CN210000572U - unmanned aerial vehicle - Google Patents
unmanned aerial vehicle Download PDFInfo
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- CN210000572U CN210000572U CN201822183099.XU CN201822183099U CN210000572U CN 210000572 U CN210000572 U CN 210000572U CN 201822183099 U CN201822183099 U CN 201822183099U CN 210000572 U CN210000572 U CN 210000572U
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- landing gear
- fuselage
- contact surface
- mounting plate
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Abstract
The utility model relates to an aircraft field discloses unmanned vehicles, include the fuselage and install in the undercarriage subassembly of fuselage, the undercarriage subassembly includes the mounting panel, undercarriage and compact structure the mounting panel links to each other with the fuselage, and the undercarriage is installed in the mounting panel, and the undercarriage can rotate around the central line for the mounting panel, and in mounting panel and the undercarriage are provided with two at least lockholes, in addition are provided with the lockpin, two at least lockholes are the circumference around the central line and distribute, compact structure connects mounting panel and undercarriage for provide the packing force that makes mounting panel and undercarriage be close to each other along the central line, unmanned vehicles disposes the undercarriage subassembly, and undercarriage among the undercarriage subassembly can for the fuselage expandes or is folding, can realize unmanned vehicles portable.
Description
[ technical field ] A method for producing a semiconductor device
The utility model relates to an aircraft field especially relates to kinds of unmanned vehicles.
[ background of the invention ]
The landing gear is an attachment device with force bearing and maneuverability as an unmanned aerial vehicle, plays an extremely important role in the safe taking-off and landing process of the unmanned aerial vehicle, and is which is an important part of the unmanned aerial vehicle.
Currently, landing gear is generally stationary.
However, the inventors discovered that, in the course of implementing the present invention; the fixed landing gear is inconvenient to carry. Accordingly, there is a need in the art for improvements.
[ summary of the invention ]
In order to solve the technical problem, the embodiment of the utility model provides an kinds of unmanned vehicles who dispose the undercarriage, this unmanned vehicles portable.
In order to solve the technical problem, an embodiment of the utility model provides a following technical scheme:
unmanned aerial vehicle is provided, which is characterized by comprising a fuselage and a landing gear assembly mounted on the fuselage, wherein the landing gear assembly comprises a landing gear capable of rotating around a central line relative to the fuselage, a hold-down structure, wherein end of the hold-down structure is connected with the landing gear, another end of the hold-down structure is connected with the fuselage, the hold-down structure is used for providing hold-down force for enabling the landing gear to approach the fuselage along the central line, of the fuselage and the landing gear are provided with lock holes, another of the fuselage and the landing gear are provided with lock pins, the lock pins are matched with the lock holes to enable the position of the landing gear relative to the fuselage to be locked, and the lock pins can be separated from the lock holes to enable the landing gear to rotate around the central line relative to the fuselage.
In embodiments, the fuselage is further provided with a mounting plate, of the mounting plate and the landing gear are provided with the locking holes, and the other of the mounting plate and the landing gear are provided with the locking pins.
In , the lock pin is disposed on the landing gear and the lock hole is disposed on the mounting plate.
In , the mounting plate has a th contact surface, the landing gear has a second contact surface facing the th contact surface and contacting the th contact surface, the locking pin is arranged on the th contact surface and extends along the centerline toward the second contact surface, and the locking hole is correspondingly formed on the second contact surface.
In , the lock hole is provided on the landing gear and the lock pin is provided on the mounting plate.
In , the mounting plate has a th contact surface, the landing gear has a second contact surface facing the th contact surface and contacting the th contact surface, the lock pin is arranged on the second contact surface and extends along the centerline to the th contact surface, and the lock hole is correspondingly formed on the th contact surface.
In , the mounting plate is provided with a mounting groove, the second contact surface is the bottom of the mounting groove, and the end of the landing gear provided with the th contact surface is accommodated in the mounting groove.
In embodiments, of the landing gear and the fuselage are provided with a shaft disposed along the centerline, and another are provided with shaft holes into which the shaft is inserted.
