Universal impact vibration test tool for medium and small caliber solid rocket engine

Abstract

The invention belongs to the field of solid rocket engine design, and particularly relates to a general impact vibration test tool for medium and small caliber solid rocket engines, which comprises an L-shaped mounting base, an upper bracket, a lower bracket and an annular clamping block. The L-shaped mounting base is provided with two parallel mounting slideways and a plurality of mounting clamping grooves, the mounting slideways adjust the support to move back and forth so as to adapt to mounting and fixing of engines with different lengths, and the mounting clamping grooves are used for being connected and fixed with various vibration bases. Annular clamping blocks with different sizes are replaced to adapt to solid engines with different calibers. The test direction needs to be changed in the axial direction of the engine, rotation and fixation of the engine in the test direction can be completed by adjusting the tightness degree between the upper support and the lower support, and when the axial direction and the radial direction need to be changed in an environment test, only the installation and fixation positions of the L-shaped installation base and the vibration base need to be integrally adjusted. The dismounting times and the number of test tools are reduced, and the impact vibration test efficiency of the engine is greatly improved.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of solid rocket engine design, and particularly relates to a universal impact vibration test tool for a medium-small caliber solid rocket engine. BACKGROUND

[0002] Solid rocket engines are widely used in unmanned aerial vehicle power devices due to their simple structure, reliability, convenience and long-term storage advantages. However, unmanned aerial vehicles may be affected by high-frequency vibration, impact and random vibration during launch, transportation and service processing, which may lead to structural fatigue damage of the weapon system. Therefore, it is necessary to simulate the complex impact vibration environment that the engine may encounter in the actual use scenario through vibration impact test, so as to verify the rationality of the engine design, the stability of the structure and the reliability of the function. Due to the great difference in structure form of different types of solid rocket engine products, the corresponding environmental test tool is also different. The traditional impact vibration test tool needs to design corresponding axial and radial environmental test tools for different types of solid rocket engines, resulting in a large number of impact vibration test tools, various specifications, poor universality, and certain resource waste. The existing patent CN221120140U "Solid rocket engine axial mechanical environmental test tool" can be used for axial mechanical environmental test of various types of engines, but cannot be applied to radial mechanical environmental test. The existing patent CN211262709U "Solid rocket engine vibration test tool" can be applied to axial and radial vibration test of different diameter engines, but it needs to be disassembled and assembled twice when developing axial forward and reverse direction vibration, and it needs to design different diameter front and rear skirt supports to meet the environmental test requirements of different diameter engines, which is complex and difficult to disassemble and assemble. SUMMARY

[0003] (I) Technical problem to be solved

[0004] The technical problem to be solved by the present application is how to provide a universal solid rocket engine impact vibration test tool that can be applied to different length specifications, meet the impact vibration environmental test of different caliber solid rocket engines, and be compatible with the installation requirements of various vibration bases, has a simple structure, is easy to disassemble and assemble, and improves the assembly efficiency of the impact vibration environmental test.

[0005] (II) Technical solution

[0006] To solve the above technical problems, the application provides a universal impact vibration test tool for small and medium caliber solid rocket engines, which can meet the installation and fixation of engines with different lengths by adjusting the distance between the lower supports, meet the installation and fixation of engines with different calibers by replacing ring-shaped clamping blocks with different diameters, and realize the fixation with different vibration bases through the design of the L-shaped mounting base mounting clamping groove, so as to realize the use of one set of tool for different length specifications, meet the axial and radial impact vibration environmental test requirements of solid rocket engines with different calibers, and meet the installation requirements of various vibration bases.

[0007] The impact vibration test tool comprises an L-shaped mounting base (1), an upper support (2), a lower support (3), a ring-shaped clamping block (4), and a connecting bolt (5).

[0008] The L-shaped mounting base (1) is provided with a plurality of mounting clamping grooves (11) for mounting and fixing with a vibration base (7 or 8).

[0009] The upper support (2) and the lower support (3) are provided in sets, and each set comprises at least two upper supports (2) and at least two lower supports (3). The inner part of each upper support (2) and each lower support (3) is connected with a fixed ring-shaped clamping block (4) through a fastening screw. The upper support (2) and the lower support (3) are connected and fixed through a connecting bolt (5). The lower support (3) is connected and fixed with the L-shaped mounting base (1) through a connecting bolt (5).

[0010] Each set of upper support (2) and lower support (3) is fixed to each other to form a circular accommodating space. Multiple sets of upper support (2) and lower support (3) are fixed to each other to form multiple coaxial circular accommodating spaces, which are used to carry the engine (6).

[0011] When the radial impact vibration test of the engine is carried out, the long end face of the L-shaped mounting base (1) is fixed with the vibration base (7 or 8). According to the installation and fixation length of the engine, the distance between the lower supports (3) is adjusted, and the lower supports (3) are installed and fixed with the L-shaped mounting base (1) through connecting bolts (5).

[0012] According to the different calibers of the engine, ring-shaped clamping blocks (4) with different specifications are selected, and the ring-shaped clamping blocks (4) are installed and fixed with the upper support (2) and the lower support (3) through fastening screws.

[0013] The engine (6) is placed in the multiple concentric circles formed by the upper support (2) and the lower support (3) and is installed and fixed through connecting bolts.

[0014] When the direction of the radial impact vibration test needs to be adjusted, the connecting bolts (5) between the upper support (2) and the lower support (3) are loosened, and the engine (6) is rotated by 90° along the axial direction to realize the rotation of the direction.

[0015] When the axial impact vibration test of the engine is carried out, the L-shaped mounting base (1) is directly turned over 90 degrees with the upper support (2), the lower support (3), the annular clamping block (4) and the engine, the long end face of the L-shaped mounting base (1) is fixed to the vibration base (7 or 8) through the connecting bolt (5), and the engine (6) and the upper support (2) and the lower support (3) do not need to be disassembled.

[0016] The side edges of the long end face and the short end face of the L-shaped mounting base (1) are respectively provided with a plurality of long strip-shaped mounting clamping grooves (11) for the mounting and fixing of the vibration base; two parallel mounting slides (12) are arranged in the middle of the long end face of the L-shaped mounting base (1) for the mounting and fixing of the lower support (3); and an embedded step structure (13) is arranged at the bottom end of the long end face of the L-shaped mounting base (1) for the placement of the connecting bolt (5).

[0017] The upper support (2) is a semicircular structure, and the through holes are arranged in the protruding lugs at both ends of the upper support (2) and are connected and fixed to the lower support (3) through connecting bolts; and a plurality of screw holes are arranged in the upper support (2) and are distributed along the radial direction for the connection and fixing of the annular clamping block (4).

[0018] The through holes are arranged in the protruding lugs at the upper end of the lower support (3) and are arranged in the through holes arranged in the protruding lugs at both ends of the upper support (2) in a top-to-bottom corresponding manner and are connected and fixed to the upper support (2) through connecting bolts; a plurality of screw holes are arranged in the lower support (3) and are distributed along the radial direction for the connection and fixing of the annular clamping block (4); and long strip-shaped mounting clamping grooves are arranged at both sides of the bottom end of the lower support (3) to meet the mounting and fixing of the mounting slides (12) of the L-shaped mounting base (1) with different intervals.

[0019] The annular clamping block (4) is designed with a plurality of screw holes along the radial direction, and is mounted and fixed to the upper support (2) and the lower support (3) through fastening screws.

[0020] The connecting bolt includes a screw rod (51) and a nut (52).

[0021] The distance between the lower supports (3) is adjusted to meet the mounting and fixing of solid rocket engines with different length ranges.

[0022] Different sizes of annular clamping blocks (4) are replaced to meet the mounting and fixing of solid rocket engines with different caliber ranges.

