CN204489177U - Four rotor unmanned aircrafts - Google Patents
Four rotor unmanned aircrafts Download PDFInfo
- Publication number
- CN204489177U CN204489177U CN201420820746.2U CN201420820746U CN204489177U CN 204489177 U CN204489177 U CN 204489177U CN 201420820746 U CN201420820746 U CN 201420820746U CN 204489177 U CN204489177 U CN 204489177U
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- China
- Prior art keywords
- suspension
- rotor unmanned
- protective case
- unmanned aircrafts
- motor
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- 239000000725 suspension Substances 0.000 claims abstract description 71
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 23
- 239000001257 hydrogen Substances 0.000 claims abstract description 23
- 125000004435 hydrogen atom Chemical group [H]* 0.000 claims abstract description 23
- 230000001681 protective effect Effects 0.000 claims abstract description 22
- 239000000203 mixture Substances 0.000 claims abstract 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 9
- 229910052744 lithium Inorganic materials 0.000 claims description 9
- 229920000642 polymer Polymers 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- 229910052799 carbon Inorganic materials 0.000 claims description 4
- 239000000835 fiber Substances 0.000 claims description 4
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 239000000470 constituent Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000005672 electromagnetic field Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Classifications
-
- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
Landscapes
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The utility model discloses a kind of four rotor unmanned aircrafts, " ten " font suspension body that it is made up of the first suspension and the second suspension, motor, screw propeller, GPS and protective case composition, protective case is provided with above described first suspension and the second suspension intersection location, described protective case edge is provided with GPS, motor is connected at the two ends of described first suspension and the second suspension, described motor output shaft is connected with screw propeller, hydrogen cell is connected with in the below of described first suspension and the second suspension intersection location, described hydrogen cell is electrically connected with motor.The beneficial effects of the utility model are: the cruise duration with overlength, can operation aloft for a long time.
Description
Technical field
The utility model relates to unmanned vehicle field, is specifically related to a kind of four rotor unmanned aircrafts adopting hydrogen cell microkinetic.
Background technology
Four rotor unmanned aircrafts are emerging a kind of unmanned vehicle technology grown up in recent years, four rotor unmanned aircrafts are compared with other aircraft, its physical construction is simply compact, take action more flexible, landing environmental requirement is lower, there is good operating characteristic, can realize among a small circle taking off, hover, land.Due to these features, the numerous areas such as quadrotor is widely used in power-line patrolling, takes photo by plane, monitors, investigates, emergency management and rescue.
Four current rotor unmanned aircrafts mainly adopt lithium cell as power plant, and power capacity is limited, and cruise duration is short, can not the task of executive chairman when navigating, and have impact on its application in a lot of field.
Utility model content
It is not enough that the utility model overcomes the short grade of power-on time that in prior art, four rotor unmanned aircrafts employing lithium celies exist as power plant, there is provided a kind of structure simple, be easy to carry, flight stability, full automaticity degree is high, noise is little, can operation under lowered in field environment, there is the cruise duration of overlength, can for a long time at four rotor unmanned aircrafts controlling operation.
For achieving the above object, the utility model is by the following technical solutions:
A kind of four rotor unmanned aircrafts; " ten " font suspension body, motor, screw propeller, GPS and protective case that it is made up of the first suspension and the second suspension form; protective case is provided with above described first suspension and the second suspension intersection location; described protective case edge is provided with GPS; motor is connected at the two ends of described first suspension and the second suspension; described motor output shaft is connected with screw propeller; be connected with hydrogen cell in the below of described first suspension and the second suspension intersection location, described hydrogen cell is electrically connected with motor.
By being connected hydrogen cell at the first suspension with the below of the second suspension intersection location in the technical program, the mode adopting lithium battery power supply in prior art is replaced by hydrogen cell, because hydrogen cell capacity increases, thus add the cruise duration of aircraft, enable aircraft operation aloft for a long time.
Further technical scheme is, described hydrogen cell adopts the mode hung to be arranged on the below of the first suspension and the second suspension intersection location.
By adopting the mode hung hydrogen cell be arranged on the below of the first suspension and the second suspension intersection location thus make the sinking again of aircraft entirety in the technical program, add the overall wind resistance flight performance of aircraft.
Further technical scheme is, described first suspension two ends are provided with support foot rest.
Further technical scheme is, described second suspension two ends are provided with support foot rest.
By arranging support foot rest at the first suspension two ends in the technical program, support foot rest being set at the second suspension two ends, forming a supporting plane by four support foot rests, being convenient to steadily putting in aircraft descent.
Further technical scheme is, described first suspension and the second suspension all adopt carbon fibre material to make.
In the technical program, due to carbon fibre material, to have quality lighter than metallic aluminium, intensity is but higher than the performance of iron and steel, so the quality of the first suspension and the second suspension alleviates, reaches and the weight of aircraft entirety is reduced, from but aircraft reduce in the load-carrying of flight course, add cruise duration.
Further technical scheme is, described protective case is semisphere.
In the technical program by arrange protective case can in rainy day or the large weather of moisture flight thus the wherein airborne electronic machine of protection, by protective case is arranged to semisphere, decrease windage, make aircraft be subject to windage little.
Further technical scheme is, described GPS is connected with protective case by bracing frame.
In the technical program, GPS is connected with protective case by bracing frame, thus improves the height of GPS, lower the impact that magnetic field is caused it.
Further technical scheme is, described hydrogen cell comprises power supply module, and described power supply module is made up of the battery protection module be electrically connected to each other, lithium polymer battery, 5v supply module, 12v supply module and 28v supply module.
By providing lithium polymer battery in the technical program, can export as auxiliary power in big current situation.
Compared with prior art, the beneficial effects of the utility model are:
The utility model is not only easy to carry, flight stability, full-automatic degree is high, noise is little, can operation under lowered in field environment, also there is the cruise duration of overlength, can operation aloft for a long time.In the work such as power-line patrolling, emergency repair, disaster relief prospecting, make ground staff obtain aerial multi-view image, increase work efficiency, reduce the cost.
Accompanying drawing explanation
Fig. 1 is the structural representation of four rotor unmanned aircrafts of a kind of embodiment of the utility model.
As shown in Figure 1, wherein corresponding Reference numeral name is called:
1 screw propeller, 2 first suspensions, 3 hydrogen cells, 4 support foot rests, 5 second suspensions, 6 bracing frames, 7 GPS, 8 protective cases.
Fig. 2 is the power pack structural representation of four rotor unmanned aircrafts of a kind of embodiment of the utility model.
As shown in Figure 2, wherein corresponding Reference numeral name is called:
31 lighium polymer electromagnetism, 32 5V supply modules, 33 12V supply modules, 34 28V supply modules, 35 battery protection modules.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is further elaborated.
One four rotor unmanned aircraft as shown in Figure 1, " ten " font suspension body that it is made up of the first suspension 2 and the second suspension 5, motor, screw propeller 1, GPS7 and protective case 8 form, protective case 8 is provided with above described first suspension 2 and the second suspension 5 intersection location, described protective case 8 edge is provided with GPS7, motor is connected at the two ends of described first suspension 2 and the second suspension 5, described motor output shaft is connected with screw propeller 1, hydrogen cell 3 is connected with in the below of described first suspension 2 and the second suspension 5 intersection location, described hydrogen cell 3 adopts the mode hung to be arranged on the below of the first suspension 2 and the second suspension 5 intersection location, with the mounting means by adopting suspension, thus reduce the center of gravity of aircraft, improve wind resistance power, described hydrogen cell 3 is electrically connected with motor, by hydrogen cell 3 for electric machine rotation provides power, because the capacitance of hydrogen cell 3 is large, thus make machine operation time expand, thus add the cruise time of aircraft.
According to an embodiment of utility model, described first suspension 2 two ends are provided with support foot rest 4, described second suspension 5 two ends are provided with support foot rest 4, described support foot rest 4 is four, be separately positioned on the two ends of the first suspension 2 and the second suspension 5, the position of support foot rest 4 particular location close motor on the first suspension 2 or the second suspension 5.
According to an embodiment of the present utility model, described first suspension 2 and the second suspension 5 are the pipe of inner hollow, and adopt carbon fibre material to make, by adopting said structure and material to make the first suspension 2 and the second suspension 5, thus alleviate the weight of aircraft entirety, thus improve the time of aircraft continuation of the journey.
According to an embodiment of the present utility model; described protective case 8 is semisphere; the air resistance in flight course is decreased by hemispherical shape; described GPS7 is connected with protective case 8 by bracing frame 6; GPS7 adopts said structure to increase from the height making GPS7 arrange, and avoids the impact of electromagnetic field on GPS7.
The power pack structure of a kind of four rotor unmanned aircrafts as shown in Figure 2; described hydrogen cell 3 comprises power supply module, and described power supply module is made up of the battery protection module 35 be electrically connected to each other, lithium polymer battery 31,5v supply module 32,12v supply module 33 and 28v supply module 34.
Its effect is in order to avoid avoiding the outgoing current of hydrogen cell 3 not enough when unmanned vehicle carries out large powered maneuver, therefore adopt lithium polymer battery 31 as part, power module, according to the current needs of electricity consumption device, takes the circumstances into consideration to use lithium polymer battery 31 to originate as compensates electric.
Spoken of in this manual " embodiment ", " another embodiment ", " embodiment ", etc., refer to the specific features, structure or the feature that describe in conjunction with this embodiment and be included at least one embodiment of the application's generality description.Multiple place occurs that statement of the same race is not necessarily refer to same embodiment in the description.Furthermore, when describing specific features, structure or a feature in conjunction with any embodiment, what advocate is also drop in scope of the present utility model to realize this feature, structure or feature in conjunction with other embodiments.
Although be described utility model with reference to multiple explanatory embodiment of the present utility model here, but, should be appreciated that, those skilled in the art can design a lot of other amendment and embodiment, these amendments and embodiment will drop within spirit disclosed in the present application and spirit.More particularly, in the scope of, accompanying drawing open in the application and claim, multiple modification and improvement can be carried out to the constituent elements of subject combination layout and/or layout.Except the modification of carrying out constituent elements and/or layout is with except improvement, to those skilled in the art, other purposes also will be obvious.
Claims (8)
1. a rotor unmanned aircraft, " ten " font suspension body that it is made up of the first suspension (2) and the second suspension (5), motor, screw propeller (1), GPS (7) and protective case (8) composition, protective case (8) is provided with in the top of described first suspension (2) and the second suspension (5) intersection location, described protective case (8) edge is provided with GPS (7), motor is connected at the two ends of described first suspension (2) and the second suspension (5), described motor output shaft is connected with screw propeller (1), it is characterized in that: be connected with hydrogen cell (3) in the below of described first suspension (2) and the second suspension (5) intersection location, described hydrogen cell (3) is electrically connected with motor.
2. four rotor unmanned aircrafts according to claim 1, is characterized in that described hydrogen cell (3) adopts the mode hung to be arranged on the below of the first suspension (2) and the second suspension (5) intersection location.
3. four rotor unmanned aircrafts according to claim 1 and 2, is characterized in that described first suspension (2) two ends are provided with support foot rest (4).
4. four rotor unmanned aircrafts according to claim 1 and 2, is characterized in that described second suspension (5) two ends are provided with support foot rest (4).
5. four rotor unmanned aircrafts according to claim 1, is characterized in that described first suspension (2) and the second suspension (5) all adopt carbon fibre material to make.
6. four rotor unmanned aircrafts according to claim 1, is characterized in that described protective case (8) is semisphere.
7. four rotor unmanned aircrafts according to claim 1, is characterized in that described GPS (7) is connected with protective case (8) by bracing frame (6).
8. four rotor unmanned aircrafts according to claim 1; it is characterized in that described hydrogen cell (3) comprises power supply module, described power supply module is made up of the battery protection module be electrically connected to each other (35), lithium polymer battery (31), 5v supply module (32), 12v supply module (33) and 28v supply module (34).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420820746.2U CN204489177U (en) | 2014-12-19 | 2014-12-19 | Four rotor unmanned aircrafts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420820746.2U CN204489177U (en) | 2014-12-19 | 2014-12-19 | Four rotor unmanned aircrafts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204489177U true CN204489177U (en) | 2015-07-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420820746.2U Active CN204489177U (en) | 2014-12-19 | 2014-12-19 | Four rotor unmanned aircrafts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204489177U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105277177A (en) * | 2015-10-17 | 2016-01-27 | 佛山市安尔康姆航空科技有限公司 | Oblique photography system adopting multi-rotor unmanned aerial vehicle |
| CN106697274A (en) * | 2017-01-20 | 2017-05-24 | 蜂巢航宇科技（北京）有限公司 | Six-rotor wing unmanned aerial vehicle |
| CN106943727A (en) * | 2017-04-18 | 2017-07-14 | 佛山市神风航空科技有限公司 | A kind of Electric booster |
| CN107200118A (en) * | 2017-04-20 | 2017-09-26 | 湖北工业大学 | Fuel cell plant protection depopulated helicopter |
| CN107380458A (en) * | 2017-08-07 | 2017-11-24 | 雅各·维拉萨 | A kind of manned investigation single-blade list rotor craft of long endurance of hovering |
| CN107883927A (en) * | 2017-11-09 | 2018-04-06 | 陕西科技大学 | Quadrotor plant growth inspection system |
| US11368002B2 (en) | 2016-11-22 | 2022-06-21 | Hydro-Quebec | Unmanned aerial vehicle for monitoring an electrical line |
-
2014
- 2014-12-19 CN CN201420820746.2U patent/CN204489177U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105277177A (en) * | 2015-10-17 | 2016-01-27 | 佛山市安尔康姆航空科技有限公司 | Oblique photography system adopting multi-rotor unmanned aerial vehicle |
| US11368002B2 (en) | 2016-11-22 | 2022-06-21 | Hydro-Quebec | Unmanned aerial vehicle for monitoring an electrical line |
| CN106697274A (en) * | 2017-01-20 | 2017-05-24 | 蜂巢航宇科技（北京）有限公司 | Six-rotor wing unmanned aerial vehicle |
| CN106943727A (en) * | 2017-04-18 | 2017-07-14 | 佛山市神风航空科技有限公司 | A kind of Electric booster |
| CN107200118A (en) * | 2017-04-20 | 2017-09-26 | 湖北工业大学 | Fuel cell plant protection depopulated helicopter |
| CN107200118B (en) * | 2017-04-20 | 2020-02-11 | 湖北工业大学 | Unmanned helicopter of fuel cell plant protection |
| CN107380458A (en) * | 2017-08-07 | 2017-11-24 | 雅各·维拉萨 | A kind of manned investigation single-blade list rotor craft of long endurance of hovering |
| CN107883927A (en) * | 2017-11-09 | 2018-04-06 | 陕西科技大学 | Quadrotor plant growth inspection system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |