CN103803059A - Unmanned plane multi-spoiler side wing - Google Patents
Unmanned plane multi-spoiler side wing Download PDFInfo
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- CN103803059A CN103803059A CN201310507036.4A CN201310507036A CN103803059A CN 103803059 A CN103803059 A CN 103803059A CN 201310507036 A CN201310507036 A CN 201310507036A CN 103803059 A CN103803059 A CN 103803059A
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- unmanned plane
- fuselage
- flank
- spoilers
- spoiler
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Abstract
The invention relates to an unmanned plane flying auxiliary structure, and particularly relates to an unmanned plane multi-spoiler side wing. The structure comprises a fuselage, side wings arranged in the middles of the two sides of the fuselage, side tail wings arranged at the tail parts of the two sides of the fuselage, and a tail wing arranged on the upper part of the tail end of the fuselage, wherein a plurality of laminated spoilers are respectively arranged under the two side wings. According to the unmanned plane multi-spoiler side wing, the spoilers are arranged under the side wings on the two sides of the fuselage to divide air flow passing through the side wings, so that the homogeneity and stability when the air flow flows through the side wings are kept, the supporting to the fuselage by the side wings 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 many spoilers of unmanned plane flank.
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 flank 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 flank below, both sides is respectively equipped with multiple stacked spoilers.
Preferably, described spoiler is the L shaped structure of dwindling step by step.
Preferably, the L shaped structure of described spoiler by spoiler to the backward outer horizontal-extending of downward-extension.
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 flank of the present invention arranges spoiler below the flank of fuselage both sides, air-flow through flank is shunted, homogeneity and stability while keeping airflow passes flank, make flank 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 flank 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 flank 2 belows are respectively equipped with multiple stacked spoilers 5.
In the present embodiment, the L shaped structure of described spoiler 5 for dwindling step by step.
In the present embodiment, the L shaped structure of described spoiler 5 by spoiler to the backward outer horizontal-extending of downward-extension.
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 flank, 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 flank below, both sides is respectively equipped with multiple stacked spoilers.
2. many spoilers of unmanned plane flank as claimed in claim 1, is characterized in that: described spoiler is the L shaped structure of dwindling step by step.
3. many spoilers of unmanned plane flank as claimed in claim 2, is characterized in that: the L shaped structure of described spoiler by spoiler to the backward outer horizontal-extending of downward-extension.
4. many spoilers of unmanned plane flank 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 flank as claimed in claim 4, is characterized in that: described spoiler is folding structure.
6. many spoilers of unmanned plane flank 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 flank as claimed in claim 6, is characterized in that: described spoiler horizontal-extending distance is 20-80cm.
8. many spoilers of unmanned plane flank 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 flank as claimed in claim 8, is characterized in that: described spoiler thickness is 3-5cm.
10. many spoilers of unmanned plane flank 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 |
|---|---|---|---|
| CN201310507036.4A CN103803059A (en) | 2013-10-25 | 2013-10-25 | Unmanned plane multi-spoiler side wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310507036.4A CN103803059A (en) | 2013-10-25 | 2013-10-25 | Unmanned plane multi-spoiler side wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103803059A true CN103803059A (en) | 2014-05-21 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310507036.4A Pending CN103803059A (en) | 2013-10-25 | 2013-10-25 | Unmanned plane multi-spoiler side wing |
Country Status (1)
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| CN (1) | CN103803059A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107187579A (en) * | 2017-05-22 | 2017-09-22 | 北京航空航天大学 | A kind of flight force and moment control method suitable for many aerofoil aeroplane clothes office |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6491261B1 (en) * | 2000-04-17 | 2002-12-10 | The United States Of America As Represented By The Secretary Of The Air Force | Wing mounted aircraft yaw control device |
| EP1631493B1 (en) * | 2003-06-06 | 2006-11-22 | Northrop Grumman Corporation | Aircraft with topside only spoilers |
| WO2007117260A2 (en) * | 2005-07-27 | 2007-10-18 | University Of Southern California | Aircraft with belly flaps |
| CN101096233A (en) * | 2006-06-27 | 2008-01-02 | 上海力卡塑料托盘制造厂 | Two-end core-loosing middle groove shaped steel-hidden plastic-steel tray |
| CN202279230U (en) * | 2011-09-22 | 2012-06-20 | 西北工业大学 | Flow guiding grid plate for lift augmentation of airplane |
-
2013
- 2013-10-25 CN CN201310507036.4A patent/CN103803059A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6491261B1 (en) * | 2000-04-17 | 2002-12-10 | The United States Of America As Represented By The Secretary Of The Air Force | Wing mounted aircraft yaw control device |
| EP1631493B1 (en) * | 2003-06-06 | 2006-11-22 | Northrop Grumman Corporation | Aircraft with topside only spoilers |
| WO2007117260A2 (en) * | 2005-07-27 | 2007-10-18 | University Of Southern California | Aircraft with belly flaps |
| CN101096233A (en) * | 2006-06-27 | 2008-01-02 | 上海力卡塑料托盘制造厂 | Two-end core-loosing middle groove shaped steel-hidden plastic-steel tray |
| CN202279230U (en) * | 2011-09-22 | 2012-06-20 | 西北工业大学 | Flow guiding grid plate for lift augmentation of airplane |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107187579A (en) * | 2017-05-22 | 2017-09-22 | 北京航空航天大学 | A kind of flight force and moment control method suitable for many aerofoil aeroplane clothes office |
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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 |