CN218858682U

CN218858682U - Aircraft with a flight control device

Info

Publication number: CN218858682U
Application number: CN202221695822.2U
Authority: CN
Inventors: 胡华智
Original assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Current assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Priority date: 2022-06-30
Filing date: 2022-06-30
Publication date: 2023-04-14
Anticipated expiration: 2032-06-30

Abstract

The embodiment of the application discloses aircraft, including the organism with locate two at least duct fans outside the organism, every duct fan is including: the first ducted fan unit comprises a first fan component and a first duct arranged on the periphery of the first fan component; the second duct fan unit comprises one or more second ducts which extend outwards from the first duct along the tangential direction and are communicated with the first duct, and second fan components arranged in each second duct. This application can improve propulsion efficiency greatly, reduce the size, improves the speed governing characteristic, not only can produce the propulsive force, as long as the thrust speed of every duct fan of independent control moreover, just can reach the effect of direct production attitude control power.

Description

Aircraft with a flight control device

Technical Field

The embodiment of the application relates to the field of aircrafts, in particular to an aircraft driven by a duct propeller.

Background

The ducted fan is a propeller which is provided with a duct at the periphery of a fan type propeller to generate propulsive force, and is also called a ducted propeller. Compared with the traditional propeller, the ducted propeller has the advantages of small eddy current loss, compact structure and low noise, and has obvious advantages in the application of small vertical take-off and landing unmanned aerial vehicles.

Ducted fans of the prior art are typically applied to turbine engines, with thrust generated by a central axial drive. The structure has the advantages of large through-flow resistance, high disturbance loss in flow, low propulsion efficiency, large size and low speed regulation characteristic, and can only generate thrust but not directly generate attitude control force.

Disclosure of Invention

The embodiment of the application provides an aircraft, so that the propulsion efficiency of a ducted fan is increased, the size is reduced, and the attitude control force can be directly generated.

The embodiment of the application provides an aircraft, including the organism and locate two at least duct fans outside the organism, every duct fan including:

the first ducted fan unit comprises a first fan component and a first duct arranged on the periphery of the first fan component;

the second duct fan unit comprises one or more second ducts and second fan assemblies, wherein the one or more second ducts extend outwards from the first ducts along the tangential direction and are communicated with the first ducts, and the second fan assemblies are arranged in the second ducts.

In some possible embodiments, the machine body is provided with a power groove having an open end corresponding to the second duct, the second duct is embedded in the power groove, and the second fan assembly is located at the open end of the power groove and is communicated with the interior of the machine body.

In some possible embodiments, the ducted fan is vertically fixed outside the machine body by a horn.

In some possible embodiments, a groove is further provided on the body at a position corresponding to the ducted fan, and the horn is embedded in the groove for fixation.

In some possible embodiments, the spider is of tripod construction, the ducted fan being centrally fixed at a top corner of the tripod, a bottom edge of the tripod being embedded in the groove.

In some possible embodiments, the axial position of the first fan assembly is provided with a fan inner ring;

an inner ring of a machine arm which is in the same circle with the inner ring of the fan is arranged on the inner side of the vertex angle of the tripod;

the fan inner ring and the machine arm inner ring are fixed by being overlapped and sleeved on the outer side of a middle shaft tube, two ends of which are outwards and convexly provided with limiting edges.

In some possible embodiments, the first fan assembly further includes an inner tube sleeved inside the fan inner ring, the bottom bracket tube is sleeved inside the inner tube, and the inner arm ring is axially abutted against the inner tube.

In some possible embodiments, the sum of the length of the inner tube and the length of the inner ring of the horn is equal to the length of the main body of the bottom bracket tube.

In some possible embodiments, the length of the fan inner ring is less than the length of the inner tube.

In some possible embodiments, the number of ducted fans is set to three, four, six, or eight.

In some possible embodiments, the head of the body is a cone structure, the main body is a four-sided column structure, and the number of the ducted fans is four, and the four ducted fans are respectively arranged on each side surface of the four-sided column.

The beneficial effect of this application is:

the embodiment of the application sets up second duct fan unit through setting up first duct fan unit and along this first duct fan unit tangential, it is rotatory to utilize second duct fan unit rotatory to produce the air current and drive first duct fan unit rotatory, the promotion air forms thrust, lift to the aircraft produces, because change coaxial drive into radial drive, thereby the propulsive efficiency has been improved greatly, the size has been reduced, the speed governing characteristic has been improved, not only can produce the propulsive force, and as long as the thrust speed of every duct fan of independent control, just can reach the effect of direct production attitude control power.

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following descriptions are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative efforts.

Fig. 1 is a schematic structural diagram of an aircraft according to an embodiment of the present application.

Fig. 2 is an exploded view of an aircraft according to an embodiment of the present application.

Description of the reference numerals:

1-machine body, 10-power groove, 11-groove;

2-ducted fan, 201-first ducted fan unit, 202-second ducted fan unit, 21-first-fan assembly, 22-first ducted, 23-second fan assembly, 24-second ducted, 210-inner pipe, 211-fan inner ring, 241-second fan, 242-second fan drive motor;

3-arm, 30-bottom edge, 31-arm inner ring;

4-central axle tube, 40-limit edge.

Detailed Description

In order to make the objects, technical solutions and advantages of the present application clearer, the technical solutions of the present application will be described in detail through embodiments with reference to the accompanying drawings in the examples of the present application. Obviously, the embodiments and features of the embodiments in the present application may be combined with each other without conflict.

It should be noted that: in the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout the drawings; in the description of the present application, the terms "central," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like refer to orientations or positional relationships that are based on the orientation or positional relationship shown in the drawings, merely to facilitate the description of the application and to simplify the description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the application; in the description of the present application, "first", "second", and the like are used only for distinguishing one from another, and do not indicate the degree of importance, order, and the like thereof.

In the description of the present application, unless otherwise expressly specified or limited, the terms "mounted," "connected," "communicating," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a movable connection, or a removable connection; can be mechanically or electrically connected; the two elements may be directly connected or indirectly connected through an intermediate medium, or may be communicated internally, spatially, or electrically. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.

Referring to fig. 1 and 2, an aircraft 1 provided in the embodiment of the present application includes an airframe 1 and at least two ducted fans 2 disposed outside the airframe 1, where each ducted fan 2 includes:

a first ducted fan unit 201 including a first fan assembly 21 and a first duct 22 provided at an outer periphery of the first fan assembly 21;

the second ducted fan unit 202 includes one or more second ducts 23 extending tangentially outwardly from the first duct 22 and communicating with the first duct 22, and a second fan assembly 24 disposed within each of the second ducts 23.

In some possible embodiments, the machine body 1 is provided with a power groove 10 having an open end corresponding to the second duct 23, the second duct 23 is embedded in the power groove 10, and the second fan assembly 24 is located at the open end of the power groove and is communicated with the interior of the machine body 1.

In some possible embodiments, an opening adjusting device for adjusting the size of the opening is provided at the opening.

In some possible embodiments, the ducted fan 2 is fixed vertically outside the machine body 1 by means of a horn 3.

In some possible embodiments, a groove 11 is further provided on the body 1 at a position corresponding to the ducted fan 2, and the horn 3 is fixed by being inserted into the groove 11.

In some possible embodiments, the horn 3 is a tripod structure, the ducted fan 2 is centrally fixed at a top corner of the tripod 3, and a bottom edge 30 of the tripod 3 is embedded in the groove 11.

In some possible embodiments, the axial position of the first fan assembly 21 is provided with a fan inner ring 211;

a horn inner ring 31 which is in the same circle with the fan inner ring is arranged on the inner side of the vertex angle of the tripod 3;

the fan inner ring 211 and the horn inner ring 31 are fixed by being stacked and sleeved on the outer side of the central shaft tube 4 with the two ends provided with the limiting edges 40 protruding outwards.

In some possible embodiments, the first fan assembly 21 further includes a tube 210 sleeved inside the fan inner ring 211, the bottom bracket tube 4 is sleeved inside the inner tube 210, and the arm inner ring 31 is axially abutted against the inner tube 210.

In some possible embodiments, the sum of the length of the inner tube 210 and the length of the inner arm ring 31 is equal to the main length of the bottom bracket tube 4, and it is understood that the main length refers to the length of the bottom bracket tube 4 without the limiting rim 40.

In some possible embodiments, the thickness of the fan inner ring 211 is less than the thickness of the inner tube 210 to allow sufficient rotational space for the first fan assembly 22.

In some possible embodiments, the number of ducted fans 2 is provided as three, four, six or eight.

In some possible embodiments, the head part 1 of the body is of a cone structure, the main body part is of a four-sided column structure, and the whole structure is equivalent to that of a missile shell. The number of the ducted fans 2 is four, the four ducted fans are respectively arranged on each side face of the four-face column, and the four ducted fans 2 form a four-axis control system of the aircraft, so that the power drive of the aircraft can be realized, and the accurate attitude control can be realized. It is to be noted that the foregoing is only illustrative of the presently preferred embodiments and application of the principles of the present invention. It will be understood by those skilled in the art that the present application 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 application. Therefore, although the present application has been described in more detail with reference to the above embodiments, the present application is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present application, and the scope of the present application is determined by the scope of the appended claims.

Claims

1. An aircraft, includes organism and locates at least two ducted fans outside the organism, its characterized in that, every ducted fan including:

the first ducted fan unit comprises a first fan assembly and a first duct arranged at the periphery of the first fan assembly;

2. The aircraft of claim 1, wherein:

the machine body is provided with a power groove with an opening at one end corresponding to the second duct, the second duct is embedded into the power groove, and the second fan assembly is positioned at the opening side of the power groove and communicated with the interior of the machine body.

3. The aircraft of claim 1 or 2, wherein: the ducted fan is vertically fixed on the outer side of the machine body through a machine arm.

4. The aircraft of claim 3, wherein: the positions, corresponding to the ducted fans, of the machine body are also provided with grooves, and the machine arms are embedded into the grooves and fixed.

5. The aircraft of claim 4, wherein: the horn is the tripod structure, the ducted fan center is fixed the apex angle position of tripod, the base embedding of tripod is in the recess.

6. The aircraft of claim 5, wherein:

the axial position of the first fan component is provided with a fan inner ring;

the fan inner ring and the machine arm inner ring are fixed by being overlapped and sleeved on the outer side of a middle shaft tube, wherein two ends of the middle shaft tube are provided with limiting edges in an outwards protruding mode.

7. The aircraft of claim 6, wherein: the first fan assembly further comprises an inner tube sleeved on the inner side of the fan inner ring, the middle shaft tube is sleeved on the inner side of the inner tube, and the inner ring of the machine arm is axially abutted to the inner tube.

8. The aircraft of claim 7, wherein: the sum of the length of the inner pipe and the length of the inner ring of the horn is equal to the length of the main body of the central shaft pipe.

9. The aircraft of claim 8, wherein: the length of the fan inner ring is smaller than that of the inner pipe.

10. The aircraft of claim 1 or 2, wherein: the number of the ducted fans is set to three, four, six, or eight.

11. The aircraft of claim 10, wherein: the head of the machine body is of a cone structure, the main body is of a four-sided column structure, and the number of the ducted fans is four and the four ducted fans are respectively arranged on each side face of the four-sided column.