CN103803061A - Multi-interceptor empennage of unmanned aerial vehicle (UAV) - Google Patents
Multi-interceptor empennage of unmanned aerial vehicle (UAV) Download PDFInfo
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- CN103803061A CN103803061A CN201310506978.0A CN201310506978A CN103803061A CN 103803061 A CN103803061 A CN 103803061A CN 201310506978 A CN201310506978 A CN 201310506978A CN 103803061 A CN103803061 A CN 103803061A
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- empennage
- unmanned plane
- fuselage
- spoilers
- described spoiler
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Abstract
The invention relates to a flight auxiliary structure of an unmanned aerial vehicle (UAV), and in particular relates to a multi-interceptor empennage of the UAV. The multi-interceptor empennage structurally comprises a fuselage; two side wings are respectively arranged in the middles of the two sides of the fuselage; two side empennages are respectively arranged at the tail parts of the two sides of the fuselage; the upper part of the tail end of the fuselage is provided with an empennage; a plurality of stacked interceptors are respectively arranged above the two side empennages. According to the multi-interceptor empennage of the UAV, the interceptors are respectively arranged above the two side empennages, and airflow passing through the empennage can be diverted, so that the uniformity and the stability of the airflow which passes through the empennage can be maintained, the fuselage is stably supported by the empennage, the fuselage is prevented from violently shaking or being out of control, and the stability and the safety in the operation of the UAV are improved.
Description
Technical field
The present invention 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 is 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.When 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 people or the thing to ground causes damage.
Summary of the invention
The invention provides a kind of stability of reinforcement unmanned plane during flying, many spoilers of unmanned plane empennage of raising safety in operation.
To achieve these goals, the present invention 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 multiple stacked spoilers.
Preferably, described spoiler is the L shaped structure that main frame dwindles.
Preferably, the L shaped structure of described spoiler is upwards extended 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 invention 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 embodiment of the present invention.
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 multiple 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 is upwards extended 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 the preferred embodiments of the present invention; not thereby limit the scope of the claims of the present invention; every equivalent structure or conversion of equivalent flow process that utilizes specification sheets of the present invention 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 invention.
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 multiple 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 is upwards extended 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 |
|---|---|---|---|
| CN201310506978.0A CN103803061A (en) | 2013-10-25 | 2013-10-25 | Multi-interceptor empennage of unmanned aerial vehicle (UAV) |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310506978.0A CN103803061A (en) | 2013-10-25 | 2013-10-25 | Multi-interceptor empennage of unmanned aerial vehicle (UAV) |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103803061A true CN103803061A (en) | 2014-05-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310506978.0A Pending CN103803061A (en) | 2013-10-25 | 2013-10-25 | Multi-interceptor empennage of unmanned aerial vehicle (UAV) |
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| CN (1) | CN103803061A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104015916A (en) * | 2014-06-13 | 2014-09-03 | 韩世宇 | Unmanned plane |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070164147A1 (en) * | 2002-01-14 | 2007-07-19 | Carr Robert J | Aircraft internal wing and design |
| US20110272532A1 (en) * | 2009-02-18 | 2011-11-10 | Yukitaka Matsuda | Aircraft wing load alleviation system |
| CN102390522A (en) * | 2011-09-22 | 2012-03-28 | 西北工业大学 | Flow guide blade grid for short-distance takeoff and landing of airplane |
| CN203497172U (en) * | 2013-10-25 | 2014-03-26 | 苏州艾锐泰克无人飞行器科技有限公司 | Multi-interceptor tail wing of unmanned plane |
-
2013
- 2013-10-25 CN CN201310506978.0A patent/CN103803061A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070164147A1 (en) * | 2002-01-14 | 2007-07-19 | Carr Robert J | Aircraft internal wing and design |
| US20110272532A1 (en) * | 2009-02-18 | 2011-11-10 | Yukitaka Matsuda | Aircraft wing load alleviation system |
| CN102390522A (en) * | 2011-09-22 | 2012-03-28 | 西北工业大学 | Flow guide blade grid for short-distance takeoff and landing of airplane |
| CN203497172U (en) * | 2013-10-25 | 2014-03-26 | 苏州艾锐泰克无人飞行器科技有限公司 | Multi-interceptor tail wing of unmanned plane |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104015916A (en) * | 2014-06-13 | 2014-09-03 | 韩世宇 | Unmanned plane |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140521 |