CN211491152U - Anchor clamps are used in multidirectional vibrations test of aircraft airborne equipment - Google Patents
Anchor clamps are used in multidirectional vibrations test of aircraft airborne equipment Download PDFInfo
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- CN211491152U CN211491152U CN201921996543.8U CN201921996543U CN211491152U CN 211491152 U CN211491152 U CN 211491152U CN 201921996543 U CN201921996543 U CN 201921996543U CN 211491152 U CN211491152 U CN 211491152U
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Abstract
The application discloses a clamp for a multidirectional vibration test of airborne equipment of an aircraft, which comprises a base, a pair of rotary pillars arranged on the base in opposite directions, and a pair of rotary disks arranged on opposite side surfaces of the rotary pillars respectively; a mounting flat plate is fixedly connected between the pair of rotating disks; the aircraft airborne equipment is fixed on the installation flat plate; a plurality of horizontal reversing mounting holes are formed in the base around the center of the base; the rotary support is arranged in the horizontal reversing mounting hole through a bolt; the center of the rotating disc is rotatably connected with the rotating support column through a reversing rotating shaft; a plurality of vertical reversing mounting holes are uniformly formed in the rotary support column around the reversing rotary shaft; the rotating disc is installed in the vertical reversing installation hole through a bolt. The application enables the airborne equipment of the aircraft to be precisely adjusted in rotation in multiple directions; therefore, in the multi-directional vibration test, when reversing, the base does not need to be disassembled and assembled, and multi-directional adjustment can be realized; the adjusting time is reduced, the testing efficiency is improved, and the testing cost is reduced.
Description
Technical Field
The utility model relates to an aircraft detects technical field, especially relates to a multidirectional test of shaking of aircraft airborne equipment anchor clamps of using.
Background
The equipment was subjected to vibration or shock testing simulating environmental conditions to verify the stability of vibration life and related performance, and the rationality of design, manufacture, and installation. The common vibration clamp is usually designed according to the requirements of each device, and cannot meet the requirement of multidirectional vibration testing, or needs to be disassembled and assembled again to adjust the installation direction of the clamp and the device, so that the cost in all aspects is increased.
Disclosure of Invention
In view of the above-mentioned drawbacks and deficiencies of the prior art, it would be desirable to provide a universal clamp for a multidirectional vibration test of equipment onboard an aircraft.
The first aspect of the application provides a clamp for a multidirectional vibration test of airborne equipment of an aircraft, which comprises a base, a pair of rotating pillars arranged on the base in an opposite way, and a pair of rotating disks arranged on opposite side surfaces of the rotating pillars respectively; a mounting flat plate is fixedly connected between the pair of rotating disks; the aircraft airborne equipment is fixed on the mounting flat plate;
a plurality of horizontal reversing mounting holes are formed in the base around the center of the base; the rotary support is arranged in the horizontal reversing mounting hole through a bolt;
the center of the rotating disc is rotatably connected with the rotating support column through a reversing rotating shaft; a plurality of vertical reversing mounting holes are uniformly formed in the rotary support column around the reversing rotary shaft; the rotating disc is installed in the vertical reversing installation hole through a bolt.
According to the technical scheme provided by the embodiment of the application, the opposite side surfaces of the rotating disc extend out of the mounting pieces; the side edges of the mounting pieces and the mounting flat plate are connected through bolts.
According to the technical scheme provided by the embodiment of the application, the installation flat plate comprises a flat plate body and a circular through hole formed in the middle of the flat plate body; an installation disc is embedded in the through hole; the mounting disc is provided with equipment mounting holes for mounting airborne equipment of the aircraft;
the mounting disc comprises a rotating part capable of rotating in the through hole and a mounting part which is positioned on one side of the rotating part and clamped on the outer side of the through hole; and the mounting part and the corresponding flat plate body are correspondingly and uniformly provided with disc mounting holes.
According to the technical scheme that this application embodiment provided, the installation department is kept away from the one side middle part protrusion of rotation portion has cross or rice font frame.
According to the technical scheme provided by the embodiment of the application, one end, far away from the mounting part, of the annular wall of the through hole extends inwards to form a flange; the arc surface of the rotating part is inwards sunken to form an annular notch matched with the flange.
According to the technical scheme provided by the embodiment of the application, the side surface of the mounting disc, which is used for mounting the airborne equipment of the aircraft, comprises a mounting surface and an adjusting groove arranged around the mounting surface; the equipment mounting hole is formed in the mounting surface; a plurality of adjusting blocks are connected in the adjusting grooves through springs; the surface of the adjusting block forms an adjusting surface which is flush with the mounting surface.
The application provides a clamp for a multidirectional vibration test of airborne equipment of an aircraft, which comprises a base, a pair of rotating pillars arranged on the base in opposite directions, and a pair of rotating disks arranged on opposite side surfaces of the rotating pillars respectively; a mounting flat plate is fixedly connected between the pair of rotating disks; the aircraft airborne equipment is fixed on the mounting flat plate; the aircraft airborne equipment can horizontally rotate by rotating the mounting position of the rotating pillar on the base, and the aircraft airborne equipment can rotate in a vertical plane by rotating the rotating disc and adjusting the mounting position of the rotating disc; therefore, in the multi-directional vibration test, when reversing, the base does not need to be disassembled and assembled, and multi-directional adjustment can be realized; the adjustment time is reduced, the test efficiency is improved, and the test cost is reduced; and in this application, take the form of base, have sufficient area that compresses tightly on the base and supply to install the airborne equipment of being surveyed, but operating space is reserved to the base below, is convenient for install, transport. The device can also change the specification of the mounting plate according to the mounting form and the size specification of the airborne equipment, is used for vibration tests of different tested airborne equipment, and has strong universality.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
fig. 1 is a schematic structural diagram of a jig for a multi-directional vibration test of an aircraft-mounted device according to an embodiment of the present disclosure;
fig. 2 is a schematic structural diagram of a mounting plate in a jig for a multi-directional vibration test of an aircraft-mounted device according to a second embodiment of the present application;
reference numbers in the figures:
100. a base; 200. rotating the support; 300. rotating the disc; 400. installing a flat plate; 110. a horizontal reversing mounting hole; 310. a reversing rotating shaft; 210. a vertical reversing mounting hole; 320. mounting a sheet; 410. a plate body; 420. a through hole; 430. mounting a disc; 440. an equipment mounting hole; 431. A rotating part; 432. an installation part; 433. a disk mounting hole; 434. a mounting surface; 450. and a regulating block.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Example one
Please refer to fig. 1, which illustrates a universal fixture for multi-directional vibration test of an aircraft onboard device according to an embodiment of the present invention. Comprises a base 100, a pair of rotating pillars 200 oppositely arranged on the base, and a pair of rotating discs 300 respectively arranged on the opposite side surfaces of the rotating pillars 200; a mounting flat plate 400 is fixedly connected between the pair of rotating discs 300; the aircraft onboard equipment is fixed on the mounting plate 400;
a plurality of horizontal reversing mounting holes 110 are formed in the base 100 around the center thereof; the rotating support column 200 is mounted in the horizontal reversing mounting hole 110 through a bolt;
the center of the rotating disc 300 is rotatably connected with the rotating column 200 through a reversing rotating shaft 310; a plurality of vertical reversing mounting holes 210 are uniformly formed on the rotary supporting column 200 around the reversing rotary shaft 310; the rotating plate 300 is mounted in the vertical diverting mounting hole 210 by bolts.
During the shock test, the equipment onboard the aircraft is fixed on the mounting plate 400; the base 100 is installed on the vibration test table; a plurality of operating and installing spaces are reserved on the base 100, so that the equipment is convenient to compress and install; the position and orientation of the device under test can be changed by changing the mounting position of the pair of rotating supports 200 on the base 100; the position and orientation of the device under test can also be changed by turning the rotational shaft 310. Since the positions of the vertical direction-changing mounting holes 210 are uniformly distributed around the direction-changing rotation axis, the rotation angle of the direction-changing rotation axis 310 is precisely matched with that of the vertical direction-changing mounting holes 210, and precise positioning is realized. Similarly, the horizontal direction-changing mounting holes 110 are uniformly distributed in the center of the base 100, so that the rotation angle of the rotation support 200 is determined no matter which horizontal direction-changing mounting hole is rotated to be fixedly connected with. Therefore, the above-mentioned technical scheme of this embodiment provides multidirectional vibrations test and uses anchor clamps, and when this anchor clamps switching-over, need not the dismouting base, can realize multidirectional adjustment.
In addition, in the embodiment, the specification of the mounting plate can be changed according to the mounting form and the size specification of the airborne equipment, the mounting plate is used for vibration tests of different tested airborne equipment, and the universality is high
In this embodiment, the opposite sides of the rotating disc 300 are protruded with mounting pieces 320; the mounting piece 320 is connected to the side of the mounting plate 400 by bolts.
Example two
As shown in fig. 2, on the basis of the first embodiment, in the jig for testing multidirectional vibration of an aircraft-mounted device provided in this embodiment, the mounting plate 400 includes a plate body 410 and a circular through hole 420 formed in the middle of the plate body 410; an installation plate 430 is embedded in the through hole 410; the mounting plate 430 is provided with an equipment mounting hole 440 for mounting equipment on board the aircraft;
the mounting plate 430 comprises a rotating part 431 which can rotate in the through hole 420, and a mounting part 432 which is positioned at one side of the rotating part 431 and clamped at the outer side of the through hole 420; the mounting portion 432 and the corresponding flat plate body 410 are correspondingly and uniformly provided with plate mounting holes 433.
The provision of the mounting plate 430 further provides a direction of rotation perpendicular to the reversing rotary shaft 310, further providing the jig with a greater choice of rotation in either direction. Since the disk mounting holes 433 are uniformly distributed about the axis of the through hole, rotation in this direction is also precisely positionable.
Preferably, in this embodiment, a cross or a frame shaped like a Chinese character mi protrudes from the middle of one side of the mounting part away from the rotating part. A cross or a spider may facilitate rotation of the mounting plate 430.
Preferably, in this embodiment, an end of the annular wall of the through hole 420 away from the mounting portion extends inward to form a rib 421; the arc surface of the rotating part is inwards sunken to form an annular notch matched with the flange.
Preferably, in this embodiment, the side of the mounting plate 430 for mounting equipment on board the aircraft includes a mounting surface 434 and an adjustment groove disposed around the mounting surface 434; the device mounting holes 440 are disposed on the mounting face 434; a plurality of adjusting blocks 450 are connected in the adjusting grooves through springs; the surface of the adjustment block 450 forms an adjustment surface that is flush with the mounting surface 434. The setting of the regulation face of constituteing by regulating block 450 through spring coupling makes to the machine of dysmorphism detection equipment that carries, its plane and the mounting disc laminating that correspond except with the mounting hole, the position of all the other dysmorphias also can compress tightly with mounting disc 430 through extrusion regulating block 450, has increased the installation holding surface of equipment, has improved the stability of vibrations test.
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by a person skilled in the art that the scope of the invention as referred to in the present application is not limited to the embodiments with a specific combination of the above-mentioned features, but also covers other embodiments with any combination of the above-mentioned features or their equivalents without departing from the inventive concept. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.
Claims (6)
1. The clamp for the multidirectional vibration test of the airborne equipment of the aircraft is characterized by comprising a base, a pair of rotating support columns oppositely arranged on the base and a pair of rotating disks respectively arranged on opposite side surfaces of the rotating support columns; a mounting flat plate is fixedly connected between the pair of rotating disks; the aircraft airborne equipment is fixed on the mounting flat plate;
a plurality of horizontal reversing mounting holes are formed in the base around the center of the base; the rotary support is arranged in the horizontal reversing mounting hole through a bolt;
the center of the rotating disc is rotatably connected with the rotating support column through a reversing rotating shaft; a plurality of vertical reversing mounting holes are uniformly formed in the rotary support column around the reversing rotary shaft; the rotating disc is installed in the vertical reversing installation hole through a bolt.
2. The multi-directional vibration test fixture for aircraft equipment according to claim 1, wherein mounting tabs extend from opposite sides of the rotating disk; the side edges of the mounting pieces and the mounting flat plate are connected through bolts.
3. The clamp for the multidirectional vibration test of the airborne equipment of the aircraft as recited in claim 1, wherein the mounting plate comprises a plate body and a circular through hole formed in the middle of the plate body; an installation disc is embedded in the through hole; the mounting disc is provided with equipment mounting holes for mounting airborne equipment of the aircraft;
the mounting disc comprises a rotating part capable of rotating in the through hole and a mounting part which is positioned on one side of the rotating part and clamped on the outer side of the through hole; and the mounting part and the corresponding flat plate body are correspondingly and uniformly provided with disc mounting holes.
4. The clamp for the multi-directional vibration test of the airborne equipment of the aircraft according to claim 3, wherein a cross or a cross-shaped frame protrudes from the middle of one side of the mounting portion, which is far away from the rotating portion.
5. The jig for testing multidirectional vibration of equipment on an aircraft according to claim 3, wherein an end of the annular wall of the through hole, which is far away from the mounting portion, extends inward to form a rib; the arc surface of the rotating part is inwards sunken to form an annular notch matched with the flange.
6. The jig for the multidirectional vibration testing of the equipment on the aircraft as claimed in claim 3, wherein the side surface of the mounting plate for mounting the equipment on the aircraft comprises a mounting surface and an adjusting groove arranged around the mounting surface; the equipment mounting hole is formed in the mounting surface; a plurality of adjusting blocks are connected in the adjusting grooves through springs; the surface of the adjusting block forms an adjusting surface which is flush with the mounting surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921996543.8U CN211491152U (en) | 2019-11-19 | 2019-11-19 | Anchor clamps are used in multidirectional vibrations test of aircraft airborne equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921996543.8U CN211491152U (en) | 2019-11-19 | 2019-11-19 | Anchor clamps are used in multidirectional vibrations test of aircraft airborne equipment |
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| CN211491152U true CN211491152U (en) | 2020-09-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921996543.8U Active CN211491152U (en) | 2019-11-19 | 2019-11-19 | Anchor clamps are used in multidirectional vibrations test of aircraft airborne equipment |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461478A (en) * | 2020-09-30 | 2021-03-09 | 北京航天光华电子技术有限公司 | Be applicable to all directions commonality impact test device of post toper product |
| CN112605920A (en) * | 2020-12-17 | 2021-04-06 | 陕西宝成航空仪表有限责任公司 | Clamp device suitable for three axial vibrations of components and parts |
| CN113063676A (en) * | 2021-03-15 | 2021-07-02 | 浙江省计量科学研究院 | Fixing device for three-dimensional vibration test of irregular sample |
| CN114310723A (en) * | 2022-01-19 | 2022-04-12 | 西安微电子技术研究所 | Multi-direction acceleration test fixture for acceleration test machine |
-
2019
- 2019-11-19 CN CN201921996543.8U patent/CN211491152U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461478A (en) * | 2020-09-30 | 2021-03-09 | 北京航天光华电子技术有限公司 | Be applicable to all directions commonality impact test device of post toper product |
| CN112461478B (en) * | 2020-09-30 | 2022-12-27 | 北京航天光华电子技术有限公司 | Be applicable to all directions commonality impact test device of post toper product |
| CN112605920A (en) * | 2020-12-17 | 2021-04-06 | 陕西宝成航空仪表有限责任公司 | Clamp device suitable for three axial vibrations of components and parts |
| CN113063676A (en) * | 2021-03-15 | 2021-07-02 | 浙江省计量科学研究院 | Fixing device for three-dimensional vibration test of irregular sample |
| CN113063676B (en) * | 2021-03-15 | 2022-08-16 | 浙江省计量科学研究院 | Fixing device for three-dimensional vibration test of irregular sample |
| CN114310723A (en) * | 2022-01-19 | 2022-04-12 | 西安微电子技术研究所 | Multi-direction acceleration test fixture for acceleration test machine |
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