CN219237402U - Multi-mode large-load modularized multipurpose unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses a multi-mode large-load modularized multipurpose unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles, and specifically comprises a fuselage, wings, a vertical tail stay bar, a vertical tail and a horizontal tail, wherein the front end of the fuselage is provided with a load installation space; the rear end of the machine body is provided with a power system; the wing is characterized in that wings are fixedly connected to two sides of the rear end of the fuselage, one end, far away from the nose landing gear, of each wing is connected with a vertical tail through a vertical tail stay bar, the two vertical tails are connected through the horizontal tails, each wing comprises a wing spar, each wing spar comprises a main wing spar and a pair of wing spar, and each pair of wing spar is fixedly connected with the fuselage. The multi-mode large-load modularized multipurpose unmanned aerial vehicle has the advantages that five parts, namely a fuselage, wings, a vertical tail stay bar, a vertical tail and a horizontal tail, are integrated into a whole through modularized design, rapid disassembly is supported, and transportation is convenient; and the wings are arranged at the rear end of the fuselage, so that the purpose of balancing the fuselage is achieved, and the unmanned aerial vehicle load is facilitated.

Description

Multi-mode large-load modularized multipurpose unmanned aerial vehicle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to the field of split manned aerial vehicles, and specifically relates to a multi-mode large-load modularized multipurpose unmanned aerial vehicle.

Background

Most of the aerial operations and aerial experiments on the market at present need to be carried out by using a conveyor or a helicopter, but the cost is too high and the corresponding experiment operation needs to be carried out in a preset time by using the method; the special unmanned aerial vehicle of little part use repacking back carry out relevant work, have proposed an eight rotor unmanned aerial vehicle that possesses big load effect like the patent of authorizing of application number CN202222115133.6, including eight rotor unmanned aerial vehicle, eight rotor unmanned aerial vehicle's bottom surface fixedly connected with battery fixed box, the bottom surface fixedly connected with of battery fixed box supports the diaphragm, two track spout one and four track spout two have been seted up to the inside of supporting the diaphragm, the inside rotation of supporting the diaphragm is connected with two track poles, the inside fixedly connected with of supporting the diaphragm has two track poles, every the equal sliding connection of inner wall of track spout one has fixed grip block, every the inside of fixed grip block all with two-way threaded rod threaded connection, every the inside of fixed grip block all with the track pole sliding connection who corresponds, the right-hand member fixedly connected with worm wheel of two-way threaded rod.

Above-mentioned scheme is when using, utilizes fixed grip block to carry out the centre of gravity to article, and the article that needs the transportation is fixed in unmanned aerial vehicle's bottom, and this unmanned aerial vehicle is at the operation in-process, and unmanned aerial vehicle's focus changes, and then can influence unmanned aerial vehicle's pneumatic characteristics and flying performance, based on this, this application provides a multimode big load modularization multipurpose unmanned aerial vehicle.

Disclosure of Invention

The utility model provides a multi-mode large-load modularized multipurpose unmanned aerial vehicle, which solves the problems that the transportation load of the unmanned aerial vehicle provided in the background art is fixed at the bottom of the unmanned aerial vehicle, the flight resistance of the unmanned aerial vehicle is increased, the flight gravity center of the unmanned aerial vehicle is changed, and the aerodynamic characteristics and the flight performance of the unmanned aerial vehicle are affected.

The utility model provides the following technical scheme: a multi-mode large-load modularized multipurpose unmanned aerial vehicle comprises a fuselage, wings, vertical tail stay bars, vertical tails and flat tails, wherein the fuselage, the wings, the vertical tail stay bars, the vertical tails and the flat tails are integrated into a whole through modularized design, and rapid disassembly is supported; a load installation space is arranged in the body of the unmanned aerial vehicle, and the load cannot influence the flight resistance of the unmanned aerial vehicle; the wing of the unmanned aerial vehicle is arranged at the rear end of the fuselage, so that the unmanned aerial vehicle is balanced when loaded, and the aerodynamic characteristics and the flight performance of the unmanned aerial vehicle are ensured; the wing ribs are additionally arranged on the wing, so that the strength of the wing is improved; the auxiliary wing beam of the wing is of a double auxiliary wing structure, and when one control surface fails, the other three control surfaces can maintain the normal flight of the aircraft, so that the torsion of the control surface is reduced, and meanwhile, the reliability is improved.

The multi-mode large-load modularized multipurpose unmanned aerial vehicle comprises a body, wings, a vertical tail stay bar, a vertical tail and a horizontal tail, wherein the front end of the body is provided with a load installation space; the rear end of the machine body is provided with a power system; the two sides of the rear end of the fuselage are fixedly connected with wings, one end of each wing, which is far away from the nose landing gear, is connected with a vertical tail through a vertical tail stay bar, and the two vertical tails are connected through a horizontal tail;

the wing comprises a wing spar and a wing rib, wherein the wing spar comprises a main wing spar and an auxiliary wing spar, the auxiliary wing spar is fixedly connected with a machine body, the top of the auxiliary wing spar is fixedly connected with a main wing girder, the main wing girder is fixedly connected with the wing rib, the bottom of the auxiliary wing spar is provided with a stay bar connecting point matched with a vertical tail stay bar, one end, close to a power system, of the auxiliary wing spar is provided with an auxiliary wing control surface, and two auxiliary wing steering engines are fixedly connected to the auxiliary wing spar;

the horizontal tail comprises a horizontal tail main body, two horizontal tail control surfaces are arranged at the rear end of the horizontal tail main body, one side of each horizontal tail control surface is fixedly connected with a horizontal tail steering engine, and quick-release screw holes are formed in two sides of the horizontal tail main body.

Preferably, the load installation space is of a ring beam large space structure, and a nose cabin cover is arranged at the top of the load installation space.

Preferably, a nose landing gear is arranged at the bottom of the front end of the machine body, and the nose landing gear integrates a shock absorbing device and a steering device; the bottom of the rear end of the machine body is provided with a main landing gear, the main landing gear is integrated with a hydraulic brake device, and the front landing gear and the main landing gear are made of different materials; the middle part fixedly connected with airspeed tube of fuselage front end, the middle part at fuselage top is connected with the GPS antenna.

Preferably, the strength of the wing rib material is lower than that of the wing spar material, the auxiliary wing spar is of a double auxiliary wing structure, two auxiliary wing control surfaces are arranged, and the wing ribs are perpendicular to the wing.

Preferably, the horizontal tail is of a double-horizontal-tail structure, the two horizontal-tail control surfaces are respectively a horizontal-tail left control surface and a horizontal-tail right control surface, and one side of the horizontal-tail left control surface and one side of the horizontal-tail right control surface are fixedly connected with a horizontal-tail steering engine.

Preferably, the vertical fin comprises a stay bar mounting seat connected with the telescopic tube, a horizontal fin mounting hole is formed in the bottom of the stay bar mounting seat, and a vertical fin steering engine is fixedly connected to the outer side face of the stay bar mounting seat.

Preferably, the quick-release screw hole and the horizontal tail mounting hole are matched with the M12.9-level screws, and the M12.9-level screws are two.

Preferably, the power system comprises an oil filling port, an aircraft engine and a propeller matched with the aircraft engine, an oil tank is arranged below the oil filling port to supply oil for the aircraft engine, and the propeller is positioned in the middle of the rear end of the aircraft body.

Compared with the prior art, the utility model has the following beneficial effects:

1. the multi-mode large-load modularized multipurpose unmanned aerial vehicle has the advantages that five parts, namely a fuselage, wings, a vertical tail stay bar, a vertical tail and a horizontal tail, are integrated into a whole through modularized design, rapid disassembly is supported, and transportation is convenient; and the wings are arranged at the rear end of the fuselage, so that the purpose of balancing the fuselage is achieved, and the unmanned aerial vehicle load is facilitated.

2. According to the multi-mode large-load modularized multipurpose unmanned aerial vehicle, a hanging-up function can be rapidly increased by replacing a hanging-down stay bar, and a large-capacity cabin in a fuselage can be increased to expand functions; the wing structure is arranged, so that the structural strength of the wing is improved by combining the main wing spar, the auxiliary wing spar and the wing rib; the auxiliary wing beam is in a double auxiliary wing structure, and when one control surface fails, the other three control surfaces can maintain the normal flight of the aircraft, so that the torsion of the control surface is reduced, and meanwhile, the reliability is improved.

Drawings

FIG. 1 is a schematic top view of the structure of the present utility model;

FIG. 2 is a schematic view of the structure of the present utility model from the bottom of FIG. 1;

FIG. 3 is a three-dimensional schematic view of a structural fuselage of the present utility model;

FIG. 4 is a three-dimensional schematic view of the fuselage, wing and tail connection of the structure of the present utility model;

FIG. 5 is an enlarged schematic view of a structural wing of the present utility model;

FIG. 6 is a schematic view of the bottom of a wing of the structure of the present utility model;

FIG. 7 is a schematic view of a vertical fin of the present utility model;

fig. 8 is a schematic left-hand view of the structure of the present utility model, fig. 7.

