CN110588952A - Fixed wing aircraft with quickly detachable wings and method for quickly installing and detaching wings - Google Patents
Fixed wing aircraft with quickly detachable wings and method for quickly installing and detaching wings Download PDFInfo
- Publication number
- CN110588952A CN110588952A CN201910964276.4A CN201910964276A CN110588952A CN 110588952 A CN110588952 A CN 110588952A CN 201910964276 A CN201910964276 A CN 201910964276A CN 110588952 A CN110588952 A CN 110588952A
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- connecting rod
- rod
- cross
- cross rod
- fixed
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- 238000000034 method Methods 0.000 title claims abstract description 13
- 238000003825 pressing Methods 0.000 claims description 2
- 238000001514 detection method Methods 0.000 abstract description 4
- 238000012423 maintenance Methods 0.000 abstract description 4
- 230000002349 favourable effect Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 230000035899 viability Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Abstract
The invention relates to a fixed wing aircraft with quickly detachable wings and a method for quickly installing and detaching the wings. The aircraft comprises an aircraft body and an aircraft wing, the first cross rod is symmetrically connected to two sides of the aircraft body, the second cross rod and the third cross rod are symmetrically connected to the inner side surface of the aircraft wing, a cross rod hole for the third cross rod to penetrate through is formed in the side surface of a fixing block, a plurality of coincident threaded holes are formed in the overlapped portion of the first cross rod and the second cross rod, internal threads are formed in the inner surface of each threaded hole, a spring box which is the same as the threaded holes in number and position is arranged on the upper surface of the third cross rod, a spring and a top opening are formed in the spring box, the lower end portion of a connecting rod in an inverted T shape is located inside the spring box, the outer surface of the upper portion of the connecting rod is provided with external threads meshed. The wing of the technical scheme can be quickly and accurately installed and detached without special tools, and is favorable for maintenance and detection operation of the aircraft by workers.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle equipment, in particular to a fixed wing aircraft with quickly detachable wings and a method for quickly installing and detaching the wings.
Background
Unmanned aerial vehicle is unmanned aerial vehicle for short, is the unmanned vehicles who utilizes radio remote control equipment and self-contained program control device to control, and unmanned aerial vehicle is the general name of unmanned aerial vehicle in fact, can divide into from the technical perspective: compared with manned aircrafts, the unmanned fixed wing aircraft, the unmanned vertical take-off and landing aircraft, the unmanned airship, the unmanned helicopter, the unmanned multi-rotor aircraft, the unmanned umbrella wing aircraft and the like have the advantages of small volume, low manufacturing cost, convenient use, low requirement on the battlefield environment, strong battlefield viability and the like. Since the unmanned aircraft has important significance for future air battles, the research and development work of the unmanned aircraft is carried out in all major military countries in the world. In addition, the unmanned aerial vehicle has wide application and has better development prospect in the industries of police, city management, agriculture, geology, meteorology, electric power, emergency rescue and disaster relief, video shooting and the like.
The unmanned aerial vehicle comprises a fixed-wing aircraft and a rotor aircraft, wherein the fixed-wing aircraft is an aircraft with wings fixed on a fuselage, does not move relative to the fuselage, generates lift force by acting force of air on the wings, and specifically, generates forward thrust or pull force by a power device, generates lift force by the fixed wings of the fuselage, and flies in the atmosphere and is heavier than air. In the existing fixed wing aircraft, a fuselage and a wing are connected by welding or by glue, and then are covered and beautified. However, the connection mode is a permanent fixed connection, and the disassembly and the assembly are inconvenient. Unmanned aerial vehicle need pull down the wing in transportation or the storage process when not using, pack alone and transportation to because unmanned aerial vehicle is too big, cause collision damage to fuselage or wing. Meanwhile, when the aircraft is detected, repaired and replaced, the fixed connection cannot be used for quickly and accurately installing and disassembling the flight wings, and the detection and maintenance operation of workers is not facilitated.
Disclosure of Invention
In order to overcome the defects, the invention provides the fixed-wing aircraft with the quickly-detachable wings and the method for quickly installing and detaching the wings, wherein the wings can be quickly and accurately installed and detached, and the maintenance and detection operation of the aircraft by workers is facilitated.
