CN206984351U - Unmanned vehicle main wing removable structure - Google Patents
Unmanned vehicle main wing removable structure Download PDFInfo
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- CN206984351U CN206984351U CN201720714057.7U CN201720714057U CN206984351U CN 206984351 U CN206984351 U CN 206984351U CN 201720714057 U CN201720714057 U CN 201720714057U CN 206984351 U CN206984351 U CN 206984351U
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Abstract
Description
技术领域technical field
本实用新型涉及无人飞行器技术领域，尤其涉及的是一种无人飞行器主翼可拆结构。The utility model relates to the technical field of unmanned aerial vehicles, in particular to a detachable main wing structure of an unmanned aerial vehicle.
背景技术Background technique
无人飞行器的类型多种多样，一些无人飞行器通过螺旋桨控制飞行，一些无人飞行器通过控制舵面动作来控制飞行，舵面控制飞行的无人飞行器中需要有较长的主翼来设置该舵面。现有带主翼的无人飞行器中，主翼通常是固定于机身而不可拆卸的，由于主翼左右两侧臂很长，往往需要很大的包装盒才能将其容纳在内，包装盒大不仅耗材，而且还很占用空间，不利于批量运输。另外，一些无人飞行器的材质是较为脆弱的泡沫塑料，例如是玩具飞行器，而主翼又较长，在存放运输的过程，十分容易折断。There are various types of UAVs. Some UAVs control the flight through the propeller, and some UAVs control the flight by controlling the movement of the rudder surface. The UAVs controlled by the rudder surface need to have a longer main wing to set the rudder noodle. In existing unmanned aerial vehicles with main wings, the main wings are usually fixed on the fuselage and cannot be disassembled. Since the left and right arms of the main wing are very long, it often requires a large packaging box to accommodate them. The large packaging box is not only a consumable , and it takes up a lot of space, which is not conducive to bulk transportation. In addition, some unmanned aerial vehicles are made of relatively fragile foam plastics, such as toy aircraft, and the main wings are long, which is very easy to break during storage and transportation.
实用新型内容Utility model content
本实用新型所要解决的技术问题是提供一种无人飞行器主翼可拆结构，不易折断，便于运输。The technical problem to be solved by the utility model is to provide a detachable main wing structure of an unmanned aerial vehicle, which is not easy to break and is convenient for transportation.
为解决上述问题，本实用新型提出一种无人飞行器主翼可拆结构，包括机身主体，连于所述机身主体两侧的可拆主翼部，及连接结构；所述连接结构包括带有相互配合的扣位的第一电性连接件和第二电性连接件，所述第一电性连接件设于所述机身主体上，所述第二电性连接件设于所述可拆主翼部上，所述第一电性连接件和第二电性连接件相互扣接实现电性导通，并将所述可拆主翼部固定于所述机身主体上。In order to solve the above problems, the utility model proposes a detachable main wing structure of an unmanned aerial vehicle, including a fuselage body, detachable main wings connected to both sides of the fuselage body, and a connecting structure; the connecting structure includes A first electrical connector and a second electrical connector that are buckled together, the first electrical connector is arranged on the main body of the fuselage, and the second electrical connector is arranged on the removable On the detachable main wing, the first electrical connector and the second electrical connector are interlocked to realize electrical conduction, and the detachable main wing is fixed on the main body of the fuselage.
根据本实用新型的一个实施例，还包括设于所述可拆主翼部内的舵面驱动部及设于所述机身主体内的主控电路；所述舵面驱动部与所述第二电性连接件电性连接，所述主控电路与所述第一电性连接件电性连接；所述可拆主翼部上设有可动的舵面，所述舵面驱动部在所述主控电路的控制下驱动所述舵面动作。According to an embodiment of the present invention, it also includes a rudder surface driving part arranged in the detachable main wing part and a main control circuit arranged in the fuselage main body; the rudder surface driving part and the second electric The main control circuit is electrically connected to the first electrical connector; the detachable main wing is provided with a movable rudder surface, and the rudder surface driving part is on the main The rudder surface is driven to move under the control of the control circuit.
