CN207450227U - A kind of dynamic unmanned plane undercarriage of oil - Google Patents
A kind of dynamic unmanned plane undercarriage of oil Download PDFInfo
- Publication number
- CN207450227U CN207450227U CN201721477007.8U CN201721477007U CN207450227U CN 207450227 U CN207450227 U CN 207450227U CN 201721477007 U CN201721477007 U CN 201721477007U CN 207450227 U CN207450227 U CN 207450227U
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- oil
- undercarriage
- fuselage
- axis
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
A kind of dynamic unmanned plane undercarriage of oil, for being mounted on the lower section of the fuselage of the dynamic unmanned plane of oil, there are one longitudinal asymmetric axis for the fuselage tool of the dynamic unmanned plane of oil.The undercarriage includes two identical arched members and two identical cross bars, the head of the unmanned plane and the lower part of tail are respectively arranged with an arched member, the arched member has compared with the axis of symmetry symmetrical structure, and there are one the cross bars for the end connection of two arched members positioned at the same side of the axis of symmetry.The arched member of the undercarriage of the application employs symmetrical structure, and left and right is connected as one, so that the undercarriage of unmanned plane both sides is the structure to link into an integrated entity in fact, the undercarriage of integral structure inherently possesses reinforcing property, because without setting the structure particularly strengthened the tie point of undercarriage on fuselage, the construction weight of unmanned plane is reduced, improves the load level of unmanned plane.
Description
Technical field
The utility model is related to unmanned air vehicle technique fields more particularly to a kind of oil of more rotors to move unmanned plane, more particularly to
Landing gear structure available for the dynamic unmanned plane of oil.
Background technology
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Unmanned plane press application field, can be divided into it is military with it is civilian.Military aspect, unmanned plane are divided into reconnaissance plane and target
Machine.Civilian unmanned plane take photo by plane, agricultural, plant protection, miniature self-timer, express transportation, disaster relief, observation wild animal, monitoring pass
It catches an illness, survey and draw, news report, electric inspection process, the disaster relief, the fields such as movies-making are widely used.
Existing multi-rotor unmanned aerial vehicle is usually electronic unmanned plane.The structure of more electronic unmanned planes of rotor is simply easily fabricated,
Motor is light-weight, stability of rotation, and dynamical system is easy to standardize, thus complete machine is relatively easy to manipulate, and flight low noise,
Develop in short voyage civil field more active.Yet with battery energy density well below fuel oil, electronic unmanned plane by
To the limitation of battery, voyage is shorter, and load level is relatively low, can not be applied to military big load scout-attack field.It is and existing
The fuel oil unmanned plane generally use of long voyage fixes wing structure, and landing of taking off is limited be subject to airport, can not be hovered, and cost is high,
Manipulate cumbersome, the flexible property used is inadequate.
106697278 A of CN disclose that a kind of direct-drive type oil is dynamic to determine rotating speed feather multi-rotor unmanned aerial vehicle, including fuselage,
Dynamical system, undercarriage and avionics system, the fuselage are the integrated fuselage of full material again, and the dynamical system is by starting
Machine system, pitch-variable system, oil supply system and rotor system composition, the undercarriage are skid landing gear, are set thereon
Flexible lifting position, with the different task device that is connected.The oil of the above-mentioned prior art moves six rotors of unmanned plane angularly
It is set intermittently around body, causes the application load carried on body that can only be arranged at immediately below body, and due to all directions
All being stopped be subject to rotor, the load of carrying can only carry out downwards operation, weapon delivery or can not be observed obliquely upward,
Low there are load level, topology layout is unreasonable, it is difficult to which the defects of playing control and the security advantages of unmanned plane limits rotor
Unmanned aerial vehicle is in military and monitoring field development and application.
205998123 U of CN disclose a kind of vertical layout fuel power quadrotor flying platform, and composition includes machine
Frame, dynamical system, navigation and control system, electrical system and task platform.Four identical horns are docked at are connected with two-by-two
Rack is formed on the monocogue of undercarriage；Dynamical system is arranged on the end of each horn, and power is provided for flying platform
And the energy；Navigation and control system perceive and control posture, height and the position of flying platform；Electrical system, which has, to charge, supplies
Electricity and instruction function；Task platform is used to install different task devices.The oil of the prior art moves unmanned plane, and there is provided four
Independent engine, the mutual interference in air flow of adjacent rotor are difficult to mediate, and the spacing of greater engine can be increased further
Volume and weight.
The oil of the above-mentioned prior art moves unmanned plane, and an oil is configured on each cantilever and moves engine, exposed engine
In addition the noise of rotor, causes unmanned plane that cannot almost be used in city spatial domain, used under military environment and also without nothing hidden
Property.The balance of jib-length and weight so that the selection face very little of the dynamic engine of oil, the power of every engine cannot be too big,
Lift is limited, and the ability for carrying payload is extremely limited.In addition the oil of the above-mentioned prior art moves rising and falling for unmanned plane
Frame has all had both carry function, it is caused to be difficult to remove the volume for reducing unmanned plane, simultaneously because needing to consider carry, has caused
Falling the construction weight of frame increases so that the deadweight of unmanned plane is excessive, and the carrying ability of load is extremely limited.
Utility model content
The technical problem to be solved by the present invention is to provide a kind of dynamic unmanned plane undercarriage of oil, front is reduced or avoided
The problem of being previously mentioned.
In order to solve the above technical problems, the utility model proposes a kind of dynamic unmanned plane undercarriage of oil, for being mounted on oil
The lower section of the fuselage of dynamic unmanned plane, the fuselage connection of the dynamic unmanned plane of oil is there are four cantilever, there are one each cantilever supports
The rotor of same diameter, the fuselage tool is there are one longitudinal asymmetric axis, and the cantilever is with perpendicular to the side of the axis of symmetry
Formula is protruding from the fuselage, and each cantilevered distal end supports that there are one the identical annulus of the shape around the rotor
The kuppe of shape, wherein, the undercarriage includes two identical arched members and two identical cross bars, the machine of the unmanned plane
The lower part of head and tail is respectively arranged with an arched member, and the arched member has symmetrical compared with the axis of symmetry
Structure, positioned at the same side of the axis of symmetry two arched members end connection there are one the cross bar.
Preferably, described two cross bars are set parallel to the axis of symmetry.
Preferably, the vertical plane of described two arched members is mutually parallel.
Preferably, the axis of symmetry is perpendicular to the vertical plane of described two arched members.
Preferably, the end of the arched member is connected to the both ends of the cross bar by a connecting sleeve respectively.
Preferably, the connecting sleeve is tee-joint sleeve form, and the upper end is connected with the arched member, lower end one side and institute
It states cross bar to be connected, lower end opposite side is connected with a upper curved casing.
Preferably, there are one acute angles beta, the acute angles with horizontal plane formation for the end that the arched member is connected with the cross bar
The angular range of β is 50-70 degree.
Preferably, the arched member of the undercarriage moves the lower part carry curvature of space of unmanned plane one around the oil
It is stretched out obliquely after radian.
Preferably, it is socketed with yielding rubber pipe on the cross bar.
The arched member of the undercarriage of the application employs symmetrical structure, and left and right is connected as one, so that
The undercarriage of unmanned plane both sides is the structure to link into an integrated entity in fact, and the undercarriage of integral structure inherently possesses reinforcement
Can, because without setting the structure particularly strengthened the tie point of undercarriage on fuselage, reducing the knot of unmanned plane
Structure weight improves the load level of unmanned plane.In addition the application uses the structure of the arched member of the integral structure of simple function
Design, undercarriage does not also serve as carry platform, thus can also further reduce the rigidity of undercarriage, when can be unmanned plane landing
Certain buffering is provided, body is avoided to damage.
In addition, in addition to oliquely downward stretching to increase carry space by the arched member of undercarriage, also set by radian
Meter, has further conceded horizontal carry space, thus can provide broader longitudinal carry passage, can longitudinally be obtained in fuselage
Larger range of load mount point is easy to extend load layout.The bending radian of arched member also avoids straight line dog-ear simultaneously, carries
The high fatigue-resistance characteristics of structure.
Description of the drawings
The following drawings is only intended in doing schematic illustration and explanation to the utility model, does not limit the model of the utility model
It encloses.Wherein,
Fig. 1 be shown a specific embodiment according to the present utility model oil move unmanned plane stereochemical structure signal
Figure；
The bottom view of the dynamic unmanned plane of oil shown in Fig. 1 is shown in Fig. 2；
The oil that another specific embodiment according to the present utility model is shown in Fig. 3 moves the three-dimensional knot of unmanned plane undercarriage
Structure schematic diagram；
The decomposition diagram of the dynamic unmanned plane undercarriage of oil shown in Fig. 3 is shown in Fig. 4.
Specific embodiment
For a clearer understanding of the technical features, objectives and effects of the utility model, existing control description of the drawings
Specific embodiment of the present utility model.Wherein, identical component uses identical label.
Just it has been observed that the dynamic unmanned plane of existing oil is laid out mostly using holohedral symmetry, position of centre of gravity is caused to converge, load
Layout is extremely limited, and since the rotor of holohedral symmetry layout all blocks all directions of unmanned plane, causes to carry
Load weapon delivery or can not be observed obliquely upward, limit the application range of existing unmanned plane.In addition adjacent rotation
The wing is between each other there are interference in air flow, and main screw lift can be increased by extending jib-length, and the ability for carrying payload is subject to greatly
Limitation.
To solve drawbacks described above, this application provides a kind of oil to move unmanned plane, as shown in Figs. 1-2, wherein, what Fig. 1 was shown
It is that the oil of a specific embodiment according to the present utility model moves the dimensional structure diagram of unmanned plane；Fig. 1 institutes are shown in Fig. 2
Show the bottom view of the dynamic unmanned plane of oil.
Referring to Fig. 1-2, the oil of the application, which moves unmanned plane, includes fuselage 1,2, four cantilevers 3 of undercarriage and four rotors 5,
Fuselage 1 connects four cantilevers 3, and each cantilever 3 supports the rotor 5 there are one same diameter.It is different from existing multiaxis unmanned plane
, the fuselage 1 that the oil of the application moves unmanned plane is the strip of bilateral symmetry, and there are one longitudinally asymmetric axis for the tool of fuselage 1
Line 6, fuselage 1 is generally elongated to be set parallel to the axis of symmetry 6.The head and tail of unmanned plane are each provided with two
It is symmetrical with the rotor 5 that the axis of symmetry 6 is arranged.The basic conception of the application is, is strip in the fuselage 1 of the dynamic unmanned plane of oil
Shape, fuselage 1 have the axis of symmetry 6, and four rotors 5 are respectively arranged at the both sides of the axis of symmetry 6, so as to vertical below fuselage 1
To a unobstructed passage is formd, in favor of setting the load such as photoelectric nacelle 7 and arm discharge cylinder (not shown), keep away
Exempt from observation and arm discharge when interferes with cantilever 3 and rotor 5 etc., influence to use and fighting efficiency, improve nobody
The application range of machine.Further, since there is provided the axis of symmetry 6, then there will be no lift structure, cantilevers on the longitudinal direction of unmanned plane
The structures such as 3 and rotor 5 thereon can only be distributed in the both sides of the axis of symmetry 6, it is possible thereby to longitudinally be obtained in fuselage wider
Load mount point, be easy to extend load layout.
In order to overcome the problems, such as adjacent rotor interference in air flow, there are one the end of each cantilever 3 in the application supports
The kuppe 4 of the circular ring shape identical around the shape of rotor 5.The setting of kuppe 4 allows the diameter of rotor 5 maximized
It is extended, as long as not interfering with fuselage 1, so as in the case where the length of cantilever 3 need not be extended, have as far as possible
The lift of the raising unmanned plane of effect, thus the carrying ability of unmanned plane can be improved.Certainly, it is excellent for the ease of calculating and manipulating
Select four cantilevers 3 protruding from fuselage 1 in a manner of perpendicular to the axis of symmetry 6.
Further, as shown in the figure, the oil of the application moves the fusiformis structure of the fuselage substantially strip of unmanned plane, machine
The width constriction of head and tail, middle part width are maximum convenient for setting engine.The fuselage of fusiformis structure can also advance with after
Flight resistance is reduced during moving back, improves the voyage of unmanned plane.In addition, the fuselage or rotor diameter of fusiformis structure are most
Bigization provides space.
Further, as shown in Figs. 1-2, the oil of the application moves unmanned plane in a specific embodiment, the front end of fuselage 1
Be provided with can carry photoelectric nacelle 7 connection structure (not shown).In another specific embodiment, the lower part of fuselage 1
The connection structure (not shown) of carry arm discharge cylinder can be set, for example, can be parallel along the length direction of the axis of symmetry 6
Two or more arm discharge cylinders are set, wherein the arm discharge cylinder can be specially launch canister or rocket projectile
Launching tube since this kind of arm discharge cylinder needs to provide the elevation angle obliquely, is difficult to if there are the barriers such as rotor in its front
Launch a guided missile or rocket projectile (exist interference in the case of unmanned plane just crash), therefore arranged for ease of load, head and
The rotor 5 of tail is with the axis of symmetry 6 apart from equal configuration, then arm discharge cylinder can be intuitively by parallel to load path
The mode that 6 length direction is set realizes the load gravity center balance of unmanned plane, in order to the manipulation of unmanned plane, simplifies flying-controlled box
Design difficulty.
Further, as shown in Figure 3-4, another specific embodiment according to the present utility model is shown respectively
The dimensional structure diagram and decomposition diagram of the dynamic unmanned plane undercarriage of oil, as it can be seen that the undercarriage 2 of the application is for installing in figure
In the lower section of the fuselage 1 of the dynamic unmanned plane of oil, including two identical arched members 21 and two identical cross bars 22, the machine of unmanned plane
The lower part of head and tail is respectively arranged with an arched member 21, and the arched member 21 has symmetrically to be tied compared with the axis of symmetry 6
Structure, positioned at the same side of the axis of symmetry 6 two arched members 21 end connection there are one cross bar 22.The end of arched member 21 point
The both ends of cross bar 22 are not connected to by a connecting sleeve 212.
The arched member 21 of the undercarriage 2 of the application employs symmetrical structure, and left and right is connected as one, thus makes
The undercarriage for obtaining unmanned plane both sides is the structure to link into an integrated entity in fact, and the undercarriage of integral structure inherently possesses reinforcement
Can, because without setting the structure particularly strengthened the tie point of undercarriage 2 on the fuselage 1, reducing unmanned plane
Construction weight improves the load level of unmanned plane.In addition the application uses the knot of the arched member of the integral structure of simple function
Structure designs, and undercarriage does not also serve as carry platform, thus can also further reduce the rigidity of undercarriage, can be that unmanned plane lands
When certain buffering is provided, body is avoided to damage.
Further, preferably two cross bars 22 are set parallel to the axis of symmetry 6, so that being distributed on two cross bars 22
Support force it is equal and be easy to calculate.In addition, in order to which the rigidity using arched member 21 more optimized is to mitigate construction weight, preferably
The vertical plane of two arched members 21 is mutually parallel (referring to Fig. 2).It is further preferred that the axis of symmetry 6 is perpendicular to two arches
The vertical plane of part 21, thus each arched member 21 is perpendicular to fore-and-aft plane, arched member 21 is directly subject to longitudinal pressure, side
Pulling force is provided to power by cross bar 22 to be balanced, the construction weight of entire undercarriage 2 can be designed very little, reduce unmanned plane
Deadweight, further improve the load level of unmanned plane.
In addition, as shown in the figure, the arched member 21 of undercarriage 2 is not actually what straight line outward bending was stretched out, but enclose
It is stretched out obliquely after the radian of the lower part carry curvature of space one of unmanned plane, to concede certain space in order to force
The carry arrangement of device.That is, the application is by optimizing the layout of undercarriage, except by the arched member 21 of undercarriage 2 oliquely downward
It stretches to increase outside carry space, is also designed by radian, further conceded horizontal carry space, thus can provide more
Wide longitudinal carry passage can longitudinally obtain larger range of load mount point in fuselage, be easy to extend load layout.Simultaneously
The bending radian of arched member 21 also avoids straight line dog-ear, improves the fatigue-resistance characteristics of structure.
Further, due to for the dynamic relatively electronic unmanned plane of unmanned plane of oil its dead weight it is much greater, the application's
Undercarriage 2 additionally provides landing Cushioning Design.
The concrete structure of each undercarriage 2 is further described referring to Fig. 3-4.As shown in the figure, the application's
In one specific embodiment, the end of two arched members 21 of undercarriage 2 is connected to cross bar 22 by connecting sleeve 212 respectively
Both ends, connecting sleeve 212 are tee-joint sleeve form, and the upper end is connected with arched member 21, and lower end one side is connected with cross bar 22, lower end
Opposite side is connected with a upper curved casing 213.Using the connecting sleeve 212 of tee-joint sleeve form preferably by metal easy to process
It is made, such as is made of aluminium alloy.And tee-joint sleeve also allows for being connected by screw arched member 21 and cross bar 22, it is simple in structure and
It is easy to manufacture and assemble, reduces the production efficiency that cost improves unmanned plane.Upper curved casing 213 can be by nonmetallic glass
Steel or Carbon fibe are made, and to form ski structure at the both ends of cross bar 22, cross bar 22 when landing are avoided to be embedded in weak soil
In cause difficulty of taking off again.
In another specific embodiment of the application, arched member 21 is formed with the end that cross bar 22 is connected and horizontal plane
One acute angles beta, the angular range of preferably described acute angles beta is 50-70 degree.For the relatively electronic unmanned plane of the dynamic unmanned plane of oil
Its dead weight is much greater, and when unmanned plane lands and the impact force on ground can be very big.The application by the tip designs of arched member 21 into
Horizontal by the form of acute angle, when unmanned plane lands, arched member 21 can be easy to outward occur along acuter angles
Impact force when landing so as to reduce the height of arched member 21 by flexible deformation, is sponged a part by flexible deformation.
Certainly, if acute angles beta is too small, the height of arched member 21 is too low, and the liftoff space of unmanned plane is too small will to be unfavorable for complicated landform
Landing.And too small angle can also reduce the intensity of arched member 21 so that it is easy to that fatigue fracture occurs.
In addition, just it has been observed that due to the application Landing Gear Design pooling feature, it is necessary to reduce as far as possible rigidity in favor of
Its flexible deformation absorbs impact force during landing, needs to strengthen rigidity if undercarriage also serves as carry platform in favor of carry,
Then undercarriage will lose its pooling feature.Therefore the undercarriage of the application is suitable only for single drop, thus rises and falls
The structure of frame can obtain ultimate attainment simplification, reduce construction weight, and the Landing Gear Design of integral structure is conducive to undercarriage
Dismounting, easily undercarriage can be removed when transport and storage to reduce the volume of unmanned plane.And it is connected with load
Lotus undercarriage dismounting get up it is highly difficult, be not easy to the transport and storage of unmanned plane.
Further, yielding rubber pipe 214 (as shown in cross bar on the outside of Fig. 4) can also be socketed on cross bar 22, to drop
Buffering is provided when falling to protect undercarriage, avoids unmanned plane malformation.
In conclusion the arched member of the undercarriage of the application employs symmetrical structure, and left and right is connected as one,
So that the undercarriage of unmanned plane both sides is the structure to link into an integrated entity in fact, the undercarriage of integral structure inherently possesses
Reinforcing property, because without setting the structure particularly strengthened the tie point of undercarriage on fuselage, reducing nobody
The construction weight of machine improves the load level of unmanned plane.In addition the application uses the arched member of the integral structure of simple function
Structure design, undercarriage does not also serve as carry platform, thus can also further reduce the rigidity of undercarriage, can be unmanned plane
Certain buffering during landing is provided, body is avoided to damage.In addition, except the arched member of undercarriage is oliquely downward stretched to increase
It outside carry space, is also designed by radian, has further conceded horizontal carry space, thus broader longitudinal direction can be provided and hung
Passage is carried, can longitudinally obtain larger range of load mount point in fuselage, is easy to extend load layout.Arched member is curved simultaneously
Folding radian also avoids straight line dog-ear, improves the fatigue-resistance characteristics of structure.
It will be appreciated by those skilled in the art that although the utility model is described in the way of multiple embodiments
, but not each embodiment only includes an independent technical solution.So narration is just for the sake of clear in specification
For the sake of, those skilled in the art should consider the specification as a whole is understood, and by skill involved in each embodiment
Art scheme, which is regarded as, can be mutually combined into the mode of different embodiments to understand the scope of protection of the utility model.
The above descriptions are merely exemplary embodiments of the present utility model, is not limited to the model of the utility model
It encloses.Any those skilled in the art, the equivalent variations made on the premise of the design of the utility model and principle is not departed from,
Modification and combination should all belong to the scope of the utility model protection.
Claims (9)
1. a kind of dynamic unmanned plane undercarriage of oil, for being mounted on the lower section of the fuselage (1) of the dynamic unmanned plane of oil, the dynamic unmanned plane of oil
Fuselage (1) connection there are four cantilever (3), each cantilever (3) support there are one same diameter rotor (5), the fuselage
(1) tool is there are one longitudinal asymmetric axis (6), and the cantilever (3) is in a manner of perpendicular to the axis of symmetry (6) from the fuselage
(1) protruding, the end of each cantilever (3) supports that there are one the identical annulus of the shape around the rotor (5)
The kuppe (4) of shape, it is characterised in that：The undercarriage (2) includes two identical arched members (21) horizontal stroke identical with two
Bar (22), the head of the unmanned plane and the lower part of tail are respectively arranged with an arched member (21), the arched member
(21) have compared with the axis of symmetry (6) symmetrical structure, positioned at described in two of the same side of the axis of symmetry (6)
There are one the cross bars (22) for the end connection of arched member (21).
2. the dynamic unmanned plane undercarriage of oil as described in claim 1, which is characterized in that described two cross bars (22) are parallel to described
The axis of symmetry (6) is set.
3. the dynamic unmanned plane undercarriage of oil as claimed in claim 2, which is characterized in that the vertical of described two arched members (21) is put down
Face is mutually parallel.
4. the dynamic unmanned plane undercarriage of oil as claimed in claim 3, which is characterized in that the axis of symmetry (6) is perpendicular to described
The vertical plane of two arched members (21).
5. the dynamic unmanned plane undercarriage of oil as claimed in claim 4, which is characterized in that the end of the arched member (21) leads to respectively
Cross the both ends that a connecting sleeve (212) is connected to the cross bar (22).
6. the dynamic unmanned plane undercarriage of oil as claimed in claim 5, which is characterized in that the connecting sleeve (212) is threeway set
Form of tubes, the upper end are connected with the arched member (21), and lower end one side is connected with the cross bar (22), lower end opposite side and one
Upper curved casing (213) is connected.
7. the dynamic unmanned plane undercarriage of oil as claimed in claim 6, which is characterized in that the arched member (21) and the cross bar
(22) connected end is formed with horizontal plane there are one acute angles beta, and the angular range of the acute angles beta is 50-70 degree.
8. the dynamic unmanned plane undercarriage of oil as claimed in claim 7, which is characterized in that the arched member (21) of the undercarriage (2)
The radian that the lower part carry curvature of space of unmanned plane one is moved around the oil stretches out obliquely afterwards.
9. the dynamic unmanned plane undercarriage of oil as claimed in claim 8, which is characterized in that buffering rubber is socketed on the cross bar (22)
Sebific duct (214).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721477007.8U CN207450227U (en) | 2017-11-08 | 2017-11-08 | A kind of dynamic unmanned plane undercarriage of oil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721477007.8U CN207450227U (en) | 2017-11-08 | 2017-11-08 | A kind of dynamic unmanned plane undercarriage of oil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207450227U true CN207450227U (en) | 2018-06-05 |
Family
ID=62254531
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721477007.8U Active CN207450227U (en) | 2017-11-08 | 2017-11-08 | A kind of dynamic unmanned plane undercarriage of oil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207450227U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107757883A (en) * | 2017-11-08 | 2018-03-06 | 沈阳旋飞航空技术有限公司 | A kind of dynamic unmanned plane undercarriage of oil |
-
2017
- 2017-11-08 CN CN201721477007.8U patent/CN207450227U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107757883A (en) * | 2017-11-08 | 2018-03-06 | 沈阳旋飞航空技术有限公司 | A kind of dynamic unmanned plane undercarriage of oil |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103863576B (en) | Depopulated helicopter performance detecting platform | |
| CN103274042B (en) | A kind of floated driven helicopter | |
| CN207450216U (en) | A kind of load configuration structure of the dynamic unmanned plane of oil | |
| CN206273678U (en) | The unmanned plane that a kind of variable empennage is controlled with folded wing | |
| CN207450249U (en) | A kind of unmanned plane rotor pulp distance varying mechanism | |
| CN105980251B (en) | Path-based power generation control for aircraft | |
| CN106218881A (en) | Vertical layout fuel power four rotor flying platform | |
| CN204998767U (en) | Double -deck rotor unmanned aerial vehicle of modified | |
| CN202609078U (en) | Tail control system for unmanned helicopter | |
| CN110162929A (en) | A kind of autonomous air refuling hose tapered sleeve equilbrium position calculation method | |
| CN107600391A (en) | A kind of electronic unmanned plane undercarriage | |
| CN107757883A (en) | A kind of dynamic unmanned plane undercarriage of oil | |
| CN207450227U (en) | A kind of dynamic unmanned plane undercarriage of oil | |
| CN207550494U (en) | A kind of electronic unmanned plane undercarriage | |
| CN105083521A (en) | Airship | |
| CN207450243U (en) | A kind of dynamic quadrotor unmanned plane of oil | |
| CN207658039U (en) | A kind of unmanned plane undercarriage | |
| CN206552267U (en) | A kind of device for delivering express delivery on unmanned plane | |
| CN107672780A (en) | A kind of load configuration structure of the dynamic unmanned plane of oil | |
| CN107719655A (en) | A kind of dynamic four rotor wing unmanned aerial vehicles of oil | |
| CN209258410U (en) | A kind of fuel system for the dynamic unmanned plane of oil | |
| CN109572987A (en) | A kind of multi-rotor unmanned aerial vehicle based on four compression bar integral tension structures | |
| CN109484611B (en) | Fuselage bearing structure of oil-driven unmanned aerial vehicle | |
| CN107719661A (en) | A kind of unmanned plane rotor pulp distance varying mechanism | |
| CN207450220U (en) | The supporting rod quick-disassembly structure of the dynamic unmanned plane of oil |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |