CN218258680U - EVTOL aircraft wing connection structure - Google Patents
EVTOL aircraft wing connection structure Download PDFInfo
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- CN218258680U CN218258680U CN202222416947.3U CN202222416947U CN218258680U CN 218258680 U CN218258680 U CN 218258680U CN 202222416947 U CN202222416947 U CN 202222416947U CN 218258680 U CN218258680 U CN 218258680U
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- fairing
- central wing
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Abstract
The utility model discloses an eVTOL aircraft wing connecting structure, which comprises wings, a fairing and a central wing, wherein the central wing and the wings are connected with the two sides of the fairing along the chord direction, and the central wing is connected with the wings; the wing includes wing spar assembly, be connected with the wing covering on the wing spar assembly, the central wing includes central wing skeleton, be connected with central wing covering on the central wing skeleton, wing spar assembly and central wing skeleton are passed through coupling assembling and are connected at the middle part of radome fairing, the radome fairing is connected with central wing covering to wing covering. This structural security is high: the single connecting point of the wing and the central wing adopts the connection of three ears to two ears, and the wing beam assembly is formed by combining a plurality of parts, so that when a certain part fails, the wing beam assembly still can bear larger load, and the safety is higher.
Description
Technical Field
The utility model relates to an aviation technical field, concretely relates to eVTOL aircraft wing connection structure.
Background
The development of eVTOL (Electric Vertical take off and Landing) Electric Vertical take off and Landing aircraft has attracted a wide range of concerns including aerospace, automotive, transportation, government, military and academic communities. The potential future applications of the eVTOL relate to various scene modes of urban passenger transport, regional passenger transport, freight transport, personal aircraft, emergency medical services, and the like. The united states vertical flight association considers that eVTOL technology is one of the most important technological changes in the aviation industry since the birth of helicopters 75 years ago, and is likely to be more revolutionary than the advent of turbine engines. According to the world electric vertical take-off and landing (eVTOL) aircraft catalog published by the association on-line, more than 260 items are currently being developed globally for eVTOL. The use of an electric propulsion system instead of an internal combustion engine power achieves many advantages and unique qualities. The most outstanding advantages are energy saving, environmental protection, high efficiency, low energy consumption, near zero emission, low noise and vibration level, good riding comfort and being a real environment-friendly airplane. In addition, the device has the characteristics of safety, reliability (no explosion and fuel leakage), simple structure, convenience in operation and use, good maintainability, low cost, good economy and the like. The overall layout is flexible, and the optimal layout and the unconventional/innovative layout can be adopted; the airplane with extraordinary performance can be designed to meet the requirements of special purposes, and the like.
The eVTOL can be divided into three types of multi-rotor wings, composite wings and tilt wings, and for the eVTOL aircraft with the composite wings and the tilt wings, the wings are the parts of the whole eVTOL aircraft with the largest stress and are also one of important safety parts. Considering the conditions of manufacturing size, maintenance requirements, transportation requirements, etc., the individual components of an eVTOL aircraft are not necessarily too large and therefore need to be separated and connected. The wing needs to be connected to the fuselage, and the current main connection form is lug formula, to inserting formula, hangs down connection structure such as formula. And central spar and outer spar among the formula connection structure of inserting are mostly single part, and the moment of flexure on the balanced spar of two tie points of single roof beam. The damage tolerance is poor, when a single beam and a single connecting point fail, the whole connecting structure can not balance the bending moment of the wing to cause damage, and further the flight safety of the whole machine is affected, for example, patent CN201720704404.8.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an eVTOL aircraft wing connection structure to solve the problem of mentioning in the background art. In order to achieve the above object, the utility model provides a following technical scheme: an eVTOL aircraft wing attachment structure comprising an airfoil, a fairing and a center wing, the center wing and the airfoil being attached to either side of the fairing along a chord direction, the center wing being attached to the airfoil;
the wing includes the wing spar assembly, be connected with the wing covering on the wing spar assembly, the central wing includes central wing skeleton, be connected with central wing covering on the central wing skeleton, wing spar assembly and central wing skeleton pass through coupling assembling at the middle part of fairing and connect, the fairing is connected to wing covering and central wing covering.
Preferably, the wing beam assembly comprises two groups of wing beams which are connected through a connecting beam.
