New structure of medium-sized 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 medium-sized unmanned electric tilt-rotor aircraft capable of vertically taking off and landing and remotely flying at a high speed, which comprises an aircraft body, wings, an inverted T-shaped empennage, six support arms, six tilt-rotor units, a battery energy unit and two undercarriages. The six tilting rotor wing units are symmetrically installed on the wings and the inverted-T-shaped empennage through the six supporting arms. The unmanned aerial vehicle is mainly characterized in that the design of six tilting rotor wing units is adopted, so that the unmanned aerial vehicle has the advantages of vertical take-off and landing, high-speed forward flight, no structural'dead weight 'and useless power consumption avoidance; the design that the support arms extend out of the wings and the empennage to exceed the radius length of the rotors is adopted, and the downward projection of the rotor disc is not overlapped with the wings and the empennage in the vertical flight state of the unmanned aerial vehicle, so that the downward washing flow of the rotors does not generate a downward load on the wings and the empennage, the aerodynamic efficiency of the unmanned aerial vehicle is improved, and the power consumption for overcoming the downward load is avoided; 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 (UAVs), and in particular to a new type of medium-sized 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, no structural "dead weight", and no downward load on the wing caused by the rotor downwash. 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 vertical flight or horizontal forward flight, there is always one propulsion system in an inoperative state, so this configuration has the defect of structural "dead weight". Although traditional tilt-rotor UAVs combine the advantages of helicopter and fixed-wing configurations and can take off and land vertically and fly forward at high speed, their tilt-rotors are set at the ends of the wings. When flying vertically, the rotor projection overlaps with the wing, and the rotor downwash generates a downward load on the wing, reducing the aerodynamic efficiency of the tilt-rotor aircraft. The structural "dead weight" and the downward load on the wing caused by the rotor downwash will both generate power consumption.

[0003] It can be seen that the above five unmanned aircraft 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, no structural "dead weight", and no downward load on the wing caused by the rotor downwash. Summary of the invention

[0004] In view of the shortcomings of the prior art, the present invention provides a new configuration of a medium-sized 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 other methods, the unmanned aerial vehicle can have the advantages of vertical take-off and landing, high-speed forward flight, long range, no structural "dead weight", and the rotor downwash does not generate downward load on the wings.

[0005] The technical solution of the present invention is: A new configuration of a medium-sized unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight, comprising: a fuselage, wings, an inverted T-shaped tail, six arms and 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 inverted T-shaped tail is symmetrically mounted on the tail section of the fuselage, and the two landing gears are respectively mounted on the front section and the tail section of the fuselage; the wing is rectangular in plan shape, the wing structure includes two front and rear tubular beams, and the trailing edge of the wing is provided with ailerons; the inverted T-shaped tail includes a horizontal stabilizer, a vertical stabilizer, an elevator and a rudder, the horizontal stabilizer is rectangular in plan shape, and the horizontal stabilizer structure includes two front and rear tubular beams; the characteristics are: The fuselage is composed of two circular tube beams, and the two circular tube-shaped front and rear beams of the wing and the two circular tube-shaped front and rear beams of the horizontal stabilizer are vertically connected to the two circular tube beams of the fuselage; The drone also includes six arms and six tilt-rotor units, and the six tilt-rotor units are symmetrically mounted on the wings and the inverted T-shaped tail through the six arms; The six arms are divided into three pairs, including an arm pair in the wing, an arm pair at the end of the wing, and an arm pair at the end of the tail. The arm pair in the wing is each composed of a circular tube beam, the length of which is at least the rotor radius, and is vertically connected to the two circular tube-shaped front and rear beams of the wing in the middle of the wing; the arm pair at the end of the wing is formed by the front beam of the circular tube of the wing extending outward from the ends of both sides of the wing to a length equal to the rotor radius; the arm pair at the end of the tail is formed by the front beam of the circular tube of the horizontal stabilizer extending outward from the ends of both sides of the horizontal stabilizer to a length equal to the rotor radius; 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 a pair of arms at the end of the wing, and the third tilt-rotor unit pair is respectively mounted on a pair of arms at the end of the tail; When the UAV is in flight, all six tilt-rotor units are in working order; When the UAV is in a vertical flight state, the projections of the rotor discs of the six tilt-rotor units do not overlap with the wings and the horizontal stabilizer, thereby eliminating the downward loads generated by the rotor slipstream on the wings and the horizontal stabilizer; 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] Preferably, the battery energy unit is characterized in that the installation position of the battery energy unit can be adjusted along the front and rear of the fuselage according to the adjustment requirements of the center of gravity position of the entire aircraft.

[0007] Beneficial effects: 1. The present invention provides a new configuration of a medium-sized 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.

[0008] 2. The present invention provides a new configuration of a medium-sized 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 some inoperative rotors and useless power consumption; due to the design that all six arms extend from the middle of the wing, the end of the wing, and the end of the tail wing by at least more than the length of the rotor radius, in the vertical flight state, the downward projection of the rotor blade disc does not overlap with the wing, and the downwash flow of the rotor will not generate a downward load on the wing, thereby improving the aerodynamic efficiency of the UAV and avoiding power consumption to overcome the downward load; when the UAV flies forward, the wing generates lift, 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.

[0009] 3. The present invention provides a new configuration of a medium-sized unmanned electric tilt-rotor aircraft that can take off and land vertically and fly at high speed over long distances. When the designed total weight of the unmanned aircraft is 45kg 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 170km / h and the range can reach 330km. The speed and range are much higher than other medium-sized electric rotor-type unmanned aircraft of the same weight. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 A three-dimensional view of a new medium-sized 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 medium-sized unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight in vertical flight Figure 3The main beam structure diagram of the new fuselage, wings and tail of a medium-sized unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight. Figure 4 A three-dimensional view of a new medium-sized unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight in a tilt transition state Figure 5 Schematic diagram of the pitch motion control of a new type of medium-sized unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight in vertical flight Figure 6 Schematic diagram of the yaw motion control of a new type of medium-sized unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight in vertical flight Figure 7 The schematic diagram of the rolling motion control of a new medium-sized unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight in vertical flight state DETAILED DESCRIPTION

[0011] 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.

[0012] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0013] This embodiment is a new configuration of a medium-sized 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 25 kg to 150 kg, preferably, a maximum take-off weight ranging from 35 kg to 60 kg. Figure 1 As shown, the UAV includes: a fuselage 1, wings 2, an inverted T-shaped tail 3, six arms, six tilt-rotor units, a battery energy unit 6, and two landing gears 7. The wings 2 are symmetrically mounted on the middle section of the fuselage 1, the inverted T-shaped tail 3 is symmetrically mounted on the tail section of the fuselage 1, and the two landing gears 7 are respectively mounted on the front section and the tail section of the fuselage 1.

[0014] like Figure 2 As shown, the plane shape of the wing 2 is rectangular, the wing structure includes two circular tubular front beams and rear beams, and the trailing edge of the wing is provided with ailerons. The inverted T-shaped tail 3 includes a horizontal stabilizer 31, a vertical stabilizer, an elevator and a rudder. The plane shape of the horizontal stabilizer 31 is rectangular, and the structure of the horizontal stabilizer 31 includes two circular tubular front beams and rear beams. The six tilt-rotor units are symmetrically mounted on the wing 2 and the inverted T-shaped tail 3 through six arms.

[0015] like Figure 3As shown, the fuselage 1 is composed of two circular tube beams, and the two circular tube-shaped front beams 21 and rear beams 22 of the wing and the two circular tube-shaped front beams 32 and rear beams 33 of the horizontal stabilizer are vertically connected to the two circular tube beams 11 of the fuselage.

[0016] like Figure 2 As shown, the six arms of the drone are divided into three pairs, including an arm pair 41 in the wing, an arm pair 42 at the end of the wing, and an arm pair 43 at the end of the tail. Each arm pair in the wing is composed of a circular tube beam, the length of which is at least the rotor radius, and is vertically connected to the two circular tube-shaped front beams 21 and rear beams 22 of the wing in the middle of the wing. The arm pair 42 at the end of the wing is extended outward from the ends of both sides of the wing by the circular tube-shaped front beam 21 of the wing, and the length is equal to the rotor radius. The arm pair 43 at the end of the tail is extended outward from the ends of both sides of the horizontal stabilizer by the circular tube-shaped front beam 32 of the horizontal stabilizer, and the length is equal to the rotor radius.

[0017] like Figure 2 As shown, 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 the arm pair 41 in the wing, the second tilt-rotor unit pair 52 is respectively mounted on the arm pair 42 at the end of the wing, and the third tilt-rotor unit pair 53 is respectively mounted on the arm pair 43 at the end of the tail.

[0018] When the drone is in flight, all six tilt-rotor units are in working order.

[0019] like Figure 2 As shown in FIG. 1 , when the UAV is in a vertical flight state, the projections of the six tilt-rotor units do not overlap with the wings and the horizontal stabilizer, eliminating the downward load generated by the rotor slipstream on the wings and the horizontal stabilizer. When the UAV is in the tilt transition state between the vertical flight state and the horizontal forward flight state, as shown in FIG. Figure 4 As shown, the six tilt-rotor units tilt synchronously.

[0020] 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 5 As shown in FIG. 1 , when the first tilt-rotor pair increases the rotation speed and the third tilt-rotor pair decreases the rotation speed, the difference in the pulling force they generate will generate a nose-up moment. The yaw motion of the UAV is achieved by the differential tilt angle of the two tilt-rotor units in the second tilt-rotor pair, as shown in FIG. Figure 6As 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 7 shown.

[0021] Preferably, the installation position of the battery energy unit 6 can be adjusted along the front and rear of the fuselage according to the adjustment requirements of the center of gravity of the entire aircraft.

Claims

1. A new configuration of a medium-sized unmanned electric tilt-rotor aircraft capable of vertical take-off and landing and long-range high-speed flight, comprising: The fuselage, wings, inverted T-tail, six arms and 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 inverted T-shaped tail is symmetrically mounted on the tail section of the fuselage, and the two landing gears are respectively mounted on the front section and the tail section of the fuselage; the wing has a rectangular plane shape, the wing structure includes two front and rear tubular beams, and the trailing edge of the wing is provided with ailerons; the inverted T-shaped tail includes a horizontal stabilizer, a vertical stabilizer, an elevator and a rudder, the horizontal stabilizer has a rectangular plane shape, and the horizontal stabilizer structure includes two front and rear tubular beams; the characteristics are: The fuselage is composed of two circular tube beams, and the two circular tube-shaped front and rear beams of the wing and the two circular tube-shaped front and rear beams of the horizontal stabilizer are vertically connected to the two circular tube beams of the fuselage; The six tilt-rotor units are symmetrically mounted on the wing and the inverted T-shaped tail through the six arms; The six arms are divided into three pairs, including an arm pair in the wing, an arm pair at the end of the wing, and an arm pair at the end of the tail. The arm pair in the wing is each composed of a circular tube beam, the length of which is at least the rotor radius, and is vertically connected to the two circular tube-shaped front and rear beams of the wing in the middle of the wing; the arm pair at the end of the wing is formed by the circular tube-shaped front beam of the wing extending outward from the two side ends of the wing to a length equal to the rotor radius; the arm pair at the end of the tail is formed by the circular tube-shaped front beam of the horizontal stabilizer extending outward from the two side ends of the horizontal stabilizer to a length equal to the rotor radius; 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 a pair of arms at the end of the wing, and the third tilt-rotor unit pair is respectively mounted on a pair of arms at the end of the tail; when the UAV is in flight, the six tilt-rotor units are all in working state; when the UAV is in vertical flight, the six tilt-rotor units are The downward projection of the propeller disc does not overlap with the wing and the horizontal stabilizer, eliminating the downward load generated by the rotor downwash on the wing and the horizontal stabilizer; when the UAV is in a vertical flight state, the pitch motion of the UAV is achieved by the pull 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 achieved by the two tilt-rotors in the second tilt-rotor unit pair using the differential tilt angle, and the roll motion is achieved by the two tilt-rotors of the second tilt-rotor unit pair using the pull difference generated by different rotation speeds; According to the six tilt-rotor units of claim 1, it is characterized in that when the UAV is in a rotor tilt transition state between a vertical flight state and a horizontal forward flight state, the six tilt-rotor units are tilted synchronously.

2. A battery energy unit according to claim 1, characterized in that: The installation position of the battery energy unit can be adjusted along the front and rear of the fuselage according to the adjustment requirements of the center of gravity of the entire aircraft.

Images