技术领域Technical Field
本发明涉及飞行器技术领域，更具体地说，涉及一种机翼可整体变角度旋转折叠机构。The present invention relates to the technical field of aircraft, and more particularly to a folding mechanism capable of rotating and folding wings at variable angles as a whole.
此外，本发明还涉及一种包括上述机翼可整体变角度旋转折叠机构的飞行器。In addition, the present invention also relates to an aircraft comprising the above-mentioned wing integrally variable angle rotating and folding mechanism.
背景技术Background Art
小型无人机可挂在大型无人机上进行高空投放，满足多种作战场景任务需求。为了在大型无人机上尽可能多地挂载小型无人机，需要将小型无人机的机翼设计为可折叠式的，在挂载时可减少所占空间。当搭载小型无人机的大型无人机到达指定空域后，投放下小型无人机，小型无人机的机翼通过折叠机构展开，执行飞行任务。Small drones can be mounted on large drones for high-altitude drop, meeting the mission requirements of various combat scenarios. In order to mount as many small drones as possible on large drones, the wings of small drones need to be designed to be foldable, which can reduce the space occupied when mounted. When the large drone carrying the small drone arrives at the designated airspace, the small drone is dropped, and the wings of the small drone are unfolded through the folding mechanism to perform the flight mission.
现有技术中有很多都涉及到了机翼折叠机构，按照机翼展开时的驱动力可分为电机驱动式和弹簧驱动式的；对于弹簧驱动式的折叠机构，当无人机长时间储存时，折叠机构内的弹簧会由于长时间受力而容易发生永久变形，从而影响机翼折叠机构的可靠性，所以电机驱动式的折叠机构更加稳定可靠。Many existing technologies involve wing folding mechanisms, which can be divided into motor-driven and spring-driven types according to the driving force when the wings are unfolded. For the spring-driven folding mechanism, when the drone is stored for a long time, the spring in the folding mechanism will easily undergo permanent deformation due to long-term stress, thereby affecting the reliability of the wing folding mechanism. Therefore, the motor-driven folding mechanism is more stable and reliable.
在现有的电机驱动式机翼折叠机构中，按照机翼折叠后的状态可以分为平行式和层叠式。层叠式机翼折叠机构在机翼折叠后所占空间较大，且在展开过程中机翼不对称，影响飞机的稳定性。但是现有的电机驱动的平行式机翼折叠机构均未考虑机翼展开后的上反角，均是简单的展开折叠。In the existing motor-driven wing folding mechanisms, they can be divided into parallel type and stacked type according to the state of the wing after folding. The stacked wing folding mechanism occupies a large space after the wing is folded, and the wing is asymmetrical during the unfolding process, which affects the stability of the aircraft. However, the existing motor-driven parallel wing folding mechanisms do not consider the dihedral angle after the wing is unfolded, and all are simple unfolding and folding.
综上所述，如何解决机翼展开时机翼不具有上反角和机翼折叠后占用空间较大，是目前本领域技术人员亟待解决的问题。In summary, how to solve the problem that the wing has no dihedral angle when the wing is unfolded and the wing occupies a large space after being folded is a problem that needs to be solved urgently by those skilled in the art.
发明内容Summary of the invention
有鉴于此，本发明的目的是提供一种机翼可整体变角度旋转折叠机构，通过对传动齿轮的重新设计，并改变传动齿轮与被动齿轮轴线夹角，从而使机翼在展开时，能够自动翻转，获得上反角，且在折叠时自动回平，收纳不受上反角影响，减少空间占用，且整体结构简单、重量轻、运行稳定可靠。In view of this, the purpose of the present invention is to provide a wing that can rotate and fold at an overall variable angle. By redesigning the transmission gear and changing the angle between the transmission gear and the axis of the passive gear, the wing can automatically flip over when unfolded to obtain an upward angle, and automatically return to flat when folded. The storage is not affected by the upward angle, which reduces space occupancy. The overall structure is simple, the weight is light, and the operation is stable and reliable.
本发明的另一目的是提供一种包括上述机翼可整体变角度旋转折叠机构的飞行器，具有相同的技术特征，能够解决相同的技术问题。Another object of the present invention is to provide an aircraft including the above-mentioned wing integrally variable angle rotation and folding mechanism, which has the same technical features and can solve the same technical problems.
为了实现上述目的，本发明提供如下技术方案：In order to achieve the above object, the present invention provides the following technical solutions:
一种机翼可整体变角度旋转折叠机构，包括：A wing folding mechanism capable of rotating and folding at a variable angle as a whole, comprising:
舵机齿轮，其与驱动电机动力连接，用于提供动力输入；A steering gear, which is connected to the driving motor power to provide power input;
传动齿轮，其外周设置锥齿部和直齿部，所述传动齿轮的直齿部与所述舵机齿轮啮合，且所述传动齿轮的轴线与所述舵机齿轮的轴线平行；A transmission gear, the outer periphery of which is provided with a bevel gear portion and a spur gear portion, the spur gear portion of the transmission gear is meshed with the steering gear, and the axis of the transmission gear is parallel to the axis of the steering gear;
被动齿轮，其为锥齿轮，与机翼固定连接，所述被动齿轮与所述传动齿轮的锥齿部啮合，且所述被动齿轮的轴线与所述传动齿轮的轴线共面且夹角为α，0°＜α≤30°。The passive gear is a bevel gear, fixedly connected to the wing, the passive gear meshes with the bevel gear portion of the transmission gear, and the axis of the passive gear is coplanar with the axis of the transmission gear and the included angle is α, 0°＜α≤30°.
优选的，所述传动齿轮包括左传动齿轮和右传动齿轮；Preferably, the transmission gear includes a left transmission gear and a right transmission gear;
所述左传动齿轮的直齿部与所述右传动齿轮的直齿部啮合，所述左传动齿轮的直齿部或所述右传动齿轮的直齿部与所述舵机齿轮啮合。The spur tooth portion of the left transmission gear meshes with the spur tooth portion of the right transmission gear, and the spur tooth portion of the left transmission gear or the spur tooth portion of the right transmission gear meshes with the steering gear.
优选的，所述被动齿轮包括左被动齿轮和右被动齿轮；Preferably, the passive gear comprises a left passive gear and a right passive gear;
所述左被动齿轮与左机翼固定连接，且所述左被动齿轮与所述左传动齿轮的锥齿部啮合；The left passive gear is fixedly connected to the left wing, and the left passive gear is meshed with the bevel gear portion of the left transmission gear;
所述右被动齿轮与右机翼固定连接，且所述右被动齿轮与所述右传动齿轮的锥齿部啮合。The right passive gear is fixedly connected to the right wing, and the right passive gear is meshed with the bevel gear portion of the right transmission gear.
优选的，所述左被动齿轮与复合材料蜂窝芯结构的所述左机翼整体固化成型；Preferably, the left passive gear and the left wing of the composite honeycomb core structure are integrally solidified and formed;
所述右被动齿轮与复合材料蜂窝芯结构的所述右机翼整体固化成型。The right passive gear and the right wing of the composite honeycomb core structure are integrally solidified and formed.
优选的，所述传动齿轮内的直齿部与锥齿部相接位置处设置有过渡轮齿。Preferably, transition gear teeth are provided at the junction of the spur gear portion and the bevel gear portion in the transmission gear.
优选的，还包括限位架，与外置的机身相对固定连接，当所述机翼向外旋转至设定角度后，所述限位架能够与所述机翼侧壁抵接，以限制所述机翼继续旋转。Preferably, it also includes a limit frame, which is relatively fixedly connected to the external fuselage. When the wing is rotated outward to a set angle, the limit frame can abut against the side wall of the wing to limit the wing from continuing to rotate.
优选的，还包括锁定销，所述锁定销沿自身轴线与机身相对滑动安装，且所述锁定销与所述机身之间设置有提供动力的弹簧；Preferably, it further comprises a locking pin, wherein the locking pin is slidably mounted relative to the fuselage along its own axis, and a spring for providing power is arranged between the locking pin and the fuselage;
当所述机翼向外旋转至设定角度后，所述锁定销能够插入所述机翼内的锁定销孔，以限制所述机翼旋转。When the wing is rotated outward to a set angle, the locking pin can be inserted into the locking pin hole in the wing to limit the rotation of the wing.
优选的，还包括保持架，所述保持架与机身的机翼安装口盖固定连接，所述舵机齿轮、所述传动齿轮、所述被动齿轮和所述机翼均通过安装组件安装在所述保持架与所述机翼安装口盖之间。Preferably, it also includes a retaining frame, which is fixedly connected to the wing mounting cover of the fuselage, and the servo gear, the transmission gear, the driven gear and the wing are all installed between the retaining frame and the wing mounting cover through a mounting assembly.
