CN219619373U - An aircraft side guide rail with positioning function - Google Patents

An aircraft side guide rail with positioning function Download PDF

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Publication number
CN219619373U
CN219619373U CN202321018684.9U CN202321018684U CN219619373U CN 219619373 U CN219619373 U CN 219619373U CN 202321018684 U CN202321018684 U CN 202321018684U CN 219619373 U CN219619373 U CN 219619373U
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China
Prior art keywords
guide rail
ring
aircraft side
fixedly connected
side guide
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CN202321018684.9U
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江瀚
白金义
吕文
黄飞燕
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Xi'an Dier Aviation Industry Development Co ltd
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Xi'an Dier Aviation Industry Development Co ltd
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    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/40Weight reduction

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Abstract

本实用新型涉及飞机技术领域,尤其为一种具有定位功能的飞机侧导轨,包括:飞机侧导轨本体,所述飞机侧导轨本体的两侧均开设有两个定位槽,所述飞机侧导轨本体的底部开设有两个限位槽,所述限位槽的内腔设置有圆环,所述圆环的表面开设有环形凹槽,所述环形凹槽的内腔设置有两个对称的传动块,两个传动块相背的一侧均固定连接有L形块,所述L形块的顶部固定连接有定位块,所述L形块的两侧均转动连接有连接块。本实用新型具备定位精度高和使用灵活的优点,在实际使用过程中,通过三角定位的方法,能够确保飞机侧导轨定位的稳定性,方便使用者将飞机侧导轨和机侧翼本体进行连接,避免了在安装过程中,出现安装偏差。

The utility model relates to the technical field of aircraft, in particular to an aircraft side guide rail with a positioning function, comprising: an aircraft side guide rail body, two positioning grooves are opened on both sides of the aircraft side guide rail body, and the aircraft side guide rail body There are two limit grooves on the bottom of the limit groove, the inner cavity of the limit groove is provided with a ring, the surface of the ring is provided with an annular groove, and the inner cavity of the annular groove is provided with two symmetrical transmission An L-shaped block is fixedly connected to the opposite side of the two transmission blocks, a positioning block is fixedly connected to the top of the L-shaped block, and a connecting block is rotatably connected to both sides of the L-shaped block. The utility model has the advantages of high positioning accuracy and flexible use. In the actual use process, the triangular positioning method can ensure the stability of the positioning of the aircraft side guide rail, and it is convenient for the user to connect the aircraft side guide rail and the aircraft side wing body to avoid During the installation process, installation deviation occurred.

Description

一种具有定位功能的飞机侧导轨An aircraft side guide rail with positioning function

技术领域technical field

本实用新型涉及飞机技术领域,具体为一种具有定位功能的飞机侧导轨。The utility model relates to the technical field of aircraft, in particular to an aircraft side guide rail with a positioning function.

背景技术Background technique

飞机是指具有一具或多具发动机的动力装置产生前进的推力或拉力,由机身的固定机翼产生升力,在大气层上、中、下飞行的重于空气的航空器,大多数飞机都是由下面六个主要部分组成,即:机翼、机身、尾翼、起落装置、操纵系统和动力装置。它们各有其独特的功用。Aircraft refers to a power plant with one or more engines to generate forward thrust or pull, and the fixed wings of the fuselage to generate lift. Aircraft heavier than air that flies above, in, and below the atmosphere. Most aircraft are It consists of the following six main parts, namely: wing, fuselage, empennage, landing gear, control system and power plant. Each has its own unique function.

如公开号为CN207759070U所公开的一种飞机用侧导轨加强件,通过在飞机侧翼本体外侧设置侧板,然后侧板与侧导轨完成连接,侧导轨在导向轨内的导向道内滑动,在出库过程中,侧导轨受到较大的压力时,通过支撑板上的第一连接块与第二连接块协作,在弹簧与橡胶垫的作用下,能够起到缓冲作用,能够有效防止压力损坏侧导轨,在受到压力时,通过连杆带动滚轮能够在弧形座内左右滚动,协同两侧的第一连接块与第二连接块完成压力的缓冲;整个装置能够加强导向轨与飞机侧翼本体的连接强度,具备缓冲功能,能够有效防止出库过程中导向轨出现损坏,延长导向轨的使用寿命。For example, the publication number is CN207759070U for a side guide rail reinforcement disclosed by an aircraft. By setting a side plate outside the wing body of the aircraft, the side plate and the side guide rail are connected, and the side guide rail slides in the guide rail in the guide rail. During the process, when the side guide rail is subjected to a large pressure, the cooperation between the first connecting block and the second connecting block on the support plate can play a buffering role under the action of the spring and the rubber pad, and can effectively prevent the pressure from damaging the side guide rail. , when under pressure, the connecting rod drives the roller to roll left and right in the arc-shaped seat, and cooperates with the first connecting block and the second connecting block on both sides to complete the pressure buffer; the whole device can strengthen the connection between the guide rail and the wing body of the aircraft Strength, with buffer function, can effectively prevent the damage of the guide rail during the process of leaving the warehouse, and prolong the service life of the guide rail.

