CN114771820A

CN114771820A - VTOL fixed wing unmanned aerial vehicle convenient to dismouting

Info

Publication number: CN114771820A
Application number: CN202210477094.6A
Authority: CN
Inventors: 龚帮民; 艾剑良
Original assignee: Fudan University
Current assignee: Fudan University
Priority date: 2022-05-02
Filing date: 2022-05-02
Publication date: 2022-07-22

Abstract

The invention discloses a vertical take-off and landing fixed wing unmanned aerial vehicle convenient to disassemble and assemble, which belongs to the field of unmanned aerial vehicles and comprises a body, two main wings, a traction assembly, an empennage, an avionic system and a main power supply, wherein the two main wings are respectively installed on two sides of the body; the two ends of the horn extend to the front and the rear of the main wing respectively, a secondary power supply is also arranged on the horn, and the secondary power supply is electrically connected with the two lifting force components through a lead; the lifting force assembly and the secondary power supply on each machine arm are respectively in communication connection with the avionic system through control cables. According to the invention, a vertical take-off and landing mechanism can be added to the fixed-wing unmanned aerial vehicle as required, so that the fixed-wing unmanned aerial vehicle has the flight advantages of two unmanned aerial vehicles.

Description

VTOL fixed wing unmanned aerial vehicle convenient to dismouting

Technical Field

The invention relates to the field of unmanned aerial vehicles, in particular to a vertical take-off and landing fixed wing unmanned aerial vehicle convenient to disassemble and assemble.

Background

Because many rotor unmanned aerial vehicle do not receive the influence of place restriction, can hover, advantage such as with low costs, its model and quantity increase rapidly, but receive factors such as power, aerodynamic configuration, many rotor unmanned aerial vehicle are difficult to satisfy more and more rigorous user's demand in aspects such as journey, speed, flight time. The fixed wing unmanned aerial vehicle has long endurance time and high speed, but needs a takeoff runway, thereby greatly restricting the usability of the fixed wing unmanned aerial vehicle. In recent years, due to the progress of technology, the vertical take-off and landing fixed-wing unmanned aerial vehicle becomes a reality, and the vertical take-off and landing fixed-wing unmanned aerial vehicle is mainly applied to the fields of traffic supervision, oilfield pipeline inspection, large-area surveying and mapping, forest inspection, police use and military use due to long endurance time and large moving radius, and has wide application prospect.

At present, the VTOL fixed wing unmanned aerial vehicle that uses in the market all is the rotor class, it combines together many rotor unmanned aerial vehicle and fixed wing unmanned aerial vehicle, so VTOL fixed wing unmanned aerial vehicle has just possessed the mode of taking off and land of many rotors, the requirement to the place when taking off and land of fixed wing unmanned aerial vehicle has been solved, possess fixed wing unmanned aerial vehicle flying distance long simultaneously, fast, high advantage, thereby solved many rotors continuation of the journey weak point, slow in speed, flight height is lower problem.

But because the existing fixed wing structure of VTOL fixed wing unmanned aerial vehicle possesses many rotor structures simultaneously, lead to unmanned aerial vehicle's fuselage volume too big, be unfavorable for transportation and save. Meanwhile, the fixed wing structure and the multi-rotor wing structure coexist, and under the use scene that only one flight state is needed, one main wing structure does not work, so that extra burden is changed. Therefore, modular design is urgently needed, and the unmanned aerial vehicle structure can be changed in time according to flight missions.

Disclosure of Invention

The invention aims to provide a vertical take-off and landing fixed wing unmanned aerial vehicle convenient to disassemble and assemble, and aims to solve the problems that the existing fixed wing structure of the vertical take-off and landing fixed wing unmanned aerial vehicle in the prior art is provided with a multi-rotor wing structure, so that the size of the body of the unmanned aerial vehicle is too large, and transportation and storage are not facilitated.

