CN212151309U - Real-time calibration centering spacecraft lifting appliance capable of weighing - Google Patents
Real-time calibration centering spacecraft lifting appliance capable of weighing Download PDFInfo
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- CN212151309U CN212151309U CN202022132314.0U CN202022132314U CN212151309U CN 212151309 U CN212151309 U CN 212151309U CN 202022132314 U CN202022132314 U CN 202022132314U CN 212151309 U CN212151309 U CN 212151309U
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- microprocessor
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- wireless communication
- lifting appliance
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- 238000005303 weighing Methods 0.000 title claims abstract description 23
- 238000004891 communication Methods 0.000 claims abstract description 37
- 239000000725 suspension Substances 0.000 claims description 4
- 238000000034 method Methods 0.000 abstract description 8
- 210000001503 joint Anatomy 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000011179 visual inspection Methods 0.000 description 1
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Abstract
The utility model belongs to the technical field of the aerospace assembly, concretely relates to spacecraft hoist. The real-time calibration centering weighing spacecraft lifting appliance comprises a lifting appliance body, wherein the lifting appliance body comprises a lifting appliance frame, a camera, a first microprocessor and a first wireless communication device, a signal output end of the camera is electrically connected with the first microprocessor in a wired mode, and a communication end of the first microprocessor is electrically connected with the first wireless communication device in a wired mode; the display comprises a display screen, a second microprocessor and a second wireless communication device, a signal input end of the display screen is electrically connected with a signal output end of the second microprocessor in a wired mode, a communication end of the second microprocessor is electrically connected with the second wireless communication device in a wired mode, and the second wireless communication device is wirelessly connected with the first wireless communication device. The utility model discloses a division of labor cooperation of hoist body and display has alleviateed the risk that the spacecraft lifted by crane the in-process to a certain extent, has strengthened the security, has reduced user's the operation degree of difficulty.
Description
Technical Field
The utility model belongs to the technical field of the aerospace assembly, concretely relates to spacecraft hoist.
Background
In the process of assembling the spacecraft, the precision butt joint and the disassembly and assembly of the spacecraft are finished in a hoisting mode. Because the actual mass center position of the spacecraft is different from the theoretical mass center position to a certain extent, the hoisting is inclined, the point contact of the butting surface of the spacecraft is caused, the butting surface is damaged, and a positioning pin (or a guide pin) is damaged. Meanwhile, due to the deviation of the actual centroid position and the theoretical centroid position, rotation and swing are generated in the hoisting process, collision is easy to generate, and the spacecraft or operating personnel are damaged. At present, the methods mainly used for visual inspection are adopted in the lifting and butt joint processes of the spacecraft.
SUMMERY OF THE UTILITY MODEL
The utility model discloses to the spacecraft damage spacecraft butt joint face and operating personnel's technical problem easily at hoist and mount process and butt joint in-process, aim at provides a but real-time calibration centering weighing spacecraft hoist.
The real-time calibration centering weighing spacecraft lifting appliance comprises a lifting appliance body, wherein the lifting appliance body comprises a lifting appliance frame, a camera, a first microprocessor and a first wireless communication device, the camera is arranged on the lifting appliance frame, the camera end faces the top of a spacecraft, the signal output end of the camera is electrically connected with the first microprocessor in a wired mode, and the communication end of the first microprocessor is electrically connected with the first wireless communication device in a wired mode;
the display comprises a display screen, a second microprocessor and a second wireless communication device, wherein the signal input end of the display screen is in wired electric connection with the signal output end of the second microprocessor, the communication end of the second microprocessor is in wired electric connection with the second wireless communication device, and the second wireless communication device is in wireless connection with the first wireless communication device.
The utility model discloses add the camera on original hoist frame, through camera real-time observation spacecraft top, the data of camera system of making are sent for second wireless communication device through first microprocessor and first wireless communication device through wireless mode, handle the back through second microprocessor, show through the display screen to help the user to look for spacecraft focus position through the data display of display screen.
The lifting appliance body further comprises a weighing sensor (a force sensor), the upper surface of the weighing sensor is fixed on the lifting appliance frame, and a lifting rope penetrates through the lifting appliance frame and then is suspended on the lower surface of the weighing sensor.
The spreader frame is preferably a cross-foldable spreader frame;
the hanger frame comprises two hanger rods which are arranged in a crossed manner, and the middle parts of the two hanger rods are fixed through a vertical connecting shaft and a locking nut;
the bottom surfaces of two ends of each suspender are respectively welded with one weighing sensor, and four lifting ropes respectively penetrate through the suspender and are suspended on the lower surfaces of the corresponding weighing sensors.
