CN211766301U - Double-body logistics unmanned aerial vehicle with detachable cargo compartment connecting wings - Google Patents

Abstract

The utility model discloses a detachable cargo hold connecting wing double fuselage logistics unmanned aerial vehicle. The upper aileron, propulsion device, modular detachable cargo compartment, flight control system and vertical tail; the described wing-body fusion double fuselage and the lower main wing adopt a smooth transition of curved surfaces, and the lower main wing and the upper aileron are composed of The connecting wing structure, the modular detachable cargo compartment is located in the middle of the lower main wing, and the flight control system includes flaps on the inner side of the lower main wing, ailerons on the outer side, elevators and rudders on the upper aileron. The dual-body logistics UAV of the utility model has high load loading space, excellent aerodynamic performance, better airport adaptability, excellent economy and high cargo loading efficiency.

Description

A detachable cargo compartment connected wing double fuselage logistics UAV

technical field

The utility model relates to the field of unmanned aerial vehicle design and manufacture, in particular to a detachable cargo hold connecting wing double fuselage logistics unmanned aerial vehicle.

Background technique

With the rapid development of e-commerce and the regional economy of airports, the logistics industry has become more and more aware of drones. Long-distance, medium-long-distance, medium-distance, short-distance, and terminal logistics systems have been formed. Terminal and short-distance logistics distribution is generally It can be realized by manned truck express or multi-rotor drone, and the long-distance can be completed by enterprise railway, highway and large passenger-cargo-cargo manned aircraft, but for medium- and long-distance logistics transportation, the above methods will increase the cost. An air transportation method used for medium to long-distance or medium-haul logistics transportation. In view of the range defects of short-range multi-rotors and the great cost of long-range manned cargo aircraft, the use of medium-sized and larger fixed-wing cargo UAVs is one of the effective ways to achieve this.

The technical problem of the present utility model lies in the following key problems in the current design of medium and long-distance logistics drones: (1) the payload of the drone is small; (2) the adaptability of airports, especially general airports is poor; (3) ) economy and loading efficiency are lower. This limits the popularity of logistics drones.

In order to solve the above problems, the present utility model adopts the following key technical approaches: (1) by adopting a dual fuselage combined with a modular and detachable cargo compartment, the payload of the UAV can be greatly increased by 50-80%; (2) in order to improve the adaptability of the airport , using a connected-wing structure, reducing the wingspan by 30~50%, making the UAV of the same level of take-off weight suitable for navigable airports; (3) Combined with the wing-body fusion design, the modular and detachable shape of the drag reduction streamline shape The design of the cargo hold and connecting wing structure reduces the flight resistance by about 10%, and at the same time has good structural strength and low structural weight, which effectively improves the voyage; (4) The fusion type double fuselage, modular detachable cargo hold The combined design can greatly improve the speed of cargo loading and unloading, and relieve the logistics pressure faced by the airport in the future.

Utility model content

The purpose of this utility model is to solve the above problems, to provide a detachable cargo hold connecting wing double fuselage logistics drone that greatly increases the payload, improves the aviation logistics economy, and improves the airport adaptability and cargo loading and unloading speed.

In order to achieve the above purpose, the utility model adopts the following technical solutions: a detachable cargo hold connecting wing double fuselage logistics unmanned aerial vehicle of the present utility model, the detachable cargo hold connecting wing double fuselage logistics unmanned aerial vehicle Including a wing-body blended twin fuselage, a lower main wing, an upper aileron, a propulsion device, a modular and detachable cargo compartment, a flight control system and a vertical tail; the wing-body blended twin fuselage and the lower main wing adopt The curved surface transitions smoothly, the lower main wing and the upper sub-wing form a connecting wing structure, the wing-body fusion double fuselage is located at a position of 0.2~0.6 times the half-span of the lower main wing from the wing root, and the upper The aileron is connected to the wing tip position of the lower main wing to form a connecting wing structure, the propulsion device and the vertical tail are both located at the tail of the wing-body fusion type double fuselage, and the vertical tail is connected with the upper aileron, Improve the structural strength of the connecting wing and improve the directional stability of the UAV. The modular detachable cargo compartment is connected with the lower main wing, and the flaps, ailerons and elevators of the flight control system are respectively placed between the modular detachable cargo compartment and the wing-body fusion double fuselage, Outboard trailing edge of the lower main wing, trailing edge of the upper aileron.

