CN108248851B - Device for protecting the rotor of an aircraft and aircraft with such a device - Google Patents

Abstract

The invention discloses a device for protecting aircraft rotors, wherein the number of the aircraft rotors is N, N is more than or equal to 2, the device comprises a lower cover provided with a motor installation position and provided with a side support plate, and the device is characterized by also comprising an upper cover arranged above the side support plate and a rectifying piece fixed in the enclosed area of the lower cover, the upper cover and the side support plate; the side supporting plate is provided with a first airflow hole; the upper cover is provided with a second airflow hole; the side of the fairing is not provided with airflow holes to distinguish airflow areas of the N rotors from each other. The beneficial effects are as follows: by adopting the rectifying piece, the dynamic effect is better on the basis of more comprehensive protection effect. The invention also discloses an aircraft, which is provided with at least two centrally symmetrical rotor wings, and the rotor wings are provided with the device. The beneficial effects are as follows: high safety and excellent dynamic effect.

Description

Device for protecting the rotor of an aircraft and aircraft with the same

technical field

The invention relates to the technical field of aircraft rotors, in particular to a device for protecting the aircraft rotors.

The invention also relates to the technical field of rotorcraft, in particular to an aircraft with an aircraft rotor protection device.

Background technique

The quadrotor aircraft has a simple structure and flexible flight mode. It has been widely used in agricultural plant protection, geological exploration, environmental protection, express transportation, aerial photography and other industries. With the rapid development of computer technology and the application of artificial intelligence in various fields, drones will attract more and more attention.

Although the quadrotor has a simple structure and strong maneuverability, it still poses a great safety hazard for users to fly without professional training. Especially in densely populated areas, once a high-speed flying drone loses control or falls from a high altitude, it will endanger the lives and property of others, causing unnecessary casualties and economic losses.

The Chinese patent document CN204846369U published on December 9, 2015 discloses a rotor protection cover for a rotary-wing unmanned aerial vehicle. An airflow channel for the airflow to flow between the two rotor protective covers is provided at the opposite position adjacent to the rotor protective cover body, and the rest of the side wall of the protective cover body is also uniformly provided with through holes for reducing the load. The technical solution uses a circular protective cover to protect the side of the drone's rotor, but with the increase of high-rise buildings, the drone may also be affected by falling objects when taking off and landing, causing the rotor to break and lead to flight accidents.

SUMMARY OF THE INVENTION

The problem to be solved by the present invention is to provide a device for protecting the rotor of an aircraft, which has better dynamic effects on the basis of more comprehensive protection.

In order to solve the above-mentioned technical problems, the present invention adopts the following technical solutions:

Design a device for protecting the rotor of an aircraft, the number of the rotor of the aircraft is N, N≥2, including: a lower cover with a motor mounting position installed with a side support plate, an upper cover installed above the side support plate, and a rectifier fixed in the enclosed area of the lower cover, the upper cover and the side support plate; the side support plate is provided with a first air flow hole; the upper cover is provided with a second air flow hole; There are no airflow holes on the sides to distinguish the airflow areas of the N rotors from each other. In this technical solution, the upper cover is used to form the device as a whole, and its structural strength is higher, and the air flow area of the aircraft rotor is isolated from each other by the use of fairings, so as to avoid the turbulent flow in the device caused by mutual disturbance when the aircraft rotor rotates, which can reduce the factors affecting the vibration of the aircraft. The efficiency is high since the mutual influence of the aircraft is avoided.

Preferably, the bottom edge configuration of the fairing includes N arcs of equal length respectively centered on the center of the aircraft rotor, and the radius of the arc is greater than the wing length of the aircraft rotor.

Further, the arc angle of the circular arc is 90°, and the arc sides of the circular arc are connected in sequence.

Further, the side surface of the rectifier is set as an inwardly concave connecting arc surface that smoothly transitions with the bottom edge configuration. Since the flight attitude of the aircraft includes pitching motion and rolling motion, the use of curved surfaces can make the airflow channel of the rotor whose rotational speed decreases during the pitching flight of the aircraft smaller, and the airflow channel of the rotor whose rotational speed increases, which has a smoothing effect.

