WO2020062757A1 - 无人机及倾转机构 - Google Patents
无人机及倾转机构 Download PDFInfo
- Publication number
- WO2020062757A1 WO2020062757A1 PCT/CN2019/075082 CN2019075082W WO2020062757A1 WO 2020062757 A1 WO2020062757 A1 WO 2020062757A1 CN 2019075082 W CN2019075082 W CN 2019075082W WO 2020062757 A1 WO2020062757 A1 WO 2020062757A1
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- WO
- WIPO (PCT)
- Prior art keywords
- plug
- positioning pin
- positioning
- hole
- tilting mechanism
- Prior art date
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
Definitions
- the utility model relates to the technical field of aviation vehicles, in particular to an unmanned aerial vehicle and a tilting mechanism.
- Tilt rotor UAV is an aircraft with both vertical takeoff and landing and fixed-wing flight modes.
- the tilt device is one of its core components.
- the tilt device is connected to the fuselage to realize this type of UAV. Switch between fixed-wing mode and vertical take-off and landing mode.
- the tilting device of this type of drone is usually connected to the fuselage with screws and other fasteners.
- the fasteners such as screws must be removed first to remove the tilting device from the fuselage.
- the assembly of the tilting device and the fuselage must be achieved by assembling screws and other fasteners, which is inconvenient to operate and has low disassembly and assembly efficiency.
- the embodiments of the present invention provide a drone and a tilting mechanism, the main purpose of which is to make the assembly and disassembly of the tilting device and the fuselage more convenient, so as to improve the disassembly and assembly efficiency.
- the present utility model mainly provides the following technical solutions:
- an embodiment of the present invention provides a drone, including:
- a tilting mechanism comprising a main body and a first insertion portion and a first positioning portion provided on the main body;
- a fuselage the fuselage is provided with a second plug-in portion and a second positioning portion;
- first plug-in part and the second plug-in part are pluggably connected, and the first positioning part and the second positioning part are detachably cooperatively connected to prevent the first plug-in part.
- a relative movement is generated between the connection portion and the second insertion portion.
- the body includes a driver, and the body is further provided with a first electrical plug connector electrically connected to the driver;
- the body is further provided with a second electrical plug connector capable of being electrically connected to an external electrical module, and the second electrical plug connector is pluggably and electrically connected to the first electrical plug connector;
- the plugging direction of the first electrical plug connector and the second electrical plug connector is the same as that of the first plug portion and the second plug portion; the first plug portion When mating with the second plug-in portion, the first electrical plug connector and the second electrical plug connector are mated with each other; the first plug-in portion and the second plug-in portion are mutually During separation, the first electrical plug connector and the second electrical plug connector are separated from each other.
- the first plug-in portion includes a first plug-in post disposed on the body and parallel to a surface of the body;
- the second plug-in portion includes a first plug-in hole provided in the body and extending in a direction parallel to the first plug-in post;
- the first plug-in post is plug-fitted into the first plug-in hole.
- the first plug-in portion further includes a second plug-in post disposed on the body and parallel to the first plug-in post and extending in the same direction as the first plug-in post;
- the second plug-in portion further includes a second plug-in hole provided in the body and extending in a direction parallel to the second plug-in post;
- the second plug-in post and the plug are connected in the second plug-in hole.
- the first positioning portion includes a positioning card seat disposed on the body, and the positioning card seat includes a card seat body and a positioning pin elastically connected to the card seat body;
- the second positioning portion includes a third insertion hole provided in the body
- the positioning pin moves relative to the card holder body, the positioning pin is separated from the third insertion hole; when the positioning pin is reset, the positioning pin is inserted in the third insertion hole.
- an accommodating slot is provided on the card holder body, an elastic member is disposed in the accommodating slot, and an end of the card holder body is provided with a through hole communicating with the accommodating slot;
- a boss is provided on one side of the positioning pin, one end of the positioning pin is inserted into the through hole, and the positioning pin abuts the elastic member through the boss;
- the positioning pin When the positioning pin moves relative to the card body, the positioning pin compresses the elastic member through the boss, one end of the positioning pin is retracted into the through hole, and the positioning pin is separated from the first hole.
- Three insertion holes when the positioning pin is reset under the elastic force of the elastic member, one end of the positioning pin is exposed in the through hole, and one end of the positioning pin is inserted in the third insertion hole .
- the elastic member is a cylindrical spring, and a screw is connected to the side wall of the accommodation groove, and the elastic member is sleeved on the outside of the screw and is compressed or stretched relative to the screw;
- the positioning pin is Z-shaped, and the boss is formed at a turning point. One end of the positioning pin is inserted into the through hole, and the turning point is latched to an end of the elastic member.
- the other end of the positioning pin is integrally vertically connected with a push plate.
- an end of one end of the positioning pin is provided with an inclined surface
- the contour shape of the third plug-in hole matches the contour shape of the end of one end of the positioning pin.
- the embodiment of the present invention also provides a tilting mechanism for a drone, and the tilting mechanism is a tilting mechanism in the aforementioned drone.
- the utility model has at least the following beneficial effects:
- a first plug-in portion and a first positioning portion are provided on a tilting mechanism of a tilting device, and a second plug-in portion and a second positioning portion are provided on a fuselage.
- connection part and the second insertion part can realize the assembly and connection of the tilting device and the body; when the tilting device needs to be removed from the body, only the first positioning part needs to be removed
- Separation from the second positioning part and separation of the first plug-in part and the second plug-in part can realize the disassembly and separation of the tilting device from the main body, and the operation is simple and convenient, and the disassembly and assembly efficiency is improved.
