CN203698668U - Double-parachute wing-type unmanned aerial vehicle - Google Patents
Double-parachute wing-type unmanned aerial vehicle Download PDFInfo
- Publication number
- CN203698668U CN203698668U CN201420034409.0U CN201420034409U CN203698668U CN 203698668 U CN203698668 U CN 203698668U CN 201420034409 U CN201420034409 U CN 201420034409U CN 203698668 U CN203698668 U CN 203698668U
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- umbrella
- wing
- parachute
- unmanned aerial
- aerial vehicle
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Abstract
The utility model relates to a double-parachute wing-type unmanned aerial vehicle which comprises a vehicle body and wings. The wings are symmetrically installed on the two sides of the vehicle body. The double-parachute wing-type unmanned aerial vehicle is mainly characterized in that the front ends and the right ends of the two sides of the vehicle body are respectively provided with a parachute board, the middle of the wing on each side is provided with a parachute cabin, a wing tip of the wing on each side is provided with a buckle, and a parachute is arranged in the parachute cabin of the wing on each side and is connected with the corresponding two parachute boards and the corresponding buckle through a parachute rope. According to the double-parachute wing-type unmanned aerial vehicle, the parachute cabins are arranged on the wings on the two sides respectively, the horizontal posture of the unmanned aerial vehicle is effectively guaranteed, the condition that due to the fact that one parachute is used, the gravity is unstable and a vehicle body is crashed is avoided, it is guaranteed that the unmanned aerial vehicle lands stably and safely, and the stability of landing of the unmanned aerial vehicle is improved; meanwhile, the double-parachute cabins are arranged on the wings, the effective use space and the effective load of the unmanned aerial vehicle are improved, the capacity of a multi-task flight of the unmanned aerial vehicle is achieved, and the flight efficiency of the unmanned aerial machine is improved.
Description
Technical field
The utility model belongs to unmanned plane technical field, especially a kind of two parachute flying wing type unmanned planes.
Background technology
Current unmanned plane all adopts sliding race to land, hit net landing or parachuting mode.The sliding orbital distance that runs landing need to be certain, higher to landing conditional request, when contacting to earth, unmanned plane easily causes strong vibrations simultaneously, may damage the instrument of unmanned plane inside; Hitting net landing needs certain operative technique, and unmanned plane during flying medium velocity is very fast, and impulse force is larger, hits the damage that net landing also may cause unmanned plane body.Comparatively speaking, parachuting just seems relatively steadily and is easy, but single parachuting often causes crank, when landing, often collides with, and causes body impaired, the instrument in serious damage body.
Summary of the invention
The purpose of this utility model is to overcome the deficiencies in the prior art, a kind of two parachute flying wing type unmanned plane is provided, solve current unmanned aerial vehicle net landing shakiness and slided the unallowed situation of race landing condition and caused the problem that unmanned plane cannot land or unmanned plane body is impaired, also solved the problem that the single impulse force that bales out causes greatly body vibration influence instrument performance
The utility model solves existing technical matters and takes following technical scheme to realize:
A kind of two parachute flying wing type unmanned plane, comprise body and wing, wing symmetry is arranged on body both sides, be separately installed with umbrella plate in the front-end and back-end of body both sides, be respectively equipped with umbrella cabin at every side wing middle part, wing tip place at every side wing is respectively equipped with snap close, and the inside, umbrella cabin on every side wing is equipped with parachute, and each parachute is connected with snap close with two umbrella plates by umbrella rope.
And, umbrella cabin comprises umbrella hatchcover, hasp, umbrella cabin body, rubber band, one side hinge of one side of described umbrella hatchcover and umbrella cabin body be fitted together and spiral-lock at the upper surface of umbrella cabin body, install on wing one end of described rubber band, this rubber band is arranged on the hasp of installing on umbrella hatchcover upper surface and its other end and umbrella cabin body opposite side and is installed together, and this hasp is connected with steering wheel and closing and opening by steering wheel control hasp; The secondary umbrella that is provided with umbrella cloth and is wrapped up by umbrella cloth on the inner surface of umbrella hatchcover, this pair umbrella is connected with the top of main chute, and this main chute is arranged in the body of umbrella cabin, and this main chute is laid with three point of connection and is connected with snap close with two umbrella plates by umbrella rope.
And described rubber band is two, one end of two rubber bands is connected on two diverse locations of wing, and the other end of two rubber bands is connected on hasp.
Advantage of the present utility model and good effect are:
1, the utility model arranges respectively parachute umbrella cabin on the wing of both sides, when landing, parachute is opened at wing place, effectively guarantee the horizontal attitude of unmanned plane, avoid single parachuting crank to cause the situation that body collides with to occur, and, in the situation that a side parachute cannot be opened for some reason, parachute by opposite side is also controlled aspect, also can make the safe land of unmanned plane, avoid the impaired situation of unmanned plane body to occur, guaranteed the steadily landing of safety of unmanned plane, the stationarity while having improved unmanned plane landing.
2, the utility model is arranged on two parachute umbrellas cabin on wing, and that has improved unmanned plane body effectively utilizes space and capacity weight, has realized the ability of unmanned plane multitask flight, has improved the flight efficiency of unmanned plane.
3, the utility model, by the front and back umbrella plate of body and the snap close at wing wing tip place, adopts 3 fixing parachutes, the possibility of having avoided two parachutes can be intertwined in the time opening.
4, the utility model adopts thick all-wing aircraft design, has improved the wind loading rating of unmanned plane, has guaranteed the stability in unmanned plane during flying process.
Accompanying drawing explanation
Fig. 1 is integral structure schematic diagram of the present invention;
Fig. 2 is the umbrella cabin structure schematic diagram (hasp is in closed condition) on the wing of both sides;
Fig. 3 is the umbrella cabin structure schematic diagram (hasp is in open mode) on the wing of both sides;
The view that when Fig. 4 is unmanned plane landing, main chute and attached umbrella are opened;
In figure, 1-snap close, 2-umbrella cabin, 3-wing, 4-umbrella plate, 5-body, 6-umbrella hatchcover, 7-hasp, 8-steering wheel, 9-umbrella cabin body, 10-rubber band, 11-umbrella cloth, 12-main chute, the secondary umbrella of 13-.
The specific embodiment
Below in conjunction with accompanying drawing, the utility model embodiment is further described.
A kind of two parachute flying wing type unmanned plane, as shown in Figure 1, comprise body 5 and wing 3, wing symmetry is arranged on body both sides, be separately installed with umbrella plate 4 in the front-end and back-end of body both sides, be respectively equipped with umbrella cabin 2 at every side wing middle part, be respectively equipped with snap close 1 at the wing tip place of every side wing, inside, umbrella cabin on every side wing is equipped with parachute, and each parachute adopts 3 connection modes to be connected with snap close with two umbrella plates by umbrella rope.
Be arranged on umbrella cabin structure on the wing of both sides identical, as shown in Figure 2, umbrella cabin comprises umbrella hatchcover 6, hasp 7, umbrella cabin body 9, two rubber bands 10, one side hinge of one side of described umbrella hatchcover and umbrella cabin body be fitted together and spiral-lock at the upper surface of umbrella cabin body, install respectively on two diverse locations on wing one end of two rubber bands, two rubber bands are arranged on the hasp of installing on the other end of umbrella hatchcover upper surface and rubber band and umbrella cabin body opposite side and link together, this hasp is connected with steering wheel 8 and closing and open mode by steering wheel control hasp: when hasp is during in closed condition, by rubber band, umbrella hatchcover is pressed on the body of umbrella cabin tightly, when hasp is during in open mode, rubber band shrinks and umbrella hatchcover is opened along hinge dress axle, as shown in Figure 3.The secondary umbrella 13 that is provided with umbrella cloth 11 and is wrapped up by umbrella cloth on the inner surface of umbrella hatchcover, this pair umbrella is connected with the top of main chute 12, this main chute is arranged in the body of umbrella cabin, this main chute is laid with three point of connection and is connected with snap close with two umbrella plates by umbrella rope, in the time that unmanned plane lands, two umbrella hatchcovers are opened simultaneously, and two main chutes are taken out of and strained by secondary umbrella, unmanned plane is safe falling under the effect of two parachutes, as shown in Figure 4.
Principle of work of the present utility model is: in the time that unmanned plane carries out normal flight task, umbrella hatchcover covers on the body of umbrella cabin by the rubber band of steering wheel control hasp and two tensions.In the time that unmanned plane lands, flying to control hand or flight control system opens hasp by controlling steering wheel rotation, umbrella hatchcover is because the pulling force of rubber band turns over backward, the secondary umbrella (this pair umbrella is simply being wrapped by the umbrella cloth on hatchcover) being simultaneously attached on umbrella hatchcover is thrown out of, be subject to air effect, main chute is taken out of and is strained by secondary umbrella, realizes the safe parachuting of two parachutes of unmanned plane.In the present embodiment, secondary umbrella throws away backward by the effect of air, thereby main chute is taken out of from umbrella cabin, plays the effect of safe parachuting; The effect of main chute is the speed that slows down aircraft landing, and unmanned plane can be landed gently.
It is emphasized that; embodiment described in the utility model is illustrative; rather than determinate; therefore the utility model comprises and is not limited to the embodiment described in the specific embodiment; every other embodiments that drawn according to the technical solution of the utility model by those skilled in the art, belong to the scope that the utility model is protected equally.
Claims (3)
1. a two parachute flying wing type unmanned plane, comprise body and wing, wing symmetry is arranged on body both sides, it is characterized in that: be separately installed with umbrella plate in the front-end and back-end of body both sides, be respectively equipped with umbrella cabin at every side wing middle part, wing tip place at every side wing is respectively equipped with snap close, and the inside, umbrella cabin on every side wing is equipped with parachute, and each parachute is connected with snap close with two umbrella plates by umbrella rope.
2. the two parachute flying wing type unmanned planes of one according to claim 1, it is characterized in that: umbrella cabin comprises umbrella hatchcover, hasp, umbrella cabin body, rubber band, one side hinge of one side of described umbrella hatchcover and umbrella cabin body be fitted together and spiral-lock at the upper surface of umbrella cabin body, install on wing one end of described rubber band, this rubber band is arranged on the hasp of installing on umbrella hatchcover upper surface and its other end and umbrella cabin body opposite side and is installed together, and this hasp is connected with steering wheel and closing and opening by steering wheel control hasp; The secondary umbrella that is provided with umbrella cloth and is wrapped up by umbrella cloth on the inner surface of umbrella hatchcover, this pair umbrella is connected with the top of main chute, and this main chute is arranged in the body of umbrella cabin, and this main chute is laid with three point of connection and is connected with snap close with two umbrella plates by umbrella rope.
3. the two parachute flying wing type unmanned planes of one according to claim 2, is characterized in that: described rubber band is two, and one end of two rubber bands is connected on two diverse locations of wing, and the other end of two rubber bands is connected on hasp.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420034409.0U CN203698668U (en) | 2014-01-20 | 2014-01-20 | Double-parachute wing-type unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420034409.0U CN203698668U (en) | 2014-01-20 | 2014-01-20 | Double-parachute wing-type unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203698668U true CN203698668U (en) | 2014-07-09 |
Family
ID=51049143
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420034409.0U Expired - Fee Related CN203698668U (en) | 2014-01-20 | 2014-01-20 | Double-parachute wing-type unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203698668U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691788A (en) * | 2015-01-23 | 2015-06-10 | 北京空间机电研究所 | Pop-up parachute capable of realizing self-adaptive equilibrium |
| CN107444632A (en) * | 2017-06-30 | 2017-12-08 | 马鞍山市赛迪智能科技有限公司 | It is a kind of can VTOL dalta wing unmanned plane |
| CN112478171A (en) * | 2020-12-03 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | High-altitude launching device and method for unmanned aerial vehicle |
-
2014
- 2014-01-20 CN CN201420034409.0U patent/CN203698668U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691788A (en) * | 2015-01-23 | 2015-06-10 | 北京空间机电研究所 | Pop-up parachute capable of realizing self-adaptive equilibrium |
| CN107444632A (en) * | 2017-06-30 | 2017-12-08 | 马鞍山市赛迪智能科技有限公司 | It is a kind of can VTOL dalta wing unmanned plane |
| CN112478171A (en) * | 2020-12-03 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | High-altitude launching device and method for unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| C56 | Change in the name or address of the patentee | ||
| CP03 | Change of name, title or address |
Address after: Haitai Binhai high tech Zone Huayuan Industrial Area of Tianjin City, 300384 West Road No. 18 South 2-202 Patentee after: CHINARS GEO-INFORMATICS CO.,LTD. Patentee after: BEIJING HONGBO CHINARS INFORMATION TECHNOLOGY CO.,LTD. Patentee after: HEBEI ZHONGKE REMOTE SENSING INFORMATION TECHNOLOGY Co.,Ltd. Address before: 300384 Tianjin city Xiqing District No. 18 West Haitai software park south two floor 2 Patentee before: CHINARS GEOINFORMATICS Co.,Ltd. Patentee before: BEIJING HONGBO CHINARS INFORMATION TECHNOLOGY CO.,LTD. Patentee before: QINHUANGDAO CHINARS INFORMATION TECHNOLOGY CO.,LTD. |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20160503 Address after: 300384 Tianjin city Xiqing District No. 18 West Haitai software park south two floor 2 Patentee after: CHINARS GEOINFORMATICS Co.,Ltd. Patentee after: BEIJING HONGBO CHINARS INFORMATION TECHNOLOGY CO.,LTD. Patentee after: QINHUANGDAO CHINARS INFORMATION TECHNOLOGY CO.,LTD. Address before: 211300, No. 10, 3 Tan Avenue, Gaochun economic and Technological Development Zone, Jiangsu, Nanjing Patentee before: JIANGSU ZHONGKE REMOTE SENSING INFORMATION TECHNOLOGY CO.,LTD. Patentee before: CHINARS GEOINFORMATICS Co.,Ltd. Patentee before: BEIJING HONGBO CHINARS INFORMATION TECHNOLOGY CO.,LTD. Patentee before: QINHUANGDAO CHINARS INFORMATION TECHNOLOGY CO.,LTD. |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140709 Termination date: 20220120 |
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| CF01 | Termination of patent right due to non-payment of annual fee |