Composite wing eVTOL elevator structure and assembling method

Abstract

The invention relates to the technical field of electric airplanes, in particular to a composite wing eVTOL elevator structure and an assembling method.The composite wing eVTOL elevator structure comprises an elevator body and a tail pusher, and the elevator body is divided into two parts through the tail pusher; the elevator body comprises two control surfaces, a supporting structure and a control structure, the supporting structure is used for connecting the two control surfaces together to enable the two control surfaces to keep synchronous movement, and the supporting structure fixes the control surfaces on a horizontal tail at the same time and keeps the two control surfaces to rotate around the axes of the control surfaces. One end of the control structure is connected with the steering engine, the other end of the control structure is connected with one of the control surfaces, the control structure is driven by the steering engine to move, so that the two control surfaces are driven to synchronously rotate around the axis, the deflection angles of the two control surfaces are consistent during control, and the flight control precision is high; the invention has the advantages of low system complexity, low cost, high control precision, good durability and simple assembly.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of electric aircrafts, in particular to a composite wing eVTOL elevator structure and an assembling method. BACKGROUND

[0002] The composite wing eVTOL does not need a dedicated runway when taking off and landing, has the characteristics of flexible use and wide applicability, and combines vertical lift rotors and fixed wings in the form of lift + thrust separation or lift + fixed wing hybrid. The vertical take-off and landing stage is provided with lift by the rotors, the flat flight stage is provided with lift by the fixed wings, part or all of the power system is converted into a propeller, the vertical take-off and landing stage is similar to a multi-rotor, the flat flight cruising stage is similar to a fixed-wing flight, the aerodynamic efficiency is high, the range can reach 150-300km, the cruising speed can reach 200-300km / h, and only a small amount of propeller works in the flat flight stage. The composite wing eVTOL is mainly applied to intercity short-distance passenger transport, regional logistics and medical transport.

[0003] The elevator is a key component for longitudinal control of the aircraft, and mainly functions to control the pitch attitude of the aircraft, that is, to change the tendency of the aircraft to lift its head (climb) or lower its head (descend), so as to adjust the flight height. The elevator is arranged at the trailing edge of the horizontal tail. For some composite wing eVTOLs, the trailing edge of the horizontal tail is arranged with motor arms of the tail thrust motor, so that the trailing edge of the horizontal tail is divided into multiple parts in the span direction. In order to achieve certain control performance, the area of the elevator needs to reach a certain value, and therefore the trailing edge of the horizontal tail needs to be used as the elevator. How to control multiple surfaces by one servo becomes a difficult problem to be considered.

[0004] A Chinese utility model patent with the application number 201821688949.5 discloses a horizontal tail wing with a double elevator structure and an aircraft. The horizontal stabilizer is provided with a pair of elevators arranged in an upper and lower distribution manner at the trailing edge of the horizontal stabilizer. The elevators can rotate relative to the horizontal stabilizer. An aircraft with a double elevator structure is also disclosed. The aircraft comprises a fuselage, and the tail of the fuselage is provided with the horizontal tail wing with the double elevator structure. The horizontal tail wing and the aircraft adopt a novel aerodynamic layout structure. One of the pair of elevators can be rotated to open, the traditional working mode and function are retained, and the pair of elevators can also be opened simultaneously to form a certain included angle. In this way, the horizontal tail wing has elevators that are upwardly inclined and downwardly inclined at the same time, the flight resistance of the aircraft is increased, the effect of rapid deceleration is achieved, the landing time and distance are shortened, the maneuverability is improved, more flight experiences and actions are extended, and more fun and challenges are provided for the majority of enthusiasts.

[0005] The horizontal tail plane and the airplane with the double-elevon structure realize normal airplane control mode by opening one of the pair of elevons, realize the function of deceleration by opening the elevons in opposite directions, and play the role of aerodynamic control, although the horizontal tail plane has two elevon surfaces, each elevon surface needs to be controlled by an expensive elevon, and the cost cannot be reduced. SUMMARY

[0006] The present application aims to overcome the deficiencies of the prior art, and provides a compound wing eVTOL elevon, which has the advantages of low system complexity, low cost, high control accuracy, good durability and simple assembly.

[0007] To solve the above technical problems, the application adopts the following technical solutions:

[0008] A compound wing eVTOL elevon comprises:

[0009] The elevon body and the tail push, the tail push divides the elevon body into two parts;

[0010] The elevon body comprises an elevon surface, a support structure and a control structure, the elevon surface is provided with two, the support structure is used for connecting the two elevon surfaces together, so that the two elevon surfaces keep synchronous movement, the support structure fixes the elevon surface on the tail plane at the same time, keeps the two elevon surfaces capable of rotating around the axis of the elevon surface, one end of the control structure is connected with the rudder, and the other end is connected with the elevon surface, the control structure is driven to move by the rudder, so as to drive the two elevon surfaces to rotate synchronously around the axis, and the deflection angles of the two elevon surfaces can be ensured to be consistent, and the flight control accuracy is high.

[0011] Preferably, the tail push comprises a skin and a longitudinal beam, the skin is the outer surface of the tail plane, maintains the aerodynamic shape of the tail plane, the rear part of the longitudinal beam is connected with the thrust motor, the outer side of the longitudinal beam supports the skin, and the longitudinal beam and the skin are glued by structural glue to form an integral structure, the support structure passes through the longitudinal beam to connect the two elevon surfaces together, and a via hole one for the support structure to pass through is formed in the longitudinal beam.