The technical scheme of the invention is as follows:
the fixed-wing aircraft with the wings capable of being quickly disassembled and assembled comprises an aircraft body and the wings positioned on two sides of the aircraft body, and is characterized in that fixed blocks are symmetrically fixed on two sides of the aircraft body, the outer side surfaces of the fixed blocks are symmetrically connected with a first cross rod, the inner side surfaces of the wings are symmetrically connected with a second cross rod and a third cross rod, the first cross rod, the second cross rod and the third cross rod are parallel to each other, the first cross rod is positioned between the second cross rod and the third cross rod, the first cross rod and the second cross rod are mutually attached and overlapped, a cross rod hole for the third cross rod to penetrate through is formed in the side surface of the fixed block, and the free end part of the third cross rod is; the spring box is internally provided with a spring, the top of the spring box is provided with a sliding hole, the connecting rod is an inverted T-shaped rod, the lower end of the connecting rod is positioned inside the spring box, the diameter of the lower end of the connecting rod is larger than the inner diameter of the sliding hole, the outer surface of the upper part of the connecting rod is provided with an external thread meshed with the internal thread of the threaded hole, the lower part of the connecting rod is a smooth surface capable of sliding up and down in the sliding hole, the connecting rod penetrates through the sliding hole from bottom to top and penetrates through the first cross rod and the second cross rod above the connecting rod, and the upper end part of the connecting rod is locked by a nut.
The bottom of the fixing block is provided with a threaded hole communicated with the cross rod hole, and a fixing bolt is arranged in the threaded hole.
The spring box is a cylindrical box body, and the diameter of the lower end part of the connecting rod is equal to the inner diameter of the spring box.
The number of the spring boxes on one side of the machine body is 2-3.
A method for quickly installing wings of a fixed-wing aircraft comprises the following steps:
s1: pressing down the connecting rod to immerse the lower half part of the connecting rod into the spring box;
s2: the wing is closed to the fuselage, the first cross rod is inserted between the second cross rod and the third cross rod, the first cross rod and the second cross rod are mutually attached and overlapped, the threaded holes are aligned, and the third cross rod is inserted into a cross rod hole on the outer side of the fixing block;
s3: the connecting rod is loosened, rises under the action of the spring, and the top end of the connecting rod is aligned with the threaded hole right above the connecting rod;
s4: the connecting rod is rotated from the side surface and is upwards screwed into the threaded hole, and the upper end part of the connecting rod extends out of the second cross rod;
s5: screwing the nut into the top of the connecting rod to lock the connecting rod;
s6: and screwing the fixing bolt into the threaded hole at the bottom of the fixing block for locking.
A method for quickly dismantling wings of a fixed-wing aircraft comprises the following steps:
s1: removing the fixing bolt at the bottom of the fixing block;
s2: removing the nut at the top of the connecting rod;
s3: rotating the connecting rod from the side surface to enable the connecting rod to be screwed out of the threaded hole downwards;
s4: the connecting rod is pressed downwards to pull the wings outwards, so that the first cross rod is separated from the second cross rod, the third cross rod is withdrawn from the cross rod hole, and the fuselage is completely separated from the wings.
The aircraft body and the wings are connected through a first cross bar, a second cross bar and a third cross bar which are arranged in parallel, the first cross bar is fixedly connected with fixed blocks on two sides of the aircraft body, the second cross bar and the third cross bar are fixedly connected with the wings, the first cross bar and the second cross bar are mutually attached and overlapped, a plurality of overlapped threaded holes are formed in the overlapped part, and the third cross bar is inserted into cross bar holes on two sides of the fixed blocks. The first cross rod and the third cross rod are spaced by a certain distance, the upper surface of the third cross rod is provided with a spring box, the connecting rod in the shape of an inverted T penetrates through the top of the spring box from bottom to top and penetrates through the first cross rod and the second cross rod above, the outer surface of the upper portion of the connecting rod is an external thread meshed with an internal thread of a threaded hole, the lower portion of the connecting rod is a smooth surface capable of sliding up and down in a sliding hole, the connecting rod connects and fixes the first cross rod and the second cross rod, and the upper end of the connecting rod is.
When fuselage and wing equipment, the connecting rod of the font of will falling T pushes down, make the connecting rod lower half sink into in the spring box, promote the wing and draw close to the fuselage, make first horizontal pole and second horizontal pole laminate each other and overlap, the screwed hole aligns, insert the third horizontal pole in the horizontal pole hole of fixed block both sides, loosen the connecting rod, the connecting rod rises under the effect of spring, the top is aimed at the screw hole directly over, the side rotates the connecting rod and makes progress the screw in screw hole with it, the second horizontal pole is stretched out to the connecting rod upper end, with the nut locking. Finally, the fixing bolt at the bottom of the fixing block is screwed in to further fix the third cross rod, and the connection and assembly of the fuselage and the wings are completed.
When the wing needs to be detached from the fuselage, in contrast to the above steps, the nut and the fixing bolt at the bottom of the fixing block are firstly loosened, the connecting rod is rotated from the side surface and is screwed out of the threaded hole downwards, the first cross rod and the second cross rod are disconnected and fixed, a separable state is presented, the wing is pulled outwards, the third cross rod is withdrawn from the cross rod hole, the first cross rod is separated from the second cross rod at the same time, and the fuselage and the wing are detached.
Drawings
FIG. 1 is a front view of a fast wing-on-wing fixed wing aircraft of the present invention;
fig. 2 is an enlarged view of a portion a in fig. 1.
Detailed Description
The conception, the specific structure and the technical effects of the present invention will be further described with reference to the accompanying drawings to fully understand the objects, the features and the effects of the present invention.
Referring to fig. 1 and 2, the fixed-wing aircraft with the quickly detachable wings comprises a fuselage 10 and wings 20 located on two sides of the fuselage 10, fixed blocks 12 are symmetrically fixed on two sides of the fuselage 10, the fixed blocks 12 are rectangular plate-shaped, first cross bars 11 are symmetrically connected to outer side surfaces of the fixed blocks 12, second cross bars 22 and third cross bars 23 are symmetrically connected to inner side surfaces of the wings 20, the first cross bars 11, the second cross bars 22 and the third cross bars 23 are parallel to each other, the first cross bars 11 are located between the second cross bars 22 and the third cross bars 23, the first cross bars 11 and the second cross bars 22 are attached and overlapped with each other, cross bar holes for the third cross bars 23 to pass through are formed in the side surfaces of the fixed blocks 12, the third cross bars 23 are inserted into the cross bar holes, and free end portions of the third cross bars are located.
A plurality of coincident threaded holes are formed in the overlapped part of the first cross rod 11 and the second cross rod 22, and for convenience in installation, the number of the threaded holes is 2-3, and the number of the threaded holes is 2 in the embodiment. The inner surface of the threaded hole is provided with internal threads, the upper surface of the third cross rod 23 is provided with spring boxes 24 corresponding to the number and the positions of the threaded holes, each spring box 24 is a cylindrical box body, a spring 25 is arranged in each spring box 24, and the top of each spring box 24 is provided with a sliding hole. The connecting rod 26 is an inverted T-shaped rod, the lower end of which is located inside the spring case 24, and the diameter of the lower end is larger than the inner diameter of the slide hole, in this embodiment, the diameter of the lower end is equal to the inner diameter of the spring case 24. The outer surface of the upper part of the connecting rod 26 is provided with an external thread meshed with the internal thread of the threaded hole, the lower part of the connecting rod is a smooth surface capable of sliding up and down in the sliding hole, the connecting rod 26 passes through the sliding hole from bottom to top and passes through the first cross rod 11 and the second cross rod 22 above, and the upper end part of the connecting rod is locked by a nut 27.
Because the outer surface of the upper part of the connecting rod 26 is provided with an external thread, the inner surface of the threaded hole is provided with an internal thread, the upper part of the connecting rod 26 is screwed into the threaded hole, and the end part is locked by the nut 27, the first cross rod 11 and the second cross rod 22 can be fixedly connected, namely, the fuselage 10 and the wing 20 are mutually connected. The spring 25 is arranged in the spring box 24 and can provide upward thrust, the connecting rod 26 is pushed to the top of the spring box 24 in a natural state, and the connecting rod 26 is an inverted T-shaped rod, the diameter of the lower end part of the connecting rod 26 is larger than the inner diameter of the sliding hole, so that the connecting rod 26 cannot pop out of the spring box 24, but is kept at the top of the spring box 24, and the installation is convenient. After the fuselage 10 and the wing 20 are connected, the third cross rod 23 is located in the cross rod hole of the fixed block 12, in order to further fix the third cross rod 23 and prevent displacement of the third cross rod, a threaded hole communicated with the cross rod hole is formed in the bottom of the fixed block 12, and a fixing bolt 13 is arranged in the threaded hole and locks the third cross rod 23.