- FIG. 1 is a schematic structural diagram of a drone provided by an embodiment of the present invention
- FIG. 2 is a schematic structural diagram of a tilting mechanism in FIG. 1;
- FIG. 3 is an exploded view of the positioning card holder in FIG. 2;
- FIG. 4 is a schematic structural diagram of a positioning card seat in FIG. 2.
- an embodiment of the present invention provides an unmanned aerial vehicle including a tilting mechanism, which includes a main body 1, and a first insertion portion 2 and a first positioning portion are provided on the main body 1;
- the main body 4 is provided with a second plug-in portion 5 and a second positioning portion; wherein the first plug-in portion 2 and the second plug-in portion 5 are pluggably connected, and the first positioning portion It is detachably and cooperatively connected with the second positioning portion to prevent relative movement between the first plug-in portion 2 and the second plug-in portion 5.
- the tilting mechanism of the drone may be a device that controls the tilting of the drone propeller, so that the drone can have both a vertical take-off and landing flight mode and a fixed-wing flight mode.
- the first plug-in portion 2 and the first positioning portion may be provided on the outer surface of the housing of the tilting mechanism, and the fuselage 4 may be a drone.
- the wing part is provided with the second plug-in part 5 and the second positioning part.
- the second plug-in part 5 and the second positioning part may be provided on the outer surface of the casing of the wing part.
- the first plug-in part 2 After plug-in connection with the second plug-in part 5, after the first positioning part and the second positioning part are cooperatively connected, the first plug-in part 2 and the second plug-in part 5 will not produce relative movement, and the tilting mechanism can be stabilized It is installed on the wing part of the fuselage 4 to assemble the tilting mechanism and the fuselage 4; when the first positioning part and the second positioning part are separated, the first plug-in part 2 and the second plug-in part 5 After being pulled out, the tilting mechanism can be detached from the fuselage 4 to realize the disassembly of the tilting mechanism and the fuselage 4, and the operation is simple and convenient. .
- the unmanned aerial vehicle provided by the embodiment of the present utility model is provided with a first plug-in portion and a first positioning portion on a tilt mechanism, and a second plug-in portion and a second positioning portion on a fuselage, thereby achieving When the tilting mechanism is assembled on the fuselage, only the first plug-in portion and the second plug-in portion need to be mated and connected, and the first positioning portion and the second positioning portion must be mated to prevent the first plug-in connection.
- the relative movement between the part and the second insertion part can realize the assembly and connection of the tilting mechanism and the fuselage; when the tilting mechanism needs to be detached from the fuselage, only the first positioning part and the The separation of the second positioning part and the separation of the first plug-in part and the second plug-in part can realize the disassembly and separation of the tilting mechanism and the fuselage.
- the operation is simple and convenient, and the disassembly and assembly efficiency is improved.
- the body 1 may include a driver, and the body 1 may further be provided with a first electrical plug connector 7 electrically connected to the driver; and the body 4 may further be provided with an electrical module capable of communicating with an external electrical module.
- the connected second electrical plug connector 8, the second electrical plug connector 8 and the first electrical plug connector 7 are pluggable and electrically connected; the first electrical plug connector 7 and the second electrical plug connector
- the plugging direction of 8 is the same as that of the first plug-in part 2 and the second plug-in part 5; when the first plug-in part 2 and the second plug-in part 5 are mated with each other, the first electrical plug connector 7 Mating with the second electrical plug connector 8; when the first plug connector 2 and the second plug connector 5 are separated from each other, the first electrical plug connector 7 and the second electrical plug connector 8 are separated.
- the driver may be a steering gear that drives the tilting axis of the propeller
- the external electrical module may be a flight control system.
- the external electrical module may also be a power system, a communication system, or a variety of load systems such as imaging, spraying, yelling, and launching that can be mounted on the drone, which is not limited herein.
- the first electrical plug connector 7 and the second electrical plug connector 8 can be plugged in, thereby realizing the electrical connection between the servo and the flight control system, and the first positioning part and the second positioning part can be connected to ensure that the first electrical connector 7 and the second electrical The male connector 8 does not move relatively, thereby ensuring a reliable electrical connection between the two.
- the first positioning portion and the second positioning portion are separated, and then By separating the first plug-in part 2 and the second plug-in part 5, the first electrical plug connector 7 and the second electrical plug connector 8 can be separated, thereby achieving the disconnection of the steering gear from the flight control system. That is to say, such a structural design realizes that the electrical connection or disconnection between the servo and the flight control system can be completed during the installation or disassembly of the tilting mechanism and the fuselage 4, and it is not necessary to separately connect the servo and the flight.
- both the first electrical plug connector 7 and the second electrical plug connector 8 may be aviation plugs, and the first electrical plug connector 7 may be an aviation plug head, and the second electrical plug connector 8 may be an aviation plug. Male head.
- the first plug-in part 2 and the second plug-in part 5 may have various structural forms, as long as the plug-in connection between the two can be achieved.
- the first plug-in portion 2 may include a first plug-in column 21 disposed on the body 1 and parallel to the surface of the body 1; the second plug-in portion 5 may include a body 4
- the first plug-in hole 51 extends in a direction parallel to the first plug-in post 21; the first plug-in post 21 is plugged into the first plug-in hole 51.
- the first insertion hole 51 may be formed by a first clamping block 41 provided on the surface of the fuselage 4 and provided with slots penetrating through both end surfaces thereof, and the first clamping block 41 is fastened. Connected to the surface of the fuselage 4 so that the slot thereon forms a first insertion hole 51 with the surface of the fuselage 4.
- a first inserting block 9 may be installed on the surface of the body 1, and the first inserting block 9 may be provided on the surface.
- the first plug-in post 21 is plugged into the first plug-in hole 51
- the mating connection of the first plug-in part 2 and the second plug-in part 5 can be achieved, the structure is simple, the operation is convenient, and the fuselage 4 will not be damaged.
- the number of the first plug-in posts 21 may be two or more, and the number of the slots on the first plug-in block 9 may also be two or more.
- the first plug-in portion 2 may further include a second plug-in post disposed on the body 1 and parallel to the first plug-in post 21 and extending in the same direction as the first plug-in post 21. 22; the second plug-in portion 5 may further include a second plug-in hole 52 provided in the main body 4 and extending in a direction parallel to the second plug-in post 22; Two insertion holes 52.
- the second plug-in post 22 and the first plug-in post 21 may be located on both sides of the same surface of the body 1, respectively. Accordingly, the second plug-in hole 52 and the first plug-in hole 51 may be respectively located Both sides of the corresponding surface on the fuselage 4 to further improve the assembly stability of the tilting mechanism and the fuselage 4.
- a second clamping block 42 may be provided on the fuselage 4 on the surface of which is provided with slots penetrating through both end surfaces thereof. The second clamping block 42 is fastened and connected to the surface of the fuselage 4 such that The groove and the surface of the fuselage 4 form a second plug-in hole 52.
- a second plug-in block may be installed on the surface of the body 1.
- the second plug-in block may be provided with an L-shaped plug-in arm.
- the second parallel post 22 is formed on the parallel surface portion.
- the lengths of the first plug-in post 21 and the second plug-in post 22 may be equal to ensure that when the first plug-in post 21 and the first plug-in hole 51 are in place, the second plug-in post 22 and The second insertion hole 52 can also be inserted into place.
- the first positioning portion and the second positioning portion may have various structural forms, as long as the detachable cooperative connection between the two can be achieved.
- the first positioning portion may include a positioning card holder 3 disposed on the body 1, and the positioning card holder 3 may include a card body 31 and a positioning pin elastically connected to the card body 31. 32; the second positioning portion may include a third insertion hole 6 provided in the fuselage 4; when the positioning pin 32 moves relative to the card body 31, the positioning pin 32 is detached from the third insertion hole 6; when the positioning pin 32 is reset, the positioning The pin 32 is inserted in the third insertion hole 6.
- an external force may be applied to the positioning pin 32 to pull the positioning pin 32 away from the third insertion hole 6 so that the first positioning portion is separated from the second positioning portion, and then the tilt mechanism is moved.
- an external force can be applied to the positioning pin 32 first to ensure that it will not be inserted into the third plug Hole 6, and then move the tilting mechanism to make the first plug-in part 2 and the second plug-in part 5 plug-in connection, after the first plug-in part 2 and the second plug-in part 5 are inserted into position, remove the positioning pin
- the external force applied by 32 resets the positioning pin 32, so that the positioning pin 32 is inserted into the third insertion hole 6, thereby assembling the tilting mechanism.
- the body 4 may be provided with a third clamping block 43 on the surface of which is provided with a slot penetrating through both end surfaces thereof, the third insertion hole 6 may be disposed on the third clamping block 43, and the positioning card holder 3 may be It is arranged on one side of the body 1 and has a simple structure and convenient operation without causing damage to the fuselage 4.
- the aforementioned second insert block may be the same component as the card holder body 31, that is, the card holder body 31
- the end portion may be designed to be L-shaped so as to form an L-shaped plugging arm, and a portion of the plugging arm parallel to the surface of the body 1 forms the aforementioned second plugging post 22.
- the aforementioned second electrical plug connector 8, the first clamping block 41, the second clamping block 42, and the third clamping block 43 can be connected to the casing of the fuselage 4 through a connection plate 44 cushioned inside the casing of the fuselage 4, that is, the connection plate 44 is cushioned on the inner surface of the casing of the fuselage 4, and then the fasteners are sequentially passed through the connection plate 44
- the housing and the body 4 are respectively connected to the second electrical plug connector 8, the first clip block 41, the second clip block 42, and the third clip block 43, which ensure the connection strength between the body 4 and the tilt mechanism.
- the first insert block 9, the first electrical plug connector 7, and the positioning card holder 3 may be disposed on the same surface of the body 1, and The first electrical plug connector 7 is located between the first plug block 9 and the positioning card holder 3, and accordingly, the second electrical plug connector 8, the first clip block 41, the second clip block 42, and the third clip block 43 may It is arranged at a corresponding position on a surface of the casing of the fuselage 4.
- the card holder body 31 may be provided with a receiving slot 311, and the receiving slot 311 may be provided with an elastic member 312 and the card holder body 31.
- the end of the positioning pin 32 may be provided with a through hole 313 communicating with the receiving groove 311; one side of the positioning pin 32 is provided with a boss 321; one end of the positioning pin 32 is inserted into the through hole 313; The piece 312 abuts; when the positioning pin 32 moves relative to the card body 31, the positioning pin 32 compresses the elastic member 312 through the boss 321, one end of the positioning pin 32 is retracted into the through hole 313, and the positioning pin 32 is released from the third plug. Hole 6; when the positioning pin 32 is reset under the elastic force of the elastic member 312, one end of the positioning pin 32 is exposed in the through hole 313, and one end of the positioning pin 32 is inserted in the third insertion hole 6.
- the elastic member 312 may be a cylindrical spring, and a screw 314 may be threadedly connected to a side wall of the accommodation groove 311, so that the elastic member 312 is sleeved on the outside of the screw 314 and can be compressed or pulled relative to the screw 314.
- the positioning pin 32 may be Z-shaped as a whole, and a protrusion 321 is formed at the turning point. One end of the positioning pin 32 is inserted into the through hole 313, and the turning point is snapped to the end of the spring.
- a push plate 322 which is vertically connected with the integral pin can be provided at the other end of the positioning pin 32, so that when the user pushes the push plate 322, the positioning pin 32 compresses the spring through the boss 321 and overcomes the elasticity of the spring The force causes one end of the positioning pin 32 to be retracted into the through hole 313, so that the positioning pin 32 is separated from the third insertion hole 6, thereby realizing the component force of the first positioning portion and the second positioning portion; when the user releases the push plate 322 , Resetting the positioning pin 32 under the elastic force of the spring so that one end of the positioning pin 32 is exposed from the through hole 313, so that the positioning pin 32 is inserted into the third insertion hole 6, thereby realizing the first positioning portion and the second positioning Fitting connection, structure Single, reliable.
- an inclined surface 323 may be provided at an end of one end of the positioning pin 32; the contour shape of the third insertion hole 6 may be adapted to the end contour shape of one end of the positioning pin 32. .
- the positioning pin 32 and the third insertion hole 6 are realized.
- the positioning pin 32 When it is not fully plugged firmly, the positioning pin 32 will smoothly slide into the third insertion hole 6 through the inclined surface 323 due to the vibration effect generated by the drone operation, so that the positioning pin 32 is inserted into the third insertion hole 6 It is firmly connected to further ensure the assembly stability between the tilting mechanism and the fuselage 4.
- An embodiment of the present invention further provides a tilting mechanism, which includes a body 1, and the body 1 is provided with a first plug-in portion 2 and a first positioning portion.
- the tilting mechanism involved in this embodiment can adopt the tilting mechanism structure described in the drone of the above embodiment.
- the tilting mechanism structure described in the drone of the above embodiment For specific implementation and working principle, refer to the corresponding content in the above embodiment, here No longer.
- a first plug-in portion and a first positioning portion are provided on the tilting mechanism, and a second plug-in portion and a second positioning portion are provided on the fuselage.
- the relative movement between the part and the second insertion part can realize the assembly and connection of the tilting mechanism and the fuselage; when the tilting mechanism needs to be detached from the fuselage, only the first positioning part and the The separation of the second positioning part and the separation of the first plug-in part and the second plug-in part can realize the disassembly and separation of the tilting mechanism and the fuselage.
- the operation is simple and convenient, and the disassembly and assembly efficiency is improved.
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Abstract
一种无人机，包括倾转机构，倾转机构包括本体(1)和设置于本体(1)的第一插接部(2)和第一定位部；机身(4)，机身(4)上设置有第二插接部(5)和第二定位部，第一插接部(2)和第二插接部(5)可插拔地插合连接，第一定位部和第二定位部可拆卸地配合连接以阻止第一插接部(2)和所述第二插接部(5)之间产生相对运动。该无人机倾转机构组装拆卸方便，拆装效率高。同时涉及一种倾转机构。
Description
本实用新型涉及航空飞行器技术领域，具体而言，涉及一种无人机及倾转机构。
倾转旋翼无人机是一种兼具垂直起降和固定翼飞行模态的飞行器，倾转装置是其核心组成部分之一，倾转装置与机身连接，用于实现该类无人机在固定翼模态和垂直起降模态之间的转换。
目前，该类无人机的倾转装置与机身通常采用螺钉等紧固件进行连接，当用户需要拆卸倾转装置时，须首先拆卸螺钉等紧固件，才能将倾转装置从机身上拆卸下来，同样地，当用户需要组装倾转装置时，须通过组装螺钉等紧固件，才能实现倾转装置与机身的组装，操作不便，拆装效率较低。
实用新型内容
有鉴于此，本实用新型实施例提供一种无人机及倾转机构，主要目的是使得倾转装置与机身的组装和拆卸更方便，以提高拆装效率。
为达到上述目的，本实用新型主要提供如下技术方案：
一方面，本实用新型实施例提供了一种无人机，包括：
倾转机构，所述倾转机构包括本体和设置于所述本体上的第一插接部和第一定位部；
机身，所述机身上设置有第二插接部和第二定位部；
其中，所述第一插接部和所述第二插接部可插拔地插合连接，所述第一定位部和所述第二定位部可拆卸地配合连接以阻止所述第一插接部和所述第二插接部之间产生相对运动。
进一步地，所述本体包括驱动器，所述本体上还设置有与所述驱动器电连接的第一电性插接头；
所述机身上还设置有能够与外部电器模块电连接的第二电性插接头，所述第二电性插接头与所述第一电性插接头可插拔地电性插合连接；
所述第一电性插接头和所述第二电性插接头的插接方向与所述第一插接部和所述第二插接部的插接方向相同；所述第一插接部和所述第二插接部相互插合时，所述第一电性插接头和所述第二电性插接头相互插合；所述第一插接部和所述第二插接部相互分离时，所述第一电性插接头和所述第二电性插接头相互分离。
进一步地，所述第一插接部包括设置于所述本体且与所述本体的表面相 平行的第一插接柱；
所述第二插接部包括设置于所述机身且沿与所述第一插接柱相平行的方向延伸的第一插接孔；
所述第一插接柱插合连接于所述第一插接孔内。
进一步地，所述第一插接部还包括设置于所述本体，并与所述第一插接柱相平行且与所述第一插接柱延伸方向相同的第二插接柱；
所述第二插接部还包括设置于所述机身且沿与所述第二插接柱相平行的方向延伸的第二插接孔；
所述第二插接柱与插合连接于所述第二插接孔内。
进一步地，所述第一定位部包括设置于所述本体的定位卡座，所述定位卡座包括卡座本体和与所述卡座本体弹性连接的定位销；
所述第二定位部包括设置于所述机身的第三插接孔；
所述定位销相对所述卡座本体移动时，所述定位销脱离所述第三插接孔；所述定位销复位时，所述定位销插设于所述第三插接孔。
进一步地，所述卡座本体上设置有容置槽，所述容置槽内设置有弹性件，所述卡座本体的端部设置有与所述容置槽连通的通孔；
所述定位销的一侧设置有凸台，所述定位销的一端插设于所述通孔，所述定位销通过所述凸台与所述弹性件相抵接；
所述定位销相对所述卡座本体移动时，所述定位销通过所述凸台压缩所述弹性件，所述定位销的一端缩入所述通孔内，所述定位销脱离所述第三插接孔；所述定位销在所述弹性件的弹力作用下复位时，所述定位销的一端显露于所述通孔，所述定位销的一端插设于所述第三插接孔。
进一步地，所述弹性件为圆柱弹簧，所述容置槽的侧壁上螺纹连接有螺钉，所述弹性件套接在所述螺钉的外部并相对所述螺钉进行压缩或拉伸；
所述定位销呈Z形，且转折处形成所述凸台，所述定位销的一端插设在所述通孔内，转折处卡接于所述弹性件的端部。
进一步地，所述定位销的另一端一体垂直连接有推板。
进一步地，所述定位销一端的端部设置有倾斜面；
所述第三插接孔的轮廓形状与所述定位销一端的端部轮廓形状相适配。
另一方面，本实用新型实施例还提供一种倾转机构，用于无人机，所述倾转机构为前述的无人机中的倾转机构。
借由上述技术方案，本实用新型至少具有以下有益效果：
本实用新型实施例提供的技术方案，通过在倾转装置的倾转机构上设置第一插接部和第一定位部，在机身上设置第二插接部和第二定位部，实现了当需要将倾转装置组装在机身上时，只需将第一插接部和第二插接部插合连接，以及将第一定位部和第二定位部进行配合连接以阻止第一插接部和所述第二插接部之间产生相对运动，即可实现倾转装置与机身的组装连接；当需 要将倾转装置从机身上拆卸下来时，只需将第一定位部和第二定位部分离，以及将第一插接部和第二插接部分离，即可实现倾转装置与机身的拆卸分离，操作简单方便，提高了拆装效率。
图1为本实用新型实施例提供的一种无人机的结构示意图；
图2为图1中倾转机构的结构示意图；
图3为图2中定位卡座的爆炸图；
图4为图2中定位卡座的结构示意图。
为使本实用新型的目的、技术方案和优点更加清楚，下面将结合本实用新型的优选实施例中的附图，对本实用新型实施例中的技术方案进行更加详细的描述。在附图中，自始至终相同或类似的标号表示相同或类似的元件或具有相同或类似功能的元件。所描述的实施例是本实用新型一部分实施例，而不是全部的实施例。下面通过参考附图描述的实施例是示例性的，旨在用于解释本实用新型，而不能理解为对本实用新型的限制。基于本实用新型中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例，都属于本实用新型保护的范围。下面结合附图对本实用新型的实施例进行详细说明。
在本实施例的描述中，需要理解的是，术语“中心”、“纵向”、“横向”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本实施例和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本实施例保护范围的限制。
如图1所示，本实用新型实施例提供了一种无人机，包括倾转机构，该倾转机构包括本体1，在本体1上设置有第一插接部2和第一定位部；机身4，该机身4上设置有第二插接部5和第二定位部；其中，第一插接部2和第二插接部5可插拔地插合连接，第一定位部和第二定位部可拆卸地配合连接以阻止第一插接部2和第二插接部5之间产生相对运动。
在一些示例中，该无人机的倾转机构可以为控制无人机螺旋桨发生倾转的装置，以使得无人机能够兼具垂直起降飞行模态和固定翼飞行模态，其上设置有第一插接部2和第一定位部，具体地，第一插接部2和第一定位部可以设置在倾转机构的壳体外表面，而机身4具体可以为无人机的机翼部位，其上设置有第二插接部5和第二定位部，具体，第二插接部5和第二定位部可以设置在机翼部位的壳体外表面，当第一插接部2与第二插接部5插合连接，第一定位部和第二定位部配合连接后，使得第一插接部2和第二插接部5不会产生相对运动，倾转机构即可稳固地安装到机身4的机翼部位，实现 了倾转机构与机身4的组装；当第一定位部和第二定位部相分离，第一插接部2与第二插接部5相拔离后，倾转机构即可拆离于机身4，实现了倾转机构与机身4的拆卸，操作简单方便。
本实用新型实施例提供的无人机，通过在倾转机构上设置第一插接部和第一定位部，在机身上设置第二插接部和第二定位部，实现了当需要将倾转机构组装在机身上时，只需将第一插接部和第二插接部插合连接，以及将第一定位部和第二定位部进行配合连接以阻止所述第一插接部和所述第二插接部之间产生相对运动，即可实现倾转机构与机身的组装连接；当需要将倾转机构从机身上拆卸下来时，只需将第一定位部和第二定位部分离，以及将第一插接部和第二插接部分离，即可实现倾转机构与机身的拆卸分离，操作简单方便，提高了拆装效率。
在一些示例中，参见图1，本体1可以包括驱动器，该本体1上还可以设置有与驱动器电连接的第一电性插接头7；该机身4上还可以设置能够与外部电器模块电连接的的第二电性插接头8，第二电性插接头8与第一电性插接头7可插拔地电性插合连接；第一电性插接头7和第二电性插接头8的插接方向与第一插接部2和第二插接部5的插接方向相同；第一插接部2和第二插接部5相互插合时，第一电性插接头7和第二电性插接头8插合；第一插接部2和第二插接部5相互分离时，第一电性插接头7和第二电性插接头8分离。其中，驱动器可以为驱动螺旋桨的倾转轴进行倾转的舵机，而外部电器模块可以为飞控系统。
需要说明的是，上述外部电器模块还可以是可搭载在无人机上的电源系统、通信系统或成像、喷淋、喊话、投放等多种载荷系统，在此不做限定。
根据上述实施例，当组装倾转机构与机身4时，在将第一插接部2与第二插接部5插接完毕后，第一电性插接头7与第二电性插接头8即可插接完毕，从而实现了舵机与飞控系统的电连接，而且，通过第一定位部和第二定位部地配合连接，还可以保证第一电性插接头7与第二电性插接头8不会发生相对移动，从而保证二者之间的可靠电连接；同样地，当拆卸倾转机构与机身4时，在将第一定位部和第二定位部分离后，再将第一插接部2和第二插接部5分离，第一电性插接头7与第二电性插接头8即可相分离，从而实现了舵机与飞控系统的断开，也就是说，这样的结构设计，实现了在倾转机构与机身4安装或拆卸的过程中即可完成舵机与飞控系统之间的电连接或断开，不必再另行连接舵机与飞控系统，使得倾转机构的舵机与机身4的飞控系统之间的连接或断开同样更加简单方便，进一步提高了倾转机构与机身4之间的拆装效率。具体地，第一电性插接头7和第二电性插接头8均可以为航空插头，且第一电性插接头7可以为航插母头，第二电性插接头8可以为航插公头。
其中，第一插接部2和第二插接部5的结构形式可以有多种，只要可以 实现二者之间的插合连接即可。
在一些示例中，参见图1，第一插接部2可以包括设置于本体1且与本体1的表面相平行的第一插接柱21；第二插接部5可以包括设置于机身4且沿与第一插接柱21相平行的方向延伸的第一插接孔51；第一插接柱21插合连接于第一插接孔51内。
在一些示例中，第一插接孔51可以为由设置在机身4表面上，且其上设置有贯通其两端面的插槽的第一卡块41形成，该第一卡块41扣合连接于机身4的表面，使得其上的插槽与机身4表面形成第一插接孔51，在本体1的表面可以安装有第一插块9，该第一插块9上可以设置有L形插接臂，该插接臂上与本体1表面平行的部分形成第一插接柱21，当组装倾转机构时，可以移动倾转机构使其上的第一插接柱21插入机身4的第一插接孔51内，直到第一插块9上的相应部位与第一卡块41上的相应部位相抵接，第一插接柱21与第一插接孔51插接到位，即可实现第一插接部2与第二插接部5的插合连接，结构简单，操作方便，且不会对机身4造成损伤。其中，第一插接柱21的数量可以为两个或两个以上，而第一插块9上的插槽数量亦可以为两个或两个以上。
在一些示例中，参见图1，第一插接部2还可以包括设置于本体1，并与第一插接柱21相平行且与第一插接柱21延伸方向相同的第二插接柱22；第二插接部5还可以包括设置于机身4且沿与第二插接柱22相平行的方向延伸的第二插接孔52；第二插接柱22与插合连接于第二插接孔52内。
在一些示例中，该第二插接柱22与第一插接柱21可以分别位于本体1同一表面的两侧，相应地，该第二插接孔52与第一插接孔51可以分别位于机身4上相应表面的两侧，以进一步提高倾转机构与机身4的组装稳固性。具体在实施时，可以在机身4上设置表面设置有贯通其两端面的插槽的第二卡块42，该第二卡块42扣合连接于机身4的表面，使得其上的插槽与机身4表面形成第二插接孔52，在本体1的表面可以安装有第二插块，该第二插块上可以设置有L形插接臂，该插接臂上与本体1表面平行的部分形成第二插接柱22，当组装倾转机构时，可以移动倾转机构使其上的第一插接柱21和第二插接柱22依次分别插入机身4的第一插接孔51和第二插接孔52内，直到第二插块上的相应部位与第二卡块42上的相应部位相抵接，第二插接柱22与第二插接孔52插接到位，即可实现第一插接部2与第二插接部5的插合连接，结构简单，操作方便，且不会对机身4造成损伤。
在一些示例中，第一插接柱21与第二插接柱22的长度可以相等，以保证第一插接柱21与第一插接孔51插接到位时，第二插接柱22与第二插接孔52亦可以插接到位。
其中，第一定位部和第二定位部的结构形式可以有多种，只要可以实现二者之间的可拆卸配合连接即可。
在一些示例中，参见图1和图2，第一定位部可以包括设置于本体1的定位卡座3，该定位卡座3可以包括卡座本体31和与卡座本体31弹性连接的定位销32；第二定位部可以包括设置于机身4的第三插接孔6；定位销32相对卡座本体31移动时，定位销32脱离第三插接孔6；定位销32复位时，定位销32插设于第三插接孔6。
根据上述实施例，当拆卸倾转机构时，可以向定位销32施加外力以将定位销32拔离第三插接孔6，使得第一定位部与第二定位部分离，再移动倾转机构，使得第一插接部2与第二插接部5分离，从而实现倾转机构的拆卸；当组装倾转机构时，可以首先向定位销32施加外力以保证其不会插入第三插接孔6，然后移动倾转机构以使第一插接部2与第二插接部5插合连接，待第一插接部2与第二插接部5插接到位后，撤除向定位销32施加的外力以使定位销32复位，使得定位销32插入第三插接孔6内，从而实现倾转机构的组装。具体地，可以在机身4上设置表面设置有贯通其两端面的插槽的第三卡块43，第三插接孔6可以设置在该第三卡块43上，且定位卡座3可以设置在本体1的一侧，结构简单，操作方便，且不会对机身4造成损伤。
需要说明的是，在一些示例中，参见图1，为了使得倾转机构的结构更加简单紧凑，前述的第二插块可以与卡座本体31为同一部件，也就是说，卡座本体31的端部可以设计呈L形从而形成L形插接臂，该插接臂上与本体1表面平行的部分形成前述的第二插接柱22。
在一些示例中，参见图1，为了保证机身4与倾转机构之间的连接强度，前述的第二电性插接头8、第一卡块41、第二卡块42以及第三卡块43均可以通过垫设于机身4壳体内部的连接板44与机身4壳体连接，即连接板44垫设在机身4壳体内表面，然后将紧固件依次穿过连接板44和机身4壳体分别与第二电性插接头8、第一卡块41、第二卡块42以及第三卡块43连接，保证了机身4与倾转机构之间的连接强度。
在一些示例中，为了进一步便于机身4与倾转机构之间的拆装，可以将第一插块9、第一电性插接头7和定位卡座3设置在本体1的同一表面，且第一电性插接头7位于第一插块9和定位卡座3之间，相应地，第二电性插接头8、第一卡块41、第二卡块42以及第三卡块43可以设置在机身4壳体的用一表面上的相应位置。
在一些示例中，参见图2、图3和图4，并结合图1，卡座本体31上可以设置有容置槽311，该容置槽311内可以设置有弹性件312，卡座本体31的端部可以设置有与容置槽311连通的通孔313；定位销32的一侧设置有凸台321，定位销32的一端插设于通孔313，定位销32通过凸台321与弹性件312相抵接；定位销32相对卡座本体31移动时，定位销32通过凸台321压缩所述弹性件312，定位销32的一端缩入通孔313内，定位销32脱离第三插接孔6；定位销32在弹性件312的弹力作用下复位时，定位销32的一 端显露于通孔313，定位销32的一端插设于第三插接孔6。
在一些示例中，弹性件312可以为圆柱弹簧，且在容置槽311的侧壁上可以螺纹连接一螺钉314，使得弹性件312套接在螺钉314的外部并可相对螺钉314进行压缩或拉伸，而定位销32的整体可以呈Z形，其转折处形成凸台321，该定位销32的一端插设在通孔313内，转折处卡接于弹簧的端部，同时，为了便于定位销32的控制，可以在定位销32的另一端设置与其一体垂直连接的推板322，这样便实现了当用户推动该推板322，使定位销32通过凸台321压缩弹簧并克服弹簧的弹性力使得定位销32的一端缩入通孔313内，从而使得定位销32脱离第三插接孔6，进而实现第一定位部和第二定位部的分力；当用户放开该推板322，使定位销32在弹簧的弹性力作用下复位以使定位销32的一端从通孔313中显露，从而使得定位销32插入第三插接孔6，进而实现第一定位部和第二定位部的配合连接，结构简单，实现可靠。
在一些示例中，参见图1和图3，在定位销32一端的端部可以设置有倾斜面323；第三插接孔6的轮廓形状可以与定位销32一端的端部轮廓形状相适配。通过定位销32上倾斜面323的设置，同时将第三插接孔6的轮廓形状设计为与定位销32端部的轮廓形状相适配，实现了在定位销32与第三插接孔6没有完全插接牢靠时，定位销32会因无人机运行而产生的震动作用而通过该倾斜面323顺利地滑入第三插接孔6，使得定位销32与第三插接孔6插接牢靠，进一步保证了倾转机构与机身4之间的组装稳固性。
本实用新型实施例还提供了一种倾转机构，包括本体1，该本体1上设置有第一插接部2和第一定位部。
需要说明的是，本实施例中所涉及的倾转机构可采用上述实施例无人机中所描述的倾转机构结构，具体的实现和工作原理可参见上述实施例中的相应内容，此处不再赘述。
本实用新型实施例提供的倾转机构，通过在倾转机构上设置第一插接部和第一定位部，在机身上设置第二插接部和第二定位部，实现了当需要将倾转机构组装在机身上时，只需将第一插接部和第二插接部插合连接，以及将第一定位部和第二定位部进行配合连接以阻止所述第一插接部和所述第二插接部之间产生相对运动，即可实现倾转机构与机身的组装连接；当需要将倾转机构从机身上拆卸下来时，只需将第一定位部和第二定位部分离，以及将第一插接部和第二插接部分离，即可实现倾转机构与机身的拆卸分离，操作简单方便，提高了拆装效率。
最后应说明的是：以上实施例仅用以说明本实用新型的技术方案，而非对其限制；尽管参照前述实施例对本实用新型进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本实用新型各实施例技术方案的精神和范围。
Claims (10)
- 一种无人机，其特征在于，包括：倾转机构，所述倾转机构包括本体和设置于所述本体的第一插接部和第一定位部；机身，所述机身上设置有第二插接部和第二定位部；其中，所述第一插接部和所述第二插接部可插拔地插合连接，所述第一定位部和所述第二定位部可拆卸地配合连接以阻止所述第一插接部和所述第二插接部之间产生相对运动。
- 根据权利要求1所述的无人机，其特征在于，所述本体包括驱动器，所述本体上还设置有与所述驱动器电连接的第一电性插接头；所述机身上还设置有能够与外部电器模块电连接的第二电性插接头，所述第二电性插接头与所述第一电性插接头可插拔地电性插合连接；所述第一电性插接头和所述第二电性插接头的插接方向与所述第一插接部和所述第二插接部的插接方向相同；所述第一插接部和所述第二插接部相互插合时，所述第一电性插接头和所述第二电性插接头相互插合；所述第一插接部和所述第二插接部相互分离时，所述第一电性插接头和所述第二电性插接头相互分离。
- 根据权利要求1或2所述的无人机，其特征在于，所述第一插接部包括设置于所述本体且与所述本体的表面相平行的第一插接柱；所述第二插接部包括设置于所述机身且沿与所述第一插接柱相平行的方向延伸的第一插接孔；所述第一插接柱插合连接于所述第一插接孔内。
- 根据权利要求3所述的无人机，其特征在于，所述第一插接部还包括设置于所述本体，并与所述第一插接柱相平行且与所述第一插接柱延伸方向相同的第二插接柱；所述第二插接部还包括设置于所述机身且沿与所述第二插接柱相平行的方向延伸的第二插接孔；所述第二插接柱与插合连接于所述第二插接孔内。
- 根据权利要求1至4中任一项所述的无人机，其特征在于，所述第一定位部包括设置于所述本体的定位卡座，所述定位卡座包括卡座本体和与所述卡座本体弹性连接的定位销；所述第二定位部包括设置于所述机身的第三插接孔；所述定位销相对所述卡座本体移动时，所述定位销脱离所述第三插接孔；所述定位销复位时，所述定位销插设于所述第三插接孔。
- 根据权利要求5所述的无人机，其特征在于，所述卡座本体上设置有容置槽，所述容置槽内设置有弹性件，所述卡座本体的端部设置有与所述容置槽连通的通孔；所述定位销的一侧设置有凸台，所述定位销的一端插设于所述通孔，所述定位销通过所述凸台与所述弹性件相抵接；所述定位销相对所述卡座本体移动时，所述定位销通过所述凸台压缩所述弹性件，所述定位销的一端缩入所述通孔内，所述定位销脱离所述第三插接孔；所述定位销在所述弹性件的弹力作用下复位时，所述定位销的一端显露于所述通孔，所述定位销的一端插设于所述第三插接孔。
- 根据权利要求6所述的无人机，其特征在于，所述弹性件为圆柱弹簧，所述容置槽的侧壁上螺纹连接有螺钉，所述弹性件套接在所述螺钉的外部并相对所述螺钉进行压缩或拉伸；所述定位销呈Z形，且转折处形成所述凸台，所述定位销的一端插设在所述通孔内，转折处卡接于所述弹性件的端部。
- 根据权利要求7所述的无人机，其特征在于，所述定位销的另一端一体垂直连接有推板。
- 根据权利要求6所述的无人机，其特征在于，所述定位销一端的端部设置有倾斜面；所述第三插接孔的轮廓形状与所述定位销一端的端部轮廓形状相适配。
- 一种倾转机构，用于无人机，其特征在于，所述倾转机构为权利要求1至9中任一项所述的无人机中的倾转机构。
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| EP1346910A1 (fr) * | 2002-03-20 | 2003-09-24 | Eurocopter | Rotor de giravion a entraínement homocinétique |
| US7823827B2 (en) * | 2007-07-11 | 2010-11-02 | Piasecki Frederick W | Vectored thruster augmented aircraft |
| CN106005361A (zh) * | 2016-04-07 | 2016-10-12 | 珠海市磐石电子科技有限公司 | 航空动力单元及其飞行机架和模块化飞行器 |
| CN106184734A (zh) * | 2016-08-16 | 2016-12-07 | 西安交通大学 | 一种旋翼飞行器倾转机构 |
| CN206466160U (zh) * | 2016-12-21 | 2017-09-05 | 深圳市道通智能航空技术有限公司 | 可拆卸机臂组件及飞行器 |
| CN109131871A (zh) * | 2018-09-26 | 2019-01-04 | 沈阳无距科技有限公司 | 无人机及倾转机构 |
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|---|---|---|---|---|
| EP1346910A1 (fr) * | 2002-03-20 | 2003-09-24 | Eurocopter | Rotor de giravion a entraínement homocinétique |
| US7823827B2 (en) * | 2007-07-11 | 2010-11-02 | Piasecki Frederick W | Vectored thruster augmented aircraft |
| CN106005361A (zh) * | 2016-04-07 | 2016-10-12 | 珠海市磐石电子科技有限公司 | 航空动力单元及其飞行机架和模块化飞行器 |
| CN106184734A (zh) * | 2016-08-16 | 2016-12-07 | 西安交通大学 | 一种旋翼飞行器倾转机构 |
| CN206466160U (zh) * | 2016-12-21 | 2017-09-05 | 深圳市道通智能航空技术有限公司 | 可拆卸机臂组件及飞行器 |
| CN109131871A (zh) * | 2018-09-26 | 2019-01-04 | 沈阳无距科技有限公司 | 无人机及倾转机构 |
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