CN207550494U - A kind of electronic unmanned plane undercarriage - Google Patents
A kind of electronic unmanned plane undercarriage Download PDFInfo
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- CN207550494U CN207550494U CN201721345399.2U CN201721345399U CN207550494U CN 207550494 U CN207550494 U CN 207550494U CN 201721345399 U CN201721345399 U CN 201721345399U CN 207550494 U CN207550494 U CN 207550494U
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- fuselage
- unmanned plane
- undercarriage
- electronic unmanned
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Abstract
A kind of electronic unmanned plane undercarriage, the fuselage of electronic unmanned plane is connected with multiple cantilevers, there are one longitudinal loading channels for setting below fuselage, the both sides of longitudinal loading channel are symmetrically arranged there are one undercarriage, and undercarriage includes two montants for connecting fuselage and is set to the cross bar of the end of montant；The upper end of two montants is connected respectively by the first connecting sleeve in the position that a cantilever is connected with fuselage with fuselage；Lower end is connected to the both ends of cross bar by second connecting sleeve respectively.Undercarriage is set to the both sides of longitudinal loading channel by the application, setting photoelectricity can be facilitated 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 simple in structure and be easy to manufacture and assemble convenient for being attached by screw in the form of connecting sleeve, reduce the production efficiency that cost improves unmanned plane.
Description
Technical field
The utility model is related to unmanned air vehicle technique field more particularly to a kind of electronic unmanned plane of more rotors, more particularly to
Landing gear structure available for electronic unmanned plane.
Background technology
Electronic unmanned plane is simple in structure, and noise is small, and it is low to have the advantages that maneuverability, rapid reaction, operation require, is disappearing
The occupation rate for taking grade 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 axis, six axis,
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 play control and the security advantages of unmanned plane, limit rotor unmanned aerial vehicle and exist
Military and monitoring field development and application.
206278267 U of CN disclose a kind of multi-rotor unmanned aerial vehicle, including unmanned plane ontology, unmanned plane ontology 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 connect with central plate, and difference in height is equipped between the blade on adjacent horn, adjacent blades is made to be not in same level,
The centrally disposed plate bottom of foot support.The unmanned plane setting of the prior art makes adjacent blades be not in same level, uses
Mitigate main screw lift to shorten the wheelbase of more gyroplanes, improve cruise duration.
Six rotors of the electronic unmanned plane of the above-mentioned prior art are set equiangularly spacedly around body, thus by fuselage
The center harden structure of equilateral hexagon has been designed to it, each rotor is just arranged on six angles of hexagon, utilizes body
Hexagonal centre harden structure bears the torque that the lift of rotor generates.From the point of view of the attached drawing of the 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
For amount with less construction weight stress, the circumscribed circle diameter very little of the central plate of hexagon causes stress almost all to concentrate on
The middle part of fuselage, fuselage weight thereby have to increase；And too small fuselage diameter, holohedral symmetry layout, lead to position of centre of gravity
It converges, the layouts such as load mount point are extremely limited, and the top of undercarriage is led too close to waist
The angle region for causing undercarriage is too narrow, can not the larger load of carry volume.
Utility model content
The technical problem to be solved by the present invention is to provide a kind of electronic unmanned plane undercarriage, 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 electronic unmanned plane undercarriage, for being mounted on electricity
The lower section both sides of the fuselage of dynamic unmanned plane, the fuselage of the electronic unmanned plane are connected with multiple cantilevers, and each cantilever is supported by
One motor, each motor is with propeller, and there are one longitudinal loading channels for fuselage lower section setting, and the fuselage is in length
Parallel strip is set in the longitudinal loading channel, wherein：There are one the both sides of the longitudinal loading channel are symmetrically arranged
The undercarriage, the undercarriage include two montants for connecting the fuselage and the horizontal stroke for the end for being set to the montant
Bar；The upper end of described two montants respectively by the first connecting sleeve the position that a cantilever is connected with the fuselage with
The fuselage is connected；The lower end of described two montants is connected to the both ends of the cross bar by second connecting sleeve respectively.
Preferably, second connecting sleeve is tee-joint sleeve form, and the upper end connect with the montant, lower end side and
The cross bar is connected, and lower end opposite side is connected with a upper curved casing.
Preferably, the lower end of the montant is formed there are one the bending part perpendicular to ground, and the bending part is inserted vertically into
In the upper end of the second connecting sleeve.
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 connection structure in storehouse.
Preferably, the lower part of the fuselage be provided with can carry arm discharge cylinder connection structure.
Preferably, two or more described weapons can be arranged in parallel along the length direction of the longitudinal loading channel to send out
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, it is socketed with yielding rubber pipe on the cross bar.
The electronic unmanned plane of the application will be risen and fallen by setting a longitudinal loading channel not blocked below fuselage
Set up and be placed in the both sides of longitudinal loading channel, setting photoelectricity can be facilitated to hang the load such as storehouse and arm discharge cylinder, avoid observation and
It is interfered when arm discharge with cantilever and propeller etc., influences to use and fighting efficiency, improve the application of unmanned plane
Range.In addition, the application is also by optimizing the layout of undercarriage, by two montants of same undercarriage as possible far from arrangement with
Longitudinal carry space is increased, by way of radian, lateral carry space will be conceded between two undercarriages of fuselage both sides, because
And longer and broader longitudinal loading channel 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 convenient in the form of connecting sleeve
It is attached by screw, it is simple in structure and be easy to manufacture and assemble, reduce the production efficiency that cost improves unmanned plane.
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,
The stereochemical structure signal of the electronic unmanned plane of a specific embodiment according to the present utility model is shown in Fig. 1
Figure；
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 perspective view of electronic unmanned plane undercarriage shown in Fig. 4 is shown in Fig. 5.
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 existing multiaxis unmanned plane 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.It is and too small
Fuselage diameter, holohedral symmetry layout, cause position of centre of gravity to converge, and the layouts such as load mount point are extremely limited, and
And the top of undercarriage, too close to waist, the angle region for leading to undercarriage is too narrow, can not carry volume it is larger
Load.
To solve drawbacks described above, this application provides a kind of electronic unmanned plane, as shown in Figs. 1-3, wherein, what Fig. 1 was shown
It is the dimensional structure diagram of the electronic unmanned plane of a specific embodiment according to the present utility model；Fig. 1 institutes are shown in Fig. 2
Show the front schematic view of electronic 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 respectively there are one rise and fall for installation for the lower section both sides of fuselage 1
Frame 2, the fuselage 1 of electronic unmanned plane are connected with multiple cantilevers 3, and each cantilever 3 supports that there are one motor 4, each 4 equal bands of motor
There is propeller 5.Unlike existing multiaxis unmanned plane, there are one vertical for the 1 lower section setting of fuselage of the electronic unmanned plane of the application
To load path 6, as shown in Fig. 1-3 arrow directions.Also that is, the basic conception of the application is, in the fuselage 1 of electronic unmanned plane
Lower section set a longitudinal loading channel 6 not blocked, in favor of setting photoelectricity hang the load such as storehouse 7 and arm discharge cylinder 8 (after
Face will be explained further), it avoids interfering with cantilever 3 and propeller 5 etc. when observation and arm discharge, influence
Using and fighting efficiency, improve the application range of unmanned plane.In addition, due to being provided with longitudinal loading channel 6, then in unmanned plane
Longitudinal direction on there will be no lift structure, the structures such as cantilever 3 and motor 4 thereon can only be distributed in the two of longitudinal loading channel 6
Side it is possible thereby to longitudinally obtain larger range of load mount point in fuselage, 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, lead to the quantity of rotor cannot select very little,
For example, if it is that (only symmetric configuration could keep lift to balance to four rotors in the longitudinal direction, 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 becomes smaller, 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 having longitudinal loading channel 6 select the design of six or eight rotors, and these rotors can only be divided into two
Group symmetric configuration is in the both sides of longitudinal loading channel 6.
In specific embodiment is illustrated, the both sides of longitudinal loading channel 6 are symmetrically arranged that there are four cantilever 3, electronic nothings
Man-machine fuselage 1 is generally elongated to be parallel to the longitudinal loading channel 6 and sets.In a specific embodiment, fuselage 1
Front end be provided with can carry photoelectricity hang the connection structure (not shown) in storehouse 7.In another specific embodiment, fuselage 1
Lower part be provided with can carry arm discharge cylinder 8 connection structure (not shown), for example, the length of load path 6 along longitudinal direction
Two or more arm discharge cylinders 8 can be arranged in parallel in degree direction, wherein the arm discharge cylinder 8 can be specially guided missile hair
Shooting cylinder or rocket bomb transmitting cylinder, since 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 carried intuitively by being parallel to
The mode of the length direction setting of lotus channel 6 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 shown in the figure, the both sides of longitudinal loading channel 6 are symmetrically arranged, there are one undercarriage 2, undercarriages
2 include two montants 21 for connecting fuselage 1 and are set to the cross bar 22 of the end of montant 21, the upper end difference of two montants 21
It is connected by the first connecting sleeve 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 connecting sleeve 212.Also that is, undercarriage 2 needs to carry entire 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
Putting natively needs 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 machine
The connected position of body 1 merges in same position, can simplify structure design, reduces construction weight.It likewise, can also be preferably military
Device launching tube 8 and the connection structure of fuselage 1 be located at position that cantilever 3 is connected with fuselage 1 (as shown in figure 3, arm discharge cylinder 8 with
Fuselage 1 is there are two link position, to keep the gravity balance of launching tube), it can equally simplify structure design, reduce construction weight
Further, two montants 21 positioned at the undercarriage 2 of lower section the same side of fuselage 1 are 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 cantilever 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 is provided as the link position of two montants 21 of the undercarriage 2 of the same side, can be in undercarriage 2
Two montants 21 in the case where ensureing structural strength and mitigating construction weight, be arranged in as possible at a distance of maximum position, with
Maximum structural stability is provided.For the prior art, the top of undercarriage 2 is set spacing more by the application as possible
Far, the interval between two montants 21 is also maximum, can provide space as big as possible for carry.
