Tilting rotor wing aircraft

Abstract

The utility model discloses a tilt-rotor aircraft which comprises an aircraft body, a rotor and a rotor, the main wing is connected with the fuselage, and the main wing comprises a fixed section wing and a tilting section wing capable of tilting; the supporting rods are connected with the main wings and are parallel to the length direction of the fuselage; the front rotor assembly is connected with the front end of the supporting rod; the rear rotor wing assembly is connected with the rear end of the supporting rod; and the wing rotor wing assembly is connected with the tilting section wing and can synchronously tilt with the tilting section wing, so that blades of the wing rotor wing assembly face forwards or upwards. By means of the symmetrical layout arrangement, the stress torque of the whole aircraft in the front-back direction and the left-right direction is relatively balanced, meanwhile, the yaw efficiency in the tilting stage is improved, and sufficient lift force can be provided for the aircraft through state switching of the paddles between the fixed wing mode and the multi-rotor mode.

Description

Technical Field

[0001] This utility model relates to the field of aircraft design, specifically a tilt-wing aircraft. Background Technology

[0002] Tiltrotor aircraft can freely switch between fixed-wing and multi-rotor modes by controlling the tilting of the rotors. However, most current tilttrotor aircraft adopt a dual-rotor tilting structure design, which can lead to an imbalance of forces and torques on the airframe during tilting, resulting in unstable attitude of the aircraft. In addition, the fact that only the two rotors can tilt also leads to problems such as low yaw efficiency and instability during vertical take-off and landing. Utility Model Content

[0003] To address the shortcomings of existing technologies, this invention provides a tilt-wing aircraft that, through a symmetrical layout, ensures that the overall torque on the aircraft is relatively balanced in the forward and backward and left and right directions, while improving yaw efficiency during the tilting phase. Furthermore, by switching between fixed-wing and multi-rotor modes, the propellers can provide sufficient lift for the aircraft.

[0004] To achieve the above objectives, this utility model provides the following technical solution:

[0005] A tilt-wing aircraft is provided, comprising:

[0006] body;

[0007] The main wing is connected to the fuselage, and the main wing includes a fixed wing section and a tilting wing section capable of tilting. One end of the fixed wing section is connected to the fuselage, and the other end is connected to the tilting wing section.

[0008] A support rod, which connects to the main wing and is parallel to the length direction of the fuselage;

[0009] A front rotor assembly is connected to the front end of the support rod, and the blades of the front tilt rotor assembly can be tilted to face forward or upward.

[0010] A rear rotor assembly is connected to the rear end of the support rod, and the blades of the rear rotor assembly always face upward.

[0011] The wing rotor assembly is connected to the tilt section wing and can tilt synchronously with the tilt section wing, so that the blades of the wing rotor assembly face forward or upward.

[0012] Preferably, there are two sets of support rods, and the front end and rear end of each support rod are respectively connected to a set of front rotor assemblies and a set of rear rotor assemblies, and each wing rotor assembly is connected to a tilt section wing.

[0013] Preferably, the front end and rear end of the support rod are located in front of and behind the main wing, respectively, and the front rotor assembly and the rear rotor assembly are located in front of and behind the main wing, respectively.

[0014] Preferably, the tilt section wing includes a wingtip.

[0015] Preferably, when the blades of the wing rotor assembly are facing upwards, the surfaces of both the tilt section wing and the fixed section wing are facing upwards.

[0016] Preferably, when the blades of the wing rotor assembly and the blades of the forward tilt rotor assembly are both facing forward, the blades of the rear rotor assembly are locked.

[0017] Preferably, the tilt-wing aircraft further includes a rear rotor blade, which is connected to the rear end of the support rod and always faces downwards from the support rod.

[0018] Preferably, the blades of the rear rotor assembly and the rear rotor blade are coaxial.

[0019] Preferably, the rear blade is a fixed-pitch propeller.

[0020] Preferably, the blades of the front tilt rotor assembly are variable pitch propellers, and / or the blades of the rear rotor assembly are fixed pitch propellers, and / or the blades of the wing rotor assembly are variable pitch propellers.

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

[0022] The tilt-wing aircraft of this invention adopts a symmetrical layout, which makes the torque on the aircraft relatively balanced in the front-to-back and left-to-right directions, making the flight more stable. At the same time, the yaw efficiency during the tilting phase can be improved by tilting the front rotor assembly and the tilting section of the wing. Furthermore, by switching the propeller between fixed-wing mode and multi-rotor mode, sufficient lift can be provided for the aircraft.

[0023] Furthermore, by tilting the wingtips of the main wing, the problems of thrust loss caused by downwash impact and excessive wing drag during cruise are solved. The overall dynamic performance of the flight is improved by using coaxial rear-mounted twin propellers, which ensure flight stability. Attached Figure Description

[0024] Figure 1 This is a top view of the tiltrotor aircraft in the level flight phase of this utility model.

[0025] Figure 2 This is a top view of the tiltwing aircraft in the vertical take-off phase of this utility model.

[0026] Figure 3This is a side view of the tilt-wing aircraft of this utility model. Detailed Implementation

[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0028] Example 1:

[0029] like Figure 1-2 As shown, this embodiment provides a tilt-wing aircraft, which includes:

[0030] Fuselage 1;

[0031] The main wing 2 is connected to the fuselage 1, and both wingtips 23 of the main wing 2 extend in a direction away from the side of the fuselage 1. The main wing 2 includes two fixed wing sections 21 and two tilting wing sections 22. Each fixed wing section 21 is connected to the fuselage 1 at one end and to a tilting wing section 22 at the other end through a wing tilting structure. The tilting wing section 22 can tilt under the drive of the wing tilting structure.

[0032] Support rod 3, which connects to the main wing 2 and is parallel to the length direction of the fuselage 1;

[0033] The front rotor assembly 4 is connected to the front end of the support rod 3, and can tilt so that the blades 41 of the front tilt rotor assembly face forward of the support rod 3 or upward of the support rod 3.

[0034] The rear rotor assembly 5 is connected to the rear end of the support rod 3, and the blades 51 of the rear rotor assembly always face upwards towards the support rod 3.

[0035] The wing rotor assembly 6 is connected to the tilt section wing 22 and can tilt synchronously with the tilt section wing 22, so that the blades 61 of the wing rotor assembly face forward of the main wing 2 or upward of the main wing 2.

[0036] Horizontal tail 7, which is connected to the tail of the fuselage 1;

[0037] And the vertical tail 8, which is connected to the tail of the fuselage 1 and is perpendicular to the plane of the horizontal tail 7.

[0038] In this embodiment, two fixed-section wings 21 and two tilting-section wings 22 are symmetrically arranged on both sides of the fuselage; at the same time, there are two sets of support rods 3, front rotor assembly 4, rear rotor assembly 5, and wing rotor assembly 6, and they are all symmetrically arranged on both sides of the fuselage; wherein, the front end and rear end of each support rod 3 are respectively connected to a set of front rotor assembly 4 and a set of rear rotor assembly 5, and each wing rotor assembly 6 is connected to a tilting-section wing 22.

[0039] Furthermore, the blade 41 of the forward tilt rotor assembly is a three-bladed propeller, and a variable-pitch propeller; and / or, the blade 51 of the rear rotor assembly is a two-bladed propeller, and a fixed-pitch propeller; and / or, the blade 61 of the wing rotor assembly is a three-bladed propeller, and a variable-pitch propeller. Meanwhile, the tilting action of the tilting section wing 22 and the forward rotor assembly 4 can both be achieved through corresponding tilting mechanisms, which are existing technologies and will not be described further.

[0040] like Figure 2 As shown, during the vertical takeoff phase, both tilt-section wings 22 tilt synchronously with the wing rotor assembly 6, causing the blades 61 of the wing rotor assembly to face upwards. Similarly, both forward rotor assemblies 4 tilt upwards, causing the blades 41 of the forward tilt rotor assembly to face upwards. These four blades act as lift propellers, providing the main lift for the aircraft. The blades 51 of the rear rotor assembly provide auxiliary lift, working together to propel the aircraft vertically. This allows the six propellers to provide greater force efficiency, meeting the high lift requirements of the vertical takeoff phase. Furthermore, since the blades 61 of the wing rotor assembly and the blades 41 of the forward tilt rotor assembly can both be variable-pitch propellers, the propeller thrust can be adjusted by changing the propeller tilt angle during vertical takeoff, ensuring stability during the process.

[0041] like Figure 1 As shown, during the level flight phase, both tilt-section wings 22 first tilt to drive the wing rotor assembly 6 to tilt synchronously, so that the blades 61 of the wing rotor assembly are all facing forward. When the speed and lift of the aircraft reach a certain requirement, both front rotor assemblies 4 tilt to make the blades 41 of the front tilt rotor assembly face forward, and lock the blades 51 of the two rear rotor assemblies (so that the blades 51 of the two rear rotor assemblies no longer rotate). At this time, the aircraft is in a four-propeller driven cruise state, and the tilt-section wings 22 and the fixed-section wings 21 can also provide lift for the aircraft, thereby achieving long-term, stable cruise.

[0042] During the landing phase, both forward rotor assemblies 4 first tilt, causing the blades 41 of the forward tilt rotor assembly to face upwards, and the blades 51 of the two rear rotor assemblies unlock (i.e., the blades 51 of the two rear rotor assemblies can rotate again). At this time, the four propellers provide lift to compensate for the decrease in wing lift caused by the reduction in speed during the landing process. Then, both tilt-section wings 22 tilt, causing the wing rotor assembly 6 to tilt synchronously, so that the blades 61 of the wing rotor assembly face upwards, providing sufficient lift for the landing of the aircraft, thereby achieving the purpose of safe landing.

[0043] Therefore, in this tilt-wing aircraft, both the forward rotor assembly 4 and the tilt section wing 22 can tilt, thereby driving the corresponding blades to tilt. This significantly improves the yaw efficiency during the tilting phase and enhances the stability of the aircraft during flight. Furthermore, by switching between fixed-wing and multi-rotor modes, the blades can provide sufficient lift for the aircraft, enabling it to possess both vertical takeoff and landing capabilities and the characteristics of high-speed cruise and long-endurance flight. The tilting propellers are variable-pitch propellers, which adjust the tilt angle to change the thrust and ensure stable flight during the tilting process.

[0044] Furthermore, in this embodiment, the support rod 3, the front rotor assembly 4, the rear rotor assembly 5, and the wing rotor assembly 6 are all symmetrically arranged on both sides of the fuselage, so that the overall force torque of the aircraft is relatively balanced, making the flight more stable. Moreover, when one of the propellers fails, the other propellers can still ensure the stability of the aircraft and ensure flight safety.

[0045] Example 2:

[0046] The only difference between this embodiment and embodiment 1 is that the front end and rear end of the support rod 3 are located in front of and behind the main wing 2, respectively. This allows the front rotor assembly 4 and the rear rotor assembly 5 to be located in front of and behind the main wing 2, thereby further balancing the torque of the aircraft in the forward and backward directions and further increasing the stability of the aircraft during flight.

[0047] Example 3:

[0048] The only difference between this embodiment and embodiment 1 or 2 is that both tilting wing sections 22 include wingtips 23, thereby allowing the wingtips 23 of the main wing 2 to tilt, in order to solve the problems of thrust loss caused by downwash airflow impact and excessive wing drag of the main wing 2 in cruise mode.

[0049] Meanwhile, when the blades 61 of the rotor assembly are all facing upwards, the wing surfaces of the tilt section wing 22 and the fixed section wing 21 are facing the same direction, both facing upwards. Thus, during the cruise phase, both the tilt section wing 22 and the fixed section wing 21 can provide lift for the aircraft.

