CN110844065A - Unmanned aerial vehicle with strong loading capacity and capable of vertically taking off and landing - Google Patents

Abstract

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.

Description

An unmanned aircraft with strong load capacity and vertical take-off and landing

technical field

The invention relates to the field of general aviation, in particular to an unmanned aircraft with strong load capacity and vertical take-off and landing.

Background technique

With the rapid popularization and wide application of UAVs, people's requirements for the take-off and landing, speed and flight time of UAVs continue to increase, and the vertical take-off and landing fixed-wing UAVs came into being. The advantages of UAVs and rotary-wing UAVs are the advantages of fast speed and long range of fixed-wing UAVs, and the advantages of vertical take-off and landing and hovering in the air. Vertical take-off and landing UAVs mainly include tilt-rotor aircraft, compound UAVs and tail-mounted UAVs. The comparison shows that compound vertical take-off and landing UAVs have the advantages of safety, reliability and low cost, but the current load capacity And the long endurance is weak, and some market applications are limited.

SUMMARY OF THE INVENTION

The technical problem solved by the present invention is to provide an unmanned aircraft with strong load capacity and vertical take-off and landing, which takes into account the advantages of fixed wings and multi-rotors, and has the characteristics of large load, long endurance, and quick disassembly and assembly.

The technical scheme adopted by the present invention to solve its technical problems is:

An unmanned aircraft with strong load-carrying capacity and vertical take-off and landing, comprising a fuselage, a wing arranged in the middle of the fuselage, a tail, a propulsion power device, a rotor power device, and a strut arranged at the tail of the fuselage , landing gear, canards and photoelectric pods; the wings include outer wings, central wings and ailerons, the wings are horizontally symmetrically arranged in the middle section of the fuselage, and the outer wings are divided into left and right outer wings, They are symmetrically arranged on the left and right sides of the central wing respectively, and the left and right outer wings are respectively symmetrically arranged with the ailerons; the left and right ends of the central wing and the left and right outer wings are horizontally symmetrically connected with the braces The rods form left and right struts, and the left and right struts are horizontally symmetrical with respect to the fuselage. the left and right outer wings; the tail includes a flat tail, an elevator, a vertical tail, a rudder and a strut extension, the elevator is symmetrically arranged on the left and right flat tails, the rudder is symmetrically arranged on the left and right vertical tails, and the left and right flat tails are respectively horizontal are arranged on the left and right strut extensions, the left and right vertical tails are respectively vertically arranged on the left and right strut extensions, and the left and right strut extensions are respectively connected to the tail ends of the left and right struts through quick-release parts; the The rotor power devices are symmetrically arranged on the upper surfaces of the front and rear ends of the left and right struts to form a left and right ascending power system, and the center of the left and right ascending power systems is located at the center of gravity of the whole aircraft; The canard is connected to the fuselage and the left and right struts through quick-release parts; the optoelectronic pod is arranged on the lower surface of the front end of the fuselage; the interior of the fuselage integrates a flight control system, Electromechanical systems and avionics systems.

Further, the aileron adopts double ailerons.

Further, landing gears are symmetrically arranged on the lower surfaces of the left and right struts to form left and right landing gears, and the left and right landing gears and the left and right vertical tails together form a four-point landing gear.

Further, there are at least four rotor power devices, which are symmetrically arranged at the front and rear ends of the left and right struts, respectively.

Further, the front end of the fuselage is provided with a pitot tube.

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

Further, the airfoil adopts a large aspect ratio airfoil, and adopts a low-speed high-lift airfoil.

Further, the fuselage adopts a streamlined fuselage.

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

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

The beneficial effects of the present invention are:

1. Based on the composite vertical take-off and landing UAV, it can load large and heavy task loads by comparing various mission load sizes and comprehensively considering the mission space.

2. The overall shape of the aircraft has been comprehensively calculated and optimized. In the process of level flight, the propeller has been feathered, and the battery life has been greatly improved.

Description of drawings

Fig. 1 is the three-dimensional structure diagram of the present invention;

Fig. 2 is the disassembly schematic diagram of Fig. 1;

The figure is marked as:

1. Fuselage, 2. Wing, 3. Tail, 4. Propulsion power unit, 5. Rotor power unit, 6. Strut, 7. Landing gear, 8. Canard, 9. Photoelectric pod, 10. Empty Speed tube, 21, outer wing, 22, center wing, 23, aileron, 31, flat tail, 32, elevator, 33, vertical tail, 34, rudder, 35, strut extension, 1-1, load hatch, 1-2. Battery hatch cover.

Detailed ways

In order to make the above objects, features and advantages of the present invention more clearly understood, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. However, the present invention can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without departing from the connotation of the present invention. Therefore, the present invention is not limited by the specific embodiments disclosed below.

