CN104309810B - A kind of unmanned plane descends slowly and lightly structure automatically - Google Patents
A kind of unmanned plane descends slowly and lightly structure automatically Download PDFInfo
- Publication number
- CN104309810B CN104309810B CN201410499154.XA CN201410499154A CN104309810B CN 104309810 B CN104309810 B CN 104309810B CN 201410499154 A CN201410499154 A CN 201410499154A CN 104309810 B CN104309810 B CN 104309810B
- Authority
- CN
- China
- Prior art keywords
- large area
- gillis
- wing
- unmanned plane
- lightly
- 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.)
- Expired - Fee Related
Links
Landscapes
- Emergency Lowering Means (AREA)
- Toys (AREA)
Abstract
A kind of unmanned plane descends slowly and lightly structure automatically, including engine rotor, large area wing, gillis, large area wing flap are vertical with large area stabilizes；The engine rotor bottom is provided with gillis, elastic connection between the gillis and the large area wing；Engine rotor produces the propulsion air-flow for flowing downward when the gillis is opened, and when the gillis is closed, the gillis forms complete wing with the large area wing；Large area is vertically stable to be located at the large area wing tip portion, and the large area wing flap is connected with the large area rear airfoil end, and the large area is vertically stable to ensure that unmanned plane keeps horizontal attitude to descend slowly and lightly with large area wing flap.Aircraft umklappen can be the heavy in section structure with similar parachute function by the deformation the invention provides a kind of utilization aircraft own form and gillis structure, ensure that unmanned plane can rely on the profile and deformation of itself to realize slowly descending slowly and lightly when low-latitude flying is broken down, it is to avoid unmanned plane crashes.
Description
Technical field
The present invention relates to unmanned plane safe practice, particularly a kind of high security is police, and nobody descends slowly and lightly structure automatically.
Background technology
It is that gliding is compeled that the safe practice that current police unmanned plane has many safe practices, wherein force-land has two major classes, one
Drop, two are force-landed using parachute.Gliding landing is only applicable to the gyroplane of fixed wing aircraft and releasable, other kinds of
Unmanned plane is using parachute forced landing technology.If the requirement of the parachute forced landing flying height that has of technology, such as more than 100 meters,
Less than this flying height, parachute may have little time open but forced landing unsuccessfully cause air crash.
The content of the invention
Descended slowly and lightly automatically structure the present invention relates to a kind of unmanned plane, it include engine rotor, large area wing, gillis,
Large area wing flap is vertical with large area to be stabilized；
The engine rotor bottom is provided with gillis, and elasticity connects between the gillis and the large area wing
Connect；
Engine rotor produces the propulsion air-flow for flowing downward when the gillis is opened, when the gillis is closed,
The gillis forms complete wing with the large area wing；
Large area is vertically stable to be located at the large area wing tip portion, after the large area wing flap and the large area wing
End connection, the large area is vertically stable to ensure that unmanned plane keeps horizontal attitude to descend slowly and lightly with large area wing flap.
It is preferred that the engine rotor is arranged in the large area wing.
The invention has the advantages that：
Aircraft umklappen can be by the deformation the invention provides a kind of utilization aircraft own form and gillis structure
Heavy in section structure with similar parachute function, it is ensured that unmanned plane can rely on itself when low-latitude flying is broken down
Profile and deformation are realized slowly descending slowly and lightly, it is to avoid unmanned plane crashes.
Certainly, implement any product of the invention to it is not absolutely required to while reaching all the above advantage.
Brief description of the drawings
Fig. 1 is large area wing provided in an embodiment of the present invention, large area flap configurations schematic diagram；
Fig. 2 is that large area provided in an embodiment of the present invention vertically stabilizes structural representation；
Fig. 3 is fish scale plate structure schematic diagram provided in an embodiment of the present invention.
Specific embodiment
The embodiment of the invention provides and descended slowly and lightly automatically structure the present invention relates to a kind of unmanned plane, it include engine rotor 2,
Large area wing 1, gillis 3, large area wing flap 4 vertical with large area stable 5；
The bottom of engine rotor 2 is provided with gillis 3, elastic connection between gillis 3 and large area wing 1；
Engine rotor 2 produces the propulsion air-flow for flowing downward, when the gillis 3 is closed, fish when gillis 3 is opened
Dissepiment 3 forms complete wing with large area wing 1；
Large area vertically stable 5 is located at the top of large area wing 1, and large area wing flap 4 is connected with the rear end of large area wing 1,
Large area vertically stable 5 keeps horizontal attitude to descend slowly and lightly with the guarantee unmanned plane of large area wing flap 4.
The present invention uses the design structure of large area wing 1, the aircraft power systems such as engine rotor 2 is imbedded in into wing
In.
Can in the propulsion air-flow that gillis 3 is installed in engine rotor bottom, engine rotor 2 is produced when gillis is opened
Lift is produced with downward blowout, when gillis is closed, whole large area wing and gillis formed together complete wing body,
Form heavy in section product wing.
Gillis is connected with large area wing 2 using spring.The propulsion air-flow produced when engine rotor 2 works blows
Pressure is formed on gillis 3, the stress machine of gillis connecting spring 6 is increased, gillis 3 opens.When engine rotor 2 is stopped
When, there is no on gillis 3 pressure, the stress of gillis connecting spring 6 reduce and elastic recovery, automatically close gillis.
Unmanned plane using large area vertically stabilize 5 and large area wing flap 4 ensure that unmanned plane will not during descending slowly and lightly
Car is formed to fall, keep horizontal attitude to descend slowly and lightly.
The present invention is directed to the police unmanned plane of low-latitude flying, proposes the forced landing technology that descends slowly and lightly.Principle is using the machine of large area
Wing structure and the gillis that installation can be closed on the outside of the jet of major diameter under the engine, when gillis is closed,
Whole wing is as an entirety, sectional area is big, sufficiently large air drag can be provided when aircraft descends slowly and lightly, so as to realize being similar to
The function of parachute, guarantee aircraft slowly descend slowly and lightly.
The technology that descends slowly and lightly is made up of two parts：One is vertically pacified using large area wing, large area in aircraft configuration design
Fixed and large area wing flap configurations.The engine rotor of the secondth, aircraft installs shell additional, there is closed gillis on shell,
Gillis spring is connected on shell, can only open downwards.The promotion air-flow pair that engine rotor is produced in aircraft flight
Gillis produces pressure, the connecting spring stress of gillis to open gillis downwards, ensures to promote air-flow unimpeded.When forced landing
Aircraft engine is closed, gillis loses the pressure of promotion air-flow, gillis is closed upwards under the elastic force effect of connecting spring
Air-flow can not pass through.
The aerodynamic force sectional area of aircraft aircraft in the case where gillis is closed is increased, and is added aircraft configuration and is used large area
Wing structure, very the big, exterior cross-section of aircraft itself is equivalent to small-sized landing to the aerodynamic force sectional area of whole aircraft relatively
Umbrella.The air drag that its shell is produced during airplane falling is very big, ensure that the speed ratio of falling of aircraft is relatively low, realizes similar drop
Effect, the forced landing security of guarantee aircraft that the umbrella that falls descends slowly and lightly.
Present invention disclosed above preferred embodiment is only intended to help and illustrates the present invention.Preferred embodiment is not detailed
All of details is described, it is only described specific embodiment that the invention is not limited yet.Obviously, according to the content of this specification,
Can make many modifications and variations.This specification is chosen and specifically describes these embodiments, is to preferably explain the present invention
Principle and practical application so that skilled artisan can be best understood by and utilize the present invention.The present invention is only
Limited by claims and its four corner and equivalent.
Claims (2)
1. a kind of unmanned plane descends slowly and lightly structure automatically, it is characterised in that including engine rotor, large area wing, gillis, big face
Wing flap is vertical with large area stabilizes for product；
The engine rotor bottom is provided with gillis, elastic connection between the gillis and the large area wing；
Engine rotor produces the propulsion air-flow for flowing downward when the gillis is opened, described when the gillis is closed
Gillis forms complete wing with the large area wing；
Large area is vertically stable to be located at the large area wing tip portion, and the large area wing flap connects with the large area rear airfoil end
Connect, the large area is vertically stable to ensure that unmanned plane keeps horizontal attitude to descend slowly and lightly with large area wing flap.
2. unmanned plane as claimed in claim 1 descends slowly and lightly structure automatically, it is characterised in that the engine rotor is arranged on described
In large area wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410499154.XA CN104309810B (en) | 2014-09-25 | 2014-09-25 | A kind of unmanned plane descends slowly and lightly structure automatically |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410499154.XA CN104309810B (en) | 2014-09-25 | 2014-09-25 | A kind of unmanned plane descends slowly and lightly structure automatically |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104309810A CN104309810A (en) | 2015-01-28 |
| CN104309810B true CN104309810B (en) | 2017-06-16 |
Family
ID=52365174
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410499154.XA Expired - Fee Related CN104309810B (en) | 2014-09-25 | 2014-09-25 | A kind of unmanned plane descends slowly and lightly structure automatically |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104309810B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106314777B (en) * | 2016-08-29 | 2019-12-24 | 英华达（上海）科技有限公司 | Unmanned aerial vehicle |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201086825Y (en) * | 2007-07-11 | 2008-07-16 | 郑德玉 | Wing shaped airplane |
| CN201932359U (en) * | 2011-01-21 | 2011-08-17 | 文杰 | Distributive power multi-rotor vertical take-off and landing aircraft |
| CN103600835A (en) * | 2013-11-29 | 2014-02-26 | 石家庄飞机工业有限责任公司 | Aerodynamic configuration of bionic flying wing unmanned aerial vehicle (UAV) |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IL83205A0 (en) * | 1986-07-16 | 1987-12-31 | Kimberley Vere Sadleir | Vtol aircraft and its components |
| KR101354646B1 (en) * | 2011-11-17 | 2014-01-22 | 재단법인대구경북과학기술원 | Flying Robots with Flight Angle Control function based on Solar Cells |
-
2014
- 2014-09-25 CN CN201410499154.XA patent/CN104309810B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201086825Y (en) * | 2007-07-11 | 2008-07-16 | 郑德玉 | Wing shaped airplane |
| CN201932359U (en) * | 2011-01-21 | 2011-08-17 | 文杰 | Distributive power multi-rotor vertical take-off and landing aircraft |
| CN103600835A (en) * | 2013-11-29 | 2014-02-26 | 石家庄飞机工业有限责任公司 | Aerodynamic configuration of bionic flying wing unmanned aerial vehicle (UAV) |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104309810A (en) | 2015-01-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104290906B (en) | A kind of vertically taking off and landing flyer | |
| CN209921623U (en) | Scalable collision avoidance device of unmanned aerial vehicle | |
| CN203005747U (en) | Tilt rotor aircraft | |
| CN106864744A (en) | A kind of co-axial rotor variant vertically taking off and landing flyer | |
| CN108860572B (en) | Working method of efficient low-speed aircraft | |
| CN106915463A (en) | Take off mode and the device of a kind of aircraft | |
| CN104309810B (en) | A kind of unmanned plane descends slowly and lightly structure automatically | |
| CN207683774U (en) | A kind of unmanned plane having air bag of saving oneself | |
| CN205602127U (en) | Single shot sitting posture VTOL fixed -wing aircraft | |
| CN204250361U (en) | Aircraft slow descending device | |
| CN105539816A (en) | Wing structure and propeller blade structure | |
| CN104992586A (en) | Airplane system capable of realizing flight experience | |
| CN206734629U (en) | A kind of disk aircraft | |
| CN202481307U (en) | Four-propeller aircraft taking off and landing vertically | |
| CN105109693A (en) | Unmanned aerial vehicle parachute ejection system using nail gun powder | |
| CN201086826Y (en) | Back pushing type veil opening device of minitype pilotless plane | |
| CN210592461U (en) | Install SAR's unmanned aerial vehicle additional | |
| CN204701766U (en) | Arrow formula vertical take-off and landing aircraft (VTOL aircraft) | |
| CN206278261U (en) | A kind of single-point hangs umbrella-type unmanned plane | |
| CN104548616B (en) | A kind of telecontrolled aircraft | |
| CN202624633U (en) | Crashworthy twin-rotor air vehicle | |
| CN203075664U (en) | Flying machine | |
| CN205602144U (en) | Stationary vane model aeroplane and model ship parachuting mechanism | |
| CN205633025U (en) | Power wing helicopter | |
| CN203767066U (en) | Unmanned aerial vehicle with grounded buffering fairing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20170519 Address after: 215000, 9, 401, 99, Jinji Road, Suzhou Industrial Park, Suzhou, Suzhou, Jiangsu Applicant after: Best flying technology (Suzhou) Co., Ltd. Address before: Daoxiang road in Shushan District of Hefei City, Anhui province 230001 No. 9 Business Center Applicant before: ANHUI KEYAO INTELLIGENT TECHNOLOGY CO., LTD. |
|
| TA01 | Transfer of patent application right | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170616 Termination date: 20190925 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |