Oil-electric hybrid tilting wing aircraft and flight control method thereof

Abstract

The invention discloses an oil-electric hybrid tilt-rotor aircraft and a flight control method thereof. The oil-electric hybrid tilt-rotor aircraft comprises a fuselage; two main wings; the main wing is fixed with a rotor wing and is provided with blades; the front support arm is connected with the fuselage; a tiltable rotor having a blade; the vertical fin is connected with the fuselage; the horizontal tail is connected with the vertical tail; the horizontal tail fixed rotor wings are connected with the horizontal tail; the fixed wing tilting mechanism is used for driving the main wing fixed rotor to integrally rotate; the tilting wing tilting mechanism is used for driving the whole tiltable rotor wing to rotate; the fuel power device is used for driving the fixed rotor wing tilting mechanism to act; and the electric vertical power device is used for driving the tilting wing tilting mechanism to act. According to the invention, two sets of independent power systems, namely the electric vertical power device and the fuel power device, are controlled, so that the power distribution of the aircraft is completed in different stages, the energy consumption can be saved, the cruising ability can be improved, and the flying stability and safety can be improved.

Description

Technical Field

[0001] The present invention relates to the field of aircraft design, and in particular to an oil-electric hybrid tilt-rotor aircraft and a flight control method thereof. Background Art

[0002] Tilt-rotor aircraft can combine the advantages of multi-rotor and fixed-wing aircraft to achieve vertical take-off and landing, precise hovering and high-speed cruising.

[0003] At the same time, there are technical solutions for driving tilt-rotor aircraft through hybrid power of oil and electricity. For example, the patent application with application number 202010405391.0 and patent name "A Tilt-rotor Hybrid Electric Vertical Take-off and Landing Fixed-wing UAV" discloses a technical solution for using fuel power and batteries to provide power for different flight stages of the aircraft.

[0004] However, the above technical solution only has a pair of tilting wings composed of a tilting motor and a front rotor and a pair of fixed rotors, which makes it unable to provide sufficient lift or thrust during vertical takeoff, landing and level flight. At the same time, since the tilting angles of the tilting wings and the fixed rotors cannot be adjusted at will, the flight attitude of the aircraft cannot be adjusted. Summary of the invention

[0005] In view of the shortcomings of the prior art, the present invention provides a hybrid oil-electric tilt-rotor aircraft and a flight control method thereof, which controls two independent power systems, an electric vertical take-off power unit and a fuel power unit, so as to complete the power distribution of the aircraft at different stages, thereby saving energy consumption, improving endurance, and improving flight stability and safety.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] On the one hand, there is provided a hybrid oil-electric tilt-rotor aircraft, comprising:

[0008] body;

[0009] Two main wings, both of which are rotatably connected to the fuselage as a whole, or both of which are fixedly connected to the fuselage and have rotatable parts;

[0010] The first main wing fixed rotor and the second main wing fixed rotor both have blades, and when the two main wings are rotatably connected to the fuselage as a whole, the first main wing fixed rotor and the second main wing fixed rotor are respectively connected to one main wing, and when the two main wings are fixedly connected to the fuselage and both have rotatable parts, the first main wing fixed rotor and the second main wing fixed rotor are respectively connected to the rotatable part of one main wing;

[0011] A first front arm and a second front arm, both of which are connected to the fuselage, and the free ends of the first front arm and the second front arm extend toward the front of the fuselage;

[0012] The first tiltable rotor and the second tiltable rotor both have blades and are respectively connected to the first front support arm and the second front support arm;

[0013] A vertical tail connected to the tail of the fuselage, with a free end extending upward;

[0014] A horizontal tail connected to the vertical tail;

[0015] A first horizontal tail fixed rotor and a second horizontal tail fixed rotor, both of which are connected to the horizontal tail and are both located below the horizontal tail;

[0016] A fixed-wing tilt mechanism connected to the main wing, used to drive the main wing to rotate as a whole, or only drive the rotatable part of the main wing to rotate, so as to drive the first main wing fixed rotor as a whole and / or the second main wing fixed rotor to rotate as a whole;

[0017] A tilt-wing tilt mechanism, which is connected to the first tiltable rotor and the second tiltable rotor, and is used to drive the first tiltable rotor as a whole and / or the second tiltable rotor as a whole to rotate;

[0018] A fuel power device, which is installed inside the fuselage and connected to the fixed rotor tilt mechanism, and is used to provide power through fuel combustion to drive the fixed rotor tilt mechanism to move, and drive the blades of the first main wing fixed rotor and the second main wing fixed rotor to rotate;

[0019] The electric vertical take-off power device is respectively connected to the tilt-wing tilt mechanism, the first horizontal tail fixed rotor, and the second horizontal tail fixed rotor, and is used to provide electricity through a battery to drive the tilt-wing tilt mechanism to move, and to drive the blades of one or more of the first tiltable rotor, the second tiltable rotor, the first horizontal tail fixed rotor, and the second horizontal tail fixed rotor to rotate.

[0020] Preferably, the vertical tail is a V-shaped vertical tail having two free ends.

[0021] Preferably, there are two corresponding horizontal tails, and the two horizontal tails are respectively connected to a free end of the V-shaped vertical tail.

[0022] Preferably, the oil-electric hybrid tilt-rotor aircraft further includes:

[0023] A fuel power control unit connected to the fuel power device;

[0024] A power control unit connected to a battery of the electric vertical lift power device;

[0025] a flight control system connected to the fuel power control unit and used to control the operation of the fuel power control unit so as to adjust the power output of the fuel power device through the fuel power control unit;

[0026] And / or, connected to the power control unit to control the action of the power control unit, so that the battery of the electric vertical lift power device provides power to the tilt mechanism of the tilt-wing under the control of the power control unit, and provides power to one or more of the first tilt rotor, the second tilt rotor, the first horizontal tail fixed rotor, and the second horizontal tail fixed rotor, so as to correspondingly drive the rotation of the blades of one or more of the first tilt rotor, the second tilt rotor, the first horizontal tail fixed rotor, and the second horizontal tail fixed rotor.

[0027] Preferably, the battery comprises a storage battery.

[0028] On the other hand, a flight control method for the above-mentioned hybrid tilt-rotor aircraft is also provided, which comprises the following steps:

[0029] Vertical stage control, which specifically includes:

[0030] Controlling the operation of the fuel power device so that the fuel power device provides power through fuel combustion to drive the fixed rotor tilt mechanism to operate, so that the fixed rotor tilt mechanism drives the first main wing fixed rotor as a whole and the second main wing fixed rotor as a whole to rotate, so that the first main wing fixed rotor and the second main wing fixed rotor as a whole are in a vertical state with blades facing upward; and the fuel power device provides power through fuel combustion to drive the blades of the first main wing fixed rotor and the second main wing fixed rotor to rotate;

[0031] The battery controlling the electric vertical lift power device provides electric power to the tilt-wing tilt mechanism, so as to drive the tilt-wing tilt mechanism to move by electric power, so as to drive the first tiltable rotor as a whole and the second tiltable rotor as a whole to rotate by the tilt-wing tilt mechanism, so that the first tiltable rotor and the second tiltable rotor as a whole are both in a vertical state with the blades facing upward; and the battery of the electric vertical lift power device drives the blades of the first tiltable rotor and the second tiltable rotor and the blades of the first horizontal tail fixed rotor and the second horizontal tail fixed rotor to rotate by providing electric power.

[0032] Preferably, the flight control method further comprises the following steps:

[0033] Level flight control, which specifically includes:

[0034] When the aircraft as a whole rises to a predetermined height, the fixed rotor tilt mechanism is controlled to move, so as to drive the first main wing fixed rotor as a whole and the second main wing fixed rotor as a whole to rotate again through the fixed rotor tilt mechanism, so that the first main wing fixed rotor as a whole and the second main wing fixed rotor as a whole are both in a horizontal state with the blades facing forward;

[0035] And, controlling the movement of the tilt-wing tilt mechanism to drive the first tiltable rotor assembly and the second tiltable rotor assembly to rotate again through the tilt-wing tilt mechanism, so that the first tiltable rotor assembly and the second tiltable rotor assembly are both in a horizontal state with the blades facing forward.

[0036] Preferably, the level flight stage control further includes:

[0037] The wingspan directions of the first horizontal tail fixed rotor and the second horizontal tail fixed rotor are adjusted so that the wingspan directions are consistent with the flight direction of the aircraft, and the first horizontal tail fixed rotor and the second horizontal tail fixed rotor are both in a locked state.

[0038] Preferably, the level flight stage control further includes:

[0039] When the first main wing fixed rotor whole and the second main wing fixed rotor whole are both in a horizontal state with the blades facing forward, the fixed rotor tilt mechanism is controlled to move, so as to drive the first main wing fixed rotor whole and the second main wing fixed rotor whole to rotate again by a predetermined angle through the fixed rotor tilt mechanism, so as to adjust the tilt angles of the first main wing fixed rotor and the second main wing fixed rotor;

[0040] And adjust the blade rotation speed of one or more of the first main wing fixed rotor, the second main wing fixed rotor, the first tiltable rotor, and the second tiltable rotor.

[0041] Preferably, the flight control method further comprises the following steps:

[0042] Landing phase control, which specifically includes:

[0043] Controlling the fixed rotor tilt mechanism to move, so as to drive the first main wing fixed rotor assembly and the second main wing fixed rotor assembly to rotate again through the fixed rotor tilt mechanism, so that the first main wing fixed rotor assembly and the second main wing fixed rotor assembly are both in a vertical state with blades facing upward;

[0044] Controlling the tilt-wing tilt mechanism to move, so as to drive the first tiltable rotor assembly and the second tiltable rotor assembly to rotate again through the tilt-wing tilt mechanism, so that the first tiltable rotor assembly and the second tiltable rotor assembly are both in a vertical state with blades facing upward;

[0045] In addition, the first horizontal tail fixed rotor and the second horizontal tail fixed rotor are both unlocked, and power is supplied to the first horizontal tail fixed rotor and the second horizontal tail fixed rotor through the electric vertical lift power device to drive the blades of the first horizontal tail fixed rotor and the second horizontal tail fixed rotor to rotate.

[0046] Compared with the prior art, the present invention has the following beneficial effects:

[0047] The present invention controls two independent power systems, an electric vertical take-off power unit and a fuel power unit, so as to complete the power distribution of the aircraft at different stages and realize the best power system combination, thereby saving energy consumption and improving endurance. At the same time, by adjusting the tilt angle of the fixed rotor of the main wing and combining the adjustment of the blade speed, the flight attitude of the aircraft can be flexibly adjusted, thereby enhancing its performance in resisting crosswind interference and improving the stability and safety of flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] Figure 1 A top view of the oil-electric hybrid tilt-rotor aircraft of the present invention in the vertical take-off / landing stage;

[0049] Figure 2 It is a rear view of the oil-electric hybrid tilt-rotor aircraft of the present invention in the vertical take-off / landing stage;

[0050] Figure 3 A top view of the oil-electric hybrid tilt-rotor aircraft of the present invention in the level flight stage;

[0051] Figure 4 It is a schematic diagram of the structure of the flight control system, the fuel power control unit and the electric power control unit in the present invention. DETAILED DESCRIPTION

[0052] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0053] Embodiment 1:

[0054] like Figure 1-2 ,4, this embodiment provides a hybrid oil-electric tilt-rotor aircraft, which includes:

[0055] Body 1;

[0056] Two main wings 2, which are rotatably connected to the fuselage 1 as a whole, or are fixedly connected to the fuselage 1 and have a rotatable part, and the free ends of the two main wings 2 extend on both sides of the fuselage 1 respectively;

[0057] The first main wing fixed rotor 3 and the second main wing fixed rotor 3' both have blades 31, and when the two main wings 2 are rotatably connected to the fuselage 1 as a whole, the first main wing fixed rotor 3 and the second main wing fixed rotor 3' are respectively connected to one main wing 2, and when the two main wings 2 are fixedly connected to the fuselage 1 and both have rotatable parts, the first main wing fixed rotor 3 and the second main wing fixed rotor 3' are respectively connected to the rotatable part of one main wing 2;

[0058] A first front arm 4 and a second front arm 4', both of which are connected to the fuselage 1, and the free ends of the first front arm 4 and the second front arm 4' both extend toward the front of the fuselage 1;

[0059] The first tiltable rotor 5 and the second tiltable rotor 5' both have blades 51 and are respectively connected to the first front support arm 4 and the second front support arm 4';

[0060] A vertical tail 6, which is connected to the tail of the fuselage 1, and the free end of which extends upward; in this embodiment, the vertical tail 6 is a V-shaped vertical tail, which has two free ends;

[0061] A horizontal tail 7 connected to the vertical tail 6; in this embodiment, when the vertical tail 6 is a V-shaped vertical tail, there are two horizontal tails 7, and the two horizontal tails 7 are respectively connected to a free end of the V-shaped vertical tail, and at the same time, the two horizontal tails 7 can be an integrated structure;

[0062] The first horizontal tail fixed rotor 8 and the second horizontal tail fixed rotor 8' are both connected to the horizontal tail 7 and are both located below the horizontal tail 7. Correspondingly, when there are two horizontal tails 7, the first horizontal tail fixed rotor 8 and the second horizontal tail fixed rotor 8' are respectively connected to one horizontal tail 7 and are both located below the horizontal tail 7;

[0063] The fixed-wing tilt mechanism 9 is connected to the main wing 2 and is used to drive the main wing 2 to rotate as a whole, or only drive the rotatable part of the main wing 2 to rotate, so as to drive the first main wing fixed rotor 3 as a whole and / or the second main wing fixed rotor 3' to rotate as a whole;

[0064] A tilting mechanism 10 for tilting the wing, which is connected to the first tilting rotor 5 and the second tilting rotor 5', and is used to drive the first tilting rotor 5 and / or the second tilting rotor 5' to rotate as a whole;

[0065] a fuel power device 11, which is installed inside the fuselage 1 and connected to the fixed rotor tilt mechanism 9, and is used to provide power through fuel combustion to drive the fixed rotor tilt mechanism 9 to operate, so that the fixed rotor tilt mechanism 9 drives the first main wing fixed rotor 3 and / or the second main wing fixed rotor 3' to rotate as a whole, and provides power through fuel combustion to drive the blades 31 of the first main wing fixed rotor 3 and the second main wing fixed rotor 3' to rotate;

[0066] The electric vertical lift power device 12 is respectively connected to the tilt-wing tilt mechanism 10, the first horizontal tail fixed rotor 8, and the second horizontal tail fixed rotor 8', and is used to provide power through a battery to drive the tilt-wing tilt mechanism 10 to operate, so that the tilt-wing tilt mechanism 10 drives the first tiltable rotor 5 as a whole and / or the second tiltable rotor 5' as a whole to rotate, and to provide power through a battery to drive the blades of one or more of the first tiltable rotor 5, the second tiltable rotor 5', the first horizontal tail fixed rotor 8, and the second horizontal tail fixed rotor 8' to rotate. In this embodiment, the battery includes a storage battery;

[0067] A fuel power control unit 13 (such as an ECU (Electronic Control Unit), etc.), which is connected to the fuel power device 11;

[0068] A power control unit 14 connected to a battery of the electric vertical lift power device 12;

[0069] A flight control system 15, which is connected to the fuel power control unit 13 and is used to control the operation of the fuel power control unit 13, so as to adjust the power output of the fuel power device 11 through the fuel power control unit 13. For example, the fuel power control unit 13 can adjust the output power by adjusting the throttle of the fuel power device 11, and further drive the fixed rotor tilt mechanism 9 to operate through the fuel power device 11, so that the first main wing fixed rotor 3 as a whole and / or the second main wing fixed rotor 3' as a whole can rotate;

[0070] And / or, connected to the power control unit 14, used to control the action of the power control unit 14, so that the battery of the electric vertical lift power device 12 provides power to the tilt-wing tilt mechanism 10 under the control of the power control unit 14, and further drives the tilt-wing tilt mechanism 10 to move by power, and further drives the first tiltable rotor 5 as a whole and / or the second tiltable rotor 5' as a whole to rotate by the tilt-wing tilt mechanism 10, and provides power to one or more of the first tiltable rotor 5, the second tiltable rotor 5', the first horizontal tail fixed rotor 8, and the second horizontal tail fixed rotor 8' to correspondingly drive the rotation of the blades of one or more of the first tiltable rotor 5, the second tiltable rotor 5', the first horizontal tail fixed rotor 8, and the second horizontal tail fixed rotor 8'.

