CN206502039U - Bogey and aircraft - Google Patents
Bogey and aircraft Download PDFInfo
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- CN206502039U CN206502039U CN201720007708.9U CN201720007708U CN206502039U CN 206502039 U CN206502039 U CN 206502039U CN 201720007708 U CN201720007708 U CN 201720007708U CN 206502039 U CN206502039 U CN 206502039U
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- bogey
- aircraft
- inertial measurement
- positioning component
- head
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Abstract
The utility model provides a kind of bogey, and the bogey is used for the fuselage for being installed on aircraft, and the bogey includes：Head, avoidance positioning component and inertial measurement cluster for installing the aircraft；And dampening assembly, it is installed on the head, and the head is installed on by the dampening assembly on the fuselage of the aircraft.By head so that being to be rigidly connected between avoidance positioning component and inertial measurement cluster, and avoidance positioning component also carries out shock-absorbing with inertial measurement cluster using same dampening assembly, ensure that data that avoidance positioning component and inertial measurement cluster feed back being capable of precise synchronization, the problem of effective solution avoidance positioning component and the inconsistent data that inertial measurement cluster feeds back, ensure the flight attitude of aircraft, enable aircraft smooth flight, improve satisfaction when user uses.The utility model additionally provides a kind of aircraft.
Description
Technical field
The utility model is related to aircraft devices technical field, more particularly to a kind of bogey and aircraft.
Background technology
For current aircraft, carry-on binocular head is typically fixed on the fuselage of aircraft,
Binocular head is not come out by damping, and the Inertial Measurement Unit being engaged with binocular head is then handled by damping.So
The data that may result in binocular head and Inertial Measurement Unit feedback are unable to precise synchronization, and then the figure that binocular head is obtained
As inconsistent with the image information of Inertial Measurement Unit feedback so that aircraft is in flight in the presence of the phenomenon that flight is unstable, shadow
Ring the flight attitude of aircraft, and then the satisfaction for influenceing user to use.
Utility model content
Based on this, it is necessary to which the data fed back for binocular head and the inertial measurement cluster of current aircraft can not be same
The problem of step there is provided a kind of bogey for the data precise synchronization for enabling to ocular head and inertial measurement cluster to feed back, together
When a kind of aircraft containing above-mentioned bogey is also provided.
Above-mentioned purpose is achieved through the following technical solutions：
A kind of bogey, the bogey is used for the fuselage for being installed on aircraft, and the bogey includes：
Head, avoidance positioning component and inertial measurement cluster for installing the aircraft；And
Dampening assembly, is installed on the head, and the head is installed on the aircraft by the dampening assembly
Fuselage on.
In one of the embodiments, the head includes main body rack and connecting bracket, and the inertial measurement cluster is set
It is placed on the main body rack, the avoidance positioning component is arranged in the connecting bracket；
The connecting bracket is fixedly connected or is structure as a whole with the main body rack.
In one of the embodiments, the dampening assembly is installed on the main body rack.
In one of the embodiments, be further provided with circuit board on the main body rack, the circuit board with it is described
Inertial measurement cluster is electrically connected, and the inertial measurement cluster is installed on the main body rack by the circuit board.
In one of the embodiments, the circuit board is also electrically connected with the avoidance positioning component.
In one of the embodiments, the dampening assembly is arranged on the circuit board.
In one of the embodiments, the center of the vertical curve where the center of gravity of the bogey and the dampening assembly
The vertical curve at place is conllinear.
In one of the embodiments, the dampening assembly includes multiple shock absorber parts, and multiple shock absorber parts are uniformly distributed.
In one of the embodiments, the quantity of the shock absorber part is four, and four shock absorber parts are square distribution,
And four shock absorber parts are arranged at four square corners.
In one of the embodiments, the bogey also includes installing plate, and the installing plate is installed on the damping
On component, the bogey is installed on by the installing plate on the fuselage of the aircraft.
In one of the embodiments, the quantity of the installing plate is multiple, and multiple installing plates correspond to one respectively
Or multiple shock absorber parts are set.
In one of the embodiments, the head also includes being used to install the shooting of the main camera assembly of the aircraft
Support；
The main body rack is fixedly connected or is structure as a whole with the shooting support.
In one of the embodiments, the avoidance positioning component is binocular head, and the connecting bracket includes symmetrically setting
Two parts of the main body rack both sides are placed in, the binocular head is respectively arranged on described two parts.
A kind of bogey, including head, avoidance positioning component, inertial measurement cluster and dampening assembly are further related to, it is described
Avoidance positioning component, the inertial measurement cluster may be contained within the head with the dampening assembly.
In one of the embodiments, the head includes main body rack and connecting bracket, and the inertial measurement cluster is set
It is placed on the main body rack, the avoidance positioning component is arranged in the connecting bracket；
The connecting bracket is fixedly connected or is structure as a whole with the main body rack.
In one of the embodiments, the dampening assembly is installed on the main body rack, for connecting the carrying
Device and the firmware used cooperatively with the bogey.
In one of the embodiments, the bogey also includes the circuit board being arranged on the main body rack, institute
Circuit board is stated to electrically connect with the inertial measurement cluster, and the inertial measurement cluster is installed on the master by the circuit board
On body support frame.
In one of the embodiments, the dampening assembly is arranged on the circuit board.
In one of the embodiments, the bogey also includes the main camera assembly being arranged on the head.
In one of the embodiments, the head also includes shooting support, and the main camera assembly is arranged at described take the photograph
As on support；The main body rack is fixedly connected or is structure as a whole with the shooting support.
Further relate to a kind of aircraft, including fuselage and the bogey described in any technical characteristic, the carrying as described above
Device is installed on the fuselage.
In one of the embodiments, it is provided with the fuselage and flies control plate, the winged electrical connection of control plate or communication connection
To inertial measurement cluster.
In one of the embodiments, the bogey is installed on bottom surface or the week side of boss of the fuselage.
The beneficial effects of the utility model are：
Bogey of the present utility model, structure design advantages of simple can make the avoidance positioning component of aircraft with being used to
Property measurement assembly be installed on head, i.e., setting up connection between avoidance positioning component and inertial measurement cluster by head closes
System, so enables to the connection between avoidance positioning component and inertial measurement cluster to be rigidly connected, it is ensured that avoidance positioning group
Part is consistent with the data that inertial measurement cluster feeds back, and then ensures the data of avoidance positioning component and the number of inertial measurement cluster
According to precise synchronization, it is ensured that the flight attitude of aircraft so that aircraft flight is steady, satisfaction when user uses is improved.Together
When, head is installed on the fuselage of aircraft by dampening assembly, so enables to avoidance positioning component and inertia measurement group
Part simultaneously shock-absorbing, with ensure inertial measurement cluster obtain view data effect, it is to avoid mechanical oscillation influence inertial measurement cluster
Dysfunction so that the data precise synchronization of avoidance positioning component and inertial measurement cluster.Furthermore, avoidance positioning component and inertia
Measurement assembly shares a head and dampening assembly, additionally it is possible to reduces the quantity of part, reduces the volume of bogey, mitigates
The weight of bogey, extends the flight time of aircraft, improves the security of aircraft flight.Carrying of the present utility model
Device is caused to be rigidly connected between avoidance positioning component and inertial measurement cluster by head, and avoidance positioning component and inertia
Measurement assembly also carries out shock-absorbing using same dampening assembly, it is ensured that the data energy that avoidance positioning component feeds back with inertial measurement cluster
The problem of enough precise synchronizations, effective solution avoidance positioning component and inconsistent data that inertial measurement cluster feeds back, it is ensured that fly
The flight attitude of row device so that aircraft being capable of smooth flight, satisfaction when raising user uses.
Because bogey has above-mentioned technique effect, including the aircraft of above-mentioned bogey also has corresponding skill
Art effect.
Brief description of the drawings
Fig. 1 is connected for head in the bogey of the embodiment of the utility model one with avoidance positioning component and main camera assembly
Stereogram；
The front view structure that Fig. 2 is connected for head in the bogey shown in Fig. 1 with avoidance positioning component and main camera assembly
Schematic diagram；
The backsight structure that Fig. 3 is connected for head in the bogey shown in Fig. 1 with avoidance positioning component and main camera assembly
Schematic diagram；
Fig. 4 is installed on the stereogram on head for circuit board in the bogey shown in Fig. 1 with inertial measurement cluster；
Fig. 5 is the stereogram for installing dampening assembly in the bogey shown in Fig. 4 on circuit board；
Fig. 6 is installed on the stereogram on dampening assembly for installing plate in the bogey shown in Fig. 5；
Fig. 7 is installed on the backsight structural representation on dampening assembly for installing plate in the bogey shown in Fig. 6；
Wherein：
100- bogeys；
110- heads；
111- main body racks；
112- connecting brackets；
113- images support；
120- avoidance positioning components；
130- inertial measurement clusters；
140- dampening assemblies；
141- shock absorber parts；
150- circuit boards；
160- installing plates；
The main camera assemblies of 170-.
Embodiment
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, by the following examples, and tie
Accompanying drawing is closed, bogey of the present utility model and aircraft are further elaborated.It should be appreciated that described herein
Specific embodiment only to explain the utility model, is not used to limit the utility model.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width
Degree ", " thickness ", " on ", " under ", "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer ", " axle
To ", " radial direction ", the orientation of the instruction such as " circumference " or position relationship be based on orientation shown in the drawings or position relationship, be only for
It is easy to description the utility model and simplifies describe, rather than to indicate or imply that signified device or element must have specific
Orientation, with specific azimuth configuration and operation, therefore it is not intended that to limitation of the present utility model.
In addition, term " first ", " second " are only used for describing purpose, and it is not intended that indicating or implying relative importance
Or the implicit quantity for indicating indicated technical characteristic.Thus, define " first ", the feature of " second " can express or
Implicitly include at least one this feature.In description of the present utility model, " multiple " are meant that at least two, such as two
It is individual, three etc., unless otherwise specifically defined.
In the utility model, unless otherwise clearly defined and limited, term " installation ", " connected ", " connection ", " Gu
It is fixed " etc. term should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integrally；Can be
Mechanically connect or electrically connect or can communicate each other；Can be joined directly together, the indirect phase of intermediary can also be passed through
Even, can be two element internals connection or two elements interaction relationship, unless otherwise clear and definite restriction.For this
For the those of ordinary skill in field, concrete meaning of the above-mentioned term in the utility model can be understood as the case may be.
Referring to Fig. 1 and Fig. 5, a kind of bogey 100 that the utility model is provided includes head 110 and dampening assembly 140.
Head 110 is that the avoidance positioning component 120 and inertial measurement cluster 130 of aircraft are respectively mounted for playing carrying supporting role
In on head 110.The annexation that head 110 can be set up between avoidance positioning component 120 and inertial measurement cluster 130,
That is, avoidance positioning component 120 is connected with inertial measurement cluster 130 by head 110, so ensure that avoidance positioning group
Connection between part 120 and inertial measurement cluster 130 ensures that the data of avoidance positioning component 120 can be rigidly connected
With the data precise synchronization of inertial measurement cluster 130, to ensure the avoidance performance of avoidance positioning component 120, and then ensure flight
Device is had a smooth flight, and improves the security of aircraft flight.Meanwhile, dampening assembly 140 is also installed on head 110, and head 110
It is installed on by dampening assembly 140 on the fuselage of aircraft.Dampening assembly 140 can play a part of damping, to avoid flight
The vibration of device causes the dysfunction of inertial measurement cluster 130, it is ensured that obtains the accuracy of data, and then ensures inertial measurement cluster
130 performance.Because avoidance positioning component 120 and inertial measurement cluster 130 are mounted on head 110, damping
Component 140 is also mounted on head 110, so ensure that avoidance positioning component 120 passes through with inertial measurement cluster 130
Same dampening assembly 140 carries out damping, and then the data for feeding back avoidance positioning component 120 are fed back with inertial measurement cluster 130
Data it is consistent.
Furthermore, inertial measurement cluster 130 of the present utility model shares same head 110 with avoidance positioning component 120 and carried out
Support connection, while ensureing that feedback data is consistent, reduces the quantity of the part of bogey 100, mitigates bogey
100 weight so that the compact conformation of bogey 100, and then reduce the space that bogey 100 takes so that carrying dress
The need for putting 100 and more meeting small-sized or minute vehicle, mitigate the heavy burden of aircraft, extend the endurance of aircraft, carry
The security of high aircraft flight, satisfaction when lifting user uses.Also, avoidance positioning component 120 and inertia measurement group
Part 130 shares a dampening assembly 140 and carries out shock-absorbing, reduces the quantity of dampening assembly 140, saves assembly process, improves dress
With efficiency, simultaneously, additionally it is possible to reduce the volume of bogey 100, mitigate the weight of bogey 100, extend flying for aircraft
The row time, improve the security of aircraft flight.
Bogey 100 of the present utility model is installed on the fuselage of aircraft, and bogey 100 can position avoidance
Component 120 with inertial measurement cluster 130 is rigid is fixed together, and then ensure avoidance positioning component 120 and inertia measurement group
Data precise synchronization between part 130, meanwhile, avoidance positioning component 120 passes through same dampening assembly with inertial measurement cluster 130
140 carry out damping, ensure that avoidance positioning component 120 is consistent with the data that inertial measurement cluster 130 feeds back, to ensure to fly
Row device is had a smooth flight, and then ensures the flight attitude of aircraft, is extended the flight time of aircraft, is improved the peace of aircraft flight
Quan Xing, satisfaction when lifting user uses.Inertial measurement cluster 130 is capable of the operation posture of sense aircraft, so that flight
The data of the operation posture of device are consistent with the data that capturing element feeds back, it is ensured that aircraft flight is steady, improve aircraft
Security during flight.Avoidance positioning component 120 is positioned for avoidance, to avoid aircraft impacting object, is improved aircraft and is flown
Security during row.
Referring to Fig. 1 to Fig. 3, specifically, head 110 includes main body rack 111 and connecting bracket 112.Inertial measurement cluster
130 are arranged on main body rack 111, and avoidance positioning component 120 is arranged in connecting bracket 112.Connecting bracket 112 and main body branch
Frame 111 is fixedly connected or is structure as a whole.So it ensure that to be rigidly connected between main body rack 111 and connecting bracket 112,
And then ensure that the inertial measurement cluster 130 on main body rack 111 is rigidity with the avoidance positioning component 120 in connecting bracket 112
Connection, is relatively fixed the position of inertial measurement cluster 130 and binocular support.That is, inertial measurement cluster 130 and avoidance
Rigidly fixed between positioning component 120, so ensure that avoidance positioning component 120 feeds back with inertial measurement cluster 130
Data it is consistent so that data and the back-to-back running appearance of inertial measurement cluster 130 of the feedback avoidance positioning of avoidance positioning component 120
The data of state can precise synchronization, and then ensure aircraft flight attitude, it is ensured that aircraft flight is steady.Meanwhile, connection branch
Frame 112 is fixedly connected or is structure as a whole with main body rack 111 and can also ensure that between connecting bracket 112 and main body rack 111
It is reliable for connection, then ensure avoidance positioning component 120 and the rigidly connected reliability of inertial measurement cluster 130, extension flight
The flight time of device, improve the security of aircraft flight.
Referring to Fig. 5, as a kind of embodiment, dampening assembly 140 is installed on main body rack 111.Dampening assembly 140
Cushioning effect can be played, damping mainly is carried out to avoidance positioning component 120 and inertial measurement cluster 130, and, it is ensured that keep away
Hinder positioning component 120 and damping is carried out by same dampening assembly 140 with inertial measurement cluster 130, so ensure that inertia is surveyed
Measure component 120 it is consistent with the running orbit of avoidance positioning component 120, it is ensured that the flight attitude of the aircraft of acquisition it is accurate
Property, and then ensure the data precise synchronization that avoidance positioning component 120 feeds back with inertial measurement cluster 130.While dampening assembly 140
It can also ensure that the shock-proof effect of inertial measurement cluster 130, it is to avoid the mechanical oscillation of the fuselage of aircraft cause inertia measurement group
The dysfunction of part 130, then ensures the flight attitude of aircraft, makes aircraft flight steady.
Referring to Fig. 4, as a kind of embodiment, circuit board 150, circuit board are further provided with main body rack 111
150 are electrically connected with inertial measurement cluster 130, and inertial measurement cluster 130 is installed on main body rack 111 by circuit board 150.Electricity
Road plate 150 can control the operation posture of the sense aircraft of inertial measurement cluster 130.Circuit board 150 enables to inertia measurement
The data feedback of the flight attitude for the aircraft that component 130 is detected gives a control system, and control system is adjusted according to the data of feedback
Save the flight attitude of aircraft.Further, circuit board 150 is also electrically connected with avoidance positioning component 120.Circuit can so be made
The control avoidance of plate 150 positioning component 120 carries out avoidance positioning performance detection, and the data feedback that avoidance is positioned, to ensure to fly
Security during row device flight.Circuit board 150 can also make the data feedback that avoidance positioning component 120 positions avoidance to control
System.Due to being rigidly connected between avoidance positioning component 120 and inertial measurement cluster 130, the avoidance that such controller is received
The data that data and the inertial measurement cluster 130 that positioning component 120 feeds back feed back can precise synchronization, then aircraft is flown
The steady security for improving aircraft flight of row, lifts satisfaction during for using.If the number that avoidance positioning component 120 feeds back
Inconsistent according to the data fed back with inertial measurement cluster 130, then deflection flight or the unstable phenomenon of flight, shadow occurs in aircraft
Ring the security of aircraft flight, and then the satisfaction for influenceing user to use.
In an embodiment of the present utility model, when the area of circuit board 150 is smaller, circuit board 150 is simply possible to use in will be used
Property measurement assembly 130 is installed to main body rack 111, circuit board 150 can only partial occlusion main body rack 111, now, dampening assembly
140 are arranged on main body rack 111, to ensure the damping performance of inertial measurement cluster 130 and avoidance positioning component 120, carrying
Device 100 is connected by the dampening assembly 140 on main body rack 111 with the fuselage of aircraft.Certainly, it is of the present utility model again
In one embodiment, when the area of circuit board 150 is more or less the same with the area of main body rack 111, circuit board 150, which is removed, to be used for inertia
Measurement assembly 130 is installed to outside main body rack 111, moreover it is possible to play a part of carrying dampening assembly 140, now, dampening assembly 140
It is arranged on circuit board 150, to ensure the damping performance of inertial measurement cluster 130 and avoidance positioning component 120, bogey
100 are connected by the dampening assembly 140 on circuit board 150 with the fuselage of aircraft.Meanwhile, circuit board 150 and main body rack 111
Between can be connected through a screw thread part and be connected, to ensure that circuit board 150 is fixed reliably, and then ensure on circuit board 150
It is to be rigidly connected between inertial measurement cluster 130 and avoidance positioning component 120.
Referring to Fig. 5, yet further, the center institute of vertical curve and dampening assembly 140 where the center of gravity of bogey 100
Vertical curve it is conllinear.It so ensure that the balance of bogey 100, it is to avoid bogey 100 glances off and influences to hold
Carry the avoidance locating effect for putting shooting effect and avoidance positioning component 120 that main camera assembly 170 is installed on 100.Meanwhile, hold
Carry and put 100 and be installed on by dampening assembly 140 when on the fuselage of aircraft, it is necessary to ensure that the center of bogey 100 is close
The position of centre of gravity of the fuselage of aircraft, it is ensured that the shooting angle of main camera assembly 170, and then ensure shooting effect.Meanwhile, also
Ensure that main camera assembly 170 avoids the fuselage and propeller of aircraft with avoidance positioning component 120, to avoid main camera assembly
170 interfere with the fuselage or propeller of avoidance positioning component 120 and aircraft, improve the security of aircraft flight.
As a kind of embodiment, dampening assembly 140 includes multiple shock absorber parts 141, and multiple shock absorber parts 141 uniformly divide
Cloth.Production cost can be so saved, while mitigating the weight of dampening assembly 140, then mitigates the weight of head 110, extension
The flight time of aircraft.Shock absorber part 141 is for playing cushioning effect, to ensure avoidance positioning component 120 and inertia measurement
The shockproof properties of component 130, it is ensured that avoidance positioning component 120 is consistent with the data that inertial measurement cluster 130 feeds back, and then protects
Demonstrate,prove aircraft flight steady.Further, shock absorber part 141 is cylindrical, spherical, kidney-shaped or taper are set.It can so make
Shock absorber part 141 plays a part of shockproof cushioning, it is ensured that ensure the shock resistance of avoidance positioning component 120 and inertial measurement cluster 130
Energy.In the present embodiment, the quantity of shock absorber part 141 is four, and four shock absorber parts 141 are square to set and are distributed in square four
Individual corner, and shock absorber part 141 is spherical.Also, in an embodiment of the present utility model, four corners of main body rack 111
On be respectively arranged with the mounting holes of four installation shock absorber parts 141, shock absorber part 141 is installed on mounting hole and protrudes main body rack 111
Surface set, in order to which the fuselage with unmanned plane is connected.In another embodiment of the present utility model, the four of circuit board 150
The mounting hole of four installation shock absorber parts 141 is respectively arranged with individual corner, shock absorber part 141 is installed on mounting hole and protrudes circuit board
150 surface is set, in order to which the fuselage with unmanned plane is connected.Certainly, it is multiple in other embodiment of the present utility model
Shock absorber part 141 connects as one structure, can so save assembly process, improves efficiency of assembling.
Referring to Fig. 6 and Fig. 7, as a kind of embodiment, bogey 100 also includes installing plate 160, installing plate 160
It is installed on dampening assembly 140, dampening assembly 140 is installed on the fuselage of aircraft by installing plate 160.Installing plate 160 is
For being installed on dampening assembly 140, dampening assembly 140 is installed on the fuselage of aircraft, dampening assembly 140 is realized
With the connection of the fuselage of aircraft.Installing plate 160 ensure that bogey 100 is installed reliably.Further, installing plate 160
Quantity to be multiple, multiple installing plates 160 connect one or more shock absorber part 141 respectively, and installing plate 160 can also be with flying
The fuselage connection of row device.It so ensure that and connect reliable between installing plate 160 and the fuselage of aircraft.In the present embodiment,
The quantity of installing plate 160 is two, and two installing plates 160 connect two shock absorber parts 141 respectively, the one of spherical shock absorber part 141
End be installed in mounting hole, the other end of spherical shock absorber part 141 is installed on installing plate 160, be provided with installing plate 160 with
The connecting portion of the fuselage connection of aircraft, to ensure to connect reliable between bogey 100 and the fuselage of aircraft.Certainly, exist
In other embodiment of the present utility model, multiple installing plates 160 connect as one structure, can so save assembly process,
Improve efficiency of assembling.
Referring to Fig. 1 to Fig. 3, as a kind of embodiment, head 110 also includes shooting support 113, images support 113
Main camera assembly 170 for installing aircraft.Main camera assembly 170 is the shoot function for realizing aircraft.Main body
Support 111 is fixedly connected or is structure as a whole with shooting support 113.It so ensure that main body rack 111 and shooting support 113
Between the reliability that connects.Further, avoidance positioning component 120 is binocular head.It is former that binocular head is mainly based upon parallax
Manage and utilize binocular head in the two images of different position acquisition objects, and it is inclined by calculating the position between image corresponding points
Difference obtains the three-dimensional geometric information of object.Based on this, binocular head can obtain the three-dimensional geometric information of object, so that aircraft
Being capable of forward location and avoidance, it is to avoid impacting object during aircraft flight, it is ensured that the flight safety of aircraft.Also, connection branch
Frame 112 includes the two parts for being symmetricly set in the both sides of main body rack 111, and binocular head is respectively arranged on two parts.In order to protect
The shooting angle for demonstrate,proving the two-part binocular head of connecting bracket 112 is consistent, and ensures binocular head and inertial measurement cluster
The data precise synchronization of 130 feedbacks, two parts, which are symmetrical arranged, ensure that binocular head is in same level position, it is ensured that binocular
The shooting angle of camera lens is consistent, and then ensures that the movement locus of binocular head is consistent, so ensure that binocular head is accurate
The three-dimensional geometric information of true acquisition object, effectively plays a part of forward location and avoidance, and then ensure aircraft flight
Security.Binocular head is respectively arranged on two parts to ensure the security of aircraft flight, and then ensures to be located at two
/ main camera assembly 170 shooting effect.
As a kind of embodiment, two-part end opens up the mounting groove for installing binocular head, binocular head
It is installed in mounting groove.So the installation of binocular head can be easy to fix.Meanwhile, connecting bracket 112 is made up of metal material,
The precision of connecting bracket 112 is so ensure that, and then so that the shooting angle of the binocular head in connecting bracket 112 is identical.
Further, bogey 100 also includes fixture, and fixture is arranged in mounting groove.Fixture is double for installing and fixing
Ocular head, makes binocular head be installed in mounting groove.Fixture is connected through a screw thread part and is fixed in mounting groove, so that binocular
Position of the head on binocular support is fixed, and then ensures that the position of binocular head is fixed, and makes the shooting angle of binocular head consistent.
Referring to Fig. 1 and Fig. 5, the utility model also provides a kind of bogey 100, and the bogey 100 includes head
110th, avoidance positioning component 120, inertial measurement cluster 130 and dampening assembly 140.Head 110 is for playing carrying supporting role
, avoidance positioning component 120 and inertial measurement cluster 130 are mounted on head 110.Head 110 can set up avoidance positioning
Annexation between component 120 and inertial measurement cluster 130, that is to say, that avoidance positioning component 120 and inertial measurement cluster
130 are connected by head 110, and it is firm for so ensure that the connection between avoidance positioning component 120 and inertial measurement cluster 130
Property connection, and then ensure avoidance positioning component 120 data can be with inertial measurement cluster 130 data precise synchronization, to protect
Demonstrate,prove the avoidance performance of avoidance positioning component 120.Meanwhile, dampening assembly 140 is also installed on head 110, for connecting carrying dress
Put 100 and the firmware used cooperatively with bogey 100.Dampening assembly 140 can play a part of damping, to avoid aircraft
Vibration cause the dysfunction of inertial measurement cluster 130, it is ensured that obtain data accuracy, and then ensure inertial measurement cluster
130 performance.Because avoidance positioning component 120 and inertial measurement cluster 130 are mounted on head 110, damping
Component 140 is also mounted on head 110, so ensure that avoidance positioning component 120 passes through with inertial measurement cluster 130
Same dampening assembly 140 carries out damping, and then the data for feeding back avoidance positioning component 120 are fed back with inertial measurement cluster 130
Data it is consistent.Specifically, inertial measurement cluster 130 includes accelerometer and gyroscope, in order to flying for sense aircraft
Row posture, it is ensured that aircraft flight is steady.It is aircraft with the firmware that bogey 100 is used cooperatively in the utility model.
Certainly, in other embodiment of the present utility model, the firmware used cooperatively with bogey 100 can be with other equipment.
Furthermore, inertial measurement cluster 130 of the present utility model shares same head 110 with avoidance positioning component 120 and carried out
Support connection, while ensureing that feedback data is consistent, reduces the quantity of the part of bogey 100, mitigates bogey
100 weight so that the compact conformation of bogey 100, and then reduce the space that bogey 100 takes so that carrying dress
The need for putting 100 and more meeting small-sized or minute vehicle, mitigate the heavy burden of aircraft, extend the endurance of aircraft, carry
The security of high aircraft flight, satisfaction when lifting user uses.Also, avoidance positioning component 120 and inertia measurement group
Part 130 shares a dampening assembly 140 and carries out shock-absorbing, reduces the quantity of dampening assembly 140, saves assembly process, improves dress
With efficiency, simultaneously, additionally it is possible to reduce the volume of bogey 100, mitigate the weight of bogey 100, extend flying for aircraft
The row time, improve the security of aircraft flight.
Referring to Fig. 1 to Fig. 3, specifically, head 110 includes main body rack 111 and connecting bracket 112.Inertial measurement cluster
130 are arranged on main body rack 111, and avoidance positioning component 120 is arranged in connecting bracket 112.Connecting bracket 112 and main body branch
Frame 111 is fixedly connected or is structure as a whole.So it ensure that to be rigidly connected between main body rack 111 and connecting bracket 112,
And then ensure that the inertial measurement cluster 130 on main body rack 111 is rigidity with the avoidance positioning component 120 in connecting bracket 112
Connection, is relatively fixed the position of inertial measurement cluster 130 and binocular support.That is, inertial measurement cluster 130 and avoidance
Rigidly fixed between positioning component 120, so ensure that avoidance positioning component 120 feeds back with inertial measurement cluster 130
Data it is consistent so that data and the back-to-back running appearance of inertial measurement cluster 130 of the feedback avoidance positioning of avoidance positioning component 120
The data of state being capable of precise synchronization.Meanwhile, connecting bracket 112 is fixedly connected or is structure as a whole with main body rack 111 can also
Ensure to connect reliable between connecting bracket 112 and main body rack 111, then ensure avoidance positioning component 120 and inertia measurement group
The rigidly connected reliability of part 130.
Referring to Fig. 5, as a kind of embodiment, dampening assembly 140 is installed on main body rack 111, is held for connecting
Carry the firmware put 100 and used cooperatively with bogey 100.Dampening assembly 140 can play cushioning effect, mainly to keeping away
Hinder positioning component 120 and carry out damping with inertial measurement cluster 130, and, it is ensured that avoidance positioning component 120 and inertial measurement cluster
130 carry out damping by same dampening assembly 140, so ensure that inertial measurement cluster 120 and avoidance positioning component 120
Running orbit is consistent, and then ensures the data precise synchronization that avoidance positioning component 120 feeds back with inertial measurement cluster 130.Hold
Carry and put 100 and ensure that dampening assembly 140 can also ensure that the shock-proof effect of inertial measurement cluster 130 to aircraft simultaneously, keep away
Exempting from the mechanical oscillation of the fuselage of aircraft causes the dysfunction of inertial measurement cluster 130, then ensures the flight attitude of aircraft,
Make aircraft flight steady.
Referring to Fig. 4, as a kind of embodiment, bogey 100 also includes the circuit being arranged on main body rack 111
Plate 150, circuit board 150 is electrically connected with inertial measurement cluster 130, and inertial measurement cluster 130 is installed on main body by circuit board 150
On support 111.Circuit board 150 can control the operation posture of the sense aircraft of inertial measurement cluster 130.Set on circuit board 150
Controller is equipped with, controller is electrically connected with circuit board 150, i.e., inertial measurement cluster 130 is electrically connected by circuit board 150 and controller
Connect, so enable to the data feedback of flight attitude of the aircraft of the detection of inertial measurement cluster 130 to controller.Further
Ground, circuit board 150 is also electrically connected with avoidance positioning component 120.Circuit board 150 can be so set to control avoidance positioning component 120
Avoidance positioning performance detection, and the data feedback that avoidance is positioned are carried out, to ensure security during aircraft flight.Avoidance is determined
Hyte part 120 is electrically connected with the controller also by circuit board 150.The data feedback that avoidance positioning component 120 positions avoidance to
Controller.Due to being rigidly connected between avoidance positioning component 120 and inertial measurement cluster 130, what such controller was received keeps away
Hinder data that data and the inertial measurement cluster 130 that positioning component 120 feeds back feed back can precise synchronization, then cause aircraft
Having a smooth flight and improve the security of aircraft flight, lifting satisfaction during for using.What if avoidance positioning component 120 fed back
Data and the data that inertial measurement cluster 130 feeds back are inconsistent, then deflection flight or the unstable phenomenon of flight occurs in aircraft,
Influence the security of aircraft flight, and then the satisfaction for influenceing user to use.
In an embodiment of the present utility model, when the area of circuit board 150 is smaller, circuit board 150 is simply possible to use in will be used
Property measurement assembly 130 is installed to main body rack 111, circuit board 150 can only partial occlusion main body rack 111, now, dampening assembly
140 are arranged on main body rack 111, to ensure the damping performance of inertial measurement cluster 130 and avoidance positioning component 120, carrying
Device 100 is connected by the dampening assembly 140 on main body rack 111 with the fuselage of aircraft.Certainly, it is of the present utility model again
In one embodiment, when the area of circuit board 150 is more or less the same with the area of main body rack 111, circuit board 150, which is removed, to be used for inertia
Measurement assembly 130 is installed to outside main body rack 111, moreover it is possible to play a part of carrying dampening assembly 140, now, dampening assembly 140
It is arranged on circuit board 150, to ensure the damping performance of inertial measurement cluster 130 and avoidance positioning component 120, bogey
100 are connected by the dampening assembly 140 on circuit board 150 with the fuselage of aircraft.Meanwhile, circuit board 150 and main body rack 111
Between can be connected through a screw thread part and be connected, to ensure that circuit board 150 is fixed reliably, and then ensure on circuit board 150
It is to be rigidly connected between inertial measurement cluster 130 and avoidance positioning component 120.
Referring to Fig. 5, yet further, the center institute of vertical curve and dampening assembly 140 where the center of gravity of bogey 100
Vertical curve it is conllinear.It so ensure that the balance of bogey 100, it is to avoid bogey 100 glances off and influences to hold
Carry the avoidance locating effect for putting shooting effect and avoidance positioning component 120 that main camera assembly 170 is installed on 100.Meanwhile, hold
Carry and put 100 and be installed on by dampening assembly 140 when on the fuselage of aircraft, it is necessary to ensure that the center of bogey 100 is close
The position of centre of gravity of the fuselage of aircraft, it is ensured that the shooting angle of main camera assembly 170, and then ensure shooting effect.Meanwhile, also
Ensure that main camera assembly 170 avoids the fuselage and propeller of aircraft with avoidance positioning component 120, to avoid main camera assembly
170 interfere with the fuselage or propeller of avoidance positioning component 120 and aircraft, improve the security of aircraft flight.
As a kind of embodiment, dampening assembly 140 includes multiple shock absorber parts 141, and multiple shock absorber parts 141 uniformly divide
Cloth.Production cost can be so saved, while mitigating the weight of dampening assembly 140, then mitigates the weight of head 110, extension
The flight time of aircraft.Shock absorber part 141 is for playing cushioning effect, to ensure avoidance positioning component 120 and inertia measurement
The shockproof properties of component 130, it is ensured that avoidance positioning component 120 is consistent with the data that inertial measurement cluster 130 feeds back, and then protects
Demonstrate,prove aircraft flight steady.Further, shock absorber part 141 is cylindrical, spherical, kidney-shaped or taper are set.It can so make
Shock absorber part 141 plays a part of shockproof cushioning, it is ensured that ensure the shock resistance of avoidance positioning component 120 and inertial measurement cluster 130
Energy.In the present embodiment, the quantity of shock absorber part 141 is four, and four shock absorber parts 141 are square to set and are distributed in square four
Individual corner, and shock absorber part 141 is spherical.Also, in an embodiment of the present utility model, four corners of main body rack 111
On be respectively arranged with the mounting holes of four installation shock absorber parts 141, shock absorber part 141 is installed on mounting hole and protrudes main body rack 111
Surface set, in order to which the fuselage with unmanned plane is connected.In another embodiment of the present utility model, the four of circuit board 150
The mounting hole of four installation shock absorber parts 141 is respectively arranged with individual corner, shock absorber part 141 is installed on mounting hole and protrudes circuit board
150 surface is set, in order to which the fuselage with unmanned plane is connected.Certainly, it is multiple in other embodiment of the present utility model
Shock absorber part 141 connects as one structure, can so save assembly process, improves efficiency of assembling.
Referring to Fig. 6 and Fig. 7, as a kind of embodiment, bogey 100 also includes installing plate 160, installing plate 160
It is installed on dampening assembly 140, dampening assembly 140 is installed on the fuselage of aircraft by installing plate 160.Installing plate 160 is
For being installed on dampening assembly 140, dampening assembly 140 is installed on the fuselage of aircraft, dampening assembly 140 is realized
With the connection of the fuselage of aircraft.Installing plate 160 ensure that bogey 100 is installed reliably.Further, installing plate 160
Quantity to be multiple, multiple installing plates 160 correspond to one or more shock absorber part 141 and set respectively, and installing plate 160 can also
It is connected with the fuselage of aircraft.It so ensure that and connect reliable between installing plate 160 and the fuselage of aircraft.In the present embodiment
In, the quantity of installing plate 160 is two, and two installing plates 160 connect two shock absorber parts 141 respectively, spherical shock absorber part 141
One end is installed in mounting hole, and the other end of spherical shock absorber part 141 is installed on installing plate 160, is provided with installing plate 160
The connecting portion being connected with the fuselage of aircraft, to ensure to connect reliable between bogey 100 and the fuselage of aircraft.Certainly,
In other embodiment of the present utility model, multiple installing plates 160 connect as one structure, can so save assembler
Sequence, improves efficiency of assembling.
Further, bogey 100 also includes main camera assembly 170.Main camera assembly 170 is for realizing aircraft
Shoot function.Further, head 110 also includes shooting support 113, and shooting support 113 is used for main camera assembly 170.
Main body rack 111 is fixedly connected or is structure as a whole with shooting support 113.It so ensure that main body rack 111 and shooting branch
The reliability connected between frame 113.Further, avoidance positioning component 120 is binocular head.Binocular head, which is mainly based upon, to be regarded
Poor principle simultaneously utilizes binocular head in the two images of different position acquisition objects, and by calculating the position between image corresponding points
Put the three-dimensional geometric information that deviation obtains object.Based on this, binocular head can obtain the three-dimensional geometric information of object, so as to fly
Row device being capable of forward location and avoidance, it is to avoid impacting object during aircraft flight, it is ensured that the flight safety of aircraft.Also, even
Two parts that support 112 includes being symmetricly set in the both sides of main body rack 111 are connect, binocular head is respectively arranged on two parts.For
Ensure that the shooting angle of the two-part binocular head of connecting bracket 112 is consistent, and ensure binocular head and inertia measurement
The data precise synchronization that component 130 feeds back, two parts, which are symmetrical arranged, ensure that binocular head is in same level position, it is ensured that
The shooting angle of binocular head is consistent, and then ensures that the movement locus of binocular head is consistent, so ensure that binocular
Head accurately obtains the three-dimensional geometric information of object, effectively plays a part of forward location and avoidance, and then ensure aircraft
The security of flight.Binocular head is respectively arranged on two parts to ensure the security of aircraft flight, and then ensures to be located at
The shooting effect of main camera assembly 170 between two parts.
As a kind of embodiment, two-part end opens up the mounting groove for installing binocular head, binocular head
It is installed in mounting groove.So the installation of binocular head can be easy to fix.Meanwhile, connecting bracket 112 is made up of metal material,
The precision of connecting bracket 112 is so ensure that, and then so that the shooting angle of the binocular head in connecting bracket 112 is identical.
Further, bogey 100 also includes fixture, and fixture is arranged in mounting groove.Fixture is double for installing and fixing
Ocular head, makes binocular head be installed in mounting groove.Fixture is connected through a screw thread part and is fixed in mounting groove, so that binocular
Position of the head on binocular support is fixed, and then ensures that the position of binocular head is fixed, and makes the shooting angle of binocular head consistent.
Bogey 100 of the present utility model can make the avoidance positioning component 120 and inertial measurement cluster 130 of aircraft
It is installed on head 110, i.e., the connection set up by head 110 between avoidance positioning component 120 and inertial measurement cluster 130 is closed
System, so enables to the connection between avoidance positioning component 120 and inertial measurement cluster 130 to be rigidly connected, it is ensured that avoidance
Positioning component 120 is consistent with the data that inertial measurement cluster 130 feeds back, so ensure the data of avoidance positioning component 120 with
The data precise synchronization of inertial measurement cluster 130, it is ensured that the flight attitude of aircraft so that aircraft flight is steady, improves and uses
Satisfaction when family is used.Meanwhile, head 110 is installed on the fuselage of aircraft by dampening assembly 140, is so enabled to
Avoidance positioning component 120 and inertial measurement cluster 130 shock-absorbing simultaneously, to ensure that inertial measurement cluster 130 obtains view data
Effect, it is to avoid mechanical oscillation influence the dysfunction of inertial measurement cluster 130 so that avoidance positioning component 120 and inertia measurement group
The data precise synchronization of part 130.Furthermore, avoidance positioning component 120 shares a head 110 with inertial measurement cluster 130 and subtracted
Shake component 140, additionally it is possible to reduce the quantity of part, reduce the volume of bogey 100, alleviate the weight of bogey 100
Amount, extends the flight time of aircraft, improves the security of aircraft flight.Bogey 100 of the present utility model passes through cloud
Platform 110 causes to be rigidly connected between avoidance positioning component 120 and inertial measurement cluster 130, and avoidance positioning component 120 is with being used to
Property measurement assembly 130 also using same dampening assembly 140 carry out shock-absorbing, it is ensured that avoidance positioning component 120 and inertial measurement cluster
The data of 130 feedbacks being capable of precise synchronization, the effective number for solving avoidance positioning component 120 and the feedback of inertial measurement cluster 130
According to it is inconsistent the problem of, it is ensured that the flight attitude of aircraft so that aircraft can smooth flight, improve user's expiring when using
Meaning degree.
The utility model additionally provides the bogey 100 in a kind of aircraft, including fuselage and above-described embodiment.Carrying
Device 100 is installed on fuselage.Inertial measurement cluster 130 and avoidance that aircraft of the present utility model passes through bogey 100
Being rigidly connected for positioning component 120 ensures the data precise synchronization of feedback, effective to solve inertial measurement cluster 130 and binocular
The problem of data of head feedback are inconsistent, it is ensured that the flight attitude of aircraft so that aircraft flight is steady.
Further, it is provided with fuselage and flies control plate, is flown control plate and be electrically connected to inertial measurement cluster 130.Inertia measurement group
Part 130 is capable of the current flight posture of sense aircraft, and feeds back to controller.The initial flight of aircraft is stored in controller
Posture, if the current flight posture of aircraft is distinguished with initial flight posture, controller is passed through by inertial measurement cluster 130
The flight attitude of aircraft can be adjusted by flying control plate, so that aircraft smooth flight, improves satisfaction when user uses.
Yet further, bogey is installed on bottom surface or the week side of boss of fuselage.The master of device 100 can be so easily carried
Camera assembly 170 is shot and avoidance positioning component 120 carries out avoidance positioning, it is to avoid main camera assembly 170 photographs winged
The parts and avoidance positioning component 120 of row device touch the parts of aircraft so that aircraft is located at main camera assembly 170
Shooting blind area, it is ensured that shooting effect.
Embodiment described above only expresses several embodiments of the present utility model, and it describes more specific and detailed,
But therefore it can not be interpreted as the limitation to the utility model the scope of the claims.It should be pointed out that for the common of this area
For technical staff, without departing from the concept of the premise utility, various modifications and improvements can be made, these all belong to
In protection domain of the present utility model.Therefore, the protection domain of the utility model patent should be determined by the appended claims.
Claims (22)
1. a kind of bogey, it is characterised in that the bogey is used for the fuselage for being installed on aircraft, the carrying dress
Put including：
Head, avoidance positioning component and inertial measurement cluster for installing the aircraft；And
Dampening assembly, is installed on the head, and the head is installed on the machine of the aircraft by the dampening assembly
With.
2. bogey according to claim 1, it is characterised in that the head includes main body rack and connecting bracket,
The inertial measurement cluster is arranged on the main body rack, and the avoidance positioning component is arranged in the connecting bracket；
The connecting bracket is fixedly connected or is structure as a whole with the main body rack.
3. bogey according to claim 2, it is characterised in that the dampening assembly is installed on the main body rack
On.
4. bogey according to claim 2, it is characterised in that be further provided with circuit on the main body rack
Plate, the circuit board is electrically connected with the inertial measurement cluster, and the inertial measurement cluster is installed on by the circuit board
On the main body rack.
5. bogey according to claim 4, it is characterised in that the circuit board is also electric with the avoidance positioning component
Connection.
6. bogey according to claim 4, it is characterised in that the dampening assembly is arranged on the circuit board.
7. the bogey according to any one of claim 1 to 6, it is characterised in that where the center of gravity of the bogey
Vertical curve it is conllinear with the vertical curve where the center of the dampening assembly.
8. bogey according to claim 7, it is characterised in that the dampening assembly includes multiple shock absorber parts, multiple
The shock absorber part is uniformly distributed.
9. bogey according to claim 8, it is characterised in that the quantity of the shock absorber part is four, and four institutes
Shock absorber part is stated to be square distribution, and four shock absorber parts are arranged at four square corners.
10. bogey according to claim 8, it is characterised in that the bogey also includes installing plate, the peace
Dress plate is installed on the dampening assembly, and the bogey is installed on by the installing plate on the fuselage of the aircraft.
11. bogey according to claim 10, it is characterised in that the quantity of the installing plate is multiple, Duo Gesuo
State installing plate and correspond to one or more shock absorber part setting respectively.
12. bogey according to claim 2, it is characterised in that the head also includes being used to install the flight
The shooting support of the main camera assembly of device；
The main body rack is fixedly connected or is structure as a whole with the shooting support.
13. bogey according to claim 12, it is characterised in that the avoidance positioning component is binocular head, institute
Stating connecting bracket includes being symmetricly set in two parts of the main body rack both sides, and the binocular head is respectively arranged in described two
On part.
14. a kind of bogey, it is characterised in that including head, avoidance positioning component, inertial measurement cluster and dampening assembly,
The avoidance positioning component, the inertial measurement cluster may be contained within the head with the dampening assembly.
15. bogey according to claim 14, it is characterised in that the head includes main body rack and connection branch
Frame, the inertial measurement cluster is arranged on the main body rack, and the avoidance positioning component is arranged in the connecting bracket；
The connecting bracket is fixedly connected or is structure as a whole with the main body rack.
16. bogey according to claim 15, it is characterised in that the dampening assembly is installed on the main body rack
On, for the firmware for connecting the bogey and being used cooperatively with the bogey.
17. bogey according to claim 15, it is characterised in that the bogey also includes being arranged at the master
Circuit board on body support frame, the circuit board is electrically connected with the inertial measurement cluster, and the inertial measurement cluster passes through institute
Circuit board is stated to be installed on the main body rack.
18. bogey according to claim 17, it is characterised in that the dampening assembly is arranged at the circuit board
On.
19. bogey according to claim 15, it is characterised in that the bogey also includes being arranged at the cloud
Main camera assembly on platform.
20. bogey according to claim 19, it is characterised in that the head also includes shooting support, the master
Camera assembly is arranged on the shooting support；The main body rack is fixedly connected or is structure as a whole with the shooting support.
21. a kind of aircraft, it is characterised in that the bogey including fuselage and as described in any one of claim 1 to 20, institute
Bogey is stated to be installed on the fuselage.
22. aircraft according to claim 21, it is characterised in that be provided with the fuselage and fly control plate, the winged control
Plate electrically connects or is communicatively connected to inertial measurement cluster.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720007708.9U CN206502039U (en) | 2017-01-04 | 2017-01-04 | Bogey and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720007708.9U CN206502039U (en) | 2017-01-04 | 2017-01-04 | Bogey and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206502039U true CN206502039U (en) | 2017-09-19 |
Family
ID=59840157
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720007708.9U Withdrawn - After Issue CN206502039U (en) | 2017-01-04 | 2017-01-04 | Bogey and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206502039U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108263626A (en) * | 2017-01-04 | 2018-07-10 | 重庆零度智控智能科技有限公司 | Bogey and aircraft |
| CN110313170A (en) * | 2018-01-19 | 2019-10-08 | 深圳市大疆创新科技有限公司 | Vision mould group integration module and unmanned plane |
| WO2022061921A1 (en) * | 2020-09-28 | 2022-03-31 | 深圳市大疆创新科技有限公司 | Inertial measurement assembly and unmanned aerial vehicle |
-
2017
- 2017-01-04 CN CN201720007708.9U patent/CN206502039U/en not_active Withdrawn - After Issue
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108263626A (en) * | 2017-01-04 | 2018-07-10 | 重庆零度智控智能科技有限公司 | Bogey and aircraft |
| CN108263626B (en) * | 2017-01-04 | 2023-08-22 | 北京远度互联科技有限公司 | Bearing device and aircraft |
| CN110313170A (en) * | 2018-01-19 | 2019-10-08 | 深圳市大疆创新科技有限公司 | Vision mould group integration module and unmanned plane |
| CN110313170B (en) * | 2018-01-19 | 2021-08-31 | 深圳市大疆创新科技有限公司 | Visual module integrated module and unmanned aerial vehicle |
| US11115642B2 (en) | 2018-01-19 | 2021-09-07 | SZ DJI Technology Co., Ltd. | Integrated vision module component and unmanned aerial vehicle |
| WO2022061921A1 (en) * | 2020-09-28 | 2022-03-31 | 深圳市大疆创新科技有限公司 | Inertial measurement assembly and unmanned aerial vehicle |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Bear device and aircraft Effective date of registration: 20180102 Granted publication date: 20170919 Pledgee: XinDa national equity investment fund (Shanghai) partnership (L.P.) Pledgor: ZEROTECH (BEIJING) INTELLIGENCE TECHNOLOGY Co.,Ltd.|CHONGQING ZERO INTELLIGENT CONTROL TECHNOLOGY CO.,LTD. Registration number: 2017990001217 |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20221008 Granted publication date: 20170919 Pledgee: XinDa national equity investment fund (Shanghai) partnership (L.P.) Pledgor: CHONGQING ZERO INTELLIGENT CONTROL TECHNOLOGY CO.,LTD. Registration number: 2017990001217 |
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| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170919 Effective date of abandoning: 20230822 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20170919 Effective date of abandoning: 20230822 |