CN105584631A - Low-resistance multi-rotor aircraft with lifting airfoil profile - Google Patents
Low-resistance multi-rotor aircraft with lifting airfoil profile Download PDFInfo
- Publication number
- CN105584631A CN105584631A CN201610099400.1A CN201610099400A CN105584631A CN 105584631 A CN105584631 A CN 105584631A CN 201610099400 A CN201610099400 A CN 201610099400A CN 105584631 A CN105584631 A CN 105584631A
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- aerofoil profile
- rotor
- concavo
- convex
- screw
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 30
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 30
- 238000000034 method Methods 0.000 claims description 6
- 238000010276 construction Methods 0.000 claims description 3
- 244000045947 parasite Species 0.000 abstract 1
- 230000007547 defect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012512 characterization method Methods 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a low-resistance multi-rotor aircraft with a lifting airfoil profile; the multi-rotor aircraft comprises a concave-convex airfoil profile shell, a multi-rotor aerofoil, a carbon rod, motors and a propeller; the concave-convex airfoil profile shell provides partial lift force to an aircraft during advancement of the multi-rotor aircraft, a phenomenon that the power is provided by the propeller of the multi-rotor aircraft alone is avoided, and the whole flight time of the multi-rotor aircraft is increased; the multi-rotor aerofoil is arranged at two sides of the concave-convex airfoil profile shell; the central position of the carbon rod is fixedly connected with the multi-rotor aerofoil; the end parts of the carbon rod are provided with the motors respectively for providing the power for the propeller; the propeller is connected with the motor; and the propeller is arranged at two ends of the carbon rod which is connected with the multi-rotor aerofoil; therefore, the parasite drag to the concave-convex airfoil profile shell, caused by air flows generated by the propeller, is avoided, and the flight time and the hovering efficiency of the multi-rotor aircraft are improved.
Description
Technical field
The present invention relates to a kind of aviation aircraft technical field, particularly a kind of have the low of lift aerofoil profileResistance multi-rotor aerocraft.
Background technology
Multi-rotor aerocraft, having advantages of can VTOL, flexible, speed and efficiency higher.This specific character makes many rotors be particularly suitable for carrying out patrol, prison in crowded urban district and field with a varied topographyDepending on etc. task.
One of pneumatic design major effect of multi-rotor aerocraft is the aerodynamic arrangement of its fuselage. Due to rotorThe general large and rotor of machine self load has the feature of cycle movement, and therefore fuselage overall resistanceGreatly, efficiency is lower than Fixed Wing AirVehicle, and this situation is especially obvious in hovering flight. Therefore,Aerodynamic arrangement's design of multi-rotor aerocraft is always to improve hovering efficiency, the increase hover time of aircraftAs an important design object.
Improve the hovering efficiency of multi-rotor aerocraft, the simplest mode is exactly the chord length by increasing rotorOr the number of blade that increases rotor improves the dynamical system of many rotors. But this mode is for many rotorsThe lifting of aircraft hovering efficiency has certain limitation, and for rotor craft, excessive rotor is realDegree declines gyroplane rotate speed, and the sensitiveness of air-flow sinuous flow disturbance raises to external world, causes the stationarity of flightDecline. Therefore to design the hover time that suitable rotor profile improves gyroplane, wherein establishing of aerofoil profileMeter is very important part.
Therefore, wish that a kind of lower resistance multi-rotor aerocraft with lift aerofoil profile can overcome or extremelyAlleviate less the above-mentioned defect of prior art.
Summary of the invention
Technical problem to be solved by this invention is to overcome the defect existing in above-mentioned prior art, and carriesFor a kind of lower resistance multi-rotor aerocraft with lift aerofoil profile.
For solving the problems of the technologies described above, a kind of many rotors of lower resistance with lift aerofoil profile of the present invention flyRow device, comprising: concavo-convex aerofoil profile casing, many rotors wing, carbon beam, motor and screw;
Concavo-convex aerofoil profile casing, described concavo-convex aerofoil profile casing advances in process at described multi-rotor aerocraftFor aircraft self provides a part of lift, avoid the screw of described multi-rotor aerocraft to carry separatelyFor power, the overall flight time of improving described multi-rotor aerocraft;
Many rotors wing, described many rotors wing is arranged on the both sides of described concavo-convex aerofoil profile casing;
Carbon beam, the center of described carbon beam and described many rotors wing are connected and fixed;
Motor, arranges respectively motor in the end of described feeler lever, for screw power is provided;
Screw, described screw connects described motor, and it is described many that described screw is arranged on connectionThe two ends of the carbon beam of rotor wing, thus avoid the air-flow of described screw generation to described concave-convex wingsThe useless resistance that type casing produces, promotes flight time and the hovering efficiency of described multi-rotor aerocraft.
Preferably, described many rotors wing is foldable structure, in the time of described many gyroplanes wingfold, and instituteState the both sides that carbon beam is arranged on described concavo-convex aerofoil profile casing, after described many gyroplanes wingfold, saveLarge quantity space, it is more convenient to carry.
Preferably, the described concavo-convex aerofoil profile casing structure that is formed in one, the master of described concavo-convex aerofoil profile casingWanting load-carrying construction is fuselage, and in described concavo-convex aerofoil profile casing, number of parts is less, thereby reduces partAssembling number of times, make overall structure more reliable.
Preferably, the straight-bar that described carbon beam is setting parallel to each other.
The invention provides a kind of lower resistance multi-rotor aerocraft with lift aerofoil profile, described many rotors flyRow utensil has the fuselage aerodynamic arrangement form of concavo-convex aerofoil profile, makes multi-rotor aerocraft in flight forwardIn process, there is lift upwards, thereby make the overall flight time of multi-rotor aerocraft longer.
Brief description of the drawings:
Fig. 1 is the structure side view with the lower resistance multi-rotor aerocraft of lift aerofoil profile.
Fig. 2 is the structural front view with the aerofoil profile of the lower resistance multi-rotor aerocraft of lift aerofoil profile.
Fig. 3 is the structural representation while having the lower resistance multi-rotor aerocraft folded wing of lift aerofoil profileFigure.
Fig. 4 is the structural representation having after the lower resistance multi-rotor aerocraft folded wing of lift aerofoil profileFigure.
Detailed description of the invention:
For making object of the invention process, technical scheme and advantage clearer, below in conjunction with the present inventionAccompanying drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the present invention. AttachedIn figure, same or similar label represents same or similar element or has identical or similar from start to finishThe element of function. Described embodiment is the present invention's part embodiment, instead of whole embodiment.Be exemplary below by the embodiment being described with reference to the drawings, be intended to for explaining the present invention, and can notBe interpreted as limitation of the present invention. Based on the embodiment in the present invention, those of ordinary skill in the art are not havingHave and make the every other embodiment obtaining under creative work prerequisite, all belong to the model of the present invention's protectionEnclose. Below in conjunction with accompanying drawing, embodiments of the invention are elaborated.
In description of the invention, it will be appreciated that term " " center ", " longitudinally ", " horizontal strokeTo ", 'fornt', 'back', " left side ", " right side ", " vertically ", " level ",Orientation or the position relationship of the instruction such as " top ", " end " " interior ", " outward " are based on shown in accompanying drawingOrientation or position relationship, be only the present invention for convenience of description and simplified characterization, instead of instruction orThe device of hint indication or element must have specific orientation, construct and operation with specific orientation,Therefore can not be interpreted as limiting the scope of the invention
A kind of lower resistance multi-rotor aerocraft with lift aerofoil profile of one wide in range embodiment according to the present inventionComprise: concavo-convex aerofoil profile casing, many rotors wing, carbon beam, motor and screw; Described concave-convex wingsType casing in described multi-rotor aerocraft advances process for aircraft self provides a part of lift,Avoid the screw of described multi-rotor aerocraft that power is provided separately, improve described multi-rotor aerocraftThe overall flight time; Described many rotors wing is arranged on the both sides of described concavo-convex aerofoil profile casing; InstituteCenter and the described many rotors wing of stating carbon beam are connected and fixed; In the end of described feeler lever differenceMotor is set, for screw power is provided; Described screw connects described motor, described spiralOar is arranged on the two ends of the carbon beam that connects described many rotors wing, thereby avoids described screw to produceAir-flow useless resistance that described concavo-convex aerofoil profile casing is produced, promote the flight of described multi-rotor aerocraftTime and hovering efficiency.
As shown in Figure 1, unmanned plane layout that can VTOL comprises: concavo-convex aerofoil profile casing 1, revolve moreWing wing 2, motor cabinet 3, the first carbon beam 4, the second carbon beam 5, fold mechanism 6, many rotors casingBonnet 8, many gyroplanes head-shield 9 and GPS baffle plate 10.
As shown in Figure 1, described concavo-convex aerofoil profile casing 1 is concavo-convex aerofoil profile, described concavo-convex aerofoil profile casingIn advancing process, described multi-rotor aerocraft for aircraft self provides a part of lift, avoids instituteThe screw of stating multi-rotor aerocraft provides separately power, improves the overall of described multi-rotor aerocraftFlight time.
In a not shown embodiment, described concavo-convex aerofoil profile casing 1 structure that is formed in one, described inThe main load-carrying construction of concavo-convex aerofoil profile casing is fuselage, and in described concavo-convex aerofoil profile casing, number of partsFew, thus the assembling number of times of minimizing part makes overall structure more reliable.
As illustrated in fig. 1 and 2, described many rotors rear chassis 8 is arranged on concavo-convex aerofoil profile casing 1Afterbody, many gyroplanes head-shield 9 is arranged on the head of concavo-convex aerofoil profile casing 1, and in concavo-convex aerofoil profileThe top, stage casing of casing 1 arranges GPS baffle plate 10.
As illustrated in fig. 1 and 2, described many rotors wing 2 is arranged on described concavo-convex aerofoil profile casing 1The left and right sides.
As shown in Figure 1, the straight line that described the first carbon beam 4 and the second carbon beam 5 are setting parallel to each otherType carbon beam, the center of described the first carbon beam 4 and the second carbon beam 5 respectively with described many gyroplanesThe wing 2 is connected and fixed.
As shown in Figure 1, the both ends of described the first carbon beam 4 and the second carbon beam 5 arrange respectively motorSeat 3, for providing screw power.
In a not shown embodiment, described screw connects described motor cabinet, and described screw is establishedPut at the two ends of the carbon beam of the described many rotors wing of connection, thus the gas of avoiding described screw to produceFlow the useless resistance that described concavo-convex aerofoil profile casing is produced, promote the flight time of described multi-rotor aerocraftAnd hovering efficiency.
As shown in Figures 3 and 4, described many rotors wing 2 is foldable structure, when described many gyroplanesWhen wingfold, described many rotors wing 2 is folded with around fold mechanism 6, and described firstCarbon beam 4 and the second carbon beam 5 are separately positioned on the both sides of described concavo-convex aerofoil profile casing 1, described revolve moreAfter wing wing-folding, save large quantity space, it is more convenient to carry.
Above embodiments of the invention are had been described in detail, but described content is only of the present invention betterEmbodiment, can not be considered to for limiting practical range of the present invention. Allly do according to the present patent application scopeEqualization change with improve etc., within all should still belonging to patent covering scope of the present invention.
Claims (4)
1. a lower resistance multi-rotor aerocraft with lift aerofoil profile, is characterized in that, comprising:Concavo-convex aerofoil profile casing, many rotors wing, carbon beam, motor and screw;
Concavo-convex aerofoil profile casing, described concavo-convex aerofoil profile casing advances in process at described multi-rotor aerocraftFor aircraft self provides a part of lift, avoid the screw of described multi-rotor aerocraft to carry separatelyFor power, the overall flight time of improving described multi-rotor aerocraft;
Many rotors wing, described many rotors wing is arranged on the both sides of described concavo-convex aerofoil profile casing;
Carbon beam, the center of described carbon beam and described many rotors wing are connected and fixed;
Motor, arranges respectively motor in the end of described feeler lever, for screw power is provided;
Screw, described screw connects described motor, and it is described many that described screw is arranged on connectionThe two ends of the carbon beam of rotor wing, thus avoid the air-flow of described screw generation to described concave-convex wingsThe useless resistance that type casing produces, promotes flight time and the hovering efficiency of described multi-rotor aerocraft.
2. according to the lower resistance multi-rotor aerocraft with lift aerofoil profile described in claim 1,It is characterized in that: described many rotors wing is foldable structure, in the time of described many gyroplanes wingfold,Described carbon beam is arranged on the both sides of described concavo-convex aerofoil profile casing, after described many gyroplanes wingfold, and jointEconomize large quantity space, it is more convenient to carry.
3. according to the lower resistance multi-rotor aerocraft with lift aerofoil profile described in claim 1,It is characterized in that: the described concavo-convex aerofoil profile casing structure that is formed in one, described concavo-convex aerofoil profile casingMain load-carrying construction is fuselage, and in described concavo-convex aerofoil profile casing, number of parts is less, thereby reduces zeroThe assembling number of times of part, makes overall structure more reliable.
4. according to the lower resistance multi-rotor aerocraft with lift aerofoil profile described in claim 1,It is characterized in that: the straight-bar that described carbon beam is setting parallel to each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610099400.1A CN105584631A (en) | 2016-02-23 | 2016-02-23 | Low-resistance multi-rotor aircraft with lifting airfoil profile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610099400.1A CN105584631A (en) | 2016-02-23 | 2016-02-23 | Low-resistance multi-rotor aircraft with lifting airfoil profile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105584631A true CN105584631A (en) | 2016-05-18 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610099400.1A Pending CN105584631A (en) | 2016-02-23 | 2016-02-23 | Low-resistance multi-rotor aircraft with lifting airfoil profile |
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| CN (1) | CN105584631A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106586001A (en) * | 2016-11-30 | 2017-04-26 | 中国电子科技集团公司第三十八研究所 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
| CN107585300A (en) * | 2017-08-28 | 2018-01-16 | 天峋（常州）智能科技有限公司 | A kind of undercarriage has the multi-rotor unmanned aerial vehicle of lift aerofoil profile |
| CN112009668A (en) * | 2019-11-01 | 2020-12-01 | 成都翼展展科技有限公司 | Aircraft |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN85104530A (en) * | 1985-06-15 | 1987-01-07 | 古飞 | Controllable wing-folded full-lift type road airplane |
| EP0282107A1 (en) * | 1987-02-12 | 1988-09-14 | Martinus Cornelis Gosen | Aeroplane or model aeroplane |
| CN1137998A (en) * | 1995-06-15 | 1996-12-18 | 刘世英 | Finless and vertical landing wing jet aero-plane |
| CN1816476A (en) * | 2003-05-05 | 2006-08-09 | 敏捷思有限责任公司 | Aircraft with a lift-generating fuselage |
| CN103043212A (en) * | 2011-10-17 | 2013-04-17 | 田瑜 | Combined aircraft composed of fixed wing and electric multi-rotor wing |
| CN104986321A (en) * | 2015-07-10 | 2015-10-21 | 哈瓦国际航空技术（深圳）有限公司 | Integrated aircraft body |
| CN204895853U (en) * | 2015-08-28 | 2015-12-23 | 武汉捷特航空科技有限公司 | Compound aircraft that stationary vane and deformable electronic many rotors are constituteed |
| CN205366065U (en) * | 2016-02-23 | 2016-07-06 | 天峋创新（北京）科技有限公司 | Low many rotor crafts of resistance with lift wing section |
-
2016
- 2016-02-23 CN CN201610099400.1A patent/CN105584631A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN85104530A (en) * | 1985-06-15 | 1987-01-07 | 古飞 | Controllable wing-folded full-lift type road airplane |
| EP0282107A1 (en) * | 1987-02-12 | 1988-09-14 | Martinus Cornelis Gosen | Aeroplane or model aeroplane |
| CN1137998A (en) * | 1995-06-15 | 1996-12-18 | 刘世英 | Finless and vertical landing wing jet aero-plane |
| CN1816476A (en) * | 2003-05-05 | 2006-08-09 | 敏捷思有限责任公司 | Aircraft with a lift-generating fuselage |
| CN103043212A (en) * | 2011-10-17 | 2013-04-17 | 田瑜 | Combined aircraft composed of fixed wing and electric multi-rotor wing |
| CN104986321A (en) * | 2015-07-10 | 2015-10-21 | 哈瓦国际航空技术（深圳）有限公司 | Integrated aircraft body |
| CN204895853U (en) * | 2015-08-28 | 2015-12-23 | 武汉捷特航空科技有限公司 | Compound aircraft that stationary vane and deformable electronic many rotors are constituteed |
| CN205366065U (en) * | 2016-02-23 | 2016-07-06 | 天峋创新（北京）科技有限公司 | Low many rotor crafts of resistance with lift wing section |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106586001A (en) * | 2016-11-30 | 2017-04-26 | 中国电子科技集团公司第三十八研究所 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
| CN107585300A (en) * | 2017-08-28 | 2018-01-16 | 天峋（常州）智能科技有限公司 | A kind of undercarriage has the multi-rotor unmanned aerial vehicle of lift aerofoil profile |
| CN112009668A (en) * | 2019-11-01 | 2020-12-01 | 成都翼展展科技有限公司 | Aircraft |
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| C06 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160518 |
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| RJ01 | Rejection of invention patent application after publication |