CN103523215A - Landing assisting wheel of unmanned aerial vehicle - Google Patents
Landing assisting wheel of unmanned aerial vehicle Download PDFInfo
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- CN103523215A CN103523215A CN201310480646.XA CN201310480646A CN103523215A CN 103523215 A CN103523215 A CN 103523215A CN 201310480646 A CN201310480646 A CN 201310480646A CN 103523215 A CN103523215 A CN 103523215A
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- wheel
- strut bar
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- falls
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Abstract
The invention relates to an unmanned aerial vehicle landing auxiliary structure, and in particular relates to a landing assisting wheel of an unmanned aerial vehicle. The landing assisting wheel structurally comprises a plane body, wherein side wings are arranged on two sides of the middle part of the plane body; side empennages are arranged on two sides of the tail part of the plane body; an empennage is arranged above the tail part of the plane body; a rear landing assisting parachute cabin is arranged at the tail part of the plane body; a rear landing assisting parachute is arranged inside the rear landing assisting parachute cabin; and a landing assisting wheel is arranged at the head part of the plane body. According to the landing assisting wheel of the unmanned aerial vehicle, when the unmanned aerial vehicle losses the power and lands in a state that the tail part faces up and the head part faces down, the landing assisting wheel lands at first, so that the head part of the plane body moves forwards, the balance state of the plane body is recovered along with forward motion, hard landing of the head part is avoided when the unmanned aerial vehicle lands, and the security of the unmanned aerial vehicle in landing is ensured.
Description
Technical field
The present invention relates to a kind of unmanned plane landing supplementary structure, wheel falls in especially a kind of unmanned machine aided.
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.
Because civilian unmanned plane does not generally have the landing runway of condition setting special use, so take off and land in the comparatively open areas such as general common square, vacant lot, especially when landing, owing to often there is no enough buffer distances, so generally fall umbrella auxiliary landing by helping of a postposition, generally be manual operation, when manual operation not at that time, unmanned plane can run out of steam when kiss the earth not yet, because afterbody helps, the auxiliary of umbrella falls, aircraft can first land by front end head when land, is unfavorable for the stable landing of unmanned plane, also easily unmanned plane is caused to damage.
Summary of the invention
The invention provides a kind of stable landing that is conducive to unmanned plane, guarantee unmanned plane safety unmanned machine aided wheel falls.
To achieve these goals, the present invention adopts following technical scheme:
Comprise a fuselage, described waist both sides are provided with flank, and afterbody both sides are provided with tail flank, afterbody top is provided with empennage, after afterbody is provided with, help and fall umbrella storehouse, after help to fall after being provided with in umbrella storehouse and help and fall umbrella, its improvement is: described fuselage head is provided with one and helps and fall wheel.
Preferably, described helping fallen wheel and is installed on strut bar.
Preferably, described strut bar is inclined upwardly along horizontal surface.
Preferably, described strut bar is scalable container structure.
Preferably, described strut bar is rotation container structure.
Preferably, in described strut bar, be provided with shock-damping structure.
Preferably, described helping fallen wheel for many wheel constructions arranged side by side.
Preferably, described strut bar is multistage foldable structure.
Preferably, described strut bar is transposition arm stretching structure.
Preferably, described helping fallen wheel and connected guiding motor.
Owing to having adopted said structure, unmanned machine aided of the present invention falls wheel and aloft runs out of steam while forming afterbody towards state landing down of head portion, help and fall wheel and first land, fuselage head is travelled forward, along with travelling forward, reply the state of equilibrium of fuselage, while avoiding unmanned plane to land, head is rigid lands, the safety while having guaranteed unmanned plane landing.
Accompanying drawing explanation
Fig. 1 is the perspective view of the embodiment of the present invention;
Fig. 2 is the folding support bar structural representation of the embodiment of the present invention;
Fig. 3 is the transposition arm supporting bar structure schematic diagram of the embodiment of the present invention.
The specific embodiment
As shown in Figure 1-Figure 3, the unmanned machine aided of the present embodiment falls wheel and comprises a fuselage 1, described fuselage 1 both sides, middle part are provided with flank 2, fuselage 1 two sides of tail is provided with tail flank 3, fuselage 1 afterbody top is provided with empennage 4, after fuselage 1 afterbody is provided with, helps and fall umbrella storehouse 5, after help to fall after being provided with in umbrella storehouse and help and fall umbrella, described fuselage 1 head is provided with one and helps and fall wheel 6.
In the present embodiment, described helping fallen wheel 6 and is installed on strut bar 7.
In the present embodiment, in order to make to help to fall in wheel 6 rolling processes, keep belly down, described strut bar 7 is inclined upwardly along horizontal surface.
In the present embodiment, for conserve space, unaffected while making unmanned plane during flying, described strut bar 7 is scalable container structure or rotation container structure.
In order reducing to help, to fall wheel impact to fuselage while landing, in the present embodiment, in described strut bar 7, to be provided with shock-damping structure.
In order to reduce to help the impact of falling wheel to single, in the present embodiment, described helping fallen wheel 6 for many wheel constructions arranged side by side.
In the present embodiment, as shown in Figures 2 and 3, in order to save the strut bar of taking in described in the needed space of strut bar, be multistage foldable structure or transposition arm stretching structure.
In order to prevent that fuselage back lands, in the present embodiment, described helping fallen wheel 6 and connected guiding motor.Help fall wheel 6 land after, guiding motor it is drawn, make the downward land of belly.
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. wheel falls in unmanned machine aided, comprise a fuselage, described waist both sides are provided with flank, afterbody both sides are provided with tail flank, afterbody top is provided with empennage, after afterbody is provided with, help and fall umbrella storehouse, after help to fall after being provided with in umbrella storehouse and help and fall umbrella, it is characterized in that: described fuselage head is provided with one and helps and fall wheel.
2. wheel falls in unmanned machine aided as claimed in claim 1, it is characterized in that: described helping fallen wheel and be installed on strut bar.
3. wheel falls in unmanned machine aided as claimed in claim 2, it is characterized in that: described helping fallen wheel and be installed on strut bar; Described strut bar is inclined upwardly along horizontal surface.
4. wheel falls in unmanned machine aided as claimed in claim 3, it is characterized in that: described helping fallen wheel and be installed on strut bar; Described strut bar is scalable container structure.
5. wheel falls in unmanned machine aided as claimed in claim 4, it is characterized in that: described helping fallen wheel and be installed on strut bar; Described strut bar is rotation container structure.
6. wheel falls in unmanned machine aided as claimed in claim 5, it is characterized in that: described helping fallen wheel and be installed on strut bar; In described strut bar, be provided with shock-damping structure.
7. wheel falls in unmanned machine aided as claimed in claim 6, it is characterized in that: described helping fallen wheel and be installed on strut bar; Described helping fallen wheel for many wheel constructions arranged side by side.
8. wheel falls in unmanned machine aided as claimed in claim 7, it is characterized in that: described helping fallen wheel and be installed on strut bar; Described strut bar is multistage foldable structure.
9. wheel falls in unmanned machine aided as claimed in claim 8, it is characterized in that: described helping fallen wheel and be installed on strut bar; Described strut bar is transposition arm stretching structure.
10. wheel falls in unmanned machine aided as claimed in claim 9, it is characterized in that: described helping fallen wheel and be installed on strut bar; Wheel connection guiding motor falls in described helping.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310480646.XA CN103523215A (en) | 2013-10-15 | 2013-10-15 | Landing assisting wheel of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310480646.XA CN103523215A (en) | 2013-10-15 | 2013-10-15 | Landing assisting wheel of unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103523215A true CN103523215A (en) | 2014-01-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310480646.XA Pending CN103523215A (en) | 2013-10-15 | 2013-10-15 | Landing assisting wheel of unmanned aerial vehicle |
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| CN (1) | CN103523215A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090045283A1 (en) * | 2007-01-11 | 2009-02-19 | Lockheed Martin Corporation | System, method and apparatus for ground-based manipulation and control of aerial vehicle during non-flying operations |
| CN102050223A (en) * | 2009-11-04 | 2011-05-11 | 奥格斯塔股份公司 | Aircraft landing gear |
| US20110180662A1 (en) * | 2008-01-24 | 2011-07-28 | Magnaghi Aeronautica S.P.A. | Landing gear |
| CN102574579A (en) * | 2009-08-25 | 2012-07-11 | 梅西耶-道提有限公司 | Main landing gear with rigid rear stay |
| CN202414153U (en) * | 2011-12-21 | 2012-09-05 | 天津风之翼科技有限公司 | Multi-purpose unmanned aerial vehicle airframe |
-
2013
- 2013-10-15 CN CN201310480646.XA patent/CN103523215A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090045283A1 (en) * | 2007-01-11 | 2009-02-19 | Lockheed Martin Corporation | System, method and apparatus for ground-based manipulation and control of aerial vehicle during non-flying operations |
| US20110180662A1 (en) * | 2008-01-24 | 2011-07-28 | Magnaghi Aeronautica S.P.A. | Landing gear |
| CN102574579A (en) * | 2009-08-25 | 2012-07-11 | 梅西耶-道提有限公司 | Main landing gear with rigid rear stay |
| CN102050223A (en) * | 2009-11-04 | 2011-05-11 | 奥格斯塔股份公司 | Aircraft landing gear |
| CN202414153U (en) * | 2011-12-21 | 2012-09-05 | 天津风之翼科技有限公司 | Multi-purpose unmanned aerial vehicle airframe |
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| C06 | Publication | ||
| 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: 20140122 |