[0050] Example 4:

[0051] The only difference between this embodiment and any one of embodiments 1-3 is that, Figure 3 As shown, the tiltrotor aircraft also includes a rear rotor blade 9, which is connected to the rear end of the support rod 3 and always faces downwards from the support rod 3. Preferably, in this embodiment, the rotor blades 51 and 9 of the rear rotor assembly are coaxial and rotate synchronously to form a coaxial dual propeller structure. Similarly, the rear rotor blade 9 can also be a three-bladed propeller, and a fixed-pitch propeller. Thus, when the motor power is insufficient or one propeller fails, the overall dynamic performance of the flight can be improved by using a coaxial rear dual propeller, ensuring flight stability.

[0052] In summary, the tilt-wing aircraft of this application adopts a symmetrical layout for the remaining structures except the fuselage, which makes the torque on the aircraft relatively balanced in the forward and backward and left and right directions, resulting in more stable flight. At the same time, the yaw efficiency during the tilting phase can be improved by tilting the forward rotor assembly and the tilting section of the wing. Furthermore, by switching between fixed-wing mode and multi-rotor mode, the rotor blades can provide sufficient lift for the aircraft, giving it both vertical take-off and landing capabilities and the characteristics of high-speed cruise and long-endurance flight.

[0053] Furthermore, by tilting the wingtips of the main wing, the problems of thrust loss caused by downwash impact and excessive wing drag during cruise are solved. The overall dynamic performance of the flight is improved by using coaxial rear-mounted twin propellers, which ensure flight stability.

[0054] It should be noted that the technical features in embodiments 1-4 above can be combined arbitrarily, and the resulting technical solutions all fall within the protection scope of this application. In this document, terms such as "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0055] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A tiltwing aircraft characterized by, The utility model relates to a tilt wing aircraft, comprising: a fuselage; a main wing connected to the fuselage, wherein the main wing comprises a fixed wing and a tiltable wing, the fixed wing is connected to the fuselage at one end and connected to the tiltable wing at the other end; a support rod connected to the main wing and parallel to the length direction of the fuselage; a front rotor assembly connected to the front end of the support rod and capable of tilting the blades of the front tiltable rotor assembly towards the front or upwards; a rear rotor assembly connected to the rear end of the support rod, wherein the blades of the rear rotor assembly are always directed upwards; a wing rotor assembly connected to the tiltable wing and capable of tilting synchronously with the tiltable wing, so that the blades of the wing rotor assembly are directed towards the front or upwards.

2. The tiltwing aircraft of claim 1, wherein, The support rod has two groups, and the front end and the rear end of each support rod are respectively connected to a group of front rotor assemblies and a group of rear rotor assemblies, and each wing rotor assembly is connected to a tiltable wing.

3. The tiltwing aircraft of claim 1, wherein, The front end and the rear end of the support rod are located in front of and behind the main wing respectively, and the front rotor assembly and the rear rotor assembly are located in front of and behind the main wing respectively.

4. The tiltwing aircraft of claim 1, wherein, The tiltable wing comprises a wing tip.

5. The tiltwing aircraft of claim 1, wherein, When the blades of the wing rotor assembly are directed upwards, the airfoils of the tiltable wing and the fixed wing are also directed upwards.

6. The tiltwing aircraft of claim 1, wherein, When the blades of the wing rotor assembly and the front tiltable rotor assembly are directed forwards, the blades of the rear rotor assembly are locked.

7. The tiltwing aircraft of claim 1, wherein, The tilt wing aircraft further comprises a rear blade connected to the rear end of the support rod and always directed downwards.

8. The tiltwing aircraft of claim 7, wherein, The blades of the rear rotor assembly and the rear blade are coaxial.

9. The tiltwing aircraft of claim 7, wherein, The rear blade is a fixed pitch propeller.

10. The tiltwing aircraft of claim 1, wherein, The blades of the front tiltable rotor assembly are variable pitch propellers, and / or the blades of the rear rotor assembly are fixed pitch propellers, and / or the blades of the wing rotor assembly are variable pitch propellers.

Images