An eVTOL aircraft aileron assembly tool

Abstract

The utility model discloses an eVTOL airplane aileron assembly frock, including aileron assembly frock main part and aileron, the aileron assembly frock main part is including pedestal, joint positioner, beam positioner, rudder angle positioner and clamping plate, the upper portion of pedestal is used for supporting the upper skin of aileron, the joint positioner, beam positioner, rudder angle positioner and clamping plate all are fixedly connected through fastener above the pedestal. The utility model discloses through aluminum alloy upper skin support block and aileron upper skin close adhesion position, cooperate end clamping plate and middle clamping plate to the compaction positioning of lower skin key area, and clamping plate all are according to lower skin shape face CNC milling cutting processing, effectively solved the problem that the present frock is insufficient to the aileron upper and lower surface profile precision guarantee, makes upper skin aerodynamic profile tolerance extremely small, lower skin key position precision stability, and overall profile precision improves significantly, ensures that aileron actual aerodynamic force and design value height is in accord with.

Description

Technical Field

[0001] This utility model relates to the field of eVTOL aircraft aileron assembly technology, specifically to an eVTOL aircraft aileron assembly tooling. 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 the 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] Because eVTOL aircraft have multiple motor arm structures and large-mass equipment such as motors and propellers on the motor arm structures that are far from the aircraft's plane of symmetry, their rotational inertia is relatively large. When the eVTOL aircraft is in level flight, the device that controls the roll of the eVTOL aircraft is the aileron. The roll attitude of the eVTOL aircraft is changed by differential deflection of the aileron. In order to meet the requirements of the large rotational inertia of the eVTOL aircraft to have good roll control characteristics, the area of ​​the aileron is generally larger than that of traditional general aviation aircraft.

[0004] Due to manufacturing tolerances, the actual aileron installed on the eVTOL aircraft deviates somewhat from the theoretical state of the eVTOL aircraft. Since the aileron has a large area, a large deviation will seriously affect the roll performance of the eVTOL aircraft. Therefore, during manufacturing, it is necessary to strictly control the precision of the eVTOL aircraft, ensure the accuracy of the aileron profile, and make the actual aerodynamic force generated by the aileron close to the theoretical position. At the same time, it is also necessary to ensure the distance between the aileron rotation axis and the rudder angle mounting point, so that the control law of the aileron deviates from the design as little as possible.

[0005] Chinese utility model patent application number 202223440720.9 discloses "an assembly fixture for an aircraft aileron," comprising a fixture frame, a front beam positioning mechanism, a side rib positioning mechanism, a hinge positioning mechanism, a control system connection joint positioning mechanism, and a skin positioning mechanism. The fixture frame includes a frame portion and a support portion, with the frame portion positioned on top of the support portion. The front beam positioning mechanism is located on the frame portion, the side rib positioning mechanism is located on the frame portion of the fixture frame, the hinge positioning mechanism is located on the frame portion of the fixture frame, and the control system connection joint positioning mechanism is located on the frame portion of the fixture frame. The skin positioning mechanism includes an external clamping plate assembly and a skin lifting and positioning assembly. This utility model precisely positions each part during assembly, improving assembly accuracy. Furthermore, the positioning method using positioning screws and nuts is simple and fast, simplifying the positioning process and improving the assembly efficiency of the aircraft aileron.

[0006] The Chinese utility model patent application number 202223440720.9, entitled "An assembly fixture for an aircraft aileron," arranges positioning plates, connecting plates, etc. around the perimeter of the frame to assemble the aileron, ensuring the accuracy of the positions of aileron spars, ribs, joints, etc. However, for the accuracy of the upper and lower surfaces of the aileron, the number of plates is small, and the surface accuracy of the airfoil is not guaranteed by the plates. The accuracy of the upper and lower surfaces of the aileron is a key factor affecting the aileron's aerodynamics. This will lead to a large change in the aileron's aerodynamic lift compared to the design, affecting the aircraft's roll control accuracy. Utility Model Content

[0007] To address the problems mentioned in the background art, the purpose of this utility model is to provide an eVTOL aircraft aileron assembly fixture, which has the advantages of high surface accuracy, precise positioning, and facilitates precise aileron control. It solves the problems of insufficient accuracy guarantee for the upper and lower surfaces of the aileron, insufficient number of clamping plates, resulting in large deviations between the aileron aerodynamic lift and the design, which affects the accuracy of aircraft roll control.

[0008] To achieve the above objectives, this utility model provides the following technical solution: an aileron assembly fixture for an eVTOL aircraft, comprising an aileron assembly fixture body and an aileron.

[0009] The main body of the aileron assembly fixture includes a base, a joint positioning device, a beam positioning device, a rudder angle positioning device, and a clamping plate. The upper part of the base is used to support the upper skin of the aileron. The joint positioning device, beam positioning device, rudder angle positioning device, and clamping plate are all fixedly connected to the upper part of the base by fasteners. The clamping plate is clamped on the outer side of the lower skin of the aileron. The clamping plate cooperates with the base to press the aileron, so as to achieve precise assembly of the aileron.

[0010] The base includes an upper skin support block, a support frame, and reference points. The upper skin support block (111) is an integrally milled aluminum alloy structure. The profile of the upper skin support block is adapted to the theoretical shape of the aileron upper skin. The support frame is used to support the upper skin support block. There are four reference points, and the positions of the four reference points are respectively set at the four corners of the top of the support frame. The four reference points are used to locate the installation positions of the joint positioning device, beam positioning device, rudder angle positioning device, and clamping plate.

[0011] The clamping plate includes an end clamping plate and a middle clamping plate; both the end clamping plate and the middle clamping plate are fixed to the base by bolts. The end clamping plate is used to position the end ribs and compact the end area of ​​the lower skin, and the middle clamping plate is used to compact the middle area of ​​the lower skin.

[0012] As a preferred embodiment of this utility model, the connector positioning device is fixedly connected to the base through a common connecting block. One side of the connector positioning device is provided with a connector positioning pin that is adapted to the aileron connector hole. The connector positioning pin is precisely positioned according to the reference point and theoretical data to ensure the accuracy of the aileron pivot.

[0013] As a preferred embodiment of this utility model, there are two beam positioning devices, which are respectively fixed in the inner areas at both ends of the base. Each beam positioning device includes a beam positioning block and a beam positioning pin. The beam positioning blocks of the two beam positioning devices are on the same plane and are used to fit the web plane of the beam. The beam positioning pin is adapted to the positioning hole on the beam to ensure the installation accuracy and aileron strength of the beam.

[0014] As a preferred embodiment of this utility model, the rudder angle positioning device includes a rudder angle positioning block and a rudder angle positioning pin; the rudder angle positioning block is used to position the motion plane of the rudder angle so that it moves in the same plane as the control rod, thereby reducing deflection; the size of the rudder angle positioning pin is adapted to the connecting hole on the rudder angle, and it is precisely positioned by the reference point on the base to ensure the accuracy of the transmission ratio of the aileron control.

[0015] As a preferred embodiment of this utility model, the end plate includes an end rib stop block, a skin plate, an upper skin positioning block, and a lower skin positioning block. The surface of the end rib stop block is provided with a stepped plane adapted to the end rib for positioning the end rib. The upper skin positioning block and the lower skin positioning block are used in conjunction with the skin plate, and the upper skin positioning block and the lower skin positioning block are used for upper skin assembly positioning and lower skin assembly positioning, respectively.

[0016] As a preferred embodiment of this utility model, the position of the central clamping plate corresponds to the position of the inner rib of the aileron. During assembly, the height can be adjusted according to the requirements to compact the structural adhesive between the rib and the upper skin. After the lower skin is bonded to the rib, the central clamping plate returns to the theoretical position on the outer side of the lower skin, applying pressure and positioning to the lower skin.