In the figure: 1. a body; 2. a wing; 3. a vertical tail stay bar; 4. a vertical tail; 5. a horizontal tail; 7. a power system; 1.1, a machine head cabin cover; 1.2, nose landing gear; 1.3, main landing gear; 2.1, spar; 2.2, ribs; 2.3, stay bar connection points; 2.4, aileron control surfaces; 4.1, a supporting rod mounting seat; 4.2, a horizontal tail mounting hole; 4.3, a vertical tail control surface; 5.1, a horizontal tail main body; 5.2, a horizontal tail left control surface; 5.3, a horizontal tail right control surface; 6.1, airspeed tube; 6.2, GPS antenna; 6.3, an aileron steering engine; 6.4, a vertical tail steering engine; 6.5, a horizontal tail steering engine; 7.1, a fuel filler; 7.2, aircraft engines; 7.3, propeller.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

The utility model provides a multi-mode large-load modularized multipurpose unmanned aerial vehicle, which comprises a machine body 1, wherein the front end of the machine body 1 is provided with a load installation space, the inside of the load installation space is of a ring beam large-space structure, the load and equipment are convenient to install, and the top of the load installation space is provided with a machine head cabin cover 1.1.

The middle part fixedly connected with airspeed tube 6.1 of fuselage 1 front end, the bottom fixedly connected with nose landing gear 1.2 of fuselage 1 front end, integrated on the nose landing gear 1.2 has shock absorber and turns to the device, and shock absorber and turn to the device and be prior art, do not make in detail here, and nose landing gear 1.2 material in this application is the aluminum alloy.

The top fixedly connected with GPS antenna 6.2 in fuselage 1 middle part, the driving system 7 is installed to fuselage 1's rear end, driving system 7 includes oil filler neck 7.1, aircraft engine 7.2 and with aircraft engine 7.3 of 7.2 adaptation, the oil filler neck below is equipped with the oil tank and supplies oil for the aircraft engine, and the screw 7.3 is located the middle part of fuselage 1 rear end, in some embodiments of this application, aircraft engine 7.2 selects for use the type of gono-Bach 275 engine.

The bottom fixedly connected with main undercarriage 1.3 of fuselage 1 rear end, the integrated hydraulic braking device of main undercarriage 1.3, hydraulic braking device are prior art, do not repeated here, and the material of nose undercarriage 1.2 and main undercarriage 1.3 is different, and the material of main undercarriage 1.3 is carbon fiber.

The wing 2 is fixedly connected to two sides of the rear end of the fuselage 1, the wing 2 comprises a wing spar 2.1, the wing spar comprises a main wing spar and a sub wing spar, the sub wing spar is fixedly connected with the fuselage 1, the top of the sub wing spar is fixedly connected with the main wing spar, the main wing spar is fixedly connected with the wing rib 2.2, the structural strength of the wing 2 is improved by the combination of the main wing spar, the sub wing spar and the wing rib 2.2, the wing rib 2.1 is made of a carbon fiber composite material, the wing rib 2.2 is vertical to the wing 2, the wing ribs 2.2 are uniformly distributed, support is provided for the wing, and the wing rib 2.2 is made of a carbon fiber composite material with a material slightly lower than the wing spar strength;

the auxiliary wing spar in this application is two auxiliary wing structures, be equipped with two auxiliary wing control surfaces 2.4 on the auxiliary wing spar, and install two auxiliary wing steering engines 6.3 on the auxiliary wing spar, every auxiliary wing steering engine 6.3 can control an auxiliary wing control surface 2.4, the unmanned aerial vehicle's in this application control wing totally 4 control surfaces and four auxiliary wing steering engines 6.3, every auxiliary wing steering engine 6.3 can control a control surface alone, so set up, other 3 control surfaces can maintain aircraft normal flight under the condition that a control surface breaks down, this unmanned aerial vehicle's reliability has been improved, and the torsion of control surface itself has been reduced.

The bottom of the auxiliary spar is provided with a stay bar connecting point 2.3, a vertical tail stay bar 3 can be installed on the wing 2 by utilizing the stay bar connecting point 2.3, the vertical tail stay bar 3 is a replaceable part, and when the aircraft needs to be lifted up, the stay bar can be lengthened.

The other end of the vertical tail stay bar 3 is fixedly connected with a vertical tail 4, the vertical tail 4 comprises a stay bar installation seat 4.1 fixedly connected with the other end of the vertical tail stay bar 3, a horizontal tail installation hole 4.2 is formed in the bottom of the stay bar installation seat 4.1, a vertical tail steering engine 6.4 is fixedly connected to the outer side face of the stay bar installation seat 4.1, and a vertical tail steering surface 4.3 is arranged on the outer side face of the stay bar installation seat 4.1.

The two vertical tails 4 are connected through a horizontal tail 5, and the horizontal tail 5 is used for keeping the stability of the airplane in flight and controlling the flight attitude of the airplane.

The horizontal tail 5 comprises a horizontal tail main body 5.1, quick-release screw holes are arranged on two sides of the horizontal tail main body 5.1, the quick-release screw holes and the horizontal tail mounting holes 4.2 are matched with M12.9-level screws, two M12.9-level screws are arranged, and the horizontal tail 5 and the vertical tail 4 can be connected together by using the M12.9-level screws; the horizontal tail main body 5.1 is of a double-horizontal-tail structure, one end of the horizontal tail main body 5.1, which is far away from the machine body 1, is provided with two horizontal tail control surfaces, one side of the horizontal tail main body 5.1, which is far away from one end of the machine body 1, is provided with a horizontal tail left control surface 5.2, the other side of the horizontal tail main body 5.1, which is far away from one end of the machine body 1, is provided with a horizontal tail right control surface 5.3, the horizontal tail left control surface 5.2 and the horizontal tail right control surface 5.3 are fixedly connected with a horizontal tail steering engine 6.5, the two horizontal tail steering engines 6.5 can differentially and synchronously move, and the horizontal tail steering engines connected with the horizontal tail steering engines can be controlled to overturn by utilizing the horizontal tail steering engines 6.5, so that the function of vertical flight of the unmanned aerial vehicle is realized.

All the electrical components related in the application are in the prior art, the connection mode is known to the person skilled in the art, all the electrical components in the application are connected with the power supply matched with the electrical components through wires by the person skilled in the art, and a proper control system is selected according to actual conditions so as to meet control requirements, specific connection and control sequences are described below, the electrical connection is completed through the sequence of operation among the electrical components, the detailed connection means are known in the art, the working principle and the process are mainly introduced, and the electrical control is not described.

To sum up: when the multi-mode large-load modularized multipurpose unmanned aerial vehicle is used, five parts of the fuselage 1, the wings 2, the vertical tail stay bars 3, the vertical tail 4 and the horizontal tail 5 are integrated into a whole through modularized design, and the rapid disassembly is supported, the load is installed in a load installation space, the unmanned aerial vehicle can be transported, and the load cannot influence the stability of flight.

When this unmanned aerial vehicle needs vertical flight, the control system in this unmanned aerial vehicle control horizontal tail steering wheel 6.5 work, and horizontal tail steering wheel 6.5 control horizontal tail steering wheel upwards deflects, and unmanned aerial vehicle upwards flies perpendicularly this moment, and when horizontal tail steering wheel deflected downwards, unmanned aerial vehicle received decurrent aerodynamic moment, unmanned aerial vehicle vertical flight now downwards.

The main technical indexes of the unmanned aerial vehicle system are as follows:

takeoff weight: 100-120 kg;

task load: 20-40 kg;

duration of time: more than or equal to 6 hours (20 kg task load);

cruise speed: 100-130 km/h;

maximum flat fly speed: 180km/h;

stall speed: less than or equal to 80km/h;

practical rise limit: 5000m;

highest takeoff altitude: 3500m;

maximum climbing rate at sea level: not less than 4m/s;

wind resistance rating: take off and land 5, cruise 7;

link range: 50km, 100km (optional);

use ambient temperature: -30-50 ℃.

The multi-mode large-load modularized multipurpose unmanned aerial vehicle can be used for various purposes such as fire protection, circuit railway line inspection, air experiment platforms and the like.

Standard parts used in the present utility model can be purchased from the market, the special-shaped parts can be customized according to the descriptions of the specification and the drawings, the specific connection modes of the parts are conventional means such as bolts, rivets, welding and the like which are mature in the prior art, and the machines, the parts and the equipment are conventional models in the prior art, so that details which are not described in detail in the specification belong to the prior art which is well known to the person skilled in the art, and although the embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations can be made in these embodiments without departing from the principle and spirit of the present utility model, and the scope of the present utility model is defined by the appended claims and equivalents thereof.

Claims (8)

1. The utility model provides a multi-mode big load modularization multipurpose unmanned aerial vehicle, includes fuselage (1), wing (2), vertical fin vaulting pole (3), vertical fin (4) and flat tail (5), its characterized in that: the front end of the machine body (1) is provided with a load installation space; the rear end of the machine body (1) is provided with a power system (7); the two sides of the rear end of the fuselage (1) are fixedly connected with wings (2), one end, far away from the nose landing gear (1.2), of each wing (2) is connected with a vertical tail (4) through a vertical tail stay bar (3), and the two vertical tails (4) are connected through a horizontal tail (5);

the wing (2) comprises a wing spar (2.1) and a wing rib (2.2), the wing spar (2.1) comprises a main wing spar and an auxiliary wing spar, the auxiliary wing spar is fixedly connected with the machine body (1), the top of the auxiliary wing spar is fixedly connected with the main wing spar, the main wing spar is fixedly connected with the wing rib (2.2), a brace connecting point (2.3) matched with a vertical brace (3) is arranged at the bottom of the auxiliary wing spar, an auxiliary wing rudder surface (2.4) is arranged at one end, close to a power system (7), of the auxiliary wing spar, and two auxiliary wing steering engines (6.3) are fixedly connected on the auxiliary wing spar;

the horizontal tail (5) comprises a horizontal tail main body (5.1), two horizontal tail control surfaces are arranged at the rear end of the horizontal tail main body (5.1), one side of each horizontal tail control surface is fixedly connected with a horizontal tail steering engine (6.5), and quick-release screw holes are formed in two sides of the horizontal tail main body.

2. A multi-mode, high-load modular multi-purpose unmanned aerial vehicle as claimed in claim 1, wherein: the load installation space is internally provided with a ring beam large space structure, and the top of the load installation space is provided with a machine head cabin cover (1.1).

3. A multi-mode, high-load modular multi-purpose unmanned aerial vehicle as claimed in claim 1, wherein: the bottom of the front end of the machine body (1) is provided with a front landing gear (1.2), and the front landing gear (1.2) integrates a shock absorbing device and a steering device; the bottom of the rear end of the machine body (1) is provided with a main landing gear (1.3), the main landing gear (1.3) is integrated with a hydraulic brake device, and the front landing gear (1.2) and the main landing gear (1.3) are made of different materials; the middle part of fuselage (1) front end fixedly connected with airspeed tube (6.1), the middle part at fuselage (1) top is connected with GPS antenna (6.2).

4. A multi-mode, high-load modular multi-purpose unmanned aerial vehicle as claimed in claim 1, wherein: the wing rib (2.2) is lower in strength than the wing spar, the auxiliary wing spar is of a double-auxiliary wing structure, two auxiliary wing control surfaces (2.4) are arranged, and the wing rib (2.2) is perpendicular to the wing (2).

5. A multi-mode, high-load modular multi-purpose unmanned aerial vehicle as claimed in claim 1, wherein: the horizontal tail (5) is of a double-horizontal-tail structure, the two horizontal-tail control surfaces are respectively a horizontal-tail left control surface (5.2) and a horizontal-tail right control surface (5.3), and one side of the horizontal-tail left control surface (5.2) and one side of the horizontal-tail right control surface (5.3) are fixedly connected with a horizontal-tail steering engine (6.5).

6. A multi-mode, high-load modular multi-purpose unmanned aerial vehicle as claimed in claim 1, wherein: the vertical fin (4) comprises a support rod installation seat (4.1) connected with a vertical fin support rod (3), a horizontal fin installation hole (4.2) is formed in the bottom of the support rod installation seat (4.1), and a vertical fin steering engine (6.4) is fixedly connected to the outer side face of the support rod installation seat (4.1).

7. The multi-mode, high-load modular multi-purpose unmanned aerial vehicle of claim 6, wherein: the quick-release screw hole and the horizontal tail mounting hole (4.2) are matched with M12.9-level screws, and two M12.9-level screws are arranged.

8. A multi-mode, high-load modular multi-purpose unmanned aerial vehicle as claimed in claim 1, wherein: the power system (7) comprises an oil filling port (7.1), an aircraft engine (7.2) and a propeller (7.3) which is matched with the aircraft engine (7.2), an oil tank is arranged below the oil filling port to supply oil for the aircraft engine, and the propeller (7.3) is positioned in the middle of the rear end of the airframe (1).

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