technical or scientific terms used herein shall have the ordinary meaning as understood by those skilled in the art to which the invention pertains.

An aircraft comprises a fuselage and wing assemblies arranged on two sides of the fuselage, wherein the fuselage comprises a front fuselage section 2, a middle fuselage section 1 and a rear fuselage section 3 which are detachably connected in sequence, each wing assembly comprises a wing 5 and a tilting power assembly 39 arranged on the wing 5, and the wing assemblies further comprise a V-shaped empennage 6 arranged on the rear fuselage section 3; the rear section 3 of the fuselage is provided with a detachable tail duct 13, and a tail duct motor is arranged in the tail duct 13;

through cutting apart the fuselage for fuselage anterior segment 2 that can dismantle the connection, fuselage middle section 1 and fuselage back end 3, the fuselage adopts the segmentation concatenation, be favorable to making, conveniently install and change equipment toward the inside additional of fuselage, fuselage anterior segment 2 can be with trading different task cabin sections, wherein, owing to set up afterbody duct 13 at fuselage back end 3, and install afterbody duct 13 motor inside can realize reducing the air resistance at the fuselage, and afterbody duct 13 motor moment of torsion can reduce fuselage structural strength reduce weight for a short time, save space, the requirement in the place of taking off has been reduced, because do not have stopping of afterbody screw 19 to be favorable to the rolloff, the short distance plays and has lacked the huge screw 19 of afterbody, and is safer.

Preferably, the front fuselage section 2, the middle fuselage section 1 and the rear fuselage section 3 are detachably connected through a mortise and tenon bolt hole structure, the mortise and tenon bolt hole structure comprises a connecting pipe arranged on the middle fuselage section 1, the connecting pipe is provided with a plurality of connecting pipes along the round angle of the middle fuselage section 1, one end of the front fuselage section 2 connected with the middle fuselage section 1 is provided with a plurality of through holes, one end of the rear fuselage section 3 connected with the middle fuselage section 1 is provided with a plurality of through holes, and the through holes on the front fuselage section 2 and the through holes on the rear fuselage section 3 are sequentially connected with the connecting pipe of the middle fuselage section 1; the bolt in the mortise and tenon structure enters the interior of the machine body through the front cover and the rear cover of the machine body and is inserted into the mortise and tenon structure, so that the sections of the three sections of the machine body form interference fit, and the three sections of the machine body form a closed, firm, smooth and integral machine body. Mortise and tenon bolt tube hole structure has avoided the slip of fuselage front and back section, and the carbon pipe that fuselage middle section 1 stretches out has shared the stress of fuselage front and back section and has transmitted for wing 5 through fuselage middle section 1 and make fuselage anterior segment 2, fuselage middle section 1 and fuselage back end 3 satisfy easy installation and install more stable convenient effect at the prerequisite that possesses demountable installation.

Preferably, the mortise and tenon bolt hole structure further comprises a mortise 25 arranged at the middle section 1 of the machine body and a tenon 24 arranged at the front section 2 of the machine body and the rear section 3 of the machine body, wherein a plurality of mortise 25 are arranged along two ends of the middle section 1 of the machine body, the tenon 24 is arranged at the joint of the front section 2 of the machine body and the joint of the rear section 3 of the machine body, and the tenon 24 is fixedly connected with the mortise 25 through a bolt; adopt the mating reaction of a plurality of fourth of twelve earthly branches head 25 and tenon 24 respectively and through bolt fixed connection in the junction of fuselage anterior segment 2, fuselage back end 3 and fuselage middle section 1, the holistic stability of fuselage has been consolidated in the connection between a plurality of tenons 24 and fourth of twelve earthly branches head 25.

Preferably, an inner wall inclined strut 30 of the machine body is arranged in the middle section 1 of the machine body, and the inner wall inclined strut 30 of the machine body is triangular and is fixedly arranged in the middle section 1 of the machine body; be provided with fuselage inner wall bracing 30 in fuselage middle section 1 inside, strengthen 1 holistic stability in fuselage middle section that has the cavity structure, realize that fuselage middle section 1 has very strong rigidity, prevent that the fuselage from producing deformation.

Preferably, the two sides of the rear section 3 of the fuselage are provided with V-shaped tailstocks, the V-shaped tailstocks 6 are fixedly mounted on the V-shaped tailstocks, and the included angle of the V-shaped tailstocks 6 is as follows: 100 degrees; the V-shaped tail bases are arranged on two sides of the rear section 3 of the airplane body, and the detachable V-shaped tail wing 6 is arranged on the V-shaped tail base, so that the interference resistance between the tail wing and the airplane body can be effectively reduced, and the flying speed and the flying stability of the airplane driven by the propeller 19 can be improved.