In , the hinge is disposed on the landing gear, the shaft hole is disposed on the mounting plate, and the shaft hole extends through the mounting plate and communicates with the interior of the fuselage.
In , the pressing structure comprises a pressing plate and an elastic element, wherein the pressing plate is arranged at the end of the rotating shaft penetrating through the shaft hole, the elastic element is sleeved on the rotating shaft, and the elastic element abuts between the pressing plate and the mounting plate.
In , the elastic member is a compression spring.
In , the pressure plate is screwed with the rotating shaft.
Compared with the prior art, in the kinds of unmanned vehicles of the embodiment of the utility model, unmanned vehicles disposes the landing gear subassembly, and landing gear in the landing gear subassembly can for the fuselage expandes or folds, can realize unmanned vehicles portable.
[ description of the drawings ]
the various embodiments are illustrated by way of example in the accompanying drawings and not by way of limitation, in which elements having the same reference number designation may be represented by like elements in the drawings and the drawings are not necessarily to scale unless otherwise indicated.
Fig. 1 is a perspective view of kinds of unmanned aerial vehicles provided by an embodiment of in the invention;
FIG. 2 is a cross-sectional view of a landing gear assembly of the unmanned aerial vehicle shown in FIG. 1, with the landing gear of the landing gear assembly partially omitted;
FIG. 3 is a top view of the UAV of FIG. 1 with some components of the UAV omitted;
FIG. 4 is a front view of the UAV of FIG. 1 with portions of the lengths of both wings omitted;
FIG. 5 is a cross-sectional view of the landing gear assembly shown in FIG. 2 in another embodiments, with the landing gear partially omitted;
FIG. 6 is a cross-sectional schematic view of the landing gear assembly shown in FIG. 2 in a th condition;
FIG. 7 is a cross-sectional schematic view of the landing gear assembly shown in FIG. 2 in a second condition;
FIG. 8 is a cross-sectional schematic view of the landing gear assembly shown in FIG. 2 in a third condition;
FIG. 9 is a cross-sectional schematic view of the landing gear assembly shown in FIG. 2 in a fourth condition.
[ detailed description ] embodiments
For purposes of explanation, the terms "vertical," "horizontal," "left," "right," "inner," "outer," and the like are used in this specification only for purposes of illustration, and are used in a generic sense only to describe the invention as it relates to the accompanying drawings and the detailed description, wherein, when an element is referred to as being "secured to" another element, it may be directly secured to the other element or there may be or more intervening elements present therebetween, when elements are referred to as being "connected" to the other element, it may be directly connected to the other element or there may be or more intervening elements present therebetween.
The terminology used in the description of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention, the terminology used in the description of the invention "and/or" includes any and all combinations of or more of the associated listed items.
Referring to fig. 1, the present invention provides kinds of unmanned aerial vehicles 100 in an embodiment of , which can be multi-rotor unmanned aerial vehicles, fixed-wing unmanned aerial vehicles, or tilt-rotor unmanned aerial vehicles, and in this embodiment, the unmanned aerial vehicle 100 is described in detail as an example of a tilt-rotor unmanned aerial vehicle.
The unmanned aerial vehicle 100 is a symmetrical structure with a symmetry plane M, and the unmanned aerial vehicle 100 includes a fuselage 10, two wings 20, two sets of propeller assemblies 30, and a landing gear assembly 40. The two wings 20 are disposed on opposite sides of the fuselage 10, the two groups of propeller assemblies 30 are disposed on the two wings 20, respectively, and the landing gear assembly 40 is disposed on the fuselage 10.
The body 10 is substantially in the form of a long shuttle, symmetrical with respect to the plane of symmetry M, the body 10 being provided with a mounting plate 11, the mounting plate 11 being detachably connectable to the body 10, for example by means of a threaded connection, the mounting plate 11 also being integrally formed with the body 10 .
The mounting plate 11 is generally flat and has a mounting surface 110, and the mounting surface 110 is an surface of the mounting plate 11 facing away from the body 10.
The two wings 20 are symmetrically distributed with respect to the plane of symmetry M.
