阅读说明：本技术 一种旋翼无人飞行器被动式增升装置及旋翼无人飞行器 (Rotor unmanned vehicles passive formula increases lift device and rotor unmanned vehicles ) 是由 张伟 于 2021-02-10 设计创作，主要内容包括：本发明公开了一种旋翼无人飞行器被动式增升装置,包括被动式增升叶片、固定轴、轴连接件、固定环和固定杆,每一个被动式增升叶片之间通过固定轴、轴连接件连接成整体,相邻的两个固定轴之间通过轴连接件连接,固定杆的一端与轴连接件连接,固定杆的另一端与固定环连接。本发明还公开了一种旋翼无人飞行器。该旋翼无人飞行器被动式增升装置的目的是解决旋翼无人飞行器的飞行效率低的问题。(The invention discloses a rotor unmanned aerial vehicle passive high lift device which comprises passive high lift blades, fixed shafts, shaft connecting pieces, fixing rings and fixing rods, wherein each passive high lift blade is connected into a whole through the fixed shaft and the shaft connecting piece, two adjacent fixed shafts are connected through the shaft connecting pieces, one end of each fixing rod is connected with the shaft connecting piece, and the other end of each fixing rod is connected with the fixing ring. The invention also discloses a rotor unmanned aerial vehicle. The purpose of this rotor unmanned vehicles passive form high lift device is to solve rotor unmanned vehicles's the problem that flight efficiency is low.)

1. The utility model provides a rotor unmanned vehicles passive form increases and rises device, its characterized in that, includes passive form increases and rises blade (1), fixed axle (2), axle connecting piece (3), solid fixed ring (4) and dead lever (5), each pass through between passive form increases and rises blade (1) fixed axle (2) axle connecting piece (3) connect into whole, adjacent two pass through between fixed axle (2) axle connecting piece (3) are connected, the one end of dead lever (5) with axle connecting piece (3) are connected, the other end of dead lever (5) with gu fixed ring (4) are connected.

2. A rotary-wing unmanned aerial vehicle passive high lift device according to claim 1, wherein at least one of the passive high lift blades (1), the stationary shaft (2) and the fixing rod (5) is made of carbon fiber.

3. The rotor Unmanned Aerial Vehicle (UAV) passive high lift device according to claim 1, wherein two ends of the upper wing surface of the passive high lift blade (1) are provided with limit fixing structures (101), and two ends of the fixed shaft (2) are respectively arranged in the corresponding limit fixing structures (101) in a penetrating manner.

4. A rotorcraft passive high lift device according to claim 1, wherein the leading and trailing edges of the passive high lift blades (1) each have a camber, with leading edge outer camber diameter and trailing edge inner camber diameter determined by the diameter of the propeller (7).

5. A rotary-wing unmanned aerial vehicle passive high lift device according to claim 4, wherein a trailing edge inner arc of the passive high lift blade (1) is at a lateral distance of 10mm from a blade plane of the propeller (7).

6. The rotorcraft passive high-lift device according to claim 5, characterized in that the mounting height of the passive high-lift blades (1) in a propeller flow field is at the same level as the wingtips of the propellers (7).

7. A rotorcraft passive high lift device according to claim 1, wherein a plurality of the fixed shafts (2) are connected to form a hexagonal structure.

8. A rotary-wing unmanned aerial vehicle, comprising a brushless motor (6), a propeller (7), a frame (8) and a rotary-wing unmanned aerial vehicle passive high-lift device according to any of claims 1-6, the brushless motor (6) being provided at an end of the frame (8), the rotary-wing unmanned aerial vehicle passive high-lift device being mounted on the frame (8) with the brushless motor (6) as a center.

9. The rotary-wing unmanned aerial vehicle of claim 8, wherein the fixed shaft (2) is circumferentially distributed around the propeller (7) by 60 ° with the brushless motor (6) as a center, and the fixed ring (4) is sleeved on the brushless motor (6).

10. A rotary-wing unmanned aerial vehicle according to claim 8, comprising one or more of said propellers (7).

Technical Field

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a rotor unmanned aerial vehicle passive lift-increasing device and a rotor unmanned aerial vehicle.

Background

The rotor unmanned aerial vehicle is widely applied to the military and civil fields at present, and although the rotor unmanned aerial vehicle can vertically take off and land, the stability and the safety are poor. The unmanned aerial vehicle with the rotors in special layout is researched and developed at home and abroad, such as a fixed-wing and rotor-wing composite unmanned aerial vehicle, a tilt-rotor unmanned aerial vehicle, a coaxial double-rotor unmanned aerial vehicle and the like. However, these particular arrangements of rotorcraft suffer from a number of disadvantages, including additional structure that adds weight to the aircraft, shorter endurance, and less efficient flight.

Meanwhile, through retrieval, the Chinese patent application with the application number of 201410790940.5, entitled oil-driven four-rotor unmanned aerial vehicle, is filed, wherein the Chinese patent application has the disadvantages of poor maneuverability and poor wind resistance caused by that an aero-engine is adopted as power, four groups of rotors are added, and the control of each group of rotors is realized through a servo steering engine and a variable pitch system, so that the traditional unmanned aerial vehicle has the advantages of poor maneuverability and good maneuverability due to that the lift force of the unmanned aerial vehicle depends on a propeller, and the operation depends on a fixed propeller pitch and variable speed mode.

Application number is 201711331142.6, and the application name discloses in the chinese patent application of a six rotor foldable plant protection unmanned vehicles, discloses about rotor unmanned aerial vehicle, wherein there is "the flight gesture of aircraft and is accomplished by four rotors on the host computer arm, and two rotors on the time horn only provide lift, have improved load capacity, also realize attitude control and speed control's decoupling zero simultaneously, have reduced the control degree of difficulty. "record, though provide lift and bearing capacity through the rotor that increases on the secondary horn, this six rotor plant protection unmanned aerial vehicle is the lithium cell energy supply, and two sets of rotor systems of increase can increase the weight of aircraft, consume more electric energy, and flight time can shorten, and there is not protective structure around the rotor, can have certain security problem.

The rotary-wing unmanned aerial vehicle disclosed in such patents can provide greater lift, but the presently described technology fundamentally has the following problems: changing the power mode and adding rotors to provide more power and lift, all of which cause problems of complex structure, increased weight, etc. that reduce the flight efficiency of the aircraft.

In view of the above, it is desirable to provide a passive high lift device for a rotor unmanned aerial vehicle and a rotor unmanned aerial vehicle to solve the above problems.

Disclosure of Invention

Technical problem to be solved

The invention solves the technical problem that the flight efficiency of the rotor unmanned aerial vehicle is low.

(II) technical scheme

The invention provides a rotor unmanned aerial vehicle passive high lift device which comprises passive high lift blades, fixed shafts, shaft connecting pieces, fixing rings and fixing rods, wherein each passive high lift blade is connected into a whole through the fixed shaft and the shaft connecting piece, two adjacent fixed shafts are connected through the shaft connecting pieces, one end of each fixing rod is connected with the shaft connecting piece, and the other end of each fixing rod is connected with the fixing ring.

Furthermore, at least one of the passive high lift blade, the fixed shaft and the fixed rod is made of carbon fiber.

Furthermore, two ends of the upper wing surface of the passive high lift blade are provided with limiting fixing structures, and two ends of the fixing shaft penetrate through the corresponding limiting fixing structures respectively.

Further, the front edge and the rear edge of the passive high lift blade are both provided with radians, and the diameter of the outer arc of the front edge and the diameter of the inner arc of the rear edge are determined according to the diameter of the propeller.

Further, the transverse distance between the inner arc of the rear edge of the passive high lift blade and the plane of the propeller blade is 10 mm.

Further, the installation height of the passive high lift blades in the propeller flow field is in the same horizontal plane with the wingtips of the propellers.

Further, a plurality of the fixed shafts are connected to form a hexagonal structure.

The invention also provides a rotary-wing unmanned aerial vehicle comprising a brushless motor, a propeller, a frame and the rotary-wing unmanned aerial vehicle passive high-lift device as claimed in any one of the claims, wherein the brushless motor is arranged at the end part of the frame, and the rotary-wing unmanned aerial vehicle passive high-lift device is mounted on the frame by taking the brushless motor as the center.

