CN112455645B - Collapsible unmanned aerial vehicle - Google Patents
Collapsible unmanned aerial vehicle Download PDFInfo
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- CN112455645B CN112455645B CN202011466853.6A CN202011466853A CN112455645B CN 112455645 B CN112455645 B CN 112455645B CN 202011466853 A CN202011466853 A CN 202011466853A CN 112455645 B CN112455645 B CN 112455645B
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- undercarriage
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- 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
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- 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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
- B64C2025/125—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The invention relates to the technical field of unmanned aerial vehicles, and discloses a foldable unmanned aerial vehicle which comprises a vehicle body, a plurality of vehicle arms and a plurality of undercarriage, wherein each vehicle arm is provided with a joint component, the vehicle body and the undercarriage are hinged with the joint components, each vehicle arm can horizontally rotate relative to the vehicle body, each joint component is provided with a first telescopic piece and a second telescopic piece, the vehicle body is provided with a first positioning through hole, the movable end of each first telescopic piece can be inserted into the first positioning through hole from one end of the first positioning through hole, the vehicle body is provided with a first pin column, the first pin column can be inserted into or withdrawn from the first positioning through hole from the other end of the first positioning through hole, the undercarriage can vertically rotate relative to the vehicle body, the undercarriage is provided with a second positioning through hole, the movable end of each second telescopic piece can be inserted into the second positioning through hole from one end of the second positioning through hole, the undercarriage is provided with a second pin column, the second pin column can be inserted into or withdrawn from the second positioning through hole from the other end of the second positioning through hole, and an antenna is embedded in the undercarriage. The horn and undercarriage are collapsible, reduce occupation space, portable and transportation.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a foldable unmanned aerial vehicle.
Background
In order to ensure stable flight of the existing unmanned aerial vehicle, the size of the unmanned aerial vehicle is set to be larger; however, the bulky drone occupies a large space, is inconvenient to carry, and is easily damaged in transportation and carrying.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a foldable unmanned aerial vehicle, which solves the problem of inconvenience in carrying.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the utility model provides a collapsible unmanned aerial vehicle, includes fuselage, a plurality of horn and a plurality of undercarriage, the horn is equipped with joint part, fuselage and undercarriage all articulate with joint part, the horn is the fuselage level relatively and rotates, joint part is equipped with first extensible member, first positioning through-hole has been seted up to the fuselage, works as first predetermined angle is opened to the relative fuselage of horn, first extensible member's expansion end can insert first positioning through-hole from the one end of first positioning through-hole, the fuselage is equipped with first round pin post movably, first round pin post can insert or withdraw from first positioning through-hole from the other end of first positioning through-hole, the undercarriage is the vertical rotation of fuselage relatively, joint part still is equipped with the second extensible member, the second positioning through-hole has been seted up to the undercarriage, works as the undercarriage opens the predetermined angle of second for the horn, the one end that second positioning through-hole can be followed to the expansion end of second extensible member inserts the second positioning through-hole, the undercarriage is equipped with second round pin post movably, the second round pin post can insert or withdraw from the other end of second positioning through-hole, be equipped with the antenna in the undercarriage.
As the improvement of above-mentioned technical scheme, the fuselage is equipped with first location blind hole, first location blind hole and first location through-hole pass through circular arc blind groove and connect, the centre of a circle of circular arc blind groove is the articulated center of fuselage and joint part, the head of first extensible member expansion end is the hemisphere, works as the relative fuselage of horn is folded the third and is predetermine the angle, the head of first extensible member expansion end can insert first location blind hole.
As an improvement of the above technical scheme, the fuselage is provided with a first unlocking snap fastener, the first unlocking snap fastener comprises a first pressing piece, a first connecting portion fixedly arranged on the fuselage and a first inclined reset elastic piece connected with the first pressing piece and the first connecting portion, a space is arranged between the first pressing piece and the fuselage, a first pin column is arranged on the first pressing piece, and the first pin column is positioned between the first pressing piece and the fuselage.
As an improvement of the technical scheme, the undercarriage is provided with a second positioning blind hole, the second positioning through hole and the second positioning blind hole are distributed on a circumference which takes the hinge center of the undercarriage and the joint part as the circle center, the head of the movable end of the second telescopic piece is hemispherical, when the undercarriage is folded by a fourth preset angle relative to the machine arm, the head of the movable end of the second telescopic piece can be inserted into the second positioning blind hole.
As an improvement of the above technical solution, a first hemispherical groove is formed at one end of the first pin near the first telescopic member, and a second hemispherical groove is formed at one end of the second pin near the second telescopic member.
As an improvement of the above technical scheme, the undercarriage is provided with a second unlocking snap fastener, the second unlocking snap fastener comprises a second pressing piece, a second connecting portion fixedly arranged on the undercarriage and a second inclined reset elastic piece connected with the second pressing piece and the second connecting portion, a gap is formed between the second pressing piece and the undercarriage, the second pin column is arranged on the second pressing piece, and the second pin column is positioned between the second pressing piece and the undercarriage.
As an improvement of the above technical scheme, a blind groove is formed in the first side of the joint component, the depth direction of the blind groove is in the horizontal direction, the undercarriage is hinged to the second side of the joint component through a second connecting shaft which horizontally penetrates through the bottom surface of the blind groove, the second side of the joint component is opposite to the first side, the second telescopic piece is a spring plunger, and the second telescopic piece is installed on the second side of the joint component.
As an improvement of the technical scheme, the machine body is provided with a clamping groove, the joint component is clamped in the clamping groove and hinged to the machine body through a first connecting shaft which penetrates through the side wall of the blind groove from top to bottom, the upper end and the lower end of the joint component are respectively provided with a first telescopic piece, the first telescopic piece is a spring plunger, and the upper wall and the lower wall of the clamping groove are respectively provided with a first positioning through hole.
As an improvement of the above technical scheme, a pipe joint is arranged on the third side of the joint component, a wire passing hole is arranged in the pipe joint and communicated with the blind groove, a wire accommodating groove is arranged on the fourth side of the joint component and located on the side wall of the blind groove, and the wire accommodating groove is communicated with the blind groove.
As an improvement of the technical scheme, the machine arm comprises a pipe arm sleeved outside the pipe joint and a propeller assembly arranged on the pipe arm, the pipe joint and the pipe arm are fixed through a positioning screw, a wire connected with the propeller assembly is arranged inside the pipe arm, and the wire is arranged in the wire passing hole, the blind groove and the wire accommodating groove.
The beneficial effects of one aspect of the invention are as follows:
according to one aspect of the disclosure, when the unmanned aerial vehicle is used, the horn and the undercarriage are directly opened, the first extensible member and the second extensible member are respectively inserted into the first positioning through hole and the second positioning through hole to position the horn and the undercarriage, no additional locking step is needed, the operation is simple, the time is saved, the locking is reliable, and the safety and the reliability of the unmanned aerial vehicle during flying are improved; when not using, insert first locating through-hole with first round pin post from the other end of first locating through-hole, make the expansion end of first extensible member withdraw from first locating through-hole, can untie the locking of horn to rotate the horn and fold to the fuselage, can rotate the undercarriage folding with the same reason, folding easy operation is simple, after folding moreover, can reduce unmanned aerial vehicle's occupation space, portable and transportation.
And the undercarriage is arranged on the joint part of the horn, and can be tightly attached to the horn and be in the same horizontal plane with the horn after being folded, so that the undercarriage does not occupy extra space after being folded, the size is smaller and more ingenious, and the space utilization rate is high. Because the undercarriage is installed on the horn, when using, the undercarriage does not occupy the space of fuselage below for there are more space carry below the fuselage, and is higher to load adaptability, and the antenna integration is in the undercarriage moreover, saves the antenna and occupies extra space, has improved unmanned aerial vehicle's space utilization greatly. The undercarriage is arranged on the horn, so that the span between adjacent undercarriages is larger, the unmanned aerial vehicle is more stable in taking off and landing and is not easy to turn over; for the unmanned aerial vehicle of dismouting undercarriage, it is more convenient during the use.
