CN105270603A - Unmanned fixed-wing aircraft with large aspect ratio - Google Patents
Unmanned fixed-wing aircraft with large aspect ratio Download PDFInfo
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- CN105270603A CN105270603A CN201510703842.8A CN201510703842A CN105270603A CN 105270603 A CN105270603 A CN 105270603A CN 201510703842 A CN201510703842 A CN 201510703842A CN 105270603 A CN105270603 A CN 105270603A
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- wing
- reinforced rib
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- pipe link
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Abstract
The invention provides an unmanned fixed-wing aircraft with a large aspect ratio. The unmanned fixed-wing aircraft comprises an aircraft, wherein the aircraft comprises an aircraft body, a wing and a tail; the wing comprises a main wing; accessory wings are respectively arranged at two ends of the main wing; the tail comprises an elevating rudder, a rudder, a horizontal tail and a vertical tail. The unmanned fixed-wing aircraft is simple in structure, and reasonable in design; the strength of the wing and the stiffness of the wing are improved, but the weight of the wing is not significantly increased; the wing is large, so that the flying performance of the aircraft is good, and the flying time of the aircraft is long; the safety of the aircraft is high; the overall stress of the wing is even, so that the phenomenon that the wing is fractured is not liable to occur; the wing is convenient to mount and demount; the aircraft is simple to operate, and is convenient to carry and maintain; the service life of the whole aircraft is prolonged, and the aircraft is wide in applicability.
Description
Technical field
The present invention relates to vehicle technology field, particularly the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio.
Background technology
Aircraft is the apparatus flyer in endoatmosphere or exoatmosphere spaceflight being manufactured by the mankind, can fly away from ground, control in spaceflight and by people.Be called aerocraft in endoatmosphere flight, be called spacecraft in space flight.And the aircraft that aspect ratio is large, performance of leaving a blank will be got well.Covering skeleton type fixed-wing unmanned vehicle mostly is girder structure, and rib trailing edge easily ruptures, cause In-Flight Performance decline even aircraft damage, without reinforcing rib design, cause wing Stiffness, easy torsional deflection.High aspect ratio fixed-wing unmanned vehicle mostly is standard aerofoil profile, shows each variant in a practical situation.Multi element wing many employings rigid connection, as bolt etc., is inconvenient to dismantle.
Summary of the invention
Problem to be solved by this invention is to provide the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, solve the aircraft that aspect ratio is large, performance of leaving a blank will be got well, covering skeleton type fixed-wing unmanned vehicle mostly is girder structure, rib trailing edge easily ruptures, cause In-Flight Performance decline even aircraft damage, without reinforcing rib design, cause wing Stiffness, easy torsional deflection, high aspect ratio fixed-wing unmanned vehicle mostly is standard aerofoil profile, show each variant in a practical situation, multi element wing many employings rigid connection, as bolt etc., inconvenient dismounting problem.
For overcoming the above problems scheme of the present invention:
The unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, comprise aircraft, described aircraft comprises fuselage, wing and tail, described wing comprises host wing, host wing two ends are provided with the slave wing, described host wing is provided with the first reinforced rib mounting hole, second reinforced rib mounting hole, main slotting mounting hole and host wing spar, described host wing spar is provided with locating dowel pin mounting hole, described host wing one end is provided with the first leading edge carbon beam, the other end is provided with the first trailing edge carbon beam, the described slave wing is provided with the first reinforced rib pipe link, second reinforced rib pipe link and secondary wing spar, described secondary wing spar is provided with main slotting pipe link, described master inserts pipe link and is provided with draw-in groove, described draw-in groove by the locating dowel pin mounting hole on locating dowel pin and host wing spar with the use of, the first reinforced rib pipe link on the described slave wing and the first reinforced rib mounting hole on host wing with the use of, the second reinforced rib pipe link on the slave wing and the second reinforced rib mounting hole on host wing with the use of, described slave wing one end is provided with the second leading edge carbon beam, the other end is provided with the second trailing edge carbon beam, described tail comprises elevating rudder, yaw rudder, horizontal tail and vertical fin.
The above-mentioned unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, wherein, described host wing comprises the thriving block of main frame, and the slave wing comprises the thriving block of slave, and the thriving block of described main frame is identical with slave thriving block size shape.
The above-mentioned unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, wherein, described wing length is 2600mm, and fuselage length is 1200mm.
The above-mentioned unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, wherein, the first described reinforced rib pipe link, the second reinforced rib pipe link, main slotting pipe link and locating dowel pin are rectangular configuration.
The above-mentioned unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, wherein, described wing is provided with one deck covering.
