WO2018103458A1

WO2018103458A1 - Tandem-wing unmanned aerial vehicle

Info

Publication number: WO2018103458A1
Application number: PCT/CN2017/106503
Authority: WO
Inventors: 刘城斌
Original assignee: 北京京东尚科信息技术有限公司; 北京京东世纪贸易有限公司
Priority date: 2016-12-09
Filing date: 2017-10-17
Publication date: 2018-06-14
Also published as: CN106828911B; CN106828911A

Abstract

Disclosed is a tandem-wing unmanned aerial vehicle, comprising a body (1), a front wing (2), a rear wing (3) and propeller assemblies (4), the front wing (2) being located lower than the rear wing (3). The propeller assemblies (4) are arranged on at least one of the front wing (2) and the rear wing (3), and the propeller assemblies (4) on two longitudinal sides of the body (1) are symmetrically arranged. Providing that the whole lift of the tandem-wing unmanned aerial vehicle is increased, the tandem-wing unmanned aerial vehicle achieves vertical ascending and descending, thereby optimizing the performance of the tandem-wing unmanned aerial vehicle, reducing the requirements of the tandem-wing unmanned aerial vehicle on a taking-off and landing field when working, and expanding the scenes of use and application scenarios of the tandem-wing unmanned aerial vehicle.

Description

Stranded drone

The present application is based on the application of the CN application number 201611127401.9, the filing date of which is filed on December 9, 2016, and the priority of which is hereby incorporated by reference.

Technical field

The present disclosure relates to the field of logistics and transportation, and more particularly to a winged drone.

Background technique

In the related art, the winged drone includes a fuselage, a front wing, a rear wing, and a front pull slurry disposed at the front end of the fuselage. When taking off, the front puller provides the power required for the flight, but the winged drone It is necessary to use the runway to take off and land.

Summary of the invention

The inventors have recognized that at least the following problems exist in the related art: the pyramidal machine can only be used in the case of a runway, so that the use of the turbofan is very limited.

In view of this, the embodiments of the present disclosure provide a winged drone that can optimize the performance of the existing winged drone and expand the use of the winged drone.

In accordance with an aspect of some embodiments of the present disclosure, a winged drone includes a fuselage, a front wing, a rear wing, and a propeller assembly, the front wing being positioned lower than the rear wing; the propeller assembly being disposed At least one of the front wing and the rear wing, the propeller assembly located on either longitudinal side of the fuselage is symmetrical.

In one embodiment, the number of propeller assemblies is greater than two and each of the propeller assemblies is equidistant from the center of gravity of the spider.

In one embodiment, the number of the propeller assemblies is four, and the positions of the first two of the propeller assemblies are higher than the positions of the two subsequent propeller assemblies.

In one embodiment, the number of the propeller assemblies is four, the first two of the propeller assemblies are located forward of the front wing, and the two rear propeller assemblies are located at the front and rear wings between.

In one embodiment, each of the propeller assemblies located on the same longitudinal side of the fuselage is fixed to the same crossbar, and the front propeller assembly is located above the crossbar, and the rear propeller assembly is located Below the crossbar; the crossbar is fixed to at least one of the front and rear wings.

In one embodiment, the distance between the propeller of each of the propeller assemblies and the crossbar is greater than the average aerodynamic chord length.

In one embodiment, the motor mounts of each of the propeller assemblies are secured to the crossbar.

In one embodiment, each of the crossbars is simultaneously secured to the front and rear wings by different vertical bars.

In one embodiment, the height of each of the propeller assemblies is between the height of the position of the front and rear wings.

In one embodiment, the horizontal distance between the front wing and the rear wing is 2.1 to 2.5 times the front chord length or the rear chord length, and/or the front wing and the rear The vertical distance of the wings is 0.8 to 1 times the front chord length or the rear chord length.

In one embodiment, the horizontal distance of the front wing and the rear wing is 2.35 times the chord length of the front wing or the chord length of the rear wing.

In one embodiment, the vertical distance of the front wing and the rear wing is 0.895 times the front chord length or the rear wing chord length.

In one embodiment, the rear wing has an upper dihedral angle of 2° to 4°.

In one embodiment, the rear corner of the rear wing is 3°.

According to the embodiment of the present disclosure, the structural form of the winged drone is skillfully utilized, and the propeller assembly is added to both sides of the fuselage unmanned aerial vehicle body, and the vertical take-off and landing of the cross-belt drone can be realized. In addition, the position of the front wing is lower than the position of the rear wing. By reasonably setting the relative positional relationship between the front wing and the rear wing, the negative influence of the lower washing airflow of the front wing on the rear wing is small, and the lift of the whole machine is obviously improved. . It can be seen that the above technical solution realizes the vertical lifting and lowering of the winged drone under the premise of improving the lift of the whole machine, and reduces the requirements for the landing and landing site when the winged drone works, and expands the wing wing. UAV usage scenarios and applications.

DRAWINGS

1 shows a front view of a winged drone in accordance with some embodiments of the present disclosure;

2 shows a left side view of a winged drone in accordance with some embodiments of the present disclosure;

3 shows a top schematic view of a winged drone in accordance with some embodiments of the present disclosure.

detailed description

The technical solution provided by the present disclosure will be described in more detail below with reference to FIGS. 1 to 3.

The technical terms or nouns used in this embodiment are explained.

Chord length: The distance from the leading edge of the wing to the trailing edge, measured in a direction parallel to the longitudinal axis of the fuselage.

Leading edge: the front point of the airfoil.

Trailing edge: the last point of the airfoil.

The chord: the line connecting the leading edge and the trailing edge.

Angle of attack: The angle between the forward direction of the wing (corresponding to the direction of the airflow) and the chord (different from the axis of the fuselage) is called the angle of attack or angle of attack, which is the reference for determining the attitude of the wing in the airflow.

Bottom wash: refers to the downward movement of the airflow through the wing when the wing generates lift, which is called down wash, and the down wash will also induce resistance.

Bottom wash angle: The angle between the direction of the airflow blown in front of the wing and the direction of the airflow behind the wing.

Upper (lower) contra-angle: The angle at which the wing is mounted on the fuselage, that is, the angle between the reference plane of the wing and the horizontal plane; when the wing is twisted, it refers to the angle between the torsion axis and the horizontal plane. From the rear of the nose along the longitudinal axis of the aircraft, the angle of the wing tips on both sides is upward. In the same way, the angle when hanging down is called the opposite angle.

Referring to FIG. 1, an embodiment of the present disclosure provides a winged drone including a fuselage 1, a front wing 2, a rear wing 3, and a propeller assembly 4. The position of the front wing 2 is lower than the position of the rear wing 3; the propeller assembly 4 is provided on the front wing 2 and/or the rear wing 3, and the propeller assembly 4 on the longitudinal sides of the fuselage 1 is symmetrical.

In this paper, the front of the winged drone is the front and the tail is the rear. The front wing 2 is closer to the nose and the rear wing 3 is closer to the tail.

Referring to Figure 1, the propeller assembly 4 includes a propeller 41, a motor (not shown), and a motor base 42 that is supported by a motor base 42 that is driven by a motor to provide vertical ascent and descent power to the winged drone.

After the propeller assembly 4 is set, the original front puller 5 of the winged drone can be retained. The operation of the front puller 5 and the propeller assembly 4 can be as follows. Here, four propeller assemblies are described as an example:

Takeoff stage: 4 vertical takeoff and landing propellers 41 start working first, providing vertical lift to make the winged drones leave the ground vertically, after the winged drones rise to a certain height (such as 100 meters), 4 vertical takeoffs and landings The propeller 41 lowers the speed so that the winged drone remains hovered.

Transfer to the leveling stage: After the hovering is stabilized, the front puller 5 starts to work, so that the winged drone can obtain the horizontal forward speed. In a short period of time (generally within 10 seconds), the winged drone The leveling speed is increased to the rated cruising speed (about 25 meters per second). At this time, the rotation speeds of the four propellers 41 are gradually decreased. After the flight speed is determined to meet the requirements, the four vertical take-off and descending propellers 41 completely stop working, and the speed is changed. Fixed wing flight mode.

Landing stage: 4 propellers 41 start to work, while the front puller 5 speed decreases. Under the action of air resistance, the horizontal flight speed gradually decreases until it is completely hovered. At this time, the front puller 5 stops working and adjusts 4 The propeller 41 causes the winged drone to land vertically on the ground.

According to the weight of the winged drone and the carrying capacity, the number of the propeller assemblies 4 can be set to 2, 4, 6 or 8 or even more, but the propeller assembly 4 on the longitudinal sides of the fuselage 1 needs Symmetrical to ensure that the winged drones take off smoothly.