[0017] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0018] 1. This utility model uses an aluminum alloy upper skin support block to tightly fit and position the upper skin of the aileron, and uses end plates and middle plates to compact and position the key areas of the lower skin. The plates are all CNC milled on the outer surface of the lower skin, which effectively solves the problem of insufficient surface accuracy of the upper and lower surfaces of the aileron in existing tooling. This results in extremely small aerodynamic surface tolerance of the upper skin, stable accuracy of key positions of the lower skin, and significantly improved overall surface accuracy, ensuring that the actual aerodynamic force of the aileron is highly consistent with the design value.

[0019] 2. This utility model uses the four corner reference points of the base as a unified reference, combined with the laser tracker for precise positioning of the joint positioning device, the rudder angle positioning device for rudder angle positioning, and the beam positioning block and beam positioning pin of the beam positioning device. This ensures the accuracy of the aileron pivot, the beam's stress position, and the rudder angle movement plane and connection hole. It also minimizes the distance tolerance between the aileron rotation axis and the rudder angle connection hole axis. At the same time, the upper and lower skin positioning blocks of the end plate can be used selectively, and the middle plate can adjust the compaction of the structural adhesive. This not only simplifies the tooling structure and reduces costs, but also improves the bonding quality and assembly efficiency. Ultimately, it ensures that the aileron control transmission ratio deviates from the design value by a very small margin, meeting the precise roll control requirements of eVTOL aircraft under large rotational inertia. Attached Figure Description

[0020] Figure 1 This is an isometric view of the structure of this utility model;

[0021] Figure 2 This is an exploded view of the structure of this utility model;

[0022] Figure 3 This is an axonometric view of the base of this utility model;

[0023] Figure 4 This is an exploded view of the base of this utility model;

[0024] Figure 5 This is an isometric view of the card plate of this utility model;

[0025] Figure 6 This is an isometric view of the end plate of this utility model;

[0026] Figure 7 This is an isometric view of the central clamping plate and joint positioning device of this utility model;

[0027] Figure 8 This is an isometric view of the beam positioning device of this utility model;

[0028] Figure 9 This is an isometric view of the rudder angle positioning device of this utility model.

[0029] In the diagram: 1. Main body of aileron assembly fixture; 11. Base; 111. Upper skin support block; 112. Support frame; 113. Reference point; 121. Joint positioning device; 1211. Joint positioning pin; 122. Beam positioning device; 1221. Beam positioning block; 1222. Beam positioning pin; 123. Rudder angle positioning device; 1231. Rudder angle positioning block; 1232. Rudder angle positioning pin; 13. Clamping plate; 131. End clamping plate; 1311. End rib block; 1312. Skin clamping plate; 1313. Upper skin positioning block; 1314. Lower skin positioning block; 132. Middle clamping plate; 2. Aileron. Detailed Implementation

[0030] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0031] like Figures 1 to 9 As shown, this utility model provides an aileron assembly fixture for an eVTOL aircraft, comprising an aileron assembly fixture body 1 and an aileron 2. The aileron 2 is composed of upper skin, lower skin, beams, ribs, joints, control angles, and other parts. The aileron 2 can be inverted on the aileron assembly fixture body 1 for assembly. The lower part of the aileron assembly fixture body 1 corresponds to the upper skin support structure of the aileron 2, realizing the precise assembly of the various parts of the aileron 2.

[0032] The main body 1 of the aileron assembly fixture includes a base 11, a joint positioning device 121, a beam positioning device 122, a rudder angle positioning device 123, and a clamping plate 13. The upper part of the base 11 is used to support the upper skin of the aileron 2. The joint positioning device 121, the beam positioning device 122, the rudder angle positioning device 123, and the clamping plate 13 are all fixedly connected to the upper part of the base 11 by fasteners. The clamping plate 13 is clamped on the outer side of the lower skin of the aileron 2. The clamping plate 13 cooperates with the base 11 to press the aileron 2, ensuring the stability of the position of each part during the assembly process and realizing the precise assembly of the aileron 2.

[0033] The base 11 includes an upper skin support block 111, a support frame 112, and a reference point 113. The upper skin support block 111 is an integrally milled aluminum alloy support structure with high machining precision. Its profile is perfectly matched with the theoretical shape of the upper skin of the aileron 2. During assembly, the upper skin support block 111 fits tightly with the upper skin, providing high-precision assembly profile support for the upper skin and ensuring the aerodynamic performance accuracy of the upper skin. The support frame 112 is welded from steel profiles and has sufficient structural strength and stability to firmly support the upper skin support block. 111, while providing operating space for assembly workers; there are four reference points 113, and the four reference points 113 are respectively set at the four corners of the top of the support frame 112. When assembling the main body of the aileron assembly fixture 1, the four reference points 113 are used as references. The installation positions of the laser tracker positioning joint positioning device 121, beam positioning device 122, rudder angle positioning device 123 and clamping plate 13 are used to ensure the relative position accuracy of all positioning components, thereby ensuring the accuracy of the aileron 2's rotating shaft, rudder angle connection point and profile.

[0034] The clamping plate 13 includes an end clamping plate 131 and a middle clamping plate 132. Both the end clamping plate 131 and the middle clamping plate 132 are fixed to the base 11 by bolts and can be quickly installed and removed by a snap-fit ​​pin. When assembling, inserting the snap-fit ​​pin can lock the position of the clamping plate and ensure that the clamping plate does not shift during the compaction process. When disassembling, the clamping plate can be quickly removed by pulling out the snap-fit ​​pin without additional bolt removal, which greatly simplifies the part removal process after the aileron is assembled. The end clamping plate 131 is used to position the end ribs and compact the end area of ​​the lower skin, and the middle clamping plate 132 is used to compact the middle area of ​​the lower skin. Multi-point positioning ensures the surface accuracy of key positions of the lower skin.

[0035] refer to Figure 7 The connector positioning device 121 and the middle clamping plate 132 share a connecting block and are fixedly connected to the base 11. One side of the connector positioning device 121 is provided with a connector positioning pin 1211 that is adapted to the connector hole of the aileron 2. The connector positioning pin 1211 is precisely positioned according to the reference point 113 and theoretical data to ensure the accuracy of the aileron 2's rotating shaft, facilitate the rotation of the aileron 2, and prevent the aileron 2 from getting stuck.

[0036] As a technical optimization of this utility model, the design of the joint positioning device 121 and the middle clamping plate 132 sharing a connecting block simplifies the tooling structure, reduces the number of parts, and ensures positioning accuracy and assembly stability.

[0037] refer to Figure 8There are two beam positioning devices 122, which are fixed to the inner areas at both ends of the base 11. Each beam positioning device 122 includes a beam positioning block 1221 and a beam positioning pin 1222. The beam positioning blocks 1221 of the two beam positioning devices 122 are on the same plane and are used to fit tightly against the web plane of the beam. The beam positioning pin 1222 is adapted to the positioning hole on the beam. The double positioning ensures the installation accuracy of the beam and positions the beam in a position with greater stress, ensuring the structural strength of the aileron 2. After positioning, the beam positioning block 1221 can compact the structural adhesive bonded to the upper skin, improving the bonding quality. After positioning, the beam positioning block 1221 fits tightly against the web plane of the beam, and the beam positioning pin 1222 is inserted into the positioning hole of the beam to fix it. At this time, the adhesive surface of the beam and the upper skin is naturally pressed, the adhesive layer thickness is uniform, the bonding strength is more stable, and the overall structural strength of the aileron is avoided due to the loosening of the adhesive layer.

[0038] As a technical optimization of this utility model, the symmetrical arrangement of the double beam positioning device 122 and the combined positioning of the beam positioning block 1221 and the beam positioning pin 1222 not only ensure the positional accuracy of the beam, but also enhance the stress performance of the aileron 2, while taking into account the quality requirements of the bonding process.

[0039] refer to Figure 9 The rudder angle positioning device 123 includes a rudder angle positioning block 1231 and a rudder angle positioning pin 1232. The rudder angle positioning block 1231 is used to position the motion plane of the rudder angle so that it moves in the same plane as the control rod, thereby reducing deflection error. The size of the rudder angle positioning pin 1232 is adapted to the connecting hole on the rudder angle and is precisely positioned by the reference point 113 on the base 11. Since the rotation axis of the aileron 2 is positioned by the joint positioning pin 1211 and the axis of the rudder angle connecting hole is positioned by the rudder angle positioning pin 1232, both are precisely calibrated based on the reference point 113, so that the length tolerance between the axis of the rudder angle connecting hole and the rotation axis of the aileron 2 is extremely small, ensuring that the transmission ratio controlled by the aileron 2 is accurate and facilitating the precise control of the aileron 2.

[0040] As a technical optimization of this utility model, the coordinated positioning of the rudder angle positioning block 1231 and the rudder angle positioning pin 1232 not only ensures the motion attitude accuracy of the rudder angle, but also achieves precise control of the transmission ratio parameter through linkage with the reference point 113, thus meeting the flight control requirements of eVTOL aircraft.

[0041] refer to Figure 6The end plate 131 includes an end rib stop block 1311, a skin plate 1312, an upper skin positioning block 1313, and a lower skin positioning block 1314. The surface of the end rib stop block 1311 is provided with a stepped plane adapted to the end rib for precise positioning of the end rib and to ensure accurate positioning of the end rib. The upper skin positioning block 1313 and the lower skin positioning block 1314 are connected to the skin plate 1312 at the same position, but are not used at the same time. During assembly, the upper skin positioning block 1313 is installed first to position the upper skin on the upper skin support block 111 of the base 11, and then the beams, ribs, and skin plates are installed inside. The end ribs, joints, and other parts are positioned and glued to the upper skin. Then, the upper skin positioning block 1313 is removed and replaced with the lower skin positioning block 1314. After the ear hole of the lower skin is matched with the lower skin positioning block 1314, the end clamping plate 131 is pressed down to complete the positioning of the lower skin. The upper skin positioning block 1313 and the lower skin positioning block 1314 share the installation interface of the skin clamping plate 1312. No additional installation structure is required. When switching, only the plug pin needs to be removed for replacement. This simplifies the tooling structure, reduces the complexity of operation, and ensures the consistency of the positioning reference of the upper and lower skins.

[0042] As a technical optimization of this utility model, by selecting one of the upper skin positioning block 1313 and the lower skin positioning block 1314, the complexity of the positioning support structure is reduced and the tooling manufacturing cost is lowered while meeting the positioning requirements of different processes, and the assembly accuracy of the upper and lower skins is guaranteed.

[0043] refer to Figure 7 The central clamping plate 132 corresponds to the position of the inner rib of the aileron 2. During assembly, the height can be adjusted as needed. During the assembly stage of the upper skin and the rib, the central clamping plate 132 is adjusted downward to a position that matches the thickness of the lower skin, so that it presses the rib and the upper skin together, applying uniform pressure to the structural adhesive to achieve a compaction effect and avoid air bubbles or uneven thickness of the adhesive layer. After the adhesive has cured, the central clamping plate 132 is adjusted back to the theoretical position on the outer side of the lower skin, leaving enough operating space for the lower skin assembly, while ensuring the accuracy of the subsequent positioning of the lower skin. This not only continues to apply pressure to the structural adhesive to ensure the quality of the adhesive bonding, but also positions the lower skin at the rib position to ensure the surface accuracy of the middle area of ​​the lower skin.

[0044] As a technical optimization of this utility model, the height of the central clamping plate 132 is adjustable, which enables it to have the dual functions of structural adhesive compaction and skin positioning, simplifying the assembly process and improving the consistency of adhesive bonding quality and skin surface accuracy.

[0045] The working principle and usage process of this utility model: Before use, ensure that the base 11 of the aileron assembly fixture body 1 is in stable contact with the ground or workbench through its lower part. The support frame 112 of the base 11 is welded from steel profiles and the reference points 113 at the four corners are accurately positioned. The positioning and installation of the joint positioning device 121, beam positioning device 122, rudder angle positioning device 123, and clamping plate 13 on the base 11 have been completed by using a laser tracker. All positioning pins (including joint positioning pin 1211, beam positioning pin 1222, and rudder angle positioning pin 1232) are machined stainless steel pins with a tapered front end. The end clamping plate 131 and the middle clamping plate 132 of the clamping plate 13 are attached to the lower skin of the aileron 2. The aluminum alloy parts with CNC milled outer surfaces and the steel modules supporting the clamping plate are firmly connected to the clamping plate by fasteners or plug pins. First, the upper skin positioning block 1313 of the end clamping plate 131 is installed on the skin clamping plate 1312. Then, the upper skin of the aileron 2 is placed on the upper skin support block 111 of the base 11 and made to fit tightly. The upper skin positioning block 1313 is positioned by the engagement of the upper skin positioning hole lugs with the upper skin positioning pins. Next, the beams, ribs, end ribs, joints and other parts of the aileron 2 are placed in the preset positions in sequence. The beam positioning device 122 uses the beam positioning stop 1221 to fit tightly against the web plane of the beam and the beam positioning pin 1222 to be inserted into the positioning hole of the beam to achieve beam positioning. The end clamping plate is then used to position the beam. The stepped plane of the end rib stop block 1311 of plate 131 positions the end rib. The joint positioning is achieved by inserting the joint positioning pin 1211 of the joint positioning device 121 into the shaft hole of the joint. These parts are then glued to the upper skin. During the gluing process, the height of the middle clamping plate 132 is adjusted to press the structural adhesive between the rib and the upper skin. After the structural adhesive has initially cured, the upper skin positioning block 1313 of the end clamping plate 131 is removed by inserting and removing the pin. The lower skin positioning block 1314 is then installed and replaced. The lower skin of the aileron 2 is positioned by engaging the lower skin positioning block 1314 with the pin through the ear hole. Then, the end clamping plate 131 is pressed down and the middle clamping plate 132 is compacted, so that the middle clamping plate 132 returns to the outside of the lower skin. The position applies pressure to the lower skin, and simultaneously applies pressure to the structural adhesive between the lower skin and the rib. During this process, the rudder angle positioning block 1231 of the rudder angle positioning device 123 positions the motion plane of the rudder angle, and the rudder angle positioning pin 1232 is inserted into the rudder angle connection hole to achieve rudder angle positioning. Both the rudder angle positioning pin 1232 and the joint positioning pin 1211 are precisely positioned based on the reference point 113 of the base 11 to ensure the accuracy of the distance between the rotation axis of the aileron 2 and the axis of the rudder angle connection hole. After the lower skin is glued to other parts, the end clamping plate 131 and the middle clamping plate 132 are removed by inserting and pulling pins, the relevant fasteners are loosened, and the assembled aileron 2 is removed from the aileron assembly fixture body 1 to complete the entire assembly process.

[0046] It is worth noting that all the clamping plates (including the end clamping plate 131 and the middle clamping plate 132) are CNC milled according to the outer surface of the lower skin. The clamping plate 13 is made of aluminum alloy, which not only ensures structural strength and surface accuracy, but also has the advantage of lightweight. The modules supporting the clamping plates are made of steel and are connected and fixed to the clamping plate 13 by fasteners or plug pins to ensure a stable and reliable connection. All the positioning pins (including the joint positioning pin 1211, the beam positioning pin 1222, and the rudder angle positioning pin 1232) are machined stainless steel pins, and the tapered structure at the front can play a guiding role. When positioning parts, the tapered structure can guide the positioning pins to be quickly and accurately inserted into the positioning holes of the parts, reducing the assembly difficulty and improving the assembly efficiency. At the same time, the stainless steel material ensures the wear resistance and service life of the positioning pins, ensuring the stability of positioning accuracy during long-term use.

[0047] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0048] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An aileron assembly fixture for an eVTOL aircraft, comprising an aileron assembly fixture body (1) and an aileron (2), characterized in that: The main body (1) of the aileron assembly fixture includes a base (11), a joint positioning device (121), a beam positioning device (122), a rudder angle positioning device (123), and a clamping plate (13). The upper part of the base (11) is used to support the upper skin of the aileron (2). The joint positioning device (121), the beam positioning device (122), the rudder angle positioning device (123), and the clamping plate (13) are all fixedly connected to the upper part of the base (11) by fasteners. The clamping plate (13) is clamped on the outer side of the lower skin of the aileron (2). The clamping plate (13) cooperates with the base (11) to press the aileron (2) to achieve precise assembly of the aileron (2). The base (11) includes an upper skin support block (111), a support frame (112), and reference points (113). The surface of the upper skin support block (111) is adapted to the theoretical shape of the upper skin of the aileron (2). The support frame (112) is used to support the upper skin support block (111). There are four reference points (113), and the positions of the four reference points (113) are respectively set at the four corners of the top of the support frame (112). The four reference points (113) are used to locate the installation positions of the joint positioning device (121), the beam positioning device (122), the rudder angle positioning device (123), and the clamping plate (13). The clamping plate (13) includes an end clamping plate (131) and a middle clamping plate (132); both the end clamping plate (131) and the middle clamping plate (132) are fixed to the base (11) by bolts. The end clamping plate (131) is used to position the end ribs and compact the end area of ​​the lower skin, and the middle clamping plate (132) is used to compact the middle area of ​​the lower skin.

2. The aileron assembly fixture for an eVTOL aircraft according to claim 1, characterized in that: The joint positioning device (121) is fixedly connected to the base (11) through a common connecting block. A joint positioning pin (1211) adapted to the joint hole of the aileron (2) is provided on one side of the joint positioning device (121). The joint positioning pin (1211) is precisely positioned according to the reference point (113) and theoretical data to ensure the rotation accuracy of the aileron (2).

3. The eVTOL aircraft aileron assembly fixture according to claim 1, characterized in that: There are two beam positioning devices (122). The two beam positioning devices (122) are fixed in the inner area at both ends of the base (11). The beam positioning device (122) includes a beam positioning block (1221) and a beam positioning pin (1222). The beam positioning blocks (1221) of the two beam positioning devices (122) are on the same plane and are used to fit the web plane of the beam. The beam positioning pin (1222) is adapted to the positioning hole on the beam to ensure the installation accuracy of the beam and the strength of the aileron (2).

4. The aileron assembly fixture for an eVTOL aircraft according to claim 1, characterized in that: The rudder angle positioning device (123) includes a rudder angle positioning block (1231) and a rudder angle positioning pin (1232). The rudder angle positioning block (1231) is used to position the motion plane of the rudder angle so that it moves in the same plane as the control rod, thereby reducing deflection. The size of the rudder angle positioning pin (1232) is adapted to the connecting hole on the rudder angle and is precisely positioned by the reference point (113) on the base (11) to ensure the accurate transmission ratio controlled by the aileron (2).

5. The aileron assembly fixture for an eVTOL aircraft according to claim 1, characterized in that: The end plate (131) includes an end rib stop (1311), a skin plate (1312), an upper skin positioning block (1313), and a lower skin positioning block (1314). The surface of the end rib stop (1311) is provided with a stepped plane adapted to the end rib for positioning the end rib. The upper skin positioning block (1313) and the lower skin positioning block (1314) are used in conjunction with the skin plate (1312), and the upper skin positioning block (1313) and the lower skin positioning block (1314) are used for upper skin assembly positioning and lower skin assembly positioning, respectively.

6. The aileron assembly fixture for an eVTOL aircraft according to claim 1, characterized in that: The position of the central clamping plate (132) corresponds to the position of the inner rib of the aileron (2). The height can be adjusted according to the requirements during assembly. It plays a role in compacting the structural adhesive between the rib and the upper skin. After the lower skin is glued to the rib, the central clamping plate (132) returns to the theoretical position on the outer side of the lower skin, pressurizes the lower skin and positions it.

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