CN104309810A - Automatic falling structure for unmanned aerial vehicle - Google Patents
Automatic falling structure for unmanned aerial vehicle Download PDFInfo
- Publication number
- CN104309810A CN104309810A CN201410499154.XA CN201410499154A CN104309810A CN 104309810 A CN104309810 A CN 104309810A CN 201410499154 A CN201410499154 A CN 201410499154A CN 104309810 A CN104309810 A CN 104309810A
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- large area
- wing
- engine rotor
- aerial vehicle
- unmanned aerial
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Abstract
The invention provides an automatic falling structure for an unmanned aerial vehicle. The automatic falling structure comprises engine rotor wings, a large-area wing, cowl flaps, large-area wing flaps and large-area vertical stabilizers, wherein the cowl flaps are mounted at the lower parts of the engine rotor wings, and the cowl flaps and the engine rotor wings are elastically connected; when the cowl flaps are opened, the engine rotor wings produce downward flowing pushing airflows, and when the cowl flaps are closed, a complete wing is formed by the cowl flaps and the engine motor wings; the large-area vertical stabilizers are arranged on the top of the large-area wing, the large-area wing flaps are connected with the rear end of the large-area wing, and the large-area vertical stabilizers and the large-area wing flaps guarantee that the unmanned aerial vehicle is kept to fall at a horizontal attitude. According to the automatic falling structure provided by the invention, an airplane can be instantly converted into the structure of a large cross section with a similar parachute function by utilizing the shape of the airplane and the structural deformation of the cowl flaps, so that the unmanned aerial vehicle can slowly fall in virtue of the shape and structural deformation of the unmanned aerial vehicle when the unmanned aerial vehicle breaks down during low-altitude flying, and the crash of the unmanned aerial vehicle is avoided.
Description
Technical field
The present invention relates to unmanned plane safety method, particularly a kind of high security police nobody automatically to descend slowly and lightly structure.
Background technology
Current police unmanned plane has many safety methods, to have two large classes, to be forced landing, two of gliding be adopt parachute to force-land for the safety method that wherein force-lands.Landing of gliding is only applicable to the cyclogyro of fixed wing aircraft and releasable, the unmanned plane of other types adopts parachute forced landing technology.If the requirement of the flying height that has of parachute forced landing technology, such as more than 100 meters are less than this flying height, parachute may have little time to open but force-land and unsuccessfully cause air crash.
Summary of the invention
The present invention relates to a kind of unmanned plane automatically to descend slowly and lightly structure, it comprises driving engine rotor, large area wing, clinker plank, large area wing flap is vertical with large area stabilizes;
Described driving engine rotor bottom is provided with clinker plank, and between described clinker plank with described driving engine rotor, elasticity is connected;
When described clinker plank is opened, driving engine rotor produces the propelling air-flow flowed downward, and when described clinker plank is closed, described clinker plank and described driving engine rotor form complete wing;
Large area is vertically stable is located at described large area wing tip portion, and described large area wing flap is connected with described large area rear airfoil end, with large area wing flap, described large area is vertically stable ensures that unmanned plane keeps horizontal attitude to descend slowly and lightly.
Preferably, described driving engine rotor is arranged in described large area wing.
The present invention has following beneficial effect:
The invention provides and a kind ofly utilize the distortion of aircraft own form and clinker plank structure to be the structure heavy in section with similar parachute function by aircraft umklappen, ensure that unmanned plane can rely on when low-latitude flying et out of order the profile of self and deformation to realize slowly descending slowly and lightly, avoid unmanned plane to crash.
Certainly, implement arbitrary product of the present invention might not need to reach above-described all advantages simultaneously.
Accompanying drawing explanation
The large area wing that Fig. 1 provides for the embodiment of the present invention, large area flap configurations schematic diagram;
The large area vertically stable structural representation that Fig. 2 provides for the embodiment of the present invention;
The clinker plank structural representation that Fig. 3 provides for the embodiment of the present invention.
Detailed description of the invention
Embodiments provide and the present invention relates to a kind of unmanned plane and automatically to descend slowly and lightly structure, it comprises driving engine rotor 2, large area wing 1, clinker plank 3, large area wing flap 4 vertical with large area stable 5;
Driving engine rotor 2 bottom is provided with clinker plank 3, and between clinker plank 3 with driving engine rotor 2, elasticity is connected;
When clinker plank 3 is opened, driving engine rotor 2 produces the propelling air-flow flowed downward, and when described clinker plank 3 is closed, clinker plank 3 and driving engine rotor 2 form complete wing;
Large area vertically stable 5 is located at large area wing 1 top, and large area wing flap 4 is connected with large area wing 1 rear end, with large area wing flap 4, large area vertically stable 5 ensures that unmanned plane keeps horizontal attitude to descend slowly and lightly.
The present invention adopts large area wing 1 project organization, is imbedded in wing by the aircraft power systems such as driving engine rotor 2.
Can blow out downwards generation lift at the propelling air-flow of driving engine rotor bottom installation clinker plank 3, driving engine rotor 2 production when clinker plank is opened, when clinker plank is closed, whole large area wing forms complete wing body together with clinker plank, wing is amassed in formation heavy in section.
Clinker plank adopts spring to be connected with large area wing 2.The propelling air-flow produced when driving engine rotor 2 works blows mineralization pressure on clinker plank 3, and the stressed machine of clinker plank linking springs 6 strengthens, clinker plank 3 opens.When driving engine rotor 2 quits work, on clinker plank 3, there is no pressure, the stressed reduction of clinker plank linking springs 6 and elastic recovery, automatically clinker plank closed.
Unmanned plane adopt large area vertically stable 5 and large area wing flap 4 can ensure that unmanned plane can not form car and fall, keeps horizontal attitude to descend slowly and lightly in the process of descending slowly and lightly.
the present invention is directed to the police unmanned plane of low-latitude flying, propose to descend slowly and lightly forced landing technology.Principle adopts large-area wing structure and under driving engine, installs the clinker plank that can close outside large diameter jet, when clinker plank is closed, whole wing becomes as a whole, sectional area is large, can provide enough large air resistance when aircraft descends slowly and lightly, thus realize similar parachute function, ensure that aircraft slowly descends slowly and lightly.
The technology that descends slowly and lightly is made up of two parts: one is in aircraft configuration design, adopt large area wing, large area vertically stable and large area wing flap configurations.The second, the driving engine rotor of aircraft adds casing, shell has closed clinker plank, and clinker plank spring is connected on shell, can only opens downwards.The promotion air-flow that driving engine rotor produces when aircraft flight produces pressure to clinker plank, clinker plank stressedly opens downwards by the linking springs of clinker plank, ensures that promotion air-flow is unimpeded.When force-landing aero-engine close, clinker plank lose promote air-flow pressure, under elastic force effect at linking springs clinker plank upwards close air-flow not by.
The aerodynamic force sectional area that aircraft gets off the plane in the situation of cutting out clinker plank strengthens, and adds that aircraft configuration adopts large area wing structure, and the aerodynamic force sectional area exterior cross-section that is relatively very large, aircraft self of whole aircraft is just equivalent to small-sized parachute.The air resistance that during airplane falling, its shell produces is very large, can ensure that the velocity ratio of falling of aircraft is lower, realize the effect that similar parachute descends slowly and lightly, the forced landing safety ensureing aircraft.
The disclosed preferred embodiment of the present invention just sets forth the present invention for helping above.Preferred embodiment does not have all details of detailed descriptionthe, does not limit the detailed description of the invention that this invention is only described yet.Obviously, according to the content of this specification sheets, can make many modifications and variations.This specification sheets is chosen and is specifically described these embodiments, is to explain principle of the present invention and practical application better, thus makes art technical personnel understand well and to utilize the present invention.The present invention is only subject to the restriction of claims and four corner and equivalent.
Claims (2)
1. unmanned plane descends slowly and lightly a structure automatically, it is characterized in that, comprises driving engine rotor, large area wing, clinker plank, large area wing flap is vertical with large area stabilizes;
Described driving engine rotor bottom is provided with clinker plank, and between described clinker plank with described driving engine rotor, elasticity is connected;
When described clinker plank is opened, driving engine rotor produces the propelling air-flow flowed downward, and when described clinker plank is closed, described clinker plank and described driving engine rotor form complete wing;
Large area is vertically stable is located at described large area wing tip portion, and described large area wing flap is connected with described large area rear airfoil end, with large area wing flap, described large area is vertically stable ensures that unmanned plane keeps horizontal attitude to descend slowly and lightly.
2. unmanned plane as claimed in claim 1 descends slowly and lightly structure automatically, and it is characterized in that, described driving engine rotor is arranged in described 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 true CN104309810A (en) | 2015-01-28 |
| CN104309810B CN104309810B (en) | 2017-06-16 |
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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 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI629213B (en) * | 2016-08-29 | 2018-07-11 | 英華達股份有限公司 | Unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1988000556A1 (en) * | 1986-07-16 | 1988-01-28 | Kimberley Vere Sadleir | A vtol aircraft and components |
| 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 |
| KR20130054805A (en) * | 2011-11-17 | 2013-05-27 | 재단법인대구경북과학기술원 | Flying robots with flight angle control function based on solar cells |
| 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) |
-
2014
- 2014-09-25 CN CN201410499154.XA patent/CN104309810B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1988000556A1 (en) * | 1986-07-16 | 1988-01-28 | Kimberley Vere Sadleir | A vtol aircraft and components |
| 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 |
| KR20130054805A (en) * | 2011-11-17 | 2013-05-27 | 재단법인대구경북과학기술원 | Flying robots with flight angle control function based on solar cells |
| 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) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI629213B (en) * | 2016-08-29 | 2018-07-11 | 英華達股份有限公司 | Unmanned aerial vehicle |
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| Publication number | Publication date |
|---|---|
| CN104309810B (en) | 2017-06-16 |
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| 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. |
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| 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 |
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| CF01 | Termination of patent right due to non-payment of annual fee |