CN218380951U

CN218380951U - Multi-mode detection platform for redundancy and geometric dimension of satellite-borne electronic equipment

Info

Publication number: CN218380951U
Application number: CN202222469691.2U
Authority: CN
Inventors: 田和强; 马洪强; 安金昌; 庞博; 刘军强
Original assignee: Shandong University of Science and Technology
Current assignee: Shandong University of Science and Technology
Priority date: 2022-09-19
Filing date: 2022-09-19
Publication date: 2023-01-24
Anticipated expiration: 2032-09-19

Abstract

The utility model discloses a multi-mode testing platform of satellite-borne electronic equipment surplus thing and geometric dimensions relates to satellite-borne electronic equipment and detects technical field. The multi-mode detection platform for the surplus and the geometric dimension of the satellite-borne electronic equipment comprises a box body and the satellite-borne electronic equipment; the device also comprises a clamping system, a steering system, a flatness detection system, a mechanical interface detection system and an electrical interface pin detection system; the satellite-borne electronic equipment is fixed on the clamping system, and the clamping system is fixed on the box body through the steering system. The steering system comprises a first steering assembly, wherein the first steering assembly comprises a first motor, a first gear, a second gear, a first transmission shaft and a cross beam bracket; the first motor is fixed on the upper chassis, the first gear is fixed on the first motor, the second gear is meshed with the first gear, one end of the first transmission shaft is connected with the second gear, the other end of the first transmission shaft is connected with the beam support, and the beam support is connected with the clamping system through the second transmission shaft.

Description

Multi-mode detection platform for surplus objects and geometric dimensions of satellite-borne electronic equipment

Technical Field

The utility model relates to a testing platform, concretely relates to multi-mode testing platform of satellite-borne electronic equipment surplus thing and geometric dimensions.

Background

The satellite-borne electronic equipment is used as an important component of a space control system, and how to solve the problem of multi-mode detection of redundancy and geometric dimension is of great importance. The methods for detecting the redundancy in the electronic equipment mainly comprise manual detection, such as hand cranking, ear listening and visual detection, and have low accuracy and high false detection rate, and can be easily influenced by a plurality of factors.

At present, no multi-mode device capable of simultaneously detecting the redundancy and the geometric dimension of the satellite-borne electronic device is available, the universality is poor, most devices use a test mode that one detection platform corresponds to one tested device, and a one-to-many high-efficiency test mode cannot be met.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a multi-mode testing platform of satellite-borne electronic equipment redundancy and geometric dimensions can detect satellite-borne electronic equipment redundancy, electric interface contact pin, plane degree and mechanical interface simultaneously to save the human cost, improved the efficiency and the accuracy that detect.

The utility model discloses a realize above-mentioned purpose, adopt following technical scheme:

a multi-mode detection platform for surplus objects and geometric dimensions of satellite-borne electronic equipment comprises a box body and the satellite-borne electronic equipment, wherein an upper chassis and a lower chassis of the box body are connected through a support column; the device also comprises a clamping system, a steering system, a flatness detection system, a mechanical interface detection system and an electrical interface contact pin detection system; the satellite-borne electronic equipment is fixed on the clamping system, and the clamping system is fixed on the box body through the steering system.

Furthermore, the clamping system comprises two clamping components, the clamping system is located in the middle of the box body, the clamping components are located on two sides of the satellite-borne electronic equipment, each clamping component comprises a clamping support, a clamping screw and a locking nut, the clamping screw penetrates through the clamping support to be connected to the satellite-borne electronic equipment, and the locking nut is arranged on the clamping support.

Further, the steering system comprises a first steering assembly and a second steering assembly, wherein the first steering assembly comprises a first motor, a first gear, a second gear, a first