CN110228590A - A kind of detachable cargo hold connection wing twin fuselage logistics unmanned plane - Google Patents

Abstract

The invention discloses a detachable cargo hold connecting wing twin-fuselage logistics unmanned aerial vehicle. The detachable cargo hold connecting wing double-fuselage logistics drone includes a wing-body fusion type double fuselage, a lower main wing, an upper Aileron, propulsion device, modular detachable cargo compartment, flight control system and vertical tail; the wing-body fusion type twin fuselage and the lower main wing adopt a smooth transition of curved surface, and the lower main wing and the upper aileron form a connection Wing structure, the modular detachable cargo compartment is located in the middle of the lower main wing, and the flight control system includes flaps located on the inner side of the lower main wing, outer ailerons, elevators and rudders located on the upper aileron. The dual-fuselage logistics UAV of the present invention has relatively high load loading space, excellent aerodynamic performance, better airport adaptability, excellent economy and high cargo loading efficiency.

Description

A detachable cargo hold connecting wing twin-fuselage logistics UAV

technical field

The invention relates to the field of design and manufacture of unmanned aerial vehicles, 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 the importance of drones, and has formed a long-distance, medium-distance, medium-distance, short-distance, and terminal logistics system. The terminal and short-distance logistics distribution is generally It can be realized by manned truck express delivery or multi-rotor UAV. Long-distance can be completed by enterprise railway, highway and large-scale passenger-to-cargo manned aircraft. However, for medium-distance and medium-distance logistics transportation, the use of the above methods will increase the cost and urgently need a solution. An air transportation method used for medium-distance or medium-distance logistics transportation. In view of the short range 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 drones is one of the effective ways to achieve this.

The technical problem of the present invention lies in the following key problems in the current design of medium and long-range logistics UAVs: (1) The payload of UAVs is small; (2) The adaptability of airports, especially general airports, is poor; (3) Economical and loading efficiency is low. Thereby limiting the popularity of logistics drones.

In order to solve the above problems, the present invention adopts the following key technical approaches: (1) The payload of the UAV can be greatly increased by 50-80% by using dual fuselages combined with a modular detachable cargo hold; (2) In order to improve the airport adaptability, The wing-to-wing structure is adopted, and the wingspan is reduced by 30-50%, so that drones with the same level of take-off weight can be applied to general aviation airports; (3) Modular and detachable combined with wing-body fusion design and drag-reducing streamline shape The structural design of the cargo compartment and connecting wings reduces the flight resistance by about 10%. At the same time, it has good structural strength and low structural weight, which effectively improves the flight range; Combined with the design, it can greatly increase the speed of cargo loading and unloading, and relieve the logistics pressure faced by future airports.

Contents of the invention

The purpose of the present invention is to address the above problems and provide a detachable cargo bay connecting wing dual-fuselage logistics UAV that greatly increases the payload, improves the economy of aviation logistics, improves airport adaptability and cargo loading and unloading speed.

In order to achieve the above object, the present invention adopts the following technical solutions: a detachable cargo hold connecting wing double-fuselage logistics UAV of the present invention, the detachable cargo hold connecting wing double-fuselage logistics UAV includes wing Body-integrated twin-fuselage, lower main wing, upper aileron, propulsion device, modular detachable cargo compartment, flight control system and vertical tail; the wing-body integrated twin-fuselage and lower main wing adopt smooth surface Transition, the lower main wing and the upper auxiliary wing form a connecting wing structure, the wing-body fusion type twin fuselage is located at the position where the lower main wing is 0.2 to 0.6 times half-span from the wing root, and the upper auxiliary wing The wing is connected to the wingtip position of the lower main wing to form a connecting wing structure. The propulsion device and the vertical tail are all located at the tail of the wing-body fusion type twin fuselage. The vertical tail is connected with the upper auxiliary wing to improve the connection. Wing structural strength, and improve UAV directional stability. The modular detachable cargo compartment is connected to 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 fused twin fuselage, The outer trailing edge of the lower main wing and the trailing edge of the upper auxiliary wing.

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

Further, the upper auxiliary wing is a low-speed airfoil or laminar flow 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, which is connected to the wing root of the lower main wing by quick insertion, and the center of gravity is basically located at 0.25 times the chord length of the wing root.

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

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 UAV takes off Lifting device for increasing lift; the aileron is located on the outer trailing edge of the lower main wing, and can extend to the inside of the lower main wing along the span direction according to mission requirements, and is used for rolling manipulation and control of the drone; the elevator is located on the upper The position of the trailing edge of the aileron realizes the pitch operation of the UAV and assists in the roll operation; the rudder is located at the rear part of the vertical tail.

Further, the upper auxiliary wing is 0~0.3 times half-span length from the wingtip,

Further, the materials of the wing-body fused twin fuselage, the lower main wing and the upper auxiliary wing are composite materials or other lightweight high-strength materials.