Drawings
The invention is further described with reference to the following detailed description of embodiments and drawings, in which:
FIG. 1 is a schematic perspective view of one embodiment of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
FIG. 3 is an enlarged view of a portion of FIG. 1 at B;
FIG. 4 is a schematic perspective view of a portion of a landing gear and a second unlocking snap connection in one embodiment of the invention;
FIG. 5 is a schematic diagram of a portion of a support arm according to one embodiment of the present invention;
FIG. 6 is a perspective view of a joint component in one embodiment of the present invention;
figure 7 is a perspective view of a second unlocking snap fastener in one of the embodiments of the invention.
Detailed Description
Referring to fig. 1 to 5, the invention discloses a foldable unmanned aerial vehicle, which includes a body 1, four booms 2 and four undercarriages 3, wherein the booms 2 are provided with joint components 4, the body 1 and the undercarriages 3 are both hinged to the joint components 4, the booms 2 can horizontally rotate relative to the body 1, the joint components 4 are provided with first telescopic parts 5, the telescopic direction of the first telescopic parts 5 is vertical, the body 1 is provided with first positioning through holes 11, when the booms 2 are opened at a first predetermined angle relative to the body 1, the movable ends of the first telescopic parts 5 can be inserted into the first positioning through holes 11 from one ends of the first positioning through holes 11, the body 1 is movably provided with first pins 6, the first pins 6 can be inserted into or withdrawn from the first positioning through holes 11 from the other ends of the first positioning through holes 11, the undercarriages 3 can vertically rotate relative to the undercarriages 3, the joint components 4 are further provided with second telescopic parts 7, the undercarriage 3 is provided with second positioning through holes 31, when the undercarriage 3 is opened at a second predetermined angle relative to the second positioning through holes 31, the undercarriage 3 is provided with a second telescopic through holes 31 or a second positioning through hole 31, and a second antenna insert into or withdraw from the second positioning through hole 8. For convenience of description, the orientation herein is based on the state of the present drone when placed on the ground.
Specifically, when the unmanned aerial vehicle is used, the horn 2 and the undercarriage 3 are directly opened, the first extensible member 5 and the second extensible member 7 are respectively inserted into the first positioning through hole 11 and the second positioning through hole 31, the horn 2 and the undercarriage 3 are positioned, an extra locking step is not needed, the operation is simple, the time is saved, the locking is reliable, and the safety and the reliability of the unmanned aerial vehicle during flying are improved; when not using, insert first locating through-hole 11 with first round pin post 6 from the other end of first locating through-hole 11, make the expansion end of first extensible member 5 withdraw from first locating through-hole 11, can untie the locking of horn 2 to rotate the horn 2 folding to fuselage 1, the same principle can rotate undercarriage 3 folding, folding easy operation is simple, after folding moreover, can reduce unmanned aerial vehicle's occupation space, portable and transportation.
Moreover, the undercarriage 3 is arranged on the joint part 4 of the horn 2, and the horn 2 can be tightly attached to the horn 2 and the horn 2 in a horizontal plane after being folded, so that the undercarriage 3 does not occupy extra space after being folded, the size is smaller and the space utilization rate is high. Because undercarriage 3 installs on horn 2, when using, undercarriage 3 does not occupy the space of fuselage 1 below for there are more space carry below fuselage 1, and is higher to load adaptability, and the antenna integration is in undercarriage 3 in addition, saves the antenna and occupies extra space, has improved unmanned aerial vehicle's space utilization greatly. The undercarriage 3 is arranged on the horn 2, and the span between the adjacent undercarriage 3 is larger, so that the unmanned aerial vehicle is more stable in taking off and landing and is not easy to turn over; for the unmanned aerial vehicle of dismouting undercarriage 3, it is more convenient during the use. Moreover, two locking mechanisms of the undercarriage 3 and the horn 2 are integrated on one joint component 4, so that the structure is compact and the occupied space is small.
In this embodiment, fuselage 1 includes the main fuselage and locates the support arm 15 of main fuselage circumference, and power 16 is installed to the main fuselage, and joint part 4 articulates on support arm 15, and unmanned aerial vehicle's complete horn is constituteed jointly to support arm 15 and horn 2, and the pin joint of support arm 15 and horn 2 is in the intermediate position department of complete horn, and after horn 2 was folded like this, unmanned aerial vehicle's occupation space can be reduced as far as possible.
With further reference to fig. 4, in order to position the landing gear 3 after being folded, the landing gear 3 is provided with a second positioning blind hole 32, the second positioning blind hole 32 is located on the side of the landing gear 3 close to the horn 2, the second positioning through hole 31 and the second positioning blind hole 32 are distributed on a circumference with the hinge center of the landing gear 3 and the joint component 4 as the center of circle, the head of the movable end of the second telescopic element 7 is hemispherical, and when the landing gear 3 is folded by a fourth predetermined angle relative to the horn 2, the head of the movable end of the second telescopic element 7 can be inserted into the second positioning blind hole 32. In this embodiment, there are two second positioning blind holes 32, and the two second positioning blind holes 32 are respectively located at two sides of the second positioning through hole 31, and are suitable for folding the landing gear 3 under different conditions.
Like this, when undercarriage 3 need draw in, with horn 2 and undercarriage 3 relative rotation folding to fourth predetermined angle, the head of second extensible member 7 expansion end inserts second location blind hole 32, the relative rotation of restriction horn 2 and undercarriage 3, and because the degree of depth of second location blind hole 32 is limited, and the head of second extensible member 7 expansion end is the hemisphere, when certain exogenic action is on horn 2 and undercarriage 3, the head of second extensible member 7 expansion end can follow and slide out in the second location blind hole 32, horn 2 and undercarriage 3 can continue to expand. Namely, the landing gear 3 has a certain locking function when being folded, has a positioning function when no external force exists, does not influence the unfolding use of the landing gear, and is reliable and convenient.
Similarly, see fig. 5, for horn 2 can fix a position after folding, fuselage 1 is equipped with first location blind hole 12, first location blind hole 12 and first location through-hole 11 are connected through circular arc blind groove 13, the centre of a circle of circular arc blind groove 13 is fuselage 1 and joint part 4's articulated center, the head of 5 expansion ends of first extensible member is the hemisphere, works as the relative fuselage 1 of horn 2 folds the third predetermined angle, the head of 5 expansion ends of first extensible member can insert first location blind hole 12.
Referring to fig. 6 specifically, a blind groove 41 is formed in a first side of the joint component 4, the depth direction of the blind groove 41 is the horizontal direction, the landing gear 3 is hinged to a second side of the joint component 4 through a second connecting shaft 43 which horizontally penetrates through the bottom surface of the blind groove 41, the second side of the joint component 4 is opposite to the first side, the second extensible member 7 is a spring plunger, and the second extensible member 7 is installed on the second side of the joint component 4.
Referring to fig. 2 again, the supporting arm 15 is provided with a clamping groove 14, the joint component 4 is clamped in the clamping groove 14, the supporting arm 15 is provided with a mounting hole 18, the joint component 4 is hinged to the supporting arm 15 through a first connecting shaft 42 which vertically penetrates through the side wall of the blind groove 41 and the mounting hole 18, the upper end and the lower end of the joint component 4 are both provided with the first telescopic part 5, in this embodiment, the first connecting shaft 42 is a first screw, the first telescopic part 5 is a spring plunger, and the upper wall and the lower wall of the clamping groove 14 are both provided with the first positioning through hole 11. The spring plunger is used, so that the structure is simple, the weight is light, and the reliability is high.
Referring to fig. 6, a pipe joint 44 is disposed on a third side of the joint component 4, a wire passing hole 45 is disposed inside the pipe joint 44, the wire passing hole 45 is communicated with the blind groove 41, a wire accommodating groove 46 is disposed on a fourth side of the joint component 4, the wire accommodating groove 46 is located on a side wall of the blind groove 41, and the wire accommodating groove 46 is communicated with the blind groove 41. The joint member 4 is lightweight and easily attached to the body 1 and the arm 2.
Referring to fig. 1, the horn 2 includes a pipe arm 21 sleeved outside a pipe joint 44 and a propeller assembly 22 mounted on the pipe arm 21, the pipe joint 44 and the pipe arm 21 are fixed by a set screw 23, and a lead wire connected with the propeller assembly 22 is arranged inside the pipe arm 21 and is placed in a wire passing hole 45, a blind groove 41 and a wire accommodating groove 46, so as to protect the lead wire.
Referring to fig. 3 and 7 in particular, the landing gear 3 is provided with a second unlocking snap fastener 10, the second unlocking snap fastener 10 includes a second pressing piece 101, a second connecting portion 103 fixedly disposed on the landing gear 3, and a second inclined return spring 102 connecting the second pressing piece 101 and the second connecting portion 103, the second pressing piece 101 is movable, a gap is formed between the second pressing piece 101 and the landing gear 3, the second pin 8 is disposed on the second pressing piece 101, and the second pin 8 is located between the second pressing piece 101 and the landing gear 3. The diameter of the second pin 8 is smaller than the diameter of the second positioning through hole 31. After the second pin 8 is inserted into the second positioning through hole 31 by the second pressing piece 101, the second pin 8 can exit from the second positioning through hole 31 under the resetting action of the second inclined resetting elastic piece 102. In order that the second pressing piece 101 does not move freely, the second connecting portion 103 is connected to the landing gear 3 by two fourth screws 33.
Moreover, a second groove 105 is formed in one side, close to the undercarriage 3, of the second inclined resetting elastic sheet 102, the second groove 105 is formed in the middle of the second inclined resetting elastic sheet 102, the second pressing sheet 101 can move to be close to the undercarriage 3 under the pressing of an external force, after the external force is removed, the second pressing sheet 101 can move to be away from the undercarriage 3 to restore the original position under the elastic force of the second inclined resetting elastic sheet 102, and the length direction of the second groove 105 is perpendicular to the moving direction of the second pressing sheet 101. The second groove 105 is used for reducing the strength of the second inclined reset elastic sheet 102 at the second groove 105, increasing the toughness of the second inclined reset elastic sheet, enabling the second pressing sheet 101 to be pressed down more easily, facilitating use and avoiding the second inclined reset elastic sheet 102 from being fractured due to too strong strength.
Similarly, referring to fig. 2, the body 1 is provided with a first unlocking snap 9, the first unlocking snap 9 includes a first pressing piece 91, a first connecting portion 93 fixedly disposed on the body 1, and a first inclined return elastic sheet 92 connecting the first pressing piece 91 and the first connecting portion 93, a distance is formed between the first pressing piece 91 and the body 1, the first pin 6 is disposed on the first pressing piece 91, and the first pin 6 is located between the first pressing piece 91 and the body 1. The diameter of the first pin 6 is smaller than the diameter of the first positioning through hole 11. The first connecting portion 93 is connected to the body 1 by two third screws 17 so that the first pressing piece 91 does not move freely.
Further, a first groove 94 is formed in one side of the first inclined resetting elastic sheet 92 close to the body 1, the first groove 94 is formed in the middle of the first inclined resetting elastic sheet 92, the first pressing sheet 91 can move to be close to or far away from the body 1, and the length direction of the first groove 94 is perpendicular to the moving direction of the first pressing sheet 91.
In addition, the horn 2 and the undercarriage 3 are hinged through a second connecting shaft 43, the second connecting shaft 43 is a second screw, the second screw is locked through a locknut, the locknut is located in the blind groove 41, the second pressing sheet 101 is opposite to the second screw, and a screw avoiding hole 104 is formed in the position, corresponding to the second screw, of the second pressing sheet 101. Be equipped with gasket 47 between the screwhead of second screw and the undercarriage 3, the diameter of gasket 47 is greater than the diameter that the screw dodged hole 104, and the back is pressed completely to second pressing piece 101, and second pressing piece 101 can be blocked by gasket 47, works as second round pin post 8 inserts second positioning hole 31 completely, predetermined interval has between second round pin post 8 and the horn 2, and the head of second round pin post 8 can not contradict horn 2 like this, avoids when the unblock, and second round pin post 8 head can withstand horn 2 and lead to the unblock unsmooth.
Specifically, second extensible member 7 is spring plunger, spring plunger is including installing the shell in horn 2, locating the inside spring of shell and inserting the plunger of locating the shell open end, the one end butt plunger of spring, other end butt shell inner wall, the plunger is the expansion end of second extensible member 7, the head of plunger is the hemisphere. Thus, even if the plunger is not completely ejected out of the second positioning through hole 31 by the second pin 8 after the second pressing piece 101 is pressed down, the plunger can easily come out of the second positioning through hole 31 due to the hemispherical head, and smooth rotation between the horn 2 and the landing gear 3 can be ensured.
In this embodiment, a second hemispherical recess 81 is formed at an end of the second pin 8 close to the second telescopic element 7. Thus, when the second pin 8 abuts against the head of the plunger, the plunger is not easy to disengage, and the plunger can be conveniently pushed out of the second positioning through hole 31 by using the second pin 8. In a similar way, a first hemispherical groove is formed in one end, close to the first telescopic piece 5, of the first pin 6, so that the movable end of the first telescopic piece 5 is not easy to disengage from the first pin 6, and the first pin 6 is convenient to use to push out the movable end of the first telescopic piece 5 through the first positioning through hole 11.
It is noted that the terms first, second, third, etc. are used herein to describe various elements or components, but these elements or components are not limited by these terms. These terms are only used to distinguish one element or part from another element or part. Terms such as "first," "second," and other numerical terms when used herein do not imply a sequence or order unless clearly indicated by the context. For convenience of description, spatially relative terms such as "inner", "outer", "upper", "lower", "left", "right", "upper", "left", "right", and the like are used herein to describe the orientation relation of the components or parts in the present embodiment, but these spatially relative terms do not limit the orientation of the technical features in practical use.
The above description is only a preferred embodiment of the present invention, but the present invention is not limited to the above embodiments, and the present invention shall fall within the protection scope of the present invention as long as the technical effects of the present invention are achieved by any similar or identical means.
Claims (9)
1. A collapsible unmanned aerial vehicle, its characterized in that: including fuselage (1), a plurality of horn (2) and a plurality of undercarriage (3), horn (2) are equipped with joint part (4), fuselage (1) and undercarriage (3) all articulate with joint part (4), horn (2) can be relative fuselage (1) level rotation, joint part (4) are equipped with first extensible member (5), first location through-hole (11) have been seted up in fuselage (1), work as first predetermined angle is opened to horn (2) relative fuselage (1), the one end that first extensible member (5) can be followed first location through-hole (11) inserts first location through-hole (11), fuselage (1) is movably equipped with first round pin post (6), first round pin post (6) can be followed the other end of first location through-hole (11) and inserted or withdraw from first location through-hole (11), undercarriage (3) can be relative fuselage (1) vertical rotation, joint part (4) still is equipped with second extensible member (7), undercarriage (3) have been seted up second location through-hole (31) and second location through-hole (31) is followed second location through-hole (31) and insert second extensible member (31), the undercarriage (3) is movably provided with a second pin column (8), the second pin column (8) can be inserted into or withdrawn from the second positioning through hole (31) from the other end of the second positioning through hole (31), and an antenna is embedded in the undercarriage (3); blind groove (41) have been seted up to the first side of joint part (4), the direction of depth of blind groove (41) is the horizontal direction, undercarriage (3) run through second connecting axle (43) of blind groove (41) bottom surface through the level and articulate the second side in joint part (4), the second side and the first side of joint part (4) are relative, second extensible member (7) are spring plunger, second extensible member (7) are installed in the second side of joint part (4).
2. The foldable drone of claim 1, characterized in that: fuselage (1) is equipped with first location blind hole (12), first location blind hole (12) and first location through-hole (11) are connected through circular arc blind groove (13), the centre of a circle of circular arc blind groove (13) is the articulated center of fuselage (1) and joint part (4), the head of first extensible member (5) expansion end is the hemisphere, works as fuselage (2) is folding third predetermined angle relatively fuselage (1), the head of first extensible member (5) expansion end can insert first location blind hole (12).
3. A foldable drone according to claim 1 or 2, characterised in that: fuselage (1) is equipped with first unblock snap-fastener (9), first unblock snap-fastener (9) reset shell fragment (92) including first pressure piece (91), fixed first connecting portion (93) of locating fuselage (1) and the first slope of connecting first pressure piece (91) and first connecting portion (93), there is the interval between first pressure piece (91) and fuselage (1), first pressure piece (91) is located in first round pin post (6), first round pin post (6) are located between first pressure piece (91) and fuselage (1).
4. The foldable drone of claim 1, characterized in that: undercarriage (3) are equipped with second location blind hole (32), second location through hole (31) and second location blind hole (32) distribute on the circumference that uses the articulated center of undercarriage (3) and joint part (4) as the centre of a circle, the head of second extensible member (7) expansion end is the hemisphere, works as undercarriage (3) fourth predetermined angle of folding relatively horn (2), the head of second extensible member (7) expansion end can insert second location blind hole (32).
5. A foldable drone according to claim 1 or 2 or 4, characterized in that: a first hemispherical groove is formed in one end, close to the first telescopic piece (5), of the first pin column (6), and a second hemispherical groove (81) is formed in one end, close to the second telescopic piece (7), of the second pin column (8).
6. A foldable drone according to claim 1 or 4, characterised in that: undercarriage (3) are equipped with second unblock snap fastener (10), second unblock snap fastener (10) include second press piece (101), fixed second connecting portion (103) of locating undercarriage (3) and second slope of connecting second press piece (101) and second connecting portion (103) shell fragment (102) that resets, there is the interval between second press piece (101) and undercarriage (3), second press piece (101) is located in second round pin post (8), second round pin post (8) are located between second press piece (101) and undercarriage (3).
7. The foldable drone of claim 1, characterized in that: fuselage (1) is equipped with presss from both sides groove (14), joint part (4) card is located and is pressed from both sides groove (14), joint part (4) articulate fuselage (1) through first connecting axle (42) that run through blind groove (41) lateral wall from top to bottom, the upper end and the lower extreme of joint part (4) all are equipped with first extensible member (5), first extensible member (5) are spring plunger, the upper wall and the lower wall that press from both sides groove (14) all are equipped with first location through-hole (11).
8. The foldable drone of claim 1, characterized in that: the joint component is characterized in that a pipe joint (44) is arranged on the third side of the joint component (4), a wire passing hole (45) is formed in the pipe joint (44), the wire passing hole (45) is communicated with the blind groove (41), a wire receiving groove (46) is formed in the fourth side of the joint component (4), the wire receiving groove (46) is located on the side wall of the blind groove (41), and the wire receiving groove (46) is communicated with the blind groove (41).
9. The foldable drone of claim 8, wherein: the mechanical arm (2) comprises a pipe arm (21) sleeved outside a pipe joint (44) and a propeller assembly (22) installed on the pipe arm (21), the pipe joint (44) and the pipe arm (21) are fixed through a positioning screw (23), a lead wire connected with the propeller assembly (22) is arranged inside the pipe arm (21), and the lead wire is arranged in a wire passing hole (45), a blind groove (41) and a wire accommodating groove (46).
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| CN202011466853.6A CN112455645B (en) | 2020-12-14 | 2020-12-14 | Collapsible unmanned aerial vehicle |
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| CN202011466853.6A CN112455645B (en) | 2020-12-14 | 2020-12-14 | Collapsible unmanned aerial vehicle |
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| CN112455645A CN112455645A (en) | 2021-03-09 |
| CN112455645B true CN112455645B (en) | 2022-11-29 |
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| CN113428344A (en) * | 2021-08-13 | 2021-09-24 | 复旦大学 | Rotor unmanned aerial vehicle with telescopic and foldable arm |
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