CN113581477B - Function module mounting structure and adopt its aircraft - Google Patents
Function module mounting structure and adopt its aircraft Download PDFInfo
- Publication number
- CN113581477B CN113581477B CN202110730690.6A CN202110730690A CN113581477B CN 113581477 B CN113581477 B CN 113581477B CN 202110730690 A CN202110730690 A CN 202110730690A CN 113581477 B CN113581477 B CN 113581477B
- Authority
- CN
- China
- Prior art keywords
- module
- main body
- mouth
- functional
- module body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000008859 change Effects 0.000 description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 230000006978 adaptation Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000003384 imaging method Methods 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Casings For Electric Apparatus (AREA)
Abstract
The invention discloses a functional module mounting structure and an aircraft adopting the same, comprising a main body, a cover body and a functional module, wherein the functional module comprises a module body and a functional device arranged on the module body, the main body is provided with a mouth communicated with an internal cavity of the main body, the module body is in a ring shape matched with the shape of the mouth, the module body is assembled on the mouth, a central through hole of the ring-shaped module body is communicated with the mouth, and the cover body is assembled on the module body again and seals the central through hole of the ring-shaped module body. The invention is easy to assemble, disassemble, maintain and replace, can be updated and upgraded rapidly, is convenient to replace and use the functional modules with different functional components, realizes more excellent, more various and comprehensive functions, has compact structure, does not prevent the main body from entering and exiting from the cavity of the main body from the mouth, and ensures that the main body can realize the functions normally.
Description
Technical Field
The invention relates to the technical field of mounting structures of functional devices such as sensors, in particular to a functional module mounting structure and an aircraft adopting the functional module mounting structure.
Background
The unmanned aerial vehicle and other equipment generally need to be provided with functional devices with various functions, for example, an obstacle avoidance sensor can be arranged on the unmanned aerial vehicle, the flight environment is monitored by the obstacle avoidance sensor, the damage to the unmanned aerial vehicle caused by landing on the water surface, treetops and other conditions is avoided, the current electronic technology is developed rapidly, the functional devices are updated very quickly, the functional devices with stronger performance are usually arranged in the next year, and the functional devices are generally directly fixed on the equipment and are difficult to update and change, so that the performance updating and the lifting of the equipment are affected.
Disclosure of Invention
The invention aims to solve the technical problems and the technical task of improving the prior art, provides a functional module mounting structure, and solves the problems that the functional devices in the prior art are inconvenient to update by adopting a fixed mounting mode.
In order to solve the technical problems, the technical scheme of the invention is as follows:
A function module mounting structure includes a main body, a cover body and a function module, wherein the function module includes a module body and a function device arranged on the module body, the main body is provided with a mouth communicated to an inner cavity of the main body, the module body is annular matched with the shape of the mouth, the module body is assembled on the mouth and a central through hole of the annular module body is communicated with the mouth, and the cover body is assembled on the module body and closes the central through hole of the annular module body. The functional module mounting structure integrates the functional devices on the module body, the module body is an independent part relative to the main body, the module body is easy to assemble, disassemble, maintain and replace, when the functional devices are damaged or need to be updated, only the functional modules are needed to be replaced, the maintenance and replacement are more convenient, the cost is lower, the updating and updating can be realized quickly, the functional modules with different functional parts are convenient to replace and use, the functions with better quality and more comprehensive functions are realized, the whole functional modules are annular and are arranged at the mouth part of the main body, when the module body is combined on the mouth part of the main body, the central through opening surrounded by the annular module body is communicated with the mouth part, so that the smoothness of the mouth part of the main body is kept, the normal functions of the chamber are not hindered, the functional modules, the main body and the cover body are organically integrated, the structure is compact, excessive additional volume is avoided, the whole equipment combining the main body, the cover body and the functional modules can meet the requirements on the shape and the volume, and the reliability of the whole equipment can be ensured.
Further, the lid is directly assembled on the oral area of main part when the functional module removes, and the lid still seals the oral area of main part in order to ensure the leakproofness of the inside cavity of main part, still has removable function when the functional module realizes convenient change, namely can remove the functional module when not needing the functional device, thereby the lid is directly assembled on the oral area of main part and lid and main part combination are as an organic whole, still ensure the integrality of whole equipment, does not lead to whole equipment appearance incomplete and unable normal work because of removing the functional module.
Further, be provided with the first electric connector who is connected with the functional device electricity on the module body, be provided with the second electric connector in the main part, the module body is assembled when the oral area first electric connector is connected with the second electric connector to the functional device on the module body realizes being connected with the electricity of main part through first electric connector, second electric connector, and the functional device on the module body is supplied power and carries out data interaction with the main part by the main part, ensures that the functional device can reliably work, can work in coordination with the main part, becomes organic whole.
Further, the cover body is connected with the module body in a clamping way, and the cover body is simple in structure, convenient to assemble and disassemble and efficient.
Further, the first clamping part is arranged on the cover body, the second clamping part matched with the first clamping part is arranged on the module body, the third clamping part matched with the first clamping part is also arranged on the main body, the first clamping part on the cover body can be matched and connected with the second clamping part and the third clamping part, the connection structure is simplified, the cover body can be connected with the module body and the main body only by arranging one connection structure, the functional module is assembled on the main body in general, then the cover body is assembled on the functional module through the matching of the first clamping part and the second clamping part, and when the functional module is removed, the cover body is directly assembled on the main body through the matching of the first clamping part and the third clamping part, the opening of the main body is still closed, the integrity of the equipment is still ensured, and the equipment can still work normally.
Further, the module body is connected with the main body in a clamping way, and the device is simple in structure, easy to implement, low in cost, and convenient to assemble and disassemble.
Further, the module body is connected with the main body along the circumferential rotation clamping of the opening, so that the module body is convenient to assemble and disassemble and good in connection stability.
Further, be provided with T shape buckle on the module body, the main part on be provided with T shape buckle complex T shape spout to be provided with the elastic pin in the T shape spout, have on the T shape buckle with elastic pin complex spacing locking groove, it is convenient to install and remove, and connection stability is good, and utilizes the cooperation in elastic pin and spacing locking groove to ensure that the block is put in place, ensure assembly accuracy.
The utility model provides an aircraft, adopts foretell functional module mounting structure, the main part be the task cabin of aircraft, functional module and the organic connection in task cabin are as an organic whole to functional module can be convenient maintain, change, can quick update upgrade, implementation cost is lower, make aircraft with the time advance, have more high-quality more comprehensive function, and functional module does not hinder task equipment normally business turn over task cabin, guarantee task cabin function is normal, can remove functional module when not needing functional module, the lid is direct to be assembled on the task cabin in order to seal the oral area in task cabin, guarantee task cabin's seal, do not influence task cabin's pneumatics, guarantee aircraft's flight performance.
Furthermore, the opening of the task cabin faces the front and rear directions of the aircraft, task equipment is easy to operate, the functional modules are connected in the front and rear directions of the task cabin in a superposition mode, the overall structure of the functional modules and the cover body assembled on the task cabin and the overall structure of the cover body assembled on the task cabin only have length change in the front and rear directions of the aircraft, the overall shape and the structure of the two modes are basically consistent, the pneumatic performances of the two modes are basically the same, and therefore the aircraft has good flight performance when the functional modules are assembled on the task cabin and the functional modules are not assembled on the task cabin.
Further, the functional device is an obstacle avoidance sensor, and the obstacle avoidance sensor is arranged on at least one of the upper side, the lower side, the left side and the right side of the module body, so that the aircraft can monitor the surrounding environment, and further can fly in a complex environment, avoid impacting obstacles, avoid damage to the aircraft caused by the situation that the aircraft falls on the water surface, the tree tips and the like, and improve the flight safety.
Furthermore, the obstacle avoidance sensor is a binocular vision module, two images of the object to be measured are obtained from different positions based on the parallax principle by using imaging equipment, and three-dimensional geometric information of the object is obtained by calculating the position deviation between corresponding points of the images, so that the recognition monitoring capability of the complex environment is ensured, and the flight safety is improved.
Compared with the prior art, the invention has the advantages that:
The functional module mounting structure is easy to assemble, disassemble, maintain and replace, can be updated and upgraded rapidly, is convenient to replace and use functional modules with different functional components, realizes more excellent, various and comprehensive functions, has a compact structure, does not prevent the main body from entering and exiting from the cavity of the main body from the mouth, and ensures that the main body can realize the functions normally;
the aircraft is convenient for maintaining and replacing functional devices, so that the aircraft can enter in time, is easy to update, upgrade and upgrade, ensures that a mission cabin has good air performance, and ensures flight performance and safety.
Drawings
FIG. 1 is an exploded view of a functional module mounting structure of the present invention;
FIG. 2 is a schematic view of the mouth structure of the body;
FIG. 3 is a schematic diagram of a functional module;
FIG. 4 is a schematic view of the overall structure of an aircraft;
FIG. 5 is a schematic view of a functional module connected to a main body by screws;
FIG. 6 is a schematic view of the structure of the cover to be connected after the functional module is assembled on the main body;
FIG. 7 is a schematic view of the structure in which the main body, the functional module and the cover are assembled together;
FIG. 8 is a schematic view of the structure of the body and the cover assembled together;
FIG. 9 is a schematic diagram of the structure of the first engaging portion and the second engaging portion in a separated state;
FIG. 10 is a schematic structural view showing a connection state between the first engaging portion and the second engaging portion;
FIG. 11 is a schematic view of a structure in which a main body is provided with a snap chute;
FIG. 12 is a schematic view of a module body with a snap fastener;
FIG. 13 is a schematic view of the module body rotated relative to the body to engage;
fig. 14 is a schematic view of the configuration of the T-shaped buckle and T-shaped chute 62.
The reference numerals in the drawings are:
A main body 1; a mouth 11; a functional module 2; a module body 21; a functional device 22; a cover 3; a first electrical connector 41; a second electrical connector 42; the first clamping part 51; a second engagement portion 52; an engagement portion III 53; a T-shaped clasp 61; a T-shaped chute 62; an elastic pin 63; a clip 64; and a snap-in chute 65.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The functional module mounting structure disclosed by the embodiment of the invention is convenient to assemble and disassemble, has high efficiency, can be rapidly updated, is convenient to replace and use modules with different functional components, realizes better and more comprehensive functions, has better flexibility and adjustability and lower use cost.
As shown in fig. 1 to 3, a function module mounting structure mainly includes a main body 1, a cover 3, and a function module 2, the function module 2 includes a module body 21 and a function device 22 provided on the module body 21, the function device 22 may be various sensors or actuators, etc., the main body 1 has a mouth 11 communicating to an inner chamber thereof for accommodating a working device, etc., the module body 21 is in a ring shape matching with the mouth 11, the module body 21 is fitted on the mouth 11 and a central opening of the ring-shaped module body 21 communicates with the mouth 11, the cover 3 is fitted on the module body 21 again and closes the central opening of the ring-shaped module body 21, that is, the cover 3 closes a chamber of the main body 1, and when the function module 2 is not required, the function module 2 may be removed, and then the cover 3 is fitted directly on the mouth 11 of the main body 1 to thereby close the chamber of the main body 1. The function module mounting structure of this embodiment has two mounting states on the whole, one is that the main part 1, lid 3 and function module 2 three are combined as an organic whole, one is that after removing function module 2, main part 1 and lid 3 are combined as an organic whole, function module 2 is the individual part that has function device 22, when function device 22 damages and needs to maintain the change or when function device 22 appears the better new product of performance, can directly replace whole function module 2, and is efficient, convenient operation, ensure that whole equipment resumes normal use soon, and different function module 2 can install different function part, thereby make whole equipment have different functions through changing different function module 2, realize more high-quality more various comprehensive functions, and still can dismantle function module 2 completely when not needing to use function module 2, and lid 3 is directly assembled on the oral area 11 of main part 1 and still satisfies whole equipment's structural integrity, do not influence whole equipment's normal work. Furthermore, because the central through hole of the annular module body 21 is communicated with the opening 11, the smoothness of the opening of the main body can be maintained, the normal function of the opening is not affected, the normal access to the cavity from the opening is not hindered, the structural form described in the embodiment is adopted, the functional module 2 is positioned between the main body 1 and the cover body 3, the central through hole of the module body 21 is covered by the cover body 3, namely the cavity of the main body 1 is closed, after the functional module 2 is removed, the smoothness of the opening of the main body 1 is still maintained, the cavity from the opening can still be accessed normally, the cover body 3 is directly connected to the main body 1, the cavity of the main body 1 can still be reliably closed, the integrity of the two structural forms is always ensured while the structure is simple, and the normal operation of the whole equipment is not affected.
In order to ensure the long-acting stable operation of the functional device 22, the module body 21 is provided with a first electric connector 41 electrically connected with the functional device 22, the main body 1 is provided with a second electric connector 42, and the first electric connector 41 is connected with the second electric connector 42 when the module body 21 is assembled on the opening 11, so that the functional device 22 is electrically connected with the main body 1 through the first electric connector 41 and the second electric connector 42, including power supply, data interaction and the like.
As shown in fig. 2 to 4, the above-mentioned function module mounting structure is applied to an unmanned aerial vehicle, specifically, the main body 1 is a mission cabin of the unmanned aerial vehicle, the hatch of the mission cabin is the mouth of the main body, the whole of the mission cabin is a fusiform flow linear cabin body, namely, the two ends of the aperture of the cabin are narrow and the middle is wide along the front-back direction of the aircraft, and the mouth 11 of the mission cabin is a generally conical shell along the front-back direction of the aircraft, in this embodiment, the mouth 11 of the mission cabin faces the front side direction of the aircraft, so that the central through opening of the module body 21 also faces the front side direction of the aircraft, namely, the module body 21 is an annular device along a vertical plane, the module body 21 is assembled on the mouth 11, and then the cover body 3 is assembled on the module body 21.
In this embodiment, the functional device 22 is an obstacle avoidance sensor, and the obstacle avoidance sensor is used to monitor the flight environment, so as to avoid collision with obstacles, avoid landing on the water surface, on the tree tips, and the like, so that the aircraft can fly in a complex environment, specifically, the obstacle avoidance sensors are respectively arranged on the lower side, the left side and the right side of the module body 21, and the obstacle avoidance sensor specifically adopts a binocular vision module, so that the effective monitoring can be performed in three directions, the collision is avoided, the flight safety is ensured, and the equipment is prevented from being damaged. In order to ensure good air performance, the binocular vision module is embedded in the module body 21, and the binocular vision module does not exceed the surface of the module body 21, so that the air performance is not affected. When the obstacle avoidance sensor is faulty, damaged or is a new generation obstacle avoidance sensor, the functional module 2 can be replaced integrally, the replacement is convenient and the efficiency is high, so that the aircraft can be put into use again as soon as possible, and functional devices 22 with different functions can be assembled on the module body 21, the functional devices 22 can be infrared sensors, radar sensors, navigation lights and the like, so that the functional module 2 has more various and comprehensive functions, the functional module 2 with different functions can be replaced as required, the integrity and good pneumatic performance of the integral mission cabin can still be guaranteed by installing different functional modules 2, and the flight reliability and safety of the aircraft can not be influenced when different functional modules 2 are used.
As shown in fig. 5 to 8, the module body 21 is provided with a plurality of through holes along the front-rear direction of the aircraft, the through holes are arranged at intervals in the circumferential direction of the central through hole, the main body 1 is correspondingly provided with a plurality of screw holes in the circumferential direction of the opening 11, and screws penetrate through the through holes of the module body 21 and then are locked on the screw holes of the main body 1, so that the functional module 2 is stably connected on the main body 1. The cover body 3 is connected with the module body 21 in a clamping manner, specifically, the first clamping portion 51 is arranged on the cover body 3, the second clamping portion 52 matched with the first clamping portion 51 is arranged on the module body 21, the third clamping portion 53 matched with the first clamping portion 51 is also arranged on the main body 1, the assembly is convenient and quick, under the condition that the functional module 2 is assembled on the main body 1, the cover body 3 is connected with the second clamping portion 52 in a clamping manner through the first clamping portion 51 so as to be assembled on the module body 21, then the main body 1, the cover body 3 and the functional module 2 are combined into a complete task cabin, and when the functional module 2 is not assembled on the main body 1, the cover body 3 is directly assembled on the main body 1 through the clamping connection of the first clamping portion 51 and the third clamping portion 53, and then the main body 1 and the cover body 3 are combined into the complete task cabin, so that the flexibility and the adjustability are good.
Specifically, as shown in fig. 9 and 10, the first clamping part 51 is a hasp type buckle, the second clamping part 52 and the third clamping part 53 are buckle seats, the first clamping part 51 comprises a fixing seat, an elastic telescopic rod and a buckle, the fixing seat is fixed on the cover body 3 through a rivet pulling screw, one end of the elastic telescopic rod is hinged to the other end of the fixing seat and is connected with the buckle, the buckle seats are respectively fixed on the module body 21 and the main body 1 through rivet pulling screws, the buckle seats are provided with barbs, the elastic telescopic rod is pulled, then the buckle is buckled on the barbs of the buckle seats, the elastic telescopic rod contracts due to self elasticity, locking and clamping are achieved, and the device is simple in structure and convenient and fast to operate.
As shown in fig. 11 to 13, the module body 21 is engaged with the main body 1 along the circumferential direction of the opening 11, a plurality of engaging members 64 are provided on the module body 21 along the circumferential direction at intervals, a plurality of engaging sliding grooves 65 are provided on the main body 1 along the circumferential direction of the opening 11 at intervals, the engaging members 64 firstly enter the engaging sliding grooves 65, and then the module body 21 is rotated relative to the main body 1, thereby realizing the engaged connection, the assembly and the disassembly are convenient, and the connection stability is good.
Specifically, as shown in fig. 14, the fastening element on the module body 21 is a T-shaped fastening element 61, the fastening sliding slot on the main body 1 is a T-shaped sliding slot 62, an elastic pin 63 is disposed in the T-shaped sliding slot 62, the elastic pin 63 is composed of a spring and a steel ball, the T-shaped fastening element 61 is provided with a limit locking slot matched with the elastic pin 63, the limit locking slot is a spherical slot, when the T-shaped fastening element 61 is fastened in place along the T-shaped sliding slot 62, the limit locking slot just faces the elastic pin 63, so that the elastic pin 63 is inserted into the limit locking slot, the accurate fastening in place between the module body 21 and the main body 1 is ensured, the cooperation of the elastic pin 63 and the limit locking slot plays a role of limit locking, the situation that the module body 21 is separated due to accidental sliding relative to the main body 1 is avoided, and the connection stability is ensured. When the module body 21 needs to be removed, the elastic pin 63 can be led to exit the limiting locking groove only by reversely applying force to move the module body 21, so that the module body 21 can be quickly separated from the main body 1, and the maintenance and the replacement are convenient. In this assembly mode, the first electrical connector 41 is provided on the surface of the module body 21 that is attached to the main body 1, and the second electrical connector 42 is provided on the surface of the main body 1 that is attached to the module body 21, and the first electrical connector 41 and the second electrical connector 42 are contact connectors.
The foregoing is merely a preferred embodiment of the present invention, and it should be noted that the above-mentioned preferred embodiment should not be construed as limiting the invention, and the scope of the invention should be defined by the appended claims. It will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the spirit and scope of the invention, and such modifications and adaptations are intended to be comprehended within the scope of the invention.
Claims (9)
1. An aircraft comprising a main body (1), a cover (3) and a functional module (2), the functional module (2) comprising a module body (21) and a functional device (22) provided on the module body (21), the main body (1) having a mouth (11) communicating to an interior chamber thereof, the module body (21) being in a ring shape matching the mouth (11), the module body (21) being fitted on the mouth (11) and a central opening of the ring-shaped module body (21) being in communication with the mouth (11), the cover (3) being reassembled on the module body (21) and closing the central opening of the ring-shaped module body (21);
The main body (1) is a mission cabin of the aircraft, the mouth part (11) of the mission cabin faces to the front-back direction of the aircraft, and the cover body (3), the functional module (2) and the main body (1) are sequentially stacked and combined to form a complete fusiform linear mission cabin; the cover (3) is fitted directly onto the mouth (11) of the body (1) when the functional module (2) is removed to combine into a complete, fusiform, flow-linear task pod.
2. An aircraft according to claim 1, characterized in that the module body (21) is provided with a first electrical connector (41) electrically connected to the functional device (22), the main body (1) is provided with a second electrical connector (42), and the first electrical connector (41) is connected to the second electrical connector (42) when the module body (21) is fitted over the mouth (11).
3. The aircraft according to claim 1, characterized in that the cover (3) is connected to the module body (21) in a snap-fit manner.
4. An aircraft according to claim 3, characterized in that the cover (3) is provided with a first engagement portion (51), the module body (21) is provided with a second engagement portion (52) which cooperates with the first engagement portion (51), and the main body (1) is also provided with a third engagement portion (53) which cooperates with the first engagement portion (51).
5. The aircraft according to claim 1, characterized in that the module body (21) is snap-connected to the main body (1).
6. The aircraft according to claim 5, characterized in that the module body (21) is connected to the main body (1) in a rotationally snap-fit manner along the circumference of the mouth (11).
7. The aircraft according to claim 5, wherein the module body (21) is provided with a T-shaped buckle (61), the main body (1) is provided with a T-shaped chute (62) matched with the T-shaped buckle (61), and an elastic pin (63) is arranged in the T-shaped chute (62), and the T-shaped buckle (61) is provided with a limit locking groove matched with the elastic pin (63).
8. The aircraft according to any one of claims 1 to 7, characterized in that the functional device (22) is an obstacle avoidance sensor, which is provided at least on one of the upper, lower, left, right sides of the module body (21).
9. The aircraft of claim 8, wherein the obstacle avoidance sensor is a binocular vision module.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110730690.6A CN113581477B (en) | 2021-06-29 | 2021-06-29 | Function module mounting structure and adopt its aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110730690.6A CN113581477B (en) | 2021-06-29 | 2021-06-29 | Function module mounting structure and adopt its aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113581477A CN113581477A (en) | 2021-11-02 |
| CN113581477B true CN113581477B (en) | 2024-04-26 |
Family
ID=78245278
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110730690.6A Active CN113581477B (en) | 2021-06-29 | 2021-06-29 | Function module mounting structure and adopt its aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113581477B (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108423153A (en) * | 2018-05-17 | 2018-08-21 | 王瀚晨 | Modularized micro unmanned plane |
| WO2019028071A1 (en) * | 2017-08-01 | 2019-02-07 | Paul Perry | Unmanned aircraft system with swappable components |
| CN109515706A (en) * | 2018-12-03 | 2019-03-26 | 成都纵横大鹏无人机科技有限公司 | A kind of Modularized unmanned machine |
| CN109681603A (en) * | 2019-02-21 | 2019-04-26 | 刘红宇 | Interface and Multifunctional foot motivation tool between a kind of multiple functional units and a power unit |
| CN109715497A (en) * | 2017-03-22 | 2019-05-03 | 极光飞行科学公司 | Multi rack structure Modularized unmanned machine system |
| CN209617488U (en) * | 2019-01-07 | 2019-11-12 | 浙江自贸区协同科技有限公司 | A kind of modularization head |
| CN209773455U (en) * | 2019-03-25 | 2019-12-13 | 无锡邦得机械有限公司 | descaling gas blowing device |
| CN110745232A (en) * | 2019-11-18 | 2020-02-04 | 西安爱生技术集团公司 | Modularization unmanned aerial vehicle fuselage butt-joint structural |
| CN210311912U (en) * | 2019-05-31 | 2020-04-14 | 西南医科大学附属中医医院 | Hospital uses edge tool box |
| CN111409843A (en) * | 2020-05-13 | 2020-07-14 | 成都纵横大鹏无人机科技有限公司 | Task equipment connecting mechanism |
| CN212448036U (en) * | 2020-05-13 | 2021-02-02 | 成都纵横大鹏无人机科技有限公司 | Rotating assembly and aircraft adopting same |
