CN218463867U - eVTOL aircraft landing gear connecting structure - Google Patents
eVTOL aircraft landing gear connecting structure Download PDFInfo
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- CN218463867U CN218463867U CN202222238435.2U CN202222238435U CN218463867U CN 218463867 U CN218463867 U CN 218463867U CN 202222238435 U CN202222238435 U CN 202222238435U CN 218463867 U CN218463867 U CN 218463867U
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- baffle
- landing gear
- joint
- undercarriage
- frame
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Abstract
The utility model discloses an eVTOL aircraft undercarriage connection structure, including connecting and baffle, connect and the baffle mounting is on the undercarriage, the baffle is located the below that connects, undercarriage and baffle are connected through the fastener to the baffle, the carriage lower extreme is all connected to the upper end both sides that connect and the both sides of baffle, the fuselage is connected to the carriage upper end. This structural security is high: the undercarriage is not easy to fall off due to the adoption of the encircling connection mode, the front connection part and the rear connection part in the machine body are connected by adopting a double-frame structure, the stress of the undercarriage can be uniformly transmitted to the two frames, the stress of a single frame is reduced, the undercarriage is not easy to damage, and the safety is high; connect reliably, prevent mistake and tear open: the double lugs are designed to be used as the joints connected with the hinges in the direct machining on the frame, so that the two joints are saved, meanwhile, the double lugs and the frame are formed in the direct machining, the precision is high, an outer joint assembling tool is not needed, and the cost is lower.
Description
Technical Field
The utility model relates to an aeronautical technical field, concretely relates to eVTOL aircraft undercarriage 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 application of the eVTOL relates to various scene modes such as urban passenger transport, regional passenger transport, freight transport, personal aircrafts and emergency medical service. The united states vertical flight consortium believed that eVTOL technology was 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 online release of the world electric vertical take-off and landing (eVTOL) aircraft catalog by the association, more than 260 items are currently engaged in the development of eVTOL globally. 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. There are also many advantages in design: 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 landing gear is used as a support for an eVTOL aircraft in the processes of taking off and landing and bears the impact in landing, and investigation shows that 70% of accidents of the aircraft occur in the stage of taking off and landing, so the landing gear is one of the most important parts for protecting the safety of passengers, the reliability of the connection between the landing gear and the aircraft body has a large influence on the landing safety of the aircraft, and therefore the landing gear connection structure needs to be considered seriously. The existing undercarriage connecting mechanism has more parts, misoperation is easily caused in the actual use process, the connecting structure is loosened, the reliability of undercarriage connection is influenced, and the flight safety is further influenced. And in field maintenance, there is also a problem that small parts are lost, for example, patent CN201410425019.0.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an eVTOL aircraft undercarriage connection structure to solve the problem of mentioning in the background art. In order to achieve the above purpose, the utility model provides a following technical scheme: the utility model provides an eVTOL aircraft undercarriage connection structure, includes and connects and the baffle, connect and the baffle mounting is on the undercarriage, the baffle is located the below that connects, undercarriage and baffle are connected through the fastener to the baffle, the connection frame lower extreme is all connected to the upper end both sides that connect and the both sides of baffle, the fuselage is connected to the connection frame upper end.
Preferably, a cushion block is arranged between the joint and the baffle, an upper arc-shaped groove is formed in the upper end of the cushion block, a lower arc-shaped groove is formed in the lower end of the joint, the upper arc-shaped groove and the lower arc-shaped groove correspond up and down to form an embracing structure, the landing gear is wrapped among the joint, the cushion block and the baffle, and the cushion block is connected with the baffle and the joint through a connecting piece.
Preferably, the connection frame includes the frame body, frame body bottom is equipped with the splice bar, the splice bar passes through fastener attach fitting both sides.
Preferably, two connectors are arranged above each baffle plate, placed on two sides of the same connecting rib and clamped and connected with the connecting rib through fasteners.
Preferably, two connecting ribs are arranged at the lower end of each connecting frame.
Preferably, the fastener comprises a bolt which passes through the joint, landing gear, spacer and stop plate and is locked by a nut.
Preferably, the cushion block is made of a non-metal material with certain strength.
The utility model discloses a technological effect and advantage: this structural security is high: the undercarriage is not easy to fall off due to the adoption of the encircling connection mode, the front connection part and the rear connection part in the machine body are connected by adopting a double-frame structure, the stress of the undercarriage can be uniformly transmitted to the two frames, the stress of a single frame is reduced, the undercarriage is not easy to damage, and the safety is high;
connect reliably, prevent mistake and tear open: the double lugs are designed to be used as joints connected by the hinge in a direct machining mode on the frame, so that two joints are saved, meanwhile, the double lugs and the frame are formed in a direct machining mode, the precision is high, an external joint assembling tool is not needed, and the cost is low;
the service life is long: at the position where the root of the landing gear is easy to wear, a non-metal cushion block is adopted, when the landing gear deforms under stress, the cushion block and the landing gear rub with each other, the cushion block is soft, the cushion block is damaged, only the cushion block needs to be replaced periodically, the service life of the landing gear is longer, and the cost is lower;
the stress is good: the joint adopts the connection mode that the fastener is buckled, is connected with the undercarriage through the mode of cohesion, has avoided the undercarriage to punch and has aroused stress concentration, improves the atress performance of undercarriage.
Drawings
Fig. 1 is an isometric view of the present invention mounted to an eVTOL aircraft;
fig. 2 is an exploded view of the present invention in conjunction with an eVTOL aircraft;
fig. 3 is an isometric view of the present invention;
FIG. 4 is a partial exploded view of the present invention;
fig. 5 is an isometric view of a connection frame of the present invention;
figure 6 is a transverse cross-sectional view of the landing gear and joint area of the present invention;
figure 7 is a longitudinal cross-sectional view of the landing gear and joint connection area of the present invention;
fig. 8 is a cross-sectional view of the joint and the connection frame of the present invention.
In the figure: 1. a landing gear attachment structure; 11. a landing gear; 12. a joint; 121. a lower arc-shaped groove; 13. a cushion block; 131. an upper arc-shaped groove; 14. a baffle plate; 15. a fastener; 151. a bolt; 152. a nut; 2. a body; 21. a connecting frame; 211. connecting ribs; 212. the frame body.
Detailed Description
In order to make the technical means, the creative features, the objectives and the functions of the present invention easily understood and appreciated, the present invention will be further described 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, and for example, the terms" fixed connection, "detachable connection," integral connection, mechanical connection, and electrical connection may be used; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements.
Examples
As shown in fig. 1 and 2, the landing gear attachment structure 1 is at the bottom of the eVTOL aircraft, supports the eVTOL at ground level, and absorbs energy during landing to provide a cushioning effect during landing.
As shown in fig. 3, the landing gear connection structure 1 is connected with the connection frame 21 of the airframe 2, and a pair of connection frames 21 are arranged at the front part and the rear part of the airframe to connect and support the landing gear 11, so that when the landing gear 11 lands on the eVTOL aircraft, the force generated by energy absorption is transmitted to the airframe 2 through the frames in a balanced manner, and the landing safety of the eVTOL aircraft is ensured.
As shown in fig. 4, the figure is only one of four areas where the landing gear 11 is connected with the connecting frame 21, the other three areas are similarly connected and comprise a joint 12 and a baffle 14, the joint 12 and the baffle 14 are installed on the landing gear 11, the baffle 14 is located below the joint 12, a cushion block 13 is arranged between the joint 14 and the baffle 14, the baffle 14 is connected with the landing gear 11, the cushion block 13 and the baffle 14 through a fastener 15, both sides of the upper end of the joint 12 and both sides of the baffle 14 are connected with the lower end of the connecting frame 21, and the upper end of the connecting frame 21 is connected with the fuselage 2; the two joints 12 are kept stressed, and the eccentric condition does not exist. The joint 12 is stressed more, so the space is saved by adopting a material with higher strength, and high-strength steel, stainless steel and the like can be adopted, in this example, stainless steel with 15-5PH is adopted.
The landing gear 11 is formed by assembling various materials according to the stress state of the landing gear, and is composed of aluminum alloy, stainless steel, high-strength steel and the like, wherein the material of the connecting area is the high-strength steel, the ultimate strength of the high-strength steel is not less than 1400MPa, the stress requirement of the landing gear 11 is met, and meanwhile, the material consumption can be reduced, and the purpose of reducing weight is achieved.
The cushion block 13 is cushioned below the landing gear 11 and fixed by the baffle 14, the cushion block 13 acts as a deformation when the landing gear 11 in the area is stressed so as to generate friction, and the cushion block 13 is made of a non-metal material with certain strength, such as a composite material, hard rubber, plastic and the like, preferably made of nylon plastic. When motion friction is prevented, the cushion block 13 instead of the landing gear 11 is damaged, when a certain service life is reached, only the cushion block 13 needs to be replaced, and the cost is low.
In order to drag the landing gear 11, when the eVTOL aircraft takes off, the landing gear 11 is subjected to a downward force under the action of gravity, if the eVTOL aircraft does not drag, the landing gear 11 falls off, the baffle plate 14 is connected with the connecting frame 21 and the joint 12 to drag the landing gear 11, and the thickness of the baffle plate 14 is smaller than that of the joint due to the fact that the upward force and the downward force of the landing gear 11 in connection are different greatly, and therefore the purpose of reducing weight is achieved.
