CN107600391A - A kind of electronic unmanned plane undercarriage - Google Patents
A kind of electronic unmanned plane undercarriage Download PDFInfo
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- CN107600391A CN107600391A CN201710972654.4A CN201710972654A CN107600391A CN 107600391 A CN107600391 A CN 107600391A CN 201710972654 A CN201710972654 A CN 201710972654A CN 107600391 A CN107600391 A CN 107600391A
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- fuselage
- unmanned plane
- undercarriage
- electronic unmanned
- sleeve pipe
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Classifications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
A kind of electronic unmanned plane undercarriage, the fuselage of electronic unmanned plane is connected with multiple cantilevers, a longitudinal loading passage is provided with below fuselage, the both sides of longitudinal loading passage are respectively symmetrically provided with a undercarriage, and undercarriage includes two montants for connecting fuselage and is arranged at the cross bar of the end of montant；The upper end of two montants is connected by the first connection sleeve pipe in the position that a cantilever is connected with fuselage with fuselage respectively；Lower end is connected to the both ends of cross bar by second connection sleeve pipe respectively.Undercarriage is arranged at the both sides of longitudinal loading passage by the application, conveniently photoelectricity can be set to hang the load such as storehouse and arm discharge cylinder, the position that the montant of undercarriage is connected with fuselage merges with the position that cantilever is connected with fuselage is arranged on same position, can simplify structure design, reduce construction weight.It is easy to be attached by screw in the form of connection sleeve pipe, it is simple in construction and be easy to manufacture and assemble, reduce the production efficiency that cost improves unmanned plane.
Description
Technical field
It is more particularly to available the present invention relates to unmanned air vehicle technique field, more particularly to a kind of electronic unmanned plane of more rotors
In the landing gear structure of electronic unmanned plane.
Background technology
Electronic unmanned plane is simple in construction, and noise is small, and there is maneuverability, rapid reaction, operation to require low advantage, disappearing
The occupation rate for taking level market is very big.But the power of electronic unmanned plane is provided by battery, battery is basically unmanned plane
Deadweight, no image of Buddha fuel oil equally consumes, and causes its payload extremely limited, the cruise time is also very short, seldom as weapon
Platform is hit to use.The electronic unmanned plane of current consumer level in the market is multiaxis unmanned plane mostly, such as four axles, six axles,
Due to cantilever, with respect to fuselage, shape is set radially outward, and volume is big, and transport is inconvenient, in addition existing rotor wing unmanned aerial vehicle generally existing
Load level is low, and topology layout is unreasonable, it is difficult to plays control and the security advantages of unmanned plane, limits rotor unmanned aerial vehicle and exist
Military and monitoring field development and application.
The U of CN 206278267 disclose a kind of multi-rotor unmanned aerial vehicle, including unmanned plane body, unmanned plane body by horn,
Central plate and foot support composition, horn include arm of force set, arm bar, motor cabinet, motor and blade, and motor is fixed on motor cabinet
On, blade is fixed on motor, and motor cabinet is fixed on arm bar one end, and the arm bar other end is provided with arm of force set, and passes through power
Arm set is connected with central plate, and difference in height is provided between the blade on adjacent horn, adjacent blades is not in same level,
The centrally disposed plate bottom of foot support.The unmanned plane of the prior art, which is set, makes adjacent blades be not in same level, uses
Mitigate main screw lift to shorten the wheelbase of more gyroplanes, improve cruising time.
Six rotors of the electronic unmanned plane of above-mentioned prior art are set around body equiangularly spacedly, thus by fuselage
The center harden structure of equilateral hexagon is designed to, each rotor is just arranged on six angles of hexagon, utilizes body
Hexagonal centre harden structure bears moment of torsion caused by the lift of rotor.From the point of view of the accompanying drawing of above-mentioned prior art, above-mentioned existing nothing
Man-machine hexagonal centre harden structure is only configured as load-carrying construction, and various load are hung in the lower section of fuselage.In order to the greatest extent
Amount the circumscribed circle diameter very little of the central plate of hexagon, causes stress almost all to concentrate on less construction weight stress
The middle part of fuselage, fuselage weight thereby have to increase；And too small fuselage diameter, holohedral symmetry layout, cause position of centre of gravity
Converge, the layout such as load mount point is extremely limited, and the top of undercarriage is led too close to waist
Cause the angle region of undercarriage too narrow and small, can not the larger load of carry volume.
The content of the invention
The technical problem to be solved in the present invention is to provide a kind of electronic unmanned plane undercarriage, to be carried before being reduced or avoided
To the problem of.
In order to solve the above technical problems, the present invention proposes a kind of electronic unmanned plane undercarriage, for installed in electronic nothing
The lower section both sides of man-machine fuselage, the fuselage of the electronic unmanned plane are connected with multiple cantilevers, and each cantilever is supported by one
Motor, each motor carry propeller, are provided with a longitudinal loading passage below the fuselage, the fuselage is elongated
Set parallel to the longitudinal loading passage, wherein：The both sides of the longitudinal loading passage are respectively symmetrically provided with described in one
Undercarriage, the undercarriage include two montants for connecting the fuselage and the cross bar for the end for being arranged at the montant；Institute
State the upper ends of two montants respectively by the first connection sleeve pipe a cantilever and the position that the fuselage is connected with it is described
Fuselage is connected；The lower end of described two montants is connected to the both ends of the cross bar by second connection sleeve pipe respectively.
Preferably, second connection sleeve pipe is tee-joint sleeve form, and its upper end is connected with the montant, lower end side with
The cross bar is connected, and lower end opposite side is connected with a upper curved sleeve pipe.
Preferably, the lower end of the montant is inserted vertically into formed with a kink perpendicular to ground, the kink
In the upper end of the second connection sleeve pipe.
Two montants of the undercarriage of lower section the same side of the fuselage are preferably located at respectively in spaced furthest
Two cantilevers are connected with the position that the fuselage is connected with the fuselage.
Preferably, the front end of the fuselage be provided with can carry photoelectricity hang the attachment structure in storehouse.
Preferably, the bottom of the fuselage be provided with can carry arm discharge cylinder attachment structure.
Preferably, sent out along the length direction of the longitudinal loading passage two or more described weapons that can be arranged in parallel
Shooting cylinder.
Preferably, the montant of the undercarriage the arm discharge cylinder one radian of location bending, to allow cloth outputting
Put the space of the arm discharge cylinder.
Preferably, yielding rubber pipe is socketed with the cross bar.
The electronic unmanned plane of the application will be risen and fallen by setting a longitudinal loading passage not blocked below fuselage
Set up and be placed in the both sides of longitudinal loading passage, conveniently photoelectricity can be set to hang the load such as storehouse and arm discharge cylinder, avoid observation and
Interfered when arm discharge with cantilever and propeller etc., influence to use and fighting efficiency, improve the application of unmanned plane
Scope.In addition, the application is also by optimizing the layout of undercarriage, by two montants of same undercarriage as far as possible away from arrangement with
Longitudinal carry space is increased, by way of radian, horizontal carry space will be conceded between two undercarriages of fuselage both sides, because
And longer and broader longitudinal loading passage can be provided, larger range of load mount point can be longitudinally obtained in fuselage,
It is easy to extend load layout.In addition, the application also passes through the position that the montant of undercarriage is connected with fuselage and cantilever and fuselage
Connected position merges in same position, can simplify structure design, reduces construction weight.It is easy in the form of connection sleeve pipe
It is attached by screw, it is simple in construction and be easy to manufacture and assemble, reduce the production efficiency that cost improves unmanned plane.
Brief description of the drawings
The following drawings is only intended to, in doing schematic illustration and explanation to the present invention, not delimit the scope of the invention.Wherein,
The dimensional structure diagram of the electronic unmanned plane of a specific embodiment according to the present invention is shown in Fig. 1；
The front schematic view of electronic unmanned plane shown in Fig. 1 is shown in Fig. 2；
The side schematic view of electronic unmanned plane shown in Fig. 1 is shown in Fig. 3；
The schematic diagram of the electronic unmanned plane undercarriage of a specific embodiment according to the application is shown in Fig. 4；
The decomposition diagram of electronic unmanned plane undercarriage shown in Fig. 4 is shown in Fig. 5.
Embodiment
In order to which technical characteristic, purpose and the effect of the present invention is more clearly understood, now control illustrates this hair
Bright embodiment.Wherein, identical part uses identical label.
Just it has been observed that existing multiaxis unmanned plane is laid out using holohedral symmetry mostly, position of centre of gravity is caused to converge, load
Layout is extremely limited, and because 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 of existing unmanned plane.It is and too small
Fuselage diameter, holohedral symmetry layout, cause position of centre of gravity to converge, and the layout such as load mount point is extremely limited, and
And the top of undercarriage causes the angle region of undercarriage too narrow and small too close to waist, can not carry volume it is larger
Load.
To solve drawbacks described above, this application provides a kind of electronic unmanned plane, as Figure 1-3, wherein, what Fig. 1 was shown
It is the dimensional structure diagram according to the electronic unmanned plane of the specific embodiment of the present invention；Fig. 2 is shown electric shown in Fig. 1
The front schematic view of dynamic unmanned plane；The side schematic view of electronic unmanned plane shown in Fig. 1 is shown in Fig. 3.
Referring to Fig. 1-3, the electronic unmanned plane of the application includes fuselage 1, and the lower section both sides of fuselage 1 are respectively provided with one and risen and fallen
Frame 2, the fuselage 1 of electronic unmanned plane are connected with multiple cantilevers 3, and each cantilever 3 is supported by a motor 4, each 4 equal band of motor
There is propeller 5.Unlike existing multiaxis unmanned plane, the lower section of fuselage 1 of the electronic unmanned plane of the application is provided with one and indulged
To load path 6, as shown in Fig. 1-3 directions of arrow.That is, the basic conception of the application is, in the fuselage 1 of electronic unmanned plane
Lower section set a longitudinal loading passage 6 not blocked, in favor of set photoelectricity hang the load such as storehouse 7 and arm discharge cylinder 8 (after
Face will be explained further), avoid interfering with cantilever 3 and propeller 5 etc. when observation and arm discharge, influence to make
With and fighting efficiency, improve the application of unmanned plane.Further, since longitudinal loading passage 6 is provided with, then in unmanned plane
There will be no lift structure on longitudinal direction, the structure such as cantilever 3 and motor 4 thereon can only be distributed in the both sides of longitudinal loading passage 6,
It is possible thereby to longitudinally obtain larger range of load mount point in fuselage, it is easy to extend load layout.
It should be noted that the electronic unmanned plane of multiaxis is due to the limitation of fuselage weight, loading demands, power of motor, especially
Be the application can carry photoelectricity hang the design requirement of storehouse 7 and arm discharge cylinder 8, cause the quantity of rotor can not select very little,
For example, if it is that (only symmetric configuration could keep lift to balance to four rotors in the vertical, so rotor quantity can only be even
Number), then power of motor is not enough to obtain enough lift；And increase rotor quantity more than eight, then the folder between adjacent rotor
Angle space diminishes, and adjacent rotor can interfere with each other, and lift can be reduced again by reducing rotor diameter.Therefore, for the big load of the application
Lotus and the design requirement for possessing longitudinal loading passage 6, the design of six or eight rotors is selected, and these rotors can only be divided into two
Group symmetric configuration is in the both sides of longitudinal loading passage 6.
In specific embodiment is illustrated, the both sides of longitudinal loading passage 6 are respectively symmetrically provided with four cantilevers 3, electronic nothing
Man-machine fuselage 1 is generally elongated to be set parallel to the longitudinal loading passage 6.In a specific embodiment, fuselage 1
Front end be provided with can carry photoelectricity hang the attachment structure (not shown) in storehouse 7.In another specific embodiment, fuselage 1
Bottom be provided with can carry arm discharge cylinder 8 attachment structure (not shown), for example, the length along longitudinal loading passage 6
Degree direction can be arranged in parallel two or more arm discharge cylinders 8, wherein the arm discharge cylinder 8 can be specially guided missile hair
Shooting cylinder or rocket bomb transmitting cylinder, because this kind of arm discharge cylinder 8 needs to provide the elevation angle (as shown in Figure 3) obliquely, if
Its front has the barriers such as rotor to be then difficult to launch a guided missile or rocket projectile (exist interference in the case of unmanned plane just crash),
And rear is also required to prevent rocket engine wake flame calcination rotor, therefore arm discharge cylinder 8 can be intuitively by parallel to load
The mode that the length direction of lotus passage 6 is set realizes the load gravity center balance of unmanned plane, in order to the manipulation of unmanned plane, simplifies and flies
Control the design difficulty of software.
Further, as illustrated, the both sides of longitudinal loading passage 6 are respectively symmetrically provided with a undercarriage 2, undercarriage
2 include two montants 21 for connecting fuselage 2 and are arranged at the cross bar 22 of the end of montant 21, the upper end difference of two montants 21
It is connected by the first connection sleeve pipe 211 in a cantilever 3 with the position that fuselage 1 is connected with fuselage 1, the lower end point of two montants 21
The both ends of cross bar 22 are not connected to by second connection sleeve pipe 212.That is, undercarriage 2 needs to carry whole unmanned plane
Weight, therefore it needs to carry out structural strengthening design with the position that fuselage 1 is connected, and the position being connected with fuselage 1 due to cantilever 3
Natively need to carry out structural strengthening, therefore, by the position that the montant 21 of undercarriage 2 is connected with fuselage 1 and cantilever 3 and fuselage 1
Connected position merges in same position, can simplify structure design, reduces construction weight.Likewise, can also preferred weapon
Launching tube 8 and the attachment structure of fuselage 1 are located at position that cantilever 3 is connected with fuselage 1 (as shown in figure 3, arm discharge cylinder 8 and machine
Body 1 has two link positions, to keep the gravity balance of launching tube), it can equally simplify structure design, reduce construction weight
Further, positioned at lower section the same side of fuselage 1 undercarriage 2 two montants 21 respectively in spaced furthest
Two cantilevers 3 are connected with the position that fuselage 1 is connected with fuselage 1.That is, in specific embodiment shown in Fig. 1, the both sides of fuselage 1 are each
There are four cantilevers 3, in this four cantilevers 3, positioned at the spaced furthest of two cantilevers 3 at both ends, the cantilever 3 of the two spaced furthests
The position being connected with fuselage 1, the link position of two montants 21 of the undercarriage 2 of the same side is provided as, can be in undercarriage 2
Two montants 21 in the case where ensureing structural strength and mitigating construction weight, be arranged in as far as possible at a distance of maximum position, with
Maximum structural stability is provided.For prior art, the top of undercarriage 2 is set spacing more by the application as far as possible
Far, the interval between two montants 21 is also maximum, can provide space as big as possible and be used for carry.
Further, since also need to consider the interference problem of undercarriage 2 and arm discharge cylinder 8, as shown in Fig. 2 undercarriage 2
Montant 21 is not actually that straight line is outwardly directed, but in the certain radian of location bending of arm discharge cylinder 8, to allow
Go out arrangement of certain space in order to arm discharge cylinder 8.That is, the montant 21 of undercarriage 2 is curved in the position of arm discharge cylinder 8
A bent radian, to concede the space of arrangement arm discharge cylinder 8.
By the above-mentioned layout of the application, except increasing longitudinal carry between two montants 21 by same undercarriage 2
Outside space, also by way of radian, horizontal carry space will be conceded between two undercarriages 2 of the both sides of fuselage 1, thus
Longer and broader longitudinal loading passage 6 can be provided, can longitudinally obtain larger range of load mount point in fuselage, easily
In extension load layout.
The concrete structure of each undercarriage 2 is further described referring to Fig. 4-5, wherein, basis is shown in Fig. 4
The schematic diagram of the electronic unmanned plane undercarriage of the specific embodiment of the application；Electronic unmanned plane shown in Fig. 4 is shown in Fig. 5
The decomposition diagram of undercarriage.
As illustrated, in the specific embodiment of the application, the lower end of two montants 21 of undercarriage 2 passes through respectively
Second connection sleeve pipe 212 is connected to the both ends of cross bar 22, and the second connection sleeve pipe 212 is tee-joint sleeve form, its upper end and montant
21 connections, lower end side are connected with cross bar 22, and lower end opposite side is connected with a upper curved sleeve pipe 213.Using tee-joint sleeve form
The second connection sleeve pipe 212 be preferably made up of the metal for being easy to processing, such as be made up of aluminium alloy.And tee-joint sleeve also allows for leading to
Cross mode connects for screw montant 21 and cross bar 22, it is simple in construction and be easy to manufacture and assemble, reduce the life that cost improves unmanned plane
Produce efficiency.Upper curved sleeve pipe 213 can be made up of nonmetallic fiberglass or Carbon fibe, to form cunning at the both ends of cross bar 22
Sledge structure, avoid causing difficulty of taking off again in the insertion of cross bar 22 weak soil when landing.Cross bar 22 can also use high intensity
Carbon fibre material is made.
In another specific embodiment of the application, montant 21 and the end that cross bar 22 is connected formed with one perpendicular to
The kink 215 on ground, the kink 215 are inserted vertically into the upper end of the second connection sleeve pipe 212.Unmanned plane docks at ground
When, support force of the cross bar 22 by ground upwardly, kink 215 is set perpendicular to ground can be upward by this support force
Montant 21 is passed to, avoids montant 21 and the excessive generation fatigue of stress of the second connection sleeve pipe 212 of the link position of cross bar 22.
In addition, just it has been observed that due to the second connection sleeve pipe 212 can be connected by screw montant 21 and cross bar 22 (Fig. 4 and
It can be seen that Screw hole structure, the screw of connection are not shown in Fig. 5 decomposition view in 5).When unmanned plane land,
When montant 21 deforms laterally, cross bar 22 moves horizontally outward, and the second connection sleeve pipe 212 is in the kink perpendicular to ground
Translation is kept in the presence of 215 without twisting, thus the screw between the second connection sleeve pipe 212 and cross bar 22 will not be
Alternate stress effect is lower to be destroyed., whereas if montant 21 as shown in the prior art as with ground form at an acute angle with
Cross bar connects, then in the case of using the second connection sleeve pipe 212 of tee-joint sleeve form, when each unmanned plane lands,
Second connection sleeve pipe 212 all can be with the deformation transformation of montant 21 and the angle on ground, so as to cause the second connection sleeve pipe 212
Twist, reversed torsion can be such that the screw between the second connection sleeve pipe 212 and cross bar 22 occurs under shearing force repeatedly
Destroy, especially the anti-shear ability of cross bar 22 is relatively weak made of carbon fiber pipe material, have more than is needed how long screw will be from
Come off in the screw of destruction, undercarriage will soon damage.Therefore, the application is because there is provided the kink perpendicular to ground
215, reliability and the life-span of undercarriage can be improved, is advantageous to the safety operation of unmanned plane.
Further, yielding rubber pipe 214 can also be socketed on cross bar 22, to provide buffering when landing to protect
Undercarriage is protected, avoids unmanned plane malformation.
In summary, the electronic unmanned plane of the application below fuselage by setting a longitudinal loading do not blocked to lead to
Road, undercarriage is arranged to the both sides of longitudinal loading passage, conveniently photoelectricity can be set to hang the load such as storehouse and arm discharge cylinder, kept away
Exempt from observation and interfered with cantilever and propeller etc. when arm discharge, influence to use and fighting efficiency, improve nobody
The application of machine.In addition, the application is also by optimizing the layout of undercarriage, two montants of same undercarriage are as far as possible remote
From arrangement to increase longitudinal carry space, by way of radian, horizontal extension will be conceded between two undercarriages of fuselage both sides
Space is carried, thus longer and broader longitudinal loading passage can be provided, can longitudinally obtain larger range of load in fuselage
Lotus mount point, it is easy to extend load layout.In addition, the application also by position that the montant of undercarriage is connected with fuselage with it is outstanding
The position that arm is connected with fuselage merges in same position, can simplify structure design, reduces construction weight.Using connection sleeve pipe
Form is easy to be attached by screw, simple in construction and be easy to manufacture and assemble, and reduces the life that cost improves unmanned plane
Produce efficiency.
It will be appreciated by those skilled in the art that although the present invention is described in the way of multiple embodiments,
It is that not each embodiment only includes an independent technical scheme.So narration is used for the purpose of for the sake of understanding in specification,
The skilled in the art should refer to the specification as a whole is understood, and by technical scheme involved in each embodiment
The modes of different embodiments can be mutually combined into understand protection scope of the present invention by regarding as.
The schematical embodiment of the present invention is the foregoing is only, is not limited to the scope of the present invention.It is any
Those skilled in the art, equivalent variations, modification and the combination made on the premise of the design of the present invention and principle is not departed from,
The scope of protection of the invention all should be belonged to.
Claims (9)
- A kind of 1. electronic unmanned plane undercarriage, for the lower section both sides of the fuselage (1) installed in electronic unmanned plane, the electronic nothing Man-machine fuselage (1) is connected with multiple cantilevers (3), and each cantilever (3) is supported by a motor (4), the equal band of each motor (4) There is propeller (5), be provided with a longitudinal loading passage (6) below the fuselage (1), the fuselage (1) is elongated parallel Set in the longitudinal loading passage (6), it is characterised in that：The both sides of the longitudinal loading passage (6) are respectively symmetrically provided with One undercarriage (2), the undercarriage (2) include two montants (21) for connecting the fuselage (2) and are arranged at institute State the cross bar (22) of the end of montant (21)；The upper end of described two montants (21) is existed by the first connection sleeve pipe (211) respectively One cantilever (3) is connected with the position that the fuselage (1) is connected with the fuselage (1)；Under described two montants (21) End is connected to the both ends of the cross bar (22) by second connection sleeve pipe (212) respectively.
- 2. electronic unmanned plane undercarriage as claimed in claim 1, it is characterised in that second connection sleeve pipe (212) is three Logical barrel forms, its upper end are connected with the montant (21), and lower end side is connected with the cross bar (22), lower end opposite side and one Individual curved sleeve pipe (213) is connected.
- 3. electronic unmanned plane undercarriage as claimed in claim 2, it is characterised in that the lower end of the montant (21) is formed with one The individual kink (215) perpendicular to ground, the kink (215) are inserted vertically into the upper end of the second connection sleeve pipe (212).
- 4. electronic unmanned plane undercarriage as claimed in claim 1, it is characterised in that same positioned at the lower section of the fuselage (1) What two montants (21) of the undercarriage (2) of side were connected in the two of spaced furthest cantilevers (3) with the fuselage (1) respectively Position is connected with the fuselage (1).
- 5. electronic unmanned plane undercarriage as claimed in claim 1, it is characterised in that the front end of the fuselage (1) is provided with can Carry photoelectricity hangs the attachment structure of storehouse (7).
- 6. electronic unmanned plane undercarriage as claimed in claim 1, it is characterised in that the bottom of the fuselage (1) is provided with can The attachment structure of carry arm discharge cylinder (8).
- 7. electronic unmanned plane undercarriage as claimed in claim 6, it is characterised in that along the length of the longitudinal loading passage (6) Degree direction can be arranged in parallel two or more described arm discharge cylinders (8).
- 8. electronic unmanned plane undercarriage as claimed in claims 6 or 7, it is characterised in that the montant (21) of the undercarriage (2) In one radian of location bending of the arm discharge cylinder (8), to concede the space for arranging the arm discharge cylinder (8).
- 9. the electronic unmanned plane undercarriage as described in one of claim 1-3, it is characterised in that be socketed with the cross bar (22) Yielding rubber pipe (214).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710972654.4A CN107600391A (en) | 2017-10-18 | 2017-10-18 | A kind of electronic unmanned plane undercarriage |
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| CN201710972654.4A CN107600391A (en) | 2017-10-18 | 2017-10-18 | A kind of electronic unmanned plane undercarriage |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108502136A (en) * | 2018-05-14 | 2018-09-07 | 天长市星舟航空技术有限公司 | A kind of horizontal landing-type multi-rotor unmanned aerial vehicle fuselage box |
| CN108945444A (en) * | 2018-08-30 | 2018-12-07 | 无锡莱特杰米科技发展有限公司 | A kind of unmanned aerial photography machine of the wedding celebration with landing protection structure |
| CN109484627A (en) * | 2018-12-24 | 2019-03-19 | 沈阳旋飞航空技术有限公司 | A kind of improved electronic unmanned plane undercarriage |
| CN110901900A (en) * | 2019-12-06 | 2020-03-24 | 沈阳旋飞航空技术有限公司 | Unmanned aerial vehicle undercarriage with quick beta structure |
| WO2022095068A1 (en) * | 2020-11-09 | 2022-05-12 | 深圳市大疆创新科技有限公司 | Foot stand and unmanned aerial vehicle |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020008175A1 (en) * | 1999-05-19 | 2002-01-24 | Bell Helicopter Textron Inc. | Stiffness de-coupled skid landing gear |
| CN203958614U (en) * | 2014-07-24 | 2014-11-26 | 山东新晨科技有限公司 | Integral type multi-rotor aerocraft |
| CN205273842U (en) * | 2015-12-31 | 2016-06-01 | 航天神舟飞行器有限公司 | Unmanned aerial vehicle undercarriage folding joint structure that can expand fast and retrieve |
| CN105752332A (en) * | 2016-04-11 | 2016-07-13 | 徐州蓝翼航空科技有限公司 | Portable foldable four-rotor aircraft |
| CN205707326U (en) * | 2016-04-28 | 2016-11-23 | 辽宁通用航空研究院 | The electronic many rotor unmanned aircrafts of restructural |
| CN205916325U (en) * | 2016-07-04 | 2017-02-01 | 燕山大学里仁学院 | Automatic unmanned aerial vehicle who patrols line of electric wire netting |
| CN206278267U (en) * | 2016-12-26 | 2017-06-27 | 宁波达鹏无人机科技有限公司 | A kind of continuation of the journey multi-rotor unmanned aerial vehicle high |
| CN206297734U (en) * | 2016-12-20 | 2017-07-04 | 北方天途航空技术发展（北京）有限公司 | The hanging structure and unmanned plane and fire-extinguishing of a kind of fire extinguisher bomb launching tube |
| CN207550494U (en) * | 2017-10-18 | 2018-06-29 | 沈阳旋飞航空技术有限公司 | A kind of electronic unmanned plane undercarriage |
-
2017
- 2017-10-18 CN CN201710972654.4A patent/CN107600391A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020008175A1 (en) * | 1999-05-19 | 2002-01-24 | Bell Helicopter Textron Inc. | Stiffness de-coupled skid landing gear |
| CN203958614U (en) * | 2014-07-24 | 2014-11-26 | 山东新晨科技有限公司 | Integral type multi-rotor aerocraft |
| CN205273842U (en) * | 2015-12-31 | 2016-06-01 | 航天神舟飞行器有限公司 | Unmanned aerial vehicle undercarriage folding joint structure that can expand fast and retrieve |
| CN105752332A (en) * | 2016-04-11 | 2016-07-13 | 徐州蓝翼航空科技有限公司 | Portable foldable four-rotor aircraft |
| CN205707326U (en) * | 2016-04-28 | 2016-11-23 | 辽宁通用航空研究院 | The electronic many rotor unmanned aircrafts of restructural |
| CN205916325U (en) * | 2016-07-04 | 2017-02-01 | 燕山大学里仁学院 | Automatic unmanned aerial vehicle who patrols line of electric wire netting |
| CN206297734U (en) * | 2016-12-20 | 2017-07-04 | 北方天途航空技术发展（北京）有限公司 | The hanging structure and unmanned plane and fire-extinguishing of a kind of fire extinguisher bomb launching tube |
| CN206278267U (en) * | 2016-12-26 | 2017-06-27 | 宁波达鹏无人机科技有限公司 | A kind of continuation of the journey multi-rotor unmanned aerial vehicle high |
| CN207550494U (en) * | 2017-10-18 | 2018-06-29 | 沈阳旋飞航空技术有限公司 | A kind of electronic unmanned plane undercarriage |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108502136A (en) * | 2018-05-14 | 2018-09-07 | 天长市星舟航空技术有限公司 | A kind of horizontal landing-type multi-rotor unmanned aerial vehicle fuselage box |
| CN108502136B (en) * | 2018-05-14 | 2023-12-22 | 天长市星舟航空技术有限公司 | Horizontally-falling type multi-rotor unmanned aerial vehicle body box |
| CN108945444A (en) * | 2018-08-30 | 2018-12-07 | 无锡莱特杰米科技发展有限公司 | A kind of unmanned aerial photography machine of the wedding celebration with landing protection structure |
| CN109484627A (en) * | 2018-12-24 | 2019-03-19 | 沈阳旋飞航空技术有限公司 | A kind of improved electronic unmanned plane undercarriage |
| CN110901900A (en) * | 2019-12-06 | 2020-03-24 | 沈阳旋飞航空技术有限公司 | Unmanned aerial vehicle undercarriage with quick beta structure |
| WO2022095068A1 (en) * | 2020-11-09 | 2022-05-12 | 深圳市大疆创新科技有限公司 | Foot stand and unmanned aerial vehicle |
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