CN113998112A

CN113998112A - flying wing unit

Info

Publication number: CN113998112A
Application number: CN202111397716.6A
Authority: CN
Inventors: 张江涛; 刘颖; 李兴艳; 欧阳娟; 宋雪庆
Original assignee: Hebei Wuke Intelligent Technology Co ltd
Current assignee: Hebei Wuke Intelligent Technology Co ltd
Priority date: 2021-11-23
Filing date: 2021-11-23
Publication date: 2022-02-01

Abstract

The invention provides a flight wing unit which comprises wing skins, a first skin, a second skin and a third skin, wherein the wing skins are enclosed to form a wing, the second skin and the wing skins are integrally formed, and the front end and the rear end of the second skin form butt joint ports respectively; the rear end of the first skin is in butt joint with the butt joint port at the upper front end of the second skin; the front end of the third skin is in butt joint with the butt joint port at the upper rear end of the second skin, and the first skin, the second skin and the third skin are enclosed to form a vertical rod. According to the flight wing unit provided by the invention, the wings and the second skin in the vertical rod are of an integrated structure, and the whole body is formed by assembling a plurality of skins, so that the connection position is simplified, and the integrity is improved; the wing has also been avoided when the installation the stack at the top of pole that hangs down to cause the structure repeated, effectively reduces unmanned aerial vehicle's dead weight, and then reduces the energy consumption when flying, and it is long when improving continuation of the journey.

Description

Flying wing unit

Technical Field

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a flight wing unit.

Background

Unmanned aerial vehicles are unmanned aerial vehicles operated by radio remote control equipment and self-contained program control devices, and have wide application in the fields of surveying and mapping, aerial photography, agriculture, express transportation, disaster relief and the like, and currently, the technology of unmanned aerial vehicles is developing rapidly.

Along with the high-speed development of unmanned aerial vehicle technique and the wide application of unmanned aerial vehicle technique, people are more and more, higher and higher to unmanned aerial vehicle's user demand, and wherein, the most urgent demand that uses unmanned aerial vehicle is high endurance, high continuation of the journey, high strength. Particularly in the field of vertical take-off and landing unmanned aerial vehicles, wings of the existing unmanned aerial vehicle are all arranged at the top of a vertical rod and are connected through threaded connecting pieces, and under the connecting condition, the connecting part can be loosened under the action of air resistance in actual flight, so that the unmanned aerial vehicle is damaged; and the part structure of wing and the coincidence of pole that hangs down has appeared repeatedly, has increased unmanned aerial vehicle's dead weight, has increased the energy consumption, has reduced continuation of the journey.

Disclosure of Invention

The embodiment of the invention provides a flight wing unit, aiming at simplifying a connecting structure between a vertical rod and a wing and improving the overall strength; reduce unmanned aerial vehicle gross weight, reduce the energy consumption, prolong the continuation of the journey.

In order to achieve the purpose, the invention adopts the technical scheme that: there is provided a flying-wing unit comprising

The aircraft wing comprises a wing skin, a first skin, a second skin and a third skin, wherein the wing skin is enclosed to form a wing;

the second skin and the wing skin are integrally formed, and the front end and the rear end of the second skin form butt joint ports respectively;

the rear end of the first skin is butted with the butt joint port at the front end of the second skin;

the front end of the third skin is in butt joint with the butt joint port at the rear end of the second skin, and the first skin, the second skin and the third skin are enclosed to form a vertical rod.

In a possible implementation manner, the top of the first skin or the third skin is provided with a mounting position, and the top surface of the mounting position forms a mounting platform for connecting with other wings.

In a possible implementation, the bottom or top of the droop shaft is provided with a plurality of first droop drivers.

In some embodiments, a tail boom is further disposed at the tail end of the third skin, and the tail boom includes a tail boom skin that is integrally formed with the third skin.

In some embodiments, a second heave drive is provided at the top of the tail boom.

In some embodiments, the first vertical driver is disposed at the bottom of the vertical rod, a fixing housing for fixing the first vertical driver is disposed at the bottom of the vertical rod, and an inner cavity of the fixing housing is tapered with a small top and a large bottom, so as to achieve self-centering of the first vertical driver.

In a possible implementation manner, a first cavity is formed in the vertical rod, a plurality of first support frames are arranged in the first cavity from front to back, and the outer edge of each first support frame abuts against the inner wall of the corresponding first cavity.

In some embodiments, the first support frame is provided with a first via hole, the first cavity is further provided with a first support beam sequentially penetrating through the first via holes, and the head end and the tail end of the first support beam are respectively and fixedly connected to the first support frame.

In a possible implementation manner, a second cavity is formed in the wing, a plurality of second support frames are arranged in the second cavity along a second preset path, the outer edge of each second support frame abuts against the inner wall of the corresponding second cavity, and the second preset path is perpendicular to the up-down direction and the front-back direction.

In some embodiments, a second supporting beam sequentially penetrating through the plurality of second supporting frames is further disposed in the second cavity, and long axes of the second supporting beams are distributed along the second preset path.

In the embodiment of the application, compared with the prior art, the flying wing unit has the advantages that the wings and the second skins in the vertical rods are of an integrated structure, and the skins are assembled to form a whole, so that the number of joints is reduced, the integrity is improved, and the integral strength is enhanced; the top of the wing of having still avoided the wing to fold the dress in the installation and having caused the structure repetition, the second covering in the pole that hangs down in this embodiment and the covering sharing of wing effectively reduce unmanned aerial vehicle's dead weight, and then the energy consumption when reducing the flight, it is long when improving continuation of the journey.

Drawings

Fig. 1 is a first schematic front view (from the top of the fuselage to the bottom) of a flying wing unit according to an embodiment of the present invention;

FIG. 2 is a schematic cross-sectional view taken along line A-A of FIG. 1;

FIG. 3 is an enlarged view of the portion B in FIG. 2;

FIG. 4 is a schematic perspective view of a flying wing unit according to an embodiment of the present invention;

fig. 5 is a schematic front view of a second structural view of a flying wing unit (internal structure of a wing, a first skin, and a second skin) according to an embodiment of the present invention;

fig. 6 is a schematic structural diagram (from the head to the tail of the fuselage) of a first support frame adopted in the embodiment of the invention;

FIG. 7 is a schematic view of a second support frame structure (from a transverse perspective along the fuselage) employed in an embodiment of the present invention;

fig. 8 is a schematic view of a position of a flying wing unit on a fuselage according to an embodiment of the present invention.

Description of reference numerals:

10-an airfoil; 11-wing skin; 13-a second support; 14-a second support beam; 15-a second lightening hole; 16-a second via; 17-a second card position;

20-a vertical pole; 21-a first skin; 22-a second skin; 23-a third skin; 25-a mounting location; 26-a stationary housing; 27-a first support frame; 271-a first via; 28-a first support beam; 29-a first lightening hole;

30-a first droop driver; 31-a motor body; 32-a blade;

40-tail boom;

50-second droop drive.

Detailed Description

In order to make the technical problems, technical solutions and advantageous effects to be solved by the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

In the present application, the term "front" refers to a direction toward the nose, and the term "rear" refers to a direction toward the tail.

Referring to fig. 1 to 8 together, a flying wing unit according to the present invention will now be described. The flight wing unit comprises a wing skin 11, a first skin 21, a second skin 22 and a third skin 23, wherein the wing skin 11 encloses to form a wing 10, the second skin 22 and the wing skin 11 are integrally formed, and the front end and the rear end of the second skin 22 form butt joint ports respectively; the rear end of the first skin 21 is butted with a butt joint port at the front end of the second skin 21; the front end of the third skin 23 is butted with the butt joint port at the rear end of the second skin 22, and the first skin 21, the second skin 22 and the third skin 23 are enclosed to form a vertical rod.

By way of example, the wing skin 11 is formed by two sheets arranged one above the other, and the corresponding second skin 22 is formed by two sheets arranged one above the other. The upper sheet ridge in the wing skin 11 forms the upper first portion in the second skin 22; the lower part of the wing skin 11, which corresponds to the first part of the second skin 22, forms a lower second part of the second skin 22.

The flight wing unit that this embodiment provided corresponds the mounting form and has: the wing skin 11 encloses to form the wing 10, the second skin 22 integrally formed with the wing skin 11 forms one part of the vertical rod, and then the first skin 21 and the third skin 23 are butted on the butting openings at the front end and the rear end of the second skin 22 to complete the assembly. After the assembly is completed, the flying wing unit of the embodiment is mounted to the fuselage for use.

It should be noted that the length of the droop pole 20 needs to be adapted to the distribution of the droop drivers in the drone, and the distribution of the droop drivers needs to satisfy a certain relationship with the center of gravity of the fuselage and the position of the wing 10. Thus, the length of the first skin 21 and the length of the third skin 23 are such as to satisfy the setting of the droop driver, for example:

(1) the length of the first skin 21 is approximately the same as the length of the third skin 23 for one wing;

(2) referring to fig. 4, for both wings, the first skin 21 is shorter in length and the third skin 23 is longer in length.

Compared with the prior art, the flying wing unit has the advantages that the wings 10 and the second skins 22 in the vertical rods 20 are of an integrated structure, and are integrally formed by assembling a plurality of skins, so that the use of threaded connectors is reduced, the joints are simplified, the integrity is improved, and the integral strength is enhanced; the top of the wing 10 overlapped at the vertical rod 20 when being installed is also avoided from causing structural repetition, the second skin 22 in the vertical rod 20 in the embodiment is shared with the skin of the wing 10, the self weight of the unmanned aerial vehicle is effectively reduced, the energy consumption during flight is further reduced, and the duration is prolonged.

In some embodiments, a modification of the first skin 21 or the third skin 23 described above may be employed in the structure shown in fig. 1 to 5. The first skin 21 and the wing skin 11 are integrally formed, and the third skin 23 is detachably connected with the wing skin 11; or the first skin 21 is detachably connected with the wing skin 11, and the third skin 23 is integrally formed with the wing skin 11. When two groups of wings are arranged on the fuselage, namely a front wing and a rear wing, the front wing and the second skin 22 are integrally formed, the rear wing needs to be installed on the third skin 23, the length of the third skin 23 needs to be larger than that of the first skin 21, the first skin 21 is short in length and is integrally formed with the wing skin 11 so as to be convenient to manufacture, and the third skin 23 is detachably connected with the wing skin 11 so as to be convenient to install; the same applies when the rear wing is integrally formed with the second skin 22.

It should be noted that, during the integral molding process, i.e. for example, the wing skin 11 is subjected to stretch molding, a molding corresponding to the first skin 21 is made, so that the wing skin 11 and the first skin 21 are integrally formed after production. The same applies to the case where the third skin 23 is integrally formed with the wing skin 11.

In some embodiments, a modification of the first skin 21 or the third skin 23 described above may be employed in the structure shown in fig. 1 to 5. Referring to fig. 1 to 5, the top of the first skin 21 or the third skin 23 is provided with a mounting location 25, and the top surface of the mounting location 25 is formed with a mounting platform for connecting with other wings 10. When the unmanned aerial vehicle is correspondingly provided with two groups of flight wings, namely a front wing and a rear wing: (1) when the front wing is integrally formed with the second skin 22, the rear wing needs to be mounted on the third skin 23, and the mounting location 25 is provided on the third skin 23. (2) The rear wing is integrally formed with the second skin 22, and the rear wing needs to be mounted on the first skin 21, and the mounting position 25 is disposed on the first skin 21.

Through setting up mounting platform for installation position 25 department forms the mounting plane, and the convenience is steadily placed in front wing or back wing installation, and then guarantees the installation accuracy.

As an alternative to the front and rear wing mounting: the rear wing may be detachably connected to the third skin 23 in an abutting manner.

In some embodiments, a modified embodiment of the flying wing unit described above may be configured as shown in fig. 1-5. Referring to fig. 1 to 5, the bottom or top of the drop rod 20 is provided with a plurality of first drop drivers 30. The first vertical drivers 30 are reasonably arranged, so that the lift force requirement of the unmanned aerial vehicle is met; especially when first pole drive 30 sets up in the pole 20 bottom that hangs down, can dodge wing 10, and then the position of wing 10 need not be considered in the arrangement of first pole drive 30 that hangs down for the installation is compacter, corresponds the whole length that adaptable reduction pole 20 that hangs down, and then reduces unmanned aerial vehicle's gross weight, reduces the flight energy consumption, thereby lengthens the flight time.

In some embodiments, a modified embodiment of the second end portion may be configured as shown in fig. 1-5. Referring to fig. 1 to 5, a tail boom 40 is further disposed at the tail end of the third skin 23, and the tail boom 40 includes a tail boom skin integrally formed with the third skin 23. The conventional tail support 40 is arranged at the tail part of the fuselage, and the tail support 40 is arranged at the tail part of the vertical rod 20, so that the effect of sharing the vertical rod 20 and the tail support 40 is achieved, the transverse control area of the unmanned aerial vehicle is increased, and the stability is improved; and the tail boom skin and the third skin 23 are integrally formed, so that the integrity of the hanging rod 20 and the tail boom 40 is improved, and the structural strength is enhanced.

Specifically, the third skin 23 includes a first sheet body and a second sheet body distributed along a first preset path, the first preset path is perpendicular to the up-down direction and the front-back direction, a third sheet body is integrally formed at the rear end of the first sheet body, a fourth sheet body is integrally formed at the rear end of the second sheet body, and the third sheet body and the fourth sheet body enclose to form the tail brace 40.

The first predetermined path is the transverse direction in the fuselage (the fore-aft direction of the fuselage is the longitudinal direction).

In this embodiment, the term "vertical" does not mean completely vertical, and may be substantially vertical.

During actual assembly, the first sheet body and the second sheet body are assembled, the first sheet body and the second sheet body enclose to form the third skin 23 and the tail support 40, and then the two parts are assembled together. The installation is convenient, the installation process is simplified, the integrality of the vertical rod 20 and the tail support 40 can be ensured, and the structural strength is enhanced.

As an alternative connection of the boom 20 to the tail boom 40: the drop rod 20 and tail boom 40 may be connected in a docking fashion (similar to the docking of a docking port).

In some embodiments, a modified embodiment of the flying wing unit described above may be configured as shown in fig. 1-5. Referring to fig. 1-5, the top of tail boom 40 is provided with a second plumb drive 50. The sum of the number of the first droop drivers 30 and the number of the second droop drivers 50 is mainly to satisfy the lift force required by the drone, too few drones cannot satisfy the lift, and too much causes the cost to increase. Through the evenly distributed of first driver 30 and the second driver 50 of droing down, can satisfy unmanned aerial vehicle's stable rising and falling, optimize the flight effect.

In specific implementation, the first and second plumb

drivers

30, 50 are mounted in two ways: (1) the first drop drive 30 is mounted on top of the drop pole 20 and the second drop drive 50 is mounted on top of the tail boom 40; (2) the first plumb drive 30 is mounted at the bottom of the plumb pole 20 and the second plumb drive 50 is mounted at the top of the tail boom.

Note that, referring to fig. 8, the first vertical drivers 30a, b, c, a ', b ', c '; second droop drivers 50d, d'; wherein the line of a-d 'and the line of d-a' intersect at the first point, the line of b-c 'and the line of c-b' intersect at the second point, the first point and the second point are superposed and are the center of gravity of the fuselage.

In some embodiments, one particular mounting arrangement for the first plumb drive 30 may be as shown in FIG. 3. Referring to fig. 3, the first vertical driver 30 is disposed at the bottom of the vertical rod 20, the bottom of the vertical rod 20 is provided with a fixing housing 26 for fixing the first vertical driver 30, and an inner cavity of the fixing housing 26 is tapered with a small top and a large bottom for realizing self-centering of the first vertical driver 30.

Note that the first vertical drive 30 includes a motor main body 31 and a paddle 32 connected to an output shaft of the motor main body 31. The second plumbing driver 50 is identical in structure to the first plumbing driver 30. Except that the motor body 31 of the second plumbing driver 50 is down and the paddle 32 is up when installed; the first plumb driver 30 is installed with the motor body 31 up and the paddle 32 down.

The motor of the first vertical driver 30 is conical to adapt to the shape of the inner cavity of the fixed housing 26, when in installation, because the first vertical driver 30 is installed at the bottom of the vertical rod 20, the self-centering can not be realized by the self-weight of the first vertical driver, if the inner cavity of the fixed housing 36 is cylindrical, in order to enable the output shaft of the motor main body 31 on the first vertical driver 30 to be in a vertical state, frequent adjustment is needed, and the installation is troublesome; once the first droop driver 30 is tilted after being installed, when the blade 32 is driven to rotate, the rotating plane of the blade 32 is not a horizontal plane, so that the flying attitude of the unmanned aerial vehicle is unstable during takeoff and falling; set up to the toper through the inner chamber with fixed shell 26, and then its inner wall can realize the guide effect to the first driver 30 that hangs down in the installation, conveniently realizes the first automatic centering that hangs down driver 30, just also can guarantee that the first paddle 32 rotor plane that hangs down driver 30 is the horizontal plane, improves the stability of unmanned aerial vehicle flight gesture, prevents to rock and takes place the flight accident.