Preferably, the wing beam comprises a beam body, a reinforcing short beam, a first joint and a second joint, the reinforcing short beam is mounted on the side edge of the beam body through a fastener, the end parts of the beam body and the reinforcing short beam are respectively connected with the second joint and the first joint through fasteners, and the second joint and the first joint form a double-lug structure.
Preferably, both sides of the end part of the central wing framework are provided with connecting parts, the connecting parts are of three-lug structures, the two-lug structures formed by connecting the second joint and the first joint through the connecting assembly are connected, and the first joint and the second joint leave sacrificial allowance at lug positions connected with the connecting parts of the central wing framework.
Preferably, the fairing is larger at the front and rear in the chordwise direction and smaller at the middle, and the fairing is connected with the wing and the central wing by a screw + pallet nut connection, the pallet nut is mounted inside the wing skin and the central wing skin, and the screws mount the fairing on the central wing skin and the wing skin.
Preferably, the connecting assembly comprises a bolt and a nut, wherein gaskets are respectively arranged below the bolt and the nut in a cushioning mode, the nut is of a double-nut structure, and the threads of the two nuts are the threads in the positive and negative directions.
Preferably, the fairing is of a carbon fiber composite material foam sandwich structure, and the beam body and the reinforcing short beam are of carbon fiber composite material structures.
The utility model discloses a technological effect and advantage: this structural security is high: the single connecting point of the wing and the central wing adopts the connection of three ears to two ears, and the wing beam assembly is formed by combining a plurality of parts, so that when a certain part fails, the wing beam assembly can still bear larger load, and the safety is higher;
the maintenance is convenient: the fairing is of a detachable structure, the occupied area of the fairing is large, a channel can be conveniently provided for mounting and dismounting the connecting assembly after the fairing is dismounted, and the maintainability is good;
the locking effect is good: the outer end of the bolt of the connecting component is connected by double nuts, and the thread sequence of the two nuts is in opposite directions, so that the problem that the nuts are loosened due to vibration in the flying process can be effectively solved after the connecting component is installed, and the anti-loosening effect is good;
easy assembly: the beam body, the reinforcing short beam, the first joint and the second joint of the wing beam assembly are connected with the three ears of the central wing framework after combination, and through designing the sacrificial allowance on the first joint and the second joint, when the wing beam assembly cannot be assembled due to tolerance accumulation, the sacrificial allowance of the first joint and the second joint can be machined and removed, so that the purpose of good assembly is achieved.
Drawings
Fig. 1 is an isometric view of the present invention on an eVTOL aircraft;
fig. 2 is an isometric view of the present invention;
FIG. 3 is an exploded view of the present invention;
FIG. 4 is a perspective view of a wing spar assembly and a central wing frame connecting shaft of the present invention;
fig. 5 is an isometric view of a wing spar of the present invention;
fig. 6 is a cross-sectional view of the wing and center wing of the present invention at the connection assembly.
In the figure: 1. a wing connection structure; 11. an airfoil; 111. a wing beam assembly; 1111. a beam body; 1112. reinforcing the short beam; 1113. a first joint; 1114. a second joint; 1115. a fastener; 112. a connecting assembly; 1121. a bolt; 1122. a nut; 1123. a gasket; 113. a connecting beam; 114. a wing skin; 12. a cowling; 13. a central wing; 131. a central wing framework; 132. a center wing skin; an eVTOL airplane.
Detailed Description
In order to make the technical means, creation features, objects and functions of the present invention easy to understand, the present invention will be further explained with reference to the specific drawings, and in the description of the present invention, unless otherwise specified or limited, the terms "mounted", "connected" and "connected" should be understood broadly, for example, they may be fixedly connected, detachably connected, integrally connected or mechanically connected, or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements.
Examples
As shown in fig. 1, the wing connection structure 1 is at a position where the wings of the eVTOL aircraft are combined with the fuselage, the upper portion of the fuselage is a central wing 13, both the left and right sides of the central wing 13 are connected with the wings 11, in this example, only the left side is shown, and the right side is symmetrical to the left side connection structure. Here, the stressed joint point of the whole eVTOL aircraft 2 is a safety area important for the whole aircraft, and once the eVTOL aircraft fails, a safety accident which may cause damage to the aircraft and death of people needs to be ensured, so that the reliability and the safety of connection are ensured.
As shown in fig. 2 and 3, the wing connection structure 1 includes wings 11, a fairing 12 and a center wing 13, the center wing 13 and the wings 11 are connected with both sides of the fairing 12 along the chord direction, the center wing 13 and the wings 11 are connected with the middle of the fairing 13, the fairing 12 is larger at the front part and the rear part along the chord direction and smaller at the middle part, a space is provided for disassembling the connection assembly 112 between the center wing 13 and the wings 11, only a space for placing tools is required at the middle area, and an operation space for rotating the tools is provided at the front part and the rear part, so that the front part and the rear part require larger spaces. The wings 11 and the central wing 13 are important safety components of the eVTOL aircraft and bear the great loads of the eVTOL. The fairing 12 is of a carbon fiber composite material foam sandwich structure, has high rigidity and maintains the appearance of the eVTOL aircraft, the connection of the fairing 12 with the wings 11 and the central wing 13 adopts a screw and supporting plate nut connection mode, the supporting plate nut is installed inside the central wing skin 132 and the wing skin 114, the fairing 12 is installed on the central wing skin 132 and the wing skin 114 through screws, and during disassembly, the disassembly of the fairing 12 can be completed only by externally disassembling the screws.
As shown in fig. 4, the connection between the wing 11 and the center wing 13 is mainly by the inner frame, and the outer center wing skin 132 and the wing skin 114 are disconnected at the position of the fairing 12, so that when disassembling, the separation between the wing 11 and the center wing 13 can be completed by only disassembling the four connection components, thereby reducing the disassembling time. The wing 11 comprises a wing spar assembly 111, a wing skin 114 is mounted on the wing spar assembly 111, the central wing 13 comprises a central wing framework 131, a central wing skin 132 is mounted on the central wing framework 131, the connection between the central wing 13 and the wing 11 mainly comprises the wing spar assembly 111, a connecting component 112 and the central wing framework 131, the wing spar assembly 111 and the central wing framework 131 are connected together through the connecting component 112, and all forces of the wing 11 are transmitted to the central wing framework 131 through the wing spar assembly 111 and the connecting component 112 to complete transmission of the transmission force.
As shown in fig. 5, the wing beam assembly 111 includes two groups of wing beams, which are connected by a connecting beam 113, and each wing beam includes a beam body 1111, a reinforcing short beam 1112, a first joint 1113 and a second joint 1114, the reinforcing short beam 1112 is mounted on the side of the beam body 1111 by a fastener 1115, and the ends of the beam body 1111 and the reinforcing short beam 1112 are connected to the second joint 1114 and the first joint 1113 by fasteners 1115 respectively. Since the skin intermediate the wing 11 and the center wing 13 is broken, the skin does not transmit forces, and all forces are transmitted through the wing spar assembly 11, so that the forces on the skin are all transmitted to the connection area, and the stiffening stub 1112 is added to transmit the forces transmitted by the skin. Roof beam body 1111 supports the main atress of wing 11 with strengthening stub beam 1112 together, for the carbon-fibre composite structure, because the carbon-fibre composite characteristic, the preparation auricle structure degree of difficulty is great, adopt first joint 1113 and second to connect 1114 and carry out transitional coupling, first joint 1113 and second connect 1114 can be for materials such as aluminum alloy, stainless steel, high strength steel, titanium alloy, according to the weight design such as space, atress size, weight and cost, what this example chooseed for use is stainless steel. First joint 1113 and second joint 1114 leave a sacrificial margin (extra thickness) at the tab position connected to center rib 131 when designing, and when subsequently assembling, due to the fit problem caused by tolerance reasons, the purpose of easy assembling can be achieved by repairing the sacrificial margin.
As shown in fig. 6, both sides of the end of the central wing framework 131 are provided with joints, the joints are of three-lug structures, and are of integrally machined metal structures, in this example, aluminum alloy structures, the wing 11 side is provided with two-lug structures formed by the first joint 1113 and the second joint 1114, the two-lug structures are connected together through the connecting assembly 112, the connecting assembly 112 comprises bolts 1121, since the diameter of the bolts 1121 is large at this position, a large tightening torque is required to ensure the connection reliability, in order to prevent the surfaces of the parts from being scratched when the bolts 1121 are tightened, gaskets 1123 are respectively padded below the bolts 1121 and the nuts 1122, the parts are isolated, and the surfaces of the parts are prevented from being scratched. The nut 1122 adopts a double-nut structure, and the threads of the two nuts 1122 are threads in the positive and negative directions, so that the looseness at the position is prevented after the two nuts are screwed, and a good anti-loosening effect is achieved. During design, the three ears and the double ears are matched and connected, except for the design of sacrifice allowance of the first joint 1113 and the second joint 1114, a tiny gap is reserved between the ears, the installation is convenient, and the optimal gap is 0.2mm.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications and variations can be made in the embodiments or in part of the technical features of the embodiments without departing from the spirit and the scope of the invention.
Claims (7)
1. An eVTOL aircraft wing connection structure, including wing, radome and central wing, its characterized in that: the central wing and the wings are connected with two sides of the fairing along the chord direction, and the central wing is connected with the wings;
the wing includes the wing spar assembly, be connected with the wing covering on the wing spar assembly, the central wing includes central wing skeleton, be connected with central wing covering on the central wing skeleton, wing spar assembly and central wing skeleton pass through coupling assembling at the middle part of fairing and connect, the fairing is connected to wing covering and central wing covering.
2. An eVTOL aircraft wing attachment structure as claimed in claim 1, wherein: the wing beam assembly comprises two groups of wing beams which are connected through connecting beams.
3. The eVTOL aircraft wing attachment structure of claim 2, wherein: the wing beam comprises a beam body, a reinforcing short beam, a first joint and a second joint, wherein the reinforcing short beam is installed on the side edge of the beam body through a fastener, the second joint and the first joint are connected with the end portion of the beam body and the end portion of the reinforcing short beam through fasteners respectively, and the second joint and the first joint form a double-lug structure.
4. An eVTOL aircraft wing attachment structure as claimed in claim 3, wherein: the utility model discloses a wing skeleton of central authorities 'both sides all are equipped with the junction, the junction is three ears structure, and connects the second through coupling assembling and connect the two ears structure that form with the first joint, the first joint leaves the sacrifice surplus in the auricle position of being connected with the junction of central authorities' wing skeleton with the second joint.
5. An eVTOL aircraft wing attachment structure as claimed in claim 1, wherein: the fairing is larger at the front part and the rear part in the chord direction and smaller at the middle part, the connection of the fairing with the wing and the central wing adopts a screw and supporting plate nut connection mode, the supporting plate nut is installed inside the wing skin and the central wing skin, and the fairing is installed on the central wing skin and the wing skin through screws.
6. An eVTOL aircraft wing attachment structure as claimed in claim 1, wherein: the connecting assembly comprises a bolt and a nut, gaskets are respectively arranged below the bolt and the nut in a cushioning mode, the nut is of a double-nut structure, and the threads of the two nuts are in the positive and negative directions.
7. The eVTOL aircraft wing attachment structure of claim 3, wherein: the fairing is of a carbon fiber composite material foam sandwich structure, and the beam body and the reinforcing short beam are of carbon fiber composite material structures.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222416947.3U CN218258680U (en) | 2022-09-13 | 2022-09-13 | EVTOL aircraft wing connection structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222416947.3U CN218258680U (en) | 2022-09-13 | 2022-09-13 | EVTOL aircraft wing connection structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218258680U true CN218258680U (en) | 2023-01-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222416947.3U Active CN218258680U (en) | 2022-09-13 | 2022-09-13 | EVTOL aircraft wing connection structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218258680U (en) |
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2022
- 2022-09-13 CN CN202222416947.3U patent/CN218258680U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: A wing connection structure for eVTOL aircraft Effective date of registration: 20230529 Granted publication date: 20230110 Pledgee: Industrial Bank Co.,Ltd. Shanghai Branch Pledgor: Shanghai wollant Aviation Technology Co.,Ltd. Registration number: Y2023310000218 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20230914 Granted publication date: 20230110 Pledgee: Industrial Bank Co.,Ltd. Shanghai Branch Pledgor: Shanghai wollant Aviation Technology Co.,Ltd. Registration number: Y2023310000218 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: A wing connection structure for eVTOL aircraft Effective date of registration: 20230920 Granted publication date: 20230110 Pledgee: Industrial Bank Co.,Ltd. Shanghai Minhang sub branch Pledgor: Shanghai wollant Aviation Technology Co.,Ltd. Registration number: Y2023310000570 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Granted publication date: 20230110 Pledgee: Industrial Bank Co.,Ltd. Shanghai Minhang sub branch Pledgor: Shanghai wollant Aviation Technology Co.,Ltd. Registration number: Y2023310000570 |