Further, the lower main wing adopts a low-speed airfoil or a laminar airfoil, the sweep angle of the lower main wing is 0 to 30 degrees, and the dihedral angle of the lower main wing is 0 to 3 degrees, Improve flight stability.

Further, the upper auxiliary wing is a low-speed airfoil or a laminar airfoil, and the forward sweep angle of the lower main wing is 5-35 degrees.

Furthermore, the shape of the modular detachable cargo compartment is a drag-reducing streamline shape, and is connected to the wing root of the lower main wing through a quick-plug method, keeping the center of gravity basically located at 0.25 times the chord length of the wing root.

Further, the propulsion device is a dual-engine propulsion system, and the propulsion device is driven by a battery or a turboprop.

Further, the flight control system includes flaps, ailerons, elevators and rudders, and the flaps are located between the modular detachable cargo compartment and the wing-body fusion double fuselage, and are used when the drone takes off. A lift-enhancing device for increasing lift; the aileron is located on the outer trailing edge of the lower main wing, and can be extended to the inner side of the lower main wing in the spanwise direction according to the mission requirements for the roll control and control of the UAV; the elevator is located on the upper part The position of the trailing edge of the aileron realizes the pitch operation of the drone and assists in the roll operation; the rudder is located on the rear part of the vertical tail.

Further, the upper aileron is 0 to 0.3 times and a half span from the wing tip,

Further, the materials of the wing-body fusion double fuselage, the lower main wing and the upper aileron are composite materials or other light-weight and high-strength materials.

Beneficial effects: The utility model is based on the double-fuselage design, the connecting wing structure, the modular and detachable cargo hold, the wing body fusion and the streamlined design, which comprehensively improves the air transport capability of the logistics drone. Combined with dual fuselage and modular detachable cargo compartment, the payload can be greatly increased by 50~80%; the modular detachable cargo compartment and connecting wing structure adopting wing-body fusion technology, drag-reducing streamline shape and connecting wing structure reduce flight resistance by 10% It has excellent adaptability to navigable airports. With the substantial increase of navigable airports, it will surely provide greater convenience for logistics drones, and the adaptability of navigable airports will become an important constraint for logistics drones; combined with modular and detachable The design idea can greatly improve the efficiency of UAV cargo loading and unloading, and improve the logistics speed.

Compared with the existing UAV with the same task, the utility model has the following advantages:

(1) The utility model effectively combines the double fuselage design and the connecting wings, which solves the contradiction between the heavy load and the adaptability of the airport, and makes it possible to take off and land the mid-to-long-distance logistics drone at the navigable airport;

(2) The load loading method of the utility model is flexible. Combined with the traditional loading method of the fuselage (for some task loads that are difficult to disassemble) and the modular detachable reloading method (mainly for conventional logistics goods), the load is greatly improved. Loading and unloading efficiency.

(3) The wing-body fusion design of the present invention reduces the flight resistance and is beneficial to improve the aerodynamic and structural characteristics of the UAV.

Description of drawings

Fig. 1 is the oblique view of the utility model;

Fig. 2 is the top view of the utility model;

Figure 3 is a side view of the utility model;

Among them, 1 wing-body blended twin fuselage, 2 lower main wings, 3 upper ailerons, 4 propulsion units, 5 modular detachable cargo compartments, 6 flight control systems, 61 flaps, 62 ailerons, 63 elevators, 64 rudders, 7 vertical stabilizers.

Detailed ways

The following examples are for illustrative purposes only and are not intended to limit the scope of the present invention.

Example 1

The utility model relates to a detachable cargo hold connecting wing double fuselage logistics drone. The detachable cargo hold connecting wing double fuselage logistics drone comprises a wing body fusion type double fuselage 1 and a lower main wing 2 , the upper aileron 3 , the propulsion device 4 , the modular detachable cargo compartment 5 , the flight control system 6 and the vertical tail 7 .

The wing-body fusion double fuselage 1 and the lower main wing 2 adopt a smooth transition of curved surfaces, and the lower main wing 2 and the upper aileron form a connecting wing structure. The wing-body blended twin fuselage 1 is located at a position of 0.2 times and a half span from the lower main wing 2 to the wing root.

The lower main wing 2 adopts a low-speed airfoil, the sweep angle is 10 degrees, and the dihedral angle is 0-3 degrees, so as to improve the flight stability. The upper sub-wing 3 is connected to the wing tip position of the lower main wing 2, and is 0.1 times and a half span from the wing tip to form a connecting wing structure, and the upper sub-wing 3 is a low-speed airfoil or a laminar airfoil. , the sweep angle is 18 degrees. The flaps 61, ailerons 62, and elevators 63 of the flight control system 6 are respectively placed between the modular detachable cargo compartment 5 and the wing-body fusion double fuselage 1, the outer rear edge of the lower main wing 2, the upper Trailing edge of aileron 3.

The wing-body fusion type double fuselage 1, the lower main wing 2 and the upper aileron 3 are composite materials or other light-weight and high-strength materials.

The modular and detachable cargo hold 5 is in the shape of a drag reduction streamline, and is connected to the wing root of the lower main wing 2 by means of quick insertion, keeping the center of gravity basically at 0.25 times the chord length of the wing root.

The propulsion device 4 is located at the tail of the wing-body fusion double fuselage 1, and is a dual-engine propulsion system, which can be driven by batteries or turboprop engines.

The described flight control system 6 includes flaps 61, ailerons 62, elevators 63 and rudders 64; the flaps 61 are located between the modular detachable cargo compartment 5 and the wing-body fusion double fuselage 1, and are used for unmanned aerial vehicles. A lift device that increases lift during take-off; aileron 62 is located on the outer rear edge of the lower main wing 2, and can be extended to the inner side of the lower main wing 2 along the span direction according to the mission requirements for the roll control and control of the UAV; the elevator 63 is located at the trailing edge position of the upper aileron 3 to realize the pitch operation of the drone and assist in the realization of the roll operation; the rudder 64 is located at the rear part of the vertical tail 7 .

The vertical tail 7 is located at the tail of the wing-body fusion double fuselage 1, and is connected with the upper sub-wing 3, which improves the structural strength of the connecting wing and improves the directional stability of the UAV.

Example 2

The difference between embodiment 2 and embodiment 1 is:

The wing-body fusion type double fuselage 1 is located at a position of 0.3 times and a half span from the lower main wing 2 from the wing root;

The lower main wing 2 adopts a low-speed airfoil, the sweep angle is 15 degrees, and the dihedral angle is 1 degree;

The upper sub-wing 3 is connected to the wing tip position of the lower main wing 2, and the distance from the wing tip is 0.15 times and a half to form a connecting wing structure. The upper sub-wing 3 is a low-speed airfoil, and the forward sweep angle is 25 degree.

The wing-body fusion type double fuselage 1, the lower main wing 2 and the upper sub-wing 3 are made of aluminum-magnesium alloy and composite materials.

Example 3

The described wing-body fusion type double fuselage 1 is located at a position where the lower main wing 2 is 0.4 times and a half span from the wing root;

The lower main wing 2 adopts a laminar airfoil, the sweep angle is 20 degrees, and the dihedral angle is 1 degree;

The upper sub-wing 3 is connected to the wing tip position of the lower main wing 2, and is 0.25 times and a half span from the wing tip to form a connecting wing structure, and the upper sub-wing 3 is a laminar airfoil with a forward sweep angle. is 35 degrees.

The wing-body fusion type double fuselage 1, the lower main wing 2 and the upper sub-wing 3 are made of aluminum-magnesium alloy and carbon fiber materials.

Example 4

The difference between Example 4 and Example 1 is:

The described wing-body fusion type double fuselage 1 is located at a position of 0.5 times and a half span from the lower main wing 2 from the wing root;

The lower main wing 2 adopts a laminar airfoil, the sweep angle is 25 degrees, and the dihedral angle is 1.5 degrees;

The upper sub-wing 3 is connected to the wing tip position of the lower main wing 2, and the distance from the wing tip is 0.3 times and a half to form a connecting wing structure. The upper sub-wing 3 is a laminar airfoil with a forward sweep angle. is 30 degrees.

The wing-body fusion type double fuselage 1, the lower main wing 2 and the upper sub-wing 3 are made of aluminum-magnesium alloy and carbon fiber materials.

Example 5

The difference between Example 5 and Example 1 is that the wing-body fusion type double fuselage (1) is located at a position of 0.2 times and a half span from the lower main wing (2) from the wing root, and the lower main wing 2 adopts a layer The flow airfoil has a swept angle of 30 degrees and a dihedral angle of 0 degrees; the upper aileron 3 is a laminar airfoil with a forward sweep angle of 35 degrees.

Example 6

The difference between Example 6 and Example 1 is that the wing-body fusion type double fuselage (1) is located at a position of 0.6 times and a half span from the lower main wing (2) from the wing root, and the lower main wing 2 adopts a layer of The flow airfoil has a sweep angle of 0 degrees and a dihedral angle of 3 degrees; the upper aileron 3 is a laminar airfoil with a forward sweep angle of 5 degrees.

