Novel structure of large unmanned electric tilting rotorcraft capable of vertically taking off and landing and remotely flying at high speed

Abstract

The invention belongs to the field of unmanned aerial vehicles, and discloses a novel structure of a large unmanned electric tilting rotorcraft capable of vertically taking off and landing and remotely flying at a high speed, which comprises a fuselage, wings, a T-shaped empennage, two support arms in the wings, six tilting rotor units, a battery energy unit and two undercarriages. The unmanned aerial vehicle is mainly characterized in that the design of six tilting rotor wing units is adopted, and when the unmanned aerial vehicle is in a flying state, the six tilting rotor wing units are all in a working state, so that the unmanned aerial vehicle has the advantages that the unmanned aerial vehicle can take off and land vertically and fly forwards at a high speed, no structural'dead weight 'exists, and useless power consumption is avoided; the fuselage of the unmanned aerial vehicle adopts a line-length streamline shape design, so that the air resistance during forward flight is remarkably reduced, and the forward flight power consumption is remarkably reduced; when the unmanned aerial vehicle flies forwards, the wings generate lift force, and the power consumption of the unmanned aerial vehicle for overcoming gravity in the air is greatly reduced. Therefore, the unmanned aerial vehicle is low in power consumption and has the remote flight capability.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicles, and in particular to a new type of large-scale unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight. Background Art

[0002] With the rapid development of drone technology, drones are increasingly used in the industrial field. The application scenarios mainly include agricultural and forestry plant protection, patrol inspection, geographic information and mapping, logistics and freight, etc. Traditional industrial drones mostly adopt the following configurations: 1) helicopter configuration; 2) multi-rotor configuration; 3) fixed-wing configuration; 4) vertical take-off and landing fixed-wing configuration. None of these configurations can simultaneously have the advantages of vertical take-off and landing, high-speed forward flight, long range, and no structural "dead weight". For example, the vertical take-off and landing fixed-wing configuration can take off and land vertically and fly forward at high speed, but because there are two propulsion systems for vertical take-off and landing and forward flight, in the vertical flight or horizontal forward flight state, there is always one propulsion system in an inoperative state. Therefore, this configuration has the defect of structural "dead weight" and generates useless power consumption.

[0003] It can be seen that the above four unmanned machine types each have their own advantages and disadvantages, and cannot simultaneously possess the advantages of vertical take-off and landing, high-speed forward flight, long range, and no structural "dead weight". Summary of the invention

[0004] In view of the shortcomings of the prior art, the present invention provides a new configuration of a large unmanned electric tilt-rotor aircraft that can take off and land vertically and fly over long distances at high speeds. By adopting a support arm design, a tilt-rotor six-rotor, and a long streamlined fuselage design, the UAV can simultaneously have the advantages of vertical take-off and landing, high-speed forward flight, long range, and no structural "dead weight".

[0005] The technical solution of the present invention is: A new configuration of a large unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight, comprising: a fuselage, wings, a T-tail, two arms in the wings, six tilt-rotor units, a battery energy unit, and two landing gears; the wings are symmetrically mounted on the middle section of the fuselage, the T-tail is symmetrically mounted on the tail section of the fuselage, the two landing gears are respectively mounted on the front section and the tail section of the fuselage, and the battery energy unit is mounted in the fuselage; the wing is rectangular in plan view, and ailerons are arranged on the trailing edge of the wing; the T-tail comprises a horizontal stabilizer, a vertical stabilizer, an elevator and a rudder, and the horizontal stabilizer is rectangular in plan view; the characteristics are: The maximum take-off weight of the UAV is between 150 kg and 350 kg; The fuselage has a slender and streamlined shape and is located below the wings and the tail; The two arms in the wing extend from the middle of the wing by at least the length of the rotor radius and are vertically connected to the front and rear beams of the wing; The six tilt-rotor units are divided into three pairs, including a first tilt-rotor unit pair, a second tilt-rotor unit pair, and a third tilt-rotor unit pair; the first tilt-rotor unit pair is respectively mounted on a pair of arms in the wing, the second tilt-rotor unit pair is respectively mounted on both side ends of the wing, and the third tilt-rotor unit pair is respectively mounted on both side ends of the horizontal stabilizer; When the UAV is in flight, all of the six tilt-rotor units are in operation; When the UAV is in a vertical flight state, the pitch motion of the UAV is realized by the pulling force difference generated by the first tilt-rotor unit pair and the third tilt-rotor unit pair respectively using different rotation speeds, the yaw motion of the UAV is realized by the two tilt-rotors in the second tilt-rotor unit pair using the differential tilt angle, and the roll motion is realized by the pulling force difference generated by the two tilt-rotors in the second tilt-rotor unit pair respectively using different rotation speeds; Preferably, the six tilt-rotor units are characterized in that when the UAV is in a tilt transition state between a vertical flight state and a horizontal forward flight state, the six tilt-rotor units tilt synchronously.

[0006] Beneficial effects: 1. The present invention provides a new configuration of a large unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight. When all six tilt-rotor units are in an upward pulling working state, the UAV can take off and land vertically and hover in the air; when all six tilt-rotor units are tilted forward at a small angle, the UAV can fly forward at a low speed; when all six tilt-rotor units are in a forward pulling working state, a large forward pulling force can be generated, and the UAV can fly forward at high speed.

[0007] 2. The present invention provides a new configuration of a large unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-distance high-speed flight. The six tilt-rotor units are all in working state when the UAV is flying, avoiding the defect of "dead weight" of the rotors that are not working in some states and avoiding useless power consumption; the fuselage adopts a slender and streamlined appearance design, which significantly reduces the air resistance during forward flight and significantly reduces the power consumption of forward flight; the wings generate lift when the UAV flies forward, which greatly reduces the power consumption of the UAV to overcome gravity in the air. Therefore, the UAV has very low power consumption and has the ability to fly long distances.

[0008] 3. The present invention provides a new configuration of a large unmanned electric tilt-rotor aircraft that can take off and land vertically and fly at high speed over long distances. When the total weight of the designed unmanned aircraft is 270kg and a battery energy unit with an energy density of 400Wh / kg is used, it is calculated that the speed of the unmanned aircraft can reach 190km / h and the range can reach 460km. The speed and range are much higher than those of other large electric rotor aircraft of the same weight. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 A three-dimensional view of a new configuration of a large unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight in vertical flight Figure 2 A top view of a new type of large unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight in vertical flight Figure 3 A three-dimensional view of a new configuration of a large unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight in a tilt transition state Figure 4 Schematic diagram of the pitch motion control of a new type of large unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight in vertical flight Figure 5 Schematic diagram of the yaw motion control of a new type of large unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight in vertical flight Figure 6 The schematic diagram of the rolling motion control of a new type of large unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-distance high-speed flight in vertical flight DETAILED DESCRIPTION

[0010] The technical solutions in the embodiments of the present invention are described clearly and completely below. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field belong to the protection scope of the present invention.

[0011] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0012] This embodiment is a new configuration of a large unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight, with a maximum take-off weight ranging from 150 kg to 350 kg, preferably, a maximum take-off weight ranging from 200 kg to 300 kg.

[0013] like Figure 1 As shown, the UAV includes: a fuselage 1, wings 2, a T-tail, two arms 4 in the wings, six tilt-rotor units, a battery energy unit, and two landing gears. The wings 2 are symmetrically mounted in the middle section of the fuselage 1, the T-tail is symmetrically mounted in the tail section of the fuselage 1, the two landing gears are respectively mounted in the front section and the tail section of the fuselage 1, and the battery energy unit is mounted in the fuselage. The plane shape of the wing 2 is a rectangle, and the trailing edge is provided with ailerons. The T-tail includes a horizontal stabilizer 31, a vertical stabilizer, an elevator, and a rudder, and the plane shape of the horizontal stabilizer 31 is a rectangle.

[0014] like Figure 2 As shown, two arms 4 in the wing extend from the middle of the wing by at least the length of the rotor radius and are vertically connected to the front and rear beams of the wing.

[0015] The six tilt-rotor units are divided into three pairs, including a first tilt-rotor unit pair 51, a second tilt-rotor unit pair 52, and a third tilt-rotor unit pair 53. The first tilt-rotor unit pair 51 is respectively mounted on two arms 4 in the wing, the second tilt-rotor unit pair 52 is respectively mounted on both side ends of the wing 2, and the third tilt-rotor unit pair 53 is respectively mounted on both side ends of the horizontal stabilizer 31.

[0016] When the UAV is in flight, all six tilt-rotor units are in operation. When the UAV is in the tilt transition state between the vertical flight state and the horizontal forward flight state, such as Figure 3 As shown, the six tilt-rotor units tilt synchronously.

[0017] When the UAV is in a vertical flight state, the pitching motion of the UAV is achieved by the pulling force difference generated by the first tilt-rotor unit pair and the third tilt-rotor unit pair using different rotation speeds, such as Figure 4 As shown in FIG. 1 , when the first tilt-rotor unit pair increases the rotation speed and the third tilt-rotor unit pair decreases the rotation speed, the difference in pulling force generated by them will form a nose-up moment. The yaw motion of the drone is achieved by the two tilt-rotors in the second tilt-rotor unit pair using the differential tilt angle, as shown in FIG. Figure 5 As shown in , when the left tilt rotor tilts forward and the right tilt rotor tilts backward, the force component of the pulling force generated by them parallel to the fuselage will form a yaw moment. The rolling motion is achieved by the difference in pulling force generated by the two tilt rotors of the second tilt rotor unit pair using different rotation speeds, as shown in Figure 6 shown.

Claims

1. A new configuration of a large unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight, comprising: The fuselage, wings, T-tail, two arms in the wing, six tilt-rotor units, battery energy unit, two landing gears; The wings are symmetrically mounted on the middle section of the fuselage, the T-shaped tail is symmetrically mounted on the tail section of the fuselage, the two landing gears are respectively mounted on the front section and the tail section of the fuselage, and the battery energy unit is mounted inside the fuselage; the wing plane shape is rectangular, and the trailing edge of the wing is provided with ailerons; the T-shaped tail includes a horizontal stabilizer, a vertical stabilizer, an elevator and a rudder, and the horizontal stabilizer plane shape is rectangular; the characteristics are: The maximum take-off weight of the UAV is between 150 kg and 350 kg; The fuselage has a slender and streamlined shape and is located below the wings and the tail; The two arms in the wing extend from the middle of the wing by at least the length of the rotor radius and are vertically connected to the front and rear beams of the wing; The six tilt-rotor units are divided into three pairs, including a first tilt-rotor unit pair, a second tilt-rotor unit pair, and a third tilt-rotor unit pair; the first tilt-rotor unit pair are respectively mounted on the arm pair in the wing, the second tilt-rotor unit pair are respectively mounted on the two side ends of the wing, and the third tilt-rotor unit pair are respectively mounted on the two side ends of the horizontal stabilizer; when the UAV is in a flight state, the six tilt-rotor units are all in a working state; when the UAV is in a vertical flight state, the pitch motion of the UAV is realized by the pulling force difference generated by the first tilt-rotor unit pair and the third tilt-rotor unit pair using different rotation speeds, the yaw motion of the UAV is realized by the two tilt-rotors in the second tilt-rotor unit pair using the differential tilt angle, and the roll motion is realized by the two tilt-rotors of the second tilt-rotor unit pair using the pulling force difference generated by the different rotation speeds.

2. The six tilt-rotor units according to claim 1, characterized in that: When the UAV is in the tilt transition state between the vertical flight state and the horizontal forward flight state, the six tilt rotor units tilt synchronously.

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