In addition, the interference problem due to also needing to consider 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, with
Concede arrangement of certain space in order to arm discharge cylinder 8.Also that is, the montant 21 of undercarriage 2 is in the position of arm discharge cylinder 8
A radian is bent, to concede the space of arrangement arm discharge cylinder 8.
By the above-mentioned layout of the application, in addition to increasing longitudinal carry between two montants 21 by same undercarriage 2
Except space, also by way of radian, lateral carry space will be conceded between two undercarriages 2 of 1 both sides of fuselage, thus
Longer and broader longitudinal loading channel 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, root is shown in Fig. 4
According to the schematic diagram of the electronic unmanned plane undercarriage of the specific embodiment of the application；Electronic nothing shown in Fig. 4 is shown in Fig. 5
The decomposition perspective view of man-machine undercarriage.
As shown in the figure, in the specific embodiment of the application, the lower end of two montants 21 of undercarriage 2 passes through respectively
Second connecting sleeve 212 is connected to the both ends of cross bar 22, and the second connecting sleeve 212 is tee-joint sleeve form, the 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 casing 213.Using tee-joint sleeve form
The second connecting sleeve 212 be preferably made of metal easy to process, such as be made of aluminium alloy.And tee-joint sleeve also allows for leading to
Cross screw connection montant 21 and cross bar 22, it is simple in structure and be easy to manufacture and assemble, reduce the life that cost improves unmanned plane
Produce efficiency.Upper curved casing 213 can be made of nonmetallic fiberglass or Carbon fibe, to form cunning at the both ends of cross bar 22
Sledge structure avoids 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, end that montant 21 is connected with cross bar 22 formed there are one perpendicular to
The bending part 215 on ground, the bending part 215 are inserted vertically into the upper end of the second connecting sleeve 212.Unmanned plane docks at ground
When face, support force of the cross bar 22 by ground upwardly, setting can be by this support force perpendicular to ground for bending part 215
Montant 21 is passed up to, avoids montant 21 and the excessive generation of stress of the second connecting sleeve 212 of the link position of cross bar 22
Fatigue.
In addition, just it has been observed that due to the second connecting sleeve 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 the decomposition view of Fig. 5 in 5).When unmanned plane land,
When montant 21 deforms outward, cross bar 22 moves horizontally outward, and the second connecting sleeve 212 is in the bending part perpendicular to ground
Translation is kept under the action of 215 without twisting, thus the screw hole between the second connecting sleeve 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 connecting sleeve 212 of tee-joint sleeve form, when each unmanned plane lands,
Second connecting sleeve 212 all can be with the deformation transformation of montant 21 and the angle on ground, so as to lead to the second connecting sleeve 212
It twists, reversed torsion can be such that the screw hole between the second connecting sleeve 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
It comes off in the screw hole of destruction, undercarriage will soon damage.Therefore, the application is due to being provided with the bending part perpendicular to ground
215, reliability and the service life of undercarriage can be improved, is conducive to the safety operation of unmanned plane.
Further, yielding rubber pipe 214 can also be socketed on cross bar 22, buffers to protect to provide when landing
Undercarriage is protected, avoids unmanned plane malformation.
In conclusion the electronic unmanned plane of the application below fuselage by setting a longitudinal loading do not blocked to lead to
Undercarriage is set to the both sides of longitudinal loading channel by road, and setting photoelectricity can be facilitated 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 range of machine.In addition, the application is also by optimizing the layout of undercarriage, two montants of same undercarriage are remote as possible
From arrangement to increase longitudinal carry space, by way of radian, lateral extension will be conceded between two undercarriages of fuselage both sides
Space is carried, thus longer and broader longitudinal loading channel can be provided, can longitudinally obtain larger range of load in fuselage
Lotus mount point 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 connecting sleeve
Form is simple in structure and be easy to manufacture and assemble convenient for being attached by screw, reduces the life that cost improves unmanned plane
Produce efficiency.
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 combined with each other 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 under the premise of the design and principle for not departing from the utility model,
Modification and combination should all belong to the range of the utility model protection.
Claims (9)
1. a kind of electronic unmanned plane undercarriage, for being mounted on the lower section both sides of the fuselage of electronic unmanned plane (1), the electronic nothing
Man-machine fuselage (1) is connected with multiple cantilevers (3), and each cantilever (3) supports that there are one motor (4), the equal bands of each motor (4)
There is a propeller (5), there are one longitudinal loading channel (6), the fuselage (1) is elongated parallel for setting below the fuselage (1)
It is set in the longitudinal loading channel (6), it is characterised in that：The both sides of the longitudinal loading channel (6) have been symmetrically arranged
One undercarriage (2), the montant (21) and be set to institute that the undercarriage (2) connects the fuselage (1) including two
State the cross bar (22) of the end of montant (21)；The upper end of described two montants (21) is existed respectively by the first connecting sleeve (211)
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 connecting sleeve (212) respectively.
2. electronic unmanned plane undercarriage as described in claim 1, which is characterized in that second connecting sleeve (212) is three
Logical barrel forms, the upper end are connect with the montant (21), and lower end side is connected with the cross bar (22), lower end opposite side and one
A curved casing (213) is connected.
3. electronic unmanned plane undercarriage as claimed in claim 2, which is characterized in that the lower end of the montant (21) is formed with one
A bending part (215) perpendicular to ground, the bending part (215) are inserted vertically into the upper end of the second connecting sleeve (212).
4. electronic unmanned plane undercarriage as described in claim 1, which is characterized in that same positioned at the lower section of the fuselage (1)
What two montants (21) of the undercarriage (2) of side were connected respectively in the two of spaced furthest cantilevers (3) with the fuselage (1)
Position is connected with the fuselage (1).
5. electronic unmanned plane undercarriage as described in claim 1, which is characterized in that the front end of the fuselage (1) is provided with can
Carry photoelectricity hangs the connection structure of storehouse (7).
6. electronic unmanned plane undercarriage as described in claim 1, which is characterized in that the lower part of the fuselage (1) is provided with can
The connection structure of carry arm discharge cylinder (8).
7. electronic unmanned plane undercarriage as claimed in claim 6, which is characterized in that along the length of the longitudinal loading channel (6)
Two or more arm discharge cylinders (8) can be arranged in parallel in degree direction.
8. electronic unmanned plane undercarriage as claimed in claims 6 or 7, which is characterized 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, which is characterized in that be socketed on the cross bar (22)
Yielding rubber pipe (214).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721345399.2U CN207550494U (en) | 2017-10-18 | 2017-10-18 | A kind of electronic unmanned plane undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721345399.2U CN207550494U (en) | 2017-10-18 | 2017-10-18 | A kind of electronic unmanned plane undercarriage |
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| Publication Number | Publication Date |
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| CN207550494U true CN207550494U (en) | 2018-06-29 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107600391A (en) * | 2017-10-18 | 2018-01-19 | 沈阳旋飞航空技术有限公司 | A kind of electronic unmanned plane undercarriage |
| CN109733596A (en) * | 2019-02-19 | 2019-05-10 | 沈阳无距科技有限公司 | Unmanned plane |
| CN111661337A (en) * | 2020-06-22 | 2020-09-15 | 安徽九洲农业科技有限公司 | Agricultural unmanned aerial vehicle mounting device |
| CN113602525A (en) * | 2021-08-25 | 2021-11-05 | 成都飞机工业（集团）有限责任公司 | Flexible support method for catapult-assisted take-off unmanned aerial vehicle full-aircraft static test |
-
2017
- 2017-10-18 CN CN201721345399.2U patent/CN207550494U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107600391A (en) * | 2017-10-18 | 2018-01-19 | 沈阳旋飞航空技术有限公司 | A kind of electronic unmanned plane undercarriage |
| CN109733596A (en) * | 2019-02-19 | 2019-05-10 | 沈阳无距科技有限公司 | Unmanned plane |
| CN111661337A (en) * | 2020-06-22 | 2020-09-15 | 安徽九洲农业科技有限公司 | Agricultural unmanned aerial vehicle mounting device |
| CN111661337B (en) * | 2020-06-22 | 2021-08-06 | 安徽九洲农业科技有限公司 | Agricultural unmanned aerial vehicle mounting device |
| CN113602525A (en) * | 2021-08-25 | 2021-11-05 | 成都飞机工业（集团）有限责任公司 | Flexible support method for catapult-assisted take-off unmanned aerial vehicle full-aircraft static test |
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| GR01 | Patent grant | ||
| GR01 | Patent grant |