The beneficial effect of this programme:
The unmanned Fixed Wing AirVehicle of a kind of high aspect ratio provided by the invention, structure is simple, reasonable in design, reinforcing rib design, wing strength and stiffness are increased while obviously not increasing wing weight, wing is larger, performance of leaving a blank is good, airborne period is long, the first reinforced rib pipe link when mounted on the slave wing and the second reinforced rib pipe link achieve a fixed connection through the first reinforced rib mounting hole on host wing and the second reinforced rib mounting hole, master on secondary wing spar inserts pipe link and inserts mounting hole through main, by orienting pin, master is inserted pipe link locked, safety is higher, overall stressed more even, be not easy to produce the phenomenon fractureed, be convenient to install and remove, simple to operate, be easy to carry in maintenance, improve overall service life, applicability is wider.
Accompanying drawing explanation
Fig. 1 is integral structure figure of the present invention.
Fig. 2 is host wing of the present invention and slave wing structure figure.
Fig. 3 is host wing constructional drawing of the present invention.
Fig. 4 is slave wing structure figure of the present invention.
Detailed description of the invention
As shown in the figure, the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, comprise aircraft 1, described aircraft 1 comprises fuselage 2, wing 3 and tail 4, described wing 3 comprises host wing 5, host wing 5 two ends are provided with the slave wing 6, described host wing 5 is provided with the first reinforced rib mounting hole 7, second reinforced rib mounting hole 8, main slotting mounting hole 9 and host wing spar 10, described host wing spar 10 is provided with locating dowel pin mounting hole 11, described host wing 5 one end is provided with the first leading edge carbon beam 12, the other end is provided with the first trailing edge carbon beam 13, the described slave wing 6 is provided with the first reinforced rib pipe link 14, second reinforced rib pipe link 15 and secondary wing spar 16, described secondary wing spar 16 is provided with main slotting pipe link 17, described master inserts pipe link 17 and is provided with draw-in groove 18, described draw-in groove 18 by locating dowel pin 19 and the locating dowel pin mounting hole 11 on host wing spar 10 with the use of, the first reinforced rib pipe link 14 on the described slave wing 6 and the first reinforced rib mounting hole 7 on host wing with the use of, the second reinforced rib pipe link 15 on the slave wing and the second reinforced rib mounting hole 8 on host wing with the use of, the described slave wing 6 one end is provided with the second leading edge carbon beam 20, the other end is provided with the second trailing edge carbon beam 21, described tail 4 comprises elevating rudder 22, yaw rudder 23, horizontal tail 24 and vertical fin 25, described host wing 5 comprises the thriving block 26 of main frame, the slave wing 6 comprises the thriving block 27 of slave, the thriving block of described main frame 26 is identical with slave thriving block 27 size shape, described wing 3 length is 2600mm, fuselage 4 length is 1200mm, the first described reinforced rib pipe link 14, second reinforced rib pipe link 15, main pipe link 17 of inserting is rectangular configuration with locating dowel pin 19, described wing 3 is provided with one deck covering 28.
The unmanned Fixed Wing AirVehicle of a kind of high aspect ratio provided by the invention, structure is simple, reasonable in design, reinforcing rib design, wing strength and stiffness are increased while obviously not increasing wing weight, wing is larger, performance of leaving a blank is good, airborne period is long, the first reinforced rib pipe link when mounted on the slave wing and the second reinforced rib pipe link achieve a fixed connection through the first reinforced rib mounting hole on host wing and the second reinforced rib mounting hole, master on secondary wing spar inserts pipe link and inserts mounting hole through main, by orienting pin, master is inserted pipe link locked, safety is higher, overall stressed more even, be not easy to produce the phenomenon fractureed, be convenient to install and remove, simple to operate, be easy to carry in maintenance, improve overall service life, applicability is wider.
Be only the present invention's preferably detailed description of the invention; but protection scope of the present invention is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the present invention discloses, the change that can expect easily or replacement, all should be encompassed in protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claims.
Claims (5)
1. the unmanned Fixed Wing AirVehicle of high aspect ratio, comprise aircraft, it is characterized by, described aircraft comprises fuselage, wing and tail, described wing comprises host wing, host wing two ends are provided with the slave wing, described host wing is provided with the first reinforced rib mounting hole, second reinforced rib mounting hole, main slotting mounting hole and host wing spar, described host wing spar is provided with locating dowel pin mounting hole, described host wing one end is provided with the first leading edge carbon beam, the other end is provided with the first trailing edge carbon beam, the described slave wing is provided with the first reinforced rib pipe link, second reinforced rib pipe link and secondary wing spar, described secondary wing spar is provided with main slotting pipe link, described master inserts pipe link and is provided with draw-in groove, described draw-in groove by the locating dowel pin mounting hole on locating dowel pin and host wing spar with the use of, the first reinforced rib pipe link on the described slave wing and the first reinforced rib mounting hole on host wing with the use of, the second reinforced rib pipe link on the slave wing and the second reinforced rib mounting hole on host wing with the use of, described slave wing one end is provided with the second leading edge carbon beam, the other end is provided with the second trailing edge carbon beam, described tail comprises elevating rudder, yaw rudder, horizontal tail and vertical fin.
2. as right wants the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio as described in 1, it is characterized by, described host wing comprises the thriving block of main frame, and the slave wing comprises the thriving block of slave, and the thriving block of described main frame is identical with slave thriving block size shape.
3. the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio as claimed in claim 1, is characterized by, and described wing length is 2600mm, and fuselage length is 1200mm.
4. the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio as claimed in claim 1, is characterized by, and the first described reinforced rib pipe link, the second reinforced rib pipe link, main slotting pipe link and locating dowel pin are rectangular configuration.
5. the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio as claimed in claim 1, it is characterized by, described wing is provided with one deck covering.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510703842.8A CN105270603B (en) | 2015-10-27 | 2015-10-27 | A kind of unmanned Fixed Wing AirVehicle of high aspect ratio |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510703842.8A CN105270603B (en) | 2015-10-27 | 2015-10-27 | A kind of unmanned Fixed Wing AirVehicle of high aspect ratio |
Publications (2)
| Publication Number | Publication Date |
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| CN105270603A true CN105270603A (en) | 2016-01-27 |
| CN105270603B CN105270603B (en) | 2018-02-13 |
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| CN201510703842.8A Active CN105270603B (en) | 2015-10-27 | 2015-10-27 | A kind of unmanned Fixed Wing AirVehicle of high aspect ratio |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775105A (en) * | 2016-05-17 | 2016-07-20 | 中国民航大学 | Oil-driven fixed wing aircraft with high load ratio |
| CN106043735A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Rigidity-equivalent wing static gas spring model |
| CN106593948A (en) * | 2016-12-13 | 2017-04-26 | 惠阳航空螺旋桨有限责任公司 | Combined type wing beam blade |
| CN107215451A (en) * | 2017-06-16 | 2017-09-29 | 中电科芜湖通用航空产业技术研究院有限公司 | A kind of wing attachment structure of general-purpose aircraft |
Citations (6)
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|---|---|---|---|---|
| US4739954A (en) * | 1986-12-29 | 1988-04-26 | Hamilton Terry W | Over-lap rib joint |
| CN2401238Y (en) * | 1999-09-16 | 2000-10-18 | 雷虎科技股份有限公司 | Main wing assembling structure for model of airplane |
| CN101214853A (en) * | 2007-12-28 | 2008-07-09 | 北京航空航天大学 | Connecting structure for middle and outside wings of unmanned aerial vehicle |
| CN202429344U (en) * | 2011-11-30 | 2012-09-12 | 中国南方航空工业(集团)有限公司 | Unmanned aerial vehicle |
| CN203698650U (en) * | 2014-01-20 | 2014-07-09 | 谭大刚 | Flexible skin M-shaped aerofoil capable of being quickly unfolded and folded |
| CN205221094U (en) * | 2015-10-27 | 2016-05-11 | 镇江顺宇飞行器有限公司 | Big unmanned fixed wing aircraft of aspect ratio |
-
2015
- 2015-10-27 CN CN201510703842.8A patent/CN105270603B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4739954A (en) * | 1986-12-29 | 1988-04-26 | Hamilton Terry W | Over-lap rib joint |
| CN2401238Y (en) * | 1999-09-16 | 2000-10-18 | 雷虎科技股份有限公司 | Main wing assembling structure for model of airplane |
| CN101214853A (en) * | 2007-12-28 | 2008-07-09 | 北京航空航天大学 | Connecting structure for middle and outside wings of unmanned aerial vehicle |
| CN202429344U (en) * | 2011-11-30 | 2012-09-12 | 中国南方航空工业(集团)有限公司 | Unmanned aerial vehicle |
| CN203698650U (en) * | 2014-01-20 | 2014-07-09 | 谭大刚 | Flexible skin M-shaped aerofoil capable of being quickly unfolded and folded |
| CN205221094U (en) * | 2015-10-27 | 2016-05-11 | 镇江顺宇飞行器有限公司 | Big unmanned fixed wing aircraft of aspect ratio |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775105A (en) * | 2016-05-17 | 2016-07-20 | 中国民航大学 | Oil-driven fixed wing aircraft with high load ratio |
| CN106043735A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Rigidity-equivalent wing static gas spring model |
| CN106593948A (en) * | 2016-12-13 | 2017-04-26 | 惠阳航空螺旋桨有限责任公司 | Combined type wing beam blade |
| CN107215451A (en) * | 2017-06-16 | 2017-09-29 | 中电科芜湖通用航空产业技术研究院有限公司 | A kind of wing attachment structure of general-purpose aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105270603B (en) | 2018-02-13 |
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Effective date of registration: 20201217 Address after: No.2 building, medical machinery industrial park, west section of Daxue Road, Wanfu office, hi tech Zone, Heze City, Shandong Province Patentee after: Shandong Green Kairui Precision Instrument Co.,Ltd. Address before: Building 1, No. 33, Yangzijiang Road, Dagang, Zhenjiang New District, Zhenjiang City, Jiangsu Province Patentee before: ZHENJIANG SHUNYU AIRCRAFT Co.,Ltd. |
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