[0012] Further, the elevon surface comprises an elevon surface body and a carbon pipe, the carbon pipe is arranged at the position of the rotating axis of the elevon surface body, one end of the carbon pipe extends out of the elevon surface body, and is used for being connected with the support structure.

[0013] Further, the support structure comprises an outer support, a middle support and an inner support, two ends of the middle support are connected with the two rudders, the outer support is used for supporting the outer end of the outer rudder, the inner support is used for supporting the inner end of the inner rudder, the support points of the outer support, the inner support and the middle support to the outer rudder and the inner rudder are on a straight line, forming the rotation axis of the two rudders, when the control structure pushes and pulls the rudder movement, the two rudders can rotate around the rotation axis.

[0014] Further, the inner support has the same structure as the outer support, the outer support comprises an outer support, a support shaft, a split pin, a support sleeve and an adjusting washer, the outer support is connected with the tail, the outer support is connected with the support shaft, and the position is provided with a through hole two for connecting the support shaft, the support shaft is inserted into the through hole two of the outer support, the outer support and the support shaft are provided with fixing holes matched with the split pin, the split pin passes through the outer support and the support shaft, and the outer support and the support shaft are fixed together to prevent mutual rotation between the outer support and the support shaft, a small gap is left between the support shaft and the outer support, the support shaft and the support sleeve rotate relative to each other to realize the movement of the rudder around the rotation axis, the support sleeve is adhered to the inside of the outer rudder through structural glue, the hole diameter of the adjusting washer is larger than the outer diameter of the support shaft and smaller than the outer diameter of the support sleeve, the adjusting washer is sleeved on the support shaft to isolate the outer support and the support sleeve.

[0015] Further, the middle support comprises a middle support, a connecting rod joint and a connecting rod, one end of the connecting rod joint is connected with the connecting rod through a fastener, the other end of the connecting rod joint is connected with the carbon pipe of the rudder through a fastener, the two rudders on the inner and outer sides are connected together through the connecting rod joint and the connecting rod to form a whole, and the carbon pipe is clamped by the middle support at the position coinciding with the middle support.

[0016] Further, one end of the connecting rod joint is processed into a square structure, one end of the connecting rod joint is inserted into a square inner hole of the connecting rod, and is fixed through a fastener; a round hole for inserting the carbon pipe is formed in the inner side of the other end of the connecting rod joint, and the carbon pipe is fixed on the connecting rod joint through a fastener.

[0017] Further, the middle support comprises a front half support, a rear half support and a round sleeve, the round sleeve is sleeved on the carbon pipe, and the inner side of the round sleeve is adhered to the carbon pipe by structural glue, and the front half support and the rear half support are fixed together by a fastener.

[0018] Further, the control structure comprises a control support and a pull rod, the control support is sleeved on the upper and lower surfaces of the rudder body, and the rudder is clamped in the inner part of the control support through a fastener.

[0019] A composite wing eVTOL elevator assembly method, comprising the following steps:

[0020] Step one: take out the finished parts, prepare fasteners, make sure the model and length are accurate;

[0021] Step two: fix the tail on the assembly tool, fix the skin and stringers of the tail push, and glue the stringers and the skin together.

[0022] Step three: position the control surface axis with the assembly tool, install the front half support of the outer support, inner support and middle support to the tail, and do not need to install the split pin at this time.

[0023] Step four: the installation method of the outer support and the inner support is similar, glue the support sleeve and the outer control surface together, glue the round sleeve on the carbon pipe, then fix it to the tool, the support shaft is inserted into the through hole two of the outer support, passes through the adjusting washer, and is inserted into the support sleeve, and then the split pin is installed, and the carbon pipe with the round sleeve of the outer control surface is matched with the inner semicircular hole of the front half support of the middle support.

[0024] Step five: install the rear half support to the front half support with fasteners, and clamp the round sleeve;

[0025] Step six: fit the connecting rod joint to the outside of the carbon pipe, pass the connecting rod through the through hole one of the stringer from the inside of the tail push to the inside of the tail push, and insert the connecting rod joint into the inside of the connecting rod, without installing fasteners at this time, there is a distance between the connecting rod joint and the connecting rod, which can slide, and the connecting rod is pushed to the outermost side.

[0026] Step seven: install the inner control surface according to the method of steps four to six, and install the control structure on the control surface with fasteners.

[0027] Step eight: fix the inner connecting rod joint on the carbon pipe, at this time, the connecting rod is outside the inner connecting rod joint, pull the connecting rod back along the axis, fit it on the inner connecting rod joint, align the fastener hole, and install the fastener, thus, the installation of the composite wing eVTOL elevator is completed, the inner and outer control surfaces are fixed together, the two control surfaces are controlled by one control machine, and the function of linkage is realized.

[0028] Steps four to six can also install the inner support first, and step seven is: install the outer control surface according to the method of steps four to six, and install the control structure on the control surface with fasteners.