In order to realize the purpose, the technical scheme of the invention is as follows:

a vertical take-off and landing fixed wing unmanned aerial vehicle convenient to disassemble and assemble comprises a fuselage, an undercarriage arranged at the bottom of the fuselage, two main wings arranged on two sides of the fuselage respectively, a traction assembly arranged on the front part of the fuselage, an empennage arranged on the tail part of the fuselage, an avionic system arranged in the fuselage and a main power supply used for supplying power to the avionic system, the traction assembly and a steering engine on the empennage, wherein vertical take-off and landing mechanisms are detachably and fixedly connected to the two main wings and comprise a machine arm and two lifting force assemblies arranged on two ends of the machine arm respectively; the two ends of the horn extend to the front and the rear of the main wing respectively, a secondary power supply is further mounted on the horn, and the secondary power supply is electrically connected with the two lifting force assemblies through a lead; the lifting force assembly and the secondary power supply on each horn are respectively in communication connection with the avionic system through control cables.

Preferably, the main wing is provided with an aileron and an aileron steering engine for driving the aileron.

Preferably, a cross beam vertically penetrating through the fuselage along the horizontal direction is fixedly mounted on the fuselage, two ends of the cross beam are respectively positioned on two sides of the fuselage, cross beam mounting holes extending towards the tips are formed in the root end faces of the two main wings, and the cross beam mounting holes are matched with the cross section of the cross beam; the root of the main wing is connected with the fuselage through a screw.

Preferably, the cross beams are sequentially distributed at intervals along the length direction of the fuselage, and the cross beams are parallel to each other and are oppositely arranged.

Preferably, the cross beam is a square tube made of carbon fiber material.

Preferably, the arm is fixedly connected to one side of the top surface of the main wing by a screw.

Preferably, the horn is provided with a power supply mounting hole for mounting the secondary power supply, and the horn is detachably connected with a power supply cover plate for sealing the power supply mounting hole.

Preferably, the power supply mounting hole is configured to penetrate through a through hole of the horn along a vertical direction, a mounting groove matched with the secondary power supply is formed in the top surface of the main wing opposite to the power supply mounting hole, and a sealing ring arranged around the mounting groove is arranged between the top surface of the main wing and the horn.

Preferably, the traction assembly comprises a traction motor fixedly installed on the machine body and a traction propeller installed on an output shaft of the traction motor; the lift force assembly comprises a lift force motor fixedly mounted on the machine arm and a lift force propeller mounted on an output shaft of the lift force motor.

By adopting the technical scheme, the invention has the beneficial effects that: due to the arrangement of the vertical take-off and landing mechanisms detachably connected on the two main wings, when the vertical take-off and landing mechanisms are connected on the main wings, the unmanned aerial vehicle has the advantages of a fixed-wing unmanned aerial vehicle and a multi-rotor unmanned aerial vehicle at the same time, and the size of the unmanned aerial vehicle can be effectively reduced by the mode of detaching the vertical take-off and landing mechanisms, so that the unmanned aerial vehicle is convenient to transport and store; in addition, when VTOL mechanism is dismantled from the main wing, unmanned aerial vehicle can regard as fixed wing unmanned aerial vehicle to use alone to in the execution does not need the task of VTOL function. The invention can change the characteristics of the original fixed-wing unmanned aerial vehicle and efficiently change the configuration of the unmanned aerial vehicle through the detachably mounted vertical take-off and landing mechanism, thereby changing the flight state of the unmanned aerial vehicle.

Drawings

FIG. 1 is a schematic structural diagram according to a first embodiment of the present invention;

FIG. 2 is a cross-sectional view of the horn and wing of the present invention taken along line A-A of FIG. 1;

fig. 3 is a schematic structural view of a third embodiment of the present invention, in which a wing on one side is detached from a fuselage;

FIG. 4 is an enlarged view of a portion of FIG. 3 at B;

fig. 5 is a cross-sectional view of an airfoil taken along line C-C of fig. 3 in accordance with a third embodiment of the invention.

In the figure, 1-a fuselage, 2-a main wing, 21-an ear, 22-a second screw, 3-a traction component, 4-a tail wing, 5-an aileron, 6-a horn, 61-a first screw, 7-a lifting component, 8-a secondary power supply, 9-a power supply cover plate and 10-a cross beam.

Detailed Description

The following further describes embodiments of the present invention with reference to the drawings. It should be noted that the description of the embodiments is provided to help understanding of the present invention, and is not intended to limit the present invention. In addition, the technical features involved in the respective embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other. It should be noted that in the description of the present invention, the terms "upper", "lower", "left", "right", "front", "rear", and the like indicate orientations or positional relationships based on structures shown in the drawings, and are only used for convenience in describing the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.

In the technical scheme, the terms "first" and "second" are only used for referring to the same or similar structures or corresponding structures with similar functions, and are not used for ranking the importance of the structures, or comparing the sizes or other meanings.

In addition, unless expressly stated or limited otherwise, the terms "mounted" and "connected" are to be construed broadly, e.g., the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; the two structures can be directly connected or indirectly connected through an intermediate medium, and the two structures can be communicated with each other. To those skilled in the art, the specific meanings of the above terms in the present invention can be understood in light of the context of the present application, along with the general concepts of the invention.

Example one

The utility model provides a VTOL fixed wing unmanned aerial vehicle convenient to dismouting, as shown in figure 1, includes fuselage 1, installs the undercarriage in fuselage 1 bottom, two main wings 2 of installing respectively in the both sides of fuselage 1, install the anterior traction assembly 3 at fuselage 1, install fin 4 at the afterbody of fuselage 1, install the avionics system inside fuselage 1 and be used for the main power supply for above-mentioned avionics system, traction assembly 3 and the steering wheel on the fin power supply. The traction assembly 3 comprises a traction motor fixedly mounted on the machine body 1 and a traction propeller mounted on an output shaft of the traction motor, and the output shaft of the traction motor is arranged in the horizontal direction parallel to the machine body 1. The tail 4 generally includes a vertical tail including a vertical stabilizer fixed to the body 1 and a rudder rotating with respect to the vertical stabilizer, and a horizontal tail including a horizontal stabilizer fixed to the body 1 and an elevator rotating with respect to the horizontal stabilizer. Usually, the aileron 5 and an aileron steering gear for driving the aileron to deflect are also arranged at the middle position of the rear side of the main wing 2. It can be understood that, above-mentioned structural design makes the unmanned aerial vehicle of this embodiment constitute fixed wing unmanned aerial vehicle at first, and fixed wing unmanned aerial vehicle is as the mature product that prior art is disclosed, and the concrete configuration description this embodiment of its each functional component is no longer described any more.

In this embodiment, in order to realize the function of fixed wing unmanned aerial vehicle's VTOL, all can dismantle fixedly connected with VTOL mechanism on configuring two main wings 2. The vertical lifting mechanism specifically comprises a machine arm 6 and two lifting force assemblies 7 which are respectively arranged at two end positions of the machine arm 6.

Here, the horn 6 is configured in an elongated configuration, which is generally a hollow structure in order to reduce weight, and the longitudinal direction of the horn 6 is configured in parallel with the longitudinal direction of the body 1. In connection, preferably, the arm 6 is installed on one side of the top surface of the main wing 2 so as to share the weight of the vertical take-off and landing mechanism through the bearing capacity of the main wing 2, in this embodiment, the arm 6 is provided with a screw hole formed in the vertical direction, and the top surface of the main wing 2 is provided with a threaded hole so that the arm 6 is detachably and fixedly connected with the top surface of the main wing 2 through a first screw 61; or in other preferred embodiments, the arm 6 is fixed on the top surface of the main wing 2 by a U-shaped hoop. Dimensionally, the arms 6 are configured to have a length greater than the width of the main wing 2 so that the arms 6 can extend at both ends forward and aft of the main wing 2, respectively, so that downwash generated by the lift assemblies 7 mounted at their ends is not obstructed by the main wing 2. The lift force assembly 7 comprises a lift force motor fixedly mounted on the machine arm 6 and a lift force propeller mounted on an output shaft of the lift force motor, and a vertical shaft of the lift force motor is arranged in the vertical direction.

