CN217515370U

CN217515370U - Ducted aircraft

Info

Publication number: CN217515370U
Application number: CN202221421952.7U
Authority: CN
Inventors: 王桦; 华杰
Original assignee: Tianjin Pegasus Robot Technology Co ltd
Current assignee: Tianjin Pegasus Robot Technology Co ltd
Priority date: 2022-06-07
Filing date: 2022-06-07
Publication date: 2022-09-30
Anticipated expiration: 2032-06-07

Abstract

The utility model relates to the technical field of aircrafts, and discloses a ducted aircraft, which comprises a system cabin and a power part, wherein the system cabin and the power part are arranged from top to bottom, the power part comprises a main body and a ducted component, the main body comprises a support piece and a propeller component, the propeller component is fixed on the support piece, and the propeller component at least comprises a first propeller and a second propeller which are arranged at intervals; the duct assembly comprises a duct shell and a connecting piece, the duct shell surrounds the outer side of the main body, one end of the connecting piece is connected with the duct shell, and the other end of the connecting piece is connected with the system cabin. The utility model discloses a duct aircraft compact structure, the size is little, and the manipulation is simple, adopts the structure setting of many rotors, through setting up the duct shell, both can play the guard action, can reduce the noise again and improve holistic pneumatic efficiency.

Description

Ducted aircraft

Technical Field

The utility model relates to an aircraft technical field especially relates to a duct aircraft.

Background

With the development of technology, aircraft are widely used in various fields. Multi-rotor aircraft have the advantage of vertical take-off and landing compared to fixed-wing aircraft, and are therefore widely used. Many rotor crafts realize attitude control through the rotational speed of controlling different screw, and a plurality of screw also need bigger structure size. The propellers of the multiple rotors are exposed, have a high noise ratio and are prone to safety accidents.

Disclosure of Invention

In order to overcome the defects of the prior art, the utility model provides a ducted aircraft to the size of the aircraft of solving many rotor screw structure, the great problem of noise.

The utility model provides a technical scheme that its technical problem adopted is:

the ducted aircraft comprises a system cabin and a power part which are arranged from top to bottom, wherein the power part comprises a main body and a ducted assembly, the main body comprises a support piece and a propeller assembly which is positioned on the support piece, and the propeller assembly at least comprises a first propeller and a second propeller which are arranged at intervals; the duct assembly comprises a duct shell and a connecting piece, the duct shell surrounds the outer side of the main body, one end of the connecting piece is connected with the duct shell, and the other end of the connecting piece is connected with the system cabin.

As a further improvement of the technical scheme, the connecting piece is of a cross-shaped bracket structure.

As a further improvement of the technical scheme, the support piece comprises a first support and a second support which are arranged at intervals along the gravity direction, a first motor is arranged on the first support, a second motor is arranged on the second support, the first propeller is driven by the first motor, and the second propeller is driven by the second motor.

As a further improvement of the above technical solution, the first propeller and the second propeller each include at least three blades.

As a further improvement of the above technical solution, a gap width between a terminal of the first propeller and/or the second propeller and an inner wall of the ducted casing is 1% -4% of its own radius.

As a further improvement of the above technical solution, the first propeller and the second propeller rotate in opposite directions, and/or the pitch of the first propeller is smaller than the pitch of the second propeller.

As a further improvement of the above technical solution, the power unit further includes a control surface control assembly, the control surface control assembly includes at least 3 control surfaces, the control surfaces are located at the bottom of the propeller assembly, and the control surfaces are distributed in central symmetry.

As a further improvement of the above technical solution, the cross section of the connecting piece and/or the control surface is a symmetrical airfoil.

As a further improvement of the above technical solution, the control surface control assembly further includes a rotating shaft, the rotating shaft is driven by a servo motor, and the servo motor is located on the support member.

As a further improvement of the above technical scheme, the power section further comprises an undercarriage fixed at the bottom of the ducted casing, one end of the rotating shaft is connected with the servo motor, and the other end of the rotating shaft is connected with the undercarriage.

The utility model has the advantages that: the utility model provides a compact structure, the size is little, manipulates simple duct aircraft, when adopting the structure setting of many rotors, through setting up the duct shell, both can play the guard action, can reduce the noise again and improve holistic pneumatic efficiency.

Drawings

The invention will be further described with reference to the following figures and examples:

fig. 1 is a schematic perspective view of a ducted aircraft according to an embodiment of the present invention;

figure 2 is a schematic side view of a ducted aircraft in an embodiment of the present invention;

figure 3 is a cross-sectional view of a ducted aircraft in an embodiment of the present invention;

FIG. 4 is a schematic view of a portion of a ducted aircraft according to an embodiment of the present invention;

FIG. 5 is a schematic view of a portion of a control surface control assembly of a ducted aircraft according to an embodiment of the present invention;

figure 6 is a cross-sectional view of a control surface of a ducted aircraft in an embodiment of the present invention;

figure 7 is a schematic structural view of a support member for a ducted aircraft in an embodiment of the present invention.