根据本实用新型的一个实施例，所述舵面驱动部为舵机和传动部件，所述舵机通过可拆主翼部内埋设的引线连接所述第二电性连接件；所述传动部件的一端连接所述舵机的输出轴，另一端连接所述舵面。According to an embodiment of the present invention, the driving part of the rudder surface is a steering gear and a transmission part, and the steering gear is connected to the second electrical connector through a lead wire embedded in the detachable main wing part; one end of the transmission part The output shaft of the steering gear is connected, and the other end is connected with the steering surface.
根据本实用新型的一个实施例，所述连接结构包括带有相互配合的扣位的电性公座连接器和电性母座连接器，所述电性公座连接器和电性母座连接器的其中一个设于所述机身主体上，另一个设于所述可拆主翼部上，所述电性公座连接器和电性母座连接器对位扣接的同时实现电性插接。According to an embodiment of the present invention, the connection structure includes an electrical male connector and an electrical female connector with mutually matched buckles, and the electrical male connector and the electrical female connector are connected One of the connectors is arranged on the main body of the fuselage, and the other is arranged on the detachable main wing. catch.
根据本实用新型的一个实施例，还包括主翼加强杆，部分插设固定于所述可拆主翼部，另一部分用于对接时插入所述机身主体内。According to an embodiment of the present invention, it further includes a main wing reinforcing rod, part of which is inserted and fixed on the detachable main wing, and the other part is inserted into the main body of the fuselage during docking.
根据本实用新型的一个实施例，还包括机身加强杆，内设于所述机身主体内，与两侧的所述主翼加强杆对接。According to an embodiment of the present invention, it further includes a fuselage reinforcing rod, which is built in the main body of the fuselage and docked with the main wing reinforcing rods on both sides.
根据本实用新型的一个实施例，所述机身加强杆呈管状结构，且口径大于所述主翼加强杆的外径，所述主翼加强杆对接时插入至所述机身加强杆内。According to an embodiment of the present invention, the fuselage reinforcing rod has a tubular structure with a diameter larger than the outer diameter of the main wing reinforcing rod, and the main wing reinforcing rod is inserted into the fuselage reinforcing rod when docked.
根据本实用新型的一个实施例，所述机身加强杆与机身主体内的电池仓框架固连，且所述机身主体内设有用于穿设所述机身加强杆的通道结构。According to an embodiment of the present invention, the fuselage reinforcing rod is fixedly connected to the battery compartment frame in the fuselage main body, and the fuselage main body is provided with a channel structure for passing through the fuselage reinforcing rod.
根据本实用新型的一个实施例，所述主翼加强杆、机身加强杆为玻璃纤维、塑胶、或碳纤维部材。According to an embodiment of the present invention, the main wing stiffener and fuselage stiffener are made of glass fiber, plastic, or carbon fiber parts.
根据本实用新型的一个实施例，所述机身主体和可拆主翼部均为泡沫塑料部材。According to an embodiment of the present invention, the main body of the fuselage and the detachable main wings are all foam plastic materials.
采用上述技术方案后，本实用新型相比现有技术具有以下有益效果：After adopting the above technical solution, the utility model has the following beneficial effects compared with the prior art:
机身主体与两侧可拆主翼部之间通过连接结构实现可快速拆装，使得较长主翼与机身主体可分离，将展开的主翼收纳起来，从而在包装时，可以缩小整机所需占用的空间，便于运输存放；通过带有扣位的第一电性连接件和第二电性连接件连接，一方面实现了机身主体和可拆主翼部之间的可拆卸连接固定，另一方面还可以实现双方的电性导通，这对于机身主电路对舵面的控制来说是十分有益的，可避免连接部位的走线紊乱或外露，电性不稳定等问题；The main body of the fuselage and the detachable main wings on both sides can be disassembled quickly through the connection structure, so that the longer main wings can be separated from the main body of the fuselage, and the unfolded main wings can be stored, so that the package can reduce the requirements of the whole machine. The occupied space is convenient for transportation and storage; through the connection between the first electrical connector and the second electrical connector with buckles, on the one hand, the detachable connection and fixation between the main body of the fuselage and the detachable main wing is realized; On the one hand, it can also realize the electrical conduction between the two sides, which is very beneficial to the control of the main circuit of the fuselage on the rudder surface, and can avoid problems such as disordered or exposed wiring of the connecting part, and electrical instability;
舵面驱动部设置在可拆主翼部上，可缩短与舵面的距离，更便于驱动；而通过第一电性连接件和第二电性连接件的电性导通来实现主控电路与舵面驱动部之间的电性连接，可以保证线路的整齐及信号的稳定性。The driving part of the rudder surface is arranged on the detachable main wing, which can shorten the distance from the rudder surface and make it easier to drive; and the main control circuit and the The electrical connection between the driving parts of the steering surface can ensure the orderliness of the circuit and the stability of the signal.
附图说明Description of drawings
图1为本实用新型一实施例的无人飞行器主翼可拆结构拆卸状态的俯视结构示意图；Fig. 1 is a top view structural schematic diagram of the detachable state of the main wing detachable structure of an unmanned aerial vehicle according to an embodiment of the present invention;
图2为本实用新型一实施例的无人飞行器主翼可拆结构拆卸状态的立体结构示意图；Fig. 2 is a three-dimensional structural schematic diagram of the detachable state of the main wing detachable structure of the unmanned aerial vehicle according to an embodiment of the present invention;
图3为本实用新型一实施例的机身主体的爆炸结构示意图；Fig. 3 is a schematic diagram of the exploded structure of the main body of the fuselage according to an embodiment of the present invention;
图4为本实用新型一实施例的无人飞行器主翼可拆结构装配状态的立体结构示意图。Fig. 4 is a three-dimensional structural schematic diagram of an assembled state of the main wing detachable structure of an unmanned aerial vehicle according to an embodiment of the present invention.
图中标记说明：Instructions for marks in the figure:
1-机身主体，11-上机身，12-下机身，101-通道结构，2-可拆主翼部，21-舵面，31-第一电性连接件，32-第二电性连接件，4-舵机，5-主翼加强杆，6-机身加强杆，7-电池仓框架。1-main fuselage, 11-upper fuselage, 12-lower fuselage, 101-channel structure, 2-detachable main wing, 21-rudder surface, 31-first electrical connector, 32-second electrical Connectors, 4-steering gear, 5-main wing reinforcement rod, 6-fuselage reinforcement rod, 7-battery compartment frame.
具体实施方式detailed description
为使本实用新型的上述目的、特征和优点能够更加明显易懂，下面结合附图对本实用新型的具体实施方式做详细的说明。In order to make the above purpose, features and advantages of the present utility model more obvious and understandable, the specific implementation of the present utility model will be described in detail below in conjunction with the accompanying drawings.
在下面的描述中阐述了很多具体细节以便于充分理解本实用新型。但是本实用新型能够以很多不同于在此描述的其它方式来实施，本领域技术人员可以在不违背本实用新型内涵的情况下做类似推广，因此本实用新型不受下面公开的具体实施的限制。In the following description, numerous specific details are set forth in order to provide a full understanding of the present invention. However, the utility model can be implemented in many other ways different from those described here, and those skilled in the art can do similar promotions without violating the connotation of the utility model, so the utility model is not limited by the specific implementation disclosed below .
在一个实施例中，参看图1-4，无人飞行器主翼可拆结构包括机身主体1，连于机身主体1两侧的可拆主翼部2，及连接结构。机身主体1的两侧通过连接结构与可拆主翼部2对接，完成整机装配，拆卸时用力拔下即可。In one embodiment, referring to FIGS. 1-4 , the detachable main wing structure of an unmanned aerial vehicle includes a fuselage main body 1 , detachable main wing parts 2 connected to both sides of the fuselage main body 1 , and a connecting structure. Both sides of the fuselage main body 1 are docked with the detachable main wing 2 through the connection structure to complete the assembly of the whole machine, which can be pulled out by force when dismounting.
连接结构可以包括带有相互配合的扣位的第一电性连接件31和第二电性连接件32。扣位结构只要能够实现第一电性连接件31和第二电性连接件32相互扣接卡固即可，可以是相互配合的定位凸块和卡钩结构，例如，第一电性连接件31上设置定位凸块，第二电性连接件32上设置卡钩结构，对位之后定位凸块扣入卡钩结构内实现两者的连接固定，但并不限于此，其他能够实现可插入固定又施力拔出的扣位结构均可适用。The connecting structure may include a first electrical connection part 31 and a second electrical connection part 32 with mutually matched buckles. As long as the buckle structure can realize the mutual fastening and locking of the first electrical connector 31 and the second electrical connector 32, it can be a positioning protrusion and a hook structure that cooperate with each other, for example, the first electrical connector 31 is provided with a positioning bump, and the second electrical connector 32 is provided with a hook structure. After alignment, the positioning bump is buckled into the hook structure to realize the connection and fixation of the two, but it is not limited to this. Others can realize insertable The buckle structure that is fixed and pulled out with force can be applied.
第一电性连接件31设于机身主体1上，第二电性连接件32设于可拆主翼部2上，优选是固设，例如是粘接固定，而且连接件的结构较为牢固不易损坏，当然，机身材质较为牢固则也可以一体成型设置。第一电性连接件31和第二电性连接件32相互扣接实现电性导通，并将可拆主翼部2固定于机身主体1上。换言之，第一电性连接件31和第二电性连接件32一方面具有用来卡固的扣位，另一方面还具有电性连接结构，该电性连接结构例如是电性插针，则第一电性连接件31和第二电性连接件32扣合到位时电性插针同时接触，使得连接既实现固定又实现电性导通。The first electrical connector 31 is arranged on the main body 1 of the fuselage, and the second electrical connector 32 is arranged on the detachable main wing part 2, preferably fixed, such as adhesively fixed, and the structure of the connector is relatively firm and difficult. Damage, of course, if the fuselage material is stronger, it can also be set in one piece. The first electrical connector 31 and the second electrical connector 32 are interlocked to achieve electrical conduction, and the detachable main wing 2 is fixed on the fuselage body 1 . In other words, on the one hand, the first electrical connector 31 and the second electrical connector 32 have buckles for fastening, and on the other hand, they also have an electrical connection structure, such as an electrical pin, Then, when the first electrical connector 31 and the second electrical connector 32 are fastened in place, the electrical pins are in contact at the same time, so that the connection is not only fixed but also electrically conductive.
可以理解，机身主体1的两侧均设一可拆主翼部2和对应连接结构，从而实现两侧可拆主翼部2的可拆卸连接，当然，若设置为仅机身主体1的一侧主翼部可拆卸也是可行的。It can be understood that a detachable main wing 2 and a corresponding connection structure are provided on both sides of the fuselage body 1, so as to realize the detachable connection of the detachable main wing 2 on both sides. Of course, if only one side of the fuselage body 1 is set It is also possible that the main wings are detachable.
机身主体1与两侧可拆主翼部2之间通过连接结构实现可快速拆装，使得较长主翼部分与机身主体1可分离，将展开的主翼收纳起来，从而在包装时，可以缩小整机所需占用的空间，便于运输存放；通过带有扣位的第一电性连接件31和第二电性连接件32连接，一方面实现了机身主体1和可拆主翼部2之间的可拆卸连接固定，另一方面还可以实现双方的电性导通，这对于机身主电路对舵面的控制来说是十分有益的，可避免连接部位的走线紊乱或外露，电性不稳定等问题。The main body 1 of the fuselage and the detachable main wings 2 on both sides can be disassembled quickly through the connection structure, so that the longer main wing part can be separated from the main body 1 of the fuselage, and the unfolded main wing can be stored, so that it can be reduced in size during packaging. The space required by the whole machine is convenient for transportation and storage; through the connection between the first electrical connector 31 and the second electrical connector 32 with buckles, on the one hand, the connection between the fuselage main body 1 and the detachable main wing 2 is realized. On the other hand, it can also realize the electrical conduction between the two sides, which is very beneficial for the control of the main circuit of the fuselage to the rudder surface, and can avoid the wiring disorder or exposure of the connecting part, and the electric issues of sexual instability.
在一个实施例中，无人飞行器主翼可拆结构还包括设于可拆主翼部2内的舵面驱动部及设于机身主体1内的主控电路(图中未示出)。舵面驱动部与第二电性连接件32电性连接，主控电路与第一电性连接件31电性连接，当第一电性连接件31和第二电性连接件32扣接实现电性连接时，也就实现了主控电路与舵面驱动部之间的电性连接，该电性连接可以包括电源、信号线等方面连接。可拆主翼部2上设有可动的舵面21，舵面驱动部在主控电路的控制下驱动舵面21动作。舵面21具体动作的控制可以是现有的方式。单侧的整个舵面21可以完全位于可拆主翼部2上。In one embodiment, the detachable structure of the main wing of the unmanned aerial vehicle further includes a rudder surface driving part disposed in the detachable main wing part 2 and a main control circuit (not shown in the figure) disposed in the fuselage main body 1 . The steering surface driving part is electrically connected to the second electrical connector 32, and the main control circuit is electrically connected to the first electrical connector 31. When the first electrical connector 31 and the second electrical connector 32 are buckled together, the During the electrical connection, the electrical connection between the main control circuit and the driving part of the steering surface is realized, and the electrical connection may include power supply, signal line and other aspects of connection. A movable rudder surface 21 is provided on the detachable main wing part 2 , and the rudder surface driving part drives the rudder surface 21 to act under the control of the main control circuit. The control of the specific action of the rudder surface 21 can be an existing mode. The entire rudder surface 21 on one side can be completely located on the detachable main wing part 2 .
舵面驱动部设置在可拆主翼部2上，可缩短与舵面21的距离，更便于驱动；而通过第一电性连接件31和第二电性连接件32的电性导通来实现主控电路与舵面驱动部之间的电性连接，可以保证线路的整齐及信号的稳定性。The rudder surface driving part is arranged on the detachable main wing part 2, which can shorten the distance from the rudder surface 21 and make it easier to drive; it is realized through the electrical conduction between the first electrical connector 31 and the second electrical connector 32. The electrical connection between the main control circuit and the driving part of the steering surface can ensure the orderliness of the circuit and the stability of the signal.
进一步的，舵面驱动部为舵机4和传动部件(图中未示出)。舵机4通过可拆主翼部2内埋设的引线连接第二电性连接件32，引线埋设可保证引线不凌乱，也起到保护作用。传动部件的一端连接舵机4的输出轴，传动部件的另一端连接舵面21。传动部件可以是短距离传动，例如可以是摇臂，在舵机4输出轴的转动下摇臂绕轴发生摆动，从而带动舵面21相应动作。Further, the steering surface driving part is the steering gear 4 and transmission components (not shown in the figure). The steering gear 4 is connected to the second electrical connector 32 through the lead wire embedded in the detachable main wing part 2. The lead wire embedding can ensure that the lead wire is not messy and also plays a protective role. One end of the transmission component is connected to the output shaft of the steering gear 4 , and the other end of the transmission component is connected to the steering surface 21 . The transmission part can be a short-distance transmission, for example, it can be a rocker arm. When the output shaft of the steering gear 4 rotates, the rocker arm swings around the axis, thereby driving the steering surface 21 to move accordingly.
在一个实施例中，参看图1，连接结构可以包括带有相互配合的扣位的电性公座连接器和电性母座连接器，电性公座连接器和电性母座连接器的其中一个设于机身主体1上，另一个设于可拆主翼部2上，电性公座连接器和电性母座连接器对位扣接的同时实现电性插接。在图1中，电性公座连接器设于机身主体1上，电性母座连接器设于可拆主翼部2上，当然也可以调换。电性公座连接器和电性母座连接器可以是在现有的公座连接器和母座连接器上设置相应配合的扣位结构，来同时实现电性连接与扣接固定。In one embodiment, referring to FIG. 1, the connection structure may include an electrical male connector and an electrical female connector with mutually mating buckles, and the electrical male connector and the electrical female connector One of them is arranged on the main body 1 of the fuselage, and the other is arranged on the detachable main wing part 2, and the electrical male connector and the electrical female connector are aligned and buckled together to achieve electrical insertion. In FIG. 1 , the electrical male connector is arranged on the fuselage main body 1 , and the electrical female connector is arranged on the detachable main wing part 2 , which of course can also be exchanged. The electrical male connector and the electrical female connector can be provided with corresponding matching buckle structures on the existing male connector and female connector, so as to simultaneously realize electrical connection and buckle fixation.
在一个实施例中，继续参看图1，无人飞行器主翼可拆结构还包括主翼加强杆5。主翼加强杆5的部分插设固定于可拆主翼部2，主翼加强杆5的另一部分用于对接时插入机身主体1内。主翼加强杆5可以对可拆主翼部2本身起到结构加强的作用，使得其不易被折断，另外可拆主翼部2与机身主体1的连接部位为更易断裂的部位，主翼加强杆5可以对此部位进行结构加强，还可起到定位作用。In one embodiment, referring to FIG. 1 , the main wing detachable structure of the unmanned aerial vehicle further includes a main wing stiffener 5 . Part of the main wing reinforcing rod 5 is inserted and fixed to the detachable main wing part 2 , and the other part of the main wing reinforcing rod 5 is inserted into the fuselage main body 1 during docking. The main wing reinforcing rod 5 can play a structural strengthening effect on the detachable main wing part 2 itself, so that it is not easy to be broken. In addition, the connecting part of the detachable main wing part 2 and the fuselage body 1 is a part that is more likely to break, and the main wing reinforcing rod 5 can be Strengthening the structure of this part can also play a positioning role.
在一个实施例中，参看图3，无人飞行器主翼可拆结构还可以包括机身加强杆6。机身加强杆6内设于机身主体1内，与两侧的主翼加强杆5对接。机身加强杆6可以对机身主体1结构起到加强的作用，使其更牢固。In one embodiment, referring to FIG. 3 , the detachable structure of the main wing of the unmanned aerial vehicle may further include fuselage stiffeners 6 . The fuselage reinforcing rod 6 is arranged inside the fuselage main body 1 and is connected with the main wing reinforcing rods 5 on both sides. Fuselage reinforcement rod 6 can strengthen the structure of fuselage main body 1, making it firmer.
优选的，机身加强杆6呈管状结构，且机身加强杆6的口径大于主翼加强杆5的外径，主翼加强杆5对接时插入至机身加强杆6内。主翼加强杆5可以内伸到机身加强杆6中，使得两者配合成为一个受力整体，在主翼加强杆5受到力时，可以传递给机身加强杆6，从而连接部位更不易折断，主翼加强杆5也不易翘开。Preferably, the fuselage stiffener 6 has a tubular structure, and the diameter of the fuselage stiffener 6 is larger than the outer diameter of the main wing stiffener 5, and the main wing stiffener 5 is inserted into the fuselage stiffener 6 when docked. The main wing reinforcing rod 5 can extend into the fuselage reinforcing rod 6, so that the two cooperate to form a stressed whole. When the main wing reinforcing rod 5 is stressed, it can be transmitted to the fuselage reinforcing rod 6, so that the connecting part is more difficult to break. The main wing reinforcing bar 5 is not easy to warp open either.
优选的，继续参看图3，机身加强杆6与机身主体1内的电池仓框架7固连，且机身主体1内设有用于穿设机身加强杆6的通道结构101。电池仓框架7内可以用来容置电池结构。电池仓框架7与机身加强杆6连接，可以使得电池仓框架7的作用力分担至机身加强杆6上，避免飞行器受外力碰撞时，导致电池仓框架7惯性冲击而容易击穿或损坏机身主体1的问题；而设置通道结构101，则可以增加机身主体1与机身加强杆6之间的接触面积，使得两者之间的相对关系更稳定。Preferably, continuing to refer to FIG. 3 , the fuselage reinforcement bar 6 is fixedly connected to the battery compartment frame 7 in the fuselage main body 1 , and the fuselage main body 1 is provided with a channel structure 101 for passing through the fuselage reinforcement bar 6 . The battery compartment frame 7 can be used to accommodate the battery structure. The battery compartment frame 7 is connected to the fuselage reinforcing bar 6, so that the force of the battery compartment frame 7 can be shared with the fuselage reinforcing bar 6, so as to prevent the battery compartment frame 7 from being easily broken down or damaged when the aircraft is hit by an external force. The problem of the fuselage main body 1; and setting the channel structure 101 can increase the contact area between the fuselage main body 1 and the fuselage stiffener 6, making the relative relationship between the two more stable.
主翼加强杆5、机身加强杆6可以为玻璃纤维、塑胶、或碳纤维等部材，更轻质且结构牢固。主翼加强杆5、机身加强杆6优选呈圆杆状，可以承受更大剪切力，各个方向上均不易折断或扭断。The main wing stiffener 5 and the fuselage stiffener 6 can be made of glass fiber, plastic, or carbon fiber, which are lighter in weight and firm in structure. The main wing reinforcing rod 5 and the fuselage reinforcing rod 6 are preferably in the shape of round rods, which can withstand greater shear force and are not easy to break or twist in all directions.
机身主体1和可拆主翼部2均为泡沫塑料部材。泡沫塑料可以为EPO(由聚烯烃和乙烯基芳族单体互聚物树脂颗粒发泡而成)泡沫塑料，也可以是EPS(发泡聚苯乙烯)、EPP(Expanded polyproplene，聚丙烯发泡材料)等其他发泡材料。Both the fuselage main body 1 and the detachable main wings 2 are foamed plastic parts. Foam can be EPO (foamed from polyolefin and vinyl aromatic monomer interpolymer resin particles) foam, or EPS (expanded polystyrene), EPP (Expanded polyproplene, polypropylene foam) material) and other foaming materials.
在一个实施例中，机身1包括连接固定的上机身11和下机身12。在加工时，上机身11和下机身12之间可以是分体制成，而后在装配时，将部件安装到上机身11和下机身12之间之后，上机身11和下机身12再连接固定起来，连接固定方式可以是粘接或其他。In one embodiment, the fuselage 1 includes an upper fuselage 11 and a lower fuselage 12 that are connected and fixed. During processing, the upper fuselage 11 and the lower fuselage 12 can be made in separate parts, and then when assembling, after the parts are installed between the upper fuselage 11 and the lower fuselage 12, the upper fuselage 11 and the lower fuselage Body 12 is connected and fixed again, and the connection and fixing method can be bonding or other.
本实用新型虽然以较佳实施例公开如上，但其并不是用来限定权利要求，任何本领域技术人员在不脱离本实用新型的精神和范围内，都可以做出可能的变动和修改，因此本实用新型的保护范围应当以本实用新型权利要求所界定的范围为准。Although the utility model is disclosed as above with preferred embodiments, it is not used to limit the claims, and any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the utility model, therefore The scope of protection of the utility model shall be defined by the claims of the utility model.
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| CN201720714057.7U CN206984351U (en) | 2017-06-19 | 2017-06-19 | Unmanned vehicle main wing removable structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108657414A (en) * | 2018-05-15 | 2018-10-16 | 北京航空航天大学 | A kind of attachment device and the connection method of unmanned plane central wing, outer wing and shoe |
| CN111434579A (en) * | 2019-01-11 | 2020-07-21 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle tail boom quick assembly disassembly structure |
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2017
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108657414A (en) * | 2018-05-15 | 2018-10-16 | 北京航空航天大学 | A kind of attachment device and the connection method of unmanned plane central wing, outer wing and shoe |
| CN111434579A (en) * | 2019-01-11 | 2020-07-21 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle tail boom quick assembly disassembly structure |
| CN111434579B (en) * | 2019-01-11 | 2022-09-09 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle tail-stay quick assembly disassembly structure |
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