CN112224411B - Microminiature unmanned aerial vehicle - Google Patents
Microminiature unmanned aerial vehicle Download PDFInfo
- Publication number
- CN112224411B CN112224411B CN202011196036.3A CN202011196036A CN112224411B CN 112224411 B CN112224411 B CN 112224411B CN 202011196036 A CN202011196036 A CN 202011196036A CN 112224411 B CN112224411 B CN 112224411B
- Authority
- CN
- China
- Prior art keywords
- module
- unmanned aerial
- aerial vehicle
- mode
- instruction
- 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
- 230000007246 mechanism Effects 0.000 claims description 28
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 24
- 238000012545 processing Methods 0.000 claims description 12
- 238000009434 installation Methods 0.000 claims description 6
- 230000008602 contraction Effects 0.000 claims description 5
- 238000013461 design Methods 0.000 abstract description 10
- 238000011084 recovery Methods 0.000 abstract 1
- 230000005540 biological transmission Effects 0.000 description 8
- 238000004064 recycling Methods 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 3
- 230000008439 repair process Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Images
Classifications
-
- 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
- B64C39/028—Micro-sized aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
- B64C1/063—Folding or collapsing to reduce overall dimensions, e.g. foldable tail booms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- 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
- B64D47/08—Arrangements of cameras
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The application discloses microminiature unmanned aerial vehicle, microminiature unmanned aerial vehicle includes: the device comprises a machine body module, a load module and a transmitting device module; the machine body module is used for switching the forms according to the state mode instruction; the loading module is used for loading a loading object; and the transmitting device module is used for carrying out transmitting control according to the transmitting instruction. The micro unmanned aerial vehicle provided by the application can be more convenient to design and install, easier to maintain and higher in recovery utilization rate; the functional modules of the micro unmanned aerial vehicle can be expanded or simplified according to actual needs, namely the micro unmanned aerial vehicle can expand or simplify the functions more conveniently, so that the micro unmanned aerial vehicle can adapt to different task demand scenes better; thereby the user experience of microminiature unmanned aerial vehicle has been improved.
Description
Technical Field
The application relates to the field of unmanned aerial vehicles, in particular to a micro unmanned aerial vehicle.
Background
The microminiature unmanned aerial vehicle has the characteristics of light weight, small size and the like, and is convenient for carrying and hidden investigation by an individual soldier. The micro unmanned aerial vehicle can be used independently and can be used cooperatively in cluster formation. In the operation environments of urban operation, beyond visual range operation and the like in modern war, the micro unmanned aerial vehicle is important equipment with extremely high efficiency.
Microminiature unmanned aerial vehicle also has the design simultaneously and makes the difficulty as a high-tech product, and is higher to installation user's operating requirement to microminiature unmanned aerial vehicle maintenance is inconvenient, and recycle is rateed lowly. Therefore, a micro unmanned aerial vehicle with simple design and installation, easy maintenance and repair and higher recycling rate is urgently needed.
Disclosure of Invention
The application provides a micro unmanned aerial vehicle, which can enable the micro unmanned aerial vehicle to be simpler and more convenient to design and install, easier to maintain and higher in recycling rate; the functional modules of the micro unmanned aerial vehicle can be expanded or simplified according to actual needs, namely the micro unmanned aerial vehicle can expand or simplify the functions more conveniently, so that the micro unmanned aerial vehicle can adapt to different task demand scenes better; thereby the user experience of microminiature unmanned aerial vehicle has been improved.
The application provides a microminiature unmanned aerial vehicle, microminiature unmanned aerial vehicle includes: the device comprises a machine body module, a load module and a transmitting device module;
the machine body module is used for switching the forms according to the state mode instruction;
the loading module is used for loading a loading object;
and the transmitting device module is used for carrying out transmitting control according to the transmitting instruction.
Optionally, the body module is specifically configured to switch the shape of the body module into a cylindrical shape according to the state mode instruction if the state mode instruction is the folding mode; the body module is specifically used for switching the state of the body module into a multi-rotor state according to the state mode instruction if the state instruction is in a flight mode.
Optionally, the body module includes: the aircraft comprises an airframe framework, a rotor wing installation frame, a plurality of rotor wings, a steering engine, a power supply module, a flight control module and an aircraft arm supporting and retracting mechanism;
the fuselage framework is used for mounting the rotor wing mounting rack, the steering engine, the power supply module, the flight control module and the horn support contraction mechanism;
the rotor wing mounting rack is used for mounting the rotor wings;
the steering engine is used for providing power for the rotors;
the power supply module is used for providing power supply;
the horn supports a retracting mechanism which is used for controlling the rotors to retract or expand;
and the flight control module is used for controlling the horn support retraction mechanism to retract or deploy the rotors according to the state mode instruction.
Optionally, the plurality of rotors is four rotors.
Optionally, the flight control module is specifically configured to:
if the state mode instruction is a folding mode, controlling the horn support retraction mechanism to retract the four rotors;
and if the aircraft is in a flight mode according to the state mode instruction, controlling the aircraft arm supporting and retracting mechanism to unfold the four rotors so as to switch the form of the airframe module into a four-rotor or multi-rotor form.
Optionally, the body module further includes: an image processing module; the image processing module is arranged on the airframe framework; the image processing module is used for acquiring images and storing the acquired images or transmitting the acquired images to other equipment; the load module is specifically used for loading a camera.
Optionally, the transmitting device module includes: the booster, the ejection device and the counterweight device; the transmitting device module is specifically configured to:
if the launching instruction is in a barrel launching mode, the booster is used for barrel launching;
if the launching instruction is in a launching mode, launching by utilizing the launching device;
and if the launching instruction is in a hand-held takeoff mode, carrying out hand-held takeoff by using the counterweight device.
Optionally, the connection mode between the machine body module and the load module is a mechanical hanging assembly mode; the connection mode between the engine body module and the transmitting device module is a mechanical hanging assembly mode.
Optionally, one surface of the machine body module facing the load module is a hook surface, and one surface of the load module facing the machine body module is a groove surface; and locking holes are correspondingly formed in the hook surface and the groove surface, and the hook surface and the locking holes in the groove surface are connected and assembled through locking pins.
Optionally, one surface of the body module facing the transmitter module is a hook surface, and one surface of the transmitter module facing the body module is a groove surface; and locking holes are correspondingly formed in the hook surface and the groove surface, and the hook surface and the locking holes in the groove surface are connected and assembled through locking pins.
It can be seen from above-mentioned technical scheme that this application provides a microminiature unmanned aerial vehicle, and this microminiature unmanned aerial vehicle includes: the device comprises a machine body module, a load module and a transmitting device module; the machine body module is used for switching the forms according to the state mode instruction; the loading module is used for loading a loading object; and the transmitting device module is used for carrying out transmitting control according to the transmitting instruction. Therefore, the micro unmanned aerial vehicle is in a modular design, namely the micro unmanned aerial vehicle comprises a machine body module, a load module and a transmitting device module, so that the micro unmanned aerial vehicle in the modular design is simpler and more convenient to design and install, easier to maintain and repair and higher in recycling rate; the functional modules of the micro unmanned aerial vehicle can be expanded or simplified according to actual needs, namely the micro unmanned aerial vehicle can expand or simplify the functions more conveniently, so that the micro unmanned aerial vehicle can adapt to different task demand scenes better; thereby the user experience of microminiature unmanned aerial vehicle has been improved.
Further effects of the above-mentioned unconventional preferred modes will be described below in conjunction with specific embodiments.
Drawings
In order to more clearly illustrate the embodiments or prior art solutions of the present application, the drawings needed for describing the embodiments or prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present application, and that other drawings can be obtained by those skilled in the art without inventive exercise.
Fig. 1 is a schematic structural diagram of a micro unmanned aerial vehicle according to an embodiment of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be described in detail and completely with reference to the following embodiments and accompanying drawings. It should be apparent that the described embodiments are only some of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
Various non-limiting embodiments of the present application are described in detail below with reference to the accompanying drawings.
Referring to fig. 1, a micro unmanned aerial vehicle in the embodiment of the present application is shown. The microminiature unmanned aerial vehicle includes: the device comprises a machine body module, a load module and a transmitting device module.
