CN114834636A - Connecting mechanism for combination and separation of aircraft - Google Patents
Connecting mechanism for combination and separation of aircraft Download PDFInfo
- Publication number
- CN114834636A CN114834636A CN202210445022.3A CN202210445022A CN114834636A CN 114834636 A CN114834636 A CN 114834636A CN 202210445022 A CN202210445022 A CN 202210445022A CN 114834636 A CN114834636 A CN 114834636A
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- flexible
- aerial vehicle
- spacer pin
- taper sleeve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 18
- 238000000926 separation method Methods 0.000 title abstract description 10
- 125000006850 spacer group Chemical group 0.000 claims abstract description 23
- 230000005611 electricity Effects 0.000 claims abstract description 4
- 230000008878 coupling Effects 0.000 claims description 7
- 238000010168 coupling process Methods 0.000 claims description 7
- 238000005859 coupling reaction Methods 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 5
- 238000013461 design Methods 0.000 abstract description 3
- 239000000178 monomer Substances 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
- B64C37/02—Flying units formed by separate aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention discloses a connecting mechanism for combination and separation of an aircraft, and particularly relates to the technical field of structural design of supersonic aircrafts. Including flexible taper sleeve, flexible spacer pin and connector, flexible taper sleeve and flexible spacer pin interval set up the wing point department at arbitrary unmanned aerial vehicle, flexible taper sleeve and flexible spacer pin all are connected with this unmanned aerial vehicle's control system electricity, the fixed wing point department that sets up at another unmanned aerial vehicle of connector, it has the opening with flexible spacer pin matched with to open on the connector. By adopting the technical scheme of the invention, the problem of short cruising time of the existing small and medium-sized unmanned aerial vehicles is solved, and the unmanned aerial vehicle can be used for combination among a plurality of unmanned aerial vehicles.
Description
Technical Field
The invention relates to the technical field of aircraft structure design, in particular to a connecting mechanism for combination and separation of an aircraft.
Background
With the increasing development of unmanned aerial vehicle technology, the functions of the unmanned aerial vehicle are improved, the unmanned aerial vehicle plays an important role in various fields such as agriculture, fire fighting, military and the like gradually, and replaces partial manual operation gradually, so that human resources are greatly saved. The small and medium-sized unmanned aerial vehicle has low manufacturing cost and low maintenance cost, so the small and medium-sized unmanned aerial vehicle has wide application prospect.
Under general conditions, the oil loading of small and medium-sized unmanned aerial vehicles is less, and the voyage is shorter compared with that of large unmanned aerial vehicles and manned unmanned aerial vehicles. At present, if a small-and-medium-sized unmanned aerial vehicle needs to reach a remote destination to execute a task, a man-machine or a large-sized unmanned aerial vehicle needs to transport the small-and-medium-sized unmanned aerial vehicle, so that the cost is increased, and the man-machine or the high-value unmanned aerial vehicle is possibly in danger. To sum up, how to make the middle-size and small-size unmanned aerial vehicle that is a lot of can cruise for a long time is the problem that needs to solve at present urgently.
Disclosure of Invention
The invention aims to provide a connecting mechanism for combination and separation of aircrafts, and solves the problem that the conventional small and medium-sized unmanned aerial vehicle is short in cruising time.
In order to achieve the purpose, the technical scheme of the invention is as follows: the utility model provides a coupling mechanism that can be used to aircraft combination and separation, includes flexible taper sleeve, flexible spacer pin and connector, flexible taper sleeve and flexible spacer pin interval set up the wing point department at arbitrary unmanned aerial vehicle, flexible taper sleeve and flexible spacer pin all are connected with this unmanned aerial vehicle's control system electricity, the fixed wing point department that sets up at another unmanned aerial vehicle of connector, it has the opening with flexible spacer pin matched with to open on the connector.
Furthermore, the telescopic limiting pin is obliquely arranged.
Through the arrangement, the stability between the two unmanned aerial vehicles is convenient to maintain under the combined state.
Further, the combination method of the connecting mechanism is as follows: start flexible taper sleeve through unmanned aerial vehicle, the taper sleeve through its front end cooperatees with the connector after flexible taper sleeve extension, then starts flexible spacer pin, and the opening part of connector is inserted in the extension of flexible spacer pin this moment to realize two unmanned aerial vehicle's combination.
Compared with the prior art, the beneficial effect of this scheme:
the scheme can realize the operation mode that a man machine or a large host carries a small and medium-sized unmanned aerial vehicle, and has lower cost; compared with the single unmanned aerial vehicle flying, the scheme has longer range and longer time; the mechanical mode of the combining/separating mechanism is adopted to combine and separate the unmanned aerial vehicles, so that the combination and separation of the unmanned aerial vehicles are easier to realize.
Drawings
FIG. 1 is a schematic structural view of an aircraft with a detachable coupling mechanism according to the present invention in an assembled state;
FIG. 2 is a schematic structural view of the grasping machine in the present embodiment;
FIG. 3 is a schematic structural view of the joining machine of the present embodiment;
fig. 4 is a schematic structural view of a detachable connection mechanism for aircraft assembly and disassembly according to the present invention.
Detailed Description
The present invention will be described in further detail below by way of specific embodiments:
reference numerals in the drawings of the specification include: the device comprises a telescopic taper sleeve 1, a telescopic limiting pin 2, a connecting body 3, a grabbing machine 4 and a connecting machine 5.
Examples
As shown in figures 1 to 4: the utility model provides a coupling mechanism that can be used to aircraft combination and separation, includes flexible taper sleeve, flexible spacer pin and connector, flexible taper sleeve and flexible spacer pin interval set up the wing point department at arbitrary unmanned aerial vehicle (this unmanned aerial vehicle later is called the snatching plane), and flexible taper sleeve and flexible spacer pin all are connected with the control system electricity of snatching the machine, and flexible spacer pin slope sets up. The connector is fixed to be set up in the wingtip department of another unmanned aerial vehicle (this unmanned aerial vehicle is called the junctor later), and it has the opening with flexible spacer pin matched with to open on the connector.
The working process of the scheme is as follows:
the combination method of the connecting mechanism comprises the following steps: the snatch machine reaches predetermined flight path, through not having the flexible taper sleeve of snatch machine start, flexible taper sleeve extension is to keeping away from the position of wing point whirlpool, this in-process junctor follows behind the snatch machine, after flexible taper sleeve extension to predetermined position, the junctor is close to with higher speed slowly when reaching the exercise level region, the tip that makes the connector reaches the design position through the guide of flexible taper sleeve mouth, then start flexible spacer pin, the opening part of connector is inserted in the extension of flexible spacer pin this moment, thereby realize the combination of snatch machine and junctor. The outer side surface of the taper sleeve of the telescopic taper sleeve and the connector are correspondingly provided with rotary displacement when being inserted into the limiting pin hole, so that the two machines can rotate relatively under the combined state, and a certain bending degree of freedom is released; in the separation process, the telescopic limiting pin of the grabbing machine is started to leave the connecting machine, and then the two machines are controlled to perform speed differential motion to complete separation.
The coupling mechanism of this scheme can be used to many unmanned aerial vehicles on, many unmanned aerial vehicles with the coupling mechanism group becomes the combination, the combination can decompose out the unmanned aerial vehicle monomer and carry out the network deployment flight, also can add the unmanned aerial vehicle monomer and become to contain the free combination of more unmanned aerial vehicles of quantity.
When this scheme is in the assembly, two unmanned aerial vehicles connect side by side, for single unmanned aerial vehicle, the assembly has increased unmanned aerial vehicle's exhibition length, has improved lift-drag ratio, under the same oil mass, has improved unmanned aerial vehicle's voyage.
The foregoing are merely examples of the present invention and common general knowledge of known specific structures and/or features of the schemes has not been described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (3)
1. A connecting mechanism capable of being used for combining and separating an aircraft is characterized in that: including flexible taper sleeve, flexible spacer pin and connector, flexible taper sleeve and flexible spacer pin interval set up the wing point department at arbitrary unmanned aerial vehicle, flexible taper sleeve and flexible spacer pin all are connected with this unmanned aerial vehicle's control system electricity, the fixed wing point department that sets up at another unmanned aerial vehicle of connector, it has the opening with flexible spacer pin matched with to open on the connector.
2. A coupling mechanism for aircraft assembly and disassembly as claimed in claim 1, wherein: the telescopic limiting pin is obliquely arranged.
3. A coupling mechanism for aircraft assembly and disassembly as claimed in claim 1, wherein: the combination method of the connecting mechanism comprises the following steps: start flexible taper sleeve through unmanned aerial vehicle, the taper sleeve through its front end cooperatees with the connector after flexible taper sleeve extension, then starts flexible spacer pin, and the opening part of connector is inserted in the extension of flexible spacer pin this moment to realize two unmanned aerial vehicle's combination.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210445022.3A CN114834636A (en) | 2022-04-26 | 2022-04-26 | Connecting mechanism for combination and separation of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210445022.3A CN114834636A (en) | 2022-04-26 | 2022-04-26 | Connecting mechanism for combination and separation of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114834636A true CN114834636A (en) | 2022-08-02 |
Family
ID=82565874
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210445022.3A Pending CN114834636A (en) | 2022-04-26 | 2022-04-26 | Connecting mechanism for combination and separation of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114834636A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105059550A (en) * | 2015-08-31 | 2015-11-18 | 深圳市飞研智能科技有限公司 | Double unmanned aerial vehicle with improved endurance |
| CN108583876A (en) * | 2018-04-24 | 2018-09-28 | 北京航空航天大学 | A kind of mechanism of aerial wing tip docking/separation |
| CN112550695A (en) * | 2020-12-07 | 2021-03-26 | 北京航空航天大学 | Vertical take-off and landing wingtip hinged combined unmanned aerial vehicle |
-
2022
- 2022-04-26 CN CN202210445022.3A patent/CN114834636A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105059550A (en) * | 2015-08-31 | 2015-11-18 | 深圳市飞研智能科技有限公司 | Double unmanned aerial vehicle with improved endurance |
| CN108583876A (en) * | 2018-04-24 | 2018-09-28 | 北京航空航天大学 | A kind of mechanism of aerial wing tip docking/separation |
| CN112550695A (en) * | 2020-12-07 | 2021-03-26 | 北京航空航天大学 | Vertical take-off and landing wingtip hinged combined unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR102243228B1 (en) | Release and capture of a fixedwing aircraft | |
| US6641082B2 (en) | Aircraft ferrying system and method thereof | |
| US9505484B1 (en) | Modular aircraft system | |
| CN108216621A (en) | A kind of wing tip connection composite lights aircraft in parallel | |
| US20090095843A1 (en) | Enhanced ruddevator for improved air refueling boom flight control | |
| CN109296462A (en) | Dynamic formula air intake duct combination blanking cover is made in supersonic speed explosion | |
| US7201348B1 (en) | Cruise missile recovery system | |
| CN107117311A (en) | A kind of changeable wheelbase unmanned plane | |
| RU181026U1 (en) | Multipurpose Unmanned Aerial Vehicle | |
| CN109515732B (en) | Combined aircraft based on barrel type launching | |
| US2777655A (en) | Airplane with separable fuel tanks | |
| CN202295289U (en) | Special high-speed unmanned aerial vehicle | |
| CN111976948B (en) | Pneumatic layout of unmanned combat bomber of flying wing formula | |
| CN114834636A (en) | Connecting mechanism for combination and separation of aircraft | |
| CN110127067A (en) | Combined type VTOL high speed fixed-wing unmanned flight's platform | |
| CN108313281B (en) | Variable-configuration unmanned aerial vehicle | |
| CN209427030U (en) | Unmanned plane parachuting Emergency recovery system | |
| CN109606679B (en) | Wingtip winglet type combined airplane | |
| CN216916309U (en) | Fusion type unmanned aerial vehicle suitable for batched long-range voyage | |
| CN103507954A (en) | Air injection flying saucer | |
| CN216102766U (en) | Reconfigurable combined type unmanned aerial vehicle | |
| CN202529147U (en) | Worm disk-shaped aircraft | |
| CN110104163A (en) | One kind can hang down flying wing type unmanned plane | |
| CN114852332A (en) | Chain wing electromagnetic connecting mechanism for combined aircraft | |
| CN113428361B (en) | Intelligent separable variant vertical take-off and landing unmanned platform and control strategy thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |