An eVTOL aircraft elevator linkage link structure

Abstract

The utility model relates to electric airplane technical field especially relates to a kind of eVTOL airplane elevator linkage connecting rod structure, including connecting rod body, connecting rod body is located after the both ends of connecting rod body through the tail push region of flat tail two sides of tail push region of flat tail, the both ends of connecting rod body are stuck by joint and plug cover, the both ends of connecting rod body are clamped using fastener, the joint of the both ends of connecting rod body is connected with two elevators respectively, so that two elevators are connected together, form an integral structure, when rudder control one elevator deflection, another elevator can be driven to move, realize the function of one rudder control two elevators, the utility model has the characteristics of low cost, control precision is high, easy to install, high stiffness.

Description

Technical Field

[0001] This utility model relates to the field of electric aircraft technology, and in particular to an elevator linkage structure for an eVTOL aircraft. Background Technology

[0002] eVTOL (Electric Vertical Takeoff and Landing) aircraft can take off and land vertically, eliminating the need for long runways and enabling takeoff and landing operations within limited spaces. This significantly improves the flexibility and accessibility of air transport, making them suitable for scenarios such as urban air mobility. Powered by electricity, they produce no pollutants such as carbon dioxide and nitrogen oxides during operation, meeting the zero-carbon vision and environmental requirements. They also significantly reduce noise, enhancing passenger experience and comfort. The overall configuration allows for various innovative aerodynamic-propulsion integrated designs and unconventional aerodynamic layouts, including multi-rotor, compound, and vector propulsion types, to meet diverse travel needs. Their structure is relatively simple, maintenance requirements are low, and electricity costs are typically lower than fuel costs, suggesting the potential for lower operating costs after large-scale commercial operation.

[0003] During the fixed-wing flight phase, the pitch attitude of an eVTOL aircraft is controlled by the elevators. Currently, the deflection of the elevators is controlled by servos. Since the cost of a single servo is high, the cost of a single servo for controlling the elevators of a 2-ton eVTOL aircraft exceeds 40,000 yuan. If multiple elevators can be deflected by a single servo, the number of servos can be effectively reduced, thereby reducing costs and the complexity of power supply lines to the servos and the difficulty of controlling the servos by the flight control computer.

[0004] Chinese utility model patent application number 202322189871.X discloses "a control surface linkage structure for an unmanned aerial vehicle," comprising a main body and control surface one and control surface two located on one side of the main body. The bottom ends of control surface one and control surface two are each provided with symmetrically arranged control surface connecting parts one. The bottom end of the main body is provided with several control surface connecting parts two corresponding to the positions of the control surface connecting parts one. The control surface connecting parts two are connected to the control surface connecting parts one via a rotating shaft. Beneficial effects: The rotation of the power component drives a linkage assembly consisting of a ball joint fixing part, a ball joint, a connecting rod, and a self-locking nut, causing the control surface to rotate around the control surface rotation axis by a certain angle. The control surface linkage parts one and two are assembled into a control surface linkage mechanism. Control surface linkage parts one and two are respectively installed on control surface one and control surface two. The rotation of control surface one simultaneously drives the rotation of control surface two, solving the problem of requiring two power systems for two control surfaces and reducing enterprise production costs.

[0005] Chinese utility model patent application number 202322189871.X, entitled "A Control Surface Linkage Structure for an Unmanned Aerial Vehicle," uses a linkage rod and a linkage groove to control the rotation of one control surface, causing the linkage rod to slide within the linkage groove, thereby controlling the deflection of the other control surface. The connection is a clearance fit. During use, the control surfaces are subjected to airflow and significant vibration, which may cause wear on the linkage rod and linkage groove, affecting their lifespan. Furthermore, to ensure relative movement between the linkage rod and linkage groove, a clearance fit is used. This results in a large amount of play in the other control surface when one control surface deflects, causing inconsistent deflection angles and affecting the control of the aircraft. Utility Model Content

[0006] The purpose of this invention is to overcome the shortcomings of the existing technology and provide an eVTOL aircraft elevator linkage structure, which has the characteristics of low cost, high control precision, convenient installation and high rigidity.

[0007] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0008] An eVTOL aircraft elevator linkage structure includes a linkage body. After passing through the tail thrust area of ​​the horizontal stabilizer, the two ends of the linkage body are located on both sides of the tail thrust area. Both ends of the linkage body are secured by connectors and caps, and fasteners are used to clamp the two ends of the linkage body. The connectors at both ends of the linkage body are connected to two elevators respectively, so that the two elevators are connected together to form an integral structure. When a servo controls the deflection of one elevator, it can drive the movement of the other elevator, realizing the function of controlling two elevators with one servo.

[0009] Preferably, the connecting rod body includes a middle rod, an end, and an inner hole. The middle rod is a round tube, and the axis of the middle rod is consistent with the rotation axis of the elevator. The end has two mounting holes for use with fasteners. Both mounting holes are round holes, and the inner hole is the inner hole of the round tube itself.

[0010] Furthermore, the joint includes a rib-skin connection edge, a weight-reducing hole, a slot, a through hole, a fastener groove, and a beam connection edge. The rib-skin connection edge is connected to the elevator. The weight-reducing hole is used to reduce the weight of the joint. The slot is used to install the end of the connecting rod body. The height of the through hole is larger than the size of the end. There are two fastener grooves, one of which is a round hole and the other is an oblong hole.

[0011] Furthermore, the elevator includes a skin, ribs, and beams, the beams being connected to the beam connection edge of the joint by fasteners, and the skin, ribs, and ribs of the joint being connected to the skin connection edge by fasteners.

[0012] Furthermore, the plug has two connecting holes for use with fasteners, one of which is a round hole and the other is an oblong hole. The end mating area between the plug and the connecting rod body is a plane, and the plug has a groove.

[0013] Furthermore, a connecting rod opening is provided at the rear of the flat tail, and the size of the connecting rod opening is larger than the size of the end.

[0014] Furthermore, the cross-sections of the end, the slot, and the plug are all trapezoidal.

[0015] Furthermore, the fasteners include bolts and nuts used in conjunction with the bolts.

[0016] The beneficial effects of this utility model are:

[0017] The linkage structure of this utility model passes through the tail thruster of the horizontal tail and connects the two elevators together. One servo motor controls one of the elevators to achieve the linkage of the other elevator, saving one servo motor and making this application have the advantage of low cost.

[0018] The connector and plug secure the connecting rod body within the connector's slot. The connector connects to the elevator's skin, ribs, and beams via ribs and skin connecting edges and beam connecting edges, ensuring continuous force transmission between the two elevators. It possesses good rigidity and strength. The connector's slot and the end of the connecting rod body are fitted with three planes, and both ends are inclined planes, exhibiting a tightening characteristic. The fit will not produce play due to manufacturing tolerances, ensuring direct linkage between the two elevators and making the two control surfaces move in unison without control lag. This gives this application the advantage of high control precision.

[0019] The plug is installed from top to bottom. After placing the end of the connecting rod body into the slot of the connector, the plug only needs to be installed into the slot, installed and tightened with fasteners to complete the installation. The open operating space makes this application easy to install.

[0020] The linkage body is made of stainless steel, which has high shear and bending modulus. When the elevator is under stress, the deformation of the linkage body is small, which can ensure that the deformation difference between the two elevators is small, which is beneficial to the pitch control of the eVTOL aircraft by the elevator. Attached Figure Description

[0021] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is an isometric view of an eVTOL aircraft linkage structure installed on a horizontal stabilizer according to this utility model.

[0023] Figure 2 This is an exploded view of the linkage structure, horizontal stabilizer, and elevator of an eVTOL aircraft according to this utility model.

[0024] Figure 3 This is an isometric view of an eVTOL aircraft linkage structure according to the present invention.

[0025] Figure 4 This is an exploded view of an eVTOL aircraft linkage structure according to this utility model;

[0026] Figure 5 This is an isometric view of the mating point between the horizontal tail and the linkage structure of this utility model;

[0027] Figure 6 This is an isometric view of the connection between the elevator and the linkage structure of this utility model;

[0028] Figure 7 This is a forward isometric view of the connector of this utility model;

[0029] Figure 8 This is a back-view isometric view of the connector of this utility model;

[0030] Figure 9 This is an isometric view of the connecting rod body of this utility model;

[0031] Figure 10 This is a cross-sectional view of the linkage structure of this utility model connected at the fastener.

[0032] The markings in the diagram are as follows: 11. Connecting rod body; 111. Center rod; 112. End; 113. Inner hole; 12. Joint; 121. Rib and skin connection edge; 122. Lightening hole; 123. Slot; 124. Through hole; 125. Fastener groove; 126. Beam connection edge; 13. Plug; 14. Fastener; 141. Bolt; 142. Nut; 2. Elevator; 21. Skin; 22. Rib; 23. Beam; 3. Tail rail; 31. Connecting rod opening; 4. Clearance. Detailed Implementation

[0033] 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, not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0034] It should be understood that, when used in this specification and the appended claims, the terms "comprising" and "including" indicate the presence of the described features, integrals, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or collections thereof.

[0035] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the scope of the invention. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0036] It should also be further understood that the term "and / or" as used in this specification and the appended claims refers to any combination of one or more of the associated listed items and all possible combinations, and includes such combinations.

[0037] Example 1

[0038] like Figure 1 and Figure 2 As shown, elevator 2 is located at the rear of horizontal stabilizer 3 and is connected to horizontal stabilizer 3 via a suspension joint. In this example, a tail thrust motor is installed at the rear of horizontal stabilizer 3 to provide thrust for the eVTOL aircraft. Elevator 2 is divided into inner and outer parts by the tail thrust. To control the deflection of elevator 2, a servo motor is required. In this example, the linkage structure passes through the tail thrust of horizontal stabilizer 3 and connects the inner and outer elevators 2 together to form an integral structure. In this way, when the servo motor controls the deflection of one elevator 2, it can drive the other elevator 2 to move synchronously, realizing the function of one servo motor controlling two elevators 2.

[0039] like Figure 1-10 As shown, the present invention provides an eVTOL aircraft elevator linkage structure, including a linkage body 11. After passing through the tail thrust area of ​​the horizontal stabilizer 3, the two ends of the linkage body 11 are respectively located on both sides of the tail thrust area of ​​the horizontal stabilizer 3. Both ends of the linkage body 11 are locked by connectors 12 and plugs 13. Fasteners 14 are used to clamp the two ends of the linkage body 11. The connectors 12 at both ends of the linkage body 11 are respectively connected to two elevators 2, so that the two elevators 2 are connected together to form an integral structure. When the servo controls the deflection of one elevator 2, it can drive the other elevator 2 to move, realizing the function of one servo controlling two elevators 2.

[0040] like Figure 9As shown, the connecting rod body 11 includes a middle rod 111, an end 112, and an inner hole 113. The middle rod 111 is a round tube, and the axis of the middle rod 111 is consistent with the rotation axis of the elevator 2. The end 112 is provided with two mounting holes for use with fasteners 14. Both mounting holes are round holes, and the inner hole 113 is the inner hole of the round tube itself.

[0041] In this embodiment, the connecting rod body 11 is made of steel, which has a high elastic modulus and shear modulus. When subjected to bending moment and torque transmitted by the elevator 2, the deformation is small. The material used in this example is 15-5PH stainless steel, and the preferred heat treatment state is H900. In order to save processing costs, this example uses round tubes for processing.

[0042] The middle rod 111 is machined by turning, and the end 112 is machined by machining. The middle rod 111 is circular, and the axis of the middle rod 111 is consistent with the rotation axis of the elevator 2. In this way, when the elevator 2 rotates, the motion envelope of the middle rod 111 is its own shape, which can effectively reduce the size of the connecting rod opening 31 on the horizontal tail 3.

[0043] The two fastener mounting holes 14 on the end 112 are both round holes. The gap between the fastener 14 and the hole is minimized to prevent movement misalignment. The assembly tolerance is absorbed by the plug 13 and the elongated hole on the connector 12.

[0044] like Figure 7 and 8 As shown, the connector 12 includes a rib and skin connecting edge 121, a weight-reducing hole 122, a slot 123, a through hole 124, a fastener groove 125, and a beam connecting edge 126. The rib and skin connecting edge 121 is connected to the elevator 2. The weight-reducing hole 122 is used to reduce the weight of the connector 12. The slot 123 is used to install the end 112 of the connecting rod body 11. The height of the through hole 124 is larger than the size of the end 112. There are two fastener grooves 125, one of which is a round hole and the other is an oblong hole.

[0045] The connector 12 is a machined aluminum alloy part, preferably made of 7050, and preferably heat treated in T7451 condition. The rib and skin connecting edge 121 is connected to the rib 22 and skin 21 of the elevator 2. The slot 123 holds the end 112 of the connecting rod body 11 inside. The end 112 of the connecting rod body 11 is pressed tightly by the plug 13 and the fastener 14 so that it will not rotate relative to the slot 123 when subjected to torsional load, thus eliminating play. When rotating, it rotates together with the elevator 2.

[0046] The through hole 124 is a hole on the outside of the connecting rod body 11. Its height dimension is larger than that of the end 112. This allows the connecting rod body 11 to move left and right during assembly, making installation convenient.

[0047] The fastener recess 125 conceals the end of the bolt 141 inside, preventing it from protruding from the surface of the part. At the same time, the size of the fastener recess 125 provides tool space for the installation of the fastener 14. Compared with countersunk fasteners, the fastener recess 125 can reduce weight while providing a larger installation torque for the fastener 14 and a greater preload force for the fastener 14, pressing the end 112 of the connecting rod body 11 tighter. The hole in the fastener recess 125 has the same size as the corresponding hole on the plug 13, one being a round hole and the other an oblong hole to absorb tolerances.

[0048] The beam connecting edge 126 is connected to the beam 23 of the elevator 2 using a joint, which can effectively distribute the load of the connecting rod body 11 to the rib 22, beam 23 and skin 21, making the force transmission more direct.

[0049] like Figure 6 As shown, the elevator 2 includes a skin 21, ribs 22 and beams 23. The beams 23 are connected to the beam connection edge 126 of the joint by fasteners 14. The skin 21, ribs 22 and the ribs and skin connection edge 121 of the joint 12 are connected by fasteners 14.

[0050] Specifically, the area where the elevator 2 cooperates with the linkage structure consists of beam 23, rib 22, and skin 21. This area is an open structure, which is connected to the joint 12. The beam 23 is connected to the beam connection edge 126 of the joint 12, and the rib 22 and skin 21 are connected to the rib and skin connection edge 121 of the joint 12 by fasteners 14. Among them, the fasteners 14 connected to the rib and skin connection edge 121 are countersunk fasteners to ensure aerodynamic shape, and the fasteners 14 connected to the web of the beam 23 are convex fasteners to reduce costs.

[0051] Beam 23, rib 22 and skin 21 are all made of carbon fiber composite material. The part connected to joint 12 is partially covered with glass cloth to prevent electrochemical corrosion.

[0052] like Figure 3 and Figure 4 As shown, the plug 13 has two connecting holes for use with the fastener 14. One of the connecting holes is a round hole and the other is an oblong hole. The mating area between the plug 13 and the end 112 of the connecting rod body 11 is a plane, and the plug 13 has a groove.

[0053] The plug 13 is machined from aluminum alloy, preferably 7050, and preferably heat treated under T7451 conditions.

[0054] The plug 13 is designed with fastener connection holes. Considering the machining tolerance of each part, the two fastener connection holes on the plug 13 are one round hole and one oblong hole to absorb the positional tolerance between the two fastener holes. The mating area between the plug 13 and the end 112 of the connecting rod body 11 is a plane. The outer side is the outer surface of the elevator 2. A fastener groove similar to that on a joint is designed on the outer surface to prevent the head of the nut 142 and the bolt 141 from exceeding the aerodynamic surface and to prevent interference with the flat tail 3 when rotating over the surface.

[0055] The axis of the connecting rod body 11 is consistent with the axis of the elevator 2 deflection. In this way, when the elevator 2 deflects, the motion envelope of the connecting rod body 11 remains unchanged. This can minimize the size of the connecting rod opening 31 on the horizontal stabilizer 3 and avoid excessively weakening the strength of the horizontal stabilizer 3 in this area.

[0056] like Figure 5 As shown, a connecting rod opening 31 is provided at the rear of the horizontal stabilizer 3. The size of the connecting rod opening 31 is larger than the size of the end 112. During assembly, the connecting rod body 11 can pass through the connecting rod opening 31. The size of the connecting rod opening 31 is larger than the size of the end 112 of the connecting rod body 11, so that the connecting rod body 11 can pass through. At the same time, when the eVTOL aircraft is in flight, the connecting rod body 11 will also undergo slight deformation due to the force. The larger connecting rod opening 31 will not cause interference between the horizontal stabilizer 3 structure and the connecting rod body 11.

[0057] like Figure 10 As shown, the cross-sections of the end 112, the slot 123, and the plug 13 are all trapezoidal. This ensures that, due to machining tolerances, at least two surfaces of the end 112 of the connecting rod body 11 are tightly fitted during assembly. When subjected to torque, they are tightly locked without any play. A gap 4 is designed between the two sides of the plug 13 and the slot 123 to facilitate installation and prevent the plug 13 from failing to fit into the slot 123 due to manufacturing tolerances. The fastener 14 consists of a bolt 141 and a nut 142, which are installed inside the fastener groove 125 of the connector 12 and the plug 13, respectively, so that they do not protrude from the surface of the parts and prevent the protruding fastener 14 from interfering with the rear area of ​​the horizontal tail 3 when the elevator 2 rotates.

[0058] The installation order in this example is as follows:

[0059] Connect the connector 12 to the elevator 2 using fasteners 14. First, install one elevator 2 onto the horizontal stabilizer 3. Then, insert the connecting rod body 11 into the connecting rod opening 31 of the horizontal stabilizer 3 from the other side, extending it into the through hole 124 of the connector 12 on the other side, ensuring that the position of the connecting rod body 11 does not occupy the space of the uninstalled elevator 2. Next, install the second elevator 2. At this time, move the connecting rod body 11 toward the connector slot 123 of the elevator 2 on this side, align it with the installation hole of the fastener 14, and then tighten the end caps 13 at both ends using the fasteners 14 to complete the installation.

[0060] In summary, this utility model provides an eVTOL aircraft elevator linkage structure. The linkage structure passes through the tail thruster of the horizontal stabilizer 3 and connects the two elevators 2 together. One servo motor controls one control surface to achieve linkage with the other control surface, saving one servo motor and making this application have the advantage of low cost.

[0061] The connector 12 and the plug 13 lock the connecting rod body 11 into the slot 123 of the connector 12. The connector 12 is connected to the skin 21, rib 22, and beam 23 of the elevator 2 through the rib and skin connection edge 121 and the beam connection edge 126, ensuring continuous force transmission between the two elevators 2 and having good rigidity and strength. The slot 123 of the connector 12 and the end 112 of the connecting rod body 11 are three-plane fits, and the two end planes are inclined, which has the characteristic of tightening as it is pressed. The fit will not produce play due to manufacturing tolerances, ensuring the direct linkage of the two elevators 2, making the movement of the two control surfaces consistent, and there will be no control lag, which makes this application have the advantage of high control precision.

