Quick-release battery mechanism for folding coaxial barrel type aircraft

Abstract

The utility model discloses a quick-release battery mechanism for a folding coaxial barrel-shaped aircraft, which comprises a lower aircraft and an upper aircraft which are respectively arranged at the upper part and the lower part of a barrel-shaped battery pack, and relates to the technical field of quick-release batteries. According to the quick-release battery mechanism for the folding coaxial barrel-shaped aircraft, a first steering wheel and a second steering wheel are arranged on the opposite sides of a barrel-shaped battery pack, an upper aircraft and a lower aircraft correspondingly, a first clamping block and a second clamping block are installed on the inner sides, and the quick-release battery mechanism is used in cooperation with a first guide clamping groove and a second guide clamping groove; due to the arrangement of the structures, when the cylindrical battery pack is disassembled, a first clamping block and a second clamping block can be separated from a first guide clamping groove and a second guide clamping groove respectively only by rotating a first steering wheel and a second steering wheel in sequence by a worker, so that the effect of quickly disassembling the cylindrical battery pack is achieved; and the overall use efficiency of the aircraft is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to quick detach battery technical field, concretely is a kind of quick detach battery mechanism for folding coaxial cylinder type aircraft. BACKGROUND

[0002] Coaxial cylinder type aircraft is the current more novel small aircraft, since its whole simple and convenient is thermos cup, small, light in weight, and fan can be folded very portable, while endurance time can be increased by about one time compared with same level multicopter unmanned aerial vehicle, effectively improve the development speed of current small aircraft.

[0003] Although current coaxial cylinder type aircraft is high in flexibility and long in endurance time, it still needs to be charged in time, but when charging, the battery inside the aircraft needs to be detached for separate charging, and the battery is relatively cumbersome to detach, cannot be quickly detached, resulting in low efficiency in battery replacement, thereby indirectly affecting the practicability of the aircraft.

[0004] Therefore, a quick detach battery mechanism for folding coaxial cylinder type aircraft is designed to improve speed to solve such defects INVENTION CONTENTS

[0005] In view of the deficiencies of the prior art, the utility model provides a quick detach battery mechanism for folding coaxial cylinder type aircraft, which solves the problem of slow battery detachment speed of existing coaxial cylinder type aircraft.

[0006] To achieve the above purpose, the utility model is implemented by the following technical scheme: a quick detach battery mechanism for folding coaxial cylinder type aircraft, comprising a lower aircraft and an upper aircraft arranged on the upper and lower parts of a cylindrical battery pack respectively, a first connector fixedly installed on the top of the upper aircraft, a second connector fixedly installed on the bottom of the cylindrical battery pack and matched with the first connector, a third connector fixedly installed on the top of the cylindrical battery pack, and a fourth connector fixedly installed on the bottom of the lower aircraft.

[0007] Preferably, the upper part of the surface of the cylindrical battery pack is rotatably connected with a first steering disc through a bearing piece, the upper side of the inner wall of the first steering disc is fixedly connected with a first clamping block, and the first clamping block is provided with a plurality of first clamping blocks.

[0008] Preferably, the lower part of the surface of the cylindrical battery pack is provided with a first guide clamping groove matched with the first clamping block, and the number of the first guide clamping groove is the same as that of the first clamping block.

[0009] Preferably, the upper part of the surface of the cylindrical battery pack is rotatably connected with a second steering disc through a bearing piece, the upper side of the inner wall of the second steering disc is fixedly connected with a second clamping block, and the second clamping block is provided with a plurality of second clamping blocks.

[0010] Preferably, the lower part of the lower aircraft surface is provided with a second guide clamping groove, and the number of the second guide clamping groove is same as that of the second clamping block.

[0011] Beneficial effects

[0012] The utility model provides a quick release battery mechanism for folding coaxial cylinder type aircraft, which has the following beneficial effects compared with the prior art:

[0013] (1), the quick release battery mechanism for folding coaxial cylinder type aircraft, through being provided with first steering disc and second steering disc on the side of cylinder battery group, upper aircraft and lower aircraft opposite each other respectively, and being provided with first clamping block and second clamping block on the inner side, and being used in conjunction with first guide clamping groove and second guide clamping groove, the arrangement of these structures can make first clamping block and second clamping block separate from first guide clamping groove and second guide clamping groove respectively when cylinder battery group is disassembled, so that the effect of quick release of cylinder battery group is achieved, and the use efficiency of the whole aircraft is improved.

[0014] (2), the quick release battery mechanism for folding coaxial cylinder type aircraft, through being electrically connected between cylinder battery group, upper aircraft and lower aircraft by first butt joint, second butt joint, third butt joint and fourth butt joint, the arrangement of these structures can ensure that upper aircraft is smoothly powered after being connected with lower aircraft and cylinder battery group, and will not be easily loosened, and the stability of the whole equipment is improved. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 It is a structural schematic view of the utility model;

[0016] Figure 2 It is a bottom view of first butt joint, first steering disc and first clamping block structure of the utility model;

[0017] Figure 3 It is a schematic view of cylinder battery group, second butt joint and first guide clamping groove structure of the utility model;

[0018] Figure 4 It is a schematic view of third butt joint, second steering disc and second clamping block structure of the utility model;

[0019] Figure 5 It is a schematic view of lower aircraft, third butt joint and second guide clamping groove structure of the utility model.

[0020] In the figure: 1, cylindrical battery pack; 2, upper aircraft; 3, lower aircraft; 4, first joint; 5, second joint; 6, third joint; 7, fourth joint; 8, first guide clamping groove; 9, first steering disc; 10, first clamping block; 11, second steering disc; 12, second clamping block; 13, second guide clamping groove. DETAILED DESCRIPTION

[0021] The technical solutions in the embodiments of the utility model will be apparently and completely described in conjunction with 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.

[0022] Please refer to Figures 1-5 The utility model provides a kind of technical scheme: a quick-release battery mechanism for folding coaxial cylinder aircraft, including lower aircraft 3 and upper aircraft 2 respectively arranged in the upper and lower parts of cylindrical battery pack 1, the top of upper aircraft 2 is fixedly installed with first joint 4, the bottom of cylindrical battery pack 1 is fixedly installed with second joint 5 used in cooperation with first joint 4, the top of cylindrical battery pack 1 is fixedly installed with third joint 6, the bottom of lower aircraft 3 is fixedly installed with fourth joint 7, the upper part of the surface of cylindrical battery pack 1 is rotatably connected with first steering disc 9 by bearing piece, the upper side of the inner wall of first steering disc 9 is fixedly connected with first clamping block 10, and first clamping block 10 is provided with several, the lower part of the surface of cylindrical battery pack 1 is provided with first guide clamping groove 8 used in cooperation with first clamping block 10, and the number of first guide clamping groove 8 and first clamping block 10 is same, and first guide clamping groove 8 and first clamping block 10 are interference fit with friction.

[0023] When using, staff first installs cylindrical battery pack 1 on the bottom of lower aircraft 3, first aligns third joint 6 with fourth joint 7, then rotates second steering disc 11 to make several second clamping blocks 12 align with second guide clamping groove 13, then presses cylindrical battery pack 1 to make third joint 6 insert fourth joint 7 and rotates second steering disc 11, to make second clamping block 12 slide to the top of second guide clamping groove 13 under the guidance of second guide clamping groove 13, at this time, second clamping block 12 and second guide clamping groove 13 are clamped, then install upper aircraft 2 on the bottom of cylindrical battery pack 1, also first align first joint 4 with second joint 5, and rotate first steering disc 9 to drive first clamping block 10 and first guide clamping groove 8 to be clamped, then can be used with power.

[0024] Further, the upper portion of the surface of the cylindrical battery pack 1 is rotatably connected with a second steering disc 11 through a bearing piece, the upper side of the inner wall of the second steering disc 11 is fixedly connected with second clamping blocks 12, and the second clamping blocks 12 are provided with a plurality of second guiding clamping grooves 13 are arranged on the lower portion of the surface of the lower aircraft 3, and the number of the second guiding clamping grooves 13 is same as that of the second clamping blocks 12, and the second guiding clamping grooves 13 and the second clamping blocks 12 are in interference fit and have friction force.

[0025] When disassembly is needed, the first steering disc 9 and the second steering disc 11 are rotated in sequence to separate the first clamping blocks 10 and the second clamping blocks 12 from the inner side of the first guiding clamping grooves 8 and the second guiding clamping grooves 13 respectively, and then the cylindrical battery pack 1 is taken out for charging or replacement.

[0026] Meanwhile, the contents not described in detail in the specification all belong to the prior art known to those skilled in the art.

Claims

1. A quick-release battery mechanism for a folded coaxial cylindrical aircraft, comprising a lower aircraft (3) and an upper aircraft (2) disposed on the upper and lower portions of a cylindrical battery pack (1), respectively, characterized in that: The top of the upper aircraft (2) is fixedly provided with a first pair of joints (4), the bottom of the cylindrical battery pack (1) is fixedly provided with a second pair of joints (5) matched with the first pair of joints (4), the top of the cylindrical battery pack (1) is fixedly provided with a third pair of joints (6), and the bottom of the lower aircraft (3) is fixedly provided with a fourth pair of joints (7).

2. A quick release battery mechanism for a folded coaxial cylinder aircraft according to claim 1, characterized in that: The upper part of the surface of the cylindrical battery pack (1) is rotatably connected with a first steering disc (9) through a bearing piece, the upper side of the inner wall of the first steering disc (9) is fixedly connected with a first clamping block (10), and the first clamping block (10) is provided with a plurality of first clamping blocks (10).

3. A quick release battery mechanism for a folded coaxial cylinder aircraft according to claim 1, wherein: The lower part of the surface of the cylindrical battery pack (1) is provided with a first guide clamping groove (8) matched with the first clamping block (10), and the number of the first guide clamping groove (8) is the same as that of the first clamping block (10).

4. A quick release battery mechanism for a folded coaxial cylinder aircraft according to claim 1, wherein: The upper part of the surface of the cylindrical battery pack (1) is rotatably connected with a second steering disc (11) through a bearing piece, the upper side of the inner wall of the second steering disc (11) is fixedly connected with a second clamping block (12), and the second clamping block (12) is provided with a plurality of second clamping blocks (12).

5. A quick release battery mechanism for a folded coaxial cylinder aircraft according to claim 4, wherein: The lower part of the surface of the lower aircraft (3) is provided with a second guide clamping groove (13), and the number of the second guide clamping groove (13) is the same as that of the second clamping block (12).

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