Preferably, the rectifier is a casing. The housing saves space and minimizes the impact of its weight.

Preferably, the rectifier is fixedly connected to the lower cover and the upper cover at the same time. The rectifier is fixedly connected with the lower cover and the upper cover, so that the rectifier has the function of supporting and connecting, and the weight of the device can be optimized and reduced without reducing the strength of the device.

Preferably, there are N side support plates, which are arc-shaped, and the curvature of the side support plates satisfies: the circumferences formed when any two adjacent aircraft rotors rotate have a common tangent, and the side support plates It is arranged in the area on the rotor side of the two adjacent aircraft with the tangent line as the dividing line.

Preferably, a top column is further provided between the lower cover and the upper cover, and both ends of the top column are respectively fixedly connected to the upper cover and the lower cover. The top post is used to increase the strength of the unit.

Further, the top column is an aluminum column with a height of 55 mm and an outer diameter of 5 mm, and the number of the aluminum columns is 16, which are installed on the lower cover in a symmetrical distribution.

Preferably, the first airflow holes are evenly distributed on the plate surface of the side support plate, and the second airflow holes are evenly distributed on the upper cover plate, and correspond to the lower aircraft rotors respectively.

Preferably, the lower cover is a carbon fiber board with a thickness of 2 mm; the upper cover is a glass fiber board with a thickness of 1.5 mm; The arc radius of the plate minus the radius of the propeller is ≥24mm.

The present invention also provides an aircraft, the aircraft has at least two rotors arranged symmetrically in the center, and the aforementioned device is installed on the rotors.

Compared with the prior art, the beneficial technical effect of the present invention is that the use of the rectifier has a better dynamic effect on the basis of a more comprehensive protective effect.

Description of drawings

FIG. 1 is a structural diagram of a lower cover of a device for protecting a rotor of an aircraft.

FIG. 2 is a structural diagram of an upper cover of a device for protecting the rotor of an aircraft.

3 is a perspective view of a side support plate of an apparatus for protecting an aircraft rotor.

FIG. 4 is a top view of FIG. 3 .

FIG. 5 is a top view of a device for protecting the rotor of an aircraft with the upper cover removed, wherein the holes of the lower cover are not drawn to make the structure clear.

FIG. 6 is an EE sectional view of FIG. 5 .

Figure 7 is another configuration of a fairing of a device for protecting the rotor of an aircraft.

In the figure, 1 is the lower cover, 11 is the motor installation position, 14 is the perforation, 15 is the weight reduction hole, 2 is the upper cover, 21 is the second airflow hole, 22 is the weight reduction hole, 24 is the perforation, and 3 is the side support Plate, 31 is the first airflow hole, 32 is the side support plate mounting hole, 4 is the rectifier, 41 is the bottom edge of the rectifier, 42 is the side of the rectifier, and 43 is the top surface of the rectifier.

Detailed ways

The specific embodiments of the present invention will be described below with reference to the accompanying drawings and examples, but the following examples are only used to describe the present invention in detail, and do not limit the scope of the present invention in any way.

Embodiment 1: A device for protecting the rotor of an aircraft, see Figures 1-7, the number of rotors of the aircraft is N=4, including: a lower cover 1 with a motor mounting position 11 installed with a side support plate 3, installed in the The upper cover 2 above the side support plate 3, and the rectifier 4 fixed in the enclosed area of the lower cover 1, the upper cover 2 and the side support plate 3; the side support plate 3 is provided with a first air flow hole 31; the upper cover 2 is provided with For the second airflow hole 21, the side surface of the fairing element 4 is not provided with an airflow hole so that the airflow areas of the four rotors can be distinguished from each other. The airflow area used to separate the aircraft rotors. In this embodiment, the lower cover 1 is provided with four motor mounting positions 11 , that is, it is applied to a four-wing aircraft. The motor mounting positions 11 can be set to match the number and position of the rotors of the aircraft to meet the needs of the aircraft.

FIG. 1 is roughly the same as FIG. 3 disclosed in CN204846369U, the difference is that in FIG. 1 , the lower cover is provided with through holes 14 , which facilitate the use of screws to fix the lower cover 1 and the side support plate 3 together. The weight-reducing hole 15 is a waist-shaped hole in the bar-shaped hole. The first function is to reduce the weight without affecting the strength of the lower cover, and the second function is to form a fixed position, which is convenient for tying other equipment.

