CN211139659U

CN211139659U - Coaxial double-propeller propulsion type tail rotor unmanned helicopter for logistics transportation

Info

Publication number: CN211139659U
Application number: CN201921269935.4U
Authority: CN
Inventors: 赵苏铭; �田�浩
Original assignee: Tianjin Dawn Times Information Technology Co ltd
Current assignee: Beiyisen Technology Chongqing Co ltd
Priority date: 2019-08-07
Filing date: 2019-08-07
Publication date: 2020-07-31
Anticipated expiration: 2029-08-07

Abstract

The utility model provides a coaxial double-oar adds unmanned helicopter of propulsion type tail-rotor for commodity circulation transportation, including fuselage, wing, coaxial double-oar screw, afterbody propulsion oar, fin, undercarriage and goods cabin. The aircraft body is used for installing the cargo compartment, the wings mainly provide certain lift force when the aircraft flies flatly, the coaxial double-propeller propellers improve the stability of the helicopter, the tail propulsion propeller provides thrust in the course when the aircraft flies flatly, the speed of the helicopter is increased, the tail wing controls the advancing and retreating of the helicopter, the landing gear is an integral 'sled' landing gear, the cargo compartment is composed of three independent cargo compartments and mainly made of glass fiber materials, the independent cargo compartment doors can rotate around the same rotating shaft, the independent cargo compartment doors can be opened to one side, the cargo can be loaded and unloaded conveniently, and meanwhile, two-dimensional codes are printed on the cargo compartment doors and used for recording detailed information of the cargo. The utility model discloses because of its load is big, the time of flight is long, and overall structure overall dimension is little, and the place requirement is not high, and the navigational speed is high, is fit for the commodity circulation transportation that is used for remote mountain area/area.

Description

Coaxial double-propeller propulsion type tail rotor unmanned helicopter for logistics transportation

Technical Field

The invention belongs to the technical field of logistics transportation unmanned aerial vehicle helicopters, and particularly relates to a coaxial double-propeller propulsion type tail rotor unmanned helicopter for logistics transportation.

Background

Unmanned aerial vehicle is the aircraft that rises gradually at present, because of its characteristics such as small, the cost is low, convenient to use, maintenance cost are low, require to the environment low and obtain wide application. In mountainous areas of China, the traditional road transportation cost is high, the efficiency is low, and particularly in remote mountainous areas, the road transportation cannot be realized at all. Therefore, a low-cost and high-efficiency transportation mode is needed to realize the cargo transportation in remote mountainous areas, and the general traditional unmanned aerial vehicle is small in load, short in range and low in speed, is widely applied to short-distance logistics transportation, but is weak in large-load and long-distance transportation.

The coaxial double-paddle propulsion tail-rotor unmanned helicopter has a good application prospect, and the coaxial double-paddle layout enables the helicopter to be compact in structure, small in overall dimension, symmetrical in reaction torque and high in hovering efficiency. Two pairs of rotors generate lift force, and the diameter of each pair of rotors can be correspondingly shortened. The body components can be compactly arranged at the center of gravity of the helicopter, and the flight stability is good. Compared with a single-rotor and tail rotor helicopter, the coaxial double-rotor helicopter has the advantages that the tail rotor is eliminated, so that the overall dimension of the coaxial double-rotor helicopter is reduced, the influence of crosswind is reduced, and the maneuverability of the coaxial double-rotor helicopter is remarkably improved. Meanwhile, the propulsion propeller is added at the tail part of the unmanned helicopter, so that the speed of the unmanned helicopter is greatly improved when the unmanned helicopter flies flatly, under the conditions of the same load and the same oil carrying capacity, the range of the coaxial double-propeller and tail-propulsion unmanned helicopter is farther than that of a single-rotor and tail-propulsion unmanned helicopter, and the speed of the unmanned helicopter during the flying flatly is higher than that of other unmanned helicopters, so that the unmanned helicopter is particularly suitable for logistics transportation.

Disclosure of Invention

In order to solve the technical problem, the invention provides a coaxial double-propeller propulsion type tail rotor unmanned helicopter wing for logistics transportation, which is arranged on two sides of a fuselage by taking the fuselage as a symmetry axis, wherein the two sides of the fuselage are respectively a left wing and a right wing; the wings and the axis of the helicopter are in the same plane and are perpendicular to the normal axis of the helicopter; a coaxial double-propeller is arranged on the machine body; the tail part of the machine body is provided with a tail propelling paddle; the belly of the machine body is provided with a cargo compartment which is divided into 3 independent cargo compartments.

Preferably, the outer skin of the fuselage is mainly made of carbon fiber materials, and part of the outer skin is made of glass fiber non-metal materials, so that the self weight of the fuselage is reduced.

Preferably, the independent cargo compartments are independently rotatable about the same axis of rotation.

Preferably, the independent cargo compartment is printed with a cargo information two-dimensional code.

The invention has the beneficial effects that: the load is big, long duration, overall structure overall dimension is little, and the place requirement is not high, and the navigational speed is high, is particularly suitable for the commodity circulation transportation in remote mountain area/region.

Drawings

Fig. 1 is a schematic structural diagram of a coaxial double-propeller propulsion type tail rotor logistics transportation unmanned helicopter.

Fig. 2 is a schematic structural diagram of the coaxial double-rotor propulsion type tail rotor unmanned helicopter.

Fig. 3 is a schematic view of the structure of the coaxial twin-screw propeller of the present invention.

Fig. 4 is a schematic view of the landing gear and fuselage deckle structure of the present invention.

Fig. 5 is a schematic illustration of the structural attachment of the fuselage cargo compartment of the present invention.

Fig. 6 is a schematic structural view of the fuselage cargo compartment securing mechanism of the present invention.

In the figure: a fuselage-1; a wing-2; coaxial double-oar propeller-3; tail propulsion paddle-4; a tail fin-5; a landing gear-6; a cargo hold-7; -a separate cargo hold-71; a hydraulic rod joint-72 for lifting the independent cargo hold; independent cargo compartment locking hooks-73; a limiting rod-74; -75 fixed joint; an independent cargo compartment door-76; the independent cargo compartment and fuselage joint connecting shaft-77; the cargo hold of the fuselage is connected with the joint-11; the fuselage is connected with the cargo hold by the shaft pin-12; a hydraulic rod-13; independent cargo compartment locking structures-14; landing gear clasp-61; a frame plate-15 of the machine body mechanism; landing gear buckle bolt holes-611; fuselage frame plate bolt holes-151.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The invention is further described below:

example 1:

as shown in attached figures 1 and 2, the wings 2 of the coaxial double-propeller propulsion type tail rotor unmanned helicopter for logistics transportation are arranged on two sides of a fuselage 1 by taking the fuselage 1 as a symmetry axis, the outer skin of the fuselage 1 is mainly made of carbon fiber materials, the part of the outer skin is made of glass fiber non-metal materials, the dead weight of the fuselage is reduced, and the two sides are respectively a left wing and a right wing; the wing 2 and the axis of the helicopter are in the same plane and are perpendicular to the normal axis of the helicopter; a coaxial double-propeller 3 is arranged on the machine body 1; the tail of the engine body 1 is provided with a tail propelling paddle 4, and the tail propelling paddle 4 transmits a part of power output by the engine to the tail propelling paddle through a transmission device connected with a speed reducing device. The tail propulsion paddle is in a working mode realized by an electric control system, and is enabled to enter a working state when the helicopter flies flatly and stop working in the taking-off and landing processes; the belly of the machine body 1 is provided with a cargo compartment 7.

As shown in fig. 3, the propellers are arranged in the form of the coaxial double-propeller propellers, the coaxial double-propeller helicopter is stable in flight and is divided into an upper-layer main propeller 31 and a lower-layer main propeller 32, and torsional moments generated by rotation of the propellers are offset by means of reverse rotation of the upper-layer main propeller and the lower-layer main propeller, so that the stable posture of the helicopter is ensured. When the machine body turns, the rotating speed of the upper layer of main slurry and the lower layer of main slurry is changed to form a torsion moment difference, so that the machine body turns. The lower main paddle is pulled through a servo (steering engine) to change the inclination direction of the lower main paddle, so that the helicopter can transversely move left and right.

As shown in fig. 4, the helicopter landing gear is an integral ski type landing gear, and the landing gear fixing part comprises an upper clamping piece 15 welded with the frame plate of the helicopter body and a lower clamping piece 61 fixed with the upper clamping piece 15 welded with the frame plate of the helicopter body. Wherein, the upper clamping piece 15 is provided with a bolt mounting hole 151, the lower clamping piece 16 is provided with a bolt mounting hole 611, a bolt fixes the undercarriage 6 and the machine body 1 through the mounting hole 151 and the mounting hole 611, the undercarriage 6 is formed by bending two ends of a rectangular frame downwards, and the middle part of the rectangular frame is fixed between the upper clamping piece 15 and the lower clamping piece 61 welded on a frame plate of the machine body. Meanwhile, a rubber sleeve 612 is clamped between the landing gear fixing upper clamping piece 15, the lower clamping piece 61 and the landing gear 6, so that the helicopter can play a slight role in shock absorption when landing.

As shown in fig. 5, the cargo compartment 7 is formed by fixing three independent cargo compartments 71 together through a rotating shaft 77, the independent cargo compartments 71 are integrally made of glass fiber materials, so that the cargo compartment is light in weight and has sufficient strength, the cargo compartment 7 is provided with a pull rod 74, a pull rod 74 connecting and fixing joint 75 and a compartment door 76, the compartment door 76 and the independent cargo compartment 71 are fixedly connected through a hinge joint, one end of the pull rod 74 is fixed with the independent cargo compartment 71 through a bolt, the other end of the pull rod 74 is fixed with the fixing joint 75 through a bolt, and the fixing joint 75 is connected with the cargo compartment door 76 through a bolt.

As shown in fig. 5 and fig. 6, the cargo hold 7 is connected to the pivot joint 11 of the body 1 through the pivot 77, the hydraulic rod 12 of the body 1 is connected to the hydraulic rod joint 72 of the cargo hold 7 through a bolt, and is mainly used for the lifting of the cargo hold 7 during the loading and unloading of cargo, the cargo hold 7 uses the pivot 77 of the cargo hold as a rotation axis during the lifting, the two-dimensional code is printed on the independent cargo hold door 76 of the cargo hold 7, the two-dimensional code on the independent cargo hold door 76 is used for recording the cargo information in the cargo hold, and when the two-dimensional code is scanned by a code scanner, the cargo information in the cargo hold can be displayed, so that ground personnel can conveniently obtain the cargo information in the hold.

It should be noted that, in the present embodiment, relative spatial terms such as "upper", "lower", "left", "right", and the like are used to describe a relationship between a feature in the drawing and another feature of an element. The spatial terms are intended to encompass different orientations of the device in use or operation. For example, if the device in the figures is turned over, elements described as being "left" relative to other elements or features would then be oriented "right" relative to the other elements or features. Thus, "left" in example terminology may encompass both "left" and "right" orientations. The elements may be otherwise oriented (rotated 90 or at other orientations) and the spatially relative descriptors used herein interpreted accordingly. Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. A coaxial double-propeller propulsion type tail rotor unmanned helicopter for logistics transportation is characterized in that wings (2) are arranged on two sides of a fuselage (1) by taking the fuselage (1) as a symmetry axis, and a left wing and a right wing are respectively arranged on two sides of the fuselage (1); the wing (2) and the axis of the helicopter are in the same plane and are perpendicular to the normal axis of the helicopter; a coaxial double-propeller (3) is arranged on the machine body (1); the tail part of the machine body (1) is provided with a tail propelling paddle (4); the belly of the machine body (1) is provided with a cargo cabin (7), and the cargo cabin (7) is divided into 3 independent cargo cabins (71).

2. The coaxial twin-screw propulsion type tail rotor unmanned helicopter for logistics transportation of claim 1, characterized in that: the outer skin of the fuselage (1) is mainly made of carbon fiber materials, and the part of the outer skin is made of glass fiber non-metal materials, so that the dead weight of the fuselage is reduced.

3. The coaxial twin-screw propulsion type tail rotor unmanned helicopter for logistics transportation of claim 1, characterized in that: the independent cargo compartments (71) can rotate independently around the same rotating shaft.

4. The coaxial twin-screw propulsion type tail rotor unmanned helicopter for logistics transportation of claim 1, characterized in that: the independent cargo hold (71) is printed with a cargo information two-dimensional code.