CN203497172U - Multi-interceptor tail wing of unmanned plane - Google Patents
Multi-interceptor tail wing of unmanned plane Download PDFInfo
- Publication number
- CN203497172U CN203497172U CN201320659680.9U CN201320659680U CN203497172U CN 203497172 U CN203497172 U CN 203497172U CN 201320659680 U CN201320659680 U CN 201320659680U CN 203497172 U CN203497172 U CN 203497172U
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- unmanned plane
- empennage
- spoilers
- described spoiler
- spoiler
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Abstract
The utility model relates to a flight assisting structure of an unmanned plane and particularly relates to a multi-interceptor tail wing of the unmanned plane. The structure comprises a plane body, wherein side wings are arranged at the middles of two sides of the plane body, side tail wings are arranged at the tails of two sides of the plane body, tail wings are arranged at the upper parts of the tail ends of the plane body, and a plurality of stacked interceptors are arranged below the side wings on two sides of the plane body. According to the multi-interceptor tail wing of the unmanned plane, the interceptors are arranged below the tail wings on two sides of the plane body and are used for dividing air current flowing through the side wings, so that the uniformity and stability of the air current, flowing through tail wings, are maintained, the plane body is stably supported by the tail wings, the acute shaking or an out-of-control state of the plane body is avoided, and the stability and safety of the unmanned plane during the operation are improved.
Description
Technical field
The utility model relates to a kind of unmanned plane during flying supplementary structure, especially a kind of many spoilers of unmanned plane empennage.
Background technology
Robot airplane is called for short " unmanned plane ", is the not manned aircraft that utilizes radio robot and the process controller of providing for oneself to handle.On machine, without driving compartment, but the equipment such as autopilot, process controller are installed.On ground, naval vessels or machine tool command and control station personnel by equipment such as radars, to its follow the tracks of, location, remote control, remote measurement and digital communication.Can under radio telecommand, as conventional airplane, take off or launch with booster rocket, also can take aerial input to by machine tool and fly.During recovery, the available mode automatic Landing the same with conventional airplane landing mission, also can reclaim with parachute or block by remote control.
Owing to not establishing driving compartment on unmanned plane, in order to reduce consumption of power, generally unmanned plane is carried out to miniaturization and weight-saving design, so, small-sized unmanned plane, in flight course, often receives that the impact of air-flow is larger, and air-flow is inhomogeneous fuselage and wing section, easily cause rocking of fuselage, when taking, be unfavorable for the stability of picture, more serious, even can cause crash, easily the people on ground or thing be caused to damage.
Summary of the invention
A kind of stability of reinforcement unmanned plane during flying is provided the utility model, many spoilers of unmanned plane empennage of raising safety in operation.
To achieve these goals, the utility model adopts following technical scheme:
Comprise that fuselage, fuselage two middle side parts are provided with flank, fuselage both sides afterbody is provided with side empennage, and tail cone top is provided with empennage, and its improvement is: described empennage top, both sides is respectively equipped with a plurality of stacked spoilers.
Preferably, described spoiler is the L shaped structure that main frame dwindles.
Preferably, the L shaped structure of described spoiler extends upward backward outer horizontal-extending by spoiler.
Preferably, described spoiler is located on flank middle part with interior position.
Preferably, described spoiler is folding structure.
Preferably, the downward extended distance of described spoiler is less than 20-80cm.
Preferably, described spoiler horizontal-extending distance is 20-80cm.
Preferably, the downward extended distance of described spoiler equals horizontal-extending distance.
Preferably, described spoiler thickness is 3-5cm.
Preferably, described spoiler width is 20-50cm.
Owing to having adopted said structure, many spoilers of unmanned plane empennage of the present utility model arranges spoiler above the empennage of fuselage both sides, air-flow through empennage is shunted, homogeneity and stability while keeping airflow passes empennage, make empennage keep stable support to fuselage, avoided fuselage acutely rock or out of control, improved stability and the safety of unmanned plane operation.
Accompanying drawing explanation
Fig. 1 is the perspective view of the utility model embodiment.
The specific embodiment
As shown in Figure 1, many spoilers of unmanned plane empennage of the present embodiment comprises that fuselage 1,1 liang of middle side part of fuselage are provided with flank 2, fuselage 1 both sides afterbody is provided with side empennage 3, and fuselage 1 upper end is provided with empennage 4, and described both sides empennage 3 tops are respectively equipped with a plurality of stacked spoilers 5.
In the present embodiment, the L shaped structure that described spoiler 5 dwindles for main frame.
In the present embodiment, the L shaped structure of described spoiler 5 extends upward backward outer horizontal-extending by spoiler.
In the present embodiment, described spoiler 5 is located on flank middle part with interior position.
In the present embodiment, described spoiler 5 is folding structure.
In the present embodiment, the described downward extended distance of spoiler 5 is less than 20-80cm.
In the present embodiment, described spoiler 5 horizontal-extending distances are 20-80cm.
In the present embodiment, the described downward extended distance of spoiler 5 equals horizontal-extending distance.
In the present embodiment, described spoiler 5 thickness are 3-5cm.
In the present embodiment, described spoiler 5 width are 20-50cm.
The foregoing is only preferred embodiment of the present utility model; not thereby limit the scope of the claims of the present utility model; every equivalent structure or conversion of equivalent flow process that utilizes the utility model specification sheets and accompanying drawing content to do; or be directly or indirectly used in other relevant technical fields, be all in like manner included in scope of patent protection of the present utility model.
Claims (10)
1. many spoilers of unmanned plane empennage, comprises that fuselage, fuselage two middle side parts are provided with flank, and fuselage both sides afterbody is provided with side empennage, and tail cone top is provided with empennage, it is characterized in that: described empennage top, both sides is respectively equipped with a plurality of stacked spoilers.
2. many spoilers of unmanned plane empennage as claimed in claim 1, is characterized in that: described spoiler is the L shaped structure that main frame dwindles.
3. many spoilers of unmanned plane empennage as claimed in claim 2, is characterized in that: the L shaped structure of described spoiler extends upward backward outer horizontal-extending by spoiler.
4. many spoilers of unmanned plane empennage as claimed in claim 3, is characterized in that: described spoiler is located on flank middle part with interior position.
5. many spoilers of unmanned plane empennage as claimed in claim 4, is characterized in that: described spoiler is folding structure.
6. many spoilers of unmanned plane empennage as claimed in claim 5, is characterized in that: the downward extended distance of described spoiler is less than 20-80cm.
7. many spoilers of unmanned plane empennage as claimed in claim 6, is characterized in that: described spoiler horizontal-extending distance is 20-80cm.
8. many spoilers of unmanned plane empennage as claimed in claim 7, is characterized in that: the downward extended distance of described spoiler equals horizontal-extending distance.
9. many spoilers of unmanned plane empennage as claimed in claim 8, is characterized in that: described spoiler thickness is 3-5cm.
10. many spoilers of unmanned plane empennage as claimed in claim 9, is characterized in that: described spoiler width is 20-50cm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320659680.9U CN203497172U (en) | 2013-10-25 | 2013-10-25 | Multi-interceptor tail wing of unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320659680.9U CN203497172U (en) | 2013-10-25 | 2013-10-25 | Multi-interceptor tail wing of unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203497172U true CN203497172U (en) | 2014-03-26 |
Family
ID=50328171
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320659680.9U Expired - Fee Related CN203497172U (en) | 2013-10-25 | 2013-10-25 | Multi-interceptor tail wing of unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203497172U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103803061A (en) * | 2013-10-25 | 2014-05-21 | 苏州艾锐泰克无人飞行器科技有限公司 | Multi-interceptor empennage of unmanned aerial vehicle (UAV) |
-
2013
- 2013-10-25 CN CN201320659680.9U patent/CN203497172U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103803061A (en) * | 2013-10-25 | 2014-05-21 | 苏州艾锐泰克无人飞行器科技有限公司 | Multi-interceptor empennage of unmanned aerial vehicle (UAV) |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140326 Termination date: 20141025 |
|
| EXPY | Termination of patent right or utility model |