CN107571992A - A kind of device for increasing multi-rotor aerocraft flying distance - Google Patents
A kind of device for increasing multi-rotor aerocraft flying distance Download PDFInfo
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- CN107571992A CN107571992A CN201710843410.6A CN201710843410A CN107571992A CN 107571992 A CN107571992 A CN 107571992A CN 201710843410 A CN201710843410 A CN 201710843410A CN 107571992 A CN107571992 A CN 107571992A
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- rotor aerocraft
- rotor
- magnechuck
- aerocraft
- connecting rod
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Abstract
A kind of device for increasing multi-rotor aerocraft flying distance, belong to technical field of aerospace, including control terminal, the first multi-rotor aerocraft and the second multi-rotor aerocraft；Terminal wireless is controlled to control the first multi-rotor aerocraft and the second multi-rotor aerocraft；First multi-rotor aerocraft is provided with connecting rod, and connecting rod is located at the position of centre of gravity below the first multi-rotor aerocraft, and the end of connecting rod is provided with magnechuck, and the adsorption plane for the second multi-rotor aerocraft docks；Adsorption plane is installed, adsorption plane is located at the upper surface position of centre of gravity of the second multi-rotor aerocraft on the second multi-rotor aerocraft.During the first multi-rotor aerocraft flies with the second multi-rotor aerocraft, the dynamical system of only the first multi-rotor aerocraft starts, the dynamical system of second multi-rotor aerocraft is in holding state, a part of electric energy is saved for the second multi-rotor aerocraft, which adds the cruising time of the second multi-rotor aerocraft and flying distance.
Description
Technical field
A kind of device for increasing multi-rotor aerocraft flying distance, belong to technical field of aerospace, more particularly to a kind of growth
The device of multi-rotor aerocraft flying distance.
Background technology
Traditional multi-rotor aerocraft is mostly using battery as the energy, because the capacity of battery is smaller, so cruising time
It is usually no more than 40 minutes, voyage is limited by very large, and this is also the short slab of multi-rotor aerocraft.
The content of the invention
The purpose of the present invention is to overcome the above-mentioned deficiency of traditional multi-rotor aerocraft, there is provided one kind increases more rotor flyings
The device of device flying distance.
A kind of device for increasing multi-rotor aerocraft flying distance, including control terminal, the first multi-rotor aerocraft and the
Two multi-rotor aerocrafts；The control terminal wireless controls the first multi-rotor aerocraft and the second multi-rotor aerocraft；Described
One multi-rotor aerocraft is provided with connecting rod, and connecting rod is located at the position of centre of gravity below the first multi-rotor aerocraft, and connecting rod is erected
Directly magnechuck is installed, magnechuck electromagnetic principle, passes through electricity in the first multi-rotor aerocraft, the end of connecting rod
Source controls the magnetic force of magnechuck, and the adsorption plane for the second multi-rotor aerocraft docks；On second multi-rotor aerocraft
Adsorption plane is installed, the material that adsorption plane uses is the material easily adsorbed by magnechuck, and adsorption plane is located at rotor more than second
The upper surface position of centre of gravity of aircraft.
Preferably, the adsorption plane can use into magnechuck instead.
When the second multi-rotor aerocraft needs execution task, by controlling the multi-rotor aerocraft of terminal control first to take off
The top of the second multi-rotor aerocraft is flown to, calibrating position, magnechuck is directed at adsorption plane, the first multi-rotor aerocraft is down
Fly, magnechuck and adsorption plane fit together, and are powered to magnechuck, magnechuck adsorbs adsorption plane, then more than first
Rotor craft takes off with the second multi-rotor aerocraft, and the direction flown to is the side that the second multi-rotor aerocraft performs task
To after the segment distance that flies, the electricity of the first multi-rotor aerocraft can just enable the first multi-rotor aerocraft return alone
Departure location, at this moment, the dynamical system of the second multi-rotor aerocraft start, until the second multi-rotor aerocraft can independently fly
When, magnechuck power-off, separate magnechuck and adsorption plane, the first multi-rotor aerocraft determines starting point by built-in GPS
Information, then returns to alone takeoff point, and the second multi-rotor aerocraft continues task place of flying to.
The beneficial effects of the invention are as follows：The machine to be flown using the first multi-rotor aerocraft with the second multi-rotor aerocraft
System, during the first multi-rotor aerocraft flies with the second multi-rotor aerocraft, only the first multi-rotor aerocraft
Dynamical system starts, and the dynamical system of the second multi-rotor aerocraft is in holding state, is saved for the second multi-rotor aerocraft
A part of electric energy, which adds the cruising time of the second multi-rotor aerocraft and flying distance.
Brief description of the drawings
Fig. 1 is the first multi-rotor aerocraft and the second multi-rotor aerocraft docking schematic diagram, and Fig. 2 is connecting rod and adsorption plane
Structural representation.
Label in figure：The multi-rotor aerocrafts of 1- first, the multi-rotor aerocrafts of 2- second, 3- adsorption planes, 4- connecting rods, 41-
Magnechuck, 5- control terminals.
Embodiment
The present invention is illustrated below in conjunction with the accompanying drawings.
A kind of device for increasing multi-rotor aerocraft flying distance, including control terminal 5, the and of the first multi-rotor aerocraft 1
Second multi-rotor aerocraft 2；Control controlled in wireless first multi-rotor aerocraft 1 of terminal 5 and the second multi-rotor aerocraft 2；
Connecting rod 4 is installed, connecting rod 4 is located at the center of gravity position of the lower section of the first multi-rotor aerocraft 1 on first multi-rotor aerocraft 1
Put, connecting rod 4 is vertically to the first multi-rotor aerocraft 1, and the end of connecting rod 4 is provided with magnechuck 41, and magnechuck 41 is adopted
With with electromagnetic principle, by the magnetic force of power supply magnechuck 41, the adsorption plane 3 for the second multi-rotor aerocraft 1 docks；
Adsorption plane 3 is installed, the material that adsorption plane 3 uses is easily to be adsorbed by magnechuck 41 on second multi-rotor aerocraft 2
Material, adsorption plane 3 is located at the upper surface position of centre of gravity of the second multi-rotor aerocraft 2.
When the second multi-rotor aerocraft 2 needs execution task, by controlling terminal 5 to control the first multi-rotor aerocraft 1
Take off and fly to the top of the second multi-rotor aerocraft 2, calibrating position, magnechuck 41 is directed at adsorption plane 3, rotor flies more than first
Row device 1 down flies, and magnechuck 41 and adsorption plane 3 fit together, and are powered to magnechuck 41, and magnechuck 41 adsorbs
Attached face 3, then the first multi-rotor aerocraft 1 taken off with the second multi-rotor aerocraft 2, the direction flown to is that rotor flies more than second
Row device 2 performs the direction of task, and after the segment distance that flies, the electricity of the first multi-rotor aerocraft 1 can just make to revolve first more
Rotor aircraft 1 can return to departure location alone, and at this moment, the dynamical system of the second multi-rotor aerocraft 2 starts, until more than second rotations
Rotor aircraft 2 can independent flight when, magnechuck 41 powers off, and departs from connecting rod 4 and adsorption plane 3, the first multi-rotor aerocraft 1
Origin information is determined by built-in GPS, then returns to takeoff point alone, the second multi-rotor aerocraft 2 is with continuing the task of flying to
Point.
Claims (2)
- A kind of 1. device for increasing multi-rotor aerocraft flying distance, it is characterised in that：Including control terminal (5), more than first rotations Rotor aircraft (1) and the second multi-rotor aerocraft (2)；It is described control terminal (5) first multi-rotor aerocraft of controlled in wireless (1) and Second multi-rotor aerocraft (2)；Connecting rod (4) is installed, connecting rod (4) is located at first on first multi-rotor aerocraft (1) Position of centre of gravity below multi-rotor aerocraft (1), connecting rod (4) are vertically to the first multi-rotor aerocraft (1), connecting rod (4) End is provided with magnechuck (41), magnechuck (41) use electromagnetic principle, passes through power supply magnechuck (41) Magnetic force, the adsorption plane (3) for the second multi-rotor aerocraft (1) dock；Suction is installed on second multi-rotor aerocraft (2) Attached face (3), the material that adsorption plane (3) uses are the materials easily adsorbed by magnechuck (41), and adsorption plane (3) is located at more than second The upper surface position of centre of gravity of rotor craft (2).
- A kind of 2. device for increasing multi-rotor aerocraft flying distance according to claim 1, it is characterised in that：The suction Attached face (3) can use into magnechuck instead.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710843410.6A CN107571992A (en) | 2017-09-18 | 2017-09-18 | A kind of device for increasing multi-rotor aerocraft flying distance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710843410.6A CN107571992A (en) | 2017-09-18 | 2017-09-18 | A kind of device for increasing multi-rotor aerocraft flying distance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107571992A true CN107571992A (en) | 2018-01-12 |
Family
ID=61032773
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710843410.6A Pending CN107571992A (en) | 2017-09-18 | 2017-09-18 | A kind of device for increasing multi-rotor aerocraft flying distance |
Country Status (1)
| Country | Link |
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| CN (1) | CN107571992A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11912435B2 (en) | 2019-07-10 | 2024-02-27 | Israel Aerospace Industries Ltd. | Air vehicle system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8657228B2 (en) * | 2010-11-01 | 2014-02-25 | Textron Innovations Inc. | Method and apparatus for actively manipulating aerodynamic surfaces |
| CN106716273A (en) * | 2016-07-28 | 2017-05-24 | 深圳市大疆创新科技有限公司 | A multirotor unmanned aerial vehicle and a controlling method thereof |
| CN106853870A (en) * | 2017-01-03 | 2017-06-16 | 上海量明科技发展有限公司 | The platform that rises and falls of aircraft, control system, takeoff method and landing method |
| CN106882386A (en) * | 2017-03-10 | 2017-06-23 | 佛山市神风航空科技有限公司 | The landing mode and its device of a kind of aircraft |
-
2017
- 2017-09-18 CN CN201710843410.6A patent/CN107571992A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8657228B2 (en) * | 2010-11-01 | 2014-02-25 | Textron Innovations Inc. | Method and apparatus for actively manipulating aerodynamic surfaces |
| CN106716273A (en) * | 2016-07-28 | 2017-05-24 | 深圳市大疆创新科技有限公司 | A multirotor unmanned aerial vehicle and a controlling method thereof |
| CN106853870A (en) * | 2017-01-03 | 2017-06-16 | 上海量明科技发展有限公司 | The platform that rises and falls of aircraft, control system, takeoff method and landing method |
| CN106882386A (en) * | 2017-03-10 | 2017-06-23 | 佛山市神风航空科技有限公司 | The landing mode and its device of a kind of aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11912435B2 (en) | 2019-07-10 | 2024-02-27 | Israel Aerospace Industries Ltd. | Air vehicle system |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180112 |