CN205366065U - Low many rotor crafts of resistance with lift wing section - Google Patents
Low many rotor crafts of resistance with lift wing section Download PDFInfo
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- CN205366065U CN205366065U CN201620136048.XU CN201620136048U CN205366065U CN 205366065 U CN205366065 U CN 205366065U CN 201620136048 U CN201620136048 U CN 201620136048U CN 205366065 U CN205366065 U CN 205366065U
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- aerofoil profile
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- rotor aerocraft
- propeller
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Abstract
The utility model discloses a low many rotor crafts of resistance with lift wing section, many rotor crafts include: unsmooth wing section casing, many rotors wing, carbon beam, motor and screw, unsmooth wing section casing is in many rotor crafts go forward the in -process provides partly lift for aircraft self, avoids the screw of many rotor crafts provides power alone, improves the overall flight time of many rotor crafts, many rotors wing sets up the both sides of unsmooth wing section casing, the central point of carbon beam put with many rotors wing is connected fixedly, the tip of probe rod do not sets up the motor for provide screw power, the screw is connected the motor, the screw sets up to be connected the both ends of the carbon beam of many rotors wing, thus avoid the air current that the screw produced is right useless the hindering that unsmooth wing section casing produced promotes the flight time and the hovering efficiency of many rotor crafts.
Description
Technical field
This utility model relates to a kind of aviation aircraft technical field, particularly a kind of lower resistance multi-rotor aerocraft with lift aerofoil profile.
Background technology
Multi-rotor aerocraft, having can VTOL, flexible, speed and the higher advantage of efficiency.This characteristic makes many rotors be particularly suitable for performing the task such as patrol, supervision in crowded urban district and field with a varied topography.
One of pneumatic design major effect of multi-rotor aerocraft is the aerodynamic arrangement of its fuselage.Owing to gyroplane own load is generally large and rotor has cycle movement, therefore fuselage overall resistance is relatively big, and efficiency is lower than Fixed Wing AirVehicle, and this situation is especially apparent in hovering flight.Therefore, aerodynamic arrangement's design of multi-rotor aerocraft is always to improve the hovering efficiency of aircraft, increase hovering time as an important design object.
Improving the hovering efficiency of multi-rotor aerocraft, simplest mode is through the number of blade increasing the chord length of rotor or increase rotor to improve the dynamical system of many rotors.But, this mode has certain limitation for the lifting of multi-rotor aerocraft hovering efficiency, and for rotor craft, excessive rotor solidity makes rotor rotating speed decline, and the sensitivity of air-flow sinuous flow disturbance to external world raises, and causes that the stationarity of flight declines.Therefore designing suitable rotor profile to improve the hovering time of gyroplane, wherein the design of aerofoil profile is critically important ingredient.
Thus, it is desirable to have a kind of lower resistance multi-rotor aerocraft with lift aerofoil profile can overcome or at least alleviate the drawbacks described above of prior art.
Utility model content
Technical problem to be solved in the utility model is in that to overcome the defect existed in above-mentioned prior art, and provides a kind of lower resistance multi-rotor aerocraft with lift aerofoil profile.
For solving above-mentioned technical problem, a kind of lower resistance multi-rotor aerocraft with lift aerofoil profile of the present utility model, including: concavo-convex aerofoil profile casing, many rotors wing, carbon beam, motor and propeller；
Concavo-convex aerofoil profile casing, described concavo-convex aerofoil profile casing provides a part of lift for aircraft self in described multi-rotor aerocraft advance process, it is to avoid the propeller of described multi-rotor aerocraft individually provides power, improves the overall flight time of 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 is connected fixing with described many rotors wing；
Motor, is respectively provided with motor in the end of described feeler lever, is used for providing propeller power；
Propeller, described propeller connects described motor, described propeller is arranged on the two ends of the carbon beam connecting described many rotors wing, thus the useless resistance avoiding the air-flow that described propeller produces that described concavo-convex aerofoil profile casing is produced, promotes flight time and the hovering efficiency of described multi-rotor aerocraft.
Preferably, described many rotors wing is foldable structure, and when 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, saves big quantity space, carries and more rationally facilitate.
Preferably, described concavo-convex aerofoil profile casing is formed in one structure, and the main load-carrying construction of described concavo-convex aerofoil profile casing is fuselage, and in described concavo-convex aerofoil profile casing, number of parts is less, thus reducing the assembling number of times of part, makes overall structure relatively reliable.
Preferably, described carbon beam is the straight-bar of setting parallel to each other.
This utility model provides a kind of lower resistance multi-rotor aerocraft with lift aerofoil profile, described multi-rotor aerocraft has the fuselage aerodynamic arrangement form of concavo-convex aerofoil profile, multi-rotor aerocraft is made to have lift upwards in flight forward process, so that the overall flight time of multi-rotor aerocraft is longer.
Accompanying drawing illustrates:
Fig. 1 is the structural side view of the lower resistance multi-rotor aerocraft with lift aerofoil profile.
Fig. 2 is the structural front view of the aerofoil profile of the lower resistance multi-rotor aerocraft with lift aerofoil profile.
Fig. 3 is the structural representation during lower resistance multi-rotor aerocraft folded wing with lift aerofoil profile.
Fig. 4 is the structural representation after having the lower resistance multi-rotor aerocraft folded wing of lift aerofoil profile.
Detailed description of the invention:
For the purpose making this utility model implement, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has the element of same or like function from start to finish.Described embodiment is a part of embodiment of this utility model, rather than whole embodiments.The embodiment described below with reference to accompanying drawing is illustrative of, it is intended to be used for explaining this utility model, and it is not intended that to restriction of the present utility model.Based on the embodiment in this utility model, the every other embodiment that those of ordinary skill in the art obtain under not making creative work premise, broadly fall into the scope of this utility model protection.Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail.
In description of the present utility model, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, it is for only for ease of description this utility model and simplifies description, rather than the device of instruction or hint indication or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that restriction to this utility model protection domain
A kind of lower resistance multi-rotor aerocraft with lift aerofoil profile according to this utility model one broad embodiment includes: concavo-convex aerofoil profile casing, many rotors wing, carbon beam, motor and propeller；Described concavo-convex aerofoil profile casing provides a part of lift for aircraft self in described multi-rotor aerocraft advance process, it is to avoid the propeller of described multi-rotor aerocraft individually provides power, improves the overall flight time of described multi-rotor aerocraft；Described many rotors wing is arranged on the both sides of described concavo-convex aerofoil profile casing；The center of described carbon beam is connected fixing with described many rotors wing；It is respectively provided with motor in the end of described feeler lever, is used for providing propeller power；Described propeller connects described motor, described propeller is arranged on the two ends of the carbon beam connecting described many rotors wing, thus the useless resistance avoiding the air-flow that described propeller produces that described concavo-convex aerofoil profile casing is produced, promote flight time and the hovering efficiency of described multi-rotor aerocraft.
As it is shown in figure 1, can the unmanned plane layout of VTOL include: concavo-convex aerofoil profile casing 1, many rotors wing 2, motor cabinet the 3, first carbon beam the 4, second carbon beam 5, fold mechanism 6, many rotors rear chassis 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 casing provides a part of lift for aircraft self in described multi-rotor aerocraft advance process, the propeller avoiding described multi-rotor aerocraft individually provides power, improves the overall flight time of described multi-rotor aerocraft.
In a not shown embodiment, described concavo-convex aerofoil profile casing 1 is formed in one structure, and the main load-carrying construction of described concavo-convex aerofoil profile casing is fuselage, and in described concavo-convex aerofoil profile casing, number of parts is less, thus reducing the assembling number of times of part, make overall structure relatively reliable.
As illustrated in fig. 1 and 2, described many rotors rear chassis 8 is arranged on the afterbody of concavo-convex aerofoil profile casing 1, and many gyroplanes head-shield 9 is arranged on the head of concavo-convex aerofoil profile casing 1, and is provided above GPS baffle plate 10 in the stage casing of concavo-convex aerofoil profile casing 1.
As illustrated in fig. 1 and 2, described many rotors wing 2 is arranged on the left and right sides of described concavo-convex aerofoil profile casing 1.
As it is shown in figure 1, described first carbon beam 4 and linear type carbon beam that the second carbon beam 5 is setting parallel to each other, the center of described first carbon beam 4 and the second carbon beam 5 is connected fixing respectively with described many rotors wing 2.
As it is shown in figure 1, the both ends of described first carbon beam 4 and the second carbon beam 5 are respectively provided with motor cabinet 3, it is used for providing propeller power.
In a not shown embodiment, described propeller connects described motor cabinet, described propeller is arranged on the two ends of the carbon beam connecting described many rotors wing, thus the useless resistance avoiding the air-flow that described propeller produces that described concavo-convex aerofoil profile casing is produced, promote flight time and the hovering efficiency of described multi-rotor aerocraft.
As shown in Figures 3 and 4, described many rotors wing 2 is foldable structure, when described many gyroplanes wingfold, described many rotors wing 2 is folded around mechanism 6 and is folded with, described first carbon beam 4 and the second carbon beam 5 are separately positioned on the both sides of described concavo-convex aerofoil profile casing 1, after described many gyroplanes wingfold, save big quantity space, carry and more rationally facilitate.
Above embodiment of the present utility model is described in detail, but described content has been only preferred embodiment of the present utility model, it is impossible to be considered for limiting practical range of the present utility model.All equalizations made according to this utility model application range change and improvement etc., all should still belong within patent covering scope of the present utility model.
Claims (4)
1. a lower resistance multi-rotor aerocraft with lift aerofoil profile, it is characterised in that including: concavo-convex aerofoil profile casing, many rotors wing, carbon beam, motor and propeller；
Concavo-convex aerofoil profile casing, described concavo-convex aerofoil profile casing provides a part of lift for aircraft self in described multi-rotor aerocraft advance process, it is to avoid the propeller of described multi-rotor aerocraft individually provides power, improves the overall flight time of 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 is connected fixing with described many rotors wing；
Motor, is respectively provided with motor in the end of described feeler lever, is used for providing propeller power；
Propeller, described propeller connects described motor, described propeller is arranged on the two ends of the carbon beam connecting described many rotors wing, thus the useless resistance avoiding the air-flow that described propeller produces that described concavo-convex aerofoil profile casing is produced, promotes flight time and the hovering efficiency of described multi-rotor aerocraft.
2. the lower resistance multi-rotor aerocraft with lift aerofoil profile according to claim 1, it is characterized in that: described many rotors wing is foldable structure, when 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, save big quantity space, carry and more rationally facilitate.
3. the lower resistance multi-rotor aerocraft with lift aerofoil profile according to claim 1, it is characterized in that: described concavo-convex aerofoil profile casing is formed in one structure, the main load-carrying construction of described concavo-convex aerofoil profile casing is fuselage, in described concavo-convex aerofoil profile casing, number of parts is less, thus reducing the assembling number of times of part, make overall structure relatively reliable.
4. the lower resistance multi-rotor aerocraft with lift aerofoil profile according to claim 1, it is characterised in that: described carbon beam is the straight-bar of setting parallel to each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620136048.XU CN205366065U (en) | 2016-02-23 | 2016-02-23 | Low many rotor crafts of resistance with lift wing section |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201620136048.XU CN205366065U (en) | 2016-02-23 | 2016-02-23 | Low many rotor crafts of resistance with lift wing section |
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| CN205366065U true CN205366065U (en) | 2016-07-06 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105584631A (en) * | 2016-02-23 | 2016-05-18 | 天峋创新（北京）科技有限公司 | Low-resistance multi-rotor aircraft with lifting airfoil profile |
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- 2016-02-23 CN CN201620136048.XU patent/CN205366065U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105584631A (en) * | 2016-02-23 | 2016-05-18 | 天峋创新（北京）科技有限公司 | Low-resistance multi-rotor aircraft with lifting airfoil profile |
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