The invention discloses a method for quickly installing wings of a fixed-wing aircraft, which comprises the following steps of:
s1: the connecting rod 26 is pressed down so that the lower half of the connecting rod 26 is submerged in the spring case 24;
s2: the wing 20 is closed to the fuselage 10, the first cross bar 11 is inserted between the second cross bar 22 and the third cross bar 23, the first cross bar 11 and the second cross bar 22 are mutually attached and overlapped, the threaded holes are aligned, and the third cross bar 23 is inserted into a cross bar hole on the outer side of the fixed block 12;
s3: the connecting rod 26 is loosened, the connecting rod 26 rises under the action of the spring 25, and the top end of the connecting rod is aligned with the threaded hole right above;
s4: turning the connecting rod 26 from the side to screw it up into the threaded hole, with the upper end of the connecting rod 26 extending out of the second cross bar 22;
s5: screwing the nut 27 on top of the tie-rod 26 to lock it;
s6: and screwing the fixing bolt 13 into the threaded hole at the bottom of the fixing block 12 for locking.
The invention discloses a method for quickly dismantling wings of a fixed wing aircraft, which comprises the following steps:
s1: loosening the fixing bolt 13 at the bottom of the fixing block 12;
s2: loosening the nut 27 at the top of the tie rod 26;
s3: rotating the connecting rod 26 from the side to screw it out of the threaded hole;
s4: the connecting rod 26 is pressed downwards to pull the wing 20 outwards, so that the first cross rod 11 is separated from the second cross rod 22, the third cross rod 23 is withdrawn from the cross rod hole, and the fuselage 10 is completely separated from the wing 20.
The fixed wing aircraft has the advantages that the wings can be quickly and conveniently mounted and dismounted, no special tool is needed in the mounting and dismounting process, and the dismounting operation of workers is greatly simplified. The aircraft wing protection device is beneficial to maintenance and detection operations of workers on the aircraft, and is also convenient to detach the wing for independent packaging or transportation when the aircraft needs to be transported or stored, so that the overall size of the aircraft is reduced, and collision damage caused by overlarge size is avoided.
The above disclosure is only an example of the present invention, but the present invention is not limited thereto, and any variations that can be made by those skilled in the art should fall within the scope of the present invention.
Claims (6)
1. A fixed wing aircraft with quickly detachable wings comprises a fuselage (10) and wings (20) positioned on two sides of the fuselage (10), it is characterized in that fixed blocks (12) are symmetrically fixed on both sides of the machine body (10), the outer side surfaces of the fixed blocks (12) are symmetrically connected with a first cross bar (11), the inner side surfaces of the wings (20) are symmetrically connected with a second cross bar (22) and a third cross bar (23), the first cross bar (11), the second cross bar (22) and the third cross bar (23) are parallel to each other, the first cross bar (11) is positioned between the second cross bar (22) and the third cross bar (23), the first cross bar (11) and the second cross bar (22) are mutually attached and overlapped, a cross rod hole for the third cross rod (23) to penetrate through is formed in the side face of the fixed block (12), and the free end part of the third cross rod (23) is located in the fixed block (12); a plurality of coincident threaded holes are formed in the overlapped part of the first cross rod (11) and the second cross rod (22), internal threads are formed in the inner surface of each threaded hole, a spring box (24) with the same number and position as the threaded holes is arranged on the upper surface of the third cross rod (23), a spring (25) is arranged in the spring box (24), a sliding hole is formed in the top of the spring box (24), the connecting rod (26) is an inverted T-shaped rod, the lower end of the connecting rod is located inside the spring box (24), the diameter of the lower end of the connecting rod is larger than the inner diameter of the sliding hole, external threads meshed with the internal threads of the threaded holes are arranged on the outer surface of the upper portion of the connecting rod (26), the lower portion of the connecting rod is a smooth surface capable of sliding up and down in the sliding hole, the connecting rod (26) penetrates through the sliding hole.
2. The fixed-wing aircraft as claimed in claim 1, wherein the bottom of the fixed block (12) is provided with a threaded hole communicated with the cross bar hole, and a fixed bolt (13) is arranged in the threaded hole.
3. The fixed-wing aircraft of claim 1, wherein the spring cassette (24) is a cylindrical box, and the connecting rod (26) has a lower end diameter equal to the inner diameter of the spring cassette (24).
4. The fixed-wing aircraft according to claim 1, characterized in that the number of spring cassettes (24) on one side of the fuselage (10) is 2-3.
