CN106628161B - Quick-dismantling structure for duct - Google Patents
Quick-dismantling structure for duct Download PDFInfo
- Publication number
- CN106628161B CN106628161B CN201710031313.7A CN201710031313A CN106628161B CN 106628161 B CN106628161 B CN 106628161B CN 201710031313 A CN201710031313 A CN 201710031313A CN 106628161 B CN106628161 B CN 106628161B
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- Prior art keywords
- duct
- base
- quick
- fixing part
- dismantling
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Duct Arrangements (AREA)
Abstract
The invention discloses a quick-dismantling structure of a duct, which is suitable for quickly assembling the duct on a support frame, wherein the quick-dismantling structure of the duct comprises a base, the base is of a hollow annular structure, the base is also provided with a support table protruding inwards of the annular structure, the base is also provided with a quick-dismantling piece protruding upwards, when the duct is inserted into the base, the lower end of the duct is abutted against the support table, and the quick-dismantling piece is detachably connected with the duct. The quick-dismantling structure of the duct can enable the duct to be stable, firm and capable of being assembled on the support frame quickly.
Description
Technical Field
The invention relates to the field of aircraft manufacturing, in particular to a bypass rapid heat dissipation structure.
Background
An aircraft is any flying object manufactured by a human being, capable of flying off the ground, flying in space, and controlled by the human being for personal use. As aircraft become popular, personal aircraft are necessarily a future development. A lightweight, flexible low-altitude, low-speed aircraft would be a direction of development for personal aircraft. At present, a personal aircraft usually drives the aircraft to fly by a plurality of ducts installed on the aircraft, the ducts usually comprise a duct body, a fan blade mechanism and a controller, the duct body is of a hollow structure, the fan blade mechanism is installed in the duct body, the controller is installed outside the duct body and electrically connected with a driving piece (a motor or a motor) of the fan blade mechanism, the controller is used for controlling the rotating speed of the driving piece, the driving piece is used for driving blades of the fan blade mechanism, the blades are rotated in the duct body to provide lifting force, meanwhile, the duct body of the hollow structure also plays a role of rectifying air, and the lifting force generated by the rotation of the blades is further improved, so that most of the aircraft adopts the duct instead of directly adopting a propeller, and the aircraft can smoothly leave the ground to fly under the effect of the duct.
The duct is one of the most important parts on the aircraft, the stability and the safety of the duct are not ignored, so that the duct must be maintained and maintained regularly according to a maintenance manual, the existing duct is fixed on a support frame of the aircraft in a direct welding mode, the whole aircraft flies away from the ground by virtue of the lifting force provided by the duct, and the fixed duct in a welding mode has overlarge stress on all welding points because the welding points cannot be uniformly welded and are the same as the welding points when the duct provides strong lifting force, the stress on all the welding points is relatively small, and the welding points with overlarge stress are extremely easy to break away from the welding points for a long time, so that the duct shakes during operation, the aircraft bumps, and the aircraft is seriously out of control, and a safety accident occurs; at the same time, this welding method is inconvenient for replacing the duct and for maintaining the mechanism inside the duct.
Therefore, there is a need for a quick-dismantling structure for a duct that can stabilize, firmly and quickly assemble on a support frame.
Disclosure of Invention
The invention aims to provide a quick-dismantling structure of a duct, which can enable the duct to be stable, firm and capable of being quickly assembled and arranged on a support frame.
In order to achieve the above purpose, the invention provides a quick-dismantling structure of a duct, which is suitable for quickly assembling the duct on a support frame, wherein the quick-dismantling structure of the duct comprises a base, the base is of a hollow annular structure, the base is also provided with a support table protruding inwards towards the annular structure, the base is also provided with a quick-dismantling piece protruding upwards, when the duct is inserted into the base, the lower end of the duct is in contact with the support table, and the quick-dismantling piece is detachably connected with the duct.
Compared with the prior art, the base of the duct quick-release structure is of a hollow annular structure, and the support table is formed by protruding in the annular structure, so that the lower end of the duct can be abutted against the base by the support table. The base also protrudes upwards to form a quick-release part, and the duct and the base can be quickly connected in a detachable mode through the quick-release part. When the base is fixed on the support frame, the lower end of the duct is inserted into the base and is abutted against the support table, and the duct is stably and firmly fixed on the support frame by matching with the support arm and the quick-release piece, so that the duct can uniformly provide lifting force and keep stable connection on the support frame when providing strong lifting force, and the safety of the working process of the aircraft is ensured; because the quick-release part of the base is detachably connected with the duct, the duct can be quickly assembled and disassembled with the support frame through the base, and the duct replacement and the maintenance of a mechanism in the duct are more facilitated.
Preferably, the quick-dismantling member comprises a supporting arm and a first fixing part, wherein the lower end of the supporting arm is fixedly connected with the base, the upper end of the supporting arm is connected with the first fixing part, and the first fixing part is detachably connected with the duct.
Preferably, the duct is provided with a second fixing portion corresponding to the first fixing portion, and when the duct is inserted into the base, the lower end of the duct abuts against the supporting table to rotate the duct, and the first fixing portion is detachably pressed on the second fixing portion.
Preferably, the supporting arm is provided with a clamping groove downwards from the first fixing part for the second fixing part to rotationally clamp in.
Preferably, the quick release members are uniformly distributed on the base.
Preferably, the duct has a hollow cylindrical structure.
Preferably, the support arm is provided with a plurality of through holes.
Preferably, the first fixing portion is provided with a plurality of first butt joint holes.
Preferably, the second fixing portion is provided with a plurality of second docking holes corresponding to the first docking holes.
Drawings
Fig. 1 is a schematic view of a duct with a quick-dismantling structure of the present invention when the duct is separated from a base.
Fig. 2 is a schematic view of a duct and a base assembly of the duct quick-release structure according to the present invention.
Fig. 3 is an overall cross-sectional view of the quick-disconnect structure of the duct of the present invention.
Fig. 4 is a front view of the duct quick release structure of the present invention when the duct is separated from the base.
Detailed Description
Embodiments of the present invention will now be described with reference to the drawings, wherein like reference numerals represent like elements throughout.
Referring to fig. 1-4, a duct quick release structure 100 of the present embodiment is suitable for quickly assembling a duct 1 on a support frame of an aircraft (not shown). Wherein the duct 1 has a hollow cylindrical structure. The quick-dismantling structure 100 for the duct comprises a base 2, wherein the base 2 is of a hollow annular structure and is provided with a supporting table 21 formed by protruding inwards of the annular structure, and the base 2 is also provided with a quick-dismantling piece 22 formed by protruding upwards. The quick release 22 is in detachable connection with the duct 1. It is worth noting that, the base 2 and the support frame of the duct quick-release structure 100 in this embodiment are integrally formed, so that stability between the base 2 and the support frame is more favorable to be maintained, when the duct 1 provides strong lifting force, the duct 1 can maintain a stable and firm connection state with the base 2, shaking of the duct 1 during operation is avoided, uneven stress of the duct 1 on the support frame is avoided, the possibility of jolt of an aircraft is reduced, and therefore the possibility of out of control of the aircraft is further reduced, and the probability of safety accidents is reduced.
Referring to fig. 1 and 4, further, the quick-dismantling device 22 includes a supporting arm 221 and a first fixing portion 222, the lower end of the supporting arm 221 is fixedly connected with the base 2, the upper end of the supporting arm 221 is connected with the first fixing portion 222, and the first fixing portion 222 is detachably connected with the duct 1. Specifically, the duct 1 is provided with a second fixing portion 11 corresponding to the first fixing portion 222, and the supporting arm 221 is provided with a clamping groove 223 from the first fixing portion 222 to be clamped by the second fixing portion 11. Specifically, as shown in fig. 3, when the duct 1 is inserted into the base 2, the lower end of the duct 1 abuts against the support table 21, the duct 1 is rotated, the second fixing portion 11 of the duct 1 is clamped into the clamping groove 223 of the supporting arm 221, and the first fixing portion 222 is detachably pressed against the second fixing portion 11. It should be noted that, the number of the quick-dismantling members 22 in the duct quick-dismantling structure 100 of the present embodiment is set to two, and the quick-dismantling members 22 need to be uniformly distributed on the base 2, and the number of the quick-dismantling members 22 may be set to 3, 4 or 5 on the premise of ensuring the stability of the aircraft in the flight process, so the present invention is not limited thereto.
With continued reference to fig. 1 and 4, further, the support arm 221 is further provided with two through holes 2211 therethrough, so that the weight of the support arm 221 can be reduced by the design of the through holes 2211, and the resistance between the aircraft and the wind in the flight process can be further reduced, thereby improving the flight efficiency of the aircraft. Specifically, as shown in fig. 3, the first fixing portion 222 is provided with two first docking holes 2221. The second fixing portion 11 is provided with two second docking holes 111 corresponding to the first docking holes 2221. By means of the first butt joint holes 2221 and the second butt joint holes 111, the second fixing portion 11 of the duct 1 can be clamped into the clamping groove 223 of the supporting arm 221, and when the first fixing portion 222 is pressed against the second fixing portion 11, the duct 1 and the base 2 can be further fixed by the screw 3. It should be noted that, on the premise of ensuring the stability of the aircraft during the flight, the number of the through holes 2211, the first docking holes 2221 and the second docking holes 111 may be specifically set according to actual needs, which is not limited herein.
The working process of the duct quick release structure 100 of the present embodiment will be described in detail below:
referring to fig. 1-4, the base 2 of the duct quick-release structure 100 of the present invention is integrally formed with a support frame of an aircraft, and when the duct 1 and the support frame are required to be assembled, the lower end of the duct 1 is stably abutted to the support table 21 of the base 2 and the lower end of the duct 1 is ensured to be fully contacted with the support table 21 of the base 2, and at this time, the second fixing portion 11 of the duct 1 and the clamping groove 223 of the quick-release member 22 are located on the same horizontal line. The duct 1 rotates steadily on the support table, and the duct 1 drives the second fixing portion 11 to be clamped into the clamping groove 223 of the quick release member 22, and at this time, the first fixing portion 222 abuts against the second fixing portion 11. The duct 1 is slightly rotated, the clamping position of the second fixing portion 11 and the first fixing portion 222 is adjusted, so that the first butt joint hole 2221 of the first fixing portion 222 is aligned with the second butt joint hole 111 of the second fixing portion 11, and at the moment, the screw 3 sequentially penetrates through the first butt joint hole 2221 and the second butt joint hole 111 and is screwed and fixed, and rapid assembly of the duct 1 and the base 2 is achieved. When the duct 1 needs to be disassembled and maintained, the screw 3 is unscrewed and taken out, the duct 1 is rotated, and the second fixing portion 11 of the duct 1 is far away from the clamping groove 223 of the quick-dismantling piece 22, so that the duct 1 and the base 2 can be disassembled quickly.
Referring to fig. 1 to fig. 4, the base 2 of the duct quick-release structure 100 of the present invention is a hollow ring structure, and protrudes into the ring structure to form a supporting table 21, so that the lower end of the duct 1 can be abutted against the base 2 by the supporting table 21. The base 2 further protrudes upwards to form a quick-release member 22, and the duct 1 and the base 2 can be detachably connected by the quick-release member 22. When the base 2 is fixed on the support frame, the lower end of the duct 1 is inserted into the base 2 and is abutted against the support table 21, and the support arm 221 and the quick release piece 22 are matched, so that the duct 1 is stably and firmly fixed on the support frame 221, and when the duct 1 provides strong lifting force, the support frame can be uniformly provided with lifting force under stress and stably connected, and the safety of the working process of the aircraft is ensured; due to the detachable connection of the quick release member 22 of the base 2 and the duct 1, the duct 1 can be quickly assembled and disassembled with the support frame through the base 2, which is more beneficial to replacing the duct 1 and maintaining the mechanism in the duct 1.
The foregoing description of the preferred embodiments of the present invention is not intended to limit the scope of the claims, which follow, as defined in the claims.
Claims (7)
1. The utility model provides a duct quick detach structure, is applicable to with the duct fast assembly on the support frame, its characterized in that: the duct quick-dismantling structure comprises a base, wherein the base is of a hollow annular structure, a supporting table protruding inwards of the annular structure is further arranged on the base, a quick-dismantling piece protruding upwards is further arranged on the base, when the duct is inserted into the base, the lower end of the duct is abutted to the supporting table, and the quick-dismantling piece is detachably connected with the duct; the quick-dismantling piece comprises a supporting arm and a first fixing part, the lower end of the supporting arm is fixedly connected with the base, the upper end of the supporting arm is connected with the first fixing part, and the first fixing part is detachably connected with the duct; the duct is provided with a second fixing part corresponding to the first fixing part; the supporting arm is downwards provided with a clamping groove for the second fixing part to rotationally clamp in from the first fixing part.
2. The bypass quick release structure of claim 1, wherein: when the duct is inserted into the base, the lower end of the duct is abutted against the supporting table, the duct is rotated, and the first fixing part is detachably abutted against the second fixing part.
3. The bypass quick release structure of any one of claims 1-2, wherein: the quick release pieces are uniformly distributed on the base.
4. The bypass quick release structure of claim 1, wherein: the duct is of a hollow cylindrical structure.
5. The bypass quick release structure of claim 1, wherein: the support arm is provided with a plurality of through holes in a penetrating way.
6. The bypass quick release structure of claim 2, wherein: the first fixing part is provided with a plurality of first butt joint holes.
7. The bypass quick release structure of claim 6, wherein the second securing portion is provided with a plurality of second mating holes corresponding to the first mating holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710031313.7A CN106628161B (en) | 2017-01-17 | 2017-01-17 | Quick-dismantling structure for duct |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710031313.7A CN106628161B (en) | 2017-01-17 | 2017-01-17 | Quick-dismantling structure for duct |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106628161A CN106628161A (en) | 2017-05-10 |
| CN106628161B true CN106628161B (en) | 2023-09-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710031313.7A Active CN106628161B (en) | 2017-01-17 | 2017-01-17 | Quick-dismantling structure for duct |
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| Country | Link |
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| CN (1) | CN106628161B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107244199B (en) * | 2017-06-23 | 2020-05-05 | 马德海 | Low-altitude aircraft |
| CN108216616B (en) * | 2018-01-23 | 2021-03-30 | 焦作大学 | High-efficient unmanned aerial vehicle automatically regulated rotor structure |
| DE102020121031A1 (en) | 2020-08-10 | 2022-02-10 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Aircraft and its manufacture |
| DE102020121030A1 (en) * | 2020-08-10 | 2022-02-10 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Aircraft and its manufacture |
| DE102020121032A1 (en) * | 2020-08-10 | 2022-02-10 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Aircraft and its manufacture |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4832633A (en) * | 1977-11-30 | 1989-05-23 | Hydronic, Ltd. | Marine propulsion system |
| CN201375818Y (en) * | 2009-03-06 | 2010-01-06 | 许群伟 | Semimetal and semiplastic structural duct |
| CN202006875U (en) * | 2011-01-21 | 2011-10-12 | 许群伟 | Ducted fan |
| CN204568060U (en) * | 2015-04-17 | 2015-08-19 | 何春旺 | Duct engine installation and aircraft |
| CN205327413U (en) * | 2016-01-04 | 2016-06-22 | 辽宁天行健航空科技有限公司 | Oil moves many for rotor craft quick detach formula duct circles of displacement |
| CN206606355U (en) * | 2017-01-17 | 2017-11-03 | 深圳市哈威飞行科技有限公司 | Duct quick-disassembly structure |
-
2017
- 2017-01-17 CN CN201710031313.7A patent/CN106628161B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4832633A (en) * | 1977-11-30 | 1989-05-23 | Hydronic, Ltd. | Marine propulsion system |
| CN201375818Y (en) * | 2009-03-06 | 2010-01-06 | 许群伟 | Semimetal and semiplastic structural duct |
| CN202006875U (en) * | 2011-01-21 | 2011-10-12 | 许群伟 | Ducted fan |
| CN204568060U (en) * | 2015-04-17 | 2015-08-19 | 何春旺 | Duct engine installation and aircraft |
| CN205327413U (en) * | 2016-01-04 | 2016-06-22 | 辽宁天行健航空科技有限公司 | Oil moves many for rotor craft quick detach formula duct circles of displacement |
| CN206606355U (en) * | 2017-01-17 | 2017-11-03 | 深圳市哈威飞行科技有限公司 | Duct quick-disassembly structure |
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| Publication number | Publication date |
|---|---|
| CN106628161A (en) | 2017-05-10 |
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