Wherein, still install secondary power supply 8 on the horn 6, for example offer the power mounting hole used for installing secondary power supply 8 on the middle part position (the position relative to main wing 2) of horn 6, and the top surface one side of horn 6 is then dismantled and is connected with the power apron 9 that is used for sealing this power mounting hole, for example power apron 9 passes through the screw or elastic buckle and connects on horn 6. The secondary power supply 8 is electrically connected with the two lifting force assemblies 7 mounted on the same horn 6 through wires so as to provide electric energy required by vertical lifting, and the wires penetrate through the hollow structure of the horn 6. In addition, the lift assemblies 7 and the secondary power supply 8 on the two arms 6 are respectively in communication connection with an avionic system installed inside the fuselage 1 through control cables, so that the avionic system can control the vertical take-off and landing mechanism conveniently, and the control cables are arranged inside the main wing 2 in a penetrating manner so as to obtain protection. Namely, the four-rotor unmanned aerial vehicle with the vertical take-off and landing function disclosed by the prior art can be formed after the two vertical take-off and landing mechanisms and the airframe 1 are combined.

Above-mentioned structural design for the unmanned aerial vehicle that this embodiment provided both has fixed wing unmanned aerial vehicle's characteristics, have many rotor unmanned aerial vehicle's characteristics again, it possesses flight advantage between them simultaneously, and through the detachable connection design between horn 6 and the main wing 2, make when the flight task that does not need the VTOL is being carried out, can subtract for unmanned aerial vehicle through the mode of dismantling horn 6 and heavily reduce the volume size, thereby prolong unmanned aerial vehicle's journey and idle time, and be convenient for transport and save.

Example two

In this embodiment, considering that the power source (secondary power source 8) is generally rectangular, in order to better mount the secondary power source 8, the horn 6 is configured to include a middle section having a rectangular or nearly rectangular cross section (for example, the top and bottom surfaces are parallel and opposite planes, and the two side surfaces are convex arc surfaces), and extension sections respectively connected to the two sides of the middle section, and the three sections are integrally configured. Wherein the middle section is fixed on the top surface of the main wing 2 by the first screw 61, and the power supply mounting hole is also provided on the middle section, so that the rectangular power supply mounting hole is more easily opened from the middle section, thereby facilitating the mounting of the secondary power supply 8 which is generally rectangular in structure.

In addition, the secondary power supply 8 is generally of a larger size, considering that the secondary power supply 8 generally needs to store more electrical energy. On the premise that the diameter of the horn 6 is fixed, the secondary power supply 8 can only extend in the direction along the length of the horn 6 and in the vertical direction (the direction perpendicular to the main wing 2), and only the power supply mounting hole needs to be elongated in the length direction of the horn 6, while the secondary power supply is blocked by the main wing 2 in the vertical direction.

Therefore, in this embodiment, as shown in fig. 2, the power supply installation hole is configured as a through hole penetrating through the horn 6 in the vertical direction, and the top surface of the main wing 2 opposite to the power supply installation hole is provided with an installation groove adapted to the secondary power supply 8, so that the secondary power supply 8 with increased size can extend into the installation groove on the top surface of the main wing 2 in the vertical direction, and the installation groove is also used for bearing the secondary power supply 8. In addition, a sealing ring disposed around the installation groove is provided between the top surface of the main wing 2 and the horn 6, so that water and dust cannot enter the installation groove, thereby protecting the secondary power supply 8.

EXAMPLE III

In order to further reduce the volume and size of the unmanned aerial vehicle under the transportation and storage conditions, as shown in fig. 3-5, in the embodiment, the main wing 2 is also detachably and fixedly connected with the main body 1, for example, an ear 21 is welded at the root of the main wing 2, a connecting hole is opened on the ear 21, and the main wing is detachably and fixedly connected with a threaded hole opened on the main body 1 through a second screw 22 penetrating through the connecting hole.

Wherein, in order to improve the connection steadiness between main wing 2 and the fuselage 1, this embodiment has seted up the perforation of perpendicular to fuselage 1 length direction along the horizontal direction on fuselage 1, wear to be equipped with crossbeam 10 in the perforation, the middle part position that crossbeam 10 is located fuselage 1 is fixed for fuselage 1 through the mode of welding or bolted connection, and the both ends of crossbeam 10 stretch out and are located the both sides of fuselage 1 from fuselage 1 respectively, and all set up the crossbeam mounting hole that extends to its tip on the root terminal surface of two main wings 2, this crossbeam mounting hole and the cross section looks adaptation of cross section crossbeam 10. So arranged, the weight of the main wing 2 and the vertical take-off and landing mechanism mounted thereon is borne by the cross beam 10, while the second screw 22 connects the main wing 2 and the fuselage 1 mainly in the horizontal direction. The cross beam 10 is configured as a square tube made of carbon fiber material, which is not only light in weight, but also can resist the torsion force of the main wing 2 relative to the fuselage 1 by virtue of the square cross section.