[0062] The plug 13 is installed from top to bottom. After the end 112 of the connecting rod body 11 is placed into the slot 123 of the connector 12, the plug 13 only needs to be installed into the slot 123, installed and tightened with the fastener 14 to complete the installation. The open operating space makes this application easy to install.

[0063] The link body 11 is made of stainless steel, which has high shear and bending modulus. When the elevator 2 is subjected to force, the deformation of the link body 11 is small, which can ensure that the deformation difference between the two elevators 2 is small, which is beneficial to the pitch control of the eVTOL aircraft by the elevator 2.

[0064] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in this utility model, and these modifications or substitutions should all be covered within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the scope of the claims.

Claims

1. A linkage structure for the elevator of an eVTOL aircraft, characterized in that, The system includes a connecting rod body (11). After passing through the tail thrust area of ​​the horizontal tail (3), the two ends of the connecting rod body (11) are located on both sides of the tail thrust area of ​​the horizontal tail (3). Both ends of the connecting rod body (11) are locked by a connector (12) and a plug (13). Fasteners (14) are used to clamp the two ends of the connecting rod body (11). The connectors (12) at both ends of the connecting rod body (11) are connected to two elevators (2) respectively, so that the two elevators (2) are connected together to form an integral structure. When the servo controls one elevator (2) to deflect, it can drive the other elevator (2) to move, realizing the function of one servo controlling two elevators (2).

2. The eVTOL aircraft elevator linkage structure according to claim 1, characterized in that, The connecting rod body (11) includes a middle rod (111), an end (112) and an inner hole (113). The middle rod (111) is a round tube, and the axis of the middle rod (111) is consistent with the rotation axis of the elevator (2). The end (112) is provided with two mounting holes for use with fasteners (14). Both mounting holes are round holes. The inner hole (113) is the inner hole of the round tube itself.

3. The eVTOL aircraft elevator linkage structure according to claim 2, characterized in that, The connector (12) includes a rib and skin connecting edge (121), a weight-reducing hole (122), a slot (123), a through hole (124), a fastener groove (125), and a beam connecting edge (126). The rib and skin connecting edge (121) is connected to the elevator (2). The weight-reducing hole (122) is used to reduce the weight of the connector (12). The slot (123) is used to install the end (112) of the connecting rod body (11). The height dimension of the through hole (124) is larger than the dimension of the end (112). There are two fastener grooves (125), one of which is a round hole and the other is an oblong hole.

4. The eVTOL aircraft elevator linkage structure according to claim 3, characterized in that, The elevator (2) includes a skin (21), ribs (22) and beams (23). The beams (23) are connected to the beam connecting edge (126) of the joint by fasteners (14). The skin (21), ribs (22) and the ribs and skin connecting edge (121) of the joint (12) are connected by fasteners (14).

5. The eVTOL aircraft elevator linkage structure according to claim 2, characterized in that, The plug (13) has two connecting holes for use with fasteners (14). One of the connecting holes is a round hole and the other is an oblong hole. The mating area between the plug (13) and the end (112) of the connecting rod body (11) is a plane. The plug (13) has a groove.

6. The eVTOL aircraft elevator linkage structure according to claim 4, characterized in that, The rear of the flat tail (3) is provided with a connecting rod opening (31), the size of which is larger than the size of the end (112).

7. The eVTOL aircraft elevator linkage structure according to claim 3, characterized in that, The cross-sections of the end (112), the slot (123), and the plug (13) are all trapezoidal.

8. The eVTOL aircraft elevator linkage structure according to claim 1, characterized in that, The fastener (14) includes a bolt (141) and a nut (142) that mates with the bolt (141).

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