CN106275408A - A kind of rotor wing unmanned aerial vehicle - Google Patents
A kind of rotor wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106275408A CN106275408A CN201610842919.4A CN201610842919A CN106275408A CN 106275408 A CN106275408 A CN 106275408A CN 201610842919 A CN201610842919 A CN 201610842919A CN 106275408 A CN106275408 A CN 106275408A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- aerial vehicle
- unmanned aerial
- wing unmanned
- rotor wing
- 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
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses a kind of rotor wing unmanned aerial vehicle, including fuselage, horn, motor and rotor, described horn is located on fuselage, motor is located on horn, rotor is located in the rotating shaft of motor, described fuselage interior is provided with battery unit, and described fuselage is provided with bag box and hydrogen generator, is provided with, in described bag box, the hydrogen gas bag being connected with hydrogen generator.This rotor wing unmanned aerial vehicle reasonable in design, fuselage roof can allow hydrogen gas bag work as required, and unmanned plane has only to provide the least lift to get final product work, significantly extends unmanned plane stream time；And the setting of hydrogen gas bag, is possible to prevent quick air crash of breaking down；Unmanned plane compact conformation, little by windage, good stability.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, especially relate to a kind of rotor wing unmanned aerial vehicle.
Background technology
Unmanned plane volume is little, lightweight, low cost, be widely used in take photo by plane, security protection, monitoring, agricultural and express delivery dispensing etc..
Existing unmanned plane mostly is rotor wing unmanned aerial vehicle, and the power of unmanned plane is provided by battery, owing to unmanned plane volume is little, and electricity
Tankage is limited, and stream time is restricted, it is impossible to aloft work for a long time；And unmanned plane such as breaks down, soon
Speed air crash, danger is the biggest；Unmanned plane aloft shoots, by wind-force and self vibrate, poor stability, and impact shooting.
Summary of the invention
Not enough for prior art, the technical problem to be solved is to provide a kind of rotor wing unmanned aerial vehicle, to reach
The purpose that can the most aloft work.
In order to solve above-mentioned technical problem, the technical solution adopted in the present invention is:
This rotor wing unmanned aerial vehicle, including fuselage, horn, motor and rotor, described horn is located on fuselage, and motor is located at machine
On arm, rotor is located in the rotating shaft of motor, and described fuselage interior is provided with battery unit, and described fuselage is provided with bag box and hydrogen is sent out
Raw device, is provided with, in described bag box, the hydrogen gas bag being connected with hydrogen generator.
Further, described underbelly is provided with bracing frame, and bracing frame is the steel-tube construction of one group of hollow.
Described underbelly is provided with bracing frame, and the bottom of bracing frame is provided with roller.
Described underbelly is provided with bracing frame, and the bottom of bracing frame is provided with buffering spring sheet.
It is provided with battery in the steel pipe of described hollow.
Described bag box is located at the top of fuselage, and the top of bag box has through hole, and through hole is circular port.
Being provided with, in described bag box, the joint being connected with hydrogen gas bag, joint is provided with air bleeding valve.
Being provided with control unit in described fuselage, air bleeding valve is electromagnetic valve, and electromagnetic valve is connected with control unit.
Described fuselage is provided with temperature sensor, and temperature sensor is connected with control unit.
Described fuselage is provided with wind sensor, and wind sensor is connected with control unit.
The present invention compared with prior art, has the advantage that
This rotor wing unmanned aerial vehicle reasonable in design, fuselage roof can allow hydrogen gas bag work as required, and unmanned plane only needs
The lift providing the least gets final product work, significantly extends unmanned plane stream time；And the setting of hydrogen gas bag, can in case
Only break down quick air crash；Unmanned plane compact conformation, little by windage, good stability.
Accompanying drawing explanation
Content expressed by width accompanying drawing each to this specification and the labelling in figure are briefly described below:
Fig. 1 is unmanned plane structural representation one of the present invention.
Fig. 2 is that schematic diagram fixed by fuselage interior battery of the present invention.
Fig. 3 is unmanned plane structural representation two of the present invention.
Fig. 4 is unmanned plane structural representation three of the present invention.
In figure: 1. fuselage, 2. bag box, 3. horn, 4. motor, 5. rotating shaft, 6. rotor, 7. bracing frame, 8. gripper shoe, 9. stretch
Contracting bar, 10. battery unit, 11. rubber blocks, 12. side block rubbers, 13. hydrogen gas bags, 14. battery blocks.
Detailed description of the invention
Below against accompanying drawing, by the description to embodiment, the detailed description of the invention of the present invention is made further details of
Explanation.
As shown in Figures 1 to 4, this rotor wing unmanned aerial vehicle, including fuselage 1, horn 3, motor 4, rotor 6, bracing frame 7, battery
Unit 10 and control unit.
Horn 3 is four, and horn 3 one end is fixing on the fuselage 1, and motor 4 is fixed on the other end of horn 3, four machines
Arm 3 cross is arranged, rotor 6 is located in the rotating shaft 5 of motor 4, and rotor 6 is positioned at the top of motor.
Horn 3 is provided with the protection board for protecting rotor, and rotor is positioned at protection board, and protection board can be arc and circle
Shape plate.
Fuselage 1 is circular box like structure, and battery unit 10 and ECU are fixed on fuselage interior, motor and battery unit
Between electrically connect.
The bottom of fuselage 1 is provided with passage, it is to avoid rainwater enters in fuselage, and fuselage interior is provided with temperature sensor, ventilation
The blower fan being connected with temperature sensor it is provided with at hole.During unmanned plane work in summer, the temperature of fuselage interior is higher, is led to by blower fan
Wind is lowered the temperature.
Fuselage 1 is internal is provided with the locating piece for locating batteries unit, and locating piece includes the rubber being located at bottom battery unit
Glue props up bracer 11 and is located at the side block rubber 12 of battery unit side, and side block rubber 12 is positioned at the side of battery unit 10 and fuselage 1
Between wall.Rubber block 11 arranges one group for uniform intervals, and ventilation effect is good.During rubber block 11 and side block rubber 12 are
Hollow structure, reduces fuselage and battery unit vibration, good stability.
Fuselage 1 is provided with bag box 2 and hydrogen generator, is provided with the hydrogen gas bag 13 being connected with hydrogen generator in bag box 2.Bag
Box is located at the top of fuselage, and the top of bag box 2 has through hole, and through hole is circular port.When hydrogen gas bag does not works, it is placed on a bag box
In；During hydrogen gas bag work, inflation hydrogen gas bag stretches out from through hole.
Unmanned plane has only to provide the least lift to get final product work, significantly extends unmanned plane stream time, and
The setting of hydrogen gas bag, is possible to prevent quick air crash of breaking down.
Being provided with, in bag box 2, the joint being connected with hydrogen gas bag, joint is provided with air bleeding valve.When unmanned plane has worked, row
Hydrogen in hydrogen gas bag is drained by air valve, it is simple to unmanned plane lands.
Containing iron powder in the material of hydrogen gas bag, bag box is provided with Magnet, and after the hydrogen in hydrogen gas bag is drained, hydrogen gas bag can be received
Contracting is inhaled on Magnet, on unmanned plane landing not impact.
Air bleeding valve is electromagnetic valve, and electromagnetic valve is connected with control unit.Fuselage is provided with temperature sensor and wind sensor,
Temperature sensor is all connected with control unit with wind sensor.When detecting wind-force and being bigger, control hydrogen gas bag and do not inflate work,
Avoid affecting the stability of unmanned plane.
Fuselage 1 bottom is provided with bracing frame 7, and bracing frame is the steel-tube construction of one group of hollow, and is provided with in the bottom of bracing frame
The bottom of roller or bracing frame is provided with buffering spring sheet.Further, in the steel pipe of hollow, it is provided with battery, improves the steady of unmanned plane
Qualitative and promote cruising time.
Horn 3 is the aluminium profile structure of hollow, by mould extrusion molding, lightweight, and intensity is high；Or horn is hollow
Frame structure.
Rotor is located at the upper end of machine shaft, and the rotating shaft lower end of motor is provided with swivel plate, and the outer rim of swivel plate is provided with ring
Connected in star.During unmanned plane work, swivel plate high speed rotating, unmanned plane can be stablized by annular groove, the impact of wind-force can be reduced,
Ensure aerial photography effect.
The lower section of fuselage 1 is provided with gripper shoe 8 and bracing frame 7, and gripper shoe is positioned at bracing frame.Gripper shoe and fuselage are by even
Bar is connected.Bracing frame is provided with the slide block that can slide up and down along bracing frame, and gripper shoe is connected with slide block by motion bar, and connecting rod is
Expansion link 9.
During skyscraper dispensing express delivery, express delivery is put on the supporting plate, and gripper shoe distance fuselage has a certain distance, it is simple to fast
Pass picking and placeing of article.
Gripper shoe is provided with magnet piece, and corresponding magnet piece is provided with stainless steel framework, and during dispensing small volume article, article are permissible
Prevent in stainless steel framework, and pick and place conveniently.
The lower section of fuselage 1 is provided with bracing frame and battery block 14, and battery block is connected with fuselage by rubber rods, and battery block is positioned at
In bracing frame.The cruising time of unmanned plane can be increased, and unmanned plane can be stablized, the impact of wind-force can be reduced.
Above in conjunction with accompanying drawing, the present invention is exemplarily described, it is clear that the present invention implements not by aforesaid way
Restriction, as long as have employed the design of the present invention and the improvement of various unsubstantialities that technical scheme is carried out, or the most improved will
Design and the technical scheme of the present invention directly apply to other occasion, all within protection scope of the present invention.
Claims (10)
1. a rotor wing unmanned aerial vehicle, including fuselage, horn, motor and rotor, described horn is located on fuselage, and motor is located at machine
On arm, rotor is located in the rotating shaft of motor, and described fuselage interior is provided with battery unit, it is characterised in that: described fuselage is provided with
Bag box and hydrogen generator, be provided with, in described bag box, the hydrogen gas bag being connected with hydrogen generator.
2. rotor wing unmanned aerial vehicle as claimed in claim 1, it is characterised in that: described underbelly is provided with bracing frame, and bracing frame is one
The steel-tube construction of group hollow.
3. rotor wing unmanned aerial vehicle as claimed in claim 1, it is characterised in that: described underbelly is provided with bracing frame, the end of bracing frame
Portion is provided with roller.
4. rotor wing unmanned aerial vehicle as claimed in claim 1, it is characterised in that: described underbelly is provided with bracing frame, the end of bracing frame
Portion is provided with buffering spring sheet.
5. rotor wing unmanned aerial vehicle as claimed in claim 2, it is characterised in that: it is provided with battery in the steel pipe of described hollow.
6. rotor wing unmanned aerial vehicle as claimed in claim 1, it is characterised in that: described bag box is located at the top of fuselage, the top of bag box
Having through hole, through hole is circular port.
7. as claimed in claim 1 rotor wing unmanned aerial vehicle, it is characterised in that: it is provided with connecing of being connected with hydrogen gas bag in described bag box
Head, joint is provided with air bleeding valve.
8. rotor wing unmanned aerial vehicle as claimed in claim 7, it is characterised in that: being provided with control unit in described fuselage, air bleeding valve is electricity
Magnet valve, electromagnetic valve is connected with control unit.
9. rotor wing unmanned aerial vehicle as claimed in claim 8, it is characterised in that: described fuselage is provided with temperature sensor, temperature sensing
Device is connected with control unit.
10. rotor wing unmanned aerial vehicle as claimed in claim 8, it is characterised in that: described fuselage is provided with wind sensor, and wind-force senses
Device is connected with control unit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610842919.4A CN106275408A (en) | 2016-09-23 | 2016-09-23 | A kind of rotor wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610842919.4A CN106275408A (en) | 2016-09-23 | 2016-09-23 | A kind of rotor wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106275408A true CN106275408A (en) | 2017-01-04 |
Family
ID=57712433
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610842919.4A Pending CN106275408A (en) | 2016-09-23 | 2016-09-23 | A kind of rotor wing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106275408A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108545174A (en) * | 2018-03-30 | 2018-09-18 | 中山市剑鸿电子科技有限公司 | A kind of overturning-preventing compact carrier unmanned plane |
| CN111717405A (en) * | 2020-06-23 | 2020-09-29 | 长沙航华电子科技有限公司 | Buoyancy auxiliary lifting device for unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1117054A (en) * | 1967-05-30 | 1968-06-12 | Arthur Paul Pedrick | Gas turbine heated hot air buoyant airships |
| US20150217848A1 (en) * | 2015-03-24 | 2015-08-06 | Kevin Arash Peyman | Airship powered aerospace vehicle |
| CN105730670A (en) * | 2015-10-28 | 2016-07-06 | 广西慧云信息技术有限公司 | Long-endurance unmanned aerial vehicle adopting new energy |
| CN205524958U (en) * | 2016-03-16 | 2016-08-31 | 上海重塑能源科技有限公司 | Fuel cell unmanned aerial vehicle |
| CN206528628U (en) * | 2016-09-23 | 2017-09-29 | 安徽翼讯飞行安全技术有限公司 | Rotor wing unmanned aerial vehicle |
-
2016
- 2016-09-23 CN CN201610842919.4A patent/CN106275408A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1117054A (en) * | 1967-05-30 | 1968-06-12 | Arthur Paul Pedrick | Gas turbine heated hot air buoyant airships |
| US20150217848A1 (en) * | 2015-03-24 | 2015-08-06 | Kevin Arash Peyman | Airship powered aerospace vehicle |
| CN105730670A (en) * | 2015-10-28 | 2016-07-06 | 广西慧云信息技术有限公司 | Long-endurance unmanned aerial vehicle adopting new energy |
| CN205524958U (en) * | 2016-03-16 | 2016-08-31 | 上海重塑能源科技有限公司 | Fuel cell unmanned aerial vehicle |
| CN206528628U (en) * | 2016-09-23 | 2017-09-29 | 安徽翼讯飞行安全技术有限公司 | Rotor wing unmanned aerial vehicle |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108545174A (en) * | 2018-03-30 | 2018-09-18 | 中山市剑鸿电子科技有限公司 | A kind of overturning-preventing compact carrier unmanned plane |
| CN111717405A (en) * | 2020-06-23 | 2020-09-29 | 长沙航华电子科技有限公司 | Buoyancy auxiliary lifting device for unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170104 |