阅读说明：本技术 一种载重能力强且可垂直起降的无人飞机 (Unmanned aerial vehicle with strong loading capacity and capable of vertically taking off and landing ) 是由 刘艳军 罗竑 梁斌 林玉祥 吴海杰 于 2019-12-06 设计创作，主要内容包括：本发明涉及一种通用航空领域,具体涉及一种载重能力强且可垂直起降的无人飞机。包括机身、设置在所述机身中段的机翼、尾翼、设置在所述机身尾部的推进动力装置、旋翼动力装置、撑杆、起落架、鸭翼和光电吊舱；所述机翼包括外翼、中央翼和副翼,所述机翼水平对称设置在所述机身的中段,所述外翼分为左右外翼,分别对称设置在所述中央翼的左右两侧,所述左右外翼分别对称设置有所述副翼。本发明以复合式垂直起降无人机为基础,对比多种任务载荷尺寸,综合考虑任务空间,可装载大而重的任务载荷,全机外形做了全面气动计算及优化,在平飞过程中,对螺旋桨做了顺桨处理,续航时间大大提高。(The invention relates to the field of general aviation, in particular to an unmanned aerial vehicle which is high in loading capacity and can take off and land vertically. The aircraft comprises an aircraft body, wings arranged in the middle section of the aircraft body, an empennage, a propulsion power device arranged at the tail part of the aircraft body, a rotor wing power device, a stay bar, an undercarriage, canard wings and a photoelectric pod; the wing includes outer wing, central authorities 'wing and aileron, the wing horizontal symmetry sets up the middle section of fuselage, outer wing divide into about outer wing, the symmetry sets up respectively the left and right sides of central authorities' wing, outer wing symmetry is provided with respectively about the aileron. The invention is based on the combined type vertical take-off and landing unmanned aerial vehicle, compares various task load sizes, comprehensively considers the task space, can load large and heavy task loads, carries out comprehensive pneumatic calculation and optimization on the appearance of the whole unmanned aerial vehicle, carries out feathering treatment on the propeller in the process of flat flying, and greatly improves the endurance time.)

1. The utility model provides a but unmanned aerial vehicle that load capacity is strong and VTOL which characterized in that: the airplane comprises an airplane body (1), wings (2) arranged in the middle section of the airplane body (1), an empennage (3), a propulsion power device (4) arranged at the tail part of the airplane body (1), a rotor wing power device (5), a stay bar (6), an undercarriage (7), canards (8) and photoelectric gondolas (9); the wing (2) comprises an outer wing (21), a central wing (22) and ailerons (23), the wing (2) is horizontally and symmetrically arranged at the middle section of the fuselage (1), the outer wing (21) is divided into a left outer wing and a right outer wing which are respectively symmetrically arranged at the left side and the right side of the central wing (22), and the ailerons (23) are respectively and symmetrically arranged on the left outer wing and the right outer wing (21); the stay bars (6) are horizontally and symmetrically connected between the left end and the right end of the central wing (22) and the left outer wing and the right outer wing (21) to form left and right stay bars, the left and right stay bars (6) are horizontally and symmetrically arranged relative to the fuselage (1), the two ends of the central wing (22) are respectively connected with the left and right stay bars (6) through quick release parts, and the left and right stay bars (6) are respectively connected with the left and the right outer wings (21) through quick release parts; the empennage (3) comprises horizontal tails (31), elevators (32), vertical tails (33), rudders (34) and strut extensions (35), the elevators (32) are symmetrically arranged on left and right horizontal tails (31), the rudders (34) are symmetrically arranged on the left and right vertical tails (33), the left and right horizontal tails (31) are respectively and horizontally arranged on the left and right strut extensions (35), the left and right vertical tails (33) are respectively and vertically arranged on the left and right strut extensions (35), and the left and right strut extensions (35) are respectively connected with the tail ends of the left and right struts (6) through quick-release pieces; the rotor wing power devices (5) are symmetrically arranged on the upper surfaces of the front end and the rear end of the left stay bar and the right stay bar (6) to form a left-right ascending power system, and the center of the left-right ascending power system is positioned at the center of gravity of the whole aircraft; the duck wings (8) are horizontally and symmetrically arranged at the front end of the machine body (1), and the duck wings (8) are connected with the machine body (1) and the left and right support rods (6) through quick disassembly pieces; the photoelectric pod (9) is arranged on the lower surface of the front end of the fuselage (1); the aircraft body (1) is internally integrated with a flight control system, an electromechanical system and an avionic system.

2. The unmanned aircraft of claim 1, wherein the unmanned aircraft is capable of carrying heavy loads and taking off and landing vertically, and further comprises: the ailerons (23) adopt double ailerons.

3. The unmanned aircraft of claim 2, wherein the unmanned aircraft is capable of carrying heavy loads and taking off and landing vertically, and further comprises: the lower surfaces of the left and right support rods (6) are respectively and symmetrically provided with landing gears (7) to form left and right landing gears, and the left and right landing gears (7) and the left and right vertical tails (33) form four-point landing gears together.

4. The unmanned aircraft of claim 3, wherein the unmanned aircraft is capable of carrying heavy loads and taking off and landing vertically, and further comprises: the number of the rotor wing power devices (5) is at least 4, and the rotor wing power devices are respectively and symmetrically arranged at the front end and the rear end of the left stay bar and the right stay bar (6).

5. An unmanned aircraft capable of carrying heavy loads and taking off and landing vertically as claimed in any one of claims 1 to 4, wherein: the front end of the machine body (1) is provided with an airspeed head (10).

6. The unmanned aerial vehicle capable of vertical takeoff and landing with high load carrying capacity as claimed in claim 5, wherein: the upper surface of the machine body 1 is provided with a load hatch cover (1-1) and a battery hatch cover (1-2).

7. The unmanned aerial vehicle capable of vertical takeoff and landing with high load carrying capacity as claimed in claim 6, wherein: the wing (2) adopts a high aspect ratio wing and adopts a low-speed high-lift wing type.

8. The unmanned aerial vehicle capable of vertical takeoff and landing and carrying loads as claimed in claim 7, wherein: the machine body (1) adopts a streamline machine body.

9. The unmanned aerial vehicle capable of vertical takeoff and landing and carrying loads as claimed in claim 8, wherein: the propulsion power device (4) adopts a propulsion motor or an oil-driven engine.

10. An unmanned aircraft capable of carrying heavy loads and taking off and landing vertically as claimed in any one of claims 6 to 9, wherein: the aspect ratio of the wing (2) is greater than 17.

Technical Field

The invention relates to the field of general aviation, in particular to an unmanned aerial vehicle which is high in loading capacity and can take off and land vertically.

Background

Along with unmanned aerial vehicle's quick popularization and wide application, people constantly improve to the requirement of performance such as unmanned aerial vehicle's take off and land, speed and time of a flight, but fixed wing unmanned aerial vehicle takes place of taking off and land perpendicularly, and it has compromise fixed wing unmanned aerial vehicle and rotor unmanned aerial vehicle's advantage, has the advantage that fixed wing unmanned aerial vehicle speed is long-range promptly, but has the advantage of hovering in the air of taking off and land perpendicularly again. VTOL unmanned aerial vehicle mainly includes tiltrotor, combined type unmanned aerial vehicle and tail sitting posture unmanned aerial vehicle, and the contrast reachs combined type VTOL unmanned aerial vehicle and has safe and reliable, advantage with low costs, but present load-carrying capacity and long endurance are weak partially, and partial market is used and is received the restriction.

Disclosure of Invention

The invention solves the technical problem of providing the unmanned aircraft which has the advantages of both fixed wings and multiple rotors, has the characteristics of large load, long endurance, quick disassembly and assembly and the like, has strong load-carrying capacity and can vertically take off and land.

The technical scheme adopted by the invention for solving the technical problems is as follows:

an unmanned aerial vehicle with strong loading capacity and capable of vertically taking off and landing comprises a body, wings arranged in the middle section of the body, an empennage, a propulsion power device arranged at the tail of the body, a rotor power device, a stay bar, an undercarriage, canard wings and a photoelectric pod; the wings comprise outer wings, a central wing and ailerons, the wings are horizontally and symmetrically arranged at the middle section of the fuselage, the outer wings are divided into a left outer wing and a right outer wing which are respectively and symmetrically arranged at the left side and the right side of the central wing, and the left outer wing and the right outer wing are respectively and symmetrically provided with the ailerons; the left and right ends of the central wing and the left and right outer wings are horizontally and symmetrically connected with the stay bars to form left and right stay bars, the left and right stay bars are horizontally symmetrical relative to the fuselage, the two ends of the central wing are respectively connected with the left and right stay bars through quick release pieces, and the left and right stay bars are respectively connected with the left and right outer wings through quick release pieces; the empennage comprises horizontal tails, elevators, vertical tails, a rudder and strut extensions, wherein the elevators are symmetrically arranged on left and right horizontal tails, the rudders are symmetrically arranged on the left and right vertical tails, the left and right horizontal tails are respectively and horizontally arranged on the left and right strut extensions, the left and right vertical tails are respectively and vertically arranged on the left and right strut extensions, and the left and right strut extensions are respectively connected with the tail ends of the left and right struts through quick-release pieces; the rotor wing power devices are symmetrically arranged on the upper surfaces of the front end and the rear end of the left stay bar and the right stay bar to form a left-right ascending power system, and the center of the left-right ascending power system is positioned at the gravity center of the whole aircraft; the duck wings are horizontally and symmetrically arranged at the front end of the machine body and are connected with the machine body and the left and right support rods through quick release pieces; the photoelectric pod is arranged on the lower surface of the front end of the fuselage; and a flight control system, an electromechanical system and an aeronautical system are integrated in the fuselage.

Further, the ailerons adopt double ailerons.

Furthermore, the lower surfaces of the left and right support rods are respectively and symmetrically provided with landing gears to form left and right landing gears, and the left and right landing gears and the left and right vertical tails form a four-point landing gear together.

Furthermore, the number of the rotor wing power devices is at least 4, and the rotor wing power devices are symmetrically arranged at the front end and the rear end of the left stay bar and the right stay bar respectively.

Further, the front end of the machine body is provided with an airspeed head.

Further, the upper surface of the body is provided with a load hatch and a battery hatch.

Further, the wing adopts high aspect ratio wing, adopts low-speed high lift wing section.

Further, the fuselage adopts the streamlined fuselage.

Further, the propulsion power device adopts a propulsion motor or an oil-driven engine.

Further, the aspect ratio of the wing is greater than 17.

The invention has the beneficial effects that:

1. based on the combined type vertical take-off and landing unmanned aerial vehicle, the sizes of various task loads are compared, the task space is comprehensively considered, and large and heavy task loads can be loaded.

2. The overall pneumatic calculation and optimization are carried out on the appearance of the whole aircraft, feathering is carried out on the propeller in the process of flat flight, and the endurance time is greatly improved.

Drawings

FIG. 1 is a perspective view of the present invention;

FIG. 2 is a schematic view of FIG. 1 in an assembled and disassembled state;

labeled as:

1. fuselage, 2, wing, 3, empennage, 4, propulsion power device, 5, rotor power device, 6, strut, 7, landing gear, 8, canard, 9, photoelectric pod, 10, pitot tube, 21, outer wing, 22, central wing, 23, aileron, 31, horizontal tail, 32, elevator, 33, vertical tail, 34, rudder, 35, strut extension, 1-1, load hatch cover, 1-2, battery hatch cover.

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.

An unmanned aerial vehicle with strong loading capacity and capable of vertically taking off and landing is shown in figure 1 and comprises a body 1, wings 2 arranged at the middle section of the body 1, a tail wing 3, a propulsion power device 4 arranged at the tail part of the body 1, a rotor wing power device 5, a stay bar 6, an undercarriage 7, a canard wing 8 and a photoelectric pod 9; the wings 2 comprise outer wings 21, a central wing 22 and ailerons 23, the wings 2 are horizontally and symmetrically arranged at the middle section of the fuselage 1, the outer wings 21 are divided into left and right outer wings which are respectively and symmetrically arranged at the left and right sides of the central wing 22, and the left and right outer wings 21 are respectively and symmetrically provided with the ailerons 23; the left and right ends of the central wing 22 and the left and right outer wings 21 are horizontally and symmetrically connected with the stay bars 6 to form left and right stay bars which are horizontally symmetrical relative to the fuselage 1, the two ends of the central wing 22 are respectively connected with the left and right stay bars 6 through quick release parts, and the left and right stay bars 6 are respectively connected with the left and right outer wings 21 through quick release parts; the empennage 3 comprises horizontal tails 31, elevators 32, vertical tails 33, rudders 34 and strut extensions 35, wherein the elevators 32 are symmetrically arranged on the left and right horizontal tails 31, the rudders 34 are symmetrically arranged on the left and right vertical tails 33, the left and right horizontal tails 31 are respectively and horizontally arranged on the left and right strut extensions 35, the left and right vertical tails 33 are respectively and vertically arranged on the left and right strut extensions 35, and the left and right strut extensions 35 are respectively connected with the left and right struts 6 through quick release parts; the rotor wing power devices 5 are symmetrically arranged on the upper surfaces of the front end and the rear end of the left stay bar and the right stay bar 6 to form a left-right ascending power system, and the center of the left-right ascending power system is positioned at the gravity center of the whole aircraft; the duck wings 8 are horizontally and symmetrically arranged at the front end of the machine body 1, and the duck wings 8 are connected with the machine body 1 and the left and right support rods 6 through quick release pieces; the photoelectric pod 9 is arranged on the lower surface of the front end of the fuselage 1; the fuselage 1 internally integrates a flight control system, an electromechanical system and an avionics system.

Further, the ailerons 23 employ multiple redundant dual ailerons, which still allow control of the aircraft in the event of a single aileron failure.

Furthermore, the lower surfaces of the left and right stay bars 6 are respectively and symmetrically provided with the landing gears 7 to form a left landing gear and a right landing gear, and the left landing gear and the right landing gear form a four-point landing gear together with the left vertical tail 33.

The number of the rotor wing power devices 5 is at least 4, and the rotor wing power devices are respectively and symmetrically arranged at the front end and the rear end of the left and right support rods 6, as shown in fig. 1, the embodiment adopts 4 rotor wing power devices 5, which are respectively and symmetrically arranged at the front end and the rear end of the left and right support rods 6 to form a left and right two-group power system. The wind power generation system can also be extended to 8 rotors, each set of rotor power device is extended to two sets of rotor power devices which are arranged up and down on the basis of four rotors, the left stay bar 6 and the right stay bar 6 are respectively and symmetrically arranged in front and back, and the center position of the extended rotor power system is positioned at the gravity center position of the whole aircraft.

Further, be provided with airspeed head 10 at fuselage 1 front end for real-time measurement unmanned aerial vehicle's air velocity.

As shown in fig. 2, the upper surface of the fuselage 1 is provided with a load hatch 1-1 and a battery hatch 1-2, the load compartment is used for arranging various control systems, task loads and the like of the aircraft, and the battery compartment is used for arranging batteries or oil tanks of the aircraft.

Preferably, the fuselage 1 is a streamlined fuselage, the wings 2 are high-aspect-ratio wings, low-speed high-lift wing profiles are adopted, the aspect ratio is greater than 17, the propulsion power device 4 is preferentially driven by a motor, and an oil-driven engine can be used for driving according to specific use requirements.

Preferably, the height of the unmanned aerial vehicle fuselage 1 is 0.33m, the width is 0.33m, the length is 1.72m, the length of the airspeed head 10 leaking out of the fuselage is 0.2m, the aspect ratio of the wing 2 is 17.5, and the wing span length is 5 m. Because the whole loader meets the quick dismounting performance, two ends of the central wing 22 are connected with the left and right stay bars 6 through quick-dismounting parts, the left and right stay bars 6 are connected with the left and right outer wings 21 through the quick-dismounting parts, the left and right stay bar extensions 35 of the empennage 3 are respectively connected with the left and right stay bars 6 through the quick-dismounting parts, the canard wing 8 is connected with the front end of the loader body 1 through the quick-dismounting parts, and the installation is sequentially carried out according to the sequence of A-B-C-D-E in the figure 2, thus the whole loader can be.

Wherein:

step A: installing the empennage 3, and quickly installing the stay bar extension 35 at the front ends of the left empennage 3 and the right empennage 6 through quick disassembly parts;

and B, step: installing the left and right stay bars 6, and quickly installing the left and right stay bars 6 and two ends of the central wing 22 through quick disassembly parts;

c, step C: mounting the duck wing 8, and quickly mounting the duck wing 8 and the support rod 6 through quick-release parts;

d, step: installing the fuselage 1, namely installing the fuselage 1 on the central wing 22 and the canard wing 8;

e, step E: and (3) installing the left and right outer wings 21, and quickly installing the left and right outer wings 21 and the left and right stay bars 6 through quick release parts.

The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.