Each lifting rope bottom is provided with the lifting hook. And the signal output end of the weighing sensor is electrically connected with the first microprocessor in a wired mode. The tension borne by four lifting ropes of the lifting appliance frame is monitored in real time through the weighing sensors, and eccentricity is prevented.
The load cell is preferably an S-shaped load cell.
The lifting appliance body further comprises an infrared distance meter, the infrared distance meter is arranged on the lifting appliance frame, and the measuring end faces the top of the spacecraft;
and the signal output end of the infrared distance meter is electrically connected with the first microprocessor in a wired mode. The image of the top of the spacecraft can be acquired through the infrared distance meter.
The infrared distance meter is preferably a laser infrared distance meter. So as to have the function of measuring and calculating the volume of the object.
The utility model discloses an actively advance the effect and lie in: the utility model discloses a but real-time calibration centering weighing spacecraft hoist, through the division of labor cooperation of hoist body and display, alleviateed the risk that the spacecraft lifted by crane the in-process to a certain extent, strengthened the security, reduced user's the operation degree of difficulty.
Drawings
Fig. 1 is a schematic diagram of a signal connection according to the present invention;
fig. 2 is a schematic structural diagram of the spreader frame of the present invention.
Detailed Description
In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention will be further explained with reference to the specific drawings.
Referring to fig. 1, the real-time calibration centering weighable spacecraft lifting appliance comprises a lifting appliance body, wherein the lifting appliance body comprises a lifting appliance frame, a camera 11, a weighing sensor 12, an infrared distance meter 13, a first microprocessor 14 and a first wireless communication device 15.
The camera 11 sets up on the hoist frame and the end of making a video recording is towards the spacecraft top, and the wired electricity of the signal output part of camera 11 is connected first microprocessor 14.
Referring to fig. 2, the upper surface of load cell 12 is fixed to spreader frame 3, and a lifting rope 31 is suspended from the lower surface of load cell 12 after passing through spreader frame 3. In particular, the spreader frame 3 is preferably a cross-foldable spreader frame. The hanger frame 3 comprises two hanger rods which are arranged in a crossed manner, and the middle parts of the two hanger rods are fixed through a vertical connecting shaft and a locking nut; the bottom surfaces of two ends of each suspension rod are respectively welded with a weighing sensor 12, and four lifting ropes 31 respectively penetrate through the suspension rods and are suspended on the lower surfaces of the corresponding weighing sensors 12. A hook 32 is arranged at the bottom of each lifting rope 31. The signal output of load cell 12 is in wired electrical connection with first microprocessor 14. Load cell 12 is preferably an S-shaped load cell 12.
The infrared distance meter 13 is arranged on the hanger frame, the measuring end faces the top of the spacecraft, and the signal output end of the infrared distance meter 13 is electrically connected with the first microprocessor 14 in a wired mode. The infrared distance meter 13 is preferably a laser infrared distance meter 13. So as to have the function of measuring and calculating the volume of the object. The communication end of the first microprocessor 14 is electrically connected with the first wireless communication device 15 in a wired mode. The first microprocessor 14 of the present invention may be a microprocessor capable of processing images, weights and infrared ranging signals in the prior art, such as an STM32F407 microprocessor, an ARM9 microprocessor, etc.
The display device further comprises a display, the display device comprises a display screen 21, a second microprocessor 22 and a second wireless communication device 23, a signal input end of the display screen 21 is electrically connected with a signal output end of the second microprocessor 22 in a wired mode, a communication end of the second microprocessor 22 is electrically connected with the second wireless communication device 23 in a wired mode, and the second wireless communication device 23 is in wireless connection with the first wireless communication device 15. The second microprocessor 22 of the present invention may be a microprocessor capable of processing data in the prior art, such as STM32F407 microprocessor, ARM9 microprocessor, etc.