Detailed Description

The conception, specific structure and technical effects of the present invention will be described clearly and completely with reference to the accompanying drawings and embodiments, so as to fully understand the objects, aspects and effects of the present invention. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.

It should be noted that, unless otherwise specified, when a feature is referred to as being "fixed" or "connected" to another feature, it can be directly fixed or connected to the other feature or indirectly fixed or connected to the other feature. Furthermore, the description of the upper, lower, left, right, front, rear, etc. used in the present invention is only relative to the mutual position relationship of the components of the present invention in the drawings.

Furthermore, unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art. The terminology used in the description herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any combination of one or more of the associated listed items.

As shown in fig. 1-3, fig. 1 is a schematic perspective view of a ducted aircraft according to an embodiment of the present invention, fig. 2 is a schematic side view of the ducted aircraft according to an embodiment of the present invention, and fig. 3 is a cross-sectional view of the ducted aircraft according to an embodiment of the present invention. The ducted aircraft comprises a system cabin 100 and a power part 200, wherein the system cabin 100 is arranged at the top position of the power part 200 along the gravity direction, a battery 110 and an electronic system 120 are integrated in the system cabin, the electronic system 120 comprises a flight control system and a management panel, and in the embodiment, the battery 110 is preferably arranged above the electronic system 120.

With reference to fig. 4-5, fig. 4 is a partial structural schematic diagram of the ducted aircraft according to an embodiment of the present invention, fig. 5 is a partial structural schematic diagram of a control surface control component of the ducted aircraft according to an embodiment of the present invention, fig. 6 is a cross-sectional view of a control surface of the ducted aircraft according to an embodiment of the present invention, and fig. 7 is a structural schematic diagram of a support member of the ducted aircraft according to an embodiment of the present invention. In the present embodiment, the power portion 200 includes a main body 210 and a bypass assembly 220. The main body 210 includes a support 211 and a propeller assembly 230 mounted on the support 211, wherein the propeller assembly 230 includes a first propeller assembly 231 and a second propeller assembly 232.

As for the screw assembly 230, the first screw assembly 231 and the second screw assembly 232 are spaced apart in the gravity direction, the first screw assembly 231 includes a first screw 2311 and a first motor 2312, the second screw assembly 232 includes a second screw 2321 and a second motor 2322, and in particular, in the present embodiment, the first propeller 2311 is mounted on the first motor 2312, and the second propeller 2321 is mounted on the second motor 2322, and therefore, correspondingly, the supporting member 211 includes a first support 2111 and a second support 2112 spaced apart in the gravitational direction, the first motor 2312 is mounted on the first support 2111, the second motor 2322 is mounted on the second support 2112, thereby, the arrangement of the first propeller assembly 231 and the second propeller assembly 232 at a distance in the vertical direction is achieved, and then it is further ensured that the first propeller 2311 and the second propeller 2321 are independent from each other without interference.

In this embodiment, the first propeller 2311 and the second propeller 2321 each include at least two blades.

In another embodiment, the first and

second propellers

2311, 2321 each include three blades, i.e., each is a three-bladed propeller.

In the present embodiment, the first propeller 2311 and the second propeller 2321 preferably rotate in opposite directions, so that the overall aerodynamic efficiency can be improved, and further preferably, the first propeller 2311 and the second propeller 2321 have different pitches, specifically, the pitch of the first propeller 2311 may be smaller than that of the second propeller 2321.

By controlling the respective rotational speed and rotational direction of the first and

second propellers

2311, 2321, simple heading control may be achieved.

In another embodiment, the pitch of the first propeller 2311 is greater than the pitch of the second propeller 2321.

In this embodiment, the first propeller 2311 and the second propeller 2321 are of a coaxial structure, and in order to avoid the first propeller 2311 and the second propeller 2321 from contacting the ducted casing 221 and at the same time ensure that the first propeller 2311 and the second propeller 2321 have the highest operational efficiency, the clearance between the tips of the propellers and the inner wall of the ducted casing 221 is defined to be 1% -4%, preferably 2%, of the radius of the propellers (i.e. the distance from the rotation center of the propellers to the tip of the blades).

In this embodiment, the duct assembly 220 includes a duct housing 221 and a connecting member 222, and the duct housing 221 is a substantially thin-walled cylinder surrounding the outside of the main body 210, which can protect the main body 210 from movement, reduce noise, and improve overall aerodynamic efficiency.

It should be noted that, since the duct assembly 220 cannot interfere with the normal operation of the propeller assembly 230, the duct assembly 220 needs to achieve the connection of the duct housing 221 thereof with the main body 210 through the connection member 222, and the duct housing 221 is prevented from being detached from the main body 210.

Meanwhile, in order to prevent the connecting member 222 from blocking and affecting the air intake (i.e., shielding the air intake) of the propeller assembly 230, the connecting member 222 is disposed above the main body 210, and in this embodiment, the system tank 100 is located at the top of the supporting member 211, i.e., the bottom of the system tank 100 is connected to the top of the supporting member 211, so that the connecting member 222 connects the system tank 100 and the supporting member 211, and thus, the ducted casing 221 and the supporting member 211 (i.e., the main body 210) can be indirectly connected.

In order to keep the ducted casing 221 in a stable state, the connecting member 222 is a cross-shaped bracket, a converging end (top end) of the cross-shaped bracket is fixed outside the system tank 100, and a diverging end (bottom end) of the cross-shaped bracket is respectively connected with the ducted casing along the circumferential direction. And simultaneously, set up connecting piece 222 to the wing section of following self center of symmetry line symmetry to make and to provide certain lift before the aircraft when flying, thereby can reduce the load of screw, improve overall efficiency, particularly, adopt NACA 0018's wing section. Preferably, the maximum thickness of the connecting member 222 is 12% -20%, preferably 18%, of the chord length of a single cruciform baffle cross-section.

Further, the power portion 200 further includes a control surface control assembly 240 including a control surface 241, and the control surface control assembly further controls the operation direction and the movement trend of the aircraft by deflecting the angle of the control surface 241.

In this embodiment, the control surface control assembly 240 includes at least 3 control surfaces 241, and the control surfaces 241 are located at the bottom of the propeller assembly 230, so that the control surfaces 241 are installed on the third support 2113 of the support 211, and a plurality of motor installation surfaces 2114 are reserved on the third support 2113 for matching the control surfaces 241.

In this embodiment, the ducted aircraft includes landing gears 243 corresponding to the number of control surfaces, and the landing gears 243 are mounted at the bottom of the ducted casing 221.

The control surface 241 comprises a rotating shaft 242, and the rotating shaft 242 is located at 24% -38% of the chord length (control surface width) of the control surface 241, that is, the rotating shaft 42 is arranged at a position which is 24% -38% of the control surface width H away from the top of the control surface, and further preferably at a position of 30%, that is, the distance H of the rotating shaft 242 from the top of the control surface 241 is in the range of 0.24-0.38 times of the width H of the control surface 241, and the optimal position is at a position which is 0.3 times of the chord length of the control surface 241, that is, a position which satisfies H ═ 0.3H; one end of the rotating shaft 242 is directly driven by a servo motor installed at a position of the motor installation surface 2114 of the support 211, and the other end is installed on the landing gear 243.

In the present embodiment, the control surface 241 is provided as an airfoil symmetric to the own center line of symmetry, specifically, an NACA0012 airfoil is adopted, and preferably, the maximum thickness of the cross section of the control surface 241 is 10% -20% of the chord length (i.e. the control surface width H) of the control surface 41, and more preferably 12%.

In another embodiment, the control surface control assembly 230 includes at least 4 control surfaces 241.

In this embodiment, the bottom of the main body 200 is provided with a load chamber 300, specifically, the load chamber is provided at the bottom of the support member 210, and the load chamber 300 may be used as a load-bearing part and may be configured with a video recording and real-time transmission device or a camera and other loads.

While the invention has been described with reference to certain preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.

Claims

1. A ducted aircraft is characterized by comprising a system cabin and a power part which are arranged from top to bottom, wherein the power part comprises a main body and a ducted assembly, the main body comprises a support piece and a propeller assembly which is positioned on the support piece, and the propeller assembly at least comprises a first propeller and a second propeller which are arranged at intervals; the duct assembly comprises a duct shell and a connecting piece, the duct shell surrounds the outer side of the main body, one end of the connecting piece is connected with the duct shell, and the other end of the connecting piece is connected with the system cabin.

2. The ducted aircraft according to claim 1, wherein the connection is a cross-strut structure.

3. The ducted aircraft according to claim 1 wherein said support member comprises a first support and a second support spaced apart in the direction of gravity, said first support having a first motor mounted thereon and said second support having a second motor mounted thereon, said first propeller being driven by said first motor and said second propeller being driven by said second motor.

4. The ducted aircraft according to claim 1, wherein the first and second propellers each include at least three blades.

5. The ducted aircraft according to claim 1, wherein the gap width of the tip of the first and/or second propeller from the inner wall of the ducted casing is 1-4% of its own radius.

6. The ducted aircraft according to claim 1 wherein the first and second propellers have opposite directions of rotation and/or the first propeller has a pitch that is less than the pitch of the second propeller.

7. The ducted aircraft according to any one of claims 1 to 6, wherein said power section further comprises a control surface control assembly comprising at least 3 control surfaces, said control surfaces being located at the bottom of said propeller assembly and said control surfaces being centrally symmetrically distributed.

8. The ducted aircraft according to claim 7, characterized in that the cross section of the connection and/or the control surface is of symmetrical airfoil shape.

9. The ducted aircraft according to claim 7 wherein the control surface control assembly further comprises a shaft driven by a servo motor, the servo motor being located on the support.

10. The ducted aircraft according to claim 9, wherein the power section further comprises an undercarriage fixed to the bottom of the ducted casing, the shaft having one end connected to the servo motor and the other end connected to the undercarriage.