CN211281472U

CN211281472U - Duct tail sitting posture VTOL unmanned aerial vehicle

Info

Publication number: CN211281472U
Application number: CN201922257498.0U
Authority: CN
Inventors: 刘艳军; 罗竑; 梁斌; 吴海杰; 林玉祥
Original assignee: Universal Star Suzhou Co ltd
Current assignee: Universal Star Suzhou Co ltd
Priority date: 2019-12-16
Filing date: 2019-12-16
Publication date: 2020-08-18
Anticipated expiration: 2029-12-16

Abstract

The utility model relates to a general aviation field, concretely relates to duct tail sitting posture VTOL unmanned aerial vehicle. Including fuselage, wing, preceding duct, screw power device, horizontal tail, back duct and undercarriage, wing horizontal symmetrical arrangement installs wing about the fuselage middle part forms, preceding duct is installed through preceding duct installation pivot horizontal symmetry the anterior formation of fuselage is preceding duct about, it can wind to control preceding duct installation pivot is rotatory to control preceding duct, horizontal symmetrical arrangement of horizontal tail is installed horizontal tail about the fuselage afterbody forms, back duct is installed perpendicularly through back duct mounting bracket the fuselage afterbody forms back duct from top to bottom, control the horizontal tail with the equal symmetry of duct is installed from top to bottom the undercarriage. The utility model discloses effectively solved too big, the aerodynamic inefficiency of control plane of screw oar that present tail sitting posture VTOL unmanned aerial vehicle exists, drooped the problem that horizontal flight mode conversion control is complicated.

Description

Duct tail sitting posture VTOL unmanned aerial vehicle

Technical Field

The utility model relates to a general aviation field, concretely relates to duct tail sitting posture VTOL unmanned aerial vehicle.

Background

The VTOL UAV combines the advantages of multi-rotor and fixed-wing aircrafts, can take off and land vertically, hover, and has the advantages of high flying speed and long flying time, thereby occupying an important position in the market. VTOL unmanned aerial vehicle divide into composite wing, tilt rotor aircraft and tail sitting posture unmanned aerial vehicle, and several kinds of type aircraft respectively have the advantage. The tail sitting type unmanned aerial vehicle has the advantages of lowest requirements on the taking-off and landing site, no dead weight and great development potential, but the control difficulty is well known; and if install conventional screw, need supporting great size screw, control plane efficiency is extremely low and inefficacy easily when VTOL simultaneously, and unmanned aerial vehicle is difficult to control.

SUMMERY OF THE UTILITY MODEL

The utility model provides a technical problem provide an efficient and duct tail sitting posture VTOL unmanned aerial vehicle of easy control.

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

the utility model provides a duct tail sitting posture VTOL unmanned aerial vehicle, includes fuselage, wing, preceding duct, screw power device, horizontal tail, back duct and undercarriage, wing horizontal symmetrical arrangement installs the wing about the fuselage middle part forms, preceding duct passes through preceding duct installation pivot horizontal symmetry and installs preceding duct about the fuselage front portion forms, control preceding duct and can wind preceding duct installation pivot is rotatory, horizontal symmetrical arrangement of horizontal tail installs horizontal tail about the fuselage afterbody forms, back duct passes through back duct mounting bracket and installs perpendicularly back duct about the fuselage afterbody forms, control horizontal tail with the equal symmetry of duct is installed from top to bottom the undercarriage controls, control preceding duct with screw power device is all installed to duct from top to bottom.

Furthermore, the left wing and the right wing are symmetrically connected with ailerons through hinges, and the left horizontal tail and the right horizontal tail are symmetrically connected with elevators through hinges.

Furthermore, rudders are symmetrically arranged and installed inside the upper and lower rear ducts.

Furthermore, the left and right front ducts and the upper and lower rear ducts form a cross-shaped four duct.

Further, the left and right front ducts can rotate around the front duct mounting rotating shaft by plus or minus 20 degrees.

Preferably, the wing is a low-speed high-lift wing type.

Further, the wing has an aspect ratio of 14.

Preferably, the fuselage is a streamlined fuselage.

Further, the rotation directions of the propeller power devices in the left and right front ducts are opposite.

Further, the rotating directions of the propeller power devices in the upper and lower rear ducts are opposite.

The utility model has the advantages that:

1. the two ducted fans are symmetrically arranged at the front and the rear, and the efficiency of the propeller is greatly improved due to the characteristic of high efficiency of the ducted fans;

2. the front group of ducts and the rear group of ducts form a cross layout, so that the stability and the safety of vertical take-off and landing are improved;

3. the front duct can rotate around the mounting shaft, so that the maneuverability of pitching and mode conversion is increased, and the mode conversion control logic is simplified;

4. the pneumatic control surface is arranged behind the rear duct, so that the control surface efficiency during yawing is improved;

5. the problem of the propeller oar face that current tail sitting posture VTOL unmanned aerial vehicle exists too big, the pneumatic inefficiency of control plane, hang down to play horizontal flight mode conversion control complicacy is effectively solved.

Drawings

FIG. 1 is a three-dimensional structure of the present invention;

labeled as:

1. fuselage, 2, wing, 3, preceding duct, 4, screw power device, 5, horizontal tail, 6, back duct, 7, rudder, 8, undercarriage, 21, aileron, 31, preceding duct installation pivot, 51, elevator, 61, back duct mounting bracket.

Detailed Description

In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein.

It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present.

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 to which this invention belongs. The terminology used in the description of the invention 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 and all combinations of one or more of the associated listed items.

The utility model provides a duct tail sitting posture VTOL unmanned aerial vehicle, as shown in figure 1, including fuselage 1, wing 2, preceding duct 3, screw power device 4, horizontal tail 5, back duct 6 and undercarriage 8, wing 2 horizontal symmetrical arrangement installs wing about 1 middle part of fuselage forms, preceding duct 3 installs preceding duct about 1 anterior formation of fuselage through preceding duct installation pivot 31 horizontal symmetry, it all can be rotatory around preceding duct installation pivot 31 to control preceding duct, rotation angle is positive and negative 20, horizontal tail 5 horizontal symmetrical arrangement installs horizontal tail about 1 afterbody formation of fuselage, back duct 6 is installed perpendicularly at 1 afterbody formation of fuselage about through back duct mounting bracket 61, horizontal tail 5 and the equal symmetry of upper and lower back duct 6 of controlling install undercarriage 8 formation four-point formula undercarriage. The left front duct 3, the right front duct 3, the upper rear duct 6 and the lower rear duct 6 are both provided with propeller power devices 4.

Furthermore, the left wing 2 and the right wing 2 are symmetrically connected and provided with the ailerons 21 through hinges, the left horizontal tail 5 and the right horizontal tail 5 are symmetrically connected and provided with elevators 51 through hinges, the elevators 51 are used for the lifting control of the unmanned aerial vehicle, the upper duct 6 and the lower duct 6 are symmetrically arranged and provided with the rudders 7, and the rudders 7 are used for yaw control.

When the front end of the fuselage 1 is seen in the forward direction, the left front duct 3, the right front duct 3, the upper rear duct 6 and the lower rear duct 6 form a cross-shaped four duct, and the cross-shaped four duct increases the stability and the safety performance of vertical take-off and landing. The rotating directions of the propeller power devices 4 in the left front duct 3 and the right front duct 3 are opposite, and the rotating directions of the propeller power devices 4 in the upper duct 6 and the lower duct 6 are opposite.

The utility model provides a duct tail sitting posture VTOL unmanned aerial vehicle's VTOL and the control process that flies cruise, unmanned aerial vehicle keeps flat subaerial through controlling horizontal tail 5 and the undercarriage 8 of duct 6 from top to bottom, then the screw power device 4 of duct 3 and duct 6 from top to bottom after starting left and right sides before 3, unmanned aerial vehicle VTOL takes off, after the appointed height, duct 3 and elevator deflection before controlling through controlling 1 front end of unmanned aerial vehicle fuselage, with unmanned aerial vehicle from the VTOL mode transition to the cruise mode that flies, unmanned aerial vehicle begins to fly cruise. When unmanned aerial vehicle fell and retrieves, deflected through controlling right and left front duct 3 and elevator, the mode transition of cruising was the VTOL mode from level flying with unmanned aerial vehicle, then slowly reduced all screw power device 4's speed to retrieve unmanned aerial vehicle fast.

The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.

Claims

1. The utility model provides a duct tail sitting posture VTOL unmanned aerial vehicle which characterized in that: comprises a fuselage (1), wings (2), a front duct (3), a propeller power device (4), a horizontal tail (5), a rear duct (6) and an undercarriage (8), wherein the wings (2) are horizontally symmetrically arranged and installed at the middle part of the fuselage (1) to form left and right wings, the front duct (3) is horizontally symmetrically installed at the front part of the fuselage (1) to form left and right front ducts through a front duct installation rotating shaft (31), the left and right front ducts can rotate around the front duct installation rotating shaft (31), the horizontal tail (5) is horizontally symmetrically arranged and installed at the rear part of the fuselage (1) to form left and right horizontal tails, the rear duct (6) is vertically installed at the rear part of the fuselage (1) to form upper and lower rear ducts through a rear duct installation frame (61), the undercarriage (8) is symmetrically installed at the left and right rear ducts (5) and the upper and lower rear ducts (6), the left and right front ducts (3) and the upper and lower rear ducts (6) are provided with propeller power devices (4), and a flight control system, an electromechanical system and an aeronautical electric system are integrated in the aircraft body (1).

2. The duct tail-sitting type VTOL UAV of claim 1, characterized in that: the left wing and the right wing (2) are symmetrically connected with ailerons (21) through hinges, and the left horizontal tail and the right horizontal tail (5) are symmetrically connected with elevators (51) through hinges.

3. The duct tail-sitting type VTOL UAV of claim 2, characterized in that: rudders (7) are symmetrically arranged and mounted in the upper and lower rear ducts (6).

4. The unmanned helicopter of any of claims 1-3, comprising: the left front duct (3) and the right front duct (3) and the upper and lower rear ducts (6) form a cross-shaped four duct.

5. The duct tail-sitting type VTOL UAV of claim 4, characterized in that: the left and right front ducts (3) can rotate around the front duct mounting rotating shaft (31) by plus or minus 20 degrees.

6. The duct tail-sitting type VTOL UAV of claim 5, characterized in that: the wing (2) is of a low-speed high-lift wing type.

7. The duct tail-sitting type VTOL UAV of claim 6, characterized in that: the wing (2) has an aspect ratio of 14.

8. The unmanned aerial vehicle of any of claims 5-7, wherein: the fuselage (1) is a streamlined fuselage.

9. The duct tail-sitting type VTOL UAV of claim 8, wherein: the rotating directions of the propeller power devices (4) in the left and right front ducts (3) are opposite.

10. The duct tail-sitting type VTOL UAV of claim 8, wherein: the rotating directions of the propeller power devices (4) in the upper and lower rear ducts (6) are opposite.