Carbon fiber grid for reinforcing aerospace equipment

Abstract

The utility model provides a carbon fiber grid for strengthening aerospace equipment, and relates to the technical field of aerospace equipment, the carbon fiber grid comprises a first connecting rod, a second connecting rod and a mounting mechanism, the first connecting rod and the second connecting rod are internally provided with connecting grooves at equal intervals, and cross rods are connected among the connecting grooves; first through holes are formed in the multiple transverse rods, a plurality of first through holes are formed in one sides of the interiors of the multiple transverse rods, first insertion rods are installed in the first through holes, first installation blocks are installed at the positions, on one sides of the transverse rods, of the tops of the first insertion rods, and a plurality of pairs of second through holes are formed in one sides of the bottoms of the transverse rods at equal intervals. Second inserting rods are clamped in the pair of second through holes, and a second mounting block is mounted between the bottoms of the pair of second inserting rods. The carbon fiber grid connecting device is simple and reasonable in structure, novel in design and easy and convenient to operate, the carbon fiber grids are effectively installed and connected, use convenience is improved, and the carbon fiber grid connecting device has high practical value.

Description

Technical Field

[0001] The utility model belongs to the technical field of aerospace equipment, and more specifically, relates to a carbon fiber grid for reinforcing aerospace equipment. Background Art

[0002] Carbon fiber mesh is also known as carbon fiber cloth, carbon fiber cloth, carbon fiber woven cloth, etc. Carbon fiber mesh cloth has the characteristics of high strength, low density, thin thickness, and basically does not increase the deadweight and cross-sectional size of the reinforced components. It is currently widely used in various fields.

[0003] Based on the above, the inventors have found the following problems: the current carbon fiber mesh does not rust and is very suitable for use in high acid, alkali, salt and atmospheric corrosion environments. However, the carbon fiber mesh structure used to reinforce traditional aerospace equipment is not strong enough, is prone to breakage, and is not convenient to install and use, and is not convenient to operate.

[0004] Therefore, in view of this, the existing structure and defects are studied and improved, and a carbon fiber grid for reinforcing aerospace equipment is provided, in order to achieve a purpose with greater practical value. Utility Model Content

[0005] In order to solve the above technical problems, the utility model provides a carbon fiber grid for reinforcing aerospace equipment to solve the problems in the current background technology.

[0006] The purpose and efficacy of the carbon fiber grid for reinforcing aerospace equipment of this utility model are achieved by the following specific technical means:

[0007] A carbon fiber grid for reinforcing aerospace equipment and materials comprises a first connecting rod, a second connecting rod and a mounting mechanism, wherein connecting grooves are provided at equal distances inside the first connecting rod and the second connecting rod, and a cross rod is connected between several of the connecting grooves, a first through hole is provided inside several of the cross rods, and a vertical rod is inserted between several of the first through holes, the cross rods and the vertical rods intersect with each other, a plurality of first through holes are provided on one side of the interior of several of the cross rods, and a first insertion rod is installed inside the first through hole, a first mounting block is installed on the top of the first insertion rod on one side of the cross rod, a plurality of pairs of second through holes are provided at equal distances on one side of the bottom of the cross rod, and a second insertion rod is engaged with the interior of a pair of the second through holes, and a second mounting block is installed between the bottoms of the pair of second insertion rods.

[0008] Furthermore, the first connecting rod and the second connecting rod are provided with fixing grooves on both sides of the connecting grooves, and a pair of fixing blocks are installed at both ends of the cross rods, and the fixing blocks are engaged with the fixing grooves.

[0009] Furthermore, a first threaded hole is provided inside each of the fixing blocks, and a plurality of second threaded holes are provided at equal distances on one side of the first connecting rod and the second connecting rod.

[0010] Furthermore, the inner thread of the second threaded hole is connected to a threaded rod, and the bottom end of the threaded rod passes through the second threaded hole and extends to the inside of the first threaded hole, and engages with the inside of the first threaded hole.

[0011] Furthermore, card slots are provided on both sides of the interior of the first insertion rod, and one end of a pair of second insertion rods passes through the horizontal rod and extends to the interior of the vertical rod.

[0012] Furthermore, a pair of the second insertion rods are each provided with a mounting groove on one side thereof, and a spring is connected to the inner side of the mounting groove, one end of the spring is connected to a clamping block, and the clamping block and the clamping groove are engaged with each other.

