Aircraft

Abstract

The utility model relates to the technical field of flight equipment, and discloses an aircraft which comprises an aircraft body and a plurality of rotors capable of driving the aircraft body to vertically lift, and further comprises tandem wings and propulsion equipment, the tandem wings are arranged on the two sides of the fuselage, and the propellers are arranged on the fuselage or the tandem wings and can provide thrust for promoting the aircraft to advance. According to the unmanned aerial vehicle, a vertical mechanism and a cruising mechanism are separated, during cruising, power is provided mainly through the serial wings and the propelling equipment, and the serial wings can naturally generate lift force for promoting the flight of the unmanned aerial vehicle in the cruising process; the multiple rotor wings only need to be closed or opened for a short time in the cruising process to play a role in assisting cruising, so that the power consumption needed in the cruising process is effectively reduced, and the aircraft can be more suitable for long-time flight tasks and is more suitable for an existing battery capacity and energy management technology.

Description

Technical Field

[0001] The utility model relates to the technical field of flight equipment, and in particular to an aircraft. Background Art

[0002] Existing personal aircraft primarily utilize multi-rotor designs. While simple and easy to manufacture, they suffer from limitations such as limited cruising capability, flight stability issues, and noise and vibration. Cruising time, in particular, is limited by battery capacity and energy management technology, hindering their application in long-duration missions.

[0003] In view of this, this application is hereby filed. Utility Model Content

[0004] The utility model discloses an aircraft to solve the technical problem in the related art that the cruising time of existing aircraft is limited by battery capacity and energy management technology, which affects its application in long-term flight missions.

[0005] In order to solve the above technical problems, the technical solution adopted by the present invention is:

[0006] The utility model provides an aircraft, comprising a fuselage and a plurality of rotors, wherein the plurality of rotors can drive the fuselage to rise and fall vertically, and further comprising tandem wings and a propulsion device;

[0007] The tandem wings are arranged on both sides of the fuselage, and the propulsion device is arranged on the fuselage or the tandem wings, and can provide thrust to drive the aircraft forward.

[0008] Furthermore, the tandem wing includes two front fixed wings and two rear fixed wings respectively fixed to the fuselage, and a connecting piece is provided between the front fixed wings and the rear fixed wings on the same side of the fuselage;

[0009] The plurality of rotors are arranged on top of the two connecting members.

[0010] Furthermore, the number of the rotors is 6, and each connecting member is connected to 3 rotors.

[0011] Furthermore, the connecting member includes a first strip portion and a second strip portion;

[0012] The rotor is connected to the first strip portion, the length direction of the first strip portion is parallel to the forward direction of the aircraft, and the first strip portion is connected to the rear fixed wing;

[0013] The second strip-shaped portion is connected between the first strip-shaped portion and the front fixed wing.

[0014] Furthermore, the front end of the first strip portion extends to the front of the front fixed wing, and the rear end of the first strip portion extends to the rear of the rear fixed wing;

[0015] The rotor is respectively provided at the front end, the middle part and the rear end of each first strip portion, and the rotor in the middle part of the first strip portion is located between the front fixed wing and the rear fixed wing.

[0016] Furthermore, the second strip portion cooperates with the front fixed wing to form a triangular structure.

[0017] Furthermore, the connecting piece is made of carbon fiber composite material.

[0018] Furthermore, a vertical tail is provided at the end of the rear fixed wing.

[0019] Furthermore, the propulsion device is a tail rotor arranged at the rear end of the fuselage.

[0020] Furthermore, the rotor has two blades.

[0021] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0022] The present invention provides an aircraft in which a plurality of rotors serve together as a vertical lift mechanism, providing power for the aircraft to ascend and descend vertically, and a tandem wing and a propulsion device serve together as a cruise mechanism, providing power for the aircraft to advance for cruise. Thus, the vertical lift mechanism and the cruise mechanism are distinguished. During cruise, the tandem wing and the propulsion device are used to provide power primarily. The tandem wing can naturally generate lift during cruise to facilitate the flight of the aircraft. The plurality of rotors only need to be closed or opened for a short period of time during cruise to assist in cruise. This effectively reduces the power consumption required during cruise, making the aircraft more adaptable to long-term flight missions and more suitable for existing battery capacity and energy management technologies. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments. It should be understood that the following drawings only illustrate certain embodiments of the present invention and should not be regarded as limiting the scope. A person of ordinary skill in the art can also derive other relevant drawings based on these drawings without inventive effort.

[0024] Figure 1 This is a schematic structural diagram of an embodiment of the present utility model;

[0025] Figure 2 It is a top view of an embodiment of the present utility model.

[0026] Markings and corresponding parts names in the accompanying drawings:

[0027] 1-fuselage, 2-rotor, 3-front fixed wing, 4-rear fixed wing, 41-vertical tail, 5-connecting piece, 51-first strip portion, 52-second strip portion, 6-tail rotor. DETAILED DESCRIPTION

[0028] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0029] In the following description, numerous specific details are set forth to provide a thorough understanding of the present invention. However, it will be apparent to one skilled in the art that these specific details are not necessarily required to practice the present invention. In other instances, well-known structures, circuits, materials, or methods are not described in detail to avoid obscuring the present invention.

[0030] Throughout this specification, references to "one embodiment," "an embodiment," "an example," or "an example" mean that a particular feature, structure, or characteristic described in conjunction with the embodiment or example is included in at least one embodiment of the present invention. Therefore, the phrases "one embodiment," "an embodiment," "an example," or "an example" appearing in various places throughout this specification do not necessarily refer to the same embodiment or example. In addition, the particular features, structures, or characteristics may be combined in one or more embodiments or examples in any suitable combination and / or subcombination. Furthermore, it will be understood by those of ordinary skill in the art that the figures provided herein are for illustrative purposes only and are not necessarily drawn to scale. As used herein, the term "and / or" includes any and all combinations of one or more of the associated listed items.

[0031] In the description of the present invention, it should be understood that the terms "front", "rear", "left", "right", "up", "down", "vertical", "horizontal", "high", "low", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limiting the scope of protection of the present invention.

[0032] Example

[0033] like Figure 1-2As shown, an embodiment of the present invention provides an aircraft, including a fuselage 1 and multiple rotors 2, and the multiple rotors 2 can drive the fuselage 1 to rise and fall vertically. In addition, it also includes tandem wings and a propulsion device; the tandem wings are arranged on both sides of the fuselage 1, and the propulsion device is arranged on the fuselage 1 or the tandem wings, which can provide thrust to propel the aircraft forward.

[0034] At this point, the multiple rotors 2 act together as the vertical lift mechanism, providing power for the aircraft's vertical ascent and descent, while the tandem wings and propulsion system act together as the cruise mechanism, providing power for the aircraft's forward movement for cruise. Thus, the vertical lift mechanism and cruise mechanism are distinguished. During cruise, power is primarily provided by the tandem wings and propulsion system. The tandem wings naturally generate lift during cruise, enabling the aircraft to fly. The multiple rotors 2 only need to be shut down or opened briefly during cruise to assist in cruise. This effectively reduces power consumption during cruise, making the aircraft more adaptable to long-duration flight missions and more suitable for existing battery capacity and energy management technologies.

[0035] Among them, Figure 1 As shown, the propulsion device can be a tail rotor 6 arranged at the rear end of the fuselage 1. The tail rotor 6 is selected to be suitable for the multiple rotors 2 of the vertical lifting mechanism. At the same time, by arranging the tail rotor 6 at the rear end of the fuselage 1 instead of on the tandem wing, the impact of the propulsion device on the wing during propulsion can be avoided, the vibration transmitted to the tandem wing can be reduced, and the flight stability can be further improved.

[0036] In one or more embodiments, the tandem wing includes two front fixed wings 3 and two rear fixed wings 4 respectively fixed to the fuselage 1, the two front fixed wings 3 are respectively symmetrically fixed on both sides of the front of the fuselage 1, and the two rear fixed wings 4 are respectively symmetrically fixed on both sides of the rear of the fuselage 1, and the design height of the front fixed wings 3 is higher than the design height of the rear fixed wings 4. At this time, during cruising, the downwash airflow of the front fixed wings 3 is unlikely to cause adverse effects on the rear fixed wings 4.

[0037] On this basis, a connector 5 is provided between the front fixed wing 3 and the rear fixed wing 4 on the same side of the fuselage 1, so that the front fixed wing 3, the rear fixed wing 4, the fuselage 1 and the connector 5 together form a relatively stable box-type structure, which improves the overall stability and vibration resistance of the aircraft, thereby reducing the vibration impact of the rotor 2 on the whole when it is started; the multiple rotors 2 are divided into two groups and are respectively arranged on the top of the two connectors 5. At this time, the rotor 2 is indirectly connected to the tandem wing through the connector 5, thereby reducing the vibration transmitted to the tandem wing when the rotor 2 is turned on, further improving the flight stability.

[0038] The number of rotors 2 can be 4, 6, 8 or even more, preferably 6. Figure 1-2 As shown, the six rotors 2 are divided into two groups, with three rotors in each group. The three rotors 2 provide lifting power to the front, middle and rear of the aircraft respectively, and have high stability.

[0039] The connector 5 is preferably made of carbon fiber composite material to reduce the weight and flight resistance of the connector 5, and further reduce vibration and power consumption during cruising.

[0040] For the connector 5, in one or more embodiments: the connector 5 includes a first strip portion 51 and a second strip portion 52; the rotor 2 is connected to the first strip portion 51, the length direction of the first strip portion 51 is parallel to the forward direction of the aircraft, and the first strip portion 51 is connected to the rear fixed wing 4; the second strip portion 52 is connected between the first strip portion 51 and the front fixed wing 3. At this time, the strip structure of the first strip portion 51 and the second strip portion 52 can reduce the flight resistance generated by the connector 5 during the cruising process of the aircraft, and further reduce the vibration and the required power consumption during the cruising process.

[0041] Among them, Figure 2 As shown, the front end of the first strip portion 51 extends to the front of the front fixed wing 3, the rear end of the first strip portion 51 extends to the rear of the rear fixed wing 4, and the middle part of the first strip portion 51 is located between the front fixed wing 3 and the rear fixed wing 4 (excluding the restriction on the height of the middle part of the first strip portion 51, only referring to the middle part of the first strip portion 51 being located between the front fixed wing 3 and the rear fixed wing 4 in the front-to-back direction of the aircraft); at this time, the front end, middle part and rear end of each first strip portion 51 are respectively provided with the rotor 2, and the rotor 2 in the middle part of the first strip portion 51 is located between the front fixed wing 3 and the rear fixed wing 4. Therefore, no wings are provided under all the rotors 2, so as to avoid the downwash airflow of the rotor 2 being blocked by the wings, thereby improving the efficiency of vertical lift and reducing the vibration of the wings.

[0042] The second strip portion 52 is bent at the portion where it is connected to the first strip portion 51 , so that both ends of the second strip portion 52 are connected to the front fixed wing 3 . At this time, the second strip portion 52 cooperates with the front fixed wing 3 to form a triangular structure, which has high stability and further improves the stability and vibration resistance of the front fixed wing 3 .

[0043] The ends of the two rear fixed wings 4 are both provided with vertical tails 41, which can increase the stability of the cruising process.

[0044] Among them, each rotor 2 has only two blades. During cruising, the rotor 2 can be locked so that the two blades are arranged in the front-to-back direction, thereby reducing the flight resistance generated by the rotor 2 during the forward movement of the aircraft, and further reducing the vibration and power consumption required during cruising.

[0045] The specific implementation methods described above further illustrate the purpose, technical solutions and beneficial effects of the utility model in detail. It should be understood that the above are only specific implementation methods of the utility model and are not intended to limit the scope of protection of the utility model. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the utility model should be included in the scope of protection of the utility model.

Claims

1. An aircraft, comprising a fuselage (1) and a plurality of rotors (2), wherein the plurality of rotors (2) can drive the fuselage (1) to ascend and descend vertically, characterized in that: It also includes tandem wings and propulsion equipment; The tandem wings are arranged on both sides of the fuselage (1), and the propulsion device is arranged on the fuselage (1) or the tandem wings, and can provide thrust to propel the aircraft forward; The tandem wing comprises two front fixed wings (3) and two rear fixed wings (4) respectively fixed to the fuselage (1), and a connecting member (5) is provided between the front fixed wings (3) and the rear fixed wings (4) on the same side of the fuselage (1); The plurality of rotors (2) are arranged on top of the two connecting members (5); Wherein, the connecting member (5) comprises a first strip-shaped portion (51) and a second strip-shaped portion (52); The rotor (2) is connected to the first strip-shaped portion (51), the length direction of the first strip-shaped portion (51) is parallel to the forward direction of the aircraft, and the first strip-shaped portion (51) is connected to the rear fixed wing (4); The second strip-shaped portion (52) is connected between the first strip-shaped portion (51) and the front fixed wing (3).

2. An aircraft according to claim 1, characterized in that: The number of the rotors (2) is 6, and each connecting member (5) is connected to 3 rotors (2).

3. An aircraft according to claim 1, characterized in that: The front end of the first strip-shaped portion (51) extends to the front of the front fixed wing (3), and the rear end of the first strip-shaped portion (51) extends to the rear of the rear fixed wing (4); The front end, middle part and rear end of each first strip-shaped portion (51) are respectively provided with the rotor (2), and the rotor (2) in the middle part of the first strip-shaped portion (51) is located between the front fixed wing (3) and the rear fixed wing (4).

4. An aircraft according to claim 1, characterized in that: The second strip portion (52) cooperates with the front fixed wing (3) to form a triangular structure.

5. An aircraft according to any one of claims 1 to 4, characterized in that: The connecting piece (5) is made of carbon fiber composite material.

6. An aircraft according to any one of claims 1 to 4, characterized in that: The end of the rear fixed wing (4) is provided with a vertical tail (41).

7. An aircraft according to any one of claims 1 to 4, characterized in that: The propulsion device is a tail rotor (6) arranged at the rear end of the fuselage (1).

8. An aircraft according to any one of claims 1 to 4, characterized in that: The rotor (2) has two blades.

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