CN202429346U - Empennage of small unmanned aerial vehicle - Google Patents
Empennage of small unmanned aerial vehicle Download PDFInfo
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- CN202429346U CN202429346U CN 201120485302 CN201120485302U CN202429346U CN 202429346 U CN202429346 U CN 202429346U CN 201120485302 CN201120485302 CN 201120485302 CN 201120485302 U CN201120485302 U CN 201120485302U CN 202429346 U CN202429346 U CN 202429346U
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- empennage
- tailplane
- starboard
- port
- stationary plane
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Abstract
The utility model provides an empennage of a small unmanned aerial vehicle. The empennage is mounted on the small unmanned aerial vehicle through a tail boom, and comprises a left empennage (3) and a right empennage (4). The left empennage (3) and the right empennage (4) are integrated, each of the left empennage (3) and the right empennage (4) comprises a fixed plane (1) and a control plane (2), the fixed plane (1) is connected with the tail boom fixedly, and each control plane (2) can be connected with each fixed plane (1) rotatably. The empennage is provided with the fixed planes and the control planes, so that flight direction can be adjusted by the matching with the empennage. The empennage is in a V-shaped structure, so that start-up performance of the unmanned aerial vehicle is better, and risks of being hung on a parachute during withdrawing process are lowered.
Description
Technical field
The utility model relates to the unmanned plane field, especially, relates to a kind of empennage of SUAV.
Background technology
SUAV is little with its volume; Characteristics such as good concealment when executing the task, each field such as the military surveillance in the low latitude, fire support, target acquisition, relaying communication, aerial photography, meteorological disasters monitoring and traffic monitoring all has a wide range of applications.
At present, the empennage of SUAV is made up of left and right sides two parts, is installed in the afterbody of SUAV after two parts use attaching parts to couple together, and this attaching parts is to be diminished gradually by forebody to be connected with empennage, and it takes up room greatly, is inconvenient to carry; Because the mode that adopts two parts separately to make, make that the performance of anti-impact force of empennage is bad; In addition, mostly existing empennage is directly to be connected with forebody, and the structure of the connecting portion of empennage and forebody is bigger, has increased the deadweight of empennage and SUAV so greatly.
The utility model content
The utility model purpose is to provide a kind of empennage of SUAV, and existing empennage deadweight is overweight to solve, the technical matters of anti-impact force poor performance.
For realizing above-mentioned purpose; Utility model provides a kind of empennage of SUAV; Empennage is installed on the SUAV through a shoe, and empennage comprises: port tailplane and starboard tailplane, and port tailplane and starboard tailplane include stationary plane and rudder face; Stationary plane is captiveed joint with shoe, and the rudder face of port tailplane and starboard tailplane rotatably is connected with the stationary plane of port tailplane and starboard tailplane respectively.
Further, the stationary plane of the edge on one side of the rudder face of port tailplane and port tailplane is connected through seccotine; The edge on one side of the rudder face of starboard tailplane is connected through seccotine with the stationary plane of starboard tailplane; A push-pull configuration respectively is set on port tailplane and starboard tailplane, and the two ends of the push-pull configuration of port tailplane are connected with stationary plane with the rudder face of port tailplane respectively, and the two ends of the push-pull configuration of starboard tailplane are connected with stationary plane with the rudder face of starboard tailplane respectively.
Further, empennage is a V-type, and port tailplane and starboard tailplane are symmetrical set, and port tailplane is provided with the shoe connecting bore with the connecting portion that starboard tailplane joins mutually.
Further, the scope of the angle between port tailplane and the starboard tailplane is 60 °～120 °.
Further, the angle between port tailplane and the starboard tailplane is 75 °, 90 ° or 105 °.
Further, empennage is the T type, and the T type tail has vertical fin and horizontal tail, and first end of vertical fin is captiveed joint with the horizontal tail middle part, and second end of vertical fin is provided with the shoe connecting bore and is connected with shoe.
Further, the horizontal horizontal of horizontal tail, the horizontal tail leading edge sweep is between 10 °～30 °.
Further, empennage comprises the skeleton that is made up of rib, stringer and beam, and skeleton is provided with the covering of glass fiber compound material, and covering is by mould molding.
The utlity model has following beneficial effect: the empennage of the utility model is provided with stationary plane and rudder face, makes empennage can cooperate the adjustment heading; Adopt the vee tail structure,, can also be reduced in the risk of hanging umbrella in the removal process referring to front reform the sanction more.
Except top described purpose, feature and advantage, the utility model also has other purpose, feature and advantage.To do further detailed explanation to the utility model with reference to figure below.
Description of drawings
The accompanying drawing that constitutes the application's a part is used to provide the further understanding to the utility model, and illustrative examples of the utility model and explanation thereof are used to explain the utility model, do not constitute the improper qualification to the utility model.In the accompanying drawings:
Fig. 1 is the empennage birds-eye view scheme drawing of the SUAV of the utility model first embodiment; And
Fig. 2 is stationary plane and the bottom section scheme drawing of rudder face of the empennage of the utility model first embodiment;
Fig. 3 is the structural representation of the vee tail of the utility model first embodiment;
Fig. 4 is the structural representation of empennage of second embodiment of the utility model.
The specific embodiment
Embodiment to the utility model is elaborated below in conjunction with accompanying drawing, but the multitude of different ways that the utility model can be defined by the claims and cover is implemented.
Referring to Fig. 1 and Fig. 2, the empennage of the SUAV of the first embodiment of the present invention comprises port tailplane 3 and starboard tailplane 4.Port tailplane 3 is an integral structure with starboard tailplane 4, and promptly port tailplane 3 is one-body molded with starboard tailplane 4 or is fixed together with attaching parts after the making respectively.Empennage is connected with the forebody of SUAV through a shoe.Port tailplane 3 includes a stationary plane 1 and a rudder face 2 with starboard tailplane 4; Stationary plane 1 and rudder face 2 are arranged along tangential (working direction when empennage tangential is this SUAV horizontal flight) of empennage; Rudder face 2 rotatably is connected with stationary plane 1, and promptly the edge on one side of rudder face 2 is pivotally connected on the stationary plane 1.This rudder face 2 can form an angle with rudder face 2 around rotation back, the edge of stationary plane 1, in order to the change air flow line, thus the heading of change unmanned plane; In addition, can be through rotating the angle that rudder face 2 changes between rudder faces 2 and the stationary plane 1 so that unmanned plane keeps balance when the turning flight.Preferably, the stationary plane 1 of the edge on one side of the rudder face 2 of port tailplane 3 and port tailplane 3 is connected through seccotine; The edge on one side of the rudder face 2 of starboard tailplane 4 and the stationary plane of starboard tailplane 41 are connected through seccotine.
On port tailplane 3 and starboard tailplane 4, also respectively be provided with a push-pull configuration 7; The two ends of this push-pull configuration 7 are connected with stationary plane 1 with rudder face 2 respectively; The two ends that are the push-pull configuration 7 of port tailplane 3 are connected with stationary plane 1 with the rudder face 2 of port tailplane 3 respectively, and the two ends of the push-pull configuration 7 of starboard tailplane 4 are connected with stationary plane 1 with the rudder face 2 of starboard tailplane 4 respectively.This push-pull configuration 7 receives after the power driven can push-and-pull rudder face 2, makes rudder face 2 around the rotation of the edge of stationary plane 1.As other embodiment, rudder face 2 can be connected through the hinge of various ways such as adhesive tape, gauze, nonwoven fabrics or cloth with stationary plane 1.
In conjunction with referring to Fig. 3, this empennage is the empennage of V-structure, and port tailplane 3 is symmetrical set with starboard tailplane 4, the structure that symmetrically arranged port tailplane 3 and starboard tailplane 4 are formed in one.Port tailplane 3 is provided with shoe connecting bore 5 with the connecting portion that starboard tailplane 4 joins mutually, and the axis of this shoe connecting bore 5 is the diad of port tailplane 3 and starboard tailplane 4.Like this, the empennage that becomes V-structure to arrange, the resistance of its generation reduces greatly, and can reduce the extension umbrella risk of unmanned plane in the landing process greatly.Preferably, the corner dimension between port tailplane 3 and the starboard tailplane 4 can be chosen in 60 °～120 ° scope as requested.More preferably, the corner dimension between port tailplane 3 and the starboard tailplane 4 is 75 °, 90 ° or 105 °.The empennage of this unmanned plane constitutes skeleton by deckle board and stringer, and the covering of glass fiber compound material is set on skeleton.
In conjunction with referring to Fig. 4, as second embodiment, the empennage of this second embodiment is the T type tail, and the T type tail has a vertical fin 6 and horizontal tail.First end of vertical fin 6 is captiveed joint with the middle part of horizontal tail, and second end of vertical fin 6 is provided with shoe connecting bore 5.The port tailplane 3 of this T type tail and the midsection symmetric arrangement of starboard tailplane 4 along vertical fin 6.Preferably, in a second embodiment, port tailplane 3 all is inclined to set with starboard tailplane 4, port tailplane 3 and starboard tailplane 4 in the exhibition of the empennage of T type to (with tangential vertical direction) all horizontal by 10 °～30 °.This angle is preferably 15 °, 20 ° or 25 °.The empennage of this unmanned plane comprises the skeleton that is made up of rib, stringer and beam, and skeleton is provided with the covering of glass fiber compound material, and covering is by mould molding.
The preferred embodiment that the above is merely the utility model is not limited to the utility model, and for a person skilled in the art, the utility model can have various changes and variation.All within the spirit and principle of the utility model, any modification of being done, be equal to replacement, improvement etc., all should be included within the protection domain of the utility model.
Claims (7)
1. the empennage of a SUAV, said empennage is installed on the said SUAV through a shoe, and said empennage comprises: port tailplane (3) and starboard tailplane (4), it is characterized in that,
Said port tailplane (3) and said starboard tailplane (4) include stationary plane (1) and rudder face (2); Said stationary plane (1) is captiveed joint with said shoe, and the rudder face (2) of said port tailplane (3) and said starboard tailplane (4) rotatably is connected with the stationary plane (1) of said port tailplane (3) and said starboard tailplane (4) respectively.
2. the empennage of SUAV according to claim 1 is characterized in that,
The edge on one side of the rudder face (2) of said port tailplane (3) and the stationary plane (1) of said port tailplane (3) are connected through seccotine; The edge on one side of the rudder face (2) of said starboard tailplane (4) and the stationary plane (1) of said starboard tailplane (4) are connected through seccotine;
On said port tailplane (3) and said starboard tailplane (4), a push-pull configuration (7) is set respectively; The two ends of the push-pull configuration (7) of said port tailplane (3) are connected with stationary plane (1) with the rudder face (2) of said port tailplane (3) respectively, and the two ends of the push-pull configuration (7) of said starboard tailplane (4) are connected with stationary plane (1) with the rudder face (2) of said starboard tailplane (4) respectively.
3. the empennage of SUAV according to claim 2 is characterized in that,
Said empennage is a V-type, and said port tailplane (3) and said starboard tailplane (4) are symmetrical set, and said port tailplane (3) is provided with shoe connecting bore (5) with the connecting portion that said starboard tailplane (4) joins mutually.
4. the empennage of SUAV according to claim 3 is characterized in that,
The scope of the angle between said port tailplane (3) and the said starboard tailplane (4) is 60 °～120 °.
5. the empennage of SUAV according to claim 3 is characterized in that,
Angle between said port tailplane (3) and the said starboard tailplane (4) is 75 °, 90 ° or 105 °.
6. the empennage of SUAV according to claim 2 is characterized in that,
Said empennage is the T type, and the empennage of said T type has vertical fin (6) and horizontal tail, and first end of said vertical fin (6) is captiveed joint with the middle part of said horizontal tail, and second end of said vertical fin (6) is provided with shoe connecting bore (5).
7. the empennage of SUAV according to claim 1 is characterized in that,
Said empennage comprises the skeleton that is made up of rib, stringer and beam, and said skeleton is provided with the covering of glass fiber compound material, and said covering is by mould molding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120485302 CN202429346U (en) | 2011-11-30 | 2011-11-30 | Empennage of small unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120485302 CN202429346U (en) | 2011-11-30 | 2011-11-30 | Empennage of small unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202429346U true CN202429346U (en) | 2012-09-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120485302 Expired - Fee Related CN202429346U (en) | 2011-11-30 | 2011-11-30 | Empennage of small unmanned aerial vehicle |
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| CN (1) | CN202429346U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103192984A (en) * | 2013-03-19 | 2013-07-10 | 北京航空航天大学 | V-shaped empennage device suitable for sea and air across amphibious unmanned aerial vehicle |
| CN104724280A (en) * | 2013-12-23 | 2015-06-24 | 空中客车营运有限公司 | Aircraft control surface |
| CN110203373A (en) * | 2019-05-24 | 2019-09-06 | 成都飞机工业（集团）有限责任公司 | A kind of vertical horizontal tail detaching structure of unmanned plane |
| CN112874760A (en) * | 2021-02-07 | 2021-06-01 | 汉王科技股份有限公司 | Aircraft and control method for aircraft |
-
2011
- 2011-11-30 CN CN 201120485302 patent/CN202429346U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103192984A (en) * | 2013-03-19 | 2013-07-10 | 北京航空航天大学 | V-shaped empennage device suitable for sea and air across amphibious unmanned aerial vehicle |
| CN103192984B (en) * | 2013-03-19 | 2015-01-21 | 北京航空航天大学 | V-shaped empennage device suitable for sea and air across amphibious unmanned aerial vehicle |
| CN104724280A (en) * | 2013-12-23 | 2015-06-24 | 空中客车营运有限公司 | Aircraft control surface |
| CN110203373A (en) * | 2019-05-24 | 2019-09-06 | 成都飞机工业（集团）有限责任公司 | A kind of vertical horizontal tail detaching structure of unmanned plane |
| CN112874760A (en) * | 2021-02-07 | 2021-06-01 | 汉王科技股份有限公司 | Aircraft and control method for aircraft |
| CN112874760B (en) * | 2021-02-07 | 2022-11-15 | 汉王科技股份有限公司 | Aircraft and aircraft control method |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120912 Termination date: 20201130 |