The present disclosure relates to the field of unmanned aerial vehicle technology and, more particularly, to a foldable unmanned aerial vehicle.
Unmanned aerial vehicles are the most popular aerial photography and video tools, and more consumers choose the unmanned aerial vehicles for capturing photography and video. In order to meet user's portability requirements for the unmanned aerial vehicles, the unmanned aerial vehicles having foldable arms gradually emerge in the current market. The foldable unmanned aerial vehicles may have smaller sizes after the arms are retracted, which may occupy less space and be more portable for users.
However, in actual applications, existing unmanned aerial vehicles may require users to manually unfold or retract the arms to deploy or retrieve the unmanned aerial vehicles, which causes more complicated operation steps.
In accordance with the disclosure, an unmanned aerial vehicle is provided in the present disclosure. The unmanned aerial vehicle includes a fuselage and a plurality of arm assemblies disposed at the fuselage. Each arm assembly includes an arm connected to the fuselage and a drive mechanism for driving the arm to rotate. The arm includes an unfolded state and a folded state. Each drive mechanism is configured to drive a corresponding arm to rotate relative to the fuselage and to enable a switching between the unfolded state and the folded state of the corresponding arm.
In order to more clearly illustrate technical solutions in embodiments of the present disclosure, drawings required for describing the embodiments are briefly illustrated hereinafter. Obviously, the following drawings are merely examples for illustrative purposes according to various disclosed embodiments of the present disclosure and are not intended to limit the scope of the present disclosure. Those skilled in the art may obtain other drawings according to the drawings of the present disclosure without any creative efforts.
The technical solutions in the embodiments of the present disclosure are clearly and completely described in the following with reference to the accompanying drawings in the embodiments of the present disclosure. It is obvious that the described embodiments are merely a part of the embodiments of the present disclosure, but not all embodiments. All other embodiments, based on the embodiments of the present disclosure, obtained by those skilled in the art without creative efforts are within the scope of the present disclosure.
Exemplary embodiments illustrated in the accompanying drawings are described in detail herein. When the accompanying drawings are described, same numerals in different drawings refer to same or similar elements unless otherwise indicated. The embodiment methods described in the following exemplary embodiments do not represent all embodiments consistent with the present disclosure. Instead, they are merely examples of devices and methods consistent with aspects of the disclosure as detailed in the appended claims.
The terminology used in the present disclosure is merely for the purpose of describing particular embodiments and is not intended to limit the disclosure. The singular forms “a”, “said”, and “the” used in the present disclosure and the appended claims may also include plural forms, unless the context clearly indicates other meanings. It should also be understood that the term “and/or” used in the present disclosure refers to and encompasses any and all possible combinations of one or more of associated listed items.
The present disclosure provides an unmanned aerial vehicle, which may include a fuselage and a plurality of arm assemblies disposed at the fuselage. For example, the plurality of arm assemblies may be disposed at an upper portion, a lower portion, a front portion, and/or a rear portion of a circumferential side of the fuselage. In some embodiments, the plurality of arm assemblies may be disposed on desired portion(s) of the circumferential side of the fuselage. Each arm assembly may include an arm connected to the fuselage and a drive mechanism for driving the arm to rotate. The arm may include an unfolded state and a folded state. The drive mechanism may drive a corresponding arm to rotate relative to the fuselage and enable the arm to switch between the unfolded state and the folded state. The unmanned aerial vehicle of the present disclosure may drive the arm to be unfolded or folded by the drive mechanism, thereby implementing the automatic unfolding or folding of the arm of the unmanned aerial vehicle, which may simplify user operation steps and be convenient for users.
The unmanned aerial vehicle of the present disclosure may be described in detail with reference to the drawings hereinafter. In case of no conflict, following embodiments and features of the embodiments may be combined with each other.
Referring to
An accommodation trench 100 may be disposed on a top of the fuselage 10. The battery 50 may be at least partially disposed in the accommodation trench 100. For example, the battery 50 may be partially or wholly disposed in the accommodation trench 100. The battery 50 may be electrically connected to a controller for supplying power to the controller. The controller may be disposed on a motor board 30, and the motor board 30 may be disposed in the accommodation trench 100 and attached to a bottom of the battery 50. A heat dissipation plate may be disposed at a bottom of the accommodation trench 100. The heat dissipation plate may be attached to the motor board 30 to dissipate heat for the motor board 30.
The gimbal camera 60 may be disposed at a front of the fuselage 10. The gimbal camera 60 may include a gimbal bracket and a camera mounted on the gimbal bracket. Optionally, the gimbal bracket may be a three-axis gimbal bracket. The gimbal bracket may include a yaw axis assembly, a roll axis assembly movably connected to the yaw axis assembly, and a pitch axis assembly movably connected to the roll axis assembly. The camera may be mounted on the pitch axis assembly.
The arm assemblies 201 and 202 may include arms 221 and 222 connected to the fuselage 10, drive mechanisms 211 and 212, and propeller assemblies. The drive mechanisms 211 and 212 may be electrically connected to the controller and be capable of driving the corresponding arms 221 and 222 to rotate relative to the fuselage 10, thereby implementing the portability of the foldable arms of the unmanned aerial vehicle 1. The propeller assemblies may include motors 70 disposed at the arms 221 and 222, and propellers (not shown) connected to the motors 70, and the motors 70 may drive the propellers to rotate, thereby implementing the flight function of the unmanned aerial vehicle 1. In one embodiment, the drive mechanisms 211 and 212 may be disposed at ends of arms 221 and 222; the motors 70 of the propeller assemblies may be disposed at ends of the arms 221 and 222 away from the drive mechanisms 211 and 212; and the arms 221 and 222 may be connected to the fuselage 10 through the corresponding drive mechanisms 211 and 212.
Referring to
In the embodiments shown in
The status indicator 420 may be disposed at a rear portion of the fuselage 10 to indicate a current status of the unmanned aerial vehicle. The unmanned aerial vehicle may be used with a remote control. A GPS positioning system, a vision system, an alarm system, a sensor, a compass and the like may be disposed inside the unmanned aerial vehicle. The status indicator lights 420 may flash different colors to indicate different statuses of the unmanned aerial vehicle. For example, when the status indicator lights 420 flash red, green and yellow continuously, it may indicate self-diagnostic testing; when the status indicator lights 420 flash alternating yellow and green, it may indicate warming up; when the status indicator lights 420 flash green slowly, it may indicate using the GPS positioning; when the status indicator lights 420 have two green flashing, it may indicate using the vision system; when the status indicator lights 420 flash yellow slowly, it may indicate no GPS and no vision system; when the status indicator lights 420 flash green fast, it may indicate braking; when the status indicator lights 420 flash yellow fast, it may indicate remote controller signal lost; when the status indicator lights 420 flash red slowly, it may indicate low battery warning; when the status indicator lights 420 flash red fast, it may indicate critical low battery warning; when the status indicator lights 420 flash alternating red, it may indicate uneven placement or large sensor error; when the status indicator lights 420 flash solid red, it may indicate critical error; and when the status indicator lights 420 flash alternating red and yellow, it may indicate compass calibration required.
Referring to
It can be seen from the above-mentioned embodiments that the unmanned aerial vehicle 1 of the present disclosure may transmit control signals to the drive mechanisms 211 and 212 through the controller, and the corresponding arms 221 and 222 may be driven to be unfolded or folded by the drive mechanisms 211 and 212, thereby implementing the automatic unfolding and folding of the arms 221 and 222 of the unmanned aerial vehicle 1. In such way, the enjoyment and intelligence level of using products may be increased; the user operation steps may be simplified; and the user operation may be more convenient, thereby improving the user experience and the product market competitiveness.
In an optional embodiment, the control signals transmitted by the controller to the drive mechanisms 211 and 212 may include a first signal for controlling the drive mechanisms 211 and 212 to rotate along a first direction, thereby driving the corresponding arms 221 and 222 to rotate along the first direction by the drive mechanisms 211 and 212. In one embodiment, the rotation of the arms 221 and 222 along the first direction driven by the drive mechanisms 211 and 212 may refer to that the arms 221 and 222 are rotated from the folded state to the unfolded state, that is, the drive mechanisms 211 and 212 may drive the arms 221 and 222 to rotate along the direction away from the fuselage 10. After the user turns on the unmanned aerial vehicle 1 and completes the aircraft detection successfully, the controller may synchronously transmit the first signal to the respective drive mechanisms 211 and 212 of the plurality of arm assemblies 201 and 202, so the respective drive mechanisms 211 and 212 of the plurality of arm assemblies 201 and 202 may drive the corresponding arms 221 and 222 to synchronously rotate relative to the fuselage to the unfolded state.
In an optional embodiment, the control signals transmitted by the controller to the drive mechanisms 211 and 212 may include a second signal for controlling the drive mechanisms 211 and 212 to rotate along a second direction, thereby driving the corresponding arms 221 and 222 to rotate along the second direction by the drive mechanisms 211 and 212, where the second direction may be opposite to the first direction. In one embodiment, the rotation of the arms 221 and 222 along the second direction driven by the drive mechanisms 211 and 212 may refer to that the arms 221 and 222 are rotated from the unfolded state to the folded state, that is, the drive mechanisms 211 and 212 may drive the arms 221 and 222 to rotate along the direction close to the fuselage 10. After the user turns off the unmanned aerial vehicle 1 and completes the aircraft detection successfully, the controller may synchronously transmit the second signal to the respective drive mechanisms 211 and 212 of the plurality of arm assemblies 201 and 202, so the respective drive mechanisms 211 and 212 of the plurality of arm assemblies 201 and 202 may drive the corresponding arms 221 and 222 to synchronously rotate relative to the fuselage to the folded state.
In an optional embodiment, the unmanned aerial vehicle 1 may further include a power button 40. The power button 40 may be disposed on the battery 50 and electrically connected to the controller. When the user presses the power button 40 to turn on the unmanned aerial vehicle 1, and the respective drive mechanisms 211 and 212 of the plurality of arm assemblies 201 and 202 may drive the corresponding arms 211 and 212 to be unfolded till rotating to the unfolded state. When the user presses the power button 40 to turn off the unmanned aerial vehicle 1, and the respective drive mechanisms 211 and 212 of the plurality of arm assemblies 201 and 202 may drive the corresponding arms 211 and 212 to be folded till rotating to the folded state.
In an optional embodiment, the arm assemblies 201 and 202 may further include stopping portions 231 and 232. The stopping portions 231 and 232 may be disposed at the fuselage 10 along a rotation direction of the arms 221 and 222. In some embodiments, the stopping portions 231 and 232 may be disposed on the fuselage 10. The rotation direction may refer to a direction of the arms 221 and 222 from the folded state to the unfolded state. When the arms 221 and 222 rotate from the folded state to the unfolded state, the arms 221 and 222 may abut against the stopping portions 231 and 232, and the stopping portions 231 and 232 may limit positions of the arms 221 and 222. When the arms 221 and 222 rotate from the unfolded state to the folded state, the arms 221 and 222 may attach to the fuselage 10.
Furthermore, the control signals transmitted by the controller to the drive mechanisms 211 and 212 may include a third signal for controlling the drive mechanisms 211 and 212 to continuously rotate along the first direction, so the drive mechanisms 211 and 212 may drive the corresponding arms 221 and 222 to continuously rotate along the first direction. When the arms 221 and 222 are in the unfolded state, the controller may transmit the third signal to the respective drive mechanisms 211 and 212 of the plurality of arm assemblies 201 and 202, so the mechanisms 211 and 212 of the plurality of arm assemblies 201 and 202 may drive the corresponding arms 221 and 222 to abut against the stopping portions 231 and 232 with a continuous drive force. That is, after the arms 221 and 222 are rotated to the unfolded state, the arms 221 and 222 may be stopped by the stopping portions 231 and 232, but the battery 50 may continue to supply power to the drive mechanisms 211 and 212 to provide a certain torque to maintain the unfolding torque of the arms 221 and 222. In such way, the situation that folding the arms 221 and 222 of the unmanned aerial vehicle 1 during flight or being hit may be avoided; and until the user presses the power button 40 to turn off the unmanned aerial vehicle 1, the controller may transmit the second signal to the drive mechanisms 211 and 212, thereby driving the corresponding arms 221 and 222 to be folded by the drive mechanisms 211 and 212.
In an optional embodiment, the unmanned aerial vehicle 1 may be a multiple propeller unmanned aerial vehicle. The plurality of arm assemblies 201 and 202 may include at least two first arm assemblies 201 and at least two second arm assemblies 202. The at least two first arm assemblies 201 may be disposed at the front portion of the fuselage 10, and the at least two second arm assemblies 202 may be disposed at the rear portion of the fuselage 10.
A quad-propeller unmanned aerial vehicle may be used as an example of the unmanned aerial vehicle 1 to describe the unmanned aerial vehicle 1 of the present disclosure in detail hereinafter. The quantity of the first arm assemblies 201 may be two, and the first arm assemblies 201 may be disposed on two sides of the front portion of the fuselage 10. The quantity of the second arm assemblies 202 may be two, and the second arm assemblies 202 may be disposed on two sides of the rear portion of the fuselage 10.
The first arm assembly 201 may include a first drive mechanism 211 disposed at the front portion of the fuselage 10, a first arm 221 connected to the first drive mechanism 211, and a first stopping portion 231 disposed at the fuselage 10 (e.g., disposed on the fuselage 10) along the rotation direction of the first arm 221. The first drive mechanism 211 may be connected to the controller, and the controller may transmit the control signals to the first drive mechanism 211 to drive the first arm 221 to rotate relative to the fuselage 10 by the first drive mechanism 211. In one embodiment, for the first arm assembly 201, the first drive mechanism 221 may be perpendicularly connected to the first arm 211, and the controller may control the first drive mechanism 211 of the first arm assembly 201 to rotate along a vertical direction 910, thereby driving the first arm 221 to rotate along the vertical direction 910 relative to the fuselage 10 by the first drive mechanism 211, that is, the first drive mechanism 211 may drive the first arm 221 to be folded back and forth relative to the fuselage 10.
The second arm assembly 202 may include a second drive mechanism 212 disposed at the rear portion of the fuselage 10, a second arm 222 connected to the second drive mechanism 212, and a second stopping portion 232 disposed at the fuselage 10 (e.g., disposed on the fuselage 10) along the rotation direction of the second arm 222. The second drive mechanism 212 may be connected to the controller, and the controller may transmit the control signals to the second drive mechanism 212 to drive the second arm 222 to rotate relative to the fuselage 10 by the second drive mechanism 212. In one embodiment, for the second arm assembly 202, the second drive mechanism 222 and the second arm 212 may be connected in a tilted direction (e.g., a non-vertical direction or a non-horizontal direction), and the controller may control the second drive mechanism 212 of the second arm assembly 202 to rotate along a horizontal direction 920, thereby driving the second arm 222 to rotate along the horizontal direction 920 relative to the fuselage 10 by the second drive mechanism 212, that is, the second drive mechanism 212 may drive the second arm 222 to be folded up and down relative to the fuselage 10.
Furthermore, a stand 80, used for take-off and landing of the unmanned aerial vehicle 1, may be disposed at the bottom of one end of the first arm 221 of the first arm assembly 201 having the motor. In order to prevent the first arm 221 and the second arm 222 from being unable to be unfolded or folded normally during the unfolding or folding process due to the impact of the stand 80, the controller may transmit control signals to the first drive mechanism 211 and the second drive mechanism 212 according to a specified sequence, so the first arm 221 and the second arm 222 may be sequentially unfolded or folded according to the specified sequence.
After the user turns on the unmanned aerial vehicle 1 and completes the aircraft detection successfully, the controller may sequentially transmit the first signal to the first drive mechanism 211 and the second drive mechanism 212 according a first sequence, so the first arm 221 and the second arm 222 may be sequentially rotated to the unfolded state. In one embodiment, the first sequence may refer to that the controller first transmits the control signal to the first drive mechanism 211 and then transmits the control signal to the second drive mechanism 212. That is, the controller may first transmit the first signal to the first drive mechanism 211 and then transmit the first signal to the second drive mechanism 212, so the first drive mechanism 211 may first drive the first arm 221 to be unfolded, and then the second drive mechanism 212 may drive the second arm 222 to be unfolded. In such way, the situation that the first arm 221 may not be unfolded normally because the stand 80 is blocked by the second arm 222 after the second arm 222 is unfolded before the first arm 221 may be prevented.
After the user turns off the unmanned aerial vehicle 1 and completes the aircraft detection successfully, the controller may sequentially transmit the second signal to the first drive mechanism 211 and the second drive mechanism 212 according a second sequence, so the first arm 221 and the second arm 222 may be sequentially rotated to the folded state, where the second sequence may be opposite to the first sequence. In one embodiment, the second sequence may refer to that the controller first transmits the control signal to the second drive mechanism 212 and then transmits the control signal to the first drive mechanism 211. That is, the controller may first transmit the second signal to the second drive mechanism 212 and then transmit the second signal to the first drive mechanism 211, so the second drive mechanism 212 may first drive the second arm 222 to be unfolded, and then the first drive mechanism 211 may drive the first arm 221 to be unfolded. In such way, the situation that the first arm 221 may not be folded normally because the stand 80 is blocked by the second arm 222 after the first arm 221 is folded before the second arm 222 may be prevented.
In an optional embodiment, referring to
Furthermore, the first arm 221 may include a first sidewall and a second sidewall, configured opposite to each other. A first abutting portion 2214 may be disposed at the first sidewall of the first arm 221, and a first attaching portion 2215 may be disposed at the second sidewall of the first arm 221. When the first arm 221 is rotated to the unfolded state, the first abutting portion 2214 may abut against the first stopping portion 231. When the first arm 221 is rotated to the folded state, the first attaching portion 2215 may attach to the fuselage 10. The second arm 222 may include a first sidewall and a second sidewall, configured opposite to each other. A second abutting portion 2222 may be disposed at the first sidewall of the second arm 222, and a third abutting portion 2223 may be disposed at the second sidewall of the second arm 222. A second attaching portion 2224 may be disposed at a third sidewall which is between the first sidewall and the second sidewall of the second arm 222 and adjacent to the fuselage 10. When the second arm 222 is rotated to the unfolded state, the second abutting portion 2222 may abut against the second stopping portion 232. When the second arm 222 is rotated to the folded state, the third abutting portion 2223 may abut against the second stopping portion 232, and the second attaching portion 2224 may attach to the fuselage 10.
In an optional embodiment, referring to
Referring to
Referring to
It should be noted that, in the present disclosure, relationship terms such as first, second and the like are merely used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such relationship or sequence between the entities or operations. The terms “including”, “comprising” or other variants thereof are intended to encompass non-exclusive inclusions, so a process, a method, an item or an device including a series of elements may include such elements, but also include other elements which are not explicitly listed, or include elements which are inherent to the process, the method, the item, or the device. Without additional restrictions, elements defined by the phrase “include a . . . ” does not exclude the presence of additional same elements in the process, the method, the item, or the device including the series of elements.
The unmanned aerial vehicle provided by the embodiments of the present disclosure is described in detail above. The principles and embodiment methods of the present disclosure are described with reference to specific examples, and the description of the above-mentioned embodiments is merely for understanding the essential concept of the present disclosure. Meanwhile, the implementation manner and application scope may be changed by those skilled in the art according to the concept of the present disclosure. The contents of the specification should not be construed as limiting the scope of the disclosure.
This application is a continuation of International Application No. PCT/CN2017/099700, filed Aug. 30, 2017, the entire content of which is incorporated herein by reference.
Number | Date | Country | |
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Parent | PCT/CN2017/099700 | Aug 2017 | US |
Child | 16748998 | US |