[0023] The long strip-shaped mounting clamping grooves (11) are designed on the side edges of the L-shaped mounting base (1), the connecting bolt (5) is used to meet the mounting and fixing of the rectangular vibration base (7) with the long strip-shaped I-shaped slide (71), or the connecting screw rod (51) is used to meet the mounting and fixing of the threaded hole disc-shaped vibration base (8), and a plurality of vibration bases can be mounted and fixed.

[0024] The vibration base is a rectangular vibration base or a disc-shaped vibration base.

[0025] (Three) beneficial effects

[0026] Compared with the prior art, the present application has the following beneficial effects:

[0027] (1) The present application designs an L-shaped mounting base, without disassembling the engine, and only needs to rotate the L-shaped mounting base and the upper and lower supports and the engine as a whole to complete the direction change of the engine axial and radial directions, so that only one set of tooling can meet the engine axial and radial impact vibration test requirements, significantly reducing the number of toolings and disassembly and assembly times, and improving the engine assembly efficiency.

[0028] (2) The present application can meet the fixing and impact vibration test requirements of solid engines of different length ranges by adjusting the mounting distance between the lower supports.

[0029] (3) The present application can meet the mounting, fixing and impact vibration test requirements of solid engines of different caliber ranges by replacing ring-shaped clamping blocks of different specifications.

[0030] (4) The present application can meet the mounting and fixing of the rectangular vibration base with a long strip-shaped I-shaped slide or the disc-shaped vibration base with threaded holes through the design of the L-shaped mounting base side edge mounting clamping groove. BRIEF DESCRIPTION OF DRAWINGS

[0031] Figure 1 is a schematic diagram of the three-dimensional structure of the present application.

[0032] Figure 2 is a schematic diagram of the structure when the present application implements radial impact vibration test (rectangular vibration base with long strip-shaped I-shaped slide).

[0033] Figure 3 is a schematic diagram of the structure when the present application implements radial impact vibration test (disc-shaped vibration base with threaded holes).

[0034] Figure 4 is a schematic diagram of the structure when the present application implements axial impact vibration test (rectangular vibration base with long strip-shaped I-shaped slide).

[0035] Figure 5 is a schematic diagram of the structure when the present application implements axial impact vibration test (disc-shaped vibration base with threaded holes).

[0036] Wherein, 1-L-shaped mounting base; 11-mounting clamping groove; 12-mounting slide; 13-embedded step structure; 2-upper support; 3-lower support; 31-lower support mounting clamping groove; 4-ring-shaped clamping block; 5-connecting bolt; 51-screw rod; 52-nut; 6-engine; 7-rectangular vibration base; 71-long strip type I-shaped slide; 8-disc-shaped vibration base; 81-threaded hole. DETAILED DESCRIPTION

[0037] In order to make the purpose, content and advantages of the present application more clear, the specific embodiments of the present application are described in further detail below in combination with the drawings and examples.

[0038] To solve the above technical problems, the present application provides a universal impact vibration test tool for small and medium caliber solid rocket engine, which can meet the installation and fixation of engines with different lengths by adjusting the distance between the lower supports, can meet the installation and fixation of engines with different diameters by replacing ring-shaped clamping blocks with different diameters, and can be fixed to different vibration bases through the design of the L-shaped mounting base mounting clamping groove, so as to realize the use of one set of tool for different length specifications, meet the axial and radial impact vibration environmental test requirements of different caliber solid rocket engines, and meet the installation requirements of various vibration bases.

[0039] The impact vibration test tool comprises an L-shaped mounting base (1), an upper support (2), a lower support (3), a ring-shaped clamping block (4) and a connecting bolt (5).

[0040] The L-shaped mounting base (1) is provided with a plurality of mounting clamping grooves (11) for installation and fixation with a vibration base (7 or 8).

[0041] The upper support (2) and the lower support (3) are provided in sets, and each set is provided with at least two supports. The inner part of each support is connected with a fixed ring-shaped clamping block (4) through a fastening screw. The upper support (2) and the lower support (3) are connected and fixed through a connecting bolt (5). The lower support (3) is connected and fixed with the L-shaped mounting base (1) through a connecting bolt (5).

[0042] After each set of upper support (2) and lower support (3) are fixed to each other, a circular accommodating space is formed. After multiple sets of upper support (2) and lower support (3) are fixed to each other, multiple coaxial circular accommodating spaces are formed, which are used to carry the engine (6).

[0043] When conducting radial impact vibration test of the engine, the long end face of the L-shaped mounting base (1) is fixed to the vibration base (7 or 8). According to the installation and fixation length of the engine, the distance between the lower supports (3) is adjusted, and the connecting bolt (5) is used to install and fix the L-shaped mounting base (1).

[0044] According to the different caliber of the engine, different specifications of annular clamping block (4) are selected, and fastening screws are used for installation and fixation with the upper support (2) and the lower support (3) respectively.

[0045] The engine (6) is placed in the multiple concentric circles surrounded by the upper support (2) and the lower support (3) and is installed and fixed by connecting bolts.

[0046] When the radial impact vibration test direction needs to be adjusted, the connecting bolts (5) between the upper support (2) and the lower support (3) are loosened, and the engine (6) is directly rotated by 90° along the axial direction to realize the direction rotation.

[0047] When the engine axial impact vibration test is carried out, the engine (6), the upper support (2) and the lower support (3) do not need to be disassembled, and the L-shaped mounting base (1) long end surface is directly turned over by 90° along with the upper support (2), the lower support (3), the annular clamping block (4) and the engine, and the short end surface is fixed with the vibration base (7 or 8) through the connecting bolts (5).

[0048] Among them, the long end surface and the short end surface of the L-shaped mounting base (1) are respectively provided with a plurality of long strip-shaped mounting clamping grooves (11) for the installation and fixation of the vibration base; the middle of the long end surface of the L-shaped mounting base (1) is provided with two parallel mounting slides (12) for the installation and fixation of the lower support (3); the bottom end of the long end surface of the L-shaped mounting base (1) is provided with an embedded step structure (13) for the placement of the connecting bolts (5).

[0049] Among them, the upper support (2) is a semicircular structure, and the through holes designed in the two end protruding ears are connected and fixed with the lower support (3) through connecting bolts; the upper support (2) is designed with a plurality of radially distributed screw holes for connecting and fixing with the annular clamping block (4).

[0050] Among them, the through holes designed in the upper end protruding ears of the lower support (3) are arranged in a corresponding upper and lower manner with the through holes designed in the two end protruding ears of the above-mentioned upper support (2) and are connected and fixed with the upper support (2) through connecting bolts; the lower support (3) is designed with a plurality of radially distributed screw holes for connecting and fixing with the annular clamping block (4); the bottom end of the lower support (3) is designed with long strip-shaped mounting clamping grooves on both sides, which can meet the installation and fixation of the mounting slides (12) of the L-shaped mounting base (1) with different distances.

[0051] Among them, the annular clamping block (4) is designed with a plurality of screw holes in the radial direction, which are installed and fixed with the upper support (2) and the lower support (3) through fastening screws.

[0052] Among them, the connecting bolt includes a screw rod (51) and a nut (52).

[0053] Wherein, by adjusting the distance between several lower supports (3) to meet the installation and fixation of solid rocket engine of different length range.

[0054] Wherein, by replacing different size ring-shaped clamping blocks (4) to meet the installation and fixation of solid rocket engine of different caliber range.

[0055] Wherein, by the design of L-shaped mounting base (1) side long strip-shaped mounting clamping groove (11), using connecting bolts (5) to meet the installation and fixation of rectangular vibration base (7) with long strip-shaped I-beam slide (71) or using connecting screw (51) and threaded hole disc-shaped vibration base (8) to meet the installation and fixation of various vibration bases.

[0056] Wherein, the vibration base is a rectangular vibration base or a disc-shaped vibration base.

[0057] Embodiment 1

[0058] As shown in Figures 1-5 , the embodiment provides a general impact and vibration test tool for small and medium caliber solid rocket engine, which comprises: an L-shaped mounting base (1), an upper support (2), a lower support (3), a ring-shaped clamping block (4), and a connecting bolt (5).

[0059] The L-shaped mounting base (1) is fixedly connected with the vibration base (7 or 8) through the connecting bolts, the upper support (2) is arranged directly above the lower support (3), and a certain distance is kept between the upper support (2) and the lower support (3) for the ring-shaped clamping block (4) to be fixedly installed with the upper support (2) and the lower support (3) through the fastening screws, and the engine (6) is placed in the concentric circle surrounded by the upper support (2), the lower support (3) and the ring-shaped clamping block (4) and is fixedly installed through the connecting bolt (5).

[0060] As shown in Figure 2 and Figure 3 , when carrying out radial impact and vibration test, the L-shaped mounting base (1) is fixedly connected with the vibration base through at least four connecting bolts, two sets of lower supports (3) are vertically placed on the L-shaped mounting base (1) and are fixedly connected through two connecting bolts (5) according to the installation and fixation length of the engine, and different specifications of ring-shaped clamping blocks (4) are selected according to the different caliber of the engine and are fixedly installed with the upper support (2) and the lower support (3) through fastening screws, and the engine (6) is horizontally placed in the center of the lower support (3) and is connected and fastened with the upper support (2) through the connecting bolt (5). When it is necessary to adjust the radial impact and vibration test direction (from Y to Z), only the connecting bolt (5) between the upper support (2) and the lower support (3) is loosened, and the engine (6) is directly rotated by 90° along the axial direction to realize the direction rotation.

[0061] As shown in Figure 4 andFigure 5 As shown, when the axial impact vibration test is carried out, the connecting bolts between the L-shaped mounting base (1) and the vibration base (7 or 8) are disassembled, the L-shaped mounting base is directly turned up and erected, and then the test can be carried out by fastening the connecting bolts.

[0062] When impact vibration tests need to be carried out on different types of solid rocket engines, the distance between the lower supports (3) and the size of the annular clamping block (4) can be adjusted according to the length and diameter of the engine to achieve the purpose. When it needs to be fixed with different vibration bases, it can be connected and fixed with various vibration bases through connecting bolts or screw rods.

[0063] The universal impact vibration test tool for small and medium caliber solid rocket engines provided by the application can be applied to impact vibration environmental tests of various types of solid rocket engines with different caliber specifications and different length sizes. The test tool can be disassembled and rotated to switch the axial and radial directions, so that one set of tool can meet the requirements of engine axial and radial impact vibration tests, greatly reducing the number of test tools and the number of disassembly and assembly times. Meanwhile, the tool can meet the installation and fixation of various vibration bases, and can effectively improve the assembly efficiency of environmental tests.

[0064] The above description is only the preferred embodiment of the application, and it should be pointed out that for ordinary skilled in the art, without departing from the technical principles of the application, several improvements and modifications can be made, and these improvements and modifications should be considered as the protection scope of the application.

Claims

1. A universal shock vibration test fixture for small and medium caliber solid rocket engines, characterized by: The impact vibration test fixture comprises: an L-shaped mounting base (1), an upper bracket (2), a lower bracket (3), and an annular clamping block (4); The L-shaped mounting base (1) is provided with a plurality of mounting slots (11) for mounting and fixing with the vibration base; The upper bracket (2) and the lower bracket (3) are provided as a set, and at least two of each are provided. The upper bracket (2) and the lower bracket (3) are both internally connected with a fixed annular clamping block (4). The upper bracket (2) and the lower bracket (3) are connected and fixed in a coordinated manner; the lower bracket (3) is connected and fixed to the L-shaped mounting base (1); After each set of upper brackets (2) and lower brackets (3) are fixed to each other, a circular accommodation space is formed. After multiple sets of upper brackets (2) and lower brackets (3) are fixed to each other, multiple coaxial circular accommodation spaces are formed, thereby being used to carry the engine (6); When carrying out the radial impact vibration test of the engine, the long end surface of the L-shaped mounting base (1) is fixedly connected to the vibration base; the distance between the plurality of lower brackets (3) is adjusted according to the fixed length of the engine installation, and the lower brackets (3) are fixedly installed to the L-shaped mounting base (1); Annular blocks (4) of different specifications are selected according to the different engine calibers, and are respectively fixed to the upper bracket (2) and the lower bracket (3); The engine (6) is placed in a plurality of concentric circles formed by the upper bracket (2) and the lower bracket (3) and fixed; When the direction of the radial impact vibration test needs to be adjusted, the upper bracket (2) and the lower bracket (3) only need to be loosened, and the engine (6) can be directly rotated 90 degrees along the axial direction to achieve the direction rotation; When carrying out an axial impact vibration test of an engine, the long end face of the L-shaped mounting base (1) together with the upper bracket (2), the lower bracket (3), the annular clamping block (4) and the engine as a whole are turned 90 degrees, and the short end face is fixed to the vibration base.

2. The universal shock vibration test fixture for small and medium-caliber solid rocket engines according to claim 1, characterized in that: The long end face and the side edges of the short end face of the L-shaped mounting base (1) are respectively provided with a plurality of long strip-shaped mounting slots (11) for mounting and fixing the vibration base; and two parallel mounting slideways (12) are provided in the middle of the long end face of the L-shaped mounting base (1) for mounting and fixing with the lower bracket (3).

3. The universal shock vibration test fixture for small and medium-caliber solid rocket engines according to claim 2, characterized in that: The upper bracket (2) is a semicircular structure, and the protruding ears at both ends are designed with through holes, which are connected and fixed to the lower bracket (3) through connecting bolts; the upper bracket (2) is designed with a plurality of screw holes distributed along the radial direction, which are used to connect and fix with the annular clamping block (4).

4. The universal shock vibration test fixture for small and medium-caliber solid rocket engines according to claim 3, characterized in that: The protruding ears at the upper end of the lower bracket (3) are designed with through holes, which are arranged in correspondence with the through holes designed for the protruding ears at both ends of the upper bracket (2) and are connected and fixed to the upper bracket (2) through connecting bolts; the lower bracket (3) is designed with a plurality of screw holes distributed along the radial direction for connecting and fixing with the annular clamping block (4); and long strip-shaped mounting slots are designed on both sides of the bottom end of the lower bracket (3), which can meet the installation and fixation of mounting slides (12) with different spacings on the L-shaped mounting base (1).

5. The universal shock vibration test fixture for small and medium-caliber solid rocket engines according to claim 4, characterized in that: The annular clamping block (4) is designed with a plurality of screw holes along the radial direction and is mounted and fixed to the upper bracket (2) and the lower bracket (3) by fastening screws.

6. The universal shock vibration test fixture for small and medium-caliber solid rocket engines according to claim 5, characterized in that: The connecting bolt comprises a screw rod (51) and a nut (52).

7. The universal shock vibration test fixture for small and medium-caliber solid rocket engines according to claim 1, characterized in that: The distance between a plurality of lower brackets (3) is adjusted to meet the installation and fixation requirements of solid engines with different length ranges.

8. The universal shock vibration test fixture for small and medium-caliber solid rocket engines according to claim 1, characterized in that: By replacing annular clamping blocks (4) of different sizes, the installation and fixation of solid engines with different caliber ranges can be met.

9. The universal shock vibration test fixture for small and medium-caliber solid rocket engines according to claim 2, characterized in that: The design of the long strip-shaped mounting slot (11) on the side of the L-shaped mounting base (1) can meet the requirements of the installation and fixation of various vibration bases.

10. The universal shock vibration test fixture for small and medium-caliber solid rocket engines according to claim 1, characterized in that: The vibration base is a rectangular vibration base or a disc-shaped vibration base.

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