In this embodiment, the body module may be configured to switch the form according to the state mode command. The state mode command may be a command for controlling the form of the body module, for example, the state mode command may include a folding mode and a flight mode; specifically, the body module may be specifically configured to, if the state mode instruction is a folding mode, switch the state of the body module to a cylindrical state according to the state mode instruction, that is, the state mode instruction corresponding to the folding mode may control the state of the body module to be switched to the cylindrical state, so that the micro unmanned aerial vehicle may be folded up, and the volume of the micro unmanned aerial vehicle may be adjusted to a minimum state, so that the micro unmanned aerial vehicle may be stored and transported in a centralized manner or carried by a single soldier, and in this state, a plurality of micro unmanned aerial vehicle clusters may be launched, so as to execute unmanned aerial vehicle cluster combat tasks; the airframe module can be specifically used for switching the state of the airframe module into a multi-rotor state according to the state mode instruction if the state instruction is in a flight mode, namely, the state mode instruction corresponding to the flight mode can control the state of the airframe module to be switched into the multi-rotor state, so that the micro unmanned aerial vehicle can fly in the air and execute flight tasks when in the multi-rotor state. It should be noted that the state mode command may be input by a user, for example, the state mode command may be input by the user to the micro drone through a remote controller.
In one implementation, the body module includes: fuselage skeleton, rotor mounting bracket, a plurality of rotors, steering wheel, power module, flight control module, horn support contraction mechanism. Next, each component in the body module will be separately described.
In this implementation, the fuselage skeleton can be used for the installation the rotor mounting bracket the steering wheel the power module the flight control module the horn supports the shrink mechanism to, the fuselage skeleton can be used for bearing the impact force of small unmanned aerial vehicle take off and land the in-process.
The rotor mounting bracket can be used for installing a plurality of rotors, namely a plurality of rotors can be installed on the rotor mounting bracket. In one implementation, the plurality of rotors on the rotor mount may be four rotors, and accordingly, the flight control module is specifically configured to: if the folding mode is adopted according to the state mode instruction, the horn support retraction mechanism is controlled to retract the four rotors, so that the micro unmanned aerial vehicle can be folded after the four rotors are retracted into the rotor mounting frame, the volume of the micro unmanned aerial vehicle is adjusted to be in a minimum cylindrical shape, the micro unmanned aerial vehicle can be conveniently stored and transported in a centralized manner or carried by a single soldier, and meanwhile, the cluster launching of a plurality of micro unmanned aerial vehicles can be realized in the shape, and the cluster combat task of the unmanned aerial vehicles can be conveniently executed; if according to the mode instruction is flight mode, control the horn supports shrink mechanism and expandes four rotors, like this, four rotors will expand from the rotor mounting bracket to make organism module's form switches into four many rotor forms, and like this, when microminiature unmanned aerial vehicle is many rotor forms, can realize air flight, carries out the flight task.
The steering wheel can be used for a plurality of rotors provide power, promptly the steering wheel is the power source. Specifically, when micro unmanned aerial vehicle is many rotors form, and a plurality of rotors expand the back from the rotor mounting bracket promptly, the steering wheel can provide power for these a plurality of rotors to this a plurality of rotors are rotatory, so that make micro unmanned aerial vehicle fly through a plurality of rotors are rotatory.
The power module can be used for providing power. It can be understood that power module can supply power for each part among the microminiature unmanned aerial vehicle to each part can be switched on with normal work operation among the microminiature unmanned aerial vehicle.
The horn supports a retraction mechanism that can be used to control the retraction or deployment of the plurality of rotors. That is, the boom support retraction mechanism can drive the plurality of rotors in the rotor mount to extend or retract, thereby changing the configuration of the airframe module. Specifically, the working state of the boom support and retraction mechanism may be controlled by a flight control module according to a state instruction, that is, the flight control module may control the boom support and retraction mechanism to retract the plurality of rotors according to a state mode instruction, or may control the boom support and retraction mechanism to deploy the plurality of rotors according to the state mode instruction, so that the form of the airframe module is switched to a four-rotor form.
The flight control module can be used for controlling the horn to support the contraction mechanism to contract or expand the rotors according to the state mode instruction, and for example, the flight control module can be a single chip microcomputer or an intelligent chip. Specifically, the flight control module receives a state mode instruction input by a user through a remote controller or other signal transmission modes (e.g., a voice input mode, etc.), can analyze a mode corresponding to the state mode instruction according to the state mode instruction, and then controls the horn support retraction mechanism to retract or deploy the plurality of rotors of the rotor mounting rack according to the mode corresponding to the state mode instruction. It should be noted that the flight control module can be used for controlling the power module to start supplying power and stop supplying power, the flight control module can be used for controlling the steering engine to start providing power and stop supplying power for a plurality of rotors, the flight control module can receive a state mode instruction, and according to the state mode instruction, the aircraft arm is controlled to support the contraction mechanism to contract or expand a plurality of rotors in the rotor installation rack so as to switch the form of the aircraft body module.