The specific embodiments described herein are merely illustrative of the spirit of the present invention. Those skilled in the art of the present invention can make various modifications or supplements to the described specific embodiments or replace them in similar ways, but will not deviate from the spirit of the present invention or go beyond the appended claims the defined range.

Although this article uses 1 blended wing body double fuselage, 2 lower main wings, 3 upper ailerons, 4 propulsion units, 5 modular detachable cargo compartments, 6 flight control systems, 61 flaps, 62 pairs Wing, 63 elevator, 64 rudder, 7 vertical tail and other terms, but does not exclude the possibility of using other terms. These terms are used only to more conveniently describe and explain the essence of the present invention; it is contrary to the spirit of the present invention to interpret them as any kind of additional limitations.

Claims (8)

1. The utility model provides a wing double-fuselage commodity circulation unmanned aerial vehicle is connected to detachable cargo hold which characterized in that: the detachable cargo compartment connection wing double-fuselage logistics unmanned aerial vehicle comprises a wing-body fusion type double fuselage (1), a lower main wing (2), an upper auxiliary wing (3), a propulsion device (4), a modularized detachable cargo compartment (5), a flight control system (6) and a vertical tail wing (7), wherein the wing-body fusion type double fuselage (1) and the lower main wing (2) adopt curved surface smooth transition, the lower main wing (2) and the upper auxiliary wing (3) form a connection wing structure, the wing-body fusion type double fuselage (1) is located at a half-extended length position of the lower main wing (2) from a wing root by 0.2-0.6, the upper auxiliary wing (3) is connected to a wing tip position of the lower main wing (2) to form a connection wing structure, and the propulsion device (4) and the vertical tail wing (7) are both located at the tail part of the wing-body fusion type double fuselage (1), vertical tail wing (7) be connected with upper portion aileron (3), the detachable cargo hold of modularization (5) be connected with lower part main wing (2), flap (61), aileron (62), elevator (63) of flight operating system (6) arrange respectively in between the detachable cargo hold of modularization (5) and the wing body integration double fuselage (1), the outside trailing edge of lower part main wing (2), the trailing edge of upper portion aileron (3).

2. The double-fuselage logistics unmanned aerial vehicle of detachable cargo hold connection wing of claim 1, characterized in that: the lower main wing (2) adopts a low-speed wing type or a laminar flow wing type, the sweepback angle of the lower main wing (2) is 0-30 degrees, and the dihedral angle of the lower main wing (2) is 0-3 degrees.

3. The double-fuselage logistics unmanned aerial vehicle of detachable cargo hold connection wing of claim 2, characterized in that: the upper auxiliary wing (3) is a low-speed wing type or a laminar wing type, and the forward sweep angle of the lower main wing (2) is 5-35 degrees.

4. The double-fuselage logistics unmanned aerial vehicle of detachable cargo hold connection wing of claim 1, characterized in that: the modularized detachable cargo hold (5) is in the shape of a drag reduction streamline and is connected to the wing root part of the lower main wing (2) in a quick insertion mode, and the gravity center is basically located at the position of 0.25 times of the chord length of the wing root.

5. The double-fuselage logistics unmanned aerial vehicle of detachable cargo hold connection wing of claim 1, characterized in that: the propulsion device (4) is a double-engine propulsion system, and the propulsion device (4) is driven by a battery or a turboprop engine.

6. The double-fuselage logistics unmanned aerial vehicle of detachable cargo hold connection wing of claim 1, characterized in that: the flight control system (6) include flap (61), aileron (62), elevator (63) and rudder (64), flap (61) be located between modularization detachable cargo hold (5) and the fusogenic twin fuselage of wing body (1), aileron (62) be located the outside trailing edge of lower part main wing (2), aileron (62) extend to lower part main wing (2) inboard along the span direction, elevator (63) are located the trailing edge position of upper portion aileron (3), rudder (64) are located the rear portion of vertical tail wing (7).

7. The double-fuselage logistics unmanned aerial vehicle of detachable cargo hold connection wing of claim 1, characterized in that: the upper auxiliary wing (3) is 0-0.3 half of the span length away from the wing tip.

8. The double-fuselage logistics unmanned aerial vehicle of detachable cargo hold connection wing of claim 1, characterized in that: the wing body integrated double-body (1), the lower main wing (2) and the upper auxiliary wing (3) are made of composite materials.

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