In order to better share the weight of the main wing 2 and the vertical lifting mechanism and prevent the main wing 2 from rotating relative to the fuselage 1, in a preferred embodiment, two or more beams 10 are disposed at intervals along the length direction of the fuselage 1, and the beams 10 are parallel and oppositely disposed.

The embodiments of the present invention have been described in detail above with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It will be apparent to those skilled in the art that various changes, modifications, substitutions and alterations can be made in the embodiments without departing from the principles and spirit of the invention, and these embodiments are still within the scope of the invention.

Claims

1. The utility model provides a VTOL fixed wing unmanned aerial vehicle convenient to dismouting, includes the fuselage, installs at undercarriage, two of fuselage bottom install respectively the main wing of the both sides of fuselage, install the anterior subassembly that pulls of fuselage, install the fin of the afterbody of fuselage, install avionics system in the fuselage and be used for doing the avionics system pull the subassembly and the main power supply of steering wheel power supply on the fin, its characterized in that: the two main wings are detachably and fixedly connected with vertical take-off and landing mechanisms, and each vertical take-off and landing mechanism comprises a machine arm and two lifting force assemblies respectively arranged at two ends of the machine arm; the two ends of the horn extend to the front and the rear of the main wing respectively, a secondary power supply is further mounted on the horn, and the secondary power supply is electrically connected with the two lifting force assemblies through a lead; the lifting force assembly and the secondary power supply on each machine arm are respectively in communication connection with the avionic system through control cables.

2. The easy-to-dismount vertical take-off and landing fixed wing drone of claim 1, wherein: and the main wing is provided with an aileron and an aileron steering engine for driving the aileron.

3. The VTOL fixed-wing UAV of claim 1, which facilitates disassembly and assembly, further comprising: a cross beam vertically penetrating through the fuselage along the horizontal direction is fixedly installed on the fuselage, two ends of the cross beam are respectively positioned at two sides of the fuselage, cross beam installation holes extending towards the tip part are respectively formed in the root end surfaces of the two main wings, and the cross beam installation holes are matched with the cross section of the cross beam; the root of the main wing is connected with the fuselage through a screw.

4. The VTOL fixed-wing UAV of claim 3 convenient to disassemble and assemble, characterized in that: the cross beams are sequentially distributed at intervals in the length direction of the machine body, and are parallel to each other and oppositely arranged.

5. The VTOL fixed-wing UAV of claim 2, wherein: the cross beam is a square tube made of carbon fiber materials.

6. The easy-to-dismount vertical take-off and landing fixed wing drone of claim 1, wherein: the horn is fixedly connected to one side of the top surface of the main wing through a screw.

7. The easy-to-dismount vertical take-off and landing fixed wing drone of claim 6, wherein: the power supply mounting hole for mounting the secondary power supply is formed in the machine arm, and a power supply cover plate for sealing the power supply mounting hole is detachably connected to the machine arm.

8. The VTOL fixed-wing UAV of claim 1, which facilitates disassembly and assembly, further comprising: the power supply mounting hole is configured to penetrate through the through hole of the horn along the vertical direction, the mounting groove matched with the secondary power supply is formed in the top surface of the main wing opposite to the power supply mounting hole, and a sealing ring surrounding the mounting groove is arranged between the top surface of the main wing and the horn.

9. The VTOL fixed-wing UAV of claim 1, which facilitates disassembly and assembly, further comprising: the traction assembly comprises a traction motor fixedly arranged on the machine body and a traction propeller arranged on an output shaft of the traction motor; the lift assembly comprises a lift motor fixedly mounted on the machine arm and a lift propeller mounted on an output shaft of the lift motor.