[0029] The beneficial effects of the present application are:

[0030] The application adopts one rudder to control two rudder surfaces of the elevator body, for the composite wing eVTOL whole machine, the application of one rudder is reduced, the wire harness connection of the rudder is saved, the rudder control logic of the flight control is saved, the complexity of the rudder control system is reduced, so that the application has the advantages of low system complexity, the application saves the use of the rudder, the cost of a single rudder is several thousand yuan, the single machine cost is saved nearly ten thousand yuan, so that the application has the advantages of low cost, the application adopts one rudder to control two rudder surfaces of the elevator body, which can ensure that the deflection angles of the two rudder surfaces are consistent, the flight control precision is high.

[0031] The two rudder surfaces on both sides of the tail push are connected together, and when control, the deflection angles of the two rudder surfaces can be ensured to be consistent, the difference between the deflection angles of the two rudder surfaces when controlling a single rudder surface is avoided, the flight control precision is high, so that the application has the advantages of high control precision. BRIEF DESCRIPTION OF DRAWINGS

[0032] In order to more clearly illustrate the technical solutions of the embodiments of the application, the drawings needed in the embodiment description will be briefly introduced. Obviously, the drawings in the following description are some embodiments of the application, and other drawings can also be obtained by those skilled in the art without creative labor.

[0033] Figure 1 The position diagram of the composite wing eVTOL elevator of the application on the composite wing eVTOL;

[0034] Figure 2 The isometric view of the composite wing eVTOL elevator of the application;

[0035] Figure 3 The exploded view of the composite wing eVTOL elevator of the application;

[0036] Figure 4 The exploded view of the elevator body of the application;

[0037] Figure 5 The isometric view of the tail push of the application;

[0038] Figure 6 The partial view of the elevator body and the tail push longitudinal beam of the application;

[0039] Figure 7 The isometric view of the tail push longitudinal beam of the application;

[0040] Figure 8 The isometric view of the rudder surface of the application;

[0041] Figure 9 The isometric view of the support structure of the application;

[0042] Figure 10 This is an exploded view of the external support of the present invention;

[0043] Figure 11 This is a partial view of the connection between the central support and the carbon fiber tube of the rudder surface in this invention;

[0044] Figure 12 This is an exploded view of the connection between the central support and the rudder surface in this invention;

[0045] Figure 13 This is an exploded view of the central support of the present invention;

[0046] Figure 14 This is a cross-sectional view of the central support location of the present invention;

[0047] Figure 15 This is a cross-sectional view of the connection between the central support and the rudder surface in this invention;

[0048] Figure 16 This is a cross-sectional view showing the connection between the control structure and the rudder surface of the present invention.

[0049] Explanation of markings in the diagram: 11. Elevator body; 111. Control surface; 1111. Control surface body; 1112. Carbon fiber tube; 112. Support structure; 1121. External support; 11211. External support; 11212. Support shaft; 11213. Cotter pin; 11214. Support sleeve; 11215. Adjusting shim; 1122. Central support; 11221. Central support; 112211. Front support; 112212, Rear support; 112213, Round sleeve; 11222, Connecting rod joint; 11223, Connecting rod; 1123, Internal support; 113, Control structure; 1131, Control support; 114, Fastener; 1141, Bolt; 1142, Washer; 1143, Nut; 12, Tail thruster; 121, Skin; 122, Longitudinal beam; 1221, Through hole one; 2, Compound wing eVTOL. Detailed Implementation

[0050] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0051] 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.

[0052] 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 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.

[0053] 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.

[0054] Example 1

[0055] like Figure 1 As shown, the present invention discloses a compound wing eVTOL elevator, which is arranged on the trailing edge of the horizontal stabilizer of the compound wing eVTOL 2. It exists on both the left and right sides of the aircraft and has a symmetrical structure. This example only describes the left side. The right side structure is the same and will not be described again here. The pitch control of the compound wing eVTOL 2 is achieved by controlling the deflection of the elevator with a servo motor. In this example, the elevator function is achieved by using one servo motor to control the deflection of the elevator.

[0056] like Figure 2 and 3 As shown, the elevator includes an elevator body 11 and a tail thruster 12. The tail thruster 12 divides the elevator body 11 into inner and outer parts. Since the tail thruster 12 is connected to the thrust motor, it is subjected to a large force. Therefore, the tail thruster 12 needs to be a strong structure and a fixed structure. The elevator body 11 needs to deflect to change the aerodynamic force of the horizontal stabilizer and realize the pitch control of the compound wing eVTOL 2. In this example, one servo is used to control the two parts of the elevator body 11. For the compound wing eVTOL 2 as a whole, reducing the application of one servo reduces the power supply and control of the servo, saving the power supply and signal wiring harness of the servo. At the same time, the reduction in the number of servos also reduces the amount of data that the flight control computer needs to calculate, thus reducing the complexity of the flight control system.

[0057] like Figure 4As shown, the elevator body 11 includes a control structure 113, a support structure 112 and a surface 111, two surfaces 111 are provided, separated by the tail push 12, the structures of the two surfaces 111 are the same, and the structure of only one surface 111 is described in this example, and the structure of the other surface 111 is not described here. The support structure 112 is used to connect the two surfaces 111 together, so that the two surfaces 111 move synchronously, and the support structure 112 fixes the surface 111 on the tail plane, keeping the two surfaces 111 able to rotate around the axis of the surface 111, and the control structure 113 is connected to the rudder at one end and to one of the surfaces 111 at the other end, which is the inner surface 111 in this example. The control structure 113 is driven by the rudder to move, thereby driving the two surfaces 111 to rotate synchronously around the axis, and the control can ensure that the deflection angles of the two surfaces 111 are consistent, and the flight control precision is high.

[0058] It also includes fasteners 114 that connect the control structure 113 to the surface 111, and also connect the support structure 112 inside together.

[0059] As shown in Figure 5 The tail push 12 includes a skin 121 and a longitudinal beam 122, the skin 121 is the outer surface of the tail plane, maintaining the aerodynamic shape of the tail plane, and the longitudinal beam 122 is connected to the thrust motor at the rear, and the outer side of the longitudinal beam 122 supports the skin 121, maintaining the stability of the skin 121.

[0060] The longitudinal beam 122 bears the load of the thrust unit and transmits the load to the tail plane, the longitudinal beam 122 is an aluminum alloy machined part, the preferred material is 7075, and the preferred heat treatment state is T7351, the skin 121 is made of carbon fiber composite material, and is glued to the longitudinal beam 122 by structural adhesive to form an integral structure, and there is a gap between the skin 121 and the surface 111, so that the surface 111 does not interfere with the skin 121 when moving, the gap takes into account the manufacturing tolerance, the stress deformation of the skin 121 and the surface 111, etc., the gap between the skin 121 and the surface 111 is not less than 3mm, and in this example it is 5mm.

[0061] As shown in Figure 6 and Figure 7As shown, the support structure 112 passes through the longitudinal beam 122 to connect the two rudder surfaces 111 together. In order to install and avoid interference, the longitudinal beam 122 is designed with a through hole 1221 at the position where it overlaps with the support structure 112. That is, a through hole 1221 is opened on the longitudinal beam 122 for the support structure 112 to pass through. Since the longitudinal beam 122 is an important load-bearing component, it cannot be broken, and the opening area should be as small as possible. Therefore, the gap between the through hole 1221 and the support structure 112 should be as small as possible. However, a certain safety gap needs to be maintained between the through hole 1221 and the rotating support structure 112. In this example, it is 5mm.

[0062] like Figure 8 As shown, the control surface 111 of the present invention is a movable structure. When it deflects downward, the surface generates an upward force, causing the compound wing eVTOL 2 to pitch down. When it deflects upward, it generates a downward force, causing the compound wing eVTOL 2 to pitch up.

[0063] The rudder surface 111 includes a rudder surface body 1111 and a carbon tube 1112. One end of the carbon tube 1112 extends out of the rudder surface body 1111. During manufacturing, the carbon tube 1112 is pre-embedded inside the rudder surface body 1111. The carbon tube 1112 and the rudder surface body 1111 are solidified together. The carbon tube 1112 is arranged at the position of the rotation axis of the rudder surface 111. The carbon tube 1112 has a circular tube structure. This way, when rotating around the axis, the outer surface of the carbon tube 1112 can be kept circular.

[0064] The rudder body 1111 is a full-height foam-core carbon fiber composite material structure. The foam inside the rudder body 1111 can be PVC foam, PMI foam, or PU foam. In this embodiment, PMI foam is preferred. The carbon fiber composite material on the surface of the rudder 111 is preferably T300 grade carbon fiber and fabric with a surface density of 200 grams per square meter.

[0065] like Figure 9 As shown, the support structure 112 includes an outer support 1121, a middle support 1122, and an inner support 1123. The inner support 1123 has the same structure as the outer support 1121. This example only describes the outer support 1121.

[0066] The middle support 1122 crosses the longitudinal beam 122 of the tail push 12, and the two ends of the middle support 1122 are connected with the two rudders 111. The outer support 1121 is used for supporting the outer end of the outer rudder 111, and the inner support 1123 is used for supporting the inner end of the inner rudder 111. The outer support 1121 and the inner support 1123, together with the middle support 1122, form two support points for the outer rudder 111 and the inner rudder 111 respectively, and the four support points are on a straight line, which constitutes the rotation axis of the two rudders 111. When the control structure 113 pushes and pulls the rudders 111 to move, the two rudders 111 can rotate around the rotation axis.

[0067] As shown in Figure 10 The outer support 1121 includes an outer support 11211, a support shaft 11212, a split pin 11213, a support sleeve 11214 and an adjusting gasket 11215. The outer support 11211 is connected with the tail plane and is an aluminum alloy machined part. The preferred material is 7075, and the preferred heat treatment state is T7351. A through hole two for connecting the support shaft 11212 is provided at the position where the outer support 11211 is connected with the support shaft 11212. That is, the support shaft 11212 is inserted into the through hole two inside the outer support 11211. The outer support 11211 is provided with a fixing hole at the front and rear positions of the support shaft 11212, which is matched with the split pin 11213. The split pin 11213 passes through the outer support 11211 and the support shaft 11212 to fix the outer support 11211 and the support shaft 11212 together to prevent them from rotating relative to each other. In order to ensure that the support shaft 11212 can be inserted into the inside of the outer support 11211 and will not shake after installation, causing the axis of the rudder 111 to change, a small gap needs to be left between the support shaft 11212 and the outer support 11211. In this example, the gap is 0.02-0.05mm. At the same time, a small gap can also reduce the vibration load.

[0068] The support shaft 11212 and the support sleeve 11214 are both made of steel, and the preferred material is 15-5PH stainless steel. The support shaft 11212 and the support sleeve 11214 rotate relative to each other to realize the movement of the rudder 111 around the rotation axis of the rudder 111. Stainless steel is more wear-resistant than aluminum alloy.

[0069] The support sleeve 11214 is connected with the outer rudder 111 and is adhered to the inside of the outer rudder 111 by structural adhesive. In this way, the support sleeve 11214 and the outer rudder 111 are a fixed structure, the support shaft 11212 is fixed with the outer support 11211 by the split pin 11213, and the rotation between the support shaft 11212 and the support sleeve 11214 realizes the rotation between the rudder 111 and the outer support 11211.

[0070] The hole diameter of the adjusting gasket 11215 is larger than the outer diameter of the support shaft 11212 and smaller than the outer diameter of the support sleeve 11214. The adjusting gasket 11215 is sleeved on the support shaft 11212, separates the outer support 11211 from the support sleeve 11214, and prevents friction between the aluminum alloy outer support 11211 and the steel support sleeve 11214, thereby preventing wear of the outer support 11211.

[0071] As shown in Figure 11 and Figure 12 The middle support 1122 has two fulcrums connected with the inner and outer rudders 111 and the tail plane. The structure is the same, and only one is described in this example.

[0072] The middle support 1122 includes a middle support 11221, a connecting rod joint 11222, and a connecting rod 11223. One end of the connecting rod joint 11222 is connected with the connecting rod 11223 through a fastener 114, and the other end of the connecting rod joint 11222 is connected with the carbon pipe 1112 of the rudder 111 through the fastener 114. The two rudders 111 on the inner and outer sides are connected together through the connecting rod joint 11222 and the connecting rod 11223 to form an integral whole, and then the carbon pipe 1112 is connected by the middle support 11221, so as to form an integral support.

[0073] The connecting rod joint 11222 and the connecting rod 11223 are both made of aluminum alloy. The connecting rod 11223 is a standard square aluminum alloy profile, and the preferred material is 6061 in the T6 heat treatment state. The connecting rod joint 11222 is a machined part. One end of the connecting rod joint 11222 is machined into a square structure, and the end is inserted into a square inner hole formed in the connecting rod 11223 and fixed through the fastener 114. The other end of the connecting rod joint 11222 is provided with a round hole for inserting the carbon pipe 1112, and the carbon pipe 1112 is fixed on the connecting rod joint 11222 through the fastener 114. The carbon pipe 1112 is clamped by the middle support 11221 at the position coinciding with the middle support 11221. In this way, the middle support 11221, together with the inner support 1123 and the inner support of the outer support 11211, forms four fulcrums for the two rudders 111, and the center lines of the holes of the four supports are on a straight line, which is the axis of rotation of the rudder 111.

[0074] As shown in Figure 13As shown, the middle support 11221 is to be passed through by the carbon tube 1112, in order to realize this function, the middle support 11221 is divided into a front half support 112211, a rear half support 112212 and a round sleeve 112213, all of which are made of 15-5PH stainless steel, the round sleeve 112213 is sleeved on the carbon tube 1112, and the inner side of the round sleeve 112213 is adhesively connected with the carbon tube 1112, the front half support 112211 and the rear half support 112212 are fixed together by fasteners 114, the front half support 112211 and the rear half support 112212 form an internal circular hole with a slight gap with the outer surface of the round sleeve 112213, and the preferred gap is 0.02mm-0.05mm, so that the inner wall of the inner circle formed by the round sleeve 112213, the front half support 112211 and the rear half support 112212 rotates to realize the deflection of the rudder surface 111, and the stainless steel is more wear-resistant, the friction surface is the outer surface of the round sleeve 112213 and the inner surface of the circular hole formed by the front half support 112211 and the rear half support 112212, during installation, the round sleeve 112213 is fixed with the carbon tube 1112, then placed in the semicircle of the front half support 112211, and then the rear half support 112212 is installed, and finally fixed by the fasteners 114.

[0075] As shown in Figure 14 The fastener 114 includes a bolt 1141, a gasket 1142 and a nut 1143, the carbon tube 1112 is sleeved by the round sleeve 112213 and fixed into the circular hole formed by the front half support 112211 and the rear half support 112212, the front half support 112211 and the rear half support 112212 are fixed by the bolt 1141, the gasket 1142 and the nut 1143, the nut 1143 is a lock nut to prevent loosening, and the bolt 1141 herein is a hexagonal head bolt, which can apply a large torque during installation to generate a large pre-tightening force, so that the front half support 112211 and the rear half support 112212 are reliably connected.

[0076] As shown in Figure 15As shown, the carbon tube 1112 is integrally formed with the rudder body 1111, the carbon tube 1112 protrudes from a part of the rudder body 1111, the round sleeve 112213 is glued outside the carbon tube 1112, the round sleeve 112213 is matched with a small gap between the inner circle formed by the front half support 112211 and the rear half support 112212, the carbon tube 1112 is inserted into the inner wall of the connecting rod joint 11222, then the other end of the connecting rod joint 11222 is inserted into the inside of the connecting rod 11223, the carbon tube 1112 and the connecting rod joint 11222, and the connecting rod joint 11222 and the connecting rod 11223 are connected by the bolt 1141, the gasket 1142 and the nut 1143, the bolt 1141 is a half-round head cross bolt, the torque applied during installation is small, the pre-tightening force is small, and the hollow structure between the connecting rod joint 11222 and the carbon tube 1112 is prevented from being deformed by a large pre-tightening force, which damages the carbon tube 1112.

[0077] As shown, Figure 16 The control structure 113 includes a control support 1131 and a pull rod, the control support 1131 is an integrally machined aluminum alloy part, the preferred material is 7075, and the preferred heat treatment state is T7351, which is fitted on the upper and lower surfaces of the rudder body 1111 and connected by fasteners 114, that is, connected by the bolt 1141, the nut 1143 and the gasket 1142, the rudder 111 is clamped inside the control support 1131, the clamping surfaces of the fasteners 114 are the control support 1131, which prevents the fasteners 114 from contacting the surface of the carbon fiber composite material of the rudder body 1111 and damaging the surface of the carbon fiber composite material, and ensures the integrity of the structure of the rudder 111.

[0078] A composite wing eVTOL elevator assembly method, comprising the following steps:

[0079] Step one: manufacture each part, prepare fasteners 114 such as bolts 1141, gaskets 1142 and nuts 1143, and ensure that the model and length of the fasteners 114 are accurate;

[0080] Step two: fix the horizontal tail on the assembly tool, fix the skin 121 and the longitudinal beam 122 of the tail push 12, and glue the longitudinal beam 122 and the skin 121 together with structural glue.

[0081] Step three: position the axis of the rudder 111 with the assembly tool, install the front half support 112211 of the outer support 1121, the inner support 1123 and the middle support 1122 to the horizontal tail, and do not need to install the split pin 11213 at this time;

[0082] Step four: the installation method of the outer support 1121 is similar to that of the inner support 1123, the support sleeve 11214 and the outer vane 111 are glued together, the round sleeve 112213 on the carbon pipe 1112 is glued, then fixed to the tool, the shaft 11212 is inserted into the through hole two of the outer support 11211 from the outside, passes through the adjusting gasket 11215, penetrates into the inside of the support sleeve 11214, and is aligned with the fixing hole of the split pin 11213 on the outer support 11211, then the split pin 11213 is installed, and the carbon pipe 1112 of the outer vane 111 with the round sleeve 112213 is combined with the front half support 112211 of the middle support 1122;

[0083] Step five: the rear half support 112212 is installed on the front half support 112211 by the fastener 114, and the round sleeve 112213 is clamped;

[0084] Step six: the connecting rod joint 11222 is combined outside the carbon pipe 1112, the connecting rod 11223 is inserted into the tail push 12 from the inside of the longitudinal beam 122 through the through hole one 1221 of the longitudinal beam 122, the connecting rod joint 11222 is inserted into the inside of the connecting rod 11223, at this time, the fastener 114 is not installed, there is a distance between the connecting rod joint 11222 and the connecting rod 11223, which can slide, and the connecting rod 11223 is pushed to the outermost side;

[0085] Step seven: the inner vane 111 is fixed and installed according to the method of steps four to six, and the control structure 113 is installed on the inner vane 111 by the fastener 114;

[0086] Step eight: the inner connecting rod joint 11222 is fixed on the carbon pipe 1112, at this time, the connecting rod 11223 is outside the inner connecting rod joint 11222, the connecting rod 11223 is pulled back along the axis to the inside of the inner connecting rod joint 11222, the fastener hole position is aligned, and the fastener 114 is installed, thus, the installation of the composite wing eVTOL elevator is completed, the inner and outer vanes 111 are fixed together, the two vanes 111 are controlled by one rudder, and the linkage function is realized;

[0087] Steps four to six can also install the inner support 1123 first, at this time, step seven is: the outer vane 111 is fixed and installed according to the method of steps four to six, and the control structure 113 is installed on the outer vane 111 by the fastener 114.

[0088] In summary, the through hole one 1221 is arranged in the longitudinal beam 122 of the tail push 12, the connecting rod 11223 of the support structure 112 passes through the through hole one 1221, and the inner and outer vanes 111 are connected.

[0089] The axis of the connecting rod 11223 coincides with the axis of rotation of the control surface 111, so that when the control surface 111 rotates, the connecting rod 11223 also rotates around its own axis, the movement envelope is minimized, and the through hole 1221 on the longitudinal beam 122 is as small as possible, reducing the damage to the strength.

[0090] The middle support 11221 is divided into two parts, the front half support 112211 is fixed at the rear of the tail plane, the control surface 111 cannot move left and right, and can only be installed forward and backward, realizing the assembly feasibility.

[0091] The outer part of the carbon tube 1112 is glued and fixed by a stainless steel round sleeve 112213 to prevent the carbon tube 1112 from rotating and wearing out.

[0092] There is a gap between the connecting rod 1123 of the outer control surface 111 and the connecting rod joint 1122, which satisfies the assembly, so that the connecting rod can move outward for a distance, and does not interfere with the forward and backward movement of the inner control surface 111 before assembly. After the inner control surface 111 is fixed, the connecting rod 1123 is moved inwardly connected.

[0093] The control support 1131 is fitted outside the control surface 111, so that the pre-tightening force of the fastener 114 is applied to the control support 1131, preventing the carbon fiber composite material outer surface of the control surface 111 from being crushed.

[0094] The small gap between the round sleeve 112213 and the holes formed by the front half support 112211 and the rear half support 112212 can rotate while reducing vibration.

[0095] The control surface body 1111 and the carbon tube 1112 are integrally formed and positioned in the mold, with relatively high accuracy.

[0096] The adjusting gasket 11215 separates the outer support 11211 from the support sleeve 11214 to prevent wear of the outer support 11211.

[0097] The relative motion position materials are all made of stainless steel to prevent wear of aluminum alloy and improve wear resistance.

[0098] The application uses one rudder to control the two control surfaces 111 of the elevator body 11. For the composite wing eVTOL 2 whole machine, the application of one rudder is reduced, the wire harness connection of the rudder is saved, the rudder control logic of the flight control is saved, the complexity of the rudder control system is reduced, the application has the advantages of low system complexity, the application saves the use of rudders, the cost of a single rudder is several thousand yuan, and the cost of a single machine is saved nearly ten thousand yuan, so that the application has the advantages of low cost. The application uses one rudder to control the two control surfaces 111 of the elevator body 11, which can ensure that the deflection angles of the two control surfaces 111 are consistent, and the flight control accuracy is high.

[0099] The two rudders 111 on both sides of the tail push 12 are connected together, and when controlled, the deflection angles of the two rudders 111 are consistent, the difference between the deflection angles of the two rudders 111 when one rudder 111 is controlled alone is avoided, the flight control precision is high, and the application has the advantages of high control precision.

[0100] When the carbon pipe 1112 of the rudder 111 is connected with the middle support 1122, a round sleeve 112213 is added to isolate the middle support 1122, so that when rotating, the round sleeve 112213 is glued and fixed with the carbon pipe 1112, only the outer surface of the round sleeve 112213 rotates with the middle support 1122, metal friction is improved, the service life of the carbon pipe 1112 is improved, and the application has the advantage of good durability.

[0101] The support structure 112 and the rudder 111 are fixed by the fastener 114, which can be conveniently installed, and the middle support 1122 is divided into a front half support 112211 and a rear half support 112212, the rudder 111 is pushed from the rear of the horizontal tail and fixed by connecting the rear half support 112212, so that the assembly of the rudder 111 is completed, and the application has the advantage of simple assembly.

[0102] The above is only a specific embodiment of the application, but the protection scope of the application is not limited to this, any skilled person in the art can easily think of various equivalent modifications or replacements within the technical range disclosed by the application, and these modifications or replacements should be covered within the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.

Claims

1. A composite wing eVTOL elevator structure, characterized by, The utility model relates to an aircraft control system, including: The rudder body (11) and the tail push (12) are divided into two parts by the tail push (12); The rudder body (11) includes two rudder surfaces (111), a support structure (112) and a control structure (113), the support structure (112) is used to connect the two rudder surfaces (111) together so that the two rudder surfaces (111) keep synchronous movement, the support structure (112) fixes the rudder surface (111) on the tail plane at the same time, keeps the two rudder surfaces (111) can rotate around the axis of the rudder surface (111), one end of the control structure (113) is connected with the rudder, and the other end is connected with the rudder surface (111), drives the control structure (113) movement through the rudder, thereby driving the two rudder surfaces (111) synchronous rotation around the axis, and the deflection angle of the two rudder surfaces (111) can be guaranteed to be consistent when controlling, and flight control precision is high.

2. The composite wing eVTOL elevator structure of claim 1, wherein, The tail push (12) includes a skin (121) and a stringer (122), the skin (121) is the outer surface of the tail plane, keeps the aerodynamic shape of the tail plane, the rear part of the stringer (122) is connected with the thrust motor, the outer side of the stringer (122) supports the skin (121), and the stringer (122) is glued with the skin (121) through structural glue and constitutes an integral structure, the support structure (112) passes through the stringer (122) and connects the two rudder surfaces (111) together, and the stringer (122) is provided with a via hole (1221) for the support structure (112) to pass through.

3. The composite wing eVTOL elevator structure of claim 1, wherein, The rudder surface (111) includes a rudder surface body (1111) and a carbon tube (1112), the carbon tube (1112) is arranged at the position of the rotating axis of the rudder surface body (1111), one end of the carbon tube (1112) extends outside the rudder surface body (1111) and is used to be connected with the support structure (112).

4. The composite wing eVTOL elevator structure of claim 1, wherein, The support structure (112) includes an outer support (1121), a middle support (1122) and an inner support (1123), both ends of the middle support (1122) are connected with the two rudder surfaces (111), the outer support (1121) is used to support the outer end of the rudder surface (111) located at the outer side, the inner support (1123) is used to support the inner end of the inner rudder surface (111), the support points of the outer rudder surface (111) and the inner rudder surface (111) formed by the outer support (1121), the inner support (1123) and the middle support (1122) are on a straight line, which constitutes the rotating axis of the two rudder surfaces (111), when the control structure (113) pushes and pulls the rudder surface (111) to move, the two rudder surfaces (111) can rotate around the rotating axis.

5. The composite wing eVTOL elevator structure of claim 4, wherein, The inner support (1123) is the same structure as the outer support (1121), the outer support (1121) includes an outer support (11211), a support shaft (11212), an open pin (11213), a support sleeve (11214) and an adjusting washer (11215), the outer support (11211) is connected with the tail, the position where the outer support (11211) is connected with the support shaft (11212) is provided with a through hole two for connecting the support shaft (11212), the support shaft (11212) is inserted into the through hole two of the outer support (11211), the outer support (11211) and the support shaft (11212) are provided with fixing holes matched with the open pin (11213), the open pin (11213) passes through the outer support (11211) and the support shaft (11212), and the outer support (11211) and the support shaft (11212) are fixed together to prevent mutual rotation between the outer support (11211) and the support shaft (11212), a small gap is left between the support shaft (11212) and the outer support (11211), the support shaft (11212) and the support sleeve (11214) rotate relative to each other to realize the movement of the rudder surface (111) around the rotation axis, the support sleeve (11214) is adhered to the inside of the outer rudder surface (111) through structural glue, the adjusting washer (11215) has a hole diameter larger than the outer diameter of the support shaft (11212) and smaller than the outer diameter of the support sleeve (11214), the adjusting washer (11215) is sleeved on the support shaft (11212), and the outer support (11211) and the support sleeve (11214) are isolated.

6. The composite wing eVTOL elevator structure of claim 4, wherein, The middle support (1122) includes a middle support (11221), a connecting rod joint (11222) and a connecting rod (11223), one end of the connecting rod joint (11222) is connected with the connecting rod (11223) through a fastener (114), the other end of the connecting rod joint (11222) is connected with the carbon pipe (1112) of the rudder surface (111) through a fastener (114), and the two rudder surfaces (111) on the inner and outer sides are connected together through the connecting rod joint (11222) and the connecting rod (11223) to form an integral whole, and the carbon pipe (112) is clamped by the middle support (11221) at the position coinciding with the middle support (11221).

7. The composite wing eVTOL elevator structure of claim 6, wherein, One end of the connecting rod joint (11222) is processed into a square structure, one end of the connecting rod joint (11222) is inserted into a square inner hole of the connecting rod (11223), and is fixed through a fastener (114); a circular hole for inserting the carbon pipe (1112) is formed in the inner side of the other end of the connecting rod joint (11222), and the carbon pipe (1112) is fixed on the connecting rod joint (11222) through a fastener (114).

8. The composite wing eVTOL elevator structure of claim 6, wherein, The middle support (11221) comprises a front half support (112211), a rear half support (112212) and a round sleeve (112213), the round sleeve (112213) is sleeved on the carbon pipe (1112), and the inner side of the round sleeve (112213) is bonded with the carbon pipe (1112) by structural glue; the front half support (112211) and the rear half support (112212) are fixed together by the fastener (114).

9. The composite wing eVTOL elevator structure of claim 1, wherein, The control structure (113) comprises a control support (1131) and a pull rod, the control support (1131) is fitted on the upper and lower surfaces of the rudder body (1111), and the rudder (111) is clamped in the inside of the control support (1131) by the fastener (14).

10. The method of assembling a composite wing eVTOL elevator structure of any of claims 1-9, wherein, The method comprises the following steps: Step one: take out the manufactured parts, prepare the fastener (114), and ensure that the type and length of the fastener (114) are accurate; Step two: fix the horizontal tail on the assembly tool, fix the skin (121) and the longitudinal beam (122) of the tail push (12), and bond the longitudinal beam (122) and the skin (121) together by structural glue; Step three: position the rudder axis by the assembly tool, install the front half support (112211) of the outer support (1121), the inner support (1123) and the middle support (1122) on the horizontal tail, and do not install the split pin (11213) at this time; Step four: install the outer support (1121) and the inner support (1123) in the same way, bond the support sleeve (11214) and the outer rudder (111) together, bond the round sleeve (112213) on the carbon pipe (1112), then fix them on the tool, pass the support shaft (11212) through the through hole two of the outer support (11211) from the outside, pass through the adjusting gasket (11215), and then pass into the inside of the support sleeve (11214); after the support shaft (11212) is aligned with the fixing hole of the split pin (11213) on the outer support (11211), install the split pin (11213), and make the carbon pipe (1112) of the outer rudder (111) with the round sleeve (112213) fit with the inner semicircular hole of the front half support (112211) of the middle support (1122); Step five: install the rear half support (112212) on the front half support (112211) by the fastener (114), and clamp the round sleeve (112213); Step six: fit the connecting rod joint (11222) on the outside of the carbon pipe (1112), pass the connecting rod (11223) into the inside of the tail push (12) through the through hole one (1221) of the longitudinal beam (122) from the inside of the tail push (12), insert the connecting rod joint (11222) into the inside of the connecting rod (11223), do not install the fastener (114) at this time, and make the connecting rod joint (11222) and the connecting rod (11223) have a distance for sliding, and then push the connecting rod (11223) to the outermost side; Step seven: install the inner rudder (111) according to the method in steps four to six, and install the control structure (113) on the rudder by the fastener (114). Step eight: fix the inner side linkage joint (11222) on the carbon tube (1112), at this time the connecting rod (11223) is outside the inner side linkage joint (11222), pull the connecting rod (11223) in along the axis, cover the inner side linkage joint (11222), align the fastener hole, install the fastener (114), at this time the installation of the composite wing eVTOL elevator is completed, the inner and outer side two control surfaces (111) are fixed together, through a servo control two control surfaces (111), realize the linkage function; Among them, steps four to six can also install the inner support (1123) first, at this time, step seven is: the outer side control surface (111) is fixed and installed according to the method of steps four to six, and the control structure (113) is installed on the control surface by the fastener (114).

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