Fastener 15 is the connection of bolt 151 and nut 152, and nut 152 is the self-locking nut, improves locking performance, and connects 12 and the connection of linking frame 21, baffle 14 and linking frame 21 be connected, baffle 14 and undercarriage 11, connect 12 be connected etc. and all adopt fastener 15 to be connected, dismantles when convenient the maintenance, when certain part damage, can change.
As shown in fig. 5, the connection frame 21 includes a frame body 212, two connection ribs 211 are disposed at the bottom of the frame body 212, each connection rib 211 is clamped between two connectors 12 to ensure that the stress balance is not eccentric, the connection rib 211 is connected with the two connectors 12 through a hole by a bolt 151 and a nut 152, the connection rib 211 and the frame body 212 are an integral metal machining part made of aluminum alloy 7075, and the heat treatment state is T7451.
As shown in fig. 6, 7, and 8, one joint 12 of the two joints 12 has a connecting hole in the vertical direction, the landing gear 11, the pad 13, and the baffle 14 all have the same connecting hole and are connected through the bolt 151 and the nut 152, the baffle at the bottom is connected with the frame, the two joints 12 are connected with the connecting rib 211 of the connecting frame 21 through the bolt 151 and the nut 152, the upper end of the pad 13 is provided with the upper arc-shaped groove 131, the lower end of the joint 12 is provided with the lower arc-shaped groove 121, the upper arc-shaped groove 131 and the lower arc-shaped groove 121 form a clasping structure, the landing gear 11 is wrapped between the joint 12, the pad 13, and the baffle 14, the forward and backward and upward movement of the landing gear 11 is limited by the joint 12, the pad 13, and the baffle 14, the left and right movement is fixed between the joint 12, the pad 13, and the baffle 14 by the bolt 151 and the nut 152, and cannot rotate at the same time, all the degrees of freedom of movement of the landing gear 11 are limited, and the connection reliability of the landing gear 11 is ensured.
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 landing gear connection structure, includes joint and baffle, its characterized in that: the landing gear is characterized in that the joint and the baffle are arranged on the landing gear, the baffle is located below the joint, the baffle is connected with the landing gear and the baffle through fasteners, the two sides of the upper end of the joint and the two sides of the baffle are both connected with the lower end of the connecting frame, and the upper end of the connecting frame is connected with the machine body.
2. An eVTOL aircraft landing gear attachment structure according to claim 1, wherein: the landing gear is characterized in that a cushion block is arranged between the joint and the baffle, an upper arc-shaped groove is formed in the upper end of the cushion block, a lower arc-shaped groove is formed in the lower end of the joint, the upper arc-shaped groove and the lower arc-shaped groove correspond to each other from top to bottom to form an embracing structure, the landing gear is wrapped among the joint, the cushion block and the baffle, and the cushion block is connected with the baffle and the joint through a connecting piece.
3. An eVTOL aircraft landing gear attachment structure according to claim 2, wherein: the connecting frame comprises a frame body, connecting ribs are arranged at the bottom of the frame body, and the connecting ribs are connected with the two sides of the connector through fasteners.
4. An eVTOL aircraft landing gear attachment structure according to claim 3, wherein: and two connectors are arranged above each baffle plate, placed on two sides of the same connecting rib and clamped and connected with the connecting rib through fasteners.
5. An eVTOL aircraft landing gear attachment structure according to claim 3, wherein: and the lower end of each connecting frame is provided with two connecting ribs.
6. An eVTOL aircraft landing gear attachment structure according to claim 4, wherein: the fastener comprises a bolt, and the bolt penetrates through the joint, the landing gear, the cushion block and the baffle plate and is locked through a nut.
7. An eVTOL aircraft landing gear attachment structure according to claim 2, wherein: the cushion block is made of non-metal materials with certain strength.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222238435.2U CN218463867U (en) | 2022-08-25 | 2022-08-25 | eVTOL aircraft landing gear connecting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222238435.2U CN218463867U (en) | 2022-08-25 | 2022-08-25 | eVTOL aircraft landing gear connecting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218463867U true CN218463867U (en) | 2023-02-10 |
Family
ID=85140352
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222238435.2U Active CN218463867U (en) | 2022-08-25 | 2022-08-25 | eVTOL aircraft landing gear connecting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218463867U (en) |
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2022
- 2022-08-25 CN CN202222238435.2U patent/CN218463867U/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: An eVTOL aircraft landing gear connection structure Effective date of registration: 20230529 Granted publication date: 20230210 Pledgee: Industrial Bank Co.,Ltd. Shanghai Branch Pledgor: Shanghai wollant Aviation Technology Co.,Ltd. Registration number: Y2023310000218 |
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| 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: 20230210 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: An eVTOL aircraft landing gear connection structure Effective date of registration: 20230920 Granted publication date: 20230210 Pledgee: Industrial Bank Co.,Ltd. Shanghai Minhang sub branch Pledgor: Shanghai wollant Aviation Technology Co.,Ltd. Registration number: Y2023310000570 |