Landing gear and electric vertical take-off and landing aircraft having the same

Abstract

A landing gear and an electric vertical take-off and landing aircraft having the same, the landing gear comprising a support crossbar, a connecting rod and a fairing, one end of the connecting rod being connected with the support crossbar, the other end being used for being connected with a fuselage of the aircraft, the fairing being sleeved outside the connecting rod, one end of the fairing being connected with the support crossbar, the other end being used for being connected with the fuselage of the aircraft, a cross section of the fairing along a direction perpendicular to an axis being a wing profile. The landing gear can reduce aerodynamic resistance, improve airflow separation phenomenon of the landing gear and improve aerodynamic performance of the aircraft.

Description

Technical Field

[0001] This utility model relates to the field of aircraft parts technology, and in particular to a low-voltage distribution box and an electric aircraft having the same. Background Technology

[0002] With the development of aviation technology, electric vertical takeoff and landing (EVTOL) aircraft are receiving increasing attention. The landing gear is a crucial component of EVTOL aircraft. During flight, due to aerodynamic effects, the airflow around the landing gear separates. This phenomenon significantly impacts the aircraft's stability and safety. Therefore, improving airflow separation in the landing gear, reducing aerodynamic drag, and enhancing the aircraft's aerodynamic performance have become key considerations in landing gear design. Utility Model Content

[0003] This invention provides a landing gear and an electric vertical takeoff and landing aircraft having the same. The landing gear can reduce aerodynamic drag, improve airflow separation, and enhance the aerodynamic performance of the aircraft.

[0004] This utility model provides a landing gear, including a support crossbar, a connecting rod, and a deflector. One end of the connecting rod is connected to the support crossbar, and the other end is used to connect to the fuselage of the aircraft. The deflector is sleeved on the connecting rod, and one end of the deflector is connected to the support crossbar, and the other end is used to connect to the fuselage of the aircraft. The cross section of the deflector along the direction perpendicular to the axis is an airfoil.

[0005] Furthermore, there are two connecting rods, and each connecting rod is fitted with a flow guide tube. The landing gear also includes a connecting crossbar, the two ends of which are respectively connected to the outer walls of the two flow guide tubes.

[0006] Furthermore, the front end of the connecting crossbar is connected to the rear edge of the guide tube at the front of the landing gear, and the rear end of the connecting crossbar is connected to the front end of the guide tube at the rear of the landing gear. Both ends of the connecting crossbar have connecting concave surfaces that are adapted to the shape of the guide tube.

[0007] Furthermore, from the end closest to the support crossbar to the end furthest from the support crossbar, the guide tube gradually bends inward.

[0008] Furthermore, the relative thickness of the airfoil of the guide tube is 30%-40%.

[0009] Furthermore, the maximum thickness of the airfoil of the guide tube is located at 25%-35% of the chord length.

[0010] Furthermore, the Reynolds number of the airfoil section of the guide tube is 10.5 -10 7 .

[0011] Furthermore, connecting portions are provided at both ends of the guide tube, and the openings of the connecting portions gradually expand from the direction closer to the guide tube to the direction farther away from the guide tube.

[0012] Furthermore, the support crossbar is shaped like a skid.

[0013] This utility model also provides an electric vertical takeoff and landing aircraft, including the aforementioned landing gear.

[0014] In summary, in this invention, a deflector with an airfoil is fitted onto the connecting rod of the landing gear. Compared to the connecting rod itself, the deflector can improve the flow field at the landing gear during flight, reduce aerodynamic drag, improve airflow separation at the landing gear, and enhance the aircraft's start-up performance.

[0015] The above description is merely an overview of the technical solution of this utility model. In order to better understand the technical means of this utility model and to implement it in accordance with the contents of the specification, and to make the above and other objects, features and advantages of this utility model more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 The diagram shown is a schematic representation of the landing gear installed on an electric vertical takeoff and landing aircraft according to an embodiment of the present invention.

[0018] Figure 2 As shown Figure 1 A schematic diagram of the axle side structure of the landing gear.

[0019] Figure 3 As shown Figure 1 A side view of the landing gear structure.

[0020] Figure 4 As shown Figure 1 A schematic diagram of the cross-sectional structure of the mid-mounted landing gear along the axis perpendicular to the deflector. Detailed Implementation

[0021] The specific embodiments of this utility model will now be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely some, not all, of the embodiments of this utility model. Based on the description of this utility model, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this utility model.

[0022] In the description of this utility model, unless otherwise explicitly specified and limited, the terms "set," "install," and "connect," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms according to the specific circumstances.

[0023] The terms “upper,” “lower,” “left,” “right,” “front,” “back,” “top,” “bottom,” “inner,” and “outer,” etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product is in use. They are used only for the convenience of description and simplification, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0024] The terms “first,” “second,” “third,” etc., are used merely to distinguish elements with similar properties, not to indicate or imply relative importance or a specific order.

[0025] The terms “include,” “comprising,” or any other variation thereof are intended to cover non-exclusive inclusion, which includes not only the elements listed but also other elements not expressly listed.

[0026] This invention provides a landing gear and an electric vertical takeoff and landing aircraft having the same. The landing gear can reduce aerodynamic drag, improve airflow separation, and enhance the aerodynamic performance of the aircraft.

[0027] Please refer to Figures 1 to 4 The landing gear provided in this embodiment includes a support crossbar 10, a connecting rod 20, and a deflector 30. One end of the connecting rod 20 is connected to the support crossbar 10, and the other end is used to connect to the aircraft fuselage. The deflector 30 is sleeved on the connecting rod 20, with one end connected to the support crossbar 10 and the other end also used to connect to the aircraft fuselage. The cross-section of the deflector 30 along the direction perpendicular to the axis is an airfoil.

[0028] In this embodiment, a deflector 30 with an airfoil is fitted onto the connecting rod 20 of the landing gear. Compared to the connecting rod 20 itself, the deflector 30 can improve the flow field at the landing gear during flight, reduce aerodynamic drag, improve the airflow separation phenomenon of the landing gear, and enhance the aircraft's start-up performance.

[0029] Furthermore, in this embodiment, there are two connecting rods 20, each of which is fitted with a guide tube 30. Correspondingly, there are also two guide tubes 30. The landing gear also includes a connecting crossbar 40, with both ends of the connecting crossbar 40 connected to the outer walls of the two guide tubes 30, respectively. That is, in this embodiment, the connecting crossbar 40 is no longer connected to the connecting rod 20 itself, but is instead directly connected to the guide tube 30. This ensures the strength of the landing gear while avoiding the need for the connecting crossbar 40 to pass through the guide tube 30, thus reducing the impact of the connecting crossbar 40 and the guide tube 30 on the airflow field.

[0030] Furthermore, the front end of the connecting crossbar 40 is connected to the rear edge of the front deflector 30 of the landing gear, while the rear end of the connecting crossbar 40 is connected to the front edge of the rear deflector 30 of the landing gear. Both ends of the connecting crossbar 40 have connecting concave surfaces 41 that conform to the shape of the deflector 30, facilitating the connection between the connecting crossbar 40 and the deflector 30.

[0031] Furthermore, the front end of the support crossbar 10 is bent upward, that is, the support crossbar 10 is in the shape of a skid, in order to further optimize the airflow field.

[0032] Furthermore, the extension trend of the guide tube 30 in the height direction is the same as that of the connecting rod 20. From the end near the support crossbar 10 to the end away from the support crossbar 10, the guide tube 30 will gradually bend inward, that is, towards the side closer to the fuselage.

[0033] On the airfoil of the guide tube 30, the relative thickness of the airfoil is 30%-40%, with the maximum thickness located at 25%-35% of the chord length. The Reynolds number of this airfoil is 10. 5 -10 7 .

[0034] To improve connection strength, connecting portions 31 are provided at both ends of the guide tube 30 for connection to the support crossbar 10 or the fuselage. The cross-sectional area of ​​the connecting portion 31 increases continuously from the direction closer to the guide tube 30 to the direction farther away from the guide tube 30. That is, the opening of the connecting portion 31 continuously expands.

[0035] Using the landing gear structure provided in this embodiment, a CFD numerical simulation analysis was conducted with the following conditions: H = 1.5 km, Ma = 0.166, a polyhedral mesh, an SST turbulence model, a second-order differential upwind scheme, an angle of attack of 6°, and a half-mode mesh size of 11 million. Compared to a landing gear without the deflector 30, the drag of the landing gear provided by this invention is reduced by 104.13 counts, which greatly optimizes the lift-drag characteristics of the aircraft landing gear.

[0036] In summary, in this utility model, a deflector 30 with an airfoil is fitted onto the connecting rod 20 of the landing gear. Compared with the connecting rod 20 itself, the deflector 30 can improve the flow field at the landing gear during flight, reduce aerodynamic drag, improve the airflow separation phenomenon of the landing gear, and enhance the aircraft's start-up performance.

[0037] This utility model also provides an electric vertical takeoff and landing aircraft, including the aforementioned landing gear. For other technical features of this electric vertical takeoff and landing aircraft, please refer to the prior art, which will not be repeated here.

[0038] The above description is merely a preferred embodiment of the present utility model and is not intended to limit the present utility model in any way. Although the present utility model has been disclosed above with reference to a preferred embodiment, it is not intended to limit the present utility model. Any person skilled in the art can make some modifications or alterations to the above-disclosed technical content to create equivalent embodiments without departing from the scope of the present utility model. Any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present utility model without departing from the scope of the present utility model shall still fall within the scope of the present utility model.

Claims

1. A landing gear, characterized in that: It includes a support crossbar, a connecting rod, and a flow guide tube. One end of the connecting rod is connected to the support crossbar, and the other end is used to connect to the fuselage of the aircraft. The flow guide tube is sleeved on the connecting rod. One end of the flow guide tube is connected to the support crossbar, and the other end is used to connect to the fuselage of the aircraft. The cross section of the flow guide tube along the direction perpendicular to the axis is an airfoil.

2. The landing gear according to claim 1, characterized in that: There are two connecting rods, and each connecting rod is fitted with a flow guide tube. The landing gear also includes a connecting crossbar, the two ends of which are respectively connected to the outer walls of the two flow guide tubes.

3. The landing gear according to claim 2, characterized in that: The front end of the connecting crossbar is connected to the rear edge of the guide tube at the front of the landing gear, and the rear end of the connecting crossbar is connected to the front end of the guide tube at the rear of the landing gear. Both ends of the connecting crossbar have connecting concave surfaces that are adapted to the shape of the guide tube.

4. The landing gear according to claim 1, characterized in that: The guide tube gradually bends inward from the end closest to the support crossbar to the end furthest from the support crossbar.

5. The landing gear according to claim 1, characterized in that: The relative thickness of the airfoil section of the guide tube is 30%-40%.

6. The landing gear according to claim 1, characterized in that: The maximum thickness of the airfoil of the guide tube is located at 25%-35% of the chord length.

7. The landing gear according to claim 1, characterized in that: The Reynolds number of the airfoil section of the deflector is 10. 5 -10 7 .

8. The landing gear according to claim 1, characterized in that: A connecting portion is provided at both ends of the guide tube, and the opening of the connecting portion gradually expands from the direction closer to the guide tube to the direction farther away from the guide tube.

9. The landing gear according to claim 1, characterized in that: The supporting crossbar is shaped like a skid.

10. An electric vertical takeoff and landing aircraft, characterized in that: Includes the landing gear as described in any one of claims 1 to 9.

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