[0071] Therefore, the power system in this embodiment adopts two independent power systems, an electric vertical take-off device and a fuel power device, and provides sufficient lift or thrust for the vertical take-off, level flight and landing of the aircraft through two tiltable rotors and two rotatable main wing fixed rotors. At the same time, the aircraft in this embodiment adopts a main wing + V-shaped vertical tail layout, which can reduce the size of the aircraft and reduce the weight of the whole machine while still providing sufficient lift for its flight and reducing the weight of the whole machine. At the same time, after arranging the rotor under the horizontal tail, the loss of aerodynamic efficiency can be reduced, and the aerodynamic performance and controllability of the whole machine can be improved.

[0072] Embodiment 2:

[0073] This embodiment provides a flight control method for the tilt-rotor aircraft described in Embodiment 1, which comprises the following steps:

[0074] (1) Vertical lift control, which specifically includes:

[0075] like Figure 1 As shown, the flight control system 15 starts the fuel power control unit 13, and controls the fuel power device 11 to move through the fuel power control unit 13, so that the fuel power device 11 provides power through fuel combustion to drive the fixed rotor tilt mechanism 9 to move, and further drives the first main wing fixed rotor 3 as a whole and the second main wing fixed rotor 3' as a whole to rotate through the fixed rotor tilt mechanism 9, so that the first main wing fixed rotor 3 and the second main wing fixed rotor 3' are in a vertical state with the blades facing upward; specifically, the fixed wing tilt mechanism 9 can drive the first main wing fixed rotor 3 and the second main wing fixed rotor 3' to rotate as a whole by driving the main wing 2 to rotate as a whole, or only driving the rotatable part of the main wing 2 to rotate;

[0076] After the first main wing fixed rotor 3 and the second main wing fixed rotor 3' are in a vertical state with the blades facing upward, the fuel power device 11 also provides power through fuel combustion to drive the blades 31 of the first main wing fixed rotor 3 and the blades 31 of the second main wing fixed rotor 3' to rotate with the maximum output power;

[0077] And, the flight control system 15 starts the power control unit 14, controls the battery of the electric vertical lift power device 12 through the power control unit 14 to provide power to the tilt-wing tilt mechanism 10, and further drives the tilt-wing tilt mechanism 10 to operate through the power, so as to drive the first tiltable rotor 5 and the second tiltable rotor 5' to rotate as a whole through the tilt-wing tilt mechanism 10, so that the first tiltable rotor 5 and the second tiltable rotor 5' are in a vertical state with the blades facing upward;

[0078] After the first tiltable rotor 5 and the second tiltable rotor 5' are in a vertical state with the blades facing upward, the battery of the electric vertical lift power device 12 also provides power to drive the blades 51 of the first tiltable rotor 5 and the second tiltable rotor 5' and the blades of the first horizontal tail fixed rotor 8 and the second horizontal tail fixed rotor 8' to rotate;

[0079] The blade rotation planes of the first tiltable rotor 5 and the second tiltable rotor 5' in a vertical state, the blade rotation planes of the first main wing fixed rotor 3 and the second main wing fixed rotor 3' in a vertical state, and the blade rotation planes of the first horizontal tail fixed rotor 8 and the second horizontal tail fixed rotor 8' are parallel to each other;

[0080] Thus, the maximum thrust can be output through the two main wing fixed rotors to provide the main lift for the aircraft, and the auxiliary lift can be provided through the two tilting rotors and the horizontal tail fixed rotor to drive the aircraft to take off vertically;

[0081] (2) Level flight control, which specifically includes:

[0082] like Figure 3 As shown, when the aircraft as a whole rises to a predetermined height, the flight control system 15 controls the fixed rotor tilt mechanism 9 to operate, so as to drive the first main wing fixed rotor 3 as a whole and the second main wing fixed rotor 3' as a whole to rotate again through the fixed rotor tilt mechanism 9, so that the first main wing fixed rotor 3 as a whole and the second main wing fixed rotor 3' as a whole are both in a horizontal state with the blades facing forward;

[0083] And, the flight control system 15 controls the tilt-wing tilt mechanism 10 to move, so as to drive the first tiltable rotor 5 as a whole and the second tiltable rotor 5' as a whole to rotate again through the tilt-wing tilt mechanism 10, so that the first tiltable rotor 5 as a whole and the second tiltable rotor 5' as a whole are both in a horizontal state with the blades facing forward;

[0084] At the same time, the flight control system 15 is used to adjust the wingspan direction of the first horizontal tail fixed rotor 8 and the second horizontal tail fixed rotor 8', so that the wingspan direction is consistent with the flight direction of the aircraft, and the first horizontal tail fixed rotor 8 and the second horizontal tail fixed rotor 8' are both in a locked state (i.e., the blades are not rotating) to prevent the rotors from being in a windmill state, so as to reduce the resistance of the aircraft and improve the control stability and flight economy of the aircraft; wherein the wingspan direction refers to the length direction of the rotor blades; and the flight control system 15 is used to adjust the blade speed of one or more of the first main wing fixed rotor 3, the second main wing fixed rotor 3', the first tiltable rotor 5, and the second tiltable rotor 5';

[0085] Further, when the first main wing fixed rotor 3 as a whole and the second main wing fixed rotor 3' as a whole are both in a horizontal state with the blades facing forward, the flight control system 15 controls the fixed rotor tilt mechanism 9 to operate, so as to drive the first main wing fixed rotor 3 as a whole and the second main wing fixed rotor 3' as a whole to rotate again by a predetermined angle through the fixed rotor tilt mechanism 9, thereby adjusting the tilt angles of the first main wing fixed rotor 3 and the second main wing fixed rotor 3', and at the same time, combined with the adjustment of the blade rotation speed, the flight attitude of the aircraft can be flexibly adjusted, thereby enhancing its performance in resisting crosswind interference and improving the stability and safety of the flight;

[0086] (3) Landing phase control, which specifically includes:

[0087] The flight control system 15 controls the fixed rotor tilt mechanism 9 to operate, so as to drive the first main wing fixed rotor 3 as a whole and the second main wing fixed rotor 3' as a whole to rotate again through the fixed rotor tilt mechanism 9, so that the first main wing fixed rotor 3 as a whole and the second main wing fixed rotor 3' as a whole are both in a vertical state with the blades facing upwards;

[0088] And, the flight control system 15 controls the tilt-wing tilt mechanism 10 to move, so as to drive the first tiltable rotor 5 as a whole and the second tiltable rotor 5' as a whole to rotate again through the tilt-wing tilt mechanism 10, so that the first tiltable rotor 5 as a whole and the second tiltable rotor 5' as a whole are both in a vertical state with the blades facing upwards;

[0089] At the same time, the first horizontal tail fixed rotor 8 and the second horizontal tail fixed rotor 8' are unlocked by the flight control system 15, and the first horizontal tail fixed rotor 8 and the second horizontal tail fixed rotor 8' are powered by the electric vertical lift power device 12 to drive the blades of the first horizontal tail fixed rotor 8 and the second horizontal tail fixed rotor 8' to rotate;

[0090] Also, by adjusting the blade speed of one or more of the first main wing fixed rotor 3, the second main wing fixed rotor 3', the first tiltable rotor 5, the second tiltable rotor 5', the first horizontal tail fixed rotor 8, and the second horizontal tail fixed rotor 8' through the flight control system 15, it is also helpful to flexibly adjust the flight attitude of the aircraft by adjusting the blade speed, thereby improving the stability and safety of the flight;

[0091] Thus, the rotation of the blades of the first main wing fixed rotor 3, the second main wing fixed rotor 3', the first tiltable rotor 5, the second tiltable rotor 5', the first horizontal tail fixed rotor 8, and the second horizontal tail fixed rotor 8' provides lift for the aircraft during the landing process, so that the flight speed and flight altitude of the aircraft are gradually reduced until the aircraft hovers above the landing point;

[0092] The aircraft then descends vertically to the landing point at a predetermined descent speed.

[0093] To sum up, the present invention can control two independent power systems, namely the electric vertical take-off power unit and the fuel power unit, so as to complete the power distribution of the aircraft in different stages, and can achieve the best power system combination, that is, in the vertical take-off stage, the fuel power is used to drive the main wing fixed rotor to output thrust as the main lift, and the two tiltable rotors and the horizontal tail fixed rotor provide auxiliary lift. In the level flight stage, the horizontal tail fixed rotor is locked, and only the main wing fixed rotor and the tiltable rotor are relied on to increase the power, thereby saving energy consumption and improving the endurance. In the landing stage, the horizontal tail fixed rotor is unlocked again to ensure a smooth landing of the aircraft, so as to give full play to the advantages of the two power systems.

[0094] At the same time, by adjusting the tilt angle of the fixed rotor of the main wing and combining it with the adjustment of the blade speed, the flight attitude of the aircraft can be flexibly adjusted, thereby enhancing its performance in resisting crosswind interference and improving the stability and safety of flight.

[0095] It should be noted that the technical features in the above-mentioned embodiments 1-2 can be combined arbitrarily, and the combined technical solutions all belong to the protection scope of the present application. In this article, terms such as "including", "comprising" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or equipment. In the absence of further restrictions, the elements defined by the sentence "including one..." do not exclude the presence of other identical elements in the process, method, article or equipment including the elements.

[0096] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A hybrid oil-electric tilt-rotor aircraft, characterized in that: include: body; Two main wings, both of which are rotatably connected to the fuselage as a whole, or both of which are fixedly connected to the fuselage and have rotatable parts; The first main wing fixed rotor and the second main wing fixed rotor both have blades, and when the two main wings are rotatably connected to the fuselage as a whole, the first main wing fixed rotor and the second main wing fixed rotor are respectively connected to one main wing, and when the two main wings are fixedly connected to the fuselage and both have rotatable parts, the first main wing fixed rotor and the second main wing fixed rotor are respectively connected to the rotatable part of one main wing; A first front arm and a second front arm, both of which are connected to the fuselage, and the free ends of the first front arm and the second front arm extend toward the front of the fuselage; The first tiltable rotor and the second tiltable rotor both have blades and are respectively connected to the first front support arm and the second front support arm; A vertical tail connected to the tail of the fuselage 1, with a free end extending upward; A horizontal tail connected to the vertical tail; A first horizontal tail fixed rotor and a second horizontal tail fixed rotor, both of which are connected to the horizontal tail and are both located below the horizontal tail; A fixed-wing tilt mechanism connected to the main wing, used to drive the main wing to rotate as a whole, or only drive the rotatable part of the main wing to rotate, so as to drive the first main wing fixed rotor as a whole and / or the second main wing fixed rotor to rotate as a whole; A tilt-wing tilt mechanism, which is connected to the first tiltable rotor and the second tiltable rotor, and is used to drive the first tiltable rotor as a whole and / or the second tiltable rotor as a whole to rotate; A fuel power device, which is installed inside the fuselage and connected to the fixed rotor tilt mechanism, and is used to provide power through fuel combustion to drive the fixed rotor tilt mechanism to move, and drive the blades of the first main wing fixed rotor and the second main wing fixed rotor to rotate; The electric vertical take-off power device is respectively connected to the tilt-wing tilt mechanism, the first horizontal tail fixed rotor, and the second horizontal tail fixed rotor, and is used to provide electricity through a battery to drive the tilt-wing tilt mechanism to move, and to drive the blades of one or more of the first tiltable rotor, the second tiltable rotor, the first horizontal tail fixed rotor, and the second horizontal tail fixed rotor to rotate.

2. The oil-electric hybrid tilt-rotor aircraft according to claim 1, characterized in that: The vertical tail is a V-shaped vertical tail having two free ends.

3. The oil-electric hybrid tilt-rotor aircraft according to claim 2, characterized in that: There are two corresponding horizontal tails, and the two horizontal tails are respectively connected to a free end of the V-shaped vertical tail.

4. The oil-electric hybrid tilt-rotor aircraft according to claim 1, characterized in that: The oil-electric hybrid tilt-rotor aircraft also includes: A fuel power control unit connected to the fuel power device; A power control unit connected to a battery of the electric vertical lift power device; a flight control system connected to the fuel power control unit and used to control the operation of the fuel power control unit so as to adjust the power output of the fuel power device through the fuel power control unit; And / or, connected to the power control unit to control the action of the power control unit, so that the battery of the electric vertical lift power device provides power to the tilt mechanism of the tilt-wing under the control of the power control unit, and provides power to one or more of the first tilt rotor, the second tilt rotor, the first horizontal tail fixed rotor, and the second horizontal tail fixed rotor, so as to correspondingly drive the rotation of the blades of one or more of the first tilt rotor, the second tilt rotor, the first horizontal tail fixed rotor, and the second horizontal tail fixed rotor.

5. The oil-electric hybrid tilt-rotor aircraft according to claim 1, characterized in that: The battery includes a storage battery.

6. A flight control method for a hybrid tilt-rotor aircraft according to any one of claims 1 to 5, characterized in that: The steps include: Vertical stage control, which specifically includes: Controlling the operation of the fuel power device so that the fuel power device provides power through fuel combustion to drive the fixed rotor tilt mechanism to operate, so that the fixed rotor tilt mechanism drives the first main wing fixed rotor as a whole and the second main wing fixed rotor as a whole to rotate, so that the first main wing fixed rotor and the second main wing fixed rotor as a whole are in a vertical state with blades facing upward; and the fuel power device provides power through fuel combustion to drive the blades of the first main wing fixed rotor and the second main wing fixed rotor to rotate; The battery controlling the electric vertical lift power device provides electric power to the tilt-wing tilt mechanism, so as to drive the tilt-wing tilt mechanism to move by electric power, so as to drive the first tiltable rotor as a whole and the second tiltable rotor as a whole to rotate by the tilt-wing tilt mechanism, so that the first tiltable rotor and the second tiltable rotor as a whole are both in a vertical state with the blades facing upward; and the battery of the electric vertical lift power device drives the blades of the first tiltable rotor and the second tiltable rotor and the blades of the first horizontal tail fixed rotor and the second horizontal tail fixed rotor to rotate by providing electric power.

7. The flight control method according to claim 6, characterized in that: The flight control method further comprises the following steps: Level flight control, which specifically includes: When the aircraft as a whole rises to a predetermined height, the fixed rotor tilt mechanism is controlled to move, so as to drive the first main wing fixed rotor as a whole and the second main wing fixed rotor as a whole to rotate again through the fixed rotor tilt mechanism, so that the first main wing fixed rotor as a whole and the second main wing fixed rotor as a whole are both in a horizontal state with the blades facing forward; And, controlling the movement of the tilt-wing tilt mechanism to drive the first tiltable rotor assembly and the second tiltable rotor assembly to rotate again through the tilt-wing tilt mechanism, so that the first tiltable rotor assembly and the second tiltable rotor assembly are both in a horizontal state with the blades facing forward.

8. The flight control method according to claim 7, characterized in that: The level flight stage control also includes: The wingspan directions of the first horizontal tail fixed rotor and the second horizontal tail fixed rotor are adjusted so that the wingspan directions are consistent with the flight direction of the aircraft, and the first horizontal tail fixed rotor and the second horizontal tail fixed rotor are both in a locked state.

9. The flight control method according to claim 7, characterized in that: The level flight stage control also includes: When the first main wing fixed rotor whole and the second main wing fixed rotor whole are both in a horizontal state with the blades facing forward, the fixed rotor tilt mechanism is controlled to move, so as to drive the first main wing fixed rotor whole and the second main wing fixed rotor whole to rotate again by a predetermined angle through the fixed rotor tilt mechanism, so as to adjust the tilt angles of the first main wing fixed rotor and the second main wing fixed rotor; And adjust the blade rotation speed of one or more of the first main wing fixed rotor, the second main wing fixed rotor, the first tiltable rotor, and the second tiltable rotor.

10. The flight control method according to claim 6, characterized in that: The flight control method further comprises the following steps: Landing phase control, which specifically includes: Controlling the fixed rotor tilt mechanism to move, so as to drive the first main wing fixed rotor assembly and the second main wing fixed rotor assembly to rotate again through the fixed rotor tilt mechanism, so that the first main wing fixed rotor assembly and the second main wing fixed rotor assembly are both in a vertical state with blades facing upward; Controlling the tilt-wing tilt mechanism to move, so as to drive the first tiltable rotor assembly and the second tiltable rotor assembly to rotate again through the tilt-wing tilt mechanism, so that the first tiltable rotor assembly and the second tiltable rotor assembly are both in a vertical state with blades facing upward; In addition, the first horizontal tail fixed rotor and the second horizontal tail fixed rotor are both unlocked, and power is supplied to the first horizontal tail fixed rotor and the second horizontal tail fixed rotor through the electric vertical lift power device to drive the blades of the first horizontal tail fixed rotor and the second horizontal tail fixed rotor to rotate.

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