Unmanned plane
A technology of unmanned aerial vehicle and fuselage, applied in the field of aircraft, can solve the problem of large occupied space, and achieve the effect of small occupied space, less folding parts, and convenient operation
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Embodiment 1
[0038] according to figure 1 As shown, an unmanned aerial vehicle of the present embodiment is illustrated, including a fuselage 11, the upper two landing gear arms placed on both sides of the fuselage and the motor installation rod 3, wherein the unmanned aerial vehicle also includes an electric folding mechanism 22. The remote control device (not shown in the figure), the control device for controlling the folding of the electric folding mechanism 22 according to the control signal sent by the remote control device, and the rotating member 4, each of the landing gear arms is connected to the fuselage 11 through the electric folding mechanism 22, The electric folding mechanism 22 is electrically connected with the control device, the control device is placed in the fuselage, and the control device is wirelessly connected with the remote control device; one end of the motor mounting rod 3 is provided with a coaxial first motor 51 and a second motor 51 whose output end is revers...
Embodiment 2
[0042] This embodiment is an optimization made on the basis of Embodiment 1: said each landing gear arm includes a first landing gear arm 211 and a second landing gear arm 212, and one end of the first landing gear arm 211 is connected with the electric folding mechanism 22, The other end is connected to one end of the second landing gear arm 212, wherein the angle between the first landing gear arm 211 and the second landing gear arm 212 is 90-135 degrees. Other structures are the same as in Embodiment 1.
[0043] Since the landing gear arm is divided into two parts, and the angle between the two parts can ensure that the second landing gear arm 212 is stably and reliably parked on the ground when it is lowered, and it can also ensure that the second landing gear arm 212 is retracted. Keep a certain distance from the propellers 111 at both ends of the fuselage 11 to avoid the propellers from being impacted by the second landing gear arm 212 during retraction.
Embodiment 3
[0045] This embodiment is an optimization made on the basis of Embodiment 2: the other end of the first landing gear arm 211 is connected to one end of the second landing gear arm 212 through a rotary buckle structure 24 . Other structures are the same as in Embodiment 2.
[0046] When the UAV is stored, the landing gear arm is retracted by the electric folding mechanism, and then the second landing gear arm is rotated to the inside of the fuselage and snapped into place, so that the storage space of the landing gear arm is further reduced and the space utilization rate is improved. . When the UAV is in use, the second landing gear arm 212 is rotated to the outside of the fuselage until the included angle with the first landing gear arm is 90-135 degrees and then snapped and fixed.
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