CN103786873A - Interceptor for airframe bottom of unmanned plane - Google Patents
Interceptor for airframe bottom of unmanned plane Download PDFInfo
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- CN103786873A CN103786873A CN201310507095.1A CN201310507095A CN103786873A CN 103786873 A CN103786873 A CN 103786873A CN 201310507095 A CN201310507095 A CN 201310507095A CN 103786873 A CN103786873 A CN 103786873A
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- spoiler
- airframe
- fuselage
- vehicle body
- aerial vehicle
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Abstract
The invention relates to an auxiliary flying structure for an unmanned plane, and particularly relates to an interceptor for an airframe bottom of an unmanned plane. The structure comprises an airframe, wherein side wings are arranged in the middle of two sides of the airframe; side tail wings are arranged on the tail parts of two sides of the airframe; a tail wing is arranged on the upper part of the tail end of the airframe; and an interceptor body is arranged at the bottom of the airframe. According to the interceptor for the airframe bottom of the unmanned plane, the interceptor is arranged at the bottom of the airframe, airflow passing through the airframe is shunted to keep uniformity and stability of airflow passing through the airframe, so that the airframe keeps stable support, violent shaking or out-of-control of the airframe is avoided, and the operation 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, spoiler at the bottom of especially a kind of unmanned aerial vehicle body.
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 reinforcement unmanned plane during flying stability, improve spoiler at the bottom of the unmanned aerial vehicle body of 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 fuselage bottom is provided with spoiler.
Preferably, described spoiler is two L shaped structures of extending dorsad.
Preferably, the L shaped structure of described spoiler by fuselage to the backward outer horizontal-extending of downward-extension.
Preferably, described spoiler is located at forward position, middle part on fuselage.
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, at the bottom of unmanned aerial vehicle body of the present invention, spoiler arranges spoiler at fuselage bottom, air-flow through fuselage is shunted, homogeneity and stability while keeping airflow passes fuselage, make fuselage keep stable support, 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, at the bottom of the unmanned aerial vehicle body of the present embodiment, spoiler 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 fuselage 1 bottom is provided with spoiler 5.
In the present embodiment, described spoiler 5 is two L shaped structures of extending dorsad.
In the present embodiment, the L shaped structure of described spoiler 5 by fuselage to the backward outer horizontal-extending of downward-extension.
In the present embodiment, described spoiler 5 is located at forward position, middle part on fuselage.
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. spoiler at the bottom of unmanned aerial vehicle body, 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 fuselage bottom is provided with spoiler.
2. spoiler at the bottom of unmanned aerial vehicle body as claimed in claim 1, is characterized in that: described spoiler is two L shaped structures of extending dorsad.
3. spoiler at the bottom of unmanned aerial vehicle body as claimed in claim 2, is characterized in that: the L shaped structure of described spoiler by fuselage to the backward outer horizontal-extending of downward-extension.
4. spoiler at the bottom of unmanned aerial vehicle body as claimed in claim 3, is characterized in that: described spoiler is located at forward position, middle part on fuselage.
5. spoiler at the bottom of unmanned aerial vehicle body as claimed in claim 4, is characterized in that: described spoiler is folding structure.
6. spoiler at the bottom of unmanned aerial vehicle body as claimed in claim 5, is characterized in that: the downward extended distance of described spoiler is less than 20-80cm.
7. spoiler at the bottom of unmanned aerial vehicle body as claimed in claim 6, is characterized in that: described spoiler horizontal-extending distance is 20-80cm.
8. spoiler at the bottom of unmanned aerial vehicle body as claimed in claim 7, is characterized in that: the downward extended distance of described spoiler equals horizontal-extending distance.
9. spoiler at the bottom of unmanned aerial vehicle body as claimed in claim 8, is characterized in that: described spoiler thickness is 3-5cm.
10. spoiler at the bottom of unmanned aerial vehicle body 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 |
|---|---|---|---|
| CN201310507095.1A CN103786873A (en) | 2013-10-25 | 2013-10-25 | Interceptor for airframe bottom of unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310507095.1A CN103786873A (en) | 2013-10-25 | 2013-10-25 | Interceptor for airframe bottom of unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103786873A true CN103786873A (en) | 2014-05-14 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310507095.1A Pending CN103786873A (en) | 2013-10-25 | 2013-10-25 | Interceptor for airframe bottom of unmanned plane |
Country Status (1)
| Country | Link |
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| CN (1) | CN103786873A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110562436A (en) * | 2019-09-17 | 2019-12-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft high lift device and have its aircraft |
| CN112541231A (en) * | 2020-12-25 | 2021-03-23 | 中国直升机设计研究所 | Helicopter exhaust pipe shaping spoiler design method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1104741A1 (en) * | 1999-12-01 | 2001-06-06 | Manuel Munoz Saiz | Aircraft lift arrangement |
| CH694987A5 (en) * | 2004-01-07 | 2005-10-31 | Ulrich La Roche | Aircraft wing with grid joined to exterior of main part has grid parts fixed to main part by individual, curved transition pieces |
| WO2007117260A2 (en) * | 2005-07-27 | 2007-10-18 | University Of Southern California | Aircraft with belly flaps |
| 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 |
-
2013
- 2013-10-25 CN CN201310507095.1A patent/CN103786873A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1104741A1 (en) * | 1999-12-01 | 2001-06-06 | Manuel Munoz Saiz | Aircraft lift arrangement |
| CH694987A5 (en) * | 2004-01-07 | 2005-10-31 | Ulrich La Roche | Aircraft wing with grid joined to exterior of main part has grid parts fixed to main part by individual, curved transition pieces |
| WO2007117260A2 (en) * | 2005-07-27 | 2007-10-18 | University Of Southern California | Aircraft with belly flaps |
| 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 |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110562436A (en) * | 2019-09-17 | 2019-12-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft high lift device and have its aircraft |
| CN110562436B (en) * | 2019-09-17 | 2022-11-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft high lift device and have its aircraft |
| CN112541231A (en) * | 2020-12-25 | 2021-03-23 | 中国直升机设计研究所 | Helicopter exhaust pipe shaping spoiler design method |
| CN112541231B (en) * | 2020-12-25 | 2022-12-06 | 中国直升机设计研究所 | Helicopter exhaust pipe shaping spoiler design method |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20140514 |