CN204433048U - Two lift-source unmanned plane - Google Patents
Two lift-source unmanned plane Download PDFInfo
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- CN204433048U CN204433048U CN201520106845.9U CN201520106845U CN204433048U CN 204433048 U CN204433048 U CN 204433048U CN 201520106845 U CN201520106845 U CN 201520106845U CN 204433048 U CN204433048 U CN 204433048U
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- fuselage
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- air bag
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Abstract
The utility model discloses a kind of two lift-source unmanned plane, comprise fuselage (1), be placed in the controller in fuselage (1), multiple support arms (4) symmetrical about fuselage (1) and be located at the rotor assemblies of each support arm (4) away from one end of fuselage (1), it also comprises the airbag apparatus controlled by controller, cylindric in horizontally set of described fuselage (1), described airbag apparatus comprises the air bag (2) and gas filled device that are foldable to fuselage (1) inner chamber, and described air bag (2) is opened rear transverse direction and is placed in directly over described fuselage (1).This pair of lift-source unmanned plane flying power is stronger, easy to operate.
Description
Technical field
The utility model relates to unmanned plane field, particularly a kind of two lift-source unmanned plane.
Background technology
Unmanned plane starts a kind of aircraft practical gradually at present, its have maneuverability, reaction fast, the advantage such as unmanned flight, operation requirements be low.Unmanned plane loads multiclass sensor, such as camera, image real-time Transmission, high-risk areas detecting function can be realized, be widely used in the fields such as fire-fighting, military affairs, traffic, police service, exploration and meteorology, to realize cruise shooting to designated area and supervision.At present, unmanned plane is carry out manufacturing and designing based on the flight theory of helicopter mostly, can realize vertical lift and high-altitude hovering, thus meet the requirement of taking photo by plane and monitoring, the most generally fixed-wing formula and many rotary wind types (such as, four rotors).But problem is, the lift-source of the unmanned plane of prior art is generally only rotor, and the meteorological conditions during work of the unmanned plane of fixed-wing formula requires high, and landing requires high, and cost is higher; And its propulsion source of many rotary wind types unmanned plane is generally battery, the battery as the unmanned plane of existing four rotors is generally 5000mAh, and its flight time is only 15-20 minute, and flying power is poor.
Summary of the invention
Technical problem to be solved in the utility model is: provide two lift-source unmanned planes that a kind of flying power is stronger, easy to operate.
The technical scheme in the invention for solving the above technical problem is: a kind of two lift-source unmanned plane, comprise fuselage, the controller be placed in fuselage, about the symmetrical multiple support arm of fuselage and be located at the rotor assemblies of each support arm away from one end of fuselage, it also comprises the airbag apparatus controlled by controller, described fuselage is the cylindric of horizontally set, described airbag apparatus comprises the air bag and gas filled device that are foldable to fuselage inner chamber, and is laterally placed in directly over described fuselage after described airbag-releasing.
Compared with prior art, the utility model has the advantage of: this pair of lift-source unmanned plane can form the second lift-source by air bag, air bag can play and well auxiliaryly rise function, makes unmanned plane flying power of the present utility model stronger.Laterally be placed in directly over fuselage after airbag-releasing, and air bag is foldable to fuselage inner chamber, is inflated when needed by gas filled device, very practical.
As preferably, the inner chamber of described fuselage is provided with the upper strata cavity of the air bag after for accommodating and folding and the lower floor's cavity for accommodating controller, electronic governor and supply unit successively, and the upper end of the upper strata cavity of described fuselage is provided with the opening for airbag-releasing; And described air bag is the cigar shape of horizontally set.Like this, the design of fuselage is more compact, and the opening of convenient air bag after the inner chamber of fuselage is divided into upper and lower layer, the layout of controller, electronic governor and supply unit is also more reasonable.
As preferably, described gas filled device comprises source of the gas and appendix, and described source of the gas is placed in the inner chamber of described fuselage, and one end of described appendix is connected with source of the gas, and the other end and the described airbags of described appendix connect.
As preferably, described supply unit comprises the first battery and the second battery, and described controller is placed in the middle part of lower floor's cavity of described fuselage, and the first described battery and the second battery are symmetrically arranged in lower floor's cavity of described fuselage.Like this, whole airframe structure is more symmetrical, and center of gravity is relatively more steady, and the balance of unmanned plane is better.
As preferably, the bottom of described fuselage is provided with for hanging standby hanger.Like this, pick up camera or other equipment of taking photo by plane can be hung easily
Accompanying drawing explanation
Fig. 1 is the main TV structure schematic diagram airbag-releasing of the two lift-source unmanned plane of the utility model.
Fig. 2 is the plan structure schematic diagram of the two lift-source unmanned plane of the utility model.
In Fig. 1-2: 1 fuselage, 1.1 upper strata cavitys, 1.2 lower floor's cavitys, 2 air bags, 3 hangers, 4 support arms.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiment of the present utility model is further described.
As shown in Figure 1-2, a kind of two lift-source unmanned plane, comprise fuselage 1, the controller be placed in fuselage 1, about the symmetrical multiple support arms 4 of fuselage 1 and be located at the rotor assemblies of each support arm 4 away from one end of fuselage 1, it is characterized in that: it also comprises the airbag apparatus controlled by controller, described fuselage 1 is the cylindric of horizontally set, described airbag apparatus comprises the air bag 2 and gas filled device that are foldable to fuselage 1 inner chamber, and described air bag 2 is opened rear transverse direction and is placed in directly over described fuselage 1.
The inner chamber of described fuselage 1 is provided with the upper strata cavity 1.1 of the air bag 2 after for accommodating and folding and the lower floor's cavity 1.2 for accommodating controller, electronic governor and supply unit successively, and the upper end of the upper strata cavity 1.1 of described fuselage 1 is provided with the opening opened for air bag 2; And the described cigar shape of air bag 2 in horizontally set.
Described gas filled device comprises source of the gas and appendix, and described source of the gas is placed in the inner chamber of described fuselage 1, and one end of described appendix is connected with source of the gas, and the other end of described appendix is connected with described air bag 2.
Described supply unit comprises the first battery and the second battery, and described controller is placed in the middle part of lower floor's cavity 1.2 of described fuselage 1, and the first described battery and the second battery are symmetrically arranged in lower floor's cavity 1.2 of described fuselage 1.
The bottom of described fuselage 1 is provided with for hanging standby hanger 3.
Below only just most preferred embodiment of the present utility model is described, but can not be interpreted as it is limitations on claims.The utility model is not only confined to above embodiment, and its concrete structure allows to change.All various changes done in the protection domain of the utility model independent claims are all in the utility model protection domain.
Claims (5)
1. a two lift-source unmanned plane, comprise fuselage (1), be placed in the controller in fuselage (1), multiple support arms (4) symmetrical about fuselage (1) and be located at the rotor assemblies of each support arm (4) away from one end of fuselage (1), it is characterized in that: it also comprises the airbag apparatus controlled by controller, cylindric in horizontally set of described fuselage (1), described airbag apparatus comprises the air bag (2) and gas filled device that are foldable to fuselage (1) inner chamber, and described air bag (2) is opened rear transverse direction and is placed in directly over described fuselage (1).
2. according to claim 1 pair of lift-source unmanned plane, it is characterized in that: the inner chamber of described fuselage (1) is provided with the upper strata cavity (1.1) of the air bag (2) after for accommodating and folding and the lower floor's cavity (1.2) for accommodating controller, electronic governor and supply unit successively, the upper end of the upper strata cavity (1.1) of described fuselage (1) is provided with the opening opened for air bag (2); And the cigar shape of described air bag (2) in horizontally set.
3. according to claim 1 and 2 pair of lift-source unmanned plane, it is characterized in that: described gas filled device comprises source of the gas and appendix, described source of the gas is placed in the inner chamber of described fuselage (1), and one end of described appendix is connected with source of the gas, the other end of described appendix is connected with described air bag (2).
4. according to claim 2 pair of lift-source unmanned plane, it is characterized in that: described supply unit comprises the first battery and the second battery, described controller is placed in the middle part of lower floor's cavity (1.2) of described fuselage (1), and the first described battery and the second battery are symmetrically arranged in lower floor's cavity (1.2) of described fuselage (1).
5. according to claim 1 pair of lift-source unmanned plane, is characterized in that: the bottom of described fuselage (1) is provided with for hanging standby hanger (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520106845.9U CN204433048U (en) | 2015-02-13 | 2015-02-13 | Two lift-source unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520106845.9U CN204433048U (en) | 2015-02-13 | 2015-02-13 | Two lift-source unmanned plane |
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| Publication Number | Publication Date |
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| CN204433048U true CN204433048U (en) | 2015-07-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520106845.9U Active CN204433048U (en) | 2015-02-13 | 2015-02-13 | Two lift-source unmanned plane |
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| CN (1) | CN204433048U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105151270A (en) * | 2015-08-28 | 2015-12-16 | 浪潮集团有限公司 | Blank balloon assembly on symmetric-layout rotorcrafts |
| GB2576504A (en) * | 2018-08-20 | 2020-02-26 | Firma Engineering Ltd | An apparatus |
-
2015
- 2015-02-13 CN CN201520106845.9U patent/CN204433048U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105151270A (en) * | 2015-08-28 | 2015-12-16 | 浪潮集团有限公司 | Blank balloon assembly on symmetric-layout rotorcrafts |
| GB2576504A (en) * | 2018-08-20 | 2020-02-26 | Firma Engineering Ltd | An apparatus |
| GB2576504B (en) * | 2018-08-20 | 2020-08-26 | Firma Engineering Ltd | A deployment and retrieval system for an unmanned aerial vehicle with a gas envelope |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20180621 Address after: 315100 room 701-22, 6 and 7, 5 Kexin building, Yinzhou District first South Street, Ningbo, Zhejiang Patentee after: NINGBO AN SHU YE INTELLIGENT TECHNOLOGY Co.,Ltd. Address before: 315000 No. 332, Yang Mu Road, hi tech Zone, Ningbo, Zhejiang Patentee before: Li Lianwai |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231122 Address after: Room 1301-4c, No. 215 Panhuo Road, Panhuo Street, Yinzhou District, Ningbo City, Zhejiang Province, 315043 Patentee after: Ningbo Daniu Construction Technology Co.,Ltd. Address before: 315100 room 701-22, 6 and 7, 5 Kexin building, Yinzhou District first South Street, Ningbo, Zhejiang Patentee before: NINGBO AN SHU YE INTELLIGENT TECHNOLOGY Co.,Ltd. |