In some embodiments, a modified embodiment of the above-described tabs 22 may be configured as shown in fig. 2 and 5. Referring to fig. 2 and 5, a first cavity is formed in the vertical rod 20, a plurality of first supporting frames 27 are arranged in the first cavity from front to back, and the outer edges of the first supporting frames 27 abut against the inner wall of the first cavity. Because the structures such as the wing 10, the tail support 40 and the first vertical driver 30 need to be installed on the vertical rod 20, the first support frame 27 is arranged in the vertical rod, the first support frame 27 provides support on the inner wall of the first cavity, the vertical rod 20 is prevented from sinking and the like due to air pressure and the like in a high-altitude environment, the structural strength of the vertical rod is improved, and further, the vertical rod can bear air resistance in high-altitude flight and meet certain load.

Alternative embodiments of the first support frame 27 are: the first support frame 27 is a plate-shaped structure, and a plate surface of the first support frame 27 is perpendicular to the front-back direction (which may also be referred to as a longitudinal direction) of the unmanned aerial vehicle, that is, the plate surface of the first support frame 27 is a cross-sectional shape of the corresponding position of the vertical rod 20.

It should be noted that the droop bar 20 is composed of a first skin 21, a second skin 22 and a third skin 23, each of the first skin 21, the second skin 22 and the third skin 23 is enclosed to form a separate cavity, the separate cavities are combined to form a first cavity, and the first support frame 27 may not be installed under the condition that any one of the first skin 21, the second skin 22 and the third skin 23 has enough strength.

In some embodiments, a modified embodiment of the above-described drop pole 20 may be configured as shown in fig. 2 and 5. Referring to fig. 2 and 5, the first support frame 27 is provided with a first through hole 271, the first support frame 27 is further provided with a first support beam 28 sequentially penetrating through the plurality of first through holes 271, and a head end and a tail end of the first support beam 28 are respectively and fixedly connected to the first support frame 27. The first support beam 28 is installed on the basis of the first support frame 27, and the first support beam 28 can enhance the structural strength thereof in the length direction of the suspension bar 20.

Specifically, the first supporting beam 28 is located at the center position in the first cavity, and the number of the first supporting frames 27 may be two or more. When there are only two first support frames 27, the two first support frames 27 are respectively located at the head end and the tail end of the first support beam 28; when the number of the first support frames 27 is more than two, two of the first support frames 27 are located at the head end and the tail end of the first support beam 28, and the rest of the first support frames 27 are evenly distributed between the two first support frames 27 at the head end and the tail end.

Similarly, in the case where the strength of the drooping pole 20 composed of the first skin 21, the second skin 22, and the third skin 23 is sufficient, the first support beam 28 may not be installed.

In some embodiments, a modified embodiment of the first support frame 27 may be configured as shown in fig. 6. Referring to fig. 6, the first support bracket 27 is provided with a first lightening hole 29. Through setting up first lightening hole 29, when the support pole 20 bulk strength that hangs down, reduce unmanned aerial vehicle's gross weight, and then reduce the energy consumption, extension flight time.

The following two alternatives are exemplified:

(1) the first support frame 27 is separately arranged in the first cavity of the vertical rod 20, because only the strength of the vertical rod 20 cannot be considered, and the total weight of the whole unmanned aerial vehicle also needs to be considered, therefore, a first lightening hole 29 is formed in the first support frame 27, and the first through hole 271 can be used as the first lightening hole 29.

(2) The first support frame 27 and the first support beam 28 are installed together in the first cavity of the vertical rod 20, and since the first through hole 271 of the first support frame 27 penetrates through the first support beam 28, the first lightening hole 29 is located around the first through hole 271, so as to realize lightening.

In some embodiments, a modified embodiment of the wing 10 described above may be configured as shown in FIG. 5. Referring to fig. 5, a second cavity is formed in the wing 10, a plurality of second support frames 13 are arranged in the second cavity along a second preset path, the outer edges of the second support frames 13 abut against the inner wall of the second cavity, and the second preset path is perpendicular to the up-down direction and the front-back direction. The second predetermined path is the above-mentioned lateral path.

The effect of wing 10 mainly is to provide lift, guarantees with tail boom 40 that the aircraft has good stability together, because the inside second cavity that is of wing 10 through setting up second support frame 13, can provide the support in the inside of second cavity, prevents to take place to cave in owing to circumstances such as atmospheric pressure in high altitude environment and leads to unmanned aerial vehicle to fall.

Optionally, the second support frame 13 is a plate-shaped structure, a plate surface of the second support frame 13 is perpendicular to the transverse path, and the plate surface of the second support frame 13 is a cross-sectional shape of the wing 10 at the corresponding position.

Specifically, referring to fig. 5, since the second cavity is communicated with the first cavity, a third cavity is formed at the intersection of the second cavity and the first cavity, and the periphery of the third cavity can be enclosed by two first supporting frames 27 and two second supporting frames 13, so as to ensure the strength of the overlapping part of the wing 10 and the vertical rod 20.

In some embodiments, a modified embodiment of the wing 10 described above may be configured as shown in FIG. 5. Referring to fig. 5, a second supporting beam 14 sequentially passing through the plurality of second supporting frames 13 is further disposed in the second cavity, and long axes of the second supporting beams 14 are distributed along a second predetermined path. The second support frame 13 mainly stabilizes the wing 10 in the longitudinal direction, and the second support beam 14 stabilizes the wing 10 in the transverse direction, thereby improving the structural strength of the wing 10.

Specifically, the second support frame 13 may be provided with a second through hole 16 for the second support beam 14 to pass through, and may also be provided with a second clamping position 17 with an upward opening, so as to be clamped and matched with the second support beam 14.

It should be noted that the wing 10 is formed by enclosing the wing skin 11, and the second support frame 13 and/or the second support beam 14 may not be provided in the case that the strength of the wing skin 11 can meet the requirement.

In the case where the first support beam 28 and the second support beam 14 are installed, the second support beam 14 needs to pass through the first cavity and then pass through the second cavity, and the second support beam 14 needs to have a through hole for passing the first support beam 28 therethrough.

In some embodiments, a modified embodiment of the second support frame 13 may be configured as shown in fig. 7. Referring to fig. 7, the second support frame 13 is provided with a second lightening hole 15. Through setting up second lightening hole 15, when guaranteeing wing 10 bulk strength, reduce unmanned aerial vehicle's gross weight, and then reduce the energy consumption, extension flight time.

The following two alternatives are exemplified:

(1) the second support frame 13 is separately arranged in a second cavity of the wing 10, because only the strength of the wing 10 cannot be considered, and the total weight of the whole unmanned aerial vehicle also needs to be considered, a second lightening hole 15 is formed in the second support frame 13, wherein the second through hole 16 or the second clamping position 17 can be used as the second lightening hole 15.

(2) The second support frame 13 and the second support beam 14 are installed together in a second cavity of the wing 10, and since the second support beam 14 is installed on the second through hole 16 or the second clamping position 17 on the second support frame 13, the first lightening holes 29 are uniformly distributed on the second support frame 13 around the second through hole 16 or the second clamping position 17, so as to realize lightening.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.

Claims

1. A flight wing unit is characterized by comprising a wing skin, a first skin, a second skin and a third skin;

the wing skins are enclosed to form a wing, the second skin and the wing skins are integrally formed, and the front end and the rear end of the second skin form butt joint ports respectively;

2. The flying wing unit of claim 1, wherein the top of the first skin or the third skin is provided with a mounting location, the top surface of the mounting location forming a mounting platform for connection to another wing.

3. The flying-wing unit of claim 1 or 2, wherein the first droop drive is provided at the bottom or top of the droop rod.

4. The flying wing unit of claim 3, wherein the aft end of the third skin is further provided with a tail boom comprising a tail boom skin integrally formed with the third skin.

5. The flying wing unit of claim 4, wherein the top of the tail boom is provided with a second droop drive.

6. The flying wing unit of claim 5, wherein the first droop drive is disposed at a bottom of the droop rod, the bottom of the droop rod is provided with a fixed housing for securing the first droop drive, and an inner cavity of the fixed housing is tapered with a smaller top and a larger bottom for self-centering of the first droop drive.

7. The flying wing unit of claim 1, wherein a first cavity is formed in the droop bar, wherein a plurality of first support brackets are disposed from front to back in the first cavity, and wherein outer edges of the first support brackets abut against inner walls of the first cavity.

8. The flying wing unit of claim 7, wherein the first support frame is provided with a first via hole, the first cavity is further provided with a first support beam sequentially penetrating through the plurality of first via holes, and the head end and the tail end of the first support beam are respectively fixedly connected to the first support frame.

9. A flying wing unit as claimed in claim 1, 7 or 8, wherein a second cavity is formed in the wing, a plurality of second struts are provided in the second cavity along a second predetermined path, the outer edges of the second struts abut against the inner wall of the second cavity, and the second predetermined path is perpendicular to the up-down direction and the front-rear direction.

10. The flying wing unit of claim 9, further comprising a second support beam sequentially passing through a plurality of said second support frames in said second cavity, said second support beam having a long axis along said second predetermined path.