Unmanned aerial vehicle with protective structure

Abstract

The unmanned aerial vehicle with the protection structure comprises an unmanned aerial vehicle body, a first grounding foot and second grounding feet, the first grounding foot is hinged to the front side of the lower end of the unmanned aerial vehicle body in a damping mode, and the second grounding feet are hinged to the left rear side and the right rear side of the lower end of the unmanned aerial vehicle body in a damping mode respectively. Compared with the prior art, the unmanned aerial vehicle has the following beneficial effects that by arranging the first grounding pin and the second grounding pin, the impact force generated during falling can be effectively counteracted, the safety of the unmanned aerial vehicle body during falling can be improved, the unmanned aerial vehicle body can be well protected when falling at any position, and due to the arrangement of the first buffer piece and the second buffer piece, the safety of the unmanned aerial vehicle body is improved. The two damping devices are matched with each other, so that impact generated by falling of the unmanned aerial vehicle body can be quickly buffered and counteracted, and sufficient protection is provided for falling of the unmanned aerial vehicle body at any position.

Description

TECHNICAL FIELD

[0001] The utility model belongs to unmanned plane technical field, especially relate to a unmanned plane with protection structure. BACKGROUND

[0002] The inspection unmanned plane generally needs frequent take-off and landing, and the existing unmanned plane lacks effective protection mechanism when landing, which leads to hard landing, damage and safety hazards in complex environment and other problems. These shortcomings mainly result from insufficient attention to the landing process during the design of the unmanned plane, especially in complex terrain or severe weather conditions. The existing conventional coping methods include increasing landing lights, using damping materials and installing auxiliary equipment such as landing parachutes.

[0003] Although these methods can improve landing safety to some extent, they have their own disadvantages. First, increasing landing lights can improve recognition in night or low visibility conditions, but it cannot fundamentally solve the problem of physical impact. Second, although the use of damping materials can absorb part of the impact force, it may still be unable to effectively prevent the unmanned plane from being damaged in high drop or extreme conditions. Although the installation of a landing parachute can increase the slow descent capability, its stability and reliability are poor in high wind speed or sudden wind conditions, which may lead to accidental landing or deviation from the target. Therefore, we hope to design an unmanned plane with a new structure to solve this problem. SUMMARY

[0004] In view of the deficiencies in the prior art, the utility model aims to provide an unmanned plane with a protection structure to solve the problems raised in the background.

[0005] The utility model realizes the following technical scheme: an unmanned plane with a protection structure, comprising: an unmanned plane body, a ground engaging foot one and a ground engaging foot two, the unmanned plane body is hinged and damped at the lower front side with the ground engaging foot one, and the lower left rear side and the right rear side of the unmanned plane body are respectively hinged and damped with one ground engaging foot two;

[0006] The unmanned plane body comprises a rack, a camera and a protection ring, the middle of the lower end of the rack is provided with a camera, and the left side and the right side of the upper end of the rack are respectively provided with one protection ring, and one fan blade is rotatably installed in each protection ring;

[0007] The ground engaging foot one comprises a ground plate one, a hinge rod one and a buffer one, the lower end of the hinge rod is hingedly and dampedly connected with the upper end of the ground plate one, and the lower side of the hinge rod is hingedly and dampedly connected with the lower end of the buffer one;

[0008] The ground engaging foot two comprises a ground plate two and a hinge rod two, and the upper end of the ground plate two is hingedly and dampedly connected with the lower end of the hinge rod two.

[0009] As a preferred implementation, the upper end of the grounding plate is provided with a hinge seat one, the lower side of the front of the hinge rod one is provided with a hinge seat two, the upper end of the hinge seat one is hingedly connected with the lower end of the hinge rod one, the two grounding feet one are arranged to form a stable support structure with the grounding foot two, and the two grounding feet one with the damping function can buffer the landing of the entire unmanned aerial vehicle body.

[0010] As a preferred implementation, the buffer one includes a telescopic rod, a buffer spring, a cylinder and a hinge joint two, the lower end of the hinge joint two is hingedly connected with the upper side of the hinge seat two, and the structure and size of the hinge joint two are matched with the structure and size of the hinge joint one.

[0011] As a preferred implementation, the upper side of the hinge joint two is fixedly connected with the lower end of the cylinder, a piston is slidably arranged in the cylinder, three through holes are formed in the upper surface of the piston and are distributed in a three-equal manner, and the upper end of the piston is fixedly connected with the lower end of the telescopic rod.

[0012] As a preferred implementation, the lower end of the telescopic rod is slidably arranged on the upper side in the cylinder, the upper end of the telescopic rod is fixedly connected with the lower end of the hinge joint one, and the buffer spring is fixed between the hinge joint one and the hinge joint two.

[0013] As a preferred implementation, the upper end of the buffer spring is abutted with the lower end of the hinge joint one, the lower end of the buffer spring is abutted with the upper end of the hinge joint two, and the buffer spring is sleeved on the outer wall of the cylinder.

[0014] As a preferred implementation, the grounding foot two further includes a hinge rod three and a buffer two, the upper end of the grounding plate two is provided with a hinge seat three, the lower end of the hinge rod two is hingedly connected with the hinge seat three, the lower side of the rear of the hinge rod two is provided with a hinge seat four, and the lower end of the hinge rod three is hingedly connected with the upper end of the hinge rod two.

[0015] The lower end of the buffer two is hingedly connected with the lower side of the hinge rod two through the hinge seat four, the structure of the buffer two is the same as that of the buffer one, one grounding foot two is arranged to form a stable support structure with two grounding feet one, and the grounding foot two with the damping function can buffer the landing of the entire unmanned aerial vehicle body.

[0016] The utility model discloses the beneficial effect is: through setting ground foot no. 1 and ground foot no. 2, two ground foot no. 1 and two ground foot no. 2 are isosceles triangle structure distribution, can form the support structure of relatively stable, and the installation direction of ground foot no. 1 and ground foot no. 2 is opposite, namely the counterforce of impact is opposite, makes unmanned aerial vehicle body when falling has greater impact, two ground foot no. 1 and two ground foot no. 2 can be stable and ground contact, cooperate its on buffer piece no. 1 and buffer piece no. 2, can effectively offset the impact when falling, help to promote the security of unmanned aerial vehicle body when falling, has good protection ability to unmanned aerial vehicle body in any position landing.

[0017] The setting of the buffer piece no. 1 and the buffer piece no. 2 greatly improves the damping effect, the operation principle of the buffer piece no. 2 is same with the operation principle of the buffer piece no. 1, and the two cooperate with each other to quickly buffer and offset the impact generated by the falling of the unmanned aerial vehicle body, so as to provide sufficient protection for the falling of the unmanned aerial vehicle body in any position. ACCURACY

[0018] In order to more clearly illustrate the technical scheme in the embodiments of the utility model or the prior art, the following will briefly introduce the drawings needed to be used in the embodiment or the prior art description, and obviously, the drawings in the following description are only some embodiments of the utility model, and for those skilled in the art, other drawings can also be obtained without creative labor under the premise of the drawings.

[0019] Figure 1 It is the whole structure schematic diagram of the utility model of a kind of unmanned aerial vehicle with protective structure.

[0020] Figure 2 It is the schematic diagram of the ground foot no. 1 structure of the utility model of a kind of unmanned aerial vehicle with protective structure.

[0021] Figure 3 It is the schematic diagram of the ground foot no. 2 structure of the utility model of a kind of unmanned aerial vehicle with protective structure.

[0022] Figure 4 It is the schematic diagram of the buffer piece no. 1 structure of the utility model of a kind of unmanned aerial vehicle with protective structure.

[0023] Figure 5 It is the schematic diagram of the cylinder internal structure of the utility model of a kind of unmanned aerial vehicle with protective structure.

[0024] In the drawing, 100-unmanned aerial vehicle body, 110-frame, 120-camera, 130-protection ring, 140-fan blade;

[0025] 200 - ground foot one, 210 - ground plate one, 211 - hinged seat one, 220 - hinged rod one, 221 - hinged seat two, 230 - buffer one, 231 - hinged joint one, 232 - telescopic rod, 233 - buffer spring, 234 - cylinder, 235 - hinged joint two, 236 - piston;

[0026] 300 - ground foot two, 310 - ground plate two, 311 - hinged seat three, 320 - hinged rod two, 321 - hinged seat four, 330 - hinged rod three, 340 - buffer two. DETAILED DESCRIPTION

[0027] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.

[0028] Please refer to Figures 1 to 5 The utility model provides a kind of technical scheme: a kind of unmanned aerial vehicle with protective structure, it include: unmanned aerial vehicle body 100, ground foot one 200 and ground foot two 300, unmanned aerial vehicle body 100 lower end front side damping hinged ground foot one 200, unmanned aerial vehicle body 100 lower end left rear side, right rear side respectively hinged damping have one ground foot two 300;

[0029] Unmanned aerial vehicle body 100 includes rack 110, camera 120 and protective ring 130, rack 110 lower end middle is provided with camera 120, rack 110 upper end left side, right side is provided with one protective ring 130 each, and one fan blade 140 is rotatably installed in each protective ring 130;

[0030] Ground foot one 200 includes ground plate one 210, hinged rod one 220 and buffer one 230, hinged rod one 220 lower end and ground plate one 210 upper end damping hinged, hinged rod front lower side and buffer one 230 lower end damping hinged;

[0031] Ground foot two 300 includes ground plate two 310, hinged rod two 320, and ground plate two 310 upper end and hinged rod two 320 lower end damping hinged.

[0032] Please refer to Figures 1 to 3The upper end of the grounding plate one 210 is provided with a hinge seat one 211, the lower front side of the hinge rod one 220 is provided with a hinge seat two 221, the upper end of the hinge seat one 211 is dampedly hinged with the lower end of the hinge rod one 220, the two grounding feet ones 200 are arranged to form a stable support structure in cooperation with a grounding foot two 300, and the two grounding feet ones 200 with the damping function can buffer the landing of the whole unmanned aerial vehicle body 100.

[0033] As a first embodiment of the utility model, through setting grounding foot one 200 and grounding foot two 300, two grounding feet one 200 and two grounding feet two 300 are distributed in isosceles triangle structure, can form relatively stable support structure, and the installation direction of grounding foot one 200 and grounding foot two 300 is opposite, namely the reaction force of impact is opposite, so that the unmanned aerial vehicle body 100 has greater impact force when falling, two grounding feet one 200 and two grounding feet two 300 can stably contact with the ground, cooperate the buffer one 230 and buffer two 340 on it, can effectively offset the impact force generated when falling, help to improve the safety of unmanned aerial vehicle body 100 when falling, have good protection ability when unmanned aerial vehicle body 100 lands at any position.

[0034] Please refer to Figures 2 to 5 Buffer one 230 includes telescopic rod 232, buffer spring 233, cylinder 234 and hinge joint two 235, the lower end of hinge joint two 235 is hinged with the upper side of hinge seat two 221, and the structure and size of hinge joint two 235 are matched with the structure and size of hinge joint one 231.

[0035] The upper side of hinge joint two 235 is fixedly connected with the lower end of cylinder 234, the piston 236 is slidably installed in the inside of cylinder 234, three through holes distributed in three equal parts are formed in the upper surface of piston 236 downwards, and the lower end of telescopic rod 232 is fixedly connected with the upper end of piston 236.

[0036] The lower end of telescopic rod 232 is slidably installed on the upper side in the inside of cylinder 234, the upper end of telescopic rod 232 is fixedly connected with the lower end of hinge joint one 231, and buffer spring 233 is fixed between hinge joint one 231 and hinge joint two 235.

[0037] The upper end of buffer spring 233 is abutted with the lower end of hinge joint one 231, the lower end of buffer spring 233 is abutted with the upper end of hinge joint two 235, and buffer spring 233 is sleeved on the outer wall of cylinder 234.

[0038] The grounding foot two 300 further includes hinge rod three 320 and buffer two 340, the upper end of grounding plate two 310 is provided with hinge seat three 311, the lower end of hinge rod two 320 is dampedly hinged with hinge seat three 311, the lower rear side of hinge rod two 320 is provided with hinge seat four 321, and the lower end of hinge rod three 320 is hinged with the upper end of hinge rod two 320.

[0039] The lower end of the buffer piece two 340 is hingedly connected with the lower side of the hinge rod two 320 through the hinge seat four 321, the structure of the buffer piece two 340 is same as that of the buffer piece one 230, one ground contact piece two 300 is arranged, stable support structures are formed by the two ground contact piece one 200, and the ground contact piece two 300 with the shock absorption function can buffer the landing of the whole unmanned aerial vehicle body 100.

[0040] As a second embodiment of the utility model, based on the above first embodiment, in actual use, since the structure of the buffer piece two 340 is same as that of the buffer piece one 230, and the installation direction of the buffer piece one 230 and the buffer piece two 340 is opposite (see the description and drawings for details Figure 1 ), when the two ground contact piece one 200 and the two ground contact piece two 300 are synchronously grounded (in actual use, the lower ends of the two ground contact piece one 200 and the two ground contact piece two 300 are flush), the buffer piece one 230 and the buffer piece two 340 are synchronously compressed due to the landing impact of the unmanned aerial vehicle body 100, at this time, the two ground contact piece one 200 and the two ground contact piece two 300 are synchronously bent, the telescopic rod 232 in the buffer piece one 230 is compressed into the cylinder 234, and the piston 236 at the lower end of the telescopic rod 232 is driven to move towards the bottom of the cylinder 234, the inside of the cylinder 234 can be filled with oil, and the height of the oil is preferably half of the depth of the cylinder 234, since the upper surface of the piston 236 is provided with three through holes which are distributed in three equal parts downward, the piston 236 extrudes the oil to form a damping effect, and the impact force is greatly reduced in cooperation with the buffer spring 233;

[0041] When the buffer spring 233 is reset, the piston 236 again forms a damping effect to resist the potential energy, thereby reducing the vibration frequency and amplitude of the ground contact piece one 200 and the ground contact piece two 300, greatly improving the shock absorption effect, the operation principle of the buffer piece two 340 is same as that of the buffer piece one 230, and the two can quickly buffer and offset the impact generated by the landing of the unmanned aerial vehicle body 100, thereby providing sufficient protection for the unmanned aerial vehicle body 100 in any position.

[0042] The above only describes the preferred embodiments of the utility model, and does not limit the utility model, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. A drone with a protective structure, comprising: The unmanned aerial vehicle body (100), the ground foot one (200) and the ground foot two (300) are characterized in that the unmanned aerial vehicle body (100) is hinged and damped with the ground foot one (200) at the front lower end, and one ground foot two (300) is hinged and damped at the left rear and right rear lower ends of the unmanned aerial vehicle body (100) respectively; The unmanned aerial vehicle body (100) comprises a frame (110), a camera (120) and a protective ring (130), the frame (110) is provided with a camera (120) at the middle lower end, and one protective ring (130) is arranged at the left and right upper ends of the frame (110) respectively, and one fan blade (140) is rotatably installed in each protective ring (130); The ground foot one (200) comprises a ground plate one (210), a hinge rod one (220) and a buffer one (230), the hinge rod one (220) is hingedly and dampedly connected with the upper end of the ground plate one (210), and the lower front side of the hinge rod is hingedly and dampedly connected with the lower end of the buffer one (230); The ground foot two (300) comprises a ground plate two (310) and a hinge rod two (320), and the upper end of the ground plate two (310) is hingedly and dampedly connected with the lower end of the hinge rod two (320).

2. The UAV with a protective structure of claim 1, wherein: The upper end of the ground plate one (210) is provided with a hinge seat one (211), the lower front side of the hinge rod one (220) is provided with a hinge seat two (221), and the upper end of the hinge seat one (211) is hingedly and dampedly connected with the lower end of the hinge rod one (220).

3. The UAV with a protective structure of claim 2, wherein: The buffer one (230) comprises a telescopic rod (232), a buffer spring (233), a cylinder (234) and a hinge head two (235), the lower end of the hinge head two (235) is hingedly connected with the upper side of the hinge seat two (221), and the structure and size of the hinge head two (235) are matched with the structure and size of the hinge head one (231).

4. The UAV with a protective structure of claim 3, wherein: The upper side of the hinge head two (235) is fixedly connected with the lower end of the cylinder (234), the cylinder (234) is internally slidably installed with a piston (236), three downwardly penetrating holes are formed on the upper surface of the piston (236) in a three-equal-distribution manner, and the upper end of the piston (236) is fixedly connected with the lower end of the telescopic rod (232).

5. The drone with a protective structure of claim 4, wherein: The lower end of the telescopic rod (232) is slidably installed on the upper side inside the cylinder (234), the upper end of the telescopic rod (232) is fixedly connected with the lower end of the hinge head one (231), and the buffer spring (233) is fixed between the hinge head one (231) and the hinge head two (235).

6. The drone with a protective structure of claim 5, wherein: The upper end of the buffer spring (233) is abutted with the lower end of the hinge head one (231), the lower end of the buffer spring (233) is abutted with the upper end of the hinge head two (235), and the buffer spring (233) is sleeved on the outer wall of the cylinder (234) on the lower side.

7. The drone with a protective structure of claim 1, wherein: The ground foot two (300) further comprises a hinge rod three (330) and a buffer two (340), the upper end of the ground plate two (310) is provided with a hinge seat three (311), and the lower end of the hinge rod two (320) is hingedly and dampedly connected with the hinge seat three (311). The articulated rod two (320) is provided with an articulated seat four (321) on the lower side, and the articulated rod three (330) is articulated with the upper end of the articulated rod two (320); The lower end of the buffer two (340) is articulated with the lower side of the articulated rod two (320) through the articulated seat four (321), and the structure of the buffer two (340) is the same as that of the buffer one (230).

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