[0013] Compared with the prior art, the present invention has the following beneficial effects:

[0014] This type of carbon fiber grid for reinforcing aerospace equipment is used in conjunction with a connecting groove, a fixing groove, a first through hole, a threaded rod, a first threaded hole, a second threaded hole, a fixing block, a first plug rod, a second plug rod, a spring, a clamping block and a clamping groove. Before using the carbon fiber grid, the two ends of the cross bar are respectively inserted into a pair of connecting grooves. During the insertion process, a pair of fixing blocks and a pair of fixing grooves are engaged with each other. Then, several threaded rods are inserted into the second threaded holes, and the threaded rods are rotated to engage with the first threaded holes. The pair of fixing blocks and the fixing grooves are fixed to each other, thereby installing the cross bar. and fix it, then insert the vertical rod into the interior of the cross rod through the first through hole, then insert the first mounting block and the first insertion rod into the interior of the first through hole, and then insert the second mounting block and a pair of second insertion rods from the bottom of the cross rod to fix the vertical rod, and at the same time, the clamping block and the clamping groove engage with each other to fix the first insertion rod, completing the installation of the cross rod and the vertical rod, and can be quickly installed and disassembled, increasing the convenience of use; the utility model has a simple and reasonable structure, a novel design, and is simple and convenient to operate, effectively installs and connects the carbon fiber grid, increases the convenience of use, and has high practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a three-dimensional schematic diagram of the present utility model.

[0016] Figure 2 It is a three-dimensional expansion schematic diagram of the utility model.

[0017] Figure 3 It is a partial three-dimensional expansion schematic diagram of the utility model.

[0018] Figure 4It is a schematic planar cross-sectional view of the first insertion rod of the utility model.

[0019] In the figure, the corresponding relationship between the component names and the drawing numbers is as follows:

[0020] 1001, first connecting rod; 1002, second connecting rod; 1003, connecting groove; 1004, fixing groove; 1005, horizontal rod; 1006, first through hole; 1007, vertical rod; 1008, first threaded hole; 1009, fixing block; 1010, second threaded hole; 1011, threaded rod; 2001, first mounting block; 2002, first insertion rod; 2003, second through hole; 2004, second mounting block; 2005, second insertion rod; 2006, mounting groove; 2007, spring; 2008, clamping block; 2009, clamping groove. DETAILED DESCRIPTION

[0021] The following embodiments of the present invention are described in further detail with reference to the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0022] Example:

[0023] As attached Figure 1 To the attached Figure 4 As shown:

[0024] The utility model provides a carbon fiber grid for reinforcing aerospace equipment, comprising a first connecting rod 1001, a second connecting rod 1002 and a mounting mechanism, wherein the first connecting rod 1001 and the second connecting rod 1002 are provided with connecting grooves 1003 at equal distances inside, and a plurality of the connecting grooves 1003 are connected with cross bars 1005, a plurality of the cross bars 1005 are provided with first through holes 1006 inside, and a plurality of the first through holes 1006 are inserted with vertical bars 1007, and the cross bars 1005 and the vertical bars 1007 are connected to each other. The cross bars 1005 are cross-linked with each other, and a plurality of first through holes 1006 are provided on one side of the inner part of each of the cross bars 1005, and a first plug rod 2002 is installed inside the first through hole 1006, and a first mounting block 2001 is installed on the top of the first plug rod 2002 on one side of the cross bar 1005, and a plurality of pairs of second through holes 2003 are equidistantly provided on one side of the bottom of the cross bar 1005, and a second plug rod 2005 is engaged with the inner part of a pair of the second through holes 2003, and a second mounting block 2004 is installed between the bottoms of the pair of the second plug rods 2005.

[0025] Among them, the first connecting rod 1001 and the second connecting rod 1002 are provided with fixing grooves 1004 on both sides of the several connecting grooves 1003, and a pair of fixing blocks 1009 are installed at both ends of the several cross bars 1005, and the several fixing blocks 1009 are engaged with the fixing grooves 1004.

[0026] Among them, a first threaded hole 1008 is provided inside each of the fixing blocks 1009, and a second threaded hole 1010 is provided at equal distances on one side of the first connecting rod 1001 and the second connecting rod 1002. By installing the threaded rod 1011, it is convenient to fix the fixing block 1009 and the fixing groove 1004 to each other, thereby completing the installation of the cross bar 1005.

[0027] The inner thread of the second threaded hole 1010 is connected to a threaded rod 1011 , and the bottom end of the threaded rod 1011 passes through the second threaded hole 1010 and extends to the inside of the first threaded hole 1008 , engaging with the inside of the first threaded hole 1008 .

[0028] Among them, there are card slots 2009 on both sides of the interior of the first insertion rod 2002, and one end of a pair of the second insertion rods 2005 passes through the horizontal rod 1005 and extends to the interior of the vertical rod 1007. The horizontal rod 1005 and the vertical rod 1007 are cross-mounted with each other to increase stability in use.

[0029] Among them, a pair of second insertion rods 2005 are each provided with a mounting groove 2006 on one side thereof, and a spring 2007 is connected to the inner side of the mounting groove 2006, and one end of the spring 2007 is connected to a clamping block 2008, and the clamping block 2008 and the clamping groove 2009 are engaged with each other. By installing the clamping block 2008, the first insertion rod 2002 can be fixed, so that the horizontal rod 1005 and the vertical rod 1007 are fixedly connected to each other.

[0030] The specific usage and function of this embodiment are as follows:

[0031] When using this product, first, check whether the connection of the product is tight. After ensuring that it is intact, before using the carbon fiber grid, insert the two ends of the crossbar 1005 into the pair of connecting grooves 1003 respectively. During the insertion process, a pair of fixing blocks 1009 and a pair of fixing grooves 1004 are engaged with each other. Then, insert a number of threaded rods 1011 into the second threaded holes 1010, rotate the threaded rods 1011, so that the threaded rods 1011 and the first threaded holes 1008 are engaged with each other, and the pair of fixing blocks 1009 and the fixing grooves 1004 are fixed to each other, thereby tightening the crossbar 1005. After installation and fixing, insert the vertical rod 1007 into the interior of the horizontal rod 1005 through the first through hole 1006, and then insert the first mounting block 2001 and the first insertion rod 2002 into the interior of the first through hole 1006, and then insert the second mounting block 2004 and a pair of second insertion rods 2005 from the bottom of the horizontal rod 1005 to fix the vertical rod 1007. At the same time, the card block 2008 and the card slot 2009 engage with each other to fix the first insertion rod 2002, completing the installation of the horizontal rod 1005 and the vertical rod 1007. It can be quickly installed and disassembled, increasing the convenience of use.

[0032] The embodiments of the present invention are provided for purposes of illustration and description and are not intended to be exhaustive or to limit the present invention to the disclosed forms. Many modifications and variations will be apparent to those skilled in the art. The embodiments are selected and described to better illustrate the principles and practical applications of the present invention and to enable those skilled in the art to understand the present invention and design various embodiments with various modifications suitable for specific applications.

Claims

1. A carbon fiber grid for reinforcing aerospace equipment, characterized by: The invention comprises a first connecting rod (1001), a second connecting rod (1002) and a mounting mechanism, wherein the first connecting rod (1001) and the second connecting rod (1002) are provided with connecting grooves (1003) at equal distances inside, and a plurality of the connecting grooves (1003) are connected with cross bars (1005), a plurality of the cross bars (1005) are provided with first through holes (1006) inside, and a plurality of vertical rods (1007) are inserted between the first through holes (1006), the cross bars (1005) and the vertical rods (1007) intersect with each other, and a plurality of the cross bars (1005) are connected with each other. 05) is provided with a plurality of first through holes (1006) on one side of the interior thereof, and a first plug rod (2002) is installed inside the first through hole (1006), a first mounting block (2001) is installed on the top of the first plug rod (2002) on one side of the cross bar (1005), a plurality of pairs of second through holes (2003) are provided at equal distances on one side of the bottom of the cross bar (1005), and a second plug rod (2005) is engaged inside a pair of the second through holes (2003), and a second mounting block (2004) is installed between the bottoms of the pair of the second plug rods (2005).

2. The carbon fiber mesh for reinforcing aerospace equipment according to claim 1, characterized in that: The first connecting rod (1001) and the second connecting rod (1002) are provided with fixing grooves (1004) on both sides of the plurality of connecting grooves (1003), and a pair of fixing blocks (1009) are installed at both ends of the plurality of cross bars (1005), and the plurality of fixing blocks (1009) are engaged with the fixing grooves (1004).

3. The carbon fiber mesh for reinforcing aerospace equipment as claimed in claim 2, characterized in that: A first threaded hole (1008) is provided inside each of the fixing blocks (1009), and a plurality of second threaded holes (1010) are provided at equal distances on one side of the first connecting rod (1001) and the second connecting rod (1002).

4. The carbon fiber mesh for reinforcing aerospace equipment as claimed in claim 3, characterized in that: The internal thread of the second threaded hole (1010) is connected to a threaded rod (1011), and the bottom end of the threaded rod (1011) passes through the second threaded hole (1010) and extends to the inside of the first threaded hole (1008), and engages with the inside of the first threaded hole (1008).

5. The carbon fiber mesh for reinforcing aerospace equipment as claimed in claim 1, characterized in that: Insertion slots (2009) are provided on both sides of the interior of the first insertion rod (2002), and one end of a pair of the second insertion rods (2005) passes through the horizontal rod (1005) and extends to the interior of the vertical rod (1007).

6. The carbon fiber mesh for reinforcing aerospace equipment as claimed in claim 5, characterized in that: A pair of the second insertion rods (2005) are each provided with a mounting groove (2006) on one inner side, and a spring (2007) is connected to the inner side of the mounting groove (2006), one end of the spring (2007) is connected to a clamping block (2008), and the clamping block (2008) and the clamping groove (2009) are engaged with each other.

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