CN111452975A

CN111452975A - Multifunctional aircraft

Info

Publication number: CN111452975A
Application number: CN202010283500.6A
Authority: CN
Inventors: 宋有洲
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-04-13
Filing date: 2020-04-13
Publication date: 2020-07-28

Abstract

The invention discloses a multifunctional aircraft, and relates to the technical field of unmanned aerial vehicle aviation; in order to assist the aircraft in completing the tasks of taking off and landing; the flying wing device comprises a main body and a buckle device, wherein a U-shaped stabilizing groove is formed in the outer wall of the top of the main body, a plurality of vertical flying wings which are uniformly distributed are fixed on two sides of the outer wall of the top of the main body through bolts, two symmetrical main wings are welded on the outer walls of the two sides of the main body respectively, and two symmetrical auxiliary wings are welded on the outer walls of the two sides of the main body respectively; the outer wall of the bottom of the main wing and the outer wall of the bottom of the aileron are both fixed with parallel engines through bolts; an oil tank is welded on the inner wall of one side of the main body, and a remote sensing flight control system is arranged inside one side of the main body. The invention adopts the technology of the parallel engine to ensure that the highest speed of the aircraft is equal to the lowest speed of the aircraft, and the relative speed of the aircraft and the aircraft can be zero; the landing gear of the airplane can be flexibly fixed by adopting the buckling device; the U-shaped machine back lowers the overall center of gravity.

Description

Multifunctional aircraft

Technical Field

The invention relates to the technical field of unmanned aerial vehicle aviation, in particular to a multifunctional aircraft.

Background

At present, on a battlefield, air force is almost the leader of a war, so that the airport is a very important part during the war, a flight runway can become an important attack target of enemy during the war, if the flight runway and a standby runway are damaged, a fighter plane cannot lift off, and the development of the war ending is disastrous. The capture of abstinence on a battlefield is usually the first action taken to provide for other combat actions. The main targets are the airplane, airport, air defense radar, air defense command control system, hangar and the like of the other party. Strategic air attacks, which are primarily the strikes of the opposing party's infrastructure, command systems, and chief forces, typically begin at the same time or later as the battle taking the air right. Starting from the strategic air attack, after the strategic air attack strength is continuously increased, the tactical air attack is simultaneously expanded and the control air right is captured. The absence of the runway leads to no air control right, and how to further reduce the dependence of the airplane on the runway becomes an important strategic subject.

Through the retrieval, chinese patent application number is CN 201725740607.9's patent, a multifunctional aircraft is disclosed, which comprises a housing, the fin is installed to the rear side of casing, the undercarriage is installed to the lower part of casing, the upper portion of casing is equipped with detachable propeller assembly, propeller assembly includes that first thick liquid mechanism and second revolve thick liquid mechanism, the inside of casing is equipped with power take off mechanism, power take off mechanism includes the axis, the axis lower extreme is equipped with a tooth case, the axis both sides correspond and are equipped with battery jar and motor element, be equipped with power transmission gear group in the tooth case, first thick liquid mechanism and second revolve thick liquid mechanism respectively through first pivot and second pivot with power transmission gear group is connected, the inside of casing still is equipped with flight controller and receiver respectively, the bottom of casing still is equipped with altitude detector and fillet camera. The aircraft in the above patent suffers from the following disadvantages: cannot bear other flying devices and cannot be used as a carrier.

Disclosure of Invention

The invention aims to solve the defects in the prior art and provides a multifunctional aircraft.

In order to achieve the purpose, the invention adopts the following technical scheme:

the multifunctional aircraft comprises a main body and a buckle device, wherein the outer wall of the top of the main body is provided with a U-shaped stable groove, a plurality of vertical flying wings which are uniformly distributed are fixed on two sides of the outer wall of the top of the main body through bolts, two symmetrical main wings are welded on the outer walls of the two sides of the main body respectively, and two symmetrical auxiliary wings are welded on the outer walls of the two sides of the main body respectively; the outer wall of the bottom of the main wing and the outer wall of the bottom of the aileron are both fixed with parallel engines through bolts; an oil tank is welded on the inner wall of one side of the main body, and a remote sensing flight control system is arranged inside one side of the main body; two symmetrical generators are respectively fixed on two sides of the interior of the main body through bolts.

Preferably: the outer walls of the bottom of the main body, the main wing and the ailerons are all provided with air bag floats; the inside water tank that is provided with of main part, main part bottom outer wall are provided with four nozzles, and the nozzle passes through the solenoid valve with the water tank to be connected, and solenoid valve and remote sensing flight control system electric connection.

Preferably: the top outer wall both ends of main part all are provided with the slope.

Preferably: the containing room has been seted up to the bottom outer wall of main part, and the containing room inner wall has the crane through the fix with screw, and the lifting wheel is installed through the pulley yoke to crane one end.

Preferably: the U-shaped stabilizing groove top inner wall is connected with a fixing frame in a sliding mode, the buckling device is arranged on the outer wall of one side of the fixing frame, and the buckling device is provided with the sensing device and the camera device.

Preferably: the buckle device comprises a buckle seat, a buckle core, a motor and two symmetrical unlocking arms, wherein the buckle seat is fixed on the outer wall of one side of the fixing frame through a bolt, the buckle core is inserted into the inner wall of the buckle seat, and the two unlocking arms are respectively positioned on two sides of the buckle seat; the output end of the motor is connected with a first threaded column through synchronous wheel rotation, a second threaded column is welded at one end of the first threaded column, threaded seats are welded on the outer wall of the bottom of the unlocking arm, and the two threaded seats are respectively connected to the outer wall of the first threaded column and the outer wall of the second threaded column through threads.

Preferably: the outer wall of the bottom of the fixing frame is welded with a lifting seat, the bottom of the lifting seat is provided with a lifting mechanism, and the outer wall of one side of the motor is fixed on the outer wall of the top of the lifting seat through the motor seat.

Preferably: the thread pitches of the first threaded column and the second threaded column are equal and the thread directions are opposite.

Preferably: the pulley has been seted up to mount one side outer wall, and the welding of one side outer wall of unblock arm has the connecting rod, and the one end outer wall sliding connection of connecting rod has the spout, and spout sliding connection is in the pulley inner wall.

Preferably: the outer wall welding of lift seat top has the support, and second screw thread post one end is fixed in one side outer wall of support through the bearing frame.

The invention has the beneficial effects that:

1. the technology of a parallel engine is adopted to enable the highest speed of the aircraft to be equal to the lowest speed of the aircraft, and the relative speed of the aircraft and the aircraft can be zero; the landing gear of the airplane can be flexibly fixed by adopting the buckling device; the U-shaped airplane back reduces the integral gravity center, and the flight control system is more convenient to operate and more stable; the design of the slopes at the two ends is convenient for the airplane to get in and out of the aircraft; the design of the air bag floater can meet the taking-off and landing tasks of the aircraft on the water surface.

2. The nozzle, the water tank and the electromagnetic valve are arranged, so that the function of manually controlling the aircraft to extinguish the fire can be realized; through the lifting seat with the lifting mechanism, the buckle device can be collected into the main body after unlocking, so that the airplane can move on the U-shaped stabilizing groove independently.

3. By setting the thread pitches of the first threaded column and the second threaded column to be equal and the thread directions to be opposite, the unlocking arms can move towards each other at the same speed, and therefore reliability is improved.

4. The movement stability of the unlocking arm can be improved by arranging the connecting rod, the pulley and the sliding chute; through setting up the support, can further promote buckle device's stability and fastness.

Drawings

Fig. 1 is a schematic structural diagram of the whole multifunctional aircraft provided by the invention;

FIG. 2 is a schematic structural diagram of a front surface of the multifunctional aircraft according to the present invention;

FIG. 3 is a schematic bottom view of the multifunctional aircraft according to the present invention;

FIG. 4 is a schematic structural view of a multifunctional aircraft buckle device according to the present invention;

FIG. 5 is a schematic structural view of the multifunctional aircraft buckle device according to the present invention from the bottom;

fig. 6 is a schematic structural diagram of a multifunctional aircraft buckle device according to the present invention in a side cross-sectional view.

In the figure: the aircraft comprises a main body 1, a 2U-shaped stabilizing groove, a 3 slope, a 4 vertical flying wing, a 5 aileron, a 6 main wing, a 7 lifting wheel, an 8 oil tank, a 9 remote sensing flight control system, a 10 fixing plate, a 11 lifting frame, a 12 parallel engine, a 13 generator, a 14 air bag floater, a 15 storage chamber, a 16 nozzle, a 17 unlocking arm, an 18 motor, a 19 lifting seat, a 20 buckle core, a 21 buckle seat, a 22 first threaded column, a 23 second threaded column, a 24 support, a 25 threaded seat, a 26 pulley, a 27 sliding chute and a 28 connecting rod.

Detailed Description

The technical solution of the present patent will be described in further detail with reference to the following embodiments.

Reference will now be made in detail to embodiments of the present patent, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present patent and are not to be construed as limiting the present patent.

In the description of this patent, it is to be understood that the terms "center," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings for the convenience of describing the patent and for the simplicity of description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the patent.

In the description of this patent, it is noted that unless otherwise specifically stated or limited, the terms "mounted," "connected," and "disposed" are to be construed broadly and can include, for example, fixedly connected, disposed, detachably connected, disposed, or integrally connected and disposed. The specific meaning of the above terms in this patent may be understood by those of ordinary skill in the art as appropriate.

Example 1:

the multifunctional aircraft comprises a main body 1 and a buckle device, wherein the outer wall of the top of the main body 1 is provided with a U-shaped stable groove 2, a plurality of vertical flying wings 4 which are uniformly distributed are fixed on two sides of the outer wall of the top of the main body 1 through bolts, two symmetrical main wings 6 are welded on the outer walls of two sides of the main body 1 respectively, and two symmetrical auxiliary wings 5 are welded on the outer walls of two sides of the main body 1 respectively; the outer wall of the bottom of the main wing 6 and the outer wall of the bottom of the aileron 5 are both fixed with a parallel engine 12 through bolts; an oil tank 8 is welded on the inner wall of one side of the main body 1, and a remote sensing flight control system 9 is arranged inside one side of the main body 1; two symmetrical generators 13 are respectively fixed on two sides of the interior of the main body 1 through bolts.

To facilitate landing and takeoff on the water surface; as shown in fig. 3, the bottom outer wall of the main body 1, the bottom outer wall of the main wing 6 and the bottom outer wall of the flap 5 are provided with air bag floats 14; a water tank is arranged in the main body 1, four nozzles 16 are arranged on the outer wall of the bottom of the main body 1, the nozzles 16 are connected with the water tank through electromagnetic valves, and the electromagnetic valves are electrically connected with the remote sensing flight control system 9; the air bag floater 14 is arranged, so that the aircraft can conveniently land and take off on the water surface; through setting up nozzle 16, water tank and solenoid valve, can realize the function that manual control aircraft was put out a fire.

In order to facilitate the airplane to get on and off the aircraft independently; as shown in fig. 1, both ends of the top outer wall of the main body 1 are provided with slopes 3; through setting up slope 3, can provide a domatic for aircraft is autonomic about the aircraft, can strengthen aerodynamic configuration and reduce the air resistance simultaneously.

In order to reduce the flight resistance; as shown in fig. 3, the outer wall of the bottom of the main body 1 is provided with a receiving chamber 15, the inner wall of the receiving chamber 15 is fixed with a lifting frame 11 through a screw, and one end of the lifting frame 11 is provided with a lifting wheel 7 through a pulley seat; by providing the storage chamber 15 and the crane 11, the lift wheels 7 can be stored during flight, thereby reducing flight resistance.

To facilitate securing the aircraft; as shown in fig. 1 and 2, a fixing frame 10 is slidably connected to an inner wall of the top of the U-shaped stabilizing groove 2, a fastening device is arranged on an outer wall of one side of the fixing frame 10, and an induction device and a camera device are mounted on the fastening device; through setting up induction system and camera device, can be through the position around the change autonomic regulation of information, adjust the focus of aircraft and the focus of aircraft to same vertical line to be convenient for fixed aircraft.

In the embodiment, when the aircraft is used, the oil tank 8 and the generator 13 in the main body 1 provide power for the aircraft, the vertical flying wing 4 can realize the lifting of the aircraft, the main wing 6 and the ailerons 5 can ensure the flying stability of the aircraft, and the technology of the parallel engine 12 is adopted to ensure that the highest speed of the aircraft is equal to the lowest speed of the aircraft, so that the relative speed of the aircraft and the ailerons can be zero; the landing gear of the airplane can be flexibly fixed by adopting the buckling device; the U-shaped stabilizing groove 2 reduces the integral gravity center, and the remote sensing flight control system 9 is more convenient to operate and more stable; the slopes 3 at the two ends are designed to facilitate the airplane to get in and out of the aircraft; the design of the air bag floater 14 can meet the taking-off and landing tasks of the aircraft on the water surface; a storage chamber 15 and a crane 11, which can store the lifting wheel 7 during flying, thereby reducing flying resistance.

Example 2:

a multifunctional aircraft, as shown in fig. 4-6, to facilitate the jamming and unlocking of the landing gear of the aircraft; the present embodiment is modified from embodiment 1 as follows: the buckle device comprises a buckle seat 21, a buckle core 20, a motor 18 and two symmetrical unlocking arms 17, wherein the buckle seat 21 is fixed on the outer wall of one side of the fixed frame 10 through bolts, the buckle core 20 is inserted into the inner wall of the buckle seat 21, and the buckle core 20 is arranged on an undercarriage of an airplane; the two unlocking arms 17 are respectively positioned at two sides of the buckle seat 21; the output end of the motor 18 is connected with a first threaded column 22 through synchronous wheel rotation, one end of the first threaded column 22 is welded with a second threaded column 23, the outer wall of the bottom of the unlocking arm 17 is welded with threaded seats 25, and the two threaded seats 25 are respectively connected to the outer wall of the first threaded column 22 and the outer wall of the second threaded column 23 through threads.

To facilitate autonomous movement of the aircraft; the outer wall of the bottom of the fixed frame 10 is welded with a lifting seat 19, the bottom of the lifting seat 19 is provided with a lifting mechanism, and the outer wall of one side of the motor 18 is fixed on the outer wall of the top of the lifting seat 19 through a motor seat; by arranging the lifting seat 19 with the lifting mechanism, the buckling device can be taken into the main body 1 after unlocking, so that the airplane can move on the U-shaped stabilizing groove 2 independently.

In order to improve reliability; as shown in fig. 5, the first threaded post 22 and the second threaded post 23 have equal thread pitches and opposite thread directions; by providing equal pitch and opposite thread direction of the first 22 and second 23 threaded cylinders, the unlocking arms 17 can be moved towards each other at the same speed, thereby increasing reliability.

To increase the stability of the movement of the unlocking arm 17; as shown in fig. 6, a pulley 26 is disposed on an outer wall of one side of the fixing frame 10, a connecting rod 28 is welded on an outer wall of one side of the unlocking arm 17, a sliding slot 27 is slidably connected to an outer wall of one end of the connecting rod 28, and the sliding slot 27 is slidably connected to an inner wall of the pulley 26; by providing the connecting rod 28, the pulley 26 and the slide groove 27, the stability of the movement of the lock release arm 17 can be increased.

To further improve stability and robustness; as shown in fig. 5, a bracket 24 is welded on the outer wall of the top of the lifting seat 19, and one end of the second threaded column 23 is fixed on the outer wall of one side of the bracket 24 through a bearing seat; through setting up support 24, can further promote buckle device's stability and fastness.

When the aircraft enters the U-shaped stabilizing groove 2 on the aircraft, the aircraft can be fixed by inserting the buckle core 20 installed on the aircraft landing gear into the buckle seat 21 on the fixing frame 10, when the aircraft is unlocked, the motor 18 drives the first threaded column 22 and the second threaded column 23 to rotate, the buckle core 20 is unlocked by driving the unlocking arm 17 to move oppositely through the threaded seat 25, the connecting rod 28 drives the sliding groove 27 to slide in the pulley 26 to move in a matched manner during the unlocking process, the support 24 can provide a supporting effect, the stability and the firmness of the buckling device are further improved, after the unlocking process is finished, the motor 18 controls the unlocking arm 17 to reset in a working mode, meanwhile, the lifting mechanism at the bottom of the lifting seat 19 operates, the lifting seat 19 is controlled to move downwards, and the buckling device is accommodated in the main body 1.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.

Claims

1. The multifunctional aircraft comprises a main body (1) and a buckle device, and is characterized in that a U-shaped stabilizing groove (2) is formed in the outer wall of the top of the main body (1), a plurality of uniformly distributed vertical flying wings (4) are fixed to two sides of the outer wall of the top of the main body (1) through bolts, two symmetrical main wings (6) are welded to the outer walls of two sides of the main body (1) respectively, and two symmetrical auxiliary wings (5) are welded to the outer walls of two sides of the main body (1) respectively; the outer wall of the bottom of the main wing (6) and the outer wall of the bottom of the aileron (5) are both fixed with a parallel engine (12) through bolts; an oil tank (8) is welded on the inner wall of one side of the main body (1), and a remote sensing flight control system (9) is arranged inside one side of the main body (1); two symmetrical generators (13) are respectively fixed on two sides of the interior of the main body (1) through bolts.

2. The multifunctional aircraft according to claim 1, characterized in that the bottom external wall of the main body (1), the bottom external wall of the main wing (6) and the bottom external wall of the aileron (5) are each provided with an airbag float (14); the inside water tank that is provided with of main part (1), main part (1) bottom outer wall is provided with four nozzles (16), and nozzle (16) pass through the solenoid valve with the water tank and are connected, and solenoid valve and remote sensing flight control system (9) electric connection.

3. Multifunctional aircraft according to claim 2 characterized in that the top outer wall of the body (1) is provided with ramps (3) at both ends.

4. The multifunctional aircraft as claimed in claim 3, characterized in that the outer wall of the bottom of the main body (1) is provided with a storage chamber (15), the inner wall of the storage chamber (15) is fixed with a lifting frame (11) through screws, and one end of the lifting frame (11) is provided with a lifting wheel (7) through a pulley seat.

5. The multifunctional aircraft as claimed in claim 4, wherein a fixing frame (10) is slidably connected to the inner wall of the top of the U-shaped stabilizing trough (2), a fastening device is arranged on the outer wall of one side of the fixing frame (10), and a sensing device and a camera device are mounted on the fastening device.

6. The multifunctional aircraft as claimed in any one of claims 1 to 5, wherein the buckle device comprises a buckle seat (21), a buckle core (20), a motor (18) and two symmetrical unlocking arms (17), the buckle seat (21) is fixed on the outer wall of one side of the fixed frame (10) through a bolt, the buckle core (20) is inserted into the inner wall of the buckle seat (21), and the two unlocking arms (17) are respectively positioned on two sides of the buckle seat (21); the output end of the motor (18) is connected with a first threaded column (22) in a rotating mode through a synchronizing wheel, a second threaded column (23) is welded at one end of the first threaded column (22), threaded seats (25) are welded on the outer wall of the bottom of the unlocking arm (17), and the two threaded seats (25) are connected to the outer wall of the first threaded column (22) and the outer wall of the second threaded column (23) through threads respectively.

7. The multifunctional aircraft as claimed in claim 6, characterized in that the outer wall of the bottom of the fixed frame (10) is welded with a lifting seat (19), the bottom of the lifting seat (19) is provided with a lifting mechanism, and the outer wall of one side of the motor (18) is fixed on the outer wall of the top of the lifting seat (19) through the motor seat.

8. Multifunctional aircraft according to claim 7, characterized in that the first threaded stud (22) and the second threaded stud (23) have an equal pitch and opposite direction of threading.

9. The multifunctional aircraft according to claim 8, wherein a pulley (26) is arranged on the outer wall of one side of the fixed frame (10), a connecting rod (28) is welded on the outer wall of one side of the unlocking arm (17), a sliding groove (27) is connected to the outer wall of one end of the connecting rod (28) in a sliding manner, and the sliding groove (27) is connected to the inner wall of the pulley (26) in a sliding manner.

10. The multifunctional aircraft according to claim 9, characterized in that a bracket (24) is welded on the outer wall of the top of the lifting seat (19), and one end of the second threaded column (23) is fixed on the outer wall of one side of the bracket (24) through a bearing seat.