CN211223827U

CN211223827U - Unmanned aerial vehicle capable of taking off and landing vertically

Info

Publication number: CN211223827U
Application number: CN201921807737.9U
Authority: CN
Inventors: 赵超; 杨兆
Original assignee: Xian Flight Automatic Control Research Institute of AVIC
Current assignee: Xian Flight Automatic Control Research Institute of AVIC
Priority date: 2019-10-25
Filing date: 2019-10-25
Publication date: 2020-08-11
Anticipated expiration: 2029-10-25

Abstract

The utility model belongs to aircraft design technique, concretely relates to but VTOL unmanned vehicles. In order to get rid of the constraint of a rotor aircraft mode, the utility model integrates multiple flight characteristics of a rotor and a fixed wing aircraft, the proposed unmanned aircraft capable of taking off and landing vertically comprises an aircraft body, wings, canard wings, a vertical fin, an electric engine and a fuel engine, wherein the aircraft body comprises a left aircraft body and a right aircraft body which are connected at the front end through the canard wings and connected at the rear end through inner side wings, the wings are arranged at the outer end, the fuel engine comprising the rotor is arranged at the rear end part, the vertical fins are arranged at the upper and lower two sides of the rear end, and the electric engine comprising the rotor is arranged at the tip part of the vertical fin; the trailing edge of the wing is provided with a flap and an aileron, and the trailing edge of the vertical tail is provided with a rudder. The cost is greatly reduced, a larger load space is provided, and the task requirement of large-load transportation of the aircraft can be met. The oil consumption is lower, and the wind resistance is effectively improved in the vertical direction.

Description

Unmanned aerial vehicle capable of taking off and landing vertically

Technical Field

The utility model belongs to aircraft design technique, concretely relates to but VTOL unmanned vehicles.

Background

Conventional rotor craft airspeed is low, the journey is short, and the carrying capacity is limited, improves airspeed, increases the flight journey, and increase load transport capacity is a hot field of rotor craft research always. Compared with other rotor crafts, the tailstock type vertical take-off and landing aircraft has the characteristics of symmetrical aerodynamic characteristics, good maneuverability, compact structure, high hovering performance and the like, and is more suitable for occasions with larger take-off and landing site limitation and strong requirements on hovering performance and maneuverability. The application space is large, the application prospect is good, the method can play a remarkable role in various military tasks such as reconnaissance, early warning, attack and unconventional combat conditions, plays an irreplaceable important role in the future military field, is a main participant in future war, and can play a unique role in related important civil fields such as electric power patrol, dam detection, traffic accident investigation and other tasks.

SUMMERY OF THE UTILITY MODEL

The utility model discloses the technical problem that will solve is: the utility model provides a but high-efficient aircraft of tailstock formula VTOL breaks away from the constraint of rotor craft mode, has synthesized the multiple flight characteristic of rotor and fixed wing aircraft, has multiple flight control instruction and multiple key flight task mode, can realize the task of VTOL formula unmanned aerial vehicle completion heavy load.

The technical scheme of the utility model is that: a vertical take-off and landing unmanned aerial vehicle comprises a fuselage, wings, canard wings, vertical tails, an electric engine and a fuel engine, wherein the fuselage comprises a left fuselage and a right fuselage which are connected at the front ends through the canard wings and at the rear ends through inner side wings, the outer ends of the left fuselage and the right fuselage are provided with the wings, the fuel engine comprising the rotors is installed at the rear end part, the vertical tails are arranged at the upper side and the lower side of the rear end, and the tip part of the vertical tail is provided with the electric engine comprising the rotors; the trailing edge of the wing is provided with a flap and an aileron, and the trailing edge of the vertical tail is provided with a rudder.

Furthermore, the fuselage and the wings adopt a wing body fusion design and are symmetrical with a longitudinal symmetry plane of the airplane.

Furthermore, the heads of the left body and the right body are both semi-transparent and are respectively an infrared photoelectric camera cabin and a visible light photoelectric camera cabin.

Further, the wing is a single-trapezoid wing, the wing tip is designed with a wingtip winglet, a supporting rod for assisting vertical lifting is arranged below the wingtip winglet and is in transition with the wing surface in a smooth mode, and the bottom end of the electric engine is provided with the supporting rod for vertical lifting.

Furthermore, the duck wing is a straight wing, the two sides of the duck wing are in smooth transition design with the fuselage, and the rear edge of the duck wing is provided with an elevator.

Further, the vertical tail is swept 40 degrees chord-wise at 1/4.

Further, the inside flight control system, electrical power generating system and emergency recovery device still include of fuselage.

Further, in the vertical take-off and landing stage, the electric engine and the fuel engine provide aircraft lift force, the horizontal attitude is controlled through asymmetric thrust provided by the engine, and the horizontal attitude control of the aircraft is controlled through a rudder and asymmetric thrust at the trailing edge of the vertical tail.

Further, during the transition stage, the attitude of the aircraft is adjusted through the asymmetric thrust provided by the electric motor and the rudders at the trailing edges of the vertical tails, and when the airframe reaches a certain speed to generate effective aerodynamic force, the stability of the system is maintained by combining each control surface and the six rotors.

Further, in the front flying stage, the course is controlled through a rudder, the rolling attitude is controlled through an aileron, the body attitude is adjusted through a self-balancing system, the lifting movement is controlled through an elevator, and the electric engine stops working.

The utility model has the advantages that: the utility model discloses but VTOL's aircraft, its thrust direction is unanimous with organism direction of motion all the time for engine thrust is at the vertical direction at the landing stage of taking off, and engine thrust flies the direction in the front at the stage of cruising, does not have thrust conversion structure, only relies on flight control system to carry out the change of flight gesture, with the mode of cruising that gets into the tie from VTOL mode, and the structure VTOL unmanned aerial vehicle of power that verts relatively is simpler, and the security is higher with the reliability.

The double-fuselage allows the pod shape-preserving outer cover to be designed by adopting two different light-transmitting materials, namely visible light and infrared light, compared with shape-preserving materials used for designing independent pods with the same performance requirement, the cost is greatly reduced, meanwhile, the double-fuselage design provides a larger load-carrying space for the aircraft, and the task requirement of large-load transportation of the aircraft can be realized.

The double-oil-driven engine increases the control allowance of the horizontal direction of the vertical take-off and landing unmanned aerial vehicle during take-off, improves the wind resistance, and has lower oil consumption, smaller engine size and relatively smaller resistance of the design of the machine body compared with a single-engine design which provides the same thrust; the design of duck wing is effective when perpendicular to improve the ability to resist wind.

Drawings

FIG. 1 is a schematic structural diagram of the unmanned aerial vehicle capable of vertical take-off and landing;

FIG. 2 is a schematic diagram of a vertical take-off and landing stage of the unmanned aerial vehicle capable of vertical take-off and landing;

fig. 3 is a schematic plan view of the front flight stage of the vertically take-off and landing unmanned aerial vehicle according to the present invention.

Wherein, 1-fuselage, 2-wing, 3-canard, 4-vertical tail, 5-electric engine and 6-fuel engine

Detailed Description

Referring to fig. 1, the structure of the unmanned aerial vehicle capable of vertical take-off and landing of the present invention includes a body 1, wings 2, canard wings 3, vertical tails 4, an electric engine 5 and a fuel engine 6. The unmanned aerial vehicle capable of vertically taking off and landing adopts a canard layout and a pneumatic layout of a single wing in a double fuselage, and the fuselage and the wings 2 and the fuselage and the canard 3 are designed by adopting wing body fusion.

The airplane body 1 is designed as a double-airplane body and comprises a left airplane body and a right airplane body which are symmetrical about a longitudinal symmetrical plane of the airplane; vertical tails 4 are respectively arranged on the upper side and the lower side of the tail parts of the left fuselage and the right fuselage, and the joint part adopts a wing body fusion design; the two heads of the left machine body and the right machine body are photoelectric camera cabins, adopt semitransparent designs and respectively adopt two different light-transmitting materials of infrared light and visible light for aiming emission or investigation; the tail end portions of the left and right fuselages have fuel engines 6 having rotors; the middle parts of the left fuselage and the right fuselage are used for arranging a battery, an oil tank, a flight control system, a power supply, an electrical system and the like.

The wing 2 is a single-trapezoid wing, a low-speed high-lift wing type Naca Ls-0417mod is used as a wing root, benedek 8405A is used as a wing tip wing type, the installation angle is 3 degrees, the dihedral angle is 0 degree, the torsion angle is 3 degrees, the tip-root ratio is 0.32, and a lifting aileron is arranged at the rear edge; the design support bar at the wing tip is too smooth with the airfoil. A benedek10355B airfoil is adopted between the left fuselage and the right fuselage. The wing part structure is designed by adopting a double-beam type, reinforcing ribs are designed on a wing root and a wing tip, rib plates are uniformly distributed on the rest part, and the skin is made of carbon fiber glass reinforced plastic and is integrally formed.

The canard wing 3 is installed at the middle front end of the left fuselage and the right fuselage, a straight wing, a middle single wing and an installation angle of 2 degrees are adopted, the installation angle is 1 degree, the span length is 850cm, and the rear edge is provided with an elevator.

The vertical tails 4 are symmetrically arranged at the upper side and the lower side of the left machine body and the right machine body, the backward sweep angle of 1/4 strings is 40 degrees, the aspect ratio is 11, and the tip ratio is 0.55; electric motors 5 with rotor wings are arranged at the wing tips of the vertical empennages at the upper side and the lower side; the rear edges of the vertical tail wings at the two sides are provided with rudders.

The electric engine 5 is divided into two parts, wherein the blade inserting disc is wrapped on the upper section of the electric engine in a parabolic shape, and the internal motor is wrapped on the lower section of the electric engine in a parabolic shape to form an electric engine cabin; a support rod is designed at the tail section; four sets of rotors are equidistant about unmanned vehicles center pin, and two liang of symmetry. The optimization scheme is that four groups of rotors are distributed in a square shape.

Table 1 shows the main performance indexes of the vtol unmanned aerial vehicle.

TABLE 1

And (3) a vertical take-off and landing stage: as shown in figure 2, four electric engines 5 and a fuel engine 6 at the tail part of the airplane body provide airplane lifting force, the horizontal attitude is controlled through the asymmetry of engine thrust, and the horizontal attitude control of the airplane is controlled through the asymmetry of rudders at the rear edge of a vertical tail and the power of the airplane bodies at two sides.

A transition stage: the asymmetric thrust provided by the electric engine 5 and the rotation of the vertical tail trailing edge rudder realize the movement in the horizontal and height directions, the posture of the body is stabilized through a self-balancing system, and when the body reaches a certain speed and generates effective aerodynamic force, the body is connected to the rudder, the elevator and the ailerons at the trailing edge of the outer wing, and the body and the four rotors jointly maintain the stability of the system.

A front flying stage: the course is controlled by a rudder, the rolling attitude is controlled by an aileron, the body attitude is regulated by a self-balancing system, and the lifting movement is controlled by an elevator.

Claims

1. The utility model provides a but VTOL unmanned vehicles which characterized in that: the aircraft comprises a fuselage (1), wings (2), canard wings (3), vertical tails (4), an electric engine (5) and a fuel engine (6), wherein the fuselage comprises a left fuselage and a right fuselage which are connected at the front ends through the canard wings (3) and at the rear ends through inner side wings, the wings (2) are arranged at the outer ends, the fuel engine (6) comprising the rotor wings is installed at the rear end part, the vertical tails (4) are arranged at the upper side and the lower side of the rear end, and the electric engine (5) comprising the rotor wings is installed at the tip part of the vertical tails (4); the trailing edge of the wing (2) is provided with a flap and an aileron, and the trailing edge of the vertical tail (4) is provided with a rudder.

2. The VTOL unmanned aerial vehicle of claim 1, wherein: the fuselage (1) and the wings adopt a wing body fusion design and are symmetrical with a longitudinal symmetrical plane of the airplane.

3. The VTOL unmanned aerial vehicle of claim 1, wherein: the head parts of the left machine body and the right machine body are both in a semitransparent design and are respectively an infrared photoelectric camera cabin and a visible light photoelectric camera cabin.

4. The VTOL unmanned aerial vehicle of claim 1, wherein: the wing (2) is a single-trapezoid wing, a wingtip winglet is designed at the wingtip, a supporting rod for assisting vertical take-off and landing is arranged below the wingtip winglet and is in smooth transition with the wing surface, and the supporting rod for vertical take-off and landing is arranged at the bottom end of the electric engine (5).

5. The VTOL unmanned aerial vehicle of claim 1, wherein: the duck wing (3) is a straight wing, the two sides of the duck wing are in smooth transition design with the machine body, and the rear edge of the duck wing is provided with an elevator.

6. The VTOL unmanned aerial vehicle of claim 1, wherein: the vertical tail (4) is swept 40 degrees behind the 1/4 chord line.

7. The VTOL unmanned aerial vehicle of claim 1, wherein: the fuselage (1) is internally provided with a flight control system, a power supply system and an emergency recovery device.

8. The VTOL unmanned aerial vehicle of claim 1, wherein: during the vertical take-off and landing stage, the electric engine (5) and the fuel engine (6) provide aircraft lift force, the horizontal attitude is controlled by asymmetric thrust provided by the engines, and the horizontal attitude control of the aircraft is controlled by a rudder and asymmetric thrust at the trailing edge of the vertical tail.

9. The VTOL unmanned aerial vehicle of claim 1, wherein: during the transition stage, the attitude of the aircraft is adjusted through asymmetric thrust provided by the electric motor (5) and the rudders at the trailing edges of the vertical tails, and when the aircraft body reaches a certain speed to generate effective aerodynamic force, the stability of the system is maintained by combining each control surface and six rotors.

10. The VTOL unmanned aerial vehicle of claim 1, wherein: in the front flying stage, the course is controlled through a rudder, the rolling attitude is controlled through an aileron, the body attitude is adjusted through a self-balancing system, the lifting movement is controlled through an elevator, and the electric engine (5) stops working.