The utility model discloses having add camera 11, weighing sensor 12 and infrared distance meter 13 on original hoist frame, having surveyd the spacecraft top in real time through camera 11, four lifting ropes through weighing sensor 12 real time monitoring hoist frame pulling force that receive prevent off-centre, can gather the image at spacecraft top through infrared distance meter 13. Data shot by the camera 11, tension information collected by the weighing sensor 12 and images collected by the infrared distance meter 13 are respectively sent to the first microprocessor 14, data processed by the first microprocessor 14 are packaged to the first wireless communication device 15, and the data are sent to the second wireless communication device 23 in a wireless mode through the first wireless communication device 15. After being processed by the second microprocessor 22, the data is displayed by the display screen 21, so that a user can be helped to calibrate the gravity center position of the centering spacecraft through the data display of the display screen 21.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. The real-time calibration centering weighing spacecraft lifting appliance comprises a lifting appliance body and is characterized in that the lifting appliance body comprises a lifting appliance frame, a camera, a first microprocessor and a first wireless communication device, wherein the camera is arranged on the lifting appliance frame, the camera end faces the top of a spacecraft, the signal output end of the camera is electrically connected with the first microprocessor in a wired mode, and the communication end of the first microprocessor is electrically connected with the first wireless communication device in a wired mode;
the display comprises a display screen, a second microprocessor and a second wireless communication device, wherein the signal input end of the display screen is in wired electric connection with the signal output end of the second microprocessor, the communication end of the second microprocessor is in wired electric connection with the second wireless communication device, and the second wireless communication device is in wireless connection with the first wireless communication device.
2. The real-time calibration centering weighable spacecraft sling according to claim 1, wherein the sling body further comprises a load cell, the upper surface of the load cell is fixed on the sling frame, and a lifting rope passes through the sling frame and then is suspended on the lower surface of the load cell;
and the signal output end of the weighing sensor is electrically connected with the first microprocessor in a wired mode.
3. The real-time calibration centering weightable spacecraft spreader of claim 2, wherein the load cells are S-shaped load cells.
4. The real-time calibration centering weighable spacecraft sling according to claim 2, wherein the sling frame is a cross-foldable sling frame, the sling frame comprises two cross-arranged suspension rods, and the middle parts of the two suspension rods are fixed through a vertical connecting shaft and a locking nut;
the bottom surfaces of two ends of each suspender are respectively welded with one weighing sensor, and four lifting ropes respectively penetrate through the suspender and are suspended on the lower surfaces of the corresponding weighing sensors.
5. The real-time calibration centering weightable spacecraft sling according to claim 4, wherein a hook is provided at the bottom of each of said lifting ropes.
6. The real-time calibration centering weighable spacecraft sling according to any one of claims 1 to 5, wherein the sling body further comprises an infrared distance meter, the infrared distance meter is arranged on the sling frame, and the measuring end faces the top of the spacecraft;
and the signal output end of the infrared distance meter is electrically connected with the first microprocessor in a wired mode.
7. The real-time calibration centering weightable spacecraft sling according to claim 6, wherein said infrared rangefinder is a laser infrared rangefinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022132314.0U CN212151309U (en) | 2020-09-25 | 2020-09-25 | Real-time calibration centering spacecraft lifting appliance capable of weighing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022132314.0U CN212151309U (en) | 2020-09-25 | 2020-09-25 | Real-time calibration centering spacecraft lifting appliance capable of weighing |
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| Publication Number | Publication Date |
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| CN212151309U true CN212151309U (en) | 2020-12-15 |
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| CN202022132314.0U Active CN212151309U (en) | 2020-09-25 | 2020-09-25 | Real-time calibration centering spacecraft lifting appliance capable of weighing |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113321126A (en) * | 2021-05-17 | 2021-08-31 | 中国电建集团海南电力设计研究院有限公司 | Fan hoisting platform and hoisting method thereof |
-
2020
- 2020-09-25 CN CN202022132314.0U patent/CN212151309U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113321126A (en) * | 2021-05-17 | 2021-08-31 | 中国电建集团海南电力设计研究院有限公司 | Fan hoisting platform and hoisting method thereof |
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| GR01 | Patent grant | ||
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Effective date of registration: 20210706 Address after: 201203 building C, 888 Huanhu West 2nd Road, Pudong New Area, Shanghai Patentee after: Shanghai Paixing Information Technology Co.,Ltd. Address before: 201210 4th floor, 99 Haike Road, Pudong New Area, Shanghai Patentee before: SHANGHAI SCAS INFORMATION TECH. Co.,Ltd. |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240528 Address after: 201304, Building 1, Building 2, No. 1588 Zhoude Road, Lingang New Area, China (Shanghai) Pilot Free Trade Zone, Pudong New Area, Shanghai Patentee after: SHANGHAI SCAS INFORMATION TECH. CO.,LTD. Country or region after: China Address before: 201203 building C, 888 Huanhu West 2nd Road, Pudong New Area, Shanghai Patentee before: Shanghai Paixing Information Technology Co.,Ltd. Country or region before: China |
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| TR01 | Transfer of patent right |