In this embodiment, the load module may be used for loading a load object. The load module can carry different loads according to task requirements; for example, when the micro-unmanned aerial vehicle needs to perform a flying combat mission, the load module may carry a combat component (e.g., a bullet launcher, a smoke bomb, etc.) to attack with the combat component, when the micro-unmanned aerial vehicle needs to perform a reconnaissance mission, the load module may carry a camera for reconnaissance, and when the micro-unmanned aerial vehicle needs to perform an information countermeasure, the load module may carry an electronic interference device for information countermeasure.
In this embodiment, the transmitting device module may be configured to perform transmission control according to a transmission instruction. The launching instruction can be understood as an instruction for determining a takeoff mode of the micro unmanned aerial vehicle, for example, the launching instruction can include a barrel launching mode, an ejection launching mode and a hand-held takeoff mode. It should be noted that the transmission instruction may be input by a user, for example, the transmission instruction may be input by the user to a flight control module of the micro unmanned aerial vehicle through a remote controller, and the flight control module controls the transmission device module to perform a transmission mode corresponding to the transmission instruction according to the transmission instruction, so as to control the take-off of the micro unmanned aerial vehicle.
In one implementation, the transmitting device module may include: the booster, the ejection device and the counterweight device; the transmitting device module is specifically configured to: if the launching instruction is in a barrel launching mode, the booster is used for barrel launching, namely the flight control module can control the booster to start according to the launching instruction corresponding to the barrel launching mode and carry out barrel launching on the micro unmanned aerial vehicle, namely the booster is assembled to realize the barrel launching of the micro unmanned aerial vehicle; if the launching instruction is in an ejection launching mode, the ejection device is used for performing ejection launching, namely the flight control module can control the ejection device to start according to the launching instruction corresponding to the ejection launching mode and perform ejection launching on the micro unmanned aerial vehicle, namely the ejection device is used for performing ejection launching on the micro unmanned aerial vehicle; if the launching instruction is in a handheld launching mode, the counterweight device is utilized to carry out handheld launching, namely, the flight control module can control the counterweight device to start according to the launching instruction corresponding to the handheld launching mode, and carry out the handheld launching mode on the micro unmanned aerial vehicle, namely, the counterweight device is used for realizing the handheld launching of the micro unmanned aerial vehicle.
It can be seen from above-mentioned technical scheme that this application provides a microminiature unmanned aerial vehicle, and this microminiature unmanned aerial vehicle includes: the device comprises a machine body module, a load module and a transmitting device module; the machine body module is used for switching the forms according to the state mode instruction; the loading module is used for loading a loading object; and the transmitting device module is used for carrying out transmitting control according to the transmitting instruction. Therefore, the micro unmanned aerial vehicle is in a modular design, namely the micro unmanned aerial vehicle comprises a machine body module, a load module and a transmitting device module, so that the micro unmanned aerial vehicle in the modular design is simpler and more convenient to design and install, easier to maintain and repair and higher in recycling rate; the functional modules of the micro unmanned aerial vehicle can be expanded or simplified according to actual needs, namely the micro unmanned aerial vehicle can expand or simplify the functions more conveniently, so that the micro unmanned aerial vehicle can adapt to different task demand scenes better; thereby the user experience of microminiature unmanned aerial vehicle has been improved.
It should be noted that, in an implementation manner, in order to implement a function that the micro unmanned aerial vehicle can implement image shooting, the body module may further include: and an image processing module. The image processing module can be arranged in the airframe framework, specifically, the image processing module can be used for collecting images and storing the collected images to the local or transmitting the collected images to other equipment, for example, the image processing module can be connected with other equipment through Bluetooth, wifi and a mobile network, so that the image processing module can transmit the images to other equipment in real time. Correspondingly, the load module can be used for loading a camera, so that the image processing module can acquire images through the camera.
It should be noted that, in an implementation manner, the connection manner between the body module and the load module may be a mechanical hanging assembly manner, and the connection manner between the body module and the launcher module is a mechanical hanging assembly manner, that is, a mechanical hanging mechanism is disposed between the body module and the load module, and a mechanical hanging mechanism is disposed between the body module and the launcher module.
The mechanical hanging assembly mode between the machine body module and the load module (namely the mechanical hanging mechanism between the machine body module and the load module) is as follows: one surface of the machine body module, which faces the load module, is a groove surface, and one surface of the load module, which faces the machine body module, is a hook surface; and locking holes are correspondingly formed in the hook surface and the groove surface, and the hook surface and the locking holes in the groove surface are connected and assembled through locking pins.
The mechanical hanging assembly mode between the engine body module and the transmitting device module (namely, the mechanical hanging mechanism between the engine body module and the transmitting device module) is as follows: one surface of the machine body module facing the transmitting device module is a groove surface, and one surface of the transmitting device module facing the machine body module is a hook surface; and locking holes are correspondingly formed in the hook surface and the groove surface, and the hook surface and the locking holes in the groove surface are connected and assembled through locking pins.
It should be noted that, in an implementation manner of this embodiment, the hook surface is provided with two sections of protruding strips, and the two sections of protruding strips are arranged in the same horizontal direction, an area of one side of the protruding strip facing the groove surface is greater than an area of one side of the protruding strip facing the hook surface, for example, a cross section of the protruding strip may be trapezoidal, and accordingly, the groove surface is also provided with concave grooves for the two sections of protruding strips (for example, a cross section of the concave groove may be trapezoidal, and an area of one side of the concave groove facing the groove surface is greater than an area of one side of the concave groove facing the hook surface), so that after the protruding strips are inserted into the concave grooves, the protruding strips and the concave grooves can be attached and engaged with each other, so that the two modules are connected together and cannot be separated through the protruding strips and the concave grooves.
In addition, in an implementation mode, the locking hole can also be arranged in a strip shape, and the locking hole, the protruding strip and the concave groove can be vertically arranged on the hook surface and the groove surface, so that the locking hole is connected and assembled through the locking pin, namely, through the matching of the locking hole and the locking pin, the protruding strip and the concave groove can not move, and further the two modules can be prevented from falling off. It will be appreciated that the space between the two projecting strips may be sufficient for the locking pin to pass through, i.e. the space between the two projecting strips may be of a size corresponding to the cross-sectional shape of the locking pin, so that the projecting strips may be prevented from moving (displacing) by the cooperation of the locking hole and the locking pin.
That is to say, there is hooking device at the faying face between the module of microminiature unmanned aerial vehicle and the module (being organism module with load module, organism module and emitter module), divide into couple face and slot face, and the locking hole has all been opened on two sides, inserts the stop pin and can accomplish the assembly, assembles portably efficiently. Like this, because the organism module with connected mode between the load module articulates the mounting means for mechanical type, and the mechanical type articulates the assembly of mounting means and the process of dismouting is all more simple and convenient, so mechanical type articulates the assembly microminiature unmanned aerial vehicle that the mounting means can be convenient to and can disassemble the module that has the problem so that maintain microminiature unmanned aerial vehicle fast, and, the unmanned aerial vehicle module that the function is normal after using can pull down recycle, like this, can great promotion microminiature unmanned aerial vehicle's use maintenance convenience and recycle ratio.
It should be noted that, in the present specification, all the embodiments are described in a progressive manner, and the same and similar parts among the embodiments may be referred to each other, and each embodiment focuses on the differences from the other embodiments. The above-described apparatus and system embodiments are merely illustrative, in that elements described as separate components may or may not be physically separate. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of the present embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.
The above description is only for the preferred embodiment, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A micro unmanned aerial vehicle, comprising: the device comprises a machine body module, a load module and a transmitting device module;
the machine body module is used for switching the forms according to the state mode instruction;
the loading module is used for loading a loading object;
the transmitting device module is used for carrying out transmitting control according to a transmitting instruction;
the connection mode between the machine body module and the load module is a mechanical hanging assembly mode; the connection mode between the engine body module and the transmitting device module is a mechanical hanging assembly mode;
one surface of the machine body module, which faces the load module, is a groove surface, and one surface of the load module, which faces the machine body module, is a hook surface; the hook surface and the groove surface are respectively and correspondingly provided with a locking hole, and the locking holes in the hook surface and the groove surface are connected and assembled through locking pins;
one surface of the machine body module facing the transmitting device module is a groove surface, and one surface of the transmitting device module facing the machine body module is a hook surface; the hook surface and the groove surface are respectively and correspondingly provided with a locking hole, and the locking holes in the hook surface and the groove surface are connected and assembled through locking pins;
the hook surface is provided with two sections of protruding strips, the two sections of protruding strips are arranged in the same horizontal direction, and the area of one side, facing the groove surface, of each protruding strip is larger than that of one side, facing the hook surface, of each protruding strip; the groove surface is also provided with a concave groove aiming at the two sections of convex strips, and the area of one side of the concave groove facing the groove surface is larger than that of one side of the concave groove facing the hook surface; the shape and the size of a gap between the two sections of the protruding strips are consistent with the shape and the size of the cross section of the locking pin;
the transmitting device module includes: the booster, the ejection device and the counterweight device; the transmitting device module is specifically configured to:
if the launching instruction is in a barrel launching mode, the booster is used for barrel launching;
if the launching instruction is in a launching mode, launching by utilizing the launching device;
and if the launching instruction is in a hand-held takeoff mode, carrying out hand-held takeoff by using the counterweight device.
2. The micro unmanned aerial vehicle of claim 1, wherein the body module is specifically configured to switch the state of the body module into a cylindrical shape according to the state mode command if the state mode command is a folding mode; the body module is specifically used for switching the state of the body module into a multi-rotor state according to the state mode instruction if the state instruction is in a flight mode.
3. A micro unmanned aerial vehicle as claimed in claim 1, wherein the body module comprises: the aircraft comprises an airframe framework, a rotor wing installation frame, a plurality of rotor wings, a steering engine, a power supply module, a flight control module and an aircraft arm supporting and retracting mechanism;
the fuselage framework is used for mounting the rotor wing mounting rack, the steering engine, the power supply module, the flight control module and the horn support contraction mechanism;
the rotor wing mounting rack is used for mounting the rotor wings;
the steering engine is used for providing power for the rotors;
the power supply module is used for providing power supply;
the horn supports a retracting mechanism which is used for controlling the rotors to retract or expand;
and the flight control module is used for controlling the horn support retraction mechanism to retract or deploy the rotors according to the state mode instruction.
4. A micro unmanned aerial vehicle as recited in claim 3, wherein the plurality of rotors comprises four rotors.
5. The micro-miniature unmanned aerial vehicle of claim 4, wherein said flight control module is specifically configured to:
if the state mode instruction is a folding mode, controlling the horn support retraction mechanism to retract the four rotors;
and if the aircraft is in a flight mode according to the state mode instruction, controlling the aircraft arm supporting and retracting mechanism to unfold the four rotors so as to switch the form of the airframe module into a four-rotor or multi-rotor form.
6. A micro unmanned aerial vehicle according to any one of claims 3-5, wherein the body module further comprises: an image processing module; the image processing module is arranged on the airframe framework; the image processing module is used for acquiring images and storing the acquired images or transmitting the acquired images to other equipment; the load module is specifically used for loading a camera.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011196036.3A CN112224411B (en) | 2020-10-30 | 2020-10-30 | Microminiature unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011196036.3A CN112224411B (en) | 2020-10-30 | 2020-10-30 | Microminiature unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112224411A CN112224411A (en) | 2021-01-15 |
| CN112224411B true CN112224411B (en) | 2021-10-22 |
Family
ID=74121683
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011196036.3A Active CN112224411B (en) | 2020-10-30 | 2020-10-30 | Microminiature unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112224411B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691589A (en) * | 2016-04-08 | 2016-06-22 | 北京博瑞爱飞科技发展有限公司 | Unmanned aerial vehicle |
| CN205574258U (en) * | 2016-04-08 | 2016-09-14 | 北京博瑞爱飞科技发展有限公司 | Unmanned aerial vehicle |
| CN106347651A (en) * | 2016-11-21 | 2017-01-25 | 北京瀚科瑞杰科技发展有限公司 | Columnar and coaxial double-propeller miniature unmanned aerial vehicle |
| CN110857148A (en) * | 2018-08-22 | 2020-03-03 | 北京理工大学 | Rotor unmanned aerial vehicle ejection device on carrying system |
| CN210882664U (en) * | 2019-11-27 | 2020-06-30 | 福建畅翔智能科技有限责任公司 | Unmanned aerial vehicle laser scanner mounting device |
| CN211364973U (en) * | 2019-08-20 | 2020-08-28 | 贵州电网有限责任公司输电运行检修分公司 | Unmanned aerial vehicle mounting device |
| CN111756983A (en) * | 2020-07-29 | 2020-10-09 | 冀湘元 | Three-dimensional space mobile monitoring equipment |
| CN112249333A (en) * | 2020-09-23 | 2021-01-22 | 北京特种机械研究所 | Microminiature aerial scattering type unmanned aerial vehicle system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IL252808B2 (en) * | 2017-06-11 | 2023-06-01 | Spear U A V Ltd | Launched unmanned aerial vehicle |
-
2020
- 2020-10-30 CN CN202011196036.3A patent/CN112224411B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691589A (en) * | 2016-04-08 | 2016-06-22 | 北京博瑞爱飞科技发展有限公司 | Unmanned aerial vehicle |
| CN205574258U (en) * | 2016-04-08 | 2016-09-14 | 北京博瑞爱飞科技发展有限公司 | Unmanned aerial vehicle |
| CN106347651A (en) * | 2016-11-21 | 2017-01-25 | 北京瀚科瑞杰科技发展有限公司 | Columnar and coaxial double-propeller miniature unmanned aerial vehicle |
| CN110857148A (en) * | 2018-08-22 | 2020-03-03 | 北京理工大学 | Rotor unmanned aerial vehicle ejection device on carrying system |
| CN211364973U (en) * | 2019-08-20 | 2020-08-28 | 贵州电网有限责任公司输电运行检修分公司 | Unmanned aerial vehicle mounting device |
| CN210882664U (en) * | 2019-11-27 | 2020-06-30 | 福建畅翔智能科技有限责任公司 | Unmanned aerial vehicle laser scanner mounting device |
| CN111756983A (en) * | 2020-07-29 | 2020-10-09 | 冀湘元 | Three-dimensional space mobile monitoring equipment |
| CN112249333A (en) * | 2020-09-23 | 2021-01-22 | 北京特种机械研究所 | Microminiature aerial scattering type unmanned aerial vehicle system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112224411A (en) | 2021-01-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR102243228B1 (en) | Release and capture of a fixedwing aircraft | |
| CN107792381B (en) | Unmanned aerial vehicle air-based towing net type recovery device and method | |
| CN101712379B (en) | Folding small-sized unmanned aerial vehicle | |
| CN106516144B (en) | A kind of middle-size and small-size fixed-wing unmanned plane recovery method | |
| CN103101621B (en) | Parafoil aircraft applicable to cylindrical space loading | |
| CN107792371B (en) | Aerial towline towing target system-based unmanned aerial vehicle air-based rapid launching device and method | |
| CN109398709B (en) | External airborne weapon fire control system and use method | |
| CN103010453A (en) | Unmanned plane folded wing unfolding and locking device | |
| CN113086235B (en) | Tubular vertical ejection type ejection unmanned aerial vehicle, ejection system thereof and implementation method | |
| CN115649446B (en) | Full-dimensional group-following type autonomous sliding and descending container carrier for air drop | |
| CN113371182A (en) | Barrel-type transmitted reconnaissance attack rotor unmanned aerial vehicle | |
| CN105460204A (en) | Military unmanned aerial vehicle with portable united wings | |
| CN206427263U (en) | multi-rotor unmanned aerial vehicle undercarriage | |
| CN112319797A (en) | Synchronous deployment mechanism of non-coaxial folding wing of unmanned aerial vehicle | |
| CN112224411B (en) | Microminiature unmanned aerial vehicle | |
| CN109515732B (en) | Combined aircraft based on barrel type launching | |
| CN114237290B (en) | Unmanned aerial vehicle group air recovery system and method | |
| US5363767A (en) | Stand-off weapons | |
| CN114212237B (en) | Accurate air drop/airborne power device | |
| CN212766773U (en) | High altitude unmanned aerial vehicle compels to land auxiliary device | |
| CN206031806U (en) | Aerial photo unmanned plane | |
| CN107902080A (en) | Unmanned plane structure and there is stealthy unmanned plane | |
| CN113220012A (en) | Integrated cabin section for swarm unmanned aerial vehicle and swarm unmanned aerial vehicle | |
| RU226216U1 (en) | MULTI-FUNCTIONAL UNMANNED AIRCRAFT LAUNCHED FROM A TRANSPORT AND LAUNCH CONTAINER | |
| CN113815887A (en) | Quick aerial launching box device |
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 |