其虽然通过第一连接块、第二连接块、弹簧和橡胶垫等零件组成加强件,从而防止出库过程中导向轨出现损坏情况的发生的优点,解决了现有装置导向轨强度不够,易发生损坏的问题。Although the first connecting block, the second connecting block, springs and rubber pads are used to form reinforcements, the advantage of preventing the guide rail from being damaged during the delivery process is to solve the problem that the strength of the guide rail in the existing device is not strong enough, and it is easy to Corruption issues.

在飞机侧导轨在使用时需要与飞机侧翼本体进行连接,现有的市面上大部分飞机用侧导轨以及上述专利均未设置有定位结构,因此在侧导轨与飞机侧翼本体连接时,侧导轨会随着连接的力进行移动,进而使得侧导轨偏离原定轨迹,提高了连接的难度,从而会提高了使用者的工作强度,降低了工作效率。The side guide rail of the aircraft needs to be connected with the wing body of the aircraft during use. Most of the side guide rails for aircraft on the market and the above-mentioned patents are not provided with a positioning structure. Therefore, when the side guide rail is connected to the wing body of the aircraft, the side guide rail will be The movement along with the force of the connection makes the side guide rail deviate from the original track, which increases the difficulty of the connection, thereby increasing the work intensity of the user and reducing the work efficiency.

实用新型内容Utility model content

本实用新型的目的在于提供一种具有定位功能的飞机侧导轨,具备定位效果好和使用灵活的优点,解决了上述背景技术提出的问题。The purpose of this utility model is to provide an aircraft side guide rail with positioning function, which has the advantages of good positioning effect and flexible use, and solves the problems raised by the above-mentioned background technology.

为达成上述目的,本实用新型提供如下技术方案:一种具有定位功能的飞机侧导轨,包括:飞机侧导轨本体,所述飞机侧导轨本体的两侧均开设有两个定位槽,所述飞机侧导轨本体的底部开设有两个限位槽,所述限位槽的内腔设置有圆环,所述圆环的表面开设有环形凹槽,所述环形凹槽的内腔设置有两个对称的传动块,两个传动块相背的一侧均固定连接有L形块,所述L形块的顶部固定连接有定位块,所述L形块的两侧均转动连接有连接块,所述连接块的底部固定连接有安装块,所述圆环内部的顶部开设有凹槽,所述圆环内部的底部开设有螺纹孔,所述螺纹孔的内腔螺纹连接有螺纹杆,所述螺纹杆的顶端固定连接有圆板,所述圆板的表面与凹槽相适配,所述螺纹杆的底部贯穿至圆环的底部。In order to achieve the above purpose, the utility model provides the following technical solutions: an aircraft side guide rail with a positioning function, comprising: an aircraft side guide rail body, two positioning grooves are opened on both sides of the aircraft side guide rail body, and the aircraft side guide rail body The bottom of the side rail body is provided with two limit grooves, the inner cavity of the limit groove is provided with a ring, the surface of the ring is provided with an annular groove, and the inner cavity of the annular groove is provided with two Symmetrical transmission blocks, the opposite sides of the two transmission blocks are fixedly connected with an L-shaped block, the top of the L-shaped block is fixedly connected with a positioning block, and both sides of the L-shaped block are rotatably connected with connecting blocks, The bottom of the connecting block is fixedly connected with a mounting block, the top inside the ring is provided with a groove, the bottom inside the ring is provided with a threaded hole, and the inner cavity of the threaded hole is threadedly connected with a threaded rod, so A circular plate is fixedly connected to the top of the threaded rod, the surface of the circular plate fits the groove, and the bottom of the threaded rod penetrates to the bottom of the ring.

进一步的,作为本实用新型一种优选的,所述圆环的底部固定连接有连接环,所述连接环的内腔与螺纹杆相适配,所述连接环的表面套设有弹簧,所述连接环的顶端与圆环固定连接。Further, as a preferred embodiment of the present invention, the bottom of the circular ring is fixedly connected with a connecting ring, the inner cavity of the connecting ring is adapted to the threaded rod, and the surface of the connecting ring is covered with a spring, so that The top of the connecting ring is fixedly connected with the circular ring.

进一步的,作为本实用新型一种优选的,所述圆环的表面固定连接有两个对称设置的限位块,所述限位块与限位槽相适配。Further, as a preferred aspect of the present invention, two symmetrically arranged limiting blocks are fixedly connected to the surface of the circular ring, and the limiting blocks are matched with the limiting grooves.

进一步的,作为本实用新型一种优选的,所述凹槽的直径大于螺纹孔的直径。Further, as a preference of the present invention, the diameter of the groove is larger than the diameter of the threaded hole.

进一步的,作为本实用新型一种优选的,所述螺纹杆的底部固定连接有转动块,所述弹簧的底端与转动块固定连接。Further, as a preferred aspect of the present invention, the bottom of the threaded rod is fixedly connected with a rotating block, and the bottom end of the spring is fixedly connected with the rotating block.

有益效果,本申请的技术方案具备如下技术效果:本实用新型具备定位精度高和使用灵活的优点,在实际使用过程中,通过三角定位的方法,能够确保飞机侧导轨定位的稳定性,方便使用者将飞机侧导轨和机侧翼本体进行连接,避免了在安装过程中,出现安装偏差,影响侧导轨的正常使用,且结构简单,使用方便,无需拆卸零件,通用性较好,即而完成对侧导轨的定位,因此,该定位结构具有良好市场前景,值得推广。Beneficial effects, the technical solution of the application has the following technical effects: the utility model has the advantages of high positioning accuracy and flexible use. In the actual use process, the triangular positioning method can ensure the stability of the positioning of the aircraft side guide rail and is convenient to use. The aircraft side guide rail is connected with the aircraft side wing body, which avoids the installation deviation during the installation process and affects the normal use of the side guide rail. It is simple in structure, easy to use, no need to disassemble parts, and has good versatility. Therefore, this positioning structure has a good market prospect and is worth promoting.

应当理解,前述构思以及在下面更加详细地描述的额外构思的所有组合只要在这样的构思不相互矛盾的情况下都可以被视为本公开的实用新型主题的一部分。It should be understood that all combinations of the foregoing concepts as well as additional concepts described in more detail below may be considered part of the inventive subject matter of the present disclosure, provided such concepts are not mutually inconsistent.

附图说明Description of drawings

附图用来提供对本实用新型的进一步理解,并且构成说明书的一部分,与本实用新型的实施例一起用于解释本实用新型,并不构成对本实用新型的限制。在附图中:The accompanying drawings are used to provide a further understanding of the utility model, and constitute a part of the description, and are used to explain the utility model together with the embodiments of the utility model, and do not constitute a limitation to the utility model. In the attached picture:

图1为本实用新型结构示意图;Fig. 1 is the structural representation of the utility model;

图2为本实用新型局部结构仰视立体图;Fig. 2 is a bottom perspective view of the partial structure of the utility model;

图3为本实用新型定位结构立体示意图;Fig. 3 is a three-dimensional schematic diagram of the positioning structure of the utility model;

图4为本实用新型局部结构立体剖面示意图;Fig. 4 is a three-dimensional cross-sectional schematic diagram of a local structure of the utility model;

图5为本实用新型局部结构立体示意图。Fig. 5 is a three-dimensional schematic diagram of a partial structure of the utility model.

图中,各附图标记的含义如下:1、飞机侧导轨本体;2、定位槽;3、限位槽;4、圆环;5、环形凹槽;6、传动块;7、L形块;8、定位块;9、连接块;10、凹槽;11、螺纹孔;12、螺纹杆;13、圆板;14、连接环;15、弹簧;16、限位块;17、安装块;18、转动块。In the figure, the meanings of the reference signs are as follows: 1. Aircraft side guide rail body; 2. Positioning groove; 3. Limiting groove; 4. Ring; 5. Annular groove; 6. Transmission block; 7. L-shaped block ; 8, positioning block; 9, connection block; 10, groove; 11, threaded hole; 12, threaded rod; 13, circular plate; 14, connection ring; 15, spring; 16, limit block; 17, installation block ; 18, turn the block.

具体实施方式Detailed ways

下面将结合本实用新型实施例中的附图,对本实用新型实施例中的技术方案进行清楚、完整地描述,为了更了解本实用新型的技术内容,特举具体实施例并配合所附图式说明如下。在本公开中参照附图来描述本实用新型的各方面,附图中示出了许多说明的实施例。应当理解,上面介绍的多种构思和实施例,以及下面更加详细地描述的那些构思和实施方式可以以很多方式中任意一种来实施。基于本实用新型中的实施例,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,都属于本实用新型保护的范围。The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. described as follows. Aspects of the invention are described in this disclosure with reference to the accompanying drawings, in which a number of illustrated embodiments are shown. It should be appreciated that the various concepts and embodiments introduced above, as well as those concepts and implementations described in more detail below, can be implemented in any of numerous ways. Based on the embodiments of the present utility model, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the scope of protection of the present utility model.

如附图1至附图5所示:本实施例提供一种具有定位功能的飞机侧导轨,包括:飞机侧导轨本体1,所述飞机侧导轨本体1的两侧均开设有两个定位槽2,所述飞机侧导轨本体1的底部开设有两个限位槽3,所述限位槽3的内腔设置有圆环4,所述圆环4的表面开设有环形凹槽5,所述环形凹槽5的内腔设置有两个对称的传动块6,两个传动块6相背的一侧均固定连接有L形块7,所述L形块7的顶部固定连接有定位块8,所述L形块7的两侧均转动连接有连接块9,所述连接块9的底部固定连接有安装块17,所述圆环4内部的顶部开设有凹槽10,所述圆环4内部的底部开设有螺纹孔11,所述凹槽10的直径大于螺纹孔11的直径,所述螺纹孔11的内腔螺纹连接有螺纹杆12,所述螺纹杆12的顶端固定连接有圆板13,所述圆板13的表面与凹槽10相适配,所述螺纹杆12的底部贯穿至圆环4的底部。As shown in accompanying drawings 1 to 5: the present embodiment provides an aircraft side guide rail with positioning function, comprising: an aircraft side guide rail body 1, two positioning grooves are provided on both sides of the aircraft side guide rail body 1 2. The bottom of the aircraft side guide rail body 1 is provided with two limiting grooves 3, the inner cavity of the limiting groove 3 is provided with a circular ring 4, and the surface of the circular ring 4 is provided with an annular groove 5, so The inner cavity of the annular groove 5 is provided with two symmetrical transmission blocks 6, and the opposite sides of the two transmission blocks 6 are fixedly connected with an L-shaped block 7, and the top of the L-shaped block 7 is fixedly connected with a positioning block 8. Both sides of the L-shaped block 7 are rotatably connected with a connecting block 9, the bottom of the connecting block 9 is fixedly connected with a mounting block 17, and the top of the ring 4 is provided with a groove 10, and the circle The bottom inside the ring 4 is provided with a threaded hole 11, the diameter of the groove 10 is greater than the diameter of the threaded hole 11, the inner cavity of the threaded hole 11 is threadedly connected with a threaded rod 12, and the top end of the threaded rod 12 is fixedly connected with a A circular plate 13 , the surface of the circular plate 13 is adapted to the groove 10 , and the bottom of the threaded rod 12 penetrates to the bottom of the ring 4 .

具体的,所述圆环4的底部固定连接有连接环14,所述连接环14的内腔与螺纹杆12相适配,所述连接环14的表面套设有弹簧15,所述连接环14的顶端与圆环4固定连接,所述螺纹杆12的底部固定连接有转动块18,所述弹簧15的底端与转动块18固定连接。Specifically, the bottom of the ring 4 is fixedly connected with a connecting ring 14, the inner cavity of the connecting ring 14 is adapted to the threaded rod 12, and the surface of the connecting ring 14 is sleeved with a spring 15, and the connecting ring The top of 14 is fixedly connected with the ring 4 , the bottom of the threaded rod 12 is fixedly connected with a rotating block 18 , and the bottom end of the spring 15 is fixedly connected with the rotating block 18 .

本实施例中:通过连接环14、弹簧15和转动块18的配合使用,起到了对12工作时进行缓冲的作用。In this embodiment: through the joint use of the connecting ring 14, the spring 15 and the rotating block 18, the function of buffering the 12 during operation is played.

具体的,所述圆环4的表面固定连接有两个对称设置的限位块16,所述限位块16与限位槽3相适配。Specifically, two symmetrically arranged limiting blocks 16 are fixedly connected to the surface of the circular ring 4 , and the limiting blocks 16 are adapted to the limiting groove 3 .

本实施例中:通过限位块16的设置,起到了将圆环4进行限位的作用,防止了圆环4在出现转动的现象。In this embodiment: through the setting of the limiting block 16, the function of limiting the position of the circular ring 4 is played, preventing the phenomenon that the circular ring 4 is rotating.

本实用新型的工作原理及使用流程:使用者通过将圆环4和限位块16嵌入限位槽3的内腔,转动螺纹杆12,螺纹杆12通过和螺纹孔11的配合使用,带动圆环4向下移动,圆环4通过圆板13带动圆环4向下移动,圆环4通过环形凹槽5和传动块6的配合使用,带动两个L形块7以连接块9为轴心向相对的一侧移动,L形块7带动定位块8卡入定位槽2的内腔,进而完成定位的目的。The working principle and use process of the utility model: the user inserts the ring 4 and the limit block 16 into the inner cavity of the limit groove 3, rotates the threaded rod 12, and the threaded rod 12 is used in conjunction with the threaded hole 11 to drive the circle The ring 4 moves downward, and the circular ring 4 drives the circular ring 4 to move downward through the circular plate 13. The circular ring 4 is used in conjunction with the annular groove 5 and the transmission block 6 to drive the two L-shaped blocks 7 with the connecting block 9 as the axis. The heart moves to the opposite side, and the L-shaped block 7 drives the positioning block 8 to snap into the inner cavity of the positioning groove 2, thereby accomplishing the purpose of positioning.

需要说明的是,在本文中,诸如第一和第二等之类的关系术语仅仅用来将一个实体或者操作与另一个实体或操作区分开来,而不一定要求或者暗示这些实体或操作之间存在任何这种实际的关系或者顺序。It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply that there is a relationship between these entities or operations. There is no such actual relationship or order between them.

虽然本实用新型已以较佳实施例揭露如上,然其并非用以限定本实用新型。本实用新型所属技术领域中具有通常知识者,在不脱离本实用新型的精神和范围内,当可作各种的更动与润饰。因此,本实用新型的保护范围当视权利要求书所界定者为准。Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Those with ordinary knowledge in the technical field to which the utility model belongs can make various changes and modifications without departing from the spirit and scope of the utility model. Therefore, the protection scope of the present utility model should be defined by the claims.

Claims (5)

1. An aircraft side rail with positioning function, comprising: aircraft side guide rail body (1), its characterized in that: two constant head tanks (2) have all been seted up to the both sides of aircraft side guide rail body (1), two spacing groove (3) have been seted up to the bottom of aircraft side guide rail body (1), the inner chamber of spacing groove (3) is provided with ring (4), annular groove (5) have been seted up on the surface of ring (4), the inner chamber of annular groove (5) is provided with two symmetrical transmission piece (6), the equal fixedly connected with L shape piece (7) in one side that two transmission piece (6) are on the back of the body mutually, the top fixedly connected with locating piece (8) of L shape piece (7), the both sides of L shape piece (7) are all rotated and are connected with connecting block (9), the bottom fixedly connected with installation piece (17) of connecting block (9), fluted (10) are seted up at the inside top of ring (4), threaded hole (11) are seted up to the inside bottom of ring (4), threaded rod (12) are threaded connection in the inner chamber of threaded hole (11), the top fixedly connected with plectane (13) of threaded rod (12), the top fixedly connected with round plate (13) of plectane (13) and the bottom of recess (12) looks, bottom of wearing to ring (4).
2. An aircraft side rail with positioning function according to claim 1, characterized in that: the bottom fixedly connected with go-between (14) of ring (4), the inner chamber and the threaded rod (12) looks adaptation of go-between (14), the surface cover of go-between (14) is equipped with spring (15), the top and the ring (4) fixed connection of go-between (14).
3. An aircraft side rail with positioning function according to claim 1, characterized in that: two symmetrically arranged limiting blocks (16) are fixedly connected to the surface of the circular ring (4), and the limiting blocks (16) are matched with the limiting grooves (3).
4. An aircraft side rail with positioning function according to claim 1, characterized in that: the diameter of the groove (10) is larger than that of the threaded hole (11).
5. An aircraft side rail with positioning function according to claim 2, characterized in that: the bottom of threaded rod (12) is fixedly connected with rotary block (18), the bottom of spring (15) and rotary block (18) fixed connection.
CN202321018684.9U 2023-04-30 2023-04-30 An aircraft side guide rail with positioning function Expired - Fee Related CN219619373U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202321018684.9U CN219619373U (en) 2023-04-30 2023-04-30 An aircraft side guide rail with positioning function

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202321018684.9U CN219619373U (en) 2023-04-30 2023-04-30 An aircraft side guide rail with positioning function

Publications (1)

Publication Number Publication Date
CN219619373U true CN219619373U (en) 2023-09-01

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN202321018684.9U Expired - Fee Related CN219619373U (en) 2023-04-30 2023-04-30 An aircraft side guide rail with positioning function

Country Status (1)

Country Link
CN (1) CN219619373U (en)

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Granted publication date: 20230901