优选的，所述安装组件包括螺栓和直衬套，所述直衬套固定套装在所述舵机齿轮、所述传动齿轮和/或所述被动齿轮的轴线孔处，所述直衬套的两端同轴设置有轴肩衬套，且一端的轴肩衬套套装在所述保持架的通孔内，所述螺栓贯穿所述直衬套和轴肩衬套的组合体，且所述螺栓的端部设置有锁紧螺母。Preferably, the mounting assembly includes a bolt and a straight bushing, the straight bushing is fixedly sleeved on the axial hole of the servo gear, the transmission gear and/or the passive gear, shoulder bushings are coaxially arranged at both ends of the straight bushing, and the shoulder bushing at one end is sleeved in the through hole of the retaining frame, the bolt passes through the combination of the straight bushing and the shoulder bushing, and a locking nut is arranged at the end of the bolt.
一种飞行器，包括上述任意一项所述的机翼可整体变角度旋转折叠机构。An aircraft comprises any one of the above-mentioned wing folding mechanisms capable of rotating and folding at variable angles as a whole.
本发明提供的机翼可整体变角度旋转折叠机构，与现有技术相比，至少具有如下有益效果：The wing integrally variable angle rotation and folding mechanism provided by the present invention has at least the following beneficial effects compared with the prior art:
1、采用传动齿轮内增加锥齿部与锥齿轮形式的被动齿轮啮合传动，从而使与被动齿轮固定的机翼在展开时，机翼自身也能发生转动，从而获得上反角，以提升机翼迎风所产生的升力；且当机翼折叠时，机翼自身能反向转动，恢复至水平，进而减小折叠后的空间占用；1. The bevel gear part is added to the transmission gear and meshed with the passive gear in the form of a bevel gear, so that when the wing fixed to the passive gear is unfolded, the wing itself can also rotate, thereby obtaining an upward angle to enhance the lift generated by the wing facing the wind; and when the wing is folded, the wing itself can rotate in the opposite direction and return to the horizontal state, thereby reducing the space occupied after folding;
2、传动齿轮采用直齿部和锥齿部结合的方式，其中直齿部用于与舵机齿轮啮合传动，或用于与其他传动齿轮啮合传动，以保证多个机翼能够同步旋转，以保证飞机的两侧升力均衡；2. The transmission gear adopts a combination of spur gear and bevel gear. The spur gear is used to mesh with the steering gear or other transmission gears to ensure that multiple wings can rotate synchronously to ensure balanced lift on both sides of the aircraft.
3、传动齿轮代替了直齿轮和锥齿轮同轴布置的组合体，有助于降低设备的重量，进而降低飞机整体的重量；同时采用齿轮进行传动，具有传动效率高、能耗损失小、传动路径简单和运行稳定可靠的优点。3. The transmission gear replaces the coaxial combination of spur gears and bevel gears, which helps to reduce the weight of the equipment and thus reduce the overall weight of the aircraft. At the same time, the use of gears for transmission has the advantages of high transmission efficiency, low energy loss, simple transmission path and stable and reliable operation.
本发明提供的飞行器，包括上述的机翼可整体变角度旋转折叠机构，具有相同的有益效果。The aircraft provided by the present invention includes the above-mentioned wing integrally variable angle rotation and folding mechanism, and has the same beneficial effects.
附图说明BRIEF DESCRIPTION OF THE DRAWINGS
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据提供的附图获得其他的附图。In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.
图1为本发明所提供机翼可整体变角度旋转折叠机构的结构示意图；FIG1 is a schematic diagram of the structure of a wing folding mechanism capable of rotating and folding at an integrally variable angle provided by the present invention;
图2为本发明所提供机翼可整体变角度旋转折叠机构底部的结构示意图；FIG2 is a schematic structural diagram of the bottom portion of the wing folding mechanism capable of rotating and folding at an integrally variable angle provided by the present invention;
图3为本发明所提供机翼可整体变角度旋转折叠机构的俯视图；FIG3 is a top view of the wing folding mechanism that can rotate and fold at an integrally variable angle provided by the present invention;
图4为本发明所提供机翼可整体变角度旋转折叠机构的端部示意图；FIG4 is a schematic diagram of the end portion of the wing folding mechanism that can rotate and fold at an integrally variable angle provided by the present invention;
图5为本发明所提供图3中A-A处的剖视图；Fig. 5 is a cross-sectional view of the A-A portion of Fig. 3 provided by the present invention;
图6为本发明所提供图4中B-B处的剖视图；Fig. 6 is a cross-sectional view of the B-B portion of Fig. 4 provided by the present invention;
图7为本发明所提供机翼可整体变角度旋转折叠机构底部的零件爆炸图。FIG. 7 is an exploded view of the parts at the bottom of the wing's overall variable angle rotation and folding mechanism provided by the present invention.
