Tandem wing tilt-rotor aircraft and aircraft manufacturing method

Abstract

The present invention provides a tandem-wing tilt-rotor aircraft and an aircraft manufacturing method, which relates to the technical field of aircraft. The tandem-wing tilt-rotor aircraft provided by the present invention comprises: a fuselage, a wing assembly and a rotor assembly; the rotor assembly is mounted on the wing assembly; the wing assembly is rotatably connected to the fuselage, and the wing assembly has a first working state and a second working state; in the first working state, the rotor assembly drives the gas to flow from front to back, and the wing assembly is used to generate lift during the gas flow process; in the second working state, the rotor assembly is used to drive the gas to flow from top to bottom to generate lift. The tandem-wing tilt-rotor aircraft provided by the present invention can adjust the rotor working state by tilting the wing assembly, increase the range of the aircraft center of gravity setting, and reduce the difficulty of aircraft layout and assembly.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a tandem-wing tilt-rotor aircraft and an aircraft manufacturing method. Background Art

[0002] At present, drones are mainly divided into five categories: fixed-wing drones, unmanned helicopters (different from multi-rotors), multi-rotor drones, hybrid-wing drones, and tilt-rotor drones. Among them, tilt-rotor drones are a new type of drone that integrates fixed-wing drones and multi-rotor drones. Tilt-rotor drones have both the vertical take-off and landing and air hovering capabilities of multi-rotor drones, and the high-speed cruising flight capabilities of fixed-wing drones. For example, the drone structure recorded in the patent document (CN107963209B) is more representative. Among them, when the engine or motor is vertical to the body, it is in the vertical state, and when the engine or motor is horizontal to the body, it is in the fixed-wing cruising state. Because the main rotor tilts in different states, it is called a tilt-rotor.

[0003] Twin-rotor tilt-rotor aircraft were put into use earlier, but they have weak balance ability, poor stability, high control difficulty, and high accident rate. In addition, when taking off and landing vertically, the wings will block the airflow generated by the rotors, resulting in a loss of about 10% of lift. Summary of the invention

[0004] The object of the present invention is to provide a tandem-wing tilt-rotor aircraft and an aircraft manufacturing method, which can adjust the working state of the rotor by tilting the wing assembly.

[0005] In a first aspect, the present invention provides a tandem wing tilt-rotor aircraft, comprising: a fuselage, a wing assembly and a rotor assembly;

[0006] The rotor assembly is mounted on the wing assembly;

[0007] The wing assembly is rotatably connected to the fuselage, and the wing assembly has a first working state and a second working state;

[0008] In the first working state, the rotor assembly drives the gas to flow from front to back, and the wing assembly is used to generate lift during the gas flow;

[0009] In the second working state, the rotor assembly is used to drive gas to flow from top to bottom to generate lift.

[0010] In combination with the first aspect, the present invention provides a first possible implementation of the first aspect, wherein the wing assembly comprises: a front wing and a rear wing;

[0011] The front wing and the rear wing are arranged at intervals from front to rear along the fuselage, and the front wing and the rear wing are respectively rotatably connected to the fuselage.

[0012] In combination with the first possible implementation of the first aspect, the present invention provides a second possible implementation of the first aspect, wherein, in the first working state, there is a height difference between the position height of the front wing and the position height of the rear wing.

[0013] In combination with the first possible implementation manner of the first aspect, the present invention provides a third possible implementation manner of the first aspect, wherein the front wing and the rear wing are transmission connected via a linkage.

[0014] In combination with the third possible implementation manner of the first aspect, the present invention provides a fourth possible implementation manner of the first aspect, wherein the linkage member includes: a first connecting rod and a second connecting rod;

[0015] The fuselage is located between the first link and the second link, one end of the first link and one end of the second link are respectively hinged to the front wing, and the other end of the first link and the other end of the second link are respectively hinged to the rear wing.

[0016] In combination with the fourth possible implementation of the first aspect, the present invention provides a fifth possible implementation of the first aspect, wherein projections of the first connecting rod and the second connecting rod on the horizontal plane have an angle.

[0017] In combination with the first possible implementation manner of the first aspect, the present invention provides a sixth possible implementation manner of the first aspect, wherein the rotor assembly includes: a first rotor and a second rotor;

[0018] The first rotor is mounted on the front wing, and the first rotor is used to drive airflow to flow along the unfolded surface of the front wing;

[0019] The second rotor is mounted on the rear wing, and the second rotor is used to drive airflow to flow along the unfolded surface of the rear wing.

[0020] In combination with the first possible implementation manner of the first aspect, the present invention provides a seventh possible implementation manner of the first aspect, wherein the rear wing is equipped with a vertical tail, and the vertical tail is equipped with a rudder.

[0021] In combination with the first aspect, the present invention provides an eighth possible implementation manner of the first aspect, wherein the wing assembly is installed with a footrest assembly;

[0022] In the second working state, the tripod assembly is located at the bottom of the wing assembly.

[0023] In combination with the first aspect, the present invention provides a ninth possible implementation manner of the first aspect, wherein a control rudder is installed on the wing assembly.

[0024] In combination with the first aspect, the present invention provides a tenth possible implementation of the first aspect, wherein an airspeed meter is installed at the front end of the fuselage.

[0025] In a second aspect, the present invention provides an aircraft manufacturing method, comprising the following steps:

[0026] Installing the rotor assembly to the wing assembly;

[0027] The wing assembly is rotatably connected to the fuselage, and the wing assembly has a first working state and a second working state;

[0028] In the first working state, the wing assembly generates lift when air flows from front to rear;

[0029] In the second working state, the rotor assembly is used to drive airflow and generate lift.

[0030] The embodiments of the present invention bring the following beneficial effects: the rotor assembly is installed on the wing assembly, the wing assembly is rotatably connected to the fuselage, and the wing assembly has a first working state and a second working state, and the wing assembly rotates relative to the fuselage to achieve switching between the first working state and the second working state. In the first working state, the rotor assembly drives the gas to flow from front to back, and lift is generated during the gas flow through the wing assembly; in the second working state, the rotor assembly drives the gas to flow from top to bottom to generate lift. The airflow direction of the rotor assembly can be adjusted by tilting the wing assembly relative to the fuselage, thereby achieving switching between vertical take-off and landing and gliding flight of the aircraft.

[0031] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the related technologies, the drawings required for use in the specific embodiments or the related technical descriptions will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0033] Figure 1 A schematic diagram of a tandem-wing tilt-rotor aircraft provided by an embodiment of the present invention;

[0034] Figure 2A right view of a tandem wing tilt-rotor aircraft provided by an embodiment of the present invention Figure 1 ;

[0035] Figure 3 A schematic diagram of a tandem-wing tilt-rotor aircraft in a vertical take-off and landing state provided by an embodiment of the present invention;

[0036] Figure 4 A top view of a tandem-wing tilt-rotor aircraft in a vertical take-off and landing state provided by an embodiment of the present invention;

[0037] Figure 5 A schematic diagram of a tandem-wing tilt-rotor aircraft in a gliding flight state provided by an embodiment of the present invention;

[0038] Figure 6 A right view of a tandem wing tilt-rotor aircraft provided by an embodiment of the present invention Figure 2 ;

[0039] Figure 7 A front view of a tandem-wing tilt-rotor aircraft in a gliding flight state provided by an embodiment of the present invention;

[0040] Figure 8 A front view of a tandem-wing tilt-rotor aircraft in a vertical take-off and landing state provided by an embodiment of the present invention.

[0041] Icons: 001 - fuselage; 101 - airspeed meter; 102 - equipment cover; 103 - battery cover; 002 - wing assembly; 210 - front wing; 220 - rear wing; 230 - linkage; 231 - first link; 232 - second link; 003 - rotor assembly; 310 - first rotor; 320 - second rotor; 004 - tripod assembly; 410 - front tripod; 420 - rear tripod; 005 - control rudder; 006 - vertical tail; 601 - rudder. DETAILED DESCRIPTION

[0042] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. 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.

[0043] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance. Physical quantities in formulas, if not separately marked, should be understood as basic quantities of the base units of the International System of Units, or derived quantities derived from the basic quantities through mathematical operations such as multiplication, division, differentiation or integration.

[0044] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0045] Embodiment 1

[0046] like Figure 1 , Figure 2 and Figure 3 As shown, the tandem-wing tilt-rotor aircraft provided by an embodiment of the present invention includes: a fuselage 001, a wing assembly 002 and a rotor assembly 003; the rotor assembly 003 is installed on the wing assembly 002; the wing assembly 002 is rotatably connected to the fuselage 001, and the wing assembly 002 has a first working state and a second working state.

[0047] In the first working state, the rotor assembly 003 drives the gas to flow from front to back, the airflow generates forward thrust, and pushes the aircraft to fly forward. The wing assembly 002 obtains lift from the relative airflow generated during the movement. At the same time, the rotor airflow passing over the wing can also generate some lift.

[0048] In the second working state, the rotor assembly 003 is used to drive the gas to flow from top to bottom to generate lift, and the airflow generates vertical thrust, which is used to maintain the state of the fuselage.

[0049] Specifically, the rotation axis of the wing assembly 002 extends in the horizontal direction. When the wing assembly 002 rotates relative to the fuselage 001, the angle between the deployment plane of the wing assembly 002 and the horizontal plane changes, and the position of the rotor assembly 003 installed on the wing assembly 002 changes. In the first working state, the axis of the rotor assembly 003 approaches the horizontal, the rotor assembly 003 drives the gas to flow from front to back, the airflow generates forward thrust, pushes the aircraft to fly forward, and the wing assembly 002 generates lift through the relative airflow generated during the movement of the wing and the thrust airflow of the rotor passing over the wing. In the second working state, the deployment plane of the wing assembly 002 approaches the vertical plane, the rotor assembly 003 drives the gas to flow from top to bottom, the airflow generates vertical thrust, and the airflow flows along the deployment surface of the wing assembly 002, thereby reducing the wing assembly 002 from blocking the airflow generated by the rotor assembly 003. In the first working state, the relative airflow generated during the movement of the wing and the thrust airflow of the rotor passing over the wing can cause the wing assembly 002 to generate lift, thereby achieving gliding takeoff; in the second working state, the rotor assembly 003 can drive the airflow to generate vertical thrust, thereby achieving vertical takeoff and landing.

[0050] In the embodiment of the present invention, the wing assembly 002 includes: a front wing 210 and a rear wing 220; the front wing 210 and the rear wing 220 are spaced apart from front to rear along the fuselage 001, and the front wing 210 and the rear wing 220 are respectively rotatably connected to the fuselage 001.

[0051] Specifically, there are two front wings 210 and two rear wings 220, respectively. The two front wings 210 are mounted on both sides of the fuselage 001 in a one-to-one correspondence, and the two rear wings 220 are mounted on both sides of the fuselage 001 in a one-to-one correspondence. Moreover, the two front wings 210 are symmetrical with respect to the middle longitudinal section of the fuselage 001, and the two rear wings 220 are symmetrical with respect to the middle longitudinal section of the fuselage 001. The two front wings 210 and the two rear wings 220 are respectively mounted with rotor assemblies 003. In the second working state, a quadrotor aircraft can be formed, thereby reducing the difficulty of flight control and improving flight stability.

[0052] In the first working state, there is a height difference between the position height of the front wing 210 and the position height of the rear wing 220 .

[0053] like Figure 1 , Figure 2 , Figure 5 and Figure 7As shown, the rotation axis position of the front wing 210 is lower than the rotation axis position of the rear wing 220, or the rotation axis position of the front wing 210 is higher than the rotation axis position of the rear wing 220. In the first working state, the deployment plane of the front wing 210 and the deployment plane of the rear wing 220 are both close to horizontal, and the position height of the front wing 210 is staggered by a certain distance from the position height of the rear wing 220, thereby preventing the airflow flowing backward through the front wing 210 from interfering with the rear wing 220, and preventing the rotor assembly 003 installed on the front wing 210 from interfering with the rotor assembly 003 installed on the rear wing 220.

[0054] In some embodiments, the front wing 210 and the rear wing 220 are respectively rotatably connected to the fuselage 001, and the front wing 210 and the rear wing 220 are transmission-connected to two rotating drive members one by one, and the front wing 210 and the rear wing 220 are respectively driven to tilt, thereby improving the flexibility of aircraft control.

[0055] In this embodiment, the front wing 210 and the rear wing 220 are transmission connected via a linkage 230 .

[0056] Specifically, the linkage 230 includes a gear assembly or a connecting rod assembly. The front wing 210 and the rear wing 220 can be moved synchronously through the transmission of the linkage 230. The front wing 210 or the rear wing 220 can be driven by a rotary drive member to tilt the front wing 210 or the rear wing 220 synchronously.

[0057] like Figure 4 As shown, the linkage 230 includes: a first link 231 and a second link 232; the fuselage 001 is located between the first link 231 and the second link 232, one end of the first link 231 and one end of the second link 232 are respectively hinged to the front wing 210, and the other end of the first link 231 and the other end of the second link 232 are respectively hinged to the rear wing 220.

[0058] Specifically, the front wings 210 on the left and right sides of the fuselage 001 are independent of each other. The front wing 210 and the rear wing 220 on the right side of the fuselage 001 tilt synchronously under the transmission action of the first connecting rod 231, and the front wing 210 and the rear wing 220 on the left side of the fuselage tilt synchronously under the transmission action of the second connecting rod 232.

[0059] Furthermore, projections of the first connecting rod 231 and the second connecting rod 232 on the horizontal plane have an angle.

[0060] Specifically, from front to rear, the distance between the first link 231 and the second link 232 increases or decreases, and the first link 231 and the second link 232 have the same length, thereby forming an isosceles trapezoidal distribution. While ensuring the flexible tilting of the front wing 210 and the rear wing 220, the torsion and displacement of the front wing 210 and the rear wing 220 in other directions can be restricted, thereby improving the stability of the aircraft structure.

[0061] like Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 and Figure 7 As shown, rotor assembly 003 includes: a first rotor 310 and a second rotor 320; the first rotor 310 is installed on the front wing 210, and the first rotor 310 is used to drive the airflow to flow along the unfolded surface of the front wing 210; the second rotor 320 is installed on the rear wing 220, and the second rotor 320 is used to drive the airflow to flow along the unfolded surface of the rear wing 220.

[0062] Specifically, two first rotors 310 are mounted one-to-one on the front wings 210 on both sides of the fuselage 001, and two second rotors 320 are mounted one-to-one on the rear wings 220 on both sides of the fuselage 001. The axis of the first rotor 310 is located on the deployment plane of the front wing 210, or the axis of the first rotor 310 forms an angle less than 30 degrees with the deployment plane of the front wing 210, so as to avoid the front wing 210 blocking the airflow generated by the first rotor 310. Similarly, the axis of the second rotor 320 is located on the deployment plane of the rear wing 220, or the axis of the second rotor 320 forms an angle less than 30 degrees with the deployment plane of the rear wing 220, so as to avoid the rear wing 220 blocking the airflow generated by the second rotor 320.

[0063] It should be noted that the axes of the first rotors 310 on the left and right sides of the fuselage 001 have an angle, and the axes of the second rotors 320 on the left and right sides of the fuselage 001 have an angle, and the rotors on the left and right sides are inclined outward or inward, thereby improving the wind resistance of the multi-rotor in the left and right directions.

[0064] like Figure 1 , Figure 3 , Figure 5 and Figure 6 As shown, the rear wing 220 is equipped with a vertical tail 006, and the vertical tail 006 is equipped with a rudder 601.

[0065] Specifically, the two vertical tails 006 are connected to the rear wing 220. When the wing assembly 002 is in the first working state, the vertical tail 006 is located below the rear wing 220. The rudder 601 is driven by the steering gear to swing, thereby adjusting the direction of gas flow and further realizing the control of the direction of travel of the aircraft.

[0066] like Figure 1 , Figure 2 , Figure 3 , Figure 5 , Figure 6 and Figure 8 As shown, the wing assembly 002 is installed with a tripod assembly 004; in the second working state, the tripod assembly 004 is located at the bottom of the wing assembly 002.

[0067] Specifically, the tripod assembly 004 includes: a front tripod 410 and a rear tripod 420, the front tripod 410 is connected to the front wing 210, and the rear tripod 420 is connected to the rear wing 220. When the wing assembly 002 is in the second working state, the two front tripods 410 and the two rear tripods 420 support each other so as to support the ground when the aircraft takes off and lands vertically. In the left view or the right view, the distance between the front tripod 410 and the rear tripod 420 increases from top to bottom, thereby forming an eight-shaped support state, thereby reducing the wind resistance of the tripod assembly 004 and ensuring the stability of the aircraft landing.

[0068] like Figure 1 and Figure 8 As shown, a control rudder 005 is installed on the wing assembly 002. In this embodiment, the control rudder 005 is installed on the front wing 210 and the rear wing 220 respectively. The control rudder 005 includes: an aileron and an elevator, the aileron is installed on the front wing 210, and the elevator is installed on the rear wing 220. The aileron and the elevator are driven separately by the driving member, and the roll and pitch moments of the wing assembly 002 can be adjusted by adjusting the control rudder 005, thereby realizing the adjustment of the flight attitude.

[0069] like Figure 1 As shown, an airspeed meter 101 is installed at the front end of the fuselage 001, and the flight speed of the aircraft can be detected by the airspeed meter 101. In addition, the fuselage 001 is provided with an equipment compartment and a battery compartment, and an equipment compartment cover 102 is detachably covered on the equipment compartment, and a battery compartment cover 103 is detachably covered on the battery compartment, and the aircraft can be maintained by opening the equipment compartment cover 102 and the battery compartment cover 103.

[0070] Embodiment 2

[0071] like Figure 1 , Figure 2 and Figure 3 As shown, the aircraft manufacturing method provided by the embodiment of the present invention includes the following steps:

[0072] Install the rotor assembly 003 on the wing assembly 002;

[0073] The wing assembly 002 is rotatably connected to the fuselage 001, and the wing assembly 002 has a first working state and a second working state;

[0074] In the first working state, the relative airflow generated during the movement of the wing assembly 002 generates lift, and at the same time, the airflow generated by the rotor assembly 003 sweeping over the wing assembly 002 can also generate a part of lift;

[0075] In the second working state, the rotor assembly 003 is used to drive the airflow to generate vertical thrust, and the thrust is used to maintain the state of the fuselage.

[0076] The aircraft manufacturing method provided in this embodiment is used to produce the tandem-wing tilt-rotor aircraft provided in Embodiment 1, thereby having the beneficial effects possessed by the tandem-wing tilt-rotor aircraft, and therefore will not be described in detail here.

[0077] The tandem-wing tilt-rotor aircraft and the aircraft manufacturing method provided in this embodiment have the following beneficial effects:

[0078] 1. The airflow direction of the rotor assembly 003 can be changed through the wing assembly 002, thereby realizing switching between vertical take-off and landing and gliding flight, which is easy to implement and the state switching is flexible.

[0079] 2. The front wing 210 and the rear wing 220 are designed in series and staggered in height, which can effectively avoid the interference of the airflow of the front wing 210 on the rear wing 220. The front wing 210 and the rear wing 220 can both be used as lift wings, which greatly shortens the wingspan of the UAV with the same load level, increases the range of the aircraft's center of gravity setting, and reduces the difficulty of aircraft layout and assembly.

[0080] 3. The tripod assembly 004 and the wing assembly 002 can be integrated into one, with a compact structure. In the vertical take-off and landing state, the front tripod 410 and the rear tripod 420 are staggered, which reduces the wind resistance generated by the tripod assembly 004 and ensures the stable landing of the aircraft.

[0081] 4. The front wing 210 and the rear wing 220 can be tilted synchronously through the linkage 230, which facilitates flight control.

[0082] 5. The first connecting rod 231 and the second connecting rod 232 form an isosceles trapezoidal distribution, which can not only ensure the flexible tilting of the wing assembly 002, but also limit the torsion and displacement of the front wing 210 and the rear wing 220 in other directions, thereby improving the stability of the aircraft.

[0083] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A tandem-wing tilt-rotor aircraft, characterized in that: include: A fuselage (001), a wing assembly (002) and a rotor assembly (003); The rotor assembly (003) is mounted on the wing assembly (002); The wing assembly (002) is rotatably connected to the fuselage (001), and the wing assembly (002) has a first working state and a second working state; In the first working state, the rotor assembly (003) drives the gas to flow from front to back, and the wing assembly (002) is used to generate lift during the gas flow process; In the second working state, the rotor assembly (003) is used to drive gas to flow from top to bottom to generate lift; The wing assembly (002) comprises: a front wing (210) and a rear wing (220); The front wing (210) and the rear wing (220) are arranged at intervals from front to rear along the fuselage (001), and the front wing (210) and the rear wing (220) are respectively rotatably connected to the fuselage (001); The rotation axis position of the front wing (210) is lower than the rotation axis position of the rear wing (220), so as to prevent the airflow flowing backward through the front wing (210) from interfering with the rear wing (220); The front wing (210) and the rear wing (220) are connected in transmission via a linkage (230), and the linkage (230) comprises: a first link (231) and a second link (232); the fuselage (001) is located between the first link (231) and the second link (232), one end of the first link (231) and one end of the second link (232) are respectively hinged to the front wing (210), and the other end of the first link (231) and the other end of the second link (232) are respectively hinged to the rear wing (220); The projections of the first connecting rod (231) and the second connecting rod (232) on the horizontal plane have an included angle, and the first connecting rod (231) and the second connecting rod (232) have the same length; The wing assembly (002) is equipped with a tripod assembly (004), and the tripod assembly (004) includes: a front tripod (410) and a rear tripod (420), the front tripod (410) is connected to the front wing (210), and the rear tripod (420) is connected to the rear wing (220); In the second working state, the front leg (410) and the rear leg (420) are both located at the bottom of the wing assembly (002), and the distance between the front leg (410) and the rear leg (420) increases from top to bottom.

2. The tandem-wing tilt-rotor aircraft according to claim 1, characterized in that: The rotor assembly (003) comprises: a first rotor (310) and a second rotor (320); The first rotor (310) is installed on the front wing (210), and the first rotor (310) is used to drive airflow to flow along the unfolded surface of the front wing (210); The second rotor (320) is installed on the rear wing (220), and the second rotor (320) is used to drive airflow to flow along the unfolded surface of the rear wing (220).

3. The tandem-wing tilt-rotor aircraft according to claim 1, characterized in that: The rear wing (220) is equipped with a vertical tail (006), and a rudder (601) is installed on the vertical tail (006).

4. The tandem-wing tilt-rotor aircraft according to claim 1, characterized in that: A control rudder (005) is installed on the wing assembly (002).

5. The tandem-wing tilt-rotor aircraft according to claim 1, characterized in that: An airspeed meter (101) is installed at the front end of the fuselage (001).

6. A method for manufacturing an aircraft, characterized in that: The aircraft manufacturing method is applied to the tandem-wing tilt-rotor aircraft according to any one of claims 1 to 5, and The following steps are involved: Installing the rotor assembly (003) on the wing assembly (002); The wing assembly (002) is rotatably connected to the fuselage (001), and the wing assembly (002) has a first working state and a second working state; In the first working state, the wing assembly (002) generates lift when the airflow flows from front to back; In the second working state, the rotor assembly (003) is used to drive airflow and generate lift; The wing assembly (002) comprises: a front wing (210) and a rear wing (220); the front wing (210) and the rear wing (220) are arranged spaced apart from front to rear along the fuselage (001), and the front wing (210) and the rear wing (220) are respectively rotatably connected to the fuselage (001); A tripod assembly (004) is installed on the wing assembly (002), wherein the tripod assembly (004) comprises: a front tripod (410) and a rear tripod (420), wherein the front tripod (410) is connected to the front wing (210), and the rear tripod (420) is connected to the rear wing (220); In the second working state, the front leg (410) and the rear leg (420) are both located at the bottom of the wing assembly (002).

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