5. A method for quickly installing wings of a fixed-wing aircraft is characterized by comprising the following steps:
s1: pressing down the connecting rod (26) to enable the lower half part of the connecting rod (26) to be submerged into the spring box (24);
s2: the wing (20) is drawn close to the fuselage (10), the first cross rod (11) is inserted between the second cross rod (22) and the third cross rod (23), the first cross rod (11) and the second cross rod (22) are mutually attached and overlapped, the threaded holes are aligned, and the third cross rod (23) is inserted into the cross rod hole on the outer side of the fixed block (12);
s3: the connecting rod (26) is loosened, the connecting rod (26) rises under the action of the spring (25), and the top end of the connecting rod is aligned with the threaded hole right above the connecting rod;
s4: the connecting rod (26) is rotated from the side surface and is screwed into the threaded hole upwards, and the upper end part of the connecting rod (26) extends out of the second cross rod (22);
s5: screwing a nut (27) into the top of the connecting rod (26) to lock the connecting rod;
s6: and screwing the fixing bolt (13) into the threaded hole at the bottom of the fixing block (12) for locking.
6. A method for quickly dismantling wings of a fixed-wing aircraft is characterized by comprising the following steps:
s1: removing the fixing bolt (13) at the bottom of the fixing block (12);
s2: removing the nut (27) at the top of the tie rod (26);
s3: rotating the connecting rod (26) from the side surface to make the connecting rod screwed out of the threaded hole downwards;
s4: the connecting rod (26) is pressed downwards, the wing (20) is pulled outwards, the first cross rod (11) is separated from the second cross rod (22), the third cross rod (23) is withdrawn from the cross rod hole, and the fuselage (10) is completely separated from the wing (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910964276.4A CN110588952A (en) | 2019-10-11 | 2019-10-11 | Fixed wing aircraft with quickly detachable wings and method for quickly installing and detaching wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910964276.4A CN110588952A (en) | 2019-10-11 | 2019-10-11 | Fixed wing aircraft with quickly detachable wings and method for quickly installing and detaching wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110588952A true CN110588952A (en) | 2019-12-20 |
Family
ID=68866559
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910964276.4A Pending CN110588952A (en) | 2019-10-11 | 2019-10-11 | Fixed wing aircraft with quickly detachable wings and method for quickly installing and detaching wings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110588952A (en) |
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| CN206939031U (en) * | 2017-06-26 | 2018-01-30 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of electronic unmanned plane of fixed-wing |
| US20180072398A1 (en) * | 2016-09-09 | 2018-03-15 | Unmanned Innovation Inc. (dba Airware) | Airframe Attachments |
| CN108438200A (en) * | 2018-05-11 | 2018-08-24 | 南京航天猎鹰飞行器技术有限公司 | A kind of fixed-wing unmanned plane of fast demountable wing |
| CN208233338U (en) * | 2018-05-07 | 2018-12-14 | 东莞众创新能源科技有限公司 | Assembly type fixed-wing unmanned plane |
| CN208439425U (en) * | 2018-07-18 | 2019-01-29 | 广东万虹科技有限公司 | A kind of novel combined fixed-wing unmanned plane |
| CN109911174A (en) * | 2019-04-17 | 2019-06-21 | 成都航空职业技术学院 | A kind of fixed-wing unmanned plane of fast demountable wing |
| CN210653614U (en) * | 2019-10-11 | 2020-06-02 | 复旦大学 | Fixed wing aircraft with quickly detachable wings |
-
2019
- 2019-10-11 CN CN201910964276.4A patent/CN110588952A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090302159A1 (en) * | 2007-01-16 | 2009-12-10 | Sagem Defense Securite | Aircraft Wing Including a Plurality of Dismountable Members |
| CN205010473U (en) * | 2015-08-26 | 2016-02-03 | 合肥工业大学 | Wing with quick assembly disassembly interfacing apparatus |
| CN205239893U (en) * | 2015-10-27 | 2016-05-18 | 镇江顺宇飞行器有限公司 | Detachable wing |
| US20180072398A1 (en) * | 2016-09-09 | 2018-03-15 | Unmanned Innovation Inc. (dba Airware) | Airframe Attachments |
| CN206939031U (en) * | 2017-06-26 | 2018-01-30 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of electronic unmanned plane of fixed-wing |
| CN208233338U (en) * | 2018-05-07 | 2018-12-14 | 东莞众创新能源科技有限公司 | Assembly type fixed-wing unmanned plane |
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| CN208439425U (en) * | 2018-07-18 | 2019-01-29 | 广东万虹科技有限公司 | A kind of novel combined fixed-wing unmanned plane |
| CN109911174A (en) * | 2019-04-17 | 2019-06-21 | 成都航空职业技术学院 | A kind of fixed-wing unmanned plane of fast demountable wing |
| CN210653614U (en) * | 2019-10-11 | 2020-06-02 | 复旦大学 | Fixed wing aircraft with quickly detachable wings |
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