阅读说明：本技术 一种电动飞机的辅助推进方法及电动飞机 (Auxiliary propulsion method of electric airplane and electric airplane ) 是由 崔峥 鲁岱晓 胡赞远 张文升 杨薇 吴宇昂 于 2021-03-10 设计创作，主要内容包括：本发明属于电动航空技术领域,公开一种电动飞机的辅助推进方法及电动飞机,第一推进装置驱动飞机本体飞行,第二推进装置与飞机本体对接,进而第一推进装置和第二推进装置同时驱动飞机本体飞行；所述电动飞机用于执行上述的电动飞机的辅助推进方法,包括飞机本体、第一推进装置和辅助推进装置,第一推进装置安装在飞机本体上,辅助推进装置包括第二推进装置和第三推进装置,第二推进装置和第三推进装置可选择地与飞机本体对接。本发明的电动飞机的辅助推进方法及电动飞机利用辅助推进装置辅助第一推进装置来驱动飞机本体飞行,能够提高飞行航程。(The invention belongs to the technical field of electric aviation, and discloses an auxiliary propulsion method of an electric airplane and the electric airplane.A first propulsion device drives an airplane body to fly, a second propulsion device is butted with the airplane body, and then the first propulsion device and the second propulsion device drive the airplane body to fly simultaneously; the electric airplane is used for executing the auxiliary propelling method of the electric airplane, and comprises an airplane body, a first propelling device and an auxiliary propelling device, wherein the first propelling device is installed on the airplane body, the auxiliary propelling device comprises a second propelling device and a third propelling device, and the second propelling device and the third propelling device can be selectively butted with the airplane body. According to the auxiliary propulsion method of the electric airplane and the electric airplane, the auxiliary propulsion device is used for assisting the first propulsion device to drive the airplane body to fly, so that the flight range can be improved.)

1. A method of auxiliary propulsion of an electric aircraft comprising a first propulsion device (2) and an aircraft body (1), the first propulsion device (2) being mounted on the aircraft body (1), characterized in that it comprises:

the first propelling device (2) drives the airplane body (1) to fly;

the second propulsion device is butted with the airplane body (1);

the first propulsion device (2) and the second propulsion device simultaneously drive the aircraft body (1) to fly.

2. Auxiliary propulsion method for electric aircraft according to claim 1, characterized in that it comprises, after the first propulsion device (2) and the second propulsion device simultaneously drive the aircraft body (1) in flight:

when the energy value of the battery of the second propulsion device is the first energy value, the third propulsion device moves from the relay station to the direction close to the airplane body (1).

3. Auxiliary propulsion method for electric aircraft according to claim 2, characterized in that when the energy value of the battery of the second propulsion device is the second energy value, the second propulsion device is detached from the aircraft body (1), the third propulsion device is docked with the aircraft body (1), and the first propulsion device (2) and the third propulsion device drive the aircraft body (1) to fly simultaneously.

4. Auxiliary propulsion method of an electric aircraft according to claim 3, characterized in that it comprises, after disengagement of the second propulsion device from the aircraft body (1):

the second propulsion device moves to the relay station, which charges the battery of the second propulsion device.

5. Auxiliary propulsion method of an electric aircraft according to claim 1, characterized in that it comprises, after the docking of the second propulsion device with the aircraft body (1):

the battery of the second propulsion device powers the propulsion fan (21) of the first propulsion device (2).

6. An electric aircraft for carrying out the auxiliary propulsion method of an electric aircraft according to any one of claims 1 to 5, characterized by comprising:

an aircraft body (1);

a first propulsion device (2) mounted on the aircraft body (1), the first propulsion device (2) being capable of driving the aircraft body (1) to fly;

-auxiliary propulsion means (3), said auxiliary propulsion means (3) comprising second and third propulsion means, said second and third propulsion means being selectively dockable with said aircraft body (1) and being able to drive said aircraft body (1) in flight.

7. Electric aircraft according to claim 6, characterized in that the second propulsion device and the third propulsion device comprise a battery, the battery of the second propulsion device or of the third propulsion device docked with the aircraft body (1) being electrically connected with the first propulsion device (2).

8. Electric aircraft according to claim 7, characterized in that the first propulsion device (2) comprises a propulsion fan (21), the battery of the second or third propulsion device docked with the aircraft body (1) being electrically connected to the propulsion fan (21).

9. Electric aircraft according to claim 6, characterized in that the second propulsion device or the third propulsion device are symmetrically distributed at the top and at the bottom of the aircraft body (1).

10. Electric aircraft according to claim 6, characterized in that the second propulsion device and the third propulsion device comprise a tail (31), the tail (31) being inclined in the driving direction of the second propulsion device and the third propulsion device, the tail (31) being connectable to the aircraft body (1).

Technical Field

The invention relates to the technical field of electric aviation, in particular to an auxiliary propulsion method of an electric airplane and the electric airplane.

Background

With the development of new energy technologies, more and more countries and enterprises begin to lay out the electric aviation field. Specifically, the biggest technical challenges faced by the development of various electric airplanes are that the key performance indexes of the electric propulsion system are low, the technology is immature, the weight is too large, and the minimum use requirements of the electric airplane can only be met, wherein the electric airplane has insufficient energy density of a battery, and the electric propulsion system has too large weight, which is the biggest problem in the design of the electric airplane, so that the flight range of the electric airplane cannot meet the requirements.

Based on the above current situation, it is urgently needed to design an auxiliary propulsion method for an electric aircraft and an electric aircraft.

Disclosure of Invention

One object of the present invention is: provided is an auxiliary propulsion method for an electric aircraft, which can improve the flight range.

Another object of the invention is: an electric airplane is provided for executing the auxiliary propulsion method of the electric airplane.

In order to achieve the purpose, the invention adopts the following technical scheme:

in one aspect, an auxiliary propulsion method for an electric aircraft is disclosed, the electric aircraft including a first propulsion device and an aircraft body, the first propulsion device being mounted on the aircraft body, the auxiliary propulsion method comprising:

the first propelling device drives the airplane body to fly;

the second propulsion device is butted with the airplane body;

the first propulsion device and the second propulsion device simultaneously drive the aircraft body to fly.

As a preferable scheme, after the first propulsion device and the second propulsion device drive the aircraft body to fly simultaneously, the aircraft comprises the following components:

when the energy value of the battery of the second propulsion device is the first energy value, the third propulsion device moves from the relay station to the direction close to the airplane body.

Preferably, when the energy value of the battery of the second propulsion device is the second energy value, the second propulsion device is separated from the aircraft body, the third propulsion device is in butt joint with the aircraft body, and the first propulsion device and the third propulsion device drive the aircraft body to fly simultaneously.

As a preferred solution, after the second propulsion device is detached from the aircraft body, it comprises:

the second propulsion device moves to the relay station, which charges the battery of the second propulsion device.

As a preferred solution, after the docking of the second propulsion device with the aircraft body, it comprises:

the battery of the second propulsion device powers the propulsion fan of the first propulsion device.

In another aspect, an electric airplane is also disclosed, which is used for executing the auxiliary propulsion method of the electric airplane, and includes:

an aircraft body;

the first propelling device is mounted on the airplane body and can drive the airplane body to fly;

an auxiliary propulsion device including a second propulsion device and a third propulsion device, the second propulsion device and the third propulsion device being selectively dockable with the aircraft body and capable of propelling the aircraft body.

Preferably, the second propulsion device and the third propulsion device comprise batteries, and the batteries of the second propulsion device or the third propulsion device docked with the aircraft body are electrically connected with the first propulsion device.

Preferably, the first propulsion device comprises a propulsion fan, and the battery of the second propulsion device or the third propulsion device docked with the aircraft body is electrically connected with the propulsion fan.

Preferably, the second propulsion device or the third propulsion device is symmetrically distributed on the top and the bottom of the aircraft body.

Preferably, the second propulsion device and the third propulsion device comprise an empennage, the empennage being inclined to the driving direction of the second propulsion device and the third propulsion device, the empennage being connectable to the aircraft body.

The invention has the beneficial effects that: the first propulsion device drives the airplane body to fly, the second propulsion device is in butt joint with the airplane body, and then the first propulsion device and the second propulsion device drive the airplane body to fly simultaneously; the electric airplane is used for executing the auxiliary propulsion method of the electric airplane. The electric airplane utilizes the auxiliary propulsion device to assist the first propulsion device to drive the airplane body to fly, and the flying range is improved.

Drawings

The invention is explained in more detail below with reference to the figures and examples.

FIG. 1 is a flow chart illustrating a method for assisting propulsion of an electric aircraft according to an exemplary embodiment;

FIG. 2 is a schematic structural diagram of an electric aircraft according to an embodiment;

FIG. 3 is a front view of the electric aircraft of FIG. 2;

fig. 4 is a side view of the electric aircraft of fig. 2.

In fig. 1 to 4:

1. an aircraft body;

2. a first propulsion device; 21. a propulsion fan;

3. an auxiliary propulsion device; 31. a tail wing.

Detailed Description

In order to make the technical problems solved, technical solutions adopted and technical effects achieved by the present invention clearer, the technical solutions of the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all 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.

In the description of the present invention, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, removably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings.

The first embodiment is as follows:

as shown in fig. 1 and fig. 2, the embodiment of the invention provides an auxiliary propulsion method of an electric airplane, the electric airplane comprises a first propulsion device 2 and an airplane body 1, the first propulsion device 2 is mounted on the airplane body 1, on one hand, the first propulsion device 2 carried by the electric airplane can drive the airplane body 1 to fly; on the other hand, the second propulsion device docked with the aircraft body 1 is able to assist the first propulsion device 2 in driving the aircraft body 1 in flight. Under the condition that the energy density of a battery is limited, the auxiliary propulsion method of the electric airplane improves the range of the electric airplane.

Specifically, the auxiliary propulsion method of the electric aircraft provided by the embodiment of the invention comprises the following steps:

step S100: the first propulsion device 2 drives the aircraft body 1 to fly.

In the embodiment, the first propulsion device 2 is mounted on the aircraft body 1, the first propulsion device 2 is a device for driving the electric aircraft, the first propulsion device 2 is provided with an electrically driven propulsion fan 21, and the propulsion fan 21 can drive the aircraft body 1 to fly.

Step S201: the second propulsion device is docked with the aircraft body 1.

Second advancing device in this embodiment sets up to electric unmanned aerial vehicle, and electric unmanned aerial vehicle adopts the mode butt joint of air refueling to the aircraft body 1 on, and then electric unmanned aerial vehicle and aircraft body 1 can be seen as a holistic flight equipment.

Step S202: the battery of the second propulsion device powers the propulsion fan 21 of the first propulsion device 2.

Specifically, when the second propulsion device is docked with the aircraft body 1, the battery of the second propulsion device is electrically connected with the propulsion fan 21 of the first propulsion device 2, and it can be understood that the battery of the second propulsion device provides electric energy for the propulsion fan 21 of the first propulsion device 2, so that the load required by the battery of the first propulsion device 2 is reduced, and the load of the aircraft body 1 is further reduced.

Step S301: the first propulsion device 2 and the second propulsion device drive the aircraft body 1 to fly at the same time.

Based on step S201, electric unmanned aerial vehicle and aircraft body 1 can regard as a holistic flight equipment, and electric unmanned aerial vehicle' S propulsion fan 21 also can drive aircraft body 1 flight when driving electric unmanned aerial vehicle flight, and then electric unmanned aerial vehicle and first advancing device 2 drive aircraft body 1 flight simultaneously.

Step S302: when the energy value of the battery of the second propulsion device is the first energy value, the third propulsion device moves from the relay station to the direction close to the aircraft body 1.

Step S303: when the energy value of the battery of the second propulsion device is the second energy value, the second propulsion device is separated from the aircraft body 1, the third propulsion device is in butt joint with the aircraft body 1, and the first propulsion device 2 and the third propulsion device drive the aircraft body 1 to fly simultaneously.

Third advancing device and second advancing device are the same electric unmanned aerial vehicle, and it can be understood that predetermines first energy value and second energy value, and the second energy value is less than first energy value, when the energy value of the battery of second advancing device descends to the second energy value from first energy value, can guarantee that third advancing device flies near aircraft body 1. Specifically, when the energy value of the battery of the second propulsion device is the first energy value, the third propulsion device starts flying toward the aircraft body 1; when the energy value of the battery of the second propulsion device is the second energy value, the third propulsion device replaces the second propulsion device to be in butt joint with the aircraft body 1, the first propulsion device 2 and the third propulsion device drive the aircraft body 1 to fly at the same time, continuous auxiliary driving of the aircraft body 1 is achieved, and the flight range is improved.

Step S304: the second propulsion device moves to the relay station, which charges the battery of the second propulsion device.

It will be appreciated that the battery of the second energy value of the second propulsion device can ensure that the second propulsion device flies to a nearby relay station, and the relay station charges the battery of the second propulsion device in preparation for the next docking with the aircraft body 1, thus achieving the cyclic operation of the second propulsion device.

Example two:

as shown in fig. 2 to 4, an embodiment of the present invention provides an electric aircraft for performing the auxiliary propulsion method of the electric aircraft according to the first embodiment, where the electric aircraft includes an aircraft body 1, a first propulsion device 2, and an auxiliary propulsion device 3, the first propulsion device 2 is mounted on the aircraft body 1, and the first propulsion device 2 is capable of driving the aircraft body 1 to fly; the auxiliary propulsion device 3 comprises a second propulsion device and a third propulsion device, which can be selectively docked with the aircraft body 1 and can drive the aircraft body 1 to fly. The first propelling device 2 is a device which is carried by the aircraft body 1 and is used for driving, and the first propelling device 2 can drive the aircraft body 1 to fly; the second propelling device and the third propelling device are arranged as an electric unmanned aerial vehicle, the second propelling device and the third propelling device can be selectively butted with the aircraft body 1 and can drive the aircraft body 1 to fly, and it can be understood that when the energy value of the second propelling device is sufficient, the second propelling device is butted with the aircraft body 1 to assist the first propelling device 2 to drive the aircraft body 1 to fly; when the energy value of the second propelling device is insufficient, the third propelling device replaces the second propelling device to be in butt joint with the airplane body 1, the third propelling device assists the first propelling device 2 to drive the airplane body 1 to fly, and the second propelling device and the third propelling device can circularly assist the first propelling device 2 to drive the airplane body 1 to fly, so that the flying range is improved.

In this embodiment, the second propulsion device and the third propulsion device comprise batteries, and the batteries of the second propulsion device or the third propulsion device docked with the aircraft body 1 are electrically connected with the first propulsion device 2. Specifically, the first propulsion device 2 includes a propulsion fan 21, and a battery of a second propulsion device or a third propulsion device docked with the aircraft body 1 is electrically connected to the propulsion fan 21. When the second propulsion device is in butt joint with the aircraft body 1, the battery of the second propulsion device supplies power to the propulsion fan 21 of the first propulsion device 2 and drives the propulsion fan 21 of the first propulsion device 2 to move, so that the load required by the power supply of the first propulsion device 2 is reduced, the load of the aircraft body 1 is further reduced, and when the third propulsion device is in butt joint with the aircraft body 1, the same effect can be achieved, and the details are omitted. Of course, in other embodiments of the invention, the battery of the second or third propulsion device docked with the aircraft body 1 may also be electrically connected with other components of the aircraft body 1 or of the first propulsion device 2, in order to supply power to the other components of the aircraft body 1 or of the first propulsion device 2.

In particular, when the second propulsion device is docked with the aircraft body 1, the second propulsion device is symmetrically distributed at the top and bottom of the aircraft body 1. The number of the second propelling devices can be set as required, the number of the second propelling devices in the embodiment is four, two of the four second propelling devices are butted on the top of the aircraft body 1, the other two second propelling devices are butted on the bottom of the aircraft body 1, the second propelling devices on the top of the aircraft body 1 and the second propelling devices on the bottom of the aircraft body 1 are symmetrical, the unfavorable pitching moment of the thrust of the second propelling devices on the aircraft body 1 is avoided, and the trimming resistance of the flight of the aircraft body 1 is reduced. The same effect can be achieved when the third propulsion device is docked with the aircraft body 1, which is not described in detail here.

In this embodiment, the second propulsion device and the third propulsion device comprise a tail 31, the tail 31 being inclined in the driving direction of the second propulsion device and the third propulsion device, the tail 31 being able to be connected to the aircraft body 1. The forward swept type tail wing 31 is mounted on the main bodies of the second propulsion device and the third propulsion device, when the second propulsion device or the third propulsion device is butted with the airplane body 1, the tail wing 31 is connected to the airplane body 1, accidental collision caused by direct contact of the main body of the second propulsion device or the third propulsion device and the airplane body 1 is reduced, and reliability is improved.

In the description herein, it is to be understood that the terms "upper," "lower," "left," "right," and the like are based on the orientation or positional relationship shown in the drawings for convenience in description and simplicity of operation, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the present invention. Furthermore, the terms "first" and "second" are used merely for descriptive purposes and are not intended to have any special meaning.

In the description herein, references to the description of "an embodiment," "an example" or the like are intended to mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example.

In addition, the foregoing is only the preferred embodiment of the present invention and the technical principles applied. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, although the present invention has been described in greater detail by the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present invention, and the scope of the present invention is determined by the scope of the appended claims.