Preferably, the fuselage middle section 1 is provided with a wing mounting hole, the wing mounting hole includes a 10mm carbon tube jack 32 and a 16mm carbon tube jack 33, the end of the wing 5 connected with the fuselage is provided with a connecting carbon tube adapted to the 10mm carbon tube jack 32 and the 16mm carbon tube jack 33, and the connecting carbon tube is arranged in the 10mm carbon tube jack 32 and the 16mm carbon tube jack 33 for fixed connection.

Preferably, the tilting power assembly 39 includes a tilting power assembly brushless motor 18 disposed on the wing 5, and a propeller 19 fixedly connected to a rotating shaft of the tilting power assembly brushless motor 18.

Preferably, a tilting steering engine 15 is fixedly arranged at the bottom of the brushless motor 18 of the tilting power assembly, the tilting steering engine 15 is fixedly arranged on a motor support rod 14, and the motor support rod 14 is detachably connected with the wing 5; the antenna is fixed to 14 other ends of motor support pole, so the circuit gets into the fuselage from the wing is inside through mounting upper portion opening, through the fixed steering wheel 15 that verts that is provided with in the bottom of the power component brushless motor 18 that verts, realize the power component brushless motor 18 that verts and drive the regulation that can also realize the power component brushless motor 18's that verts inclination under the pivoted prerequisite is realized to the blade on the horizontal plane, can realize the whole regulation of unmanned aerial vehicle orientation when flight state from this.

Preferably, the through hole direction of the tail duct is arranged along the height direction of the rear section 3 of the fuselage.

Preferably, an airspeed meter 12 is arranged on the wing 5.

Example 1

The embodiment provides an aircraft, which comprises a fuselage and wing assemblies arranged on two sides of the fuselage, wherein the fuselage comprises a front fuselage section 2, a middle fuselage section 1 and a rear fuselage section 3 which are detachably connected in sequence, each wing assembly comprises a wing 5 and a tilting power assembly 39 arranged on the wing 5, and the wing assemblies further comprise a V-shaped empennage 6 arranged on the rear fuselage section 3; the rear section 3 of the fuselage is provided with a detachable tail duct 13, and a tail duct motor is arranged in the tail duct 13; the wingspan 1740 (unit: mm, same below) of the aircraft, and the fuselage length 834. The length 800 of one main engine wing is in a trapezoidal layout, the chord lengths of an inner wing and an outer wing of a Clark-x wing type are 250 and 150, and the incidence angle of the wing is 3 degrees. The wing ribs are laminated plates with the thickness of 1mm, 15 wing ribs are sequentially arranged at equal intervals, 4 tung wood wing spars with the length of 4 x 4 are connected with each other to form a main girder and an auxiliary girder of the wing in a group, the main girder is positioned at the highest position of the wing ribs, the auxiliary girder is positioned at 80% of the wing ribs, and the reinforcing strength of 1mm of balsa wood is adhered to one side of each main girder and each auxiliary girder. Barsha wood strips with 4mm diameter at the front edge and 1mm back laminate at the rear edge. Attaching 1mm balm panels to the upper and lower surfaces of the leading to trailing rib creates a stable box-like structure for the entire wing. The surface of the mask is coated with an aviation thermal shrinkage film to make the surface of the wing smooth and waterproof. The wing is internally provided with 10mm and 16mm carbon rods extending out of the wing rib 60.

The machine body is manufactured by sections and then spliced into a whole. The machine body is divided into a front section, a middle section and a rear section (the front section refers to the machine head direction), and the front section, the middle section and the rear section are respectively 288, 271 and 275. The nose to wing leading edge distance is 306 and the tail to wing leading edge distance is 528. The rectangular upper and

lower fillets

10 and 20 of the fuselage 140 × 120 respectively have the wall thickness of 2mm, and the inner wall of the fuselage has the cross bracing reinforcing strength of 0.5. Two carbon rods are arranged between the front section and the middle section of the machine body and between the middle section and the inner wall of the top of the rear section of the machine body, and the total length is four carbon tubes with the diameter of 100 and 10. The inside of the bottom of the three-section machine body is provided with two carbon rods with the length of 500 and the diameter of 10, which are connected with the three, and the carbon rods play roles of connecting each section of machine body, aligning and supporting. The locking mechanisms distributed on the inner sides of the side walls of the three sections of the machine body are riveted together after the three sections of the machine body are tightly matched along the carbon tubes, and at the moment, a plug pin with the diameter of 5 and the length of 50 is inserted. The three sections of fuselage are now joined to form a solid unit.

The rear fuselage section is provided with a 90mm 6s-12 blade internal rotating force group which can provide 4400g of thrust at the maximum, and the mounting center is separated from the leading edge 485 of the wing and is fixed by bolts. Meanwhile, a picture transmission bin, a data transmission bin and a V-shaped tail wing of the airplane are also installed. The antenna for image transmission and data transmission is installed on the carbon rod fixing piece below the left wing and the right wing through the extension line, and the axial direction of the carbon rod fixing piece is backward in a 12mm carbon tube direction, so that the flying resistance is reduced, and the transmission distance is increased. The V-shaped empennage forms an included angle of 100 degrees, the front edge of the empennage is far from the front edge 343 of the wing, the V-shaped empennage is installed on the R10 circular bead section of the rear-section fuselage, and a bolt structure is adopted to facilitate disassembly and assembly.

The middle section of the fuselage is an important part of the whole airplane, and carbon rods extending out of the left wing and the right wing are connected, fixed and detached through carbon rod clamps and carbon plates. The flight control cabin, the battery cabin and the distribution board are arranged with the flight control cabin, the battery cabin and the distribution board. The battery compartment is formed by connecting two 6s10000mah lithium ion batteries in parallel, is pasted on an inner lining plate at the bottom of the airplane body through magic, can move between the front section of the airplane body and the middle section of the airplane body and is fixed to adjust the gravity center of the whole airplane, so that the airplane can keep the gravity center stable when different front section of the airplane body is replaced and different loads are carried on the airplane body. The power line, the signal line and the antenna in the left wing and the right wing enter the fuselage through the openings at the two sides of the middle fuselage and are connected with the flight control panel, the distribution panel and the picture transmission data transmission. In the connection of the middle fuselage and the left and right wings, power lines are connected by XT60, signal lines are connected by XT30 aviation connectors, and the picture transmission antenna is connected by two sections of picture transmission antenna connectors, so that the aim of facilitating disassembly and assembly and boxing is fulfilled.

The front fuselage is a task load cabin of the whole airplane, and the cabin section can be changed into a cabin section suitable for different tasks according to task types based on a sliding pipe mortise and tenon bolt locking structure. Such as a cloud platform cabin section, an aviation surveying and mapping cabin section, a sensor cabin section carrying air quality detection, a cargo hold and the like. The front-section fuselage can also be designed and manufactured according to the appearance and the size of the mission equipment under the permission of the aerodynamics, the gravity center and the power of the airplane based on the platform and the cabin section interface.

Example 2

The present embodiment is further optimized based on embodiment 1, and specifically, R5 through holes having the same length as the middle section of the body are formed at the corners of the two sides of the bottom side of the middle section of the body, and form an interference fit with R5mm carbon tubes penetrating through three sections of the body, M5 screw holes penetrating through the circle center of the fillet are formed at the position 20 away from the front and rear (forward to the machine head direction) sections of the middle section of the body after two carbon tubes at the bottom penetrate through the middle section of the body, two M5 screws are arranged at the front and rear of one carbon tube, and two carbon tubes are arranged at the bottom side of the middle section of the body, so four M3 screws are. The front and rear fillets on the upper side of the middle section of the machine body are provided with R5 through holes with the length of 40, the R5 through holes are in interference fit with four R5 carbon tubes on the front and rear sides, M3 screw holes penetrating through the circle centers of the fillets are arranged at positions 20 away from the front and rear sections of the middle section of the machine body, and therefore four M3 screws are arranged on the front and rear sides of the upper part of the middle section of the machine body, and. Meanwhile, mortise holes with a distance of 10 are arranged on the front side and the rear side of the middle section of the machine body, and form mortise-tenon plug pin hole structures with tenons of the front section and the rear section of the machine body.

Example 3

The embodiment is further optimized on the basis of embodiment 2, and specifically, R5 through holes with different lengths are respectively arranged at four round corners in the front section and the rear section of the machine body, the through holes and the carbon tubes in the middle section of the machine body form clearance fit, protruding tenons are arranged in the middle of openings of the sections of the front section and the rear section of the machine body, the front section and the rear section of the machine body can slide in through the carbon tubes, the sections of the three sections of the machine body are closed, and a plug pin in a mortise and tenon structure enters the interior of the machine body through the front cover and the rear cover of the machine body and is inserted into the mortise. The fuselage sections thus form a closed, firm, smooth, integral fuselage. The mortise and tenon bolt hole structure avoids the sliding of the front section and the rear section of the fuselage, and the carbon tubes extending out of the middle section of the fuselage share the stress of the front section and the rear section of the fuselage and transmit the stress to the wings through the middle section of the fuselage.