In FIG. 2 , the difference between the upper cover 2 and the lower cover 1 is that the motor installation position 11 of the lower cover 1 is formed by three keels at 120° to each other. In the upper cover 2 , the keels of the lower cover 1 are designed as: above The motor installation position 11 directly under the cover 2 is provided with a plurality of radial ribs and circumferential ribs at the center of the circle, and the apertures between the radial ribs and the circumferential ribs are the second airflow holes 21 .

In Figure 3-4, the side support plates 3 are four 200° arc plates. During installation, the side support plates 3 are installed at the four corners of the lower cover 1 . In this embodiment, the side support plate 3 can be fixedly connected to the lower cover 1 and the upper cover 2 by means of screws. In other embodiments, the support plate 3 can also be welded and fixed to the lower cover 1 and the upper cover 2 respectively. The side support plate 3 can also be designed as a member formed vertically upward along the edge of the lower cover 1, so that its integrity is better, but the manufacturing and maintenance costs are slightly higher.

In FIG. 5 , the configuration of the bottom edge 41 of the fairing 4 includes an arc of equal length with the center of the aircraft rotor as the arc center, and the radius of the arc is greater than the wing length of the aircraft rotor. The fairing 4 needs to be fixed in the device to prevent it from moving. In FIG. 6 , the side surface 42 of the rectifier 4 is an inwardly concave arc surface. In other embodiments, the side surface of the rectifier 4 may also be a vertical surface.

In FIG. 7 , the connection between the two sides of the rectifier is arc-shaped, and the area marked 44 is the airflow turbulence area. It can be seen that the solution of the rectifier is not optimal.

The following focuses on the working principle of the lower rectifier:

In Figure 5, the rotors A, B, C, and D of the quadcopter are the dashed-dotted lines on the inner ring, and the driven airflow is the dashed-dotted lines on the outer ring, and the rotation directions are shown in the figure. When the fairing 4 is set, the airflow disturbed by the four rotors does not affect each other. If the fairing 4 is removed, the airflows of the rotor A and the rotor D collide with each other at the fairing 4, and the airflows of the rotor B and the rotor C conflict with each other at the fairing 4, and the airflow conflict will produce vibration. As shown in the figure, using the side support plate 3 shown in FIG. 3 , the air flow is unobstructed in the front when it exits along the tangential direction. In FIG. 5 , the side edge of the side support plate 3 is at the tangent to the radius of the rotor along the line connecting the centers of the rotors A and D, and other places are similar.

It should be understood that the technical solution is not limited to a quadcopter aircraft, and its principle can be extended to a multi-wing aircraft that can maintain balance, that is, N≥2.

Embodiment 2: As an improvement to Embodiment 1, a device for protecting the rotor of an aircraft, see Figures 1-7, the bottom edge 41 of the fairing 4 has N configurations (in this embodiment, N=4) The arcs of equal length respectively take the center of the aircraft rotor as the arc center, and the radius of the arc is greater than the wing length of the aircraft rotor. The arc angle of the circular arc is 90°, and the arc sides of the circular arc are connected in sequence. The side surface 42 of the fairing element 4 is set as an inwardly concave connecting arc surface with a smooth transition of the bottom edge 41, and the top surface is a reduced bottom edge configuration. Since the flight attitude of the aircraft includes pitching motion and rolling motion, the use of curved surfaces can make the airflow channel of the rotor whose rotational speed decreases during the pitching flight of the aircraft smaller, and the airflow channel of the rotor whose rotational speed increases, which has a smoothing effect.

Referring to FIG. 6 , the rectifier 4 is a casing. Objects can be placed in the housing to save space and minimize the impact of its weight.

The rectifier 4 is fixedly connected to the lower cover 1 and the upper cover 2 respectively. The rectifier 4 is fixedly connected with the lower cover 1 and the upper cover 2, so that the rectifier 4 has the function of supporting and connecting, which can optimize the weight of the device without reducing the strength of the device.

In FIG. 1 , a top column is further provided between the lower cover 1 and the upper cover 2 , and both ends of the top column are fixedly connected to the upper cover 2 and the lower cover 1 respectively. The top post is used to increase the strength of the unit. In conjunction with FIG. 3 , the top post may be provided between the side support plate mounting holes 32 in FIG. 3 .

In FIG. 3 , the first airflow holes 31 are evenly distributed on the surface of the side support plate 3 . In FIG. 2 , the second airflow holes 21 are evenly distributed on the upper cover plate 2 and correspond to the lower aircraft rotors respectively.

In this embodiment, the lower cover 1 is a carbon fiber board with a thickness of 2 mm; the upper cover 2 is a glass fiber board with a thickness of 1.5 mm; The arc radius of 3 minus the radius of the propeller is ≥ 24mm.

In this embodiment, the top column is an aluminum column with a height of 55 mm and an outer diameter of 5 mm. The upper and lower end surfaces of the top column are provided with threaded holes. The number of the aluminum columns is 12, which are symmetrically arranged on the lower cover.

During installation, the side support plate and the lower cover are fixedly connected by the top column and screws; the center line of the rectifier 4 passes through the center of the upper cover and is bonded to the upper cover, and then the upper cover is aligned with the lower cover, and the center line passes through the upper cover. The center of the lower cover is glued on the lower cover, and the upper cover and the side support plate are fixedly connected through the cooperation of screws and top columns.

Embodiment 3: an aircraft, the aircraft has at least two rotors arranged symmetrically in the center, and the device described in Embodiment 1 or 2 is installed on the rotors.

The present invention has been described in detail above in conjunction with the accompanying drawings and the embodiments, but those skilled in the art can understand that, without departing from the purpose of the present invention, each specific parameter in the above-mentioned embodiments can also be changed, Forming a plurality of specific embodiments is the common variation range of the present invention, and will not be described in detail here.

Claims (9)

1. A device for protecting the rotor wings of an aircraft is provided, the number of the rotor wings of the aircraft is N, N is more than or equal to 2, the device comprises a lower cover provided with a motor installation position and provided with a side support plate, and the device is characterized by also comprising an upper cover arranged above the side support plate, and a rectifying piece fixed in the enclosed area of the lower cover, the upper cover and the side support plate; the side supporting plate is provided with a first airflow hole; the upper cover is provided with a second airflow hole; the side surface of the rectifying piece is not provided with airflow holes so as to distinguish airflow areas of the N rotors from each other, the bottom edge of the rectifying piece is configured to comprise N circular arcs with equal length and taking the center of the aircraft rotor as an arc center, and the radius of each circular arc is larger than the wing length of the aircraft rotor.

2. The device of claim 1, wherein the arcs have an arc angle of 90 ° and the arc sides of the arcs meet in sequence.

3. The device of claim 1, wherein the sides of the fairing are configured as an inwardly concave, contoured surface that smoothly transitions with the base configuration.

4. The device of claim 1, wherein the fairing is a housing.

5. The apparatus of claim 1, wherein the fairing is fixedly coupled to both the lower and upper covers.

6. The device of claim 1, wherein a top column is further arranged between the lower cover and the upper cover, and two ends of the top column are respectively fixedly connected with the upper cover and the lower cover.

7. The device of claim 1, wherein the number of the side supporting plates is N, and the side supporting plates are arc-shaped, and the radian of the side supporting plates satisfies: the contour formed when any two adjacent aircraft rotors rotate has a common tangent, and the side support plates are arranged in the area of the sides of the two adjacent aircraft rotors with the tangent as a boundary line.

8. The apparatus of claim 1, wherein the lower cover is a 2mm thick carbon fiber plate; the upper cover is a glass fiber plate with the thickness of 1.5mm, and the second airflow holes are uniformly distributed on the upper cover and respectively correspond to the aircraft rotors below; the side supporting plate is a printing body made of arc 8500 resin material with the thickness of 1.2mm, and the radius of the arc of the side supporting plate minus the radius of the propeller is more than or equal to 24 mm.

9. An aircraft having at least two rotors arranged in central symmetry, characterized in that the rotors are provided with means for protecting the rotors of the aircraft according to any one of claims 1 to 8.

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