Beneficial effects: the present invention comprehensively improves the air transportation capacity of the logistics UAV based on the dual-fuselage design, connecting wing structure, modular detachable cargo compartment, wing-body fusion and streamlined design. Combined with dual fuselages and modular detachable cargo compartments, the payload can be greatly increased by 50-80%; the modular detachable cargo compartments and connecting wing structure with wing-body fusion technology and drag-reducing streamlined shape can reduce flight resistance by 10% ;With excellent adaptability to general aviation airports, with the substantial increase of general aviation airports, it will surely provide higher convenience for logistics drones, and the adaptability of general aviation airports will become an important constraint for logistics drones; combined with modular and detachable The design idea can greatly improve the efficiency of drone cargo loading and unloading, and improve the speed of logistics.

Compared with the existing unmanned aerial vehicle with the same task, the present invention has the following advantages:

(1) The invention effectively combines the dual-fuselage design and the connecting wings, which solves the contradiction between heavy loads and airport adaptability, and makes it possible to take off and land medium- and long-range logistics drones at general aviation airports;

(2) The load loading method of the present invention is flexible, combining the traditional loading method of the fuselage (for some difficult-to-disassemble task loads) and the modular detachable reloading method (mainly for conventional logistics goods), which greatly improves the loading and unloading of cargo. efficiency.

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

Description of drawings

Fig. 1 is the oblique view of the present invention;

Fig. 2 is the top view of the present invention;

Fig. 3 is a side view of the present invention;

Among them, 1 wing-body fusion twin fuselage, 2 lower main wing, 3 upper aileron, 4 propulsion device, 5 modular detachable cargo hold, 6 flight control system, 61 flap, 62 aileron, 63 elevator, 64 rudders, 7 vertical tail.

Detailed ways

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

Example 1

A detachable logistics UAV with connecting wings and double fuselages of the present invention, the detachable logistics UAV with connecting wings and double fuselages of the cargo compartment includes a wing-body fusion double fuselage 1, a lower main wing 2, Upper auxiliary wing 3, propulsion device 4, modular detachable cargo hold 5, flight control system 6 and vertical tail 7.

The wing-body fused twin fuselage 1 and the lower main wing 2 adopt a smooth transition on a curved surface, and the lower main wing 2 and the upper auxiliary wing form a connecting wing structure. The wing-body fused twin fuselage 1 is located at the position where the lower main wing 2 is 0.2 times half-span from the wing root.

The lower main wing 2 adopts a low-speed airfoil with a sweep angle of 10 degrees and a dihedral angle of 0 to 3 degrees to improve flight stability. The upper auxiliary wing 3 is connected to the wing tip position of the lower main wing 2, and is 0.1 and a half times as long as the wing tip to form a connecting wing structure. The upper auxiliary wing 3 is a low-speed airfoil or a laminar flow airfoil , with a sweep angle of 18 degrees.

The wing-body fused twin fuselage 1, the lower main wing 2 and the upper auxiliary wing 3 are made of composite materials or other lightweight high-strength materials.

The modular detachable cargo compartment 5 has a drag-reducing and streamlined shape, and is connected to the wing root of the lower main wing 2 by quick insertion, so that the center of gravity is basically located 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 twin-fuselage 1 and is a twin-engine propulsion system, which can be driven by batteries or turboprop engines.

The 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 type twin fuselage 1, and are used for unmanned aerial vehicles A lift-increasing device for increasing lift during take-off; the aileron 62 is located on the outer trailing edge of the lower main wing 2, and can extend to the inner side of the lower main wing 2 along the span direction according to mission requirements, and is used for rolling manipulation and control of the UAV; the elevator 63 is positioned at the trailing edge position of upper auxiliary wing 3, realizes UAV pitching operation, and assists in realizing roll operation; Rudder 64 is positioned at the rear side part of vertical tail 7.

The vertical tail 7 is located at the tail of the wing-body fusion type twin fuselage 1, and is connected with the upper auxiliary wing 3, so as to improve the structural strength of the connecting wing and improve the directional stability of the drone.

Example 2

The difference between embodiment 2 and embodiment 1 is:

The wing-body fused twin fuselage 1 is located at the position where the lower main wing 2 is 0.3 times half-span from the wing root;

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

Described upper auxiliary wing 3 is connected to the wingtip position of lower main wing 2, and is 0.15 times of half spread length from wing tip, forms the connecting wing structure, and described upper auxiliary wing 3 is low-speed airfoil, and the sweep angle is 25 degree.

The wing-body fused twin fuselage 1, the lower main wing 2 and the upper auxiliary wing 3 are made of aluminum-magnesium alloy and composite materials.

Example 3

The wing-body fused twin fuselage 1 is located at the position where the lower main wing 2 is 0.4 times half-span from the wing root;

The lower main wing 2 adopts a laminar airfoil with a sweep angle of 20 degrees and a dihedral angle of 1 degree;

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

The wing-body fused twin fuselage 1, the lower main wing 2 and the upper auxiliary wing 3 are made of aluminum-magnesium alloy and carbon fiber materials.

Example 4

The difference between embodiment 4 and embodiment 1 is:

The wing-body fused twin fuselage 1 is located at the position where the lower main wing 2 is 0.5 times half-span from the root of the wing;

The lower main wing 2 adopts a laminar flow airfoil with a sweep angle of 25 degrees and a dihedral angle of 1.5 degrees;

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

The wing-body fused twin fuselage 1, the lower main wing 2 and the upper auxiliary wing 3 are made of aluminum-magnesium alloy and carbon fiber materials.

Example 5

The difference between Embodiment 5 and Embodiment 1 is that the wing-body fused twin fuselage (1) is located at a position 0.2 times half-span from the lower main wing (2) to the root of the wing, and the lower main wing 2 adopts a Flow airfoil, the sweep angle is 30 degrees, and the dihedral angle is 0 degree; the upper auxiliary wing 3 is a laminar flow airfoil, and the sweep angle is 35 degrees.

Example 6

The difference between Embodiment 6 and Embodiment 1 is that the wing-body fused twin fuselage (1) is located at a position 0.6 times the half-span length of the lower main wing (2) from the root of the wing, and the lower main wing 2 adopts a layer Flow airfoil, the sweep angle is 0 degrees, and the dihedral angle is 3 degrees; the upper auxiliary wing 3 is a laminar flow airfoil, and the forward sweep angle is 5 degrees.

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

Although this paper mostly uses 1 wing-body blended twin fuselage, 2 lower main wings, 3 upper auxiliary wings, 4 propulsion devices, 5 modular detachable cargo compartments, 6 flight control systems, 61 flaps, 62 pairs of 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 for the purpose of describing and explaining the essence of the present invention more conveniently; interpreting them as any kind of additional limitation is against the spirit of the present invention.

Claims (8)

1. a kind of detachable cargo hold connects wing twin fuselage logistics unmanned plane, it is characterised in that: the detachable cargo hold connects Wing twin fuselage logistics unmanned plane is connect to include blended wing-body formula twin fuselage (1), lower part host wing (2), upper secondary wing (3), promote Device (4), modular removable formula cargo hold (5), flight control system (6) and vertical tail (7), the blended wing-body formula are double Fuselage (1) and lower part host wing (2) are seamlessly transitted using curved surface, and the lower part host wing (2) and upper secondary wing (3) are constituted Wing structure is connected, the blended wing-body formula twin fuselage (1) are located at lower part host wing (2) away from 0.2 ~ 0.6 sesquialter length position of wing root It sets, the wingtip position that the upper secondary wing (3) is connected to lower part host wing (2) forms connection wing structure, the propulsion Device (4) and vertical tail (7) are respectively positioned on the tail portion of blended wing-body formula twin fuselage (1), the vertical tail (7) and upper secondary Wing (3) is connected, and the modular removable formula cargo hold (5) is connected with lower part host wing (2), the flight control Wing flap (61), aileron (62), the elevator (63) of system (6) are respectively placed in modular removable formula cargo hold (5) and blended wing-body Between formula twin fuselage (1), the rear of the outside rear of lower part host wing (2), upper secondary wing (3).

2. detachable cargo hold according to claim 1 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described Lower part host wing (2) uses Low Speed Airfoil or laminar flow airfoil, and the angle of sweep of the lower part host wing (2) is 0 ~ 30 degree, described Lower part host wing (2) 0 ~ 3 degree of the upper counterangle.

3. detachable cargo hold according to claim 2 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described Upper secondary wing (3) is Low Speed Airfoil or laminar flow airfoil, and the sweepforward angle of the lower part host wing (2) is 5 ~ 35 degree.

4. detachable cargo hold according to claim 1 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described The shape of modular removable formula cargo hold (5) is drag reduction streamline shape, the wing for being connected to lower part host wing (2) by inserting mode fastly Root position, keep center of gravity generally within 0.25 times of chord length of wing root at.

5. detachable cargo hold according to claim 1 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described Propulsion device (4) is double hair propulsion systems, and the propulsion device (4) is that battery or turboprop drive.

6. detachable cargo hold according to claim 1 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described Flight control system (6) includes wing flap (61), aileron (62), elevator (63) and rudder (64), the wing flap (61) position Between modular removable formula cargo hold (5) and blended wing-body formula twin fuselage (1), the aileron (62) is located at lower part host wing (2) outside rear, the aileron (62) are extended to extending on the inside of lower part host wing (2), and elevator (63) is located at top The posterior border position of the slave wing (3), rudder (64) are located at the rear section of vertical tail (7).

7. detachable cargo hold according to claim 1 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described Upper secondary wing (3) is away from 0 ~ 0.3 sesquialter length of wingtip.

8. detachable cargo hold according to claim 1 connects wing twin fuselage logistics unmanned plane, it is characterised in that: described The material of blended wing-body formula twin fuselage (1), lower part host wing (2) and upper secondary wing (3) is that composite material or other lightweights are high Strong material.