Example 4

The embodiment is further optimized on the basis of embodiment 3, and specifically, the front two power systems of the airplane can generate 4290g of tension by matching 3520 brushless motors 720kv with 6s lithium ion batteries and 1206 paddles. The maximum vertical takeoff weight of the airplane is 12984g of pulling force generated by matching the 90mm 6s-12 blade internal rotating force group.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the following claims and description.

Claims

1. The utility model provides an aircraft, includes the fuselage, sets up the wing subassembly in the fuselage both sides, its characterized in that: the aircraft body comprises an aircraft body front section (2), an aircraft body middle section (1) and an aircraft body rear section (3) which are detachably connected in sequence, the wing assembly comprises a wing (5) and a tilting power assembly (39) arranged on the wing (5), and the wing assembly further comprises a V-shaped empennage (6) arranged on the aircraft body rear section (3); the fuselage back end (3) is provided with detachable afterbody duct (13), afterbody duct (13) inside is provided with the afterbody duct motor.

2. An aircraft according to claim 1, characterized in that: fuselage anterior segment (2), fuselage middle section (1) and fuselage back end (3) can dismantle the connection through mortise and tenon bolt tube hole structure, mortise and tenon bolt tube hole structure is including setting up the connecting pipe in fuselage middle section (1), the connecting pipe is provided with a plurality ofly along the fillet department of fuselage middle section (1), the one end that fuselage anterior segment (2) and fuselage middle section (1) are connected is provided with a plurality of through-holes, the one end that fuselage back end (3) and fuselage middle section (1) are connected is provided with a plurality of through-holes, and through-hole on the through-hole on fuselage anterior segment (2) and the through-hole on fuselage back end (3) are connected with the connecting pipe of fuselage middle section (1) in proper order.

3. An aircraft according to claim 2, characterized in that: mortise and tenon bolt tube hole structure is still including setting up tenon (25) in fuselage middle section (1), sets up tenon (24) in fuselage anterior segment (2) and fuselage back end (3), mortise and tenon (25) are provided with a plurality ofly along the both ends of fuselage middle section (1), tenon (24) are in the junction of fuselage anterior segment (2) and the junction of fuselage back end (3), and tenon (24) pass through bolt fixed connection with mortise and tenon (25).

4. An aircraft according to claim 1, characterized in that: fuselage inner wall bracing (30) are provided with in fuselage middle section (1) inside, fuselage inner wall bracing (30) are the triangle-shaped and fixed setting in fuselage middle section (1) inside.

5. An aircraft according to claim 1, characterized in that: the fuselage back end (3) both sides be provided with V type tailstock, V type fin (6) fixed mounting is on V type tailstock, the contained angle of V type fin (6) is: 100 degrees.

6. An aircraft according to claim 1, characterized in that: fuselage middle section (1) is provided with the wing mounting hole, the wing mounting hole includes 10mm carbon tube jack (32) and 16mm carbon tube jack (33), the tip that wing (5) are connected with the fuselage is provided with the connection carbon tube with 10mm carbon tube jack (32) and 16mm carbon tube jack (33) looks adaptation, connects the carbon tube and arranges in 10mm carbon tube jack (32) and 16mm carbon tube jack (33) in and carries out fixed connection.

7. An aircraft according to claim 1, characterized in that: the tilting power assembly (39) comprises a tilting power assembly brushless motor (18) arranged on the wing (5) and a propeller (19) fixedly connected with a rotating shaft of the tilting power assembly brushless motor (18).

8. An aircraft according to claim 7, characterized in that: the fixed steering wheel (15) that verts that is provided with in bottom of power component brushless motor (18) verts, the steering wheel (15) that verts is fixed to be set up on motor support pole (14), the other end of motor support pole (14) sets up antenna (20), motor support pole (14) with wing (5) can be dismantled and be connected.

9. An aircraft according to claim 1, characterized in that: the through hole direction of the tail duct is arranged along the height direction of the rear section (3) of the machine body.

10. The aircraft according to any one of claims 1 to 9, wherein: and an airspeed meter (12) is arranged on the wing (5).