CN208102325U - Power wing body multi-rotor unmanned aerial vehicle - Google Patents
Power wing body multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN208102325U CN208102325U CN201820241786.XU CN201820241786U CN208102325U CN 208102325 U CN208102325 U CN 208102325U CN 201820241786 U CN201820241786 U CN 201820241786U CN 208102325 U CN208102325 U CN 208102325U
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- fuselage
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- aerial vehicle
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Abstract
The utility model discloses a kind of power wing body multi-rotor unmanned aerial vehicles, its key points of the technical solution are that including fuselage and the rotor power group for being mounted on fuselage two sides, fuselage is integrally in winglike, the tail end of fuselage is equipped with fixed-wing power packages, reach and reduced power consumption in flight course, has increased the purpose of voyage.
Description
Technical field
The utility model relates to a kind of unmanned plane, in particular to a kind of power wing body multi-rotor unmanned aerial vehicle.
Background technique
UAV is referred to as " unmanned plane "（"UAV"）, it is to utilize radio robot and the process control provided for oneself
The not manned vehicle of device manipulation.Unmanned plane is actually the general designation of unmanned vehicle, can be with from technical standpoint definition
It is divided into：Fixed wing aircraft, unmanned VTOL aircraft, multi-rotor unmanned aerial vehicle etc..
Existing multi-rotor unmanned aerial vehicle can refer to the patent that notification number is CN206231620U, and a kind of unmanned plane includes machine
Body, with the affixed front wing of fuselage and rear wing, be mounted on the fixed-wing power packages of end and be mounted on fuselage side rotor it is dynamic
Power group.It is can be convenient by rotor power group so that the vertical landing of unmanned plane, and can certain journey by fixed-wing power packages
The power of advance is provided on degree, provides the lift of unmanned plane entirety by rotor power group in flight course at this time；Certainly,
Have by unmanned aerial vehicle design in the form of similar existing large aircraft, in the side of fuselage, setting provides the wing of lift.Above
Design, only larger by rotor power group offer lift power consumption in the case where the energy that unmanned plane itself carries is certain, shadow
Ring voyage；And directly wing is installed additional in fuselage side, the self weight of unmanned plane itself is increased, in contrast also can in flight course
Increasing electric quantity consumption influences voyage in the case where the energy is certain.
Utility model content
The purpose of the utility model is to provide a kind of power wing body multi-rotor unmanned aerial vehicles, its advantage is that subtracting in flight course
Small power consumption increases voyage.
The above-mentioned technical purpose of the utility model technical scheme is that：A kind of power wing body mostly rotation
Wing unmanned plane including fuselage and is mounted on the rotor power groups of fuselage two sides, and fuselage is integrally in winglike, the tail end peace of fuselage
Equipped with fixed-wing power packages.
It by using above-mentioned technical proposal, can be vertically moved up or down by rotor power group, and pass through fixed-wing power packages
Forward thrust is provided, during flight, due to the winglike structure of fuselage, in the case where there is certain speed, due to
The difference of fuselage air velocity up and down, directly to the certain upward lift of fuselage, in this way unmanned plane during flight
Lift is not all that rotor power group is needed to provide, and does not also need additionally to increase wing on fuselage, not will increase self weight, is flying
More energy saving in the process, in the case where the energy is certain, voyage is longer；And fixed-wing power packages are arranged in tail end, rather than set
It sets in front end, is arranged after front end air-flow first passes through fixed-wing power packages using fuselage, the problem of air-flow is easy to appear disorder,
It is easy to influence fuselage offer lift, and is arranged and does not allow to be also easy to produce problem above at rear.
Preferably, setting and empennage, empennage and fuselage tail end are fixed between the tail end and fixed-wing power packages of fuselage.
By using above-mentioned technical proposal, the posture that empennage facilitates control to fly, when flight is more stable.
Preferably, fuselage includes rack and the casing that is covered on outside rack, casing upper surface arches upward to form circle upwards
Cambered surface, casing following table arch upward to form lower arc surface upwardly, and the radian of upper arc surface is less than the radian of lower arc surface.
By using above-mentioned technical proposal, certain lift is provided for fuselage, while reducing windage.
Preferably, the junction of upper arc surface front end and lower arc surface front end is formed with arc transition section.
By using above-mentioned technical proposal, windage is further decreased.
Preferably, rack is grid-shaped, it is internal to form object placing cavity.
By using above-mentioned technical proposal, object placing cavity facilitates the objects such as electric wire to place, while mitigating overall weight.
Preferably, offering lightening hole in rack.
By using above-mentioned technical proposal, further mitigate overall weight, lowers energy consumption.
Preferably, rotor power group includes being transversely mounted bar and setting in fuselage two sides through fuselage in the width direction
Vertical mounting rod, the both ends for being transversely mounted bar are affixed with vertical mounting rod respectively, and the both ends of vertical mounting rod are respectively arranged with
Rotor.
By using above-mentioned technical proposal so that be transversely mounted bar connected with fuselage it is more abundant, be transversely mounted bar company
Connect stabilization more.
Preferably, fuselage includes fuselage main body and the Auxiliary support portion for being fixed in fuselage main body two sides, Auxiliary support portion
Between two rotors adjacent positioned at front and back, the corner for rotor rotational is formed between Auxiliary support portion and fuselage main body, laterally
Mounting rod passes through Auxiliary support portion.
By using above-mentioned technical proposal, Auxiliary support portion is close to vertical mounting rod, so that the less bar that is transversely mounted stays
In outside, be transversely mounted bar connected with fuselage it is more abundant, it is relatively stable.
Preferably, corner is provided with reinforcer, reinforcer is affixed with fuselage main body and Auxiliary support portion respectively.
By using above-mentioned technical proposal, so that fuselage main body connects stabilization more with Auxiliary support portion.
Preferably, the bottom of fuselage is connected with support leg, the lower end of support leg and the tail end of fuselage form a support
Plane.
By using above-mentioned technical proposal, more steady when unmanned plane is placed.
In conclusion the utility model has the advantages that：1, reduce power consumption in the process, increase voyage；2, subtract
Light dead-weight is further reduced energy consumption；3, by support leg unmanned plane is parked steadily.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of embodiment one；
Fig. 2 is the side view of embodiment one；
Fig. 3 is the schematic diagram of internal structure of embodiment one；
Fig. 4 is the structural schematic diagram of embodiment two；
Fig. 5 is the schematic diagram of internal structure of embodiment two；
Fig. 6 is the side view of embodiment three.
In figure, 1, fuselage；11, upper arc surface；12, lower arc surface；13, arc transition section；14, casing；15, rack；
151, lightening hole；152, object placing cavity；16, fuselage main body；17, Auxiliary support portion；18, reinforcer；2, rotor power group；21, horizontal
To mounting rod；22, vertical mounting rod；23, rotor；3, fixed-wing power packages；4, empennage；5, support leg.
Specific embodiment
The utility model is described in further detail below in conjunction with attached drawing.The wherein identical attached drawing of identical components
Label indicates.It should be noted that word "front", "rear" used in the following description, "left", "right", "upper", "lower", " bottom
Face " and " top surface " refer to that the direction in attached drawing, word "inner" and "outside" are referred respectively to towards or away from particular elements geometry
The direction at center.
Embodiment one
As shown in Figure 1, a kind of power wing body multi-rotor unmanned aerial vehicle, including fuselage 1, rotor power group 2, empennage 4 and fixation
Wing power packages 3, rotor power group 2 are mounted on the two sides of fuselage 1, and empennage 4 is fixed on the tail end of fuselage 1, and fixed rotor is mounted on
The tail end of fuselage 1 and the rear for being located at empennage 4.Upward lift can be provided by rotor power group 2, facilitate VTOL,
And fixed-wing power packages 3 provide the forward thrust of unmanned plane.
In conjunction with Fig. 2, whole fuselage 1 is in airfoil, and the curve in 1 section of fuselage can directly simulate the song of actual airplane wing
Line, only reduced scale.In conjunction with Fig. 3, fuselage 1 includes rack 15 and casing 14, and casing 14 is covered on the surface of rack 15, and
Inside organic frame 15 is bonded.The upper surface of casing 14 arches upward to form arc surface 11 upwards, and 14 following table of casing arches upward upwardly
Lower arc surface 12 is formed, the radian of upper arc surface 11 is less than the radian of lower arc surface 12.Upper 11 front end of arc surface and lower arc surface
The junction of 12 front ends is formed with arc transition section 13, further decreases grouping, reduces energy consumption.
In the unmanned plane during flying of the utility model, due to providing forward power using the fixed-wing power packages 3 of tail end, make
Flight attitude when obtaining unmanned plane during flying is in parallel posture.Compared to the unmanned plane for only using more rotors, more rotations are only used
The unmanned aerial vehicle body 1 of the wing needs to turn forward certain angle, provides forward power by more rotors, 1 meeting of fuselage when inclination
Certain resistance is generated, while providing forward power plus more rotors, it is easier to consume the energy.And use the fuselage of airfoil
1, the streamlined of fuselage 1 also reduces windage on the basis of horizontal flight, improves flying speed, also reduces to a certain extent
Energy consumption.It is certain having due to the design of 1 self structure of fuselage and while fixed-wing power packages 3 provide first forward thrust
In the case where speed, air-flow is different by the flow velocity of the air-flow of about 1 fuselage, generates certain upward lift, certainly, speed is got over
High-lift is bigger；That is, during unmanned plane during flying, the speed conversion provided by fixed-wing power packages 3 is in
In contrast upward lift, rotor power group 2 can reduce the output of energy, ensure that the cruising ability of unmanned plane, in energy
In the case that amount is certain, voyage is longer.
And in order to further decrease the consumption of energy, in conjunction with Fig. 3, rack 15 is grid-shaped, inside be formed with object placing cavity
152, the objects such as electric wire can be placed in object placing cavity 152.In order to further mitigate weight, lightening hole can be opened up in rack 15
151, mitigate whole weight, reduces energy consumption.
As shown in figure 3, rotor power group 2 includes rotor 23, is transversely mounted bar 21 and vertical mounting rod 22, it is transversely mounted bar
21 pass through fuselage 1 along the width direction of fuselage 1, and both ends are stretched out outside fuselage 1, and vertical mounting rod 22 is two, are respectively and fixedly connected with
At the both ends for being transversely mounted bar 21, it is the affixed stabilization of vertical mounting rod 22, is transversely mounted bar 21 also and can be set two.Rotor 23
Can there are four, the both ends for the vertical mounting rod 22 installed respectively are transversely mounted bar 21 and to connect with fuselage 1 across fuselage 1
It is more substantially stabilized.
Embodiment two
In order to further ensure being transversely mounted the stabilization of bar 21 more, as shown in Figure 4 and Figure 5, fuselage 1 includes fuselage main body
16 and be fixed in the Auxiliary support portions 17 of 16 two sides of fuselage main body, Auxiliary support portion 17 for fuselage main body 16 more
Close to vertical mounting rod 22, bar 21 is transversely mounted across Auxiliary support portion 17, the support of bar 21 is more abundant to being transversely mounted, together
When also increase to a certain extent inside fuselage 1 place article space.In order not to interfere the rotation of rotor, Auxiliary support portion 17
Between two rotors adjacent positioned at front and back, the corner for rotor rotational is formed between Auxiliary support portion 17 and fuselage main body 16,
Space has been conceded to rotor rotational in the space of corner.
And it is provided with reinforcer 18 in order to assist mounting portion and fuselage main body 16 to connect more firm stable, corner,
Reinforcer 18 is affixed with fuselage main body 16 and Auxiliary support portion 17 respectively.
Embodiment three
In conjunction with Fig. 6, in order to which unmanned plane is parked more stable, the bottom of fuselage 1 is connected with support leg 5, under support leg 5
The tail end of end and fuselage 1 forms a supporting plane, it is of course also possible in the tail end Design assistant support leg 5 of fuselage 1.
This specific embodiment is only the explanation to the utility model, is not limitations of the present invention, ability
Field technique personnel can according to need the modification that not creative contribution is made to the present embodiment after reading this specification, but
As long as all by the protection of Patent Law in the scope of the claims of the utility model.
Claims (9)
1. a kind of power wing body multi-rotor unmanned aerial vehicle, including fuselage (1) and it is mounted on the rotor power groups of fuselage (1) two sides
(2), it is characterised in that：Integrally in winglike, the tail end of fuselage (1) is equipped with fixed-wing power packages (3) fuselage (1), and rotor is dynamic
Power group (2) includes being transversely mounted bar (21) and setting in the vertical peace of fuselage (1) two sides through fuselage (1) in the width direction
It fills bar (22), the both ends for being transversely mounted bar (21) are affixed with vertical mounting rod (22) respectively, the both ends point of vertical mounting rod (22)
It is not provided with rotor (23).
2. power wing body multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：The tail end of fuselage (1) and fixation
Setting and empennage (4) between wing power packages (3), empennage (4) and fuselage (1) tail end are fixed.
3. power wing body multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：Fuselage (1) includes rack (15)
And it is covered on the casing (14) of rack (15) outside, casing (14) upper surface arches upward to form arc surface (11), casing upwards
(14) following table arches upward to be formed lower arc surface (12) upwardly, and the radian of upper arc surface (11) is less than the radian of lower arc surface (12).
4. power wing body multi-rotor unmanned aerial vehicle according to claim 3, it is characterised in that：Upper arc surface (11) front end is under
The junction of arc surface (12) front end is formed with arc transition section (13).
5. power wing body multi-rotor unmanned aerial vehicle according to claim 3, it is characterised in that：Rack (15) is grid-shaped,
Inside forms object placing cavity (152).
6. power wing body multi-rotor unmanned aerial vehicle according to claim 3, it is characterised in that：Rack offers loss of weight on (15)
Hole (151).
7. power wing body multi-rotor unmanned aerial vehicle according to claim 2, it is characterised in that：Fuselage (1) includes fuselage main body
(16) and it is fixed in the Auxiliary support portion (17) of fuselage main body (16) two sides, Auxiliary support portion (17) are located at adjacent two in front and back
Between rotor, it is formed with the corner for rotor rotational between Auxiliary support portion (17) and fuselage main body (16), is transversely mounted bar
(21) Auxiliary support portion (17) are passed through.
8. power wing body multi-rotor unmanned aerial vehicle according to claim 7, it is characterised in that：Corner is provided with reinforcer
(18), reinforcer (18) is affixed with fuselage main body (16) and Auxiliary support portion (17) respectively.
9. power wing body multi-rotor unmanned aerial vehicle according to claim 1, it is characterised in that：The bottom of fuselage (1) is connected with
Support leg (5), the lower end of support leg (5) and the tail end of fuselage (1) form a supporting plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820241786.XU CN208102325U (en) | 2018-02-09 | 2018-02-09 | Power wing body multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820241786.XU CN208102325U (en) | 2018-02-09 | 2018-02-09 | Power wing body multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208102325U true CN208102325U (en) | 2018-11-16 |
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ID=64124994
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820241786.XU Expired - Fee Related CN208102325U (en) | 2018-02-09 | 2018-02-09 | Power wing body multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208102325U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108248847A (en) * | 2018-02-09 | 2018-07-06 | 北京白米科技有限公司 | Power wing body multi-rotor unmanned aerial vehicle |
| CN110481768A (en) * | 2019-09-01 | 2019-11-22 | 西安长峰机电研究所 | Four axis rotor tilting rotor solar energy unmanned planes |
-
2018
- 2018-02-09 CN CN201820241786.XU patent/CN208102325U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108248847A (en) * | 2018-02-09 | 2018-07-06 | 北京白米科技有限公司 | Power wing body multi-rotor unmanned aerial vehicle |
| CN110481768A (en) * | 2019-09-01 | 2019-11-22 | 西安长峰机电研究所 | Four axis rotor tilting rotor solar energy unmanned planes |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20181116 Termination date: 20220209 |
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| CF01 | Termination of patent right due to non-payment of annual fee |