| CN212644877U (en) * | 2020-05-28 | 2021-03-02 | 宁波天瑞电器有限公司 | Modularization air purifier |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2863584B1 (en) * | 2003-12-12 | 2007-01-26 | Thales Sa | MODULAR OPTRONIC SYSTEM EMBARABLE ON A BEARER |
| US10232938B2 (en) * | 2015-07-01 | 2019-03-19 | W.Morrison Consulting Group, Inc. | Unmanned supply delivery aircraft |
-
2021
- 2021-06-29 CN CN202110730690.6A patent/CN113581477B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109715497A (en) * | 2017-03-22 | 2019-05-03 | 极光飞行科学公司 | Multi rack structure Modularized unmanned machine system |
| WO2019028071A1 (en) * | 2017-08-01 | 2019-02-07 | Paul Perry | Unmanned aircraft system with swappable components |
| CN108423153A (en) * | 2018-05-17 | 2018-08-21 | 王瀚晨 | Modularized micro unmanned plane |
| CN109515706A (en) * | 2018-12-03 | 2019-03-26 | 成都纵横大鹏无人机科技有限公司 | A kind of Modularized unmanned machine |
| CN209617488U (en) * | 2019-01-07 | 2019-11-12 | 浙江自贸区协同科技有限公司 | A kind of modularization head |
| CN109681603A (en) * | 2019-02-21 | 2019-04-26 | 刘红宇 | Interface and Multifunctional foot motivation tool between a kind of multiple functional units and a power unit |
| CN209773455U (en) * | 2019-03-25 | 2019-12-13 | 无锡邦得机械有限公司 | descaling gas blowing device |
| CN210311912U (en) * | 2019-05-31 | 2020-04-14 | 西南医科大学附属中医医院 | Hospital uses edge tool box |
| CN110745232A (en) * | 2019-11-18 | 2020-02-04 | 西安爱生技术集团公司 | Modularization unmanned aerial vehicle fuselage butt-joint structural |
| CN111409843A (en) * | 2020-05-13 | 2020-07-14 | 成都纵横大鹏无人机科技有限公司 | Task equipment connecting mechanism |
| CN212448036U (en) * | 2020-05-13 | 2021-02-02 | 成都纵横大鹏无人机科技有限公司 | Rotating assembly and aircraft adopting same |
| CN212644877U (en) * | 2020-05-28 | 2021-03-02 | 宁波天瑞电器有限公司 | Modularization air purifier |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113581477A (en) | 2021-11-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11014666B2 (en) | Airframe | |
| US9914538B2 (en) | Rotor shrouding apparatus, supporting assembly, and unmanned aerial vehicle using the same | |
| US9988145B2 (en) | Supporting assembly and unmanned aerial vehicle using the same | |
| US20160244160A1 (en) | Convertible unmanned aerial vehicle | |
| JP6044881B2 (en) | Power supply control device | |
| US20210276691A1 (en) | Locking mechanism, propeller, motor, propulsion system assembly, and aircraft | |
| KR101807368B1 (en) | drone equipped with one touch battery pack | |
| CN205639421U (en) | Shock -absorbing structure and use this shock -absorbing structure's ptz assembly , unmanned aerial vehicle | |
| US20200011473A1 (en) | Pan-tilt quick locking device | |
| CN113581477B (en) | Function module mounting structure and adopt its aircraft | |
| US8477504B2 (en) | Systems and methods for blind-mate connector alignment | |
| CN208181396U (en) | Unmanned plane | |
| CN109070988A (en) | Protection cap, frame assembly and the unmanned plane of the fuselage of unmanned plane | |
| US9548575B2 (en) | Device for fixing and electrical contacting a facing element of an aircraft on a support structure | |
| US5522575A (en) | Servo case and mounting fixture therefor | |
| CN216805850U (en) | Quick detach structure and unmanned aerial vehicle for unmanned aerial vehicle mounting | |
| CN217022918U (en) | Cloud platform coupling assembling and unmanned aerial vehicle | |
| CN214776618U (en) | Lighting unmanned aerial vehicle | |
| CN215591018U (en) | Unmanned aerial vehicle bayonet joint device | |
| CN210325588U (en) | Button box unit and modular button box thereof | |
| CN109713187A (en) | Unmanned plane and power supply installs case | |
| CN216468427U (en) | Aircraft with a flight control device | |
| CN105850955B (en) | Multi-rotor-wing plant protection machine and transverse folding machine arm thereof | |
| CN216468428U (en) | Wing assembly and aircraft with same | |
| CN218463878U (en) | Sprinkler and unmanned equipment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |