CN103803060A - Unmanned plane single-spoiler empennage - Google Patents
Unmanned plane single-spoiler empennage Download PDFInfo
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- CN103803060A CN103803060A CN201310506976.1A CN201310506976A CN103803060A CN 103803060 A CN103803060 A CN 103803060A CN 201310506976 A CN201310506976 A CN 201310506976A CN 103803060 A CN103803060 A CN 103803060A
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- spoiler
- empennage
- unmanned plane
- fuselage
- plane list
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Abstract
The invention relates to an unmanned plane flying auxiliary structure, and particularly relates to an unmanned plane single-spoiler empennage. The structure comprises a fuselage, side wings arranged on the middle parts of two sides of the fuselage, side empennage bodies arranged on the tail parts of the two sides of the fuselage, and an empennage body arranged on the upper part of the tail end of the fuselage, wherein a spoiler is arranged above the two side empennage bodies. According to the unmanned plane single-spoiler empennage, the spoiler is arranged above the side empennage bodies on the two sides of the fuselage to divide air flow passing through the empennage, so that the homogeneity and stability when the air flow flows through the empennage are kept, the supporting for the fuselage by the empennage is kept, violent shaking or out of control of the fuselage is avoided, and the running stability and safety of the unmanned plane are improved.
Description
Technical field
The present invention relates to a kind of unmanned plane during flying supplementary structure, especially a kind of unmanned plane list spoiler 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, the unmanned plane list spoiler 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 a spoiler.
Preferably, described spoiler is L shaped structure.
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, unmanned plane list spoiler 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, the unmanned plane list spoiler empennage of the present embodiment comprises that fuselage 1,1 liang of middle side part of fuselage are provided with flank 2, and 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 spoiler 5.
In the present embodiment, described spoiler 5 is L shaped structure.
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. unmanned plane list spoiler 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 spoiler.
2. unmanned plane list spoiler empennage as claimed in claim 1, is characterized in that: described spoiler is L shaped structure.
3. unmanned plane list spoiler 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. unmanned plane list spoiler empennage as claimed in claim 3, is characterized in that: described spoiler is located on flank middle part with interior position.
5. unmanned plane list spoiler empennage as claimed in claim 4, is characterized in that: described spoiler is folding structure.
6. unmanned plane list spoiler empennage as claimed in claim 5, is characterized in that: the downward extended distance of described spoiler is less than 20-80cm.
7. unmanned plane list spoiler empennage as claimed in claim 6, is characterized in that: described spoiler horizontal-extending distance is 20-80cm.
8. unmanned plane list spoiler empennage as claimed in claim 7, is characterized in that: the downward extended distance of described spoiler equals horizontal-extending distance.
9. unmanned plane list spoiler empennage as claimed in claim 8, is characterized in that: described spoiler thickness is 3-5cm.
10. unmanned plane list spoiler 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 |
|---|---|---|---|
| CN201310506976.1A CN103803060A (en) | 2013-10-25 | 2013-10-25 | Unmanned plane single-spoiler empennage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310506976.1A CN103803060A (en) | 2013-10-25 | 2013-10-25 | Unmanned plane single-spoiler empennage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103803060A true CN103803060A (en) | 2014-05-21 |
Family
ID=50700552
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310506976.1A Pending CN103803060A (en) | 2013-10-25 | 2013-10-25 | Unmanned plane single-spoiler empennage |
Country Status (1)
| Country | Link |
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| CN (1) | CN103803060A (en) |
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 |
| CN203497173U (en) * | 2013-10-25 | 2014-03-26 | 苏州艾锐泰克无人飞行器科技有限公司 | Single-interceptor tail wing of unmanned plane |
-
2013
- 2013-10-25 CN CN201310506976.1A patent/CN103803060A/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 |
| CN203497173U (en) * | 2013-10-25 | 2014-03-26 | 苏州艾锐泰克无人飞行器科技有限公司 | Single-interceptor tail wing of unmanned plane |
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| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140521 |