The above technical solution makes clever use of the structural form of the winged drone, and adds the propeller assembly 4 to the two sides of the fuselage unmanned aerial vehicle body 1, which can realize the vertical take-off and landing of the cross-belt drone. In addition, the position of the front wing 2 is lower than the position of the rear wing 3, and by appropriately setting the relative positional relationship between the front wing 2 and the rear wing 3, the negative influence of the lower washing airflow of the front wing 2 on the rear wing 3 can be made small. The lift of the whole machine is obviously improved. It can be seen that the above technical solution realizes the vertical lifting of the winged drone under the premise of improving the lift of the whole machine, reduces the requirement of the landing and landing field when the winged drone works, and expands the use scenario of the winged drone. And the scope of application.

Referring to Figure 1, the number of propeller assemblies 4 is greater than two, and each propeller assembly 4 is equidistant from the center of gravity of the spider. The number of the propeller assemblies 4 is, for example, four, six, eight, or the like. The number of propeller assemblies 4 can be set according to the carrying capacity of the spider.

Referring to Figures 1 and 2, in the present embodiment, specifically, the number of propeller assemblies 4 is four, and the positions of the front two propeller assemblies 4 are higher than the positions of the latter two propeller assemblies 4. In this embodiment, taking two propeller assemblies 4 on the longitudinal sides of the fuselage 1 as an example, a total of four propeller assemblies 4 and four propeller assemblies 4 ensure that the winged drones smoothly take off and land.

Further, of the four propeller assemblies 4, the front two propeller assemblies 4 are located in front of the front wing 2, and the rear two propeller assemblies 4 are located between the front wing 2 and the rear wing 3.

The propeller assembly 4 is in the form of a front upper rear and a lower layout, which increases the distance between the propeller assembly 4 and the wing in the vertical direction, and reduces the mutual influence of the lower airflow of the propeller assembly 4 and the wing. In addition, this arrangement first ensures that the propeller assembly 4 is on both sides of the center of gravity, and then the airflow is maximally avoided in the vertical direction to improve the working efficiency. Finally, the propeller assembly 4 adopts a front upper rear lower arrangement, which is balanced with the position of the front wing 2 lower than the rear wing 3, thereby ensuring the flight performance of the winged drone.

The four propeller assemblies 4 may specifically adopt the following relative positional relationship: two propeller assemblies 4 are respectively disposed on the longitudinal sides of the fuselage 1, and the two propeller assemblies 4 located at the front end of the center of gravity of the turbofan are the same in height and located in the string. The two propeller assemblies 4 at the rear end of the center of gravity of the winged drone are positioned at the same height. This makes the center of gravity of the winged drone not change too much due to the provision of the propeller assembly 4, ensuring the flight performance of the winged drone.

Referring to Fig. 1, two propeller assemblies 4 on the same longitudinal side of the fuselage 1 are fixed on the same crossbar 6, and the front propeller assembly 4 is located above the crossbar 6, and the rear propeller assembly 4 is located on the crossbar 6. Under The crossbar 6 is fixed to the front wing 2 or the rear wing 3, and can also be fixed to the front wing 2 and the rear wing 3 at the same time.

Referring to Fig. 1, in this embodiment, the crossbar 6 is fixed to the front wing 2 and the rear wing 3 through different vertical rods 7 at the same time, so that the installation of the crossbar 6 can be more stable to ensure the installation of the propeller assembly 4. reliability.

Referring to Figure 1, in particular, a crossbar 6 is hinged with two vertical rods 7, one vertical rod 7 connected to the front wing 2, the other vertical rod 7 connected to the rear wing 3, the vertical rod 7 and the front wing 2. The connection of the rear wing 3 can be a detachable connection, such as a bolted connection. The motor of the propeller assembly 4 above is fixed to the crossbar 6, which serves as an auxiliary support.

The crossbar 6 and the vertical rod 7 may be integral or non-detachable. Of course, detachable connection can also be adopted in consideration of the convenience of subsequent disassembly and assembly and maintenance.

Referring to Figure 1, the distance between the propeller 41 of each propeller assembly 4 and the crossbar 6 is greater than the average aerodynamic chord length. The distance between the leading and trailing edges of the wing is called the chord length, and the length of the chord of the wing varies along the span. The average aerodynamic chord length is used to represent an average of the aerodynamic effects of the wing. The distance between the propeller 41 and the crossbar 6 is greater than the average aerodynamic chord length. The advantage of this arrangement is that if the distance is too small, the propeller 41 will wash the airflow on the surface of the wing when rotating, and the total lift of the aircraft is reduced. Keep the loss of lift loss within an acceptable range.

Referring to Figure 1, the motor base 42 of each propeller assembly 4 is secured to the crossbar 6. This facilitates the setting of the propeller assembly 4. This facilitates the setting of the propeller assembly 4.

Referring to Figure 1, the height of each of the propeller assemblies 4 is located between the heights of the front and

rear wings

2, 3. This arrangement makes the flight performance of the winged drones good.

The relative positional relationship between the front wing 2 and the rear wing 3 will be described below.

Referring to Fig. 1, the horizontal distance L1 of the front wing 2 and the rear wing 3 is 2.1 to 2.5 times the front chord length L0 or the rear chord length L0, and/or the vertical distance L2 of the front wing 2 and the rear wing 3 is The front chord length L0 or the rear chord length L0 is 0.8 times to 1 time.

The front chord length L0 and the rear chord length L0 are equal. For convenience of description, only the front chord length L0 will be described, but it is understood that the description of the rear chord length L0 is also possible.

The horizontal distance L1 refers to the distance between the leading edge of the front wing 2 and the leading edge of the rear wing 3 in the longitudinal direction of the body 1. The vertical distance L2 refers to the distance between the leading edge of the front wing 2 and the leading edge of the rear wing 3 in the vertical direction.

The horizontal distance L1 is specifically 2.1 times, 2.12 times, 2.16 times, 2.2 times, 2.25 times, 2.3 times, 2.4 times, 2.45 times, 2.5 times, etc. of the front chord length L0.

The vertical distance L2 is specifically, for example, 0.8 times, 0.85 times, 0.87 times, 0.9 times, 0.93 times, 0.95 times, 0.97 times, 1 time, etc. of the front chord length L0.

When the relative positional relationship between the front wing 2 and the rear wing 3 satisfies the above-mentioned qualification conditions, the negative influence of the lower washing airflow of the front wing 2 on the rear wing 3 is small, and the lift of the whole machine is remarkably improved. In the above technical solution, by cleverly setting the relative positional relationship between the front wing 2 and the rear wing 3, the current wing 2 spoiler will directly wash onto the rear wing 3, and the angle of attack of the winged drone is just the angle of attack after the stall. It is a range that is not required or will not be involved in flight, which ensures the lift of the rear wing 3 and avoids chattering.

Referring to Figure 1, in particular, the position of the front wing 2 is lower than the position of the rear wing 3. The advantage of using the front low and the high height is that if the front height is low, or the front and rear contours are taken, the airflow around the front wing will have a downward deflection tendency, and the whole or part of the rear wing will be shrouded under the front wing. In the washing airflow, the lift generated by the rear wing will be greatly reduced, which is not conducive to the increase of the aircraft lift and lift-to-drag ratio.

Further, the horizontal distance L1 between the front wing 2 and the rear wing 3 is 2.35 times the front chord length L0 or the rear wing chord length L0. When the distance of the front wing 3 and the chord length L0 maintain this relative distance, the downwashing flow of the front wing 2 has the least negative impact on the rear wing 3.

Referring to Fig. 1, alternatively, the vertical distance L2 between the front wing 2 and the rear wing 3 is 0.895 times the front chord length L0 or the rear wing chord length L0. This value causes the turbulence flowing through the front wing 2 to be in the effective range of attack angles of -6 to 16 degrees, and the greater than 16° wing unmanned stall will not directly wash onto the rear wing 3.

The upper reverse angle α of the rear wing 3 is 2° to 4°, and specifically, for example, 2°, 2.5°, 3°, 3.5°, 4°. The upper angle α increases the lateral stability of the winged drone, and the lower angle reduces the lateral stability of the winged drone, but the lower angle of reversal improves the maneuverability and flexibility of the winged drone. By adopting the lower dihedral angle of the above range, the above various performances can be well balanced. Specifically, the lateral stability of the winged drone can be increased, and the relative distance of the wing tip is increased, and the front wing 2 is in this state. The airflow interference to the rear wing 3 is small.

Alternatively, the upper reverse angle α of the rear wing 3 is 3°. With the above values, the airflow interference of the front wing 2 to the rear wing 3 is nearly minimized.

Referring to Figure 2, in particular, the front wing 2 is provided at the bottom of the fuselage drone fuselage 1. The bottom surface of the front wing 2 is almost flush with the bottom surface of the fuselage 1. This arrangement can make the front wing 2 and the rear wing 3 maintain a front low and rear high arrangement, which is beneficial to the flight performance of the winged drone.

Referring to Figure 2, in particular, the rear wing 3 is provided at the top of the fuselage drone fuselage 1. The bottom surface of the rear wing 3 can be higher than the top surface of the body 1. This arrangement can make the front wing 2 and the rear wing 3 maintain a front low rear height arrangement, and can ensure the relative positional relationship between the front wing 2 and the rear wing 3, which is beneficial to the flying performance of the winged drone. Play.

In the description of the present disclosure, it is to be understood that the terms "center", "longitudinal", "transverse", "front", "back", "left", "right", "vertical", "horizontal", "Top", "Bottom", "Inside", "Outside" The orientation or positional relationship of the indications is based on the orientation or positional relationship shown in the drawings, and is merely for the convenience of describing the present disclosure and the simplified description, and does not indicate or imply that the device or component referred to has a specific orientation, Azimuth construction and operation are therefore not to be construed as limiting the scope of the disclosure.

It should be noted that the above embodiments are only used to illustrate the technical solutions of the present disclosure and are not to be construed as limiting thereof; although the present disclosure will be described in detail with reference to the preferred embodiments, those skilled in the art should understand that Modifications of the specific embodiments disclosed are intended to be equivalent to the equivalents of the technical features of the present disclosure.

Claims

A winged drone comprising a fuselage (1), a front wing (2), a rear wing (3) and a propeller assembly (4), the front wing (2) being positioned lower than the rear wing (3) Position of the propeller assembly (4) at least one of the front wing (2) and the rear wing (3), the propeller assembly located on both longitudinal sides of the fuselage (1) (4) is symmetrical.
The winged drone according to claim 1, wherein the number of the propeller assemblies (4) is greater than two, and each of the propeller assemblies (4) is equidistant from a center of gravity of the spider.
The winged drone according to claim 1, wherein the number of the propeller assemblies (4) is four, and the positions of the first two of the propeller assemblies (4) are higher than the latter two of the propeller assemblies ( 4) The location.
The winged drone according to claim 1, wherein the number of the propeller assemblies (4) is four, and the front two of the propeller assemblies (4) are located in front of the front wing (2), behind Two of the propeller assemblies (4) are located between the front wing (2) and the rear wing (3).
The winged drone according to claim 1, wherein each of said propeller assemblies (4) located on the same longitudinal side of said fuselage (1) is fixed to the same crossbar (6), and the front The propeller assembly (4) is located above the crossbar (6), the rear propeller assembly (4) is located below the crossbar (6); the crossbar (6) is fixed to the front wing (2) And at least one of the rear wing (3).
A winged drone according to claim 5, wherein the distance between the propeller (41) of each of said propeller assemblies (4) and said crossbar (6) is greater than the average aerodynamic chord length.
A winged drone according to claim 5, wherein the motor base (42) of each of said propeller assemblies (4) is fixed to said crossbar (6).
A winged drone according to claim 5, wherein each of said crossbars (6) is simultaneously fixed to said front wing (2) and said rear wing (3) by different vertical bars (7).
The winged drone according to claim 1, wherein each of said propeller assemblies (4) has a positional height that is between a position height of said front wing (2) and said rear wing (3).
The winged drone according to claim 1, wherein a horizontal distance between the front wing (2) and the rear wing (3) is 2.1 times the front chord length or the rear wing chord length Up to 2.5 times, and/or the vertical distance of the front wing (2) and the rear wing (3) is 0.8 to 1 times the front chord length or the rear wing chord length.
The winged drone according to claim 10, wherein the horizontal distance between the front wing (2) and the rear wing (3) is 2.35 times the front chord length or the rear wing chord length .
The winged drone according to claim 10, wherein a vertical distance between the front wing (2) and the rear wing (3) is 0.895 times the front chord length or the rear wing chord length .
The winged drone according to claim 10, wherein the rear wing (3) has an upper dihedral angle of 2° to 4°.
The winged drone according to claim 13, wherein the rear wing (3) has an upper dihedral angle of 3°.