CN213841914U - Device for synchronously detecting opening and closing of tail wings of rocket projectile - Google Patents
Device for synchronously detecting opening and closing of tail wings of rocket projectile Download PDFInfo
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- CN213841914U CN213841914U CN202023184493.9U CN202023184493U CN213841914U CN 213841914 U CN213841914 U CN 213841914U CN 202023184493 U CN202023184493 U CN 202023184493U CN 213841914 U CN213841914 U CN 213841914U
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Abstract
The utility model provides a device about rocket projectile fin synchronous detection that opens and shuts has solved among the prior art and has detected the problem that the required accuracy can not reach, the unable storage of data. The device includes mechanical support, pneumatic mechanism and photoelectric control mechanism, mechanical support includes an upper fixed plate, bottom plate and curb plate, an upper fixed plate passes through the fixed column and links to each other with the bottom plate, the bottom plate middle part is fixed with the three-jaw chuck, three-jaw chuck one side is provided with infrared location support, an upper fixed plate bottom is fixed with rotatory workstation and optic fibre and begins the location chi, rotatory workstation lower extreme links to each other with rotation fixed plate, the rotation fixed plate lower extreme is equipped with the optic fibre fixed column, the upper fixed plate top is equipped with the cylinder. Through PLC control circuit, optical fiber sensor detects the fin time of opening and shutting, and the computer carries out data storage, printing, detects the precision and reaches 1us, and the position precision is high, and rotatable precision reaches 0.02 degree, through adjusting optical fiber sensor at the position of location chi, detectable multiple model.
Description
Technical Field
The utility model relates to a rocket projectile fin opens and shuts and detects technical field, especially indicates a device about rocket projectile fin synchronous detection that opens and shuts.
Background
The tail wings of the rocket projectiles need to be opened when being launched, after the tail wings of the rocket projectiles are partially assembled, the opening and closing time and the opening synchronism of the rocket projectiles need to be detected, the opening time of the tail wings is 20-100ms, the precision requirement of a time detection device is us (microseconds), the opening consistency of each wingspan is required to be good, meanwhile, the detection data can be stored and printed, and the traditional detection device is difficult to meet the requirements.
SUMMERY OF THE UTILITY MODEL
The utility model provides a device about rocket projectile fin synchronous detection that opens and shuts has solved among the prior art and has detected the problem that the required accuracy can not reach, the unable storage of data.
The technical scheme of the utility model is realized like this:
the utility model provides a device about rocket bomb fin synchronous detection that opens and shuts, including mechanical support, pneumatic mechanism and photoelectric control mechanism, mechanical support includes the upper fixed plate, bottom plate and curb plate, the upper fixed plate passes through the fixed column and links to each other with the bottom plate, the bottom plate middle part is fixed with the three-jaw chuck, three-jaw chuck one side is provided with infrared location support, the upper fixed plate bottom is fixed with rotatory workstation and optic fibre and begins the location chi, rotatory workstation lower extreme links to each other with rotatory fixed plate, the rotatory fixed plate lower extreme is equipped with the optic fibre fixed column, the upper fixed plate top is equipped with the cylinder.
Furthermore, an optical fiber sensor is arranged at the lower end of the optical fiber fixing column, and an optical fiber sensor is fixed on the optical fiber starting positioning ruler.
Furthermore, the pneumatic mechanism comprises an air cylinder, an upper electromagnetic limit switch and a lower electromagnetic limit switch are fixed at the upper end of the air cylinder, the air cylinder is connected with an electromagnetic valve, the electromagnetic valve is fixed on the side plate, and the electromagnetic valve is connected with an air filter.
Further, photoelectric control mechanism include control panel, the fiber sensor of fiber fixing column lower extreme passes through the relay and is connected with the PLC input, is fixed with control button on the control panel, control button is connected with the PLC input, the last microsecond counter that is equipped with of control panel, the microsecond counter passes through the relay and is connected with the PLC output, swivel work head passes through the driver and is connected with the PLC output.
The beneficial effect that this technical scheme can produce: through PLC control circuit, optical fiber sensor detects the fin time of opening and shutting, and the computer carries out data storage, printing, detects the precision and reaches 1us, and the position precision is high, and rotatable precision reaches 0.02 degree, through adjusting optical fiber sensor in the position of location chi, the multiple model of detectable, the device simple structure, labour saving and time saving does not harm the product, reasonable in design.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a front view of the present invention;
fig. 2 is a rear view of the present invention;
fig. 3 is a circuit diagram of the control panel.
In the figure: the device comprises an upper fixing plate 1, a lower fixing plate 2, fixing columns 3, a three-jaw chuck 4, an infrared positioning support 5, optical fiber fixing columns 6, an optical fiber starting positioning ruler 7, a rotary fixing plate 8, a rotary workbench 9, an air cylinder 10, an electromagnetic valve 11, a side plate 12 and an air filter 13.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without any creative effort belong to the protection scope of the present invention.
As shown in fig. 1-3, this embodiment provides a device about rocket projectile fin synchronous detection that opens and shuts, including mechanical support, pneumatic mechanism and photoelectric control mechanism, mechanical support includes upper fixed plate 1, bottom plate 2 and curb plate 12, upper fixed plate 1 links to each other with bottom plate 2 through fixed column 3, 2 middle parts of bottom plate are fixed with three-jaw chuck 4, three-jaw chuck 4 one side is provided with infrared positioning support 5, 1 bottom of upper fixed plate is fixed with swivel work head 9 and optic fibre and begins location chi 7, swivel work head 9 lower extreme links to each other with swivel fixed plate 8, 8 lower extremes of swivel fixed plate are equipped with optic fibre fixed column 6, 1 top of upper fixed plate is equipped with cylinder 10.
The lower end of the optical fiber fixing column 6 is provided with an optical fiber sensor, and the optical fiber starting positioning ruler 7 is fixed with the optical fiber sensor.
The pneumatic mechanism comprises an air cylinder 10, an upper electromagnetic limit switch and a lower electromagnetic limit switch are fixed at the upper end of the air cylinder 10, the air cylinder 10 is connected with an electromagnetic valve 11, the electromagnetic valve 11 is fixed on a side plate 12, and the electromagnetic valve 11 is connected with an air filter 13. The battery valve is a three-position five-way solenoid valve 11.
Photoelectric control mechanism include control panel, the optical fiber sensor of 6 lower extremes of optic fibre fixed column passes through the relay and is connected with the PLC input, is fixed with control button on the control panel, control button is connected with the PLC input, the last microsecond counter that is equipped with of control panel, the microsecond counter passes through the relay and is connected with the PLC output, swivel work head 9 passes through the driver and is connected with the PLC output.
The working process of the embodiment is as follows:
(1) setting automatic positioning angle setting in a control picture, pressing a rotary button, and driving an optical fiber sensor at the lower end of an optical fiber fixing column 6 to rotate by a rotary worktable 9 so that the optical fiber sensor corresponds to the detection position of a workpiece;
(2) a workpiece is manually installed on the three-jaw chuck 4, a descending button is pressed, and the air cylinder 10 extends out to drive the rotary workbench 9 to descend;
(3) pressing a start button, operating the system to work, and lighting an infrared calibration lamp; rotating the workpiece, aligning the corresponding position of the workpiece with the infrared rays emitted by the infrared positioning bracket 5, and clamping by the three-jaw chuck 4;
(4) when a hand loosens the workpiece, the operator leaves the operating console, presses a lifting button, retracts the air cylinder 10 to drive the rotary workbench 9 to lift, opens the tail wing of the workpiece, starts sensing by the optical fiber sensor of the optical fiber start positioning ruler 7, starts timing by the microsecond counter, receives a signal by the optical fiber sensor of the optical fiber fixing column 6, and finishes timing;
(5) the opening speed of the screen is displayed, the 'storage' of the 'main picture' is clicked, and data are stored; clicking the 'picture' print setting of the 'main picture' to print data; pressing a reset button, and resetting the detection data;
(6) and (5) repeating the work flows from (2) to (5) and continuing to detect.
Preferably, the optical fiber sensor on the optical fiber start positioning ruler 7 can move up and down along the positioning ruler, so that different products can be adapted.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. The utility model provides a device about rocket projectile fin synchronous detection that opens and shuts, includes mechanical support, pneumatic mechanism and photoelectric control mechanism, its characterized in that: the mechanical support comprises an upper fixing plate (1), a lower fixing plate (2) and a side plate (12), the upper fixing plate (1) is connected with the lower fixing plate (2) through fixing columns (3), a three-jaw chuck (4) is fixed in the middle of the lower fixing plate (2), an infrared positioning support (5) is arranged on one side of the three-jaw chuck (4), a rotary workbench (9) and an optical fiber positioning ruler (7) are fixed to the bottom of the upper fixing plate (1), the lower end of the rotary workbench (9) is connected with a rotary fixing plate (8), optical fiber fixing columns (6) are arranged at the lower end of the rotary fixing plate (8), and a cylinder (10) is arranged at the top of the upper fixing plate (1).
2. The device for synchronously detecting the opening and closing of the tail wing of the rocket projectile as claimed in claim 1, wherein: the lower end of the optical fiber fixing column (6) is provided with an optical fiber sensor, and the optical fiber starting positioning ruler (7) is fixed with the optical fiber sensor.
3. The device for synchronously detecting the opening and closing of the tail wing of the rocket projectile as claimed in claim 1, wherein: the pneumatic mechanism comprises an air cylinder (10), an upper electromagnetic limit switch and a lower electromagnetic limit switch are fixed at the upper end of the air cylinder (10), the air cylinder (10) is connected with an electromagnetic valve (11), the electromagnetic valve (11) is fixed on a side plate (12), and the electromagnetic valve (11) is connected with an air filter (13).
4. The device for synchronously detecting the opening and closing of the tail wing of the rocket projectile as claimed in claim 2, wherein: photoelectric control mechanism include control panel, the fiber sensor of optic fibre fixed column (6) lower extreme passes through the relay and is connected with the PLC input, is fixed with control button on the control panel, control button is connected with the PLC input, the last microsecond counter that is equipped with of control panel, the microsecond counter passes through the relay and is connected with the PLC output, swivel work head (9) pass through the driver and are connected with the PLC output.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023184493.9U CN213841914U (en) | 2020-12-25 | 2020-12-25 | Device for synchronously detecting opening and closing of tail wings of rocket projectile |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023184493.9U CN213841914U (en) | 2020-12-25 | 2020-12-25 | Device for synchronously detecting opening and closing of tail wings of rocket projectile |
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| CN213841914U true CN213841914U (en) | 2021-07-30 |
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| CN202023184493.9U Active CN213841914U (en) | 2020-12-25 | 2020-12-25 | Device for synchronously detecting opening and closing of tail wings of rocket projectile |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114234740A (en) * | 2021-12-03 | 2022-03-25 | 北方导航控制技术股份有限公司 | Device and method for testing opening time of folding rudder wing of rocket projectile |
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2020
- 2020-12-25 CN CN202023184493.9U patent/CN213841914U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114234740A (en) * | 2021-12-03 | 2022-03-25 | 北方导航控制技术股份有限公司 | Device and method for testing opening time of folding rudder wing of rocket projectile |
| CN114234740B (en) * | 2021-12-03 | 2023-09-26 | 北方导航控制技术股份有限公司 | Device and method for testing opening time of folded rudder wing of rocket projectile |
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