It should be noted that when an element is referred to as being "fixed 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 otherwise defined, 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 terms used herein in the description of the present invention are for the purpose of describing specific embodiments only, and are not intended to limit the present invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

An unmanned aircraft with strong load capacity and vertical take-off and landing, as shown in FIG. 1, includes a fuselage 1, a wing 2 arranged in the middle section of the fuselage 1, a tail 3, and a propulsion arranged at the tail of the fuselage 1. Power unit 4, rotor power unit 5, strut 6, landing gear 7, canard 8 and photoelectric pod 9; wing 2 includes outer wing 21, central wing 22 and aileron 23, and wing 2 is horizontally symmetrically arranged on the aircraft. In the middle section of the body 1, the outer wings 21 are divided into left and right outer wings, which are symmetrically arranged on the left and right sides of the central wing 22, respectively, and the left and right outer wings 21 are respectively symmetrically provided with ailerons 23; There are struts 6 connected horizontally and symmetrically between them to form left and right struts. The left and right struts are horizontally symmetrical with respect to the fuselage 1. Both ends of the central wing 22 are respectively connected to the left and right struts 6 through quick-release parts. The parts are respectively connected to the left and right outer wings 21; the tail 3 includes a flat tail 31, an elevator 32, a vertical tail 33, a rudder 34 and a strut extension 35, the elevator 32 is symmetrically arranged on the left and right flat tails 31, and the rudder 34 is symmetrically arranged on the left and right vertical tails. On the tail 33, the left and right flat tails 31 are respectively arranged horizontally on the left and right strut extensions 35, the left and right vertical tails 33 are respectively vertically arranged on the left and right strut extensions 35, and the left and right strut extensions 35 are respectively connected to the left and right struts 6 through quick-release parts; The power device 5 is symmetrically arranged on the upper surfaces of the front and rear ends of the left and right struts 6 to form a left and right ascending power system, and the center of the left and right ascending power system is located at the center of gravity of the whole machine; The wings 8 are connected to the fuselage 1 and the left and right struts 6 through quick-release parts; the photoelectric pod 9 is arranged on the lower surface of the front end of the fuselage 1; the interior of the fuselage 1 integrates a flight control system, an electromechanical system and an avionics system.

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

Further, landing gears 7 are symmetrically arranged on the lower surfaces of the left and right struts 6 respectively to form a left and right landing gear, and together with the left and right vertical tails 33 form a four-point landing gear.

There are at least four rotor power devices 5, which are symmetrically arranged at the front and rear ends of the left and right struts 6, respectively. As shown in FIG. The front end and the rear end form two sets of power systems on the left and right. It can also be expanded to 8 rotors. Based on the four rotors, each set of rotor power units is expanded into two sets of rotor power units installed up and down. The left and right struts 6 are symmetrically arranged in the front and rear respectively. The center position of the expanded rotor power system It is located at the center of gravity of the whole machine.

Further, a pitot tube 10 is provided at the front end of the fuselage 1 for real-time measurement of the air velocity of the drone.

As shown in Figure 2, the upper surface of the fuselage 1 is provided with a load hatch cover 1-1 and a battery hatch cover 1-2. The load compartment is used for arranging various control systems and mission loads of the aircraft, and the battery compartment is used for arranging aircraft batteries. Or the fuel tank.

Preferably, the fuselage 1 adopts a streamlined fuselage, the wing 2 adopts a large aspect ratio wing, adopts a low-speed high-lift airfoil, and the aspect ratio is greater than 17. The propulsion power device 4 is preferably driven by a motor, and can also be driven according to specific use requirements. , powered by an oil-powered engine.

Preferably, the height of the drone fuselage 1 is 0.33m, the width is 0.33m, and the length is 1.72m, the length of the pitot tube 10 leaking out of the fuselage is 0.2m, the aspect ratio of the wings 2 is 17.5, and the wingspan is long. 5m. Because the whole machine is in line with quick disassembly and assembly, both ends of the central wing 22 are connected to the left and right struts 6 through quick-release parts, and the left and right struts 6 are connected to the left and right outer wings 21 through quick-release parts. The left and right struts of the tail wing 3 extend 35 through The quick-release parts are respectively connected to the left and right struts 6, and the canard 8 is connected to the front end of the fuselage 1 through the quick-release parts, and is installed in sequence in the order of A-B-C-D-E in Figure 2, so that the whole machine can be quickly installed.

in:

Step A: Install the tail wing 3, and quickly install the support rod extension 35 at the front end of the left and right tail wings 3 and the left and right support rods 6 through quick-release parts;

Step B: install the left and right struts 6, and quickly install the left and right struts 6 and the two ends of the central wing 22 through quick-release parts;

Step C: Install the canard wings 8, and quickly install the canard wings 8 and the struts 6 through quick-release parts;

Step D: install the fuselage 1, and install the fuselage 1 on the central wing 22 and the canard wing 8;

Step E: Install the left and right outer wings 21, and quickly install the left and right outer wings 21 and the left and right struts 6 through quick-release parts.

The specific embodiments described above further describe the purpose, technical solutions and beneficial effects of the present invention in further detail. It should be understood that the above descriptions are only specific embodiments of the present invention, and are not intended to limit the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims (10)

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.

Images