The two sets of propeller assemblies 30 are symmetrically distributed with respect to the plane of symmetry M, and the two sets of propeller assemblies 30 are rotatable with respect to the two wings 20, for example, the two sets of propeller assemblies 30 are rotated by 90 degrees to provide lift in a vertical upward direction, so that the unmanned aerial vehicle 100 can be vertically lifted.
The number of landing gear assemblies 40 is two, and the two landing gear assemblies 40 are symmetrically distributed relative to the symmetry plane M.
and referring to FIG. 2, the landing gear assembly 40 includes a landing gear 42 and a hold-down structure 43, the landing gear 42 being mounted to the mounting plate 11, the hold-down structure 43 connecting the mounting plate 11 and the landing gear 42.
It is understood that the mounting plate 11 may be omitted, i.e., the mounting surface 110 is directly disposed on the body 10, depending on the actual situation.
The mounting surface 110 is provided with a mounting groove 111, the mounting groove 111 is a circular groove, the end of the landing gear 42 is received in the mounting groove 111, the bottom of the mounting groove 111 is provided with a contact surface 112, the shaft hole 113 and the at least two locking holes 114 are all arranged in the landing gear 42, the shaft hole 113 has a center line S, the shaft hole communicates with the inside of the fuselage 10, the shaft hole 113 and the at least two locking holes 114 are correspondingly formed and are in contact with the contact surface 112, that is, the shaft hole 113 and the at least two locking holes 114 are all along the direction of the center line S from the contact surface 112 is formed in a recessed manner, and the opening of the shaft hole 113 and the openings of the at least two locking holes 114 are all arranged on the contact surface.
Referring to and also to fig. 3 and 4, the centerline S is disposed at an angle a from the plane of symmetry M, and the angle a is acute, so that when the landing gear 42 rotates about the centerline S relative to the mounting plate 11, the opening and closing angle c of the landing gear 42 from the plane of symmetry changes, so that the landing gear 42 can be deployed or folded relative to the fuselage 10. when the landing gear 42 is deployed relative to the fuselage 10, the opening and closing angle c is at a maximum, and when the landing gear 42 is folded relative to the fuselage 10, the opening and closing angle c is at a minimum.
Specifically, the opening of the th included angle between the center line S and the symmetry plane M faces the tail of the fuselage 10, and when the unmanned aerial vehicle 100 flies horizontally, the center line S is horizontally arranged, so that the landing gear suffers little air resistance during the flight of the unmanned aerial vehicle.
The at least two locking holes 114 are circumferentially distributed around the center line S, preferably, the at least two locking holes 114 are equidistantly distributed, and any of the at least two locking holes 114 may be through holes or blind holes, which is not limited in this embodiment.
In the present embodiment, any of the at least two locking holes 114 are cylindrical.
referring to FIG. 5, in some other embodiments, any of the at least two locking holes 114 are hemispherical.
The at least two locking holes 114 include an th locking hole and a second locking hole, and the th locking hole and the second locking hole are symmetrically arranged with respect to the center line S.
Referring back to fig. 2, the landing gear 42 includes a supporting portion 420 and a connecting portion 421 extending from an end of the supporting portion 420 .
The support portion 420 has a long cylindrical shape, and the support portion 420 is used to support the fuselage 10 when the landing gear 42 is deployed with respect to the fuselage 10.
Connecting portion 421 is longer column, the axis of connecting portion 421 with central line S coincides mutually, connecting portion 421 with supporting part 420 is second angle b, second angle b is the obtuse angle, makes undercarriage 42 for when fuselage 10 expandes, supporting part 420 is close to the end of connecting portion 421 is far away from end of connecting portion 421 is closer to plane of symmetry M, two promptly supporting part 420 of support frame 42 is the splayed, makes undercarriage 42 supports the stability of fuselage 10 is promoted.
, the second angle b is greater than or equal to the complement of the angle a, i.e., the second angle b is greater than or equal to the difference between 180 degrees and the angle a, so that when the landing gear 42 is folded relative to the fuselage 10, the end of the support portion 420 closer to the connecting portion 421 is closer to the tail of the fuselage 10 than the end of the connecting portion 421, so that the support portion 420 is parallel or nearly parallel relative to the plane of symmetry M.
The end of the connection portion 421 facing away from the support portion 420 is provided with a second contact surface 423.
The second contact surface 423 faces the -th contact surface 112, and a rotation shaft 424 and a lock pin 425 are provided on the second contact surface 423, and the rotation shaft 424 and the lock pin 425 both extend toward the second contact surface 423 along the center line S.
The rotating shaft 424 is matched with the shaft hole 113, and the rotating shaft 424 is used for being inserted into the shaft hole 113.
It is understood that, according to practical situations, the positions of the rotating shaft 424 and the shaft hole 113 can be interchanged, that is, the rotating shaft 424 is disposed on the th contact surface 112, the shaft hole 113 is disposed on the second contact surface 423, as long as of the th contact surface 112 and the second contact surface 423 are provided with the shaft hole 113, and the other is provided with the rotating shaft 424.
The lock pin 425 is matched with any of the at least two lock holes 114, and the lock pin 425 is used for being inserted into any of the at least two lock holes 113.
It is understood that, according to practical situations, the positions of the lock pin 425 and the at least two lock holes 114 may be interchanged, that is, the lock pin 425 is disposed on the -th contact surface 112, and the at least two lock holes 114 are disposed on the second contact surface 423, as long as of the -th contact surface 112 and the second contact surface 123 are provided with the lock pin 425, and the other is provided with the at least two lock holes 114.
The locking pins 425 include th locking pin and a second locking pin, the th locking pin is inserted into of the th locking hole and the second locking hole, the second locking pin is inserted into the th locking hole and the of the second locking hole, the second locking pin is inserted into the second locking hole when the th locking pin is inserted into the th locking hole, and the second locking pin is inserted into the th locking hole when the second locking pin is inserted into the second locking hole.
and referring to FIGS. 6-9, the shaft 424 is inserted into the shaft hole 113, as shown in FIGS. 6 and 7, allows the shaft 424 to move along the centerline S relative to the shaft hole 113, i.e., the landing gear 42 to move along the centerline S relative to the mounting plate 11, and as shown in FIGS. 8 and 9, allows the shaft 424 to rotate about the centerline S relative to the shaft hole 113, i.e., the landing gear 42 to rotate about the centerline S relative to the mounting plate 11, when the locking pin 425 is not inserted into the locking hole 114.
When the landing gear 42 is rotated relative to the mounting plate 11, the lock pin 425 may be aligned with any of the at least two lock holes 114 such that the lock pin 425 may be inserted into of the lock holes 114 aligned therewith.
When the lock pin 425 is inserted into any of the at least two lock holes 114, the landing gear 42 cannot rotate relative to the mounting plate 11 about the center line S, i.e., the landing gear 42 is fixed relative to the mounting plate 11 in a direction about the center line S, by disposing the lock pin 425 and the lock holes 114 between the landing gear 42 and the mounting plate 11, the landing gear 42 cannot rotate when the landing gear 42 is unfolded or folded relative to the fuselage 10, and the stability of the landing gear 42 supporting the fuselage 10 is improved.
The lock pins 425 are inserted into of the two lock holes 114 when the landing gear 42 is folded relative to the fuselage 10 so that the landing gear 42 cannot rotate relative to the mounting plate 11 about the centerline S, i.e., the landing gear 42 is fixed relative to the mounting plate 11 in a direction about the centerline S, and the lock pins 425 are inserted into the other of the two lock holes 114 when the landing gear 42 is unfolded relative to the fuselage 10 so that the landing gear 42 cannot rotate relative to the mounting plate 11 about the centerline S, i.e., the landing gear 42 is fixed relative to the mounting plate 11 in a direction about the centerline S.
When the landing gear 42 is deployed or folded with respect to the fuselage 10, the landing gear 42 may move along the centerline S with respect to the mounting plate 11 such that the locking pin 425 is disengaged from the locking hole 114.
The hold-down structure 43 is configured to provide a hold-down force that urges the mounting plate 11 and the landing gear 42 toward each other along the centerline S such that the -th contact surface 112 and the second contact surface 423 abut.
The hold-down structure 43 includes a hold-down 430 and a resilient member 431, wherein the hold-down 430 is attached to the end of the shaft 424 that extends through the shaft hole 113, preferably, the hold-down 430 and the shaft 424 are threadably attached, and the resilient member 431 is attached between the hold-down 430 and the mounting plate 11. when the landing gear 42 is moved along the centerline S relative to the mounting plate 11 such that the locking pin 425 is disengaged from the pin hole 114, the resilient member 431 compresses to provide a hold-down force that urges the contact surface 112 and the second contact surface 423 against one another.
The elastic member 431 is a compression spring, which is sleeved on the end of the rotating shaft 424 penetrating through the shaft hole 113, and the compression spring abuts between the mounting plate 11 and the pressing plate 430.
It should be noted that, according to practical situations, the elastic member 431 may be replaced by two magnetic members, for example, a magnetic member that is magnetically attracted is embedded on each of the two opposite surfaces of the mounting plate 11 and the pressing plate 430, a pressing force that abuts the -th contact surface 112 and the second contact surface 423 may be provided, and the pressing force may be gradually increased during the process that the landing gear 42 is moved along the center line S relative to the mounting plate 11 so that the locking pin 425 is gradually separated from the locking hole 114.
When the unmanned aerial vehicle 100 is in use, the landing gear 42 is unfolded or folded relative to the fuselage 10, and when the landing gear 42 needs to be switched, for example, the landing gear 42 is switched from the unfolded state to the folded state, the switching can be performed by the following steps:
first, the landing gear 42 is moved relative to the mounting plate 11 along the center line S, so that the -th contact surface 112 and the second contact surface 423 are separated from each other, and the lock pin 425 is separated from the lock hole 114;
the landing gear 42 may then be rotated relative to the mounting plate 11 about the centerline S after the locking pin 424 is disengaged from the locking holes 114 to align the locking pin 425 with a corresponding of the at least two locking holes 114.
Finally, after the lock pin 425 is aligned with of the at least two lock holes 114, the landing gear 42 is moved relative to the mounting plate 11 along the center line S to bring the th contact surface 112 into contact with the second contact surface 423, and the lock pin 425 is inserted into the lock hole 114 aligned therewith, i.e., the landing gear 42 is completely switched from the folded state to the unfolded state.
Compared with the prior art, the embodiment of the present invention provides an unmanned aerial vehicle 100, in which unmanned aerial vehicle 100 is configured with landing gear assembly 40, and landing gear 42 in landing gear assembly 40 can be unfolded or folded relative to fuselage 10, which can be realized for convenient carrying.
In addition, the landing gear assembly 40 is a non-powered landing gear assembly, the landing gear 42 can be manually driven by a user to fold or unfold relative to the fuselage 10, and the unmanned aerial vehicle 100 provided with the landing gear assembly 40 can consume less power, and the unmanned aerial vehicle 100 has lighter weight due to the absence of a motor.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it; within the idea of the invention, also technical features in the above embodiments or in different embodiments can be combined, steps can be implemented in any order, and there are many other variations of the different aspects of the invention as described above, which are not provided in detail for the sake of brevity; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention.
Claims (12)
- An unmanned aerial vehicle (100) of the type, comprising a fuselage (10) and a landing gear assembly (40) mounted to the fuselage (10), the landing gear assembly (40) comprising:a landing gear (42), the landing gear (42) being rotatable relative to the fuselage (10) about a centre line (S);a hold-down structure (43), said hold-down structure (43) connected at one end to said landing gear (42) and at another end connected to said fuselage (10), said hold-down structure (43) for providing hold-down of said landing gear (42) along said centerline (S) toward said fuselage (10);of the fuselage (10) and the landing gear (42) are provided with locking holes (114), and the other of the fuselage (10) and the landing gear (42) are provided with locking pins (425);the locking pin (425) cooperating with the locking hole (114) to lock the position of the landing gear (42) relative to the fuselage (10);the locking pin (425) is separable from the locking hole (114) to enable the landing gear (42) to rotate about the centerline (S) relative to the fuselage (10).
- 2. The UAV (100) of claim 1, wherein the fuselage (10) is further provided with a mounting plate (11), wherein of the mounting plate (11) and the landing gear (42) are provided with the locking holes (114), and wherein the other of the mounting plate (11) and the landing gear (42) are provided with the locking pins (425).
- 3. The UAV (100) of claim 2, wherein the locking pin (425) is disposed on the landing gear (42) and the locking hole (114) is disposed on the mounting plate (11).
- 4. The UAV (100) of claim 3, wherein the mounting plate (11) has an th contact surface (112), the landing gear (42) has a second contact surface (423) facing the th contact surface (112) and in contact with the th contact surface (112);the lock pin (425) is arranged on the th contact surface (112), the lock pin (425) extends to the second contact surface (423) along the center line (S), and the lock hole (114) is correspondingly formed on the second contact surface (423).
- 5. The UAV (100) of claim 2, wherein the lock aperture (114) is disposed on the landing gear (42) and the lock pin (425) is disposed on the mounting plate (11).
- 6. The UAV (100) of claim 5 wherein the mounting plate (11) has an th interface (112), the landing gear (42) has a second interface (423) facing the th interface (112) and in contact with the th interface (112);the lock pin (425) is arranged on the second contact surface (423), the lock pin (425) extends to the -th contact surface (112) along the center line (S), and the lock hole (114) is correspondingly formed on the -th contact surface (112).
- 7. The unmanned aerial vehicle (100) of claim 4 or 6, wherein the mounting plate (11) is provided with a mounting groove (111), the -th contact surface (112) being a groove bottom of the mounting groove (111);the end of the landing gear (42) provided with the th contact surface (112) is received in the mounting groove (111).
- 8. The unmanned aerial vehicle (100) of any of claims 2-6, wherein of both the landing gear (42) and the fuselage (10) are provided with a shaft (424) disposed along the centerline (S), and another are provided with shaft holes (113), the shaft (424) being inserted into the shaft holes (113).
- 9. The UAV (100) of claim 8, wherein the shaft (424) is disposed on the landing gear (42), the shaft hole (113) is disposed on the mounting plate (11), and the shaft hole (113) extends through the mounting plate (11) and communicates with the interior of the fuselage (10).
- 10. The unmanned aerial vehicle of claim 9, wherein the compression structure (43) comprises a pressure plate (430) and a resilient member (431);the pressing plate (430) is arranged at the end of the rotating shaft (424) penetrating through the shaft hole (113), the elastic piece (431) is sleeved on the rotating shaft (424), and the elastic piece (431) abuts between the pressing plate (430) and the mounting plate (11).
- 11. The unmanned aerial vehicle (100) of claim 10, wherein the resilient member (431) is a compression spring.
- 12. The UAV (100) of claim 10, wherein the pressure plate (430) is threadably connected to the shaft (424).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822183099.XU CN210000572U (en) | 2018-12-24 | 2018-12-24 | unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822183099.XU CN210000572U (en) | 2018-12-24 | 2018-12-24 | unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN210000572U true CN210000572U (en) | 2020-01-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201822183099.XU Active CN210000572U (en) | 2018-12-24 | 2018-12-24 | unmanned aerial vehicle |
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| CN (1) | CN210000572U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109552602A (en) * | 2018-12-24 | 2019-04-02 | 深圳市道通智能航空技术有限公司 | A kind of unmanned vehicle |
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2018
- 2018-12-24 CN CN201822183099.XU patent/CN210000572U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109552602A (en) * | 2018-12-24 | 2019-04-02 | 深圳市道通智能航空技术有限公司 | A kind of unmanned vehicle |
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Address after: 518055 Guangdong city of Shenzhen province Nanshan District Xili Street Xueyuan Road No. 1001 Chi Yuen Building 9 layer B1 Patentee after: Shenzhen daotong intelligent Aviation Technology Co.,Ltd. Address before: 518055 Guangdong city of Shenzhen province Nanshan District Xili Street Xueyuan Road No. 1001 Chi Yuen Building 9 layer B1 Patentee before: AUTEL ROBOTICS Co.,Ltd. |