图1-图7中：In Figures 1 to 7:
1、舵机齿轮；2、传动齿轮；201、左传动齿轮；202、右传动齿轮；3、被动齿轮；301、左被动齿轮；302、右被动齿轮；4、锁定销；5、弹簧；6、锁定销孔；7、左机翼；8、右机翼；9、机翼安装口盖；10、限位架；11、保持架；12、直衬套；13、轴肩衬套。1. Servo gear; 2. Transmission gear; 201, left transmission gear; 202, right transmission gear; 3. Passive gear; 301, left passive gear; 302, right passive gear; 4. Locking pin; 5. Spring; 6. Locking pin hole; 7. Left wing; 8. Right wing; 9. Wing mounting cover; 10. Limiting frame; 11. Retaining frame; 12. Straight bushing; 13. Shoulder bushing.
具体实施方式DETAILED DESCRIPTION
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.
本发明的核心是提供一种机翼可整体变角度旋转折叠机构，通过对传动齿轮的重新设计，并改变传动齿轮与被动齿轮轴线夹角，从而使机翼在展开时，能够自动翻转，获得上反角，且在折叠时自动回平，收纳不受上反角影响，减少空间占用，且整体结构简单、重量轻、运行稳定可靠。The core of the present invention is to provide a wing that can rotate and fold at an overall variable angle. By redesigning the transmission gear and changing the angle between the transmission gear and the axis of the passive gear, the wing can automatically flip over when unfolded to obtain an upward angle, and automatically return to flat when folded. The storage is not affected by the upward angle, reducing space occupancy, and the overall structure is simple, light in weight, and stable and reliable in operation.
本发明的另一核心是提供一种包括上述机翼可整体变角度旋转折叠机构的飞行器，具有相同的技术特征，能够解决相同的技术问题。Another core of the present invention is to provide an aircraft including the above-mentioned wing integrally variable angle rotation and folding mechanism, which has the same technical features and can solve the same technical problems.
请参考图1-图7，一种机翼可整体变角度旋转折叠机构，包括：Please refer to Figures 1 to 7, a wing folding mechanism that can rotate and fold at a variable angle as a whole, including:
舵机齿轮1，其与驱动电机动力连接，用于提供动力输入；The steering gear 1 is connected to the driving motor for providing power input;
传动齿轮2，其外周设置锥齿部和直齿部，传动齿轮2的直齿部与舵机齿轮1啮合，且传动齿轮2的轴线与舵机齿轮1的轴线平行；The transmission gear 2 has a bevel gear portion and a spur gear portion on its outer periphery, the spur gear portion of the transmission gear 2 meshes with the steering gear 1, and the axis of the transmission gear 2 is parallel to the axis of the steering gear 1;
被动齿轮3，其为锥齿轮，与机翼固定连接，被动齿轮3与传动齿轮2的锥齿部啮合，且被动齿轮3的轴线与传动齿轮2的轴线共面且夹角为α，0°＜α≤30°；The passive gear 3 is a bevel gear, fixedly connected to the wing, the passive gear 3 meshes with the bevel gear portion of the transmission gear 2, and the axis of the passive gear 3 is coplanar with the axis of the transmission gear 2 and the included angle is α, 0°＜α≤30°;
如图1和图5所示，传动齿轮2内的外周设置直齿部和锥齿部，直齿部与舵机齿轮1啮合，保证传动齿轮2与舵机齿轮1之间动力传输平稳，也可用于多组传动齿轮2之间的相互啮合，保证多组机翼的同步展开或折叠，保证无人机的多组机翼受力均衡，从而保证无人机的飞行稳定；As shown in FIG. 1 and FIG. 5 , a spur gear portion and a bevel gear portion are arranged on the outer periphery of the transmission gear 2, and the spur gear portion meshes with the steering gear 1 to ensure smooth power transmission between the transmission gear 2 and the steering gear 1, and can also be used for mutual meshing between multiple sets of transmission gears 2 to ensure the synchronous unfolding or folding of multiple sets of wings, and ensure that the multiple sets of wings of the UAV are subjected to balanced forces, thereby ensuring the flight stability of the UAV;
而锥齿部与被动齿轮3啮合，且保证被动齿轮3与传动齿轮2的轴线之间存在夹角α，从而使被动齿轮3与传动齿轮2之间组成锥齿轮副，进而使机翼在向外展开时，机翼自身能够发生转动，从而产生上反角，而机翼在折叠时，机翼自身能够反向转动，从而使机翼恢复水平，减少折叠后的空间占用，且整个旋转折叠机构采用齿轮传动，传动效率较高，且运行稳定可靠，适合无人机的折叠机翼使用，同时整个旋转折叠机构的结构简单，便于组装；The bevel gear part meshes with the passive gear 3, and ensures that there is an angle α between the axes of the passive gear 3 and the transmission gear 2, so that a bevel gear pair is formed between the passive gear 3 and the transmission gear 2, so that when the wing is unfolded, the wing itself can rotate, thereby generating an upward dihedral angle, and when the wing is folded, the wing itself can rotate in the opposite direction, so that the wing is restored to a horizontal level, reducing the space occupied after folding, and the entire rotary folding mechanism adopts gear transmission, with high transmission efficiency and stable and reliable operation, which is suitable for the use of folding wings of drones, and the entire rotary folding mechanism has a simple structure and is easy to assemble;
而且传动齿轮2采用一组齿轮外部同时集成直齿部和锥齿部，有助于降低传动齿轮2的厚度和重量，进而减小旋转折叠机构的空间占用和降低无人机的起飞重量；Moreover, the transmission gear 2 adopts a set of gears with both straight teeth and bevel teeth integrated on the outside, which helps to reduce the thickness and weight of the transmission gear 2, thereby reducing the space occupied by the rotating folding mechanism and reducing the take-off weight of the UAV;
在有些实施例中，采用同轴固定安装的直齿轮和锥齿轮组合体代替传动齿轮2，尽管其重量有所增加，但其结构简单，传动效率高，运行稳定可靠，同样属于本申请的保护范围；In some embodiments, a coaxially fixed spur gear and bevel gear assembly is used to replace the transmission gear 2. Although its weight is increased, it has a simple structure, high transmission efficiency, stable and reliable operation, and also belongs to the protection scope of this application;
在有些实施例中，取消了舵机齿轮1，采用外置的驱动电机直接驱动传动齿轮2，进而驱动被动齿轮3，带动机翼进行折叠和展开，同样属于本申请的保护范围。In some embodiments, the servo gear 1 is eliminated, and an external drive motor is used to directly drive the transmission gear 2, and then drive the passive gear 3, so as to drive the wings to fold and unfold, which also falls within the protection scope of the present application.
在一些实施例中，传动齿轮2包括左传动齿轮201和右传动齿轮202；In some embodiments, the transmission gear 2 includes a left transmission gear 201 and a right transmission gear 202;
左传动齿轮201的直齿部与右传动齿轮202的直齿部啮合，左传动齿轮201的直齿部或右传动齿轮202的直齿部与舵机齿轮1啮合；The spur gear portion of the left transmission gear 201 meshes with the spur gear portion of the right transmission gear 202, and the spur gear portion of the left transmission gear 201 or the spur gear portion of the right transmission gear 202 meshes with the steering gear 1;
如图3所示，采用两组传动齿轮2的直齿部相互啮合的方式进行传动，保证两组传动齿轮2的运动同步，进而保证两侧的机翼展开或折叠同步；且采用其中一组传动齿轮2的直齿部与舵机齿轮1啮合传动，使整体传力路径合理，进而保证整体的运行稳定可靠。As shown in FIG3 , the transmission is performed by meshing the spur teeth of the two sets of transmission gears 2 with each other, thereby ensuring the synchronization of the movement of the two sets of transmission gears 2, and thereby ensuring the synchronization of the unfolding or folding of the wings on both sides; and the spur teeth of one set of transmission gears 2 are meshed with the steering gear 1 for transmission, so that the overall force transmission path is reasonable, thereby ensuring the overall stable and reliable operation.
在一些实施例中，被动齿轮3包括左被动齿轮301和右被动齿轮302；In some embodiments, the passive gear 3 includes a left passive gear 301 and a right passive gear 302;
左被动齿轮301与左机翼7固定连接，且左被动齿轮301与左传动齿轮201的锥齿部啮合；The left passive gear 301 is fixedly connected to the left wing 7, and the left passive gear 301 is meshed with the bevel gear portion of the left transmission gear 201;
右被动齿轮302与右机翼8固定连接，且右被动齿轮302与右传动齿轮202的锥齿部啮合；The right passive gear 302 is fixedly connected to the right wing 8, and the right passive gear 302 is meshed with the bevel gear portion of the right transmission gear 202;
如图1、图3、图4和图7所示，采用机身两侧分别设置机翼的方式，其采用左被动齿轮301带动左机翼7，右被动齿轮302带动右机翼8，具体传动路线包括：As shown in FIG. 1 , FIG. 3 , FIG. 4 and FIG. 7 , the wings are respectively arranged on both sides of the fuselage, and the left passive gear 301 drives the left wing 7, and the right passive gear 302 drives the right wing 8. The specific transmission route includes:
第一条传动路线，舵机齿轮1带动左传动齿轮201，左传动齿轮201带动左被动齿轮301，左被动齿轮301带动左机翼7；In the first transmission route, the steering gear 1 drives the left transmission gear 201, the left transmission gear 201 drives the left passive gear 301, and the left passive gear 301 drives the left wing 7;
第二条传动路线，舵机齿轮1带动左传动齿轮201，左传动齿轮201带动右传动齿轮202，右传动齿轮202带动右被动齿轮302，右被动齿轮302带动右机翼8。In the second transmission route, the steering gear 1 drives the left transmission gear 201 , the left transmission gear 201 drives the right transmission gear 202 , the right transmission gear 202 drives the right passive gear 302 , and the right passive gear 302 drives the right wing 8 .
通过两条传动路线带动左机翼7和右机翼8同步旋转，进而保证两侧的机翼能够同步展开和折叠，且两侧机翼具有相同的上反角，进而保证机身两侧机翼的上升力相等。The left wing 7 and the right wing 8 are driven to rotate synchronously through two transmission routes, thereby ensuring that the wings on both sides can be unfolded and folded synchronously, and the wings on both sides have the same dihedral angle, thereby ensuring that the lift forces of the wings on both sides of the fuselage are equal.
在一些实施例中，左被动齿轮301与复合材料蜂窝芯结构的左机翼7整体固化成型；In some embodiments, the left passive gear 301 and the left wing 7 of the composite honeycomb core structure are integrally cured and formed;
右被动齿轮302与复合材料蜂窝芯结构的右机翼8整体固化成型；The right passive gear 302 and the right wing 8 of the composite honeycomb core structure are integrally solidified and formed;
如图1、图3和图7所示，被动齿轮3优选为具有14个锥轮齿的金属结构，且与复合材料蜂窝芯结构的机翼整体固化成型，有助于提升旋转折叠结构与机翼的一体性，且降低无人机的整体重量；As shown in FIG. 1 , FIG. 3 and FIG. 7 , the passive gear 3 is preferably a metal structure having 14 bevel gear teeth, and is integrally solidified and formed with the wing of the composite honeycomb core structure, which helps to improve the integrity of the rotating folding structure and the wing and reduce the overall weight of the drone;
在一些实施例中，传动齿轮2内的直齿部与锥齿部相接位置处设置有过渡轮齿；In some embodiments, a transition gear tooth is provided at the junction of the spur gear portion and the bevel gear portion in the transmission gear 2;
传动齿轮2优选为具有38个轮齿，其中，26个轮齿为直轮齿，组成直齿部；10个轮齿为锥轮齿，组成锥齿部；2个轮齿为过渡轮齿，设置在直齿部与锥齿部的相接位置处，通过增加过渡轮齿，有助于降低打齿的几率。The transmission gear 2 preferably has 38 gear teeth, of which 26 gear teeth are spur gear teeth forming a spur gear portion; 10 gear teeth are bevel gear teeth forming a bevel gear portion; and 2 gear teeth are transition gear teeth, which are arranged at the junction of the spur gear portion and the bevel gear portion. By adding transition gear teeth, the probability of tooth playing is reduced.
在一些实施例中，还包括限位架10，与外置的机身相对固定连接，当机翼向外旋转至设定角度后，限位架10能够与机翼侧壁抵接，以限制机翼继续旋转；In some embodiments, a limit frame 10 is further included, which is relatively fixedly connected to the external fuselage. When the wing rotates outward to a set angle, the limit frame 10 can abut against the side wall of the wing to limit the wing from continuing to rotate;
如图1所示，在机身内增加限位架10，当机翼展开至设定角度后，机翼侧边缘位置与限位架10抵接，从而限制了机翼的继续转动，从而避免了被动齿轮3与传动齿轮2的直齿部啮合造成的打齿问题。As shown in FIG1 , a limit frame 10 is added inside the fuselage. When the wing is unfolded to a set angle, the side edge of the wing abuts against the limit frame 10, thereby limiting the continued rotation of the wing, thereby avoiding the problem of tooth hitting caused by the meshing of the straight teeth of the driven gear 3 and the transmission gear 2.
在一些实施例中，还包括锁定销4，锁定销4沿自身轴线与机身相对滑动安装，且锁定销4与机身之间设置有提供动力的弹簧5；In some embodiments, it also includes a locking pin 4, which is installed to slide relative to the fuselage along its own axis, and a spring 5 providing power is provided between the locking pin 4 and the fuselage;
当机翼向外旋转至设定角度后，锁定销4能够插入机翼内的锁定销孔6，以限制机翼旋转；When the wing rotates outward to a set angle, the locking pin 4 can be inserted into the locking pin hole 6 in the wing to limit the rotation of the wing;
通过在机身内设置锁定销4，并采用弹簧5进行锁定销4的驱动，锁定销4的轴线应垂直于机翼旋转所扫略的平面；当机翼处于未完全展开或折叠的状态下，锁定销4的顶部与机翼表面抵接，从而使弹簧5处于被压缩的状态，当机翼旋转至完全展开状态时，机翼表面的锁定销孔6与锁定销4的轴向投影重叠，锁定销4在弹簧5的驱动下，发生轴向位移插入锁定销孔6内，进而限制机翼继续转动，即对机翼进行锁定，使机翼不能继续展开或折叠；By arranging a locking pin 4 in the fuselage and using a spring 5 to drive the locking pin 4, the axis of the locking pin 4 should be perpendicular to the plane swept by the rotation of the wing; when the wing is in a state of not being fully unfolded or folded, the top of the locking pin 4 abuts against the surface of the wing, so that the spring 5 is in a compressed state, and when the wing rotates to a fully unfolded state, the locking pin hole 6 on the surface of the wing overlaps with the axial projection of the locking pin 4, and the locking pin 4 is driven by the spring 5 to undergo axial displacement and be inserted into the locking pin hole 6, thereby restricting the wing from continuing to rotate, that is, locking the wing so that the wing cannot continue to unfold or fold;
在有些实施例中，如图6所示，在机身下侧设置保持架11，在保持架11内设置贯穿的阶梯孔，使锁定销4贯穿阶梯孔，且弹簧5设置在阶梯孔的大径部分内，当需要使机翼折叠时，手动拉动穿出阶梯孔部分的锁定销4，使锁定销4复位，且弹簧5再次被压缩，此时锁定销4与锁定销孔6脱离，解除对机翼的限制，从而时机翼能够进行折叠。In some embodiments, as shown in FIG6 , a retaining frame 11 is provided on the lower side of the fuselage, and a penetrating stepped hole is provided in the retaining frame 11, so that the locking pin 4 passes through the stepped hole, and the spring 5 is provided in the large diameter portion of the stepped hole. When the wing needs to be folded, the locking pin 4 passing through the stepped hole portion is manually pulled to reset the locking pin 4, and the spring 5 is compressed again. At this time, the locking pin 4 is disengaged from the locking pin hole 6, and the restriction on the wing is released, so that the wing can be folded.
在一些实施例中，还包括保持架11，保持架11与机身的机翼安装口盖9固定连接，舵机齿轮1、传动齿轮2、被动齿轮3和机翼均通过安装组件安装在保持架11与机翼安装口盖9之间；In some embodiments, it also includes a holder 11, the holder 11 is fixedly connected to the wing mounting cover 9 of the fuselage, and the steering gear 1, the transmission gear 2, the driven gear 3 and the wing are all installed between the holder 11 and the wing mounting cover 9 through the mounting assembly;
如图5和图7所示，通过采用保持架11的形式，保证舵机齿轮1、传动齿轮2和被动齿轮3的相对位置稳定，从而保证整个翻转折叠机构内的动力传输稳定。As shown in FIG. 5 and FIG. 7 , by adopting the form of a retaining frame 11 , the relative positions of the steering gear 1 , the transmission gear 2 and the driven gear 3 are ensured to be stable, thereby ensuring stable power transmission in the entire flipping and folding mechanism.
在一些实施例中，安装组件包括螺栓和直衬套12，直衬套12固定套装在舵机齿轮1、传动齿轮2和/或被动齿轮3的轴线孔处，直衬套12的两端同轴设置有轴肩衬套13，且一端的轴肩衬套13套装在保持架11的通孔内，螺栓贯穿直衬套12和轴肩衬套13的组合体，且螺栓的端部设置有锁紧螺母；In some embodiments, the mounting assembly includes a bolt and a straight bushing 12, the straight bushing 12 is fixedly sleeved on the axial hole of the steering gear 1, the transmission gear 2 and/or the passive gear 3, the two ends of the straight bushing 12 are coaxially provided with shoulder bushings 13, and the shoulder bushing 13 at one end is sleeved in the through hole of the retainer 11, the bolt passes through the combination of the straight bushing 12 and the shoulder bushing 13, and the end of the bolt is provided with a locking nut;
如图5所示，通过在舵机齿轮1、传动齿轮2和/或被动齿轮3的轴线孔处设置直衬套12，减少其旋转时与螺柱之间的磨损，通过在直衬套12两端增加轴肩衬套13，且在螺栓端部增加锁紧螺母，从而实现舵机齿轮1、传动齿轮2和被动齿轮3与保持架11的安装，同时其中一组轴肩衬套13贯穿保持架11内的通孔，同样能够减少螺柱与保持架11之间的磨损。As shown in FIG5 , by setting a straight bushing 12 at the axial hole of the servo gear 1, the transmission gear 2 and/or the driven gear 3, the wear between them and the stud during rotation is reduced, and by adding shoulder bushings 13 at both ends of the straight bushing 12 and adding locking nuts at the ends of the bolts, the installation of the servo gear 1, the transmission gear 2 and the driven gear 3 and the retaining frame 11 is achieved. At the same time, one group of shoulder bushings 13 passes through the through hole in the retaining frame 11, which can also reduce the wear between the stud and the retaining frame 11.
除了上述各个实施例所公开的机翼可整体变角度旋转折叠机构以外，本发明还提供一种包括上述机翼可整体变角度旋转折叠机构的飞行器，该飞行器的其他各部分的结构请参考现有技术，本文不再赘述。In addition to the wing overall variable angle rotation and folding mechanism disclosed in the above embodiments, the present invention also provides an aircraft including the above-mentioned wing overall variable angle rotation and folding mechanism. For the structures of other parts of the aircraft, please refer to the prior art and will not be described in detail herein.
本说明书中各个实施例采用递进的方式描述，每个实施例重点说明的都是与其他实施例的不同之处，各个实施例之间相同相似部分互相参见即可。The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.
以上对本发明所提供的机翼可整体变角度旋转折叠机构及飞行器进行了详细介绍。本文中应用了具体个例对本发明的原理及实施方式进行了阐述，以上实施例的说明只是用于帮助理解本发明的方法及其核心思想。应当指出，对于本技术领域的普通技术人员来说，在不脱离本发明原理的前提下，还可以对本发明进行若干改进和修饰，这些改进和修饰也落入本发明权利要求的保护范围内。The above is a detailed introduction to the wing overall variable angle rotation and folding mechanism and the aircraft provided by the present invention. Specific examples are used in this article to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. It should be pointed out that for ordinary technicians in this technical field, without departing from the principle of the present invention, several improvements and modifications can be made to the present invention, and these improvements and modifications also fall within the scope of protection of the claims of the present invention.
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411710072.5ACN119190454B (en) | 2024-11-27 | 2024-11-27 | A wing folding mechanism capable of rotating and folding at an integrally variable angle and an aircraft |
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411710072.5ACN119190454B (en) | 2024-11-27 | 2024-11-27 | A wing folding mechanism capable of rotating and folding at an integrally variable angle and an aircraft |
| Publication Number | Publication Date |
|---|---|
| CN119190454A CN119190454A (en) | 2024-12-27 |
| CN119190454Btrue CN119190454B (en) | 2025-02-07 |
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202411710072.5AActiveCN119190454B (en) | 2024-11-27 | 2024-11-27 | A wing folding mechanism capable of rotating and folding at an integrally variable angle and an aircraft |
| Country | Link |
|---|---|
| CN (1) | CN119190454B (en) |
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