Furthermore, the fixed shaft is arranged around the propeller by surrounding the brushless motor as the center according to an angle, and the fixed ring is sleeved on the brushless motor.

Further, the rotary-wing unmanned aerial vehicle includes one or more of the propellers.

(III) advantageous effects

The invention provides a rotor unmanned aerial vehicle passive high lift device which comprises passive high lift blades, fixed shafts, shaft connecting pieces, fixing rings and fixing rods. Wherein, passive form high lift blade installs near rotor top, helps improving the flow field and provides extra stability for rotor unmanned vehicles, can produce bigger thrust with the open rotor of the same diameter and equivalent power, can make rotor unmanned vehicles have higher stability and propulsive efficiency in the high altitude area that the air is thin.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

Fig. 1 is a schematic structural diagram of a passive high lift device of a rotor unmanned aerial vehicle according to an embodiment of the present invention;

FIG. 2 is a schematic structural view of a lower airfoil surface of a passive high lift blade in a passive high lift device of a rotorcraft according to an embodiment of the present invention;

FIG. 3 is a schematic illustration of a passive high lift blade upper airfoil in a passive high lift device for a rotorcraft according to an embodiment of the present disclosure;

FIG. 4 is an isolated view of a passive high lift blade in a passive high lift device for a rotary wing drone in accordance with an embodiment of the present invention;

fig. 5 is a flight state diagram of a passive high lift device for a rotor unmanned aerial vehicle according to an embodiment of the present invention;

figure 6 is a free-state diagram of a rotary-wing unmanned aerial vehicle according to an embodiment of the present invention;

fig. 7 is a flight state diagram of a rotary-wing unmanned aerial vehicle according to an embodiment of the invention;

FIG. 8 is a schematic diagram of a passive high lift blade provided by an embodiment of the present invention;

fig. 9 is a graph of lift of a passive high lift blade versus propeller plane distance according to an embodiment of the present invention.

In the figure:

1-passive high lift blades; 101-a limit fixing structure; 2, fixing a shaft; 3-an axle connection; 4-fixing the ring; 5-fixing the rod; 6-a brushless motor; 7-a propeller; 8-a frame.

Detailed Description

The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the invention and are not intended to limit the scope of the invention, i.e., the invention is not limited to the embodiments described, but covers any modifications, alterations, and improvements in the parts, components, and connections without departing from the spirit of the invention.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

It should be clear that the embodiments in this specification are described in a progressive manner, and the same or similar parts in the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. The present invention is not limited to the specific steps and structures described above and shown in the drawings. Also, a detailed description of known process techniques is omitted herein for the sake of brevity.

According to the passive high lift device of the rotor unmanned aerial vehicle, as shown in fig. 1-5, the passive high lift device comprises passive high lift blades 1, fixed shafts 2, shaft connecting pieces 3, fixing rings 4 and fixing rods 5, wherein each passive high lift blade 1 is connected into a whole through the fixed shaft 2 and the shaft connecting piece 3, two adjacent fixed shafts 2 are connected through the shaft connecting pieces 3, one end of each fixing rod 5 is connected with the shaft connecting piece 3, and the other end of each fixing rod 5 is connected with the fixing ring 4.

In the above embodiment, the passive high lift device is in a free state when the rotor unmanned aerial vehicle is not in operation. When the unmanned aerial vehicle hovers or flies downwards, as shown in fig. 8, the airflow flowing out of the lower wing surface of the propeller 7 passes through the blade tip to form a plurality of strong vortexes and flows back to the upper wing surface of the propeller 7, and the passive high-lift blades 1 installed around the wing tip of the propeller 7 at the same horizontal plane are passively deflected upwards and are kept parallel to the plane of the propeller, so that additional lift is provided for the rotor unmanned aerial vehicle.

The arc-shaped structure of the passive high lift blade 1 is flexible to disassemble and assemble and simple to maintain.

In some alternative embodiments, at least one of the passive high lift blades 1, the fixed shaft 2 and the fixing rod 5 is made of carbon fiber. Specifically, the advantage that adopts carbon fiber material is that the quality is light, intensity is high, and is less to original rotor unmanned aerial vehicle aircraft's structure and quality influence.

In some alternative embodiments, as shown in fig. 3 to 4, two ends of the upper airfoil surface of the passive high lift vane 1 are provided with limiting fixing structures 101, and two ends of the fixing shaft 2 respectively penetrate through the corresponding limiting fixing structures 101. Specifically, two ends of the fixed shaft 2 are respectively penetrated through the limit fixing structures 101 and connected with the shaft connecting piece 3, so that the adjacent passive high lift blades 1 are sequentially connected into an integral structure.

In some alternative embodiments, as shown in fig. 2, the leading edge and the trailing edge of the passive high lift blade 1 both have a curvature, and the leading edge outer arc diameter and the trailing edge inner arc diameter are determined according to the diameter of the propeller 7.

Specifically, the radian ranges of the front edge and the rear edge are 50-60 degrees, so that six same passive high-lift blades 1 can be uniformly distributed around the propeller 7.

In some alternative embodiments, as shown in fig. 5, the inner arc of the trailing edge of the passive high lift blade 1 is 10mm from the blade plane of the propeller 7. Wherein, can guarantee that passive formula high lift blade 1 has certain safe distance with screw 7, can have better lift effect simultaneously.

In some alternative embodiments, the installation height of the passive high lift blades 1 in the propeller flow field is at the same level with the wingtips of the propeller 7.

In the above embodiment, the passive high lift blades 1 and the propeller 7 are in the same horizontal plane, so that the forward flight stability and the propulsion efficiency of the rotor unmanned aerial vehicle can be improved.

The lift force provided by the passive lift-increasing blade 1 is the largest on the plane of the propeller 7, as shown in fig. 9, the abscissa is the longitudinal distance between the lift-increasing blade and the plane of the propeller, and the ordinate is the lift force ratio between the lift-increasing blade and the single rotor, it can be seen that when the longitudinal distance between the passive lift-increasing blade 1 and the plane of the propeller 7 is 0 (that is, the lift force ratio between the passive lift-increasing blade 1 and the propeller 7 is on the same horizontal plane), the lift force ratio between the passive lift-increasing blade 1 and the propeller 7 is the largest, the maximum lift force is about 8% of the lift force provided by one propeller 7, a force opposite to the lift force direction is generated at a position above or below the plane of the rotor, and the effect is worse as the passive lift-increasing blade 1 is farther from the rotor.

In some alternative embodiments, a plurality of fixed shafts 2 are connected to form a hexagonal structure. Specifically, the passive high lift blades 1 are fixed on the carbon fiber fixing rods 5 distributed in a hexagon through the carbon fiber fixing rods 5 and the shaft connecting piece 3, and meanwhile, the passive high lift blades 1 can be limited in a horizontal position under the action of air flow.

According to a second aspect of the embodiment of the present invention, as shown in fig. 6-7, the rotor unmanned aerial vehicle includes a brushless motor 6, a propeller 7, a frame 8, and the above rotor unmanned aerial vehicle passive high-lift device, where the brushless motor 6 is disposed at an end of the frame 8, and the rotor unmanned aerial vehicle passive high-lift device is mounted on the frame 8 with the brushless motor 6 as a center.

In some alternative embodiments, the fixed shaft 2 is circumferentially distributed around the propeller 7 by 60 ° with the brushless motor 6 as the center, and the fixed ring 4 is sleeved on the brushless motor 6.

In some alternative embodiments, the rotary-wing unmanned aerial vehicle includes one or more propellers 7.

Specifically, four sets of passive high lift devices are arranged between a brushless motor 6 and a frame 8 of the four-rotor aircraft, and each high lift device is provided with six passive high lift blades 1, so that the unmanned aircraft can take off and land more flexibly, and the flight stability and the flight efficiency are higher.

It should be clear that the embodiments in this specification are described in a progressive manner, and the same or similar parts in the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. The present invention is not limited to the specific steps and structures described above and shown in the drawings. Also, a detailed description of known process techniques is omitted herein for the sake of brevity.

The above are merely examples of the present application and are not intended to limit the present application. Various modifications and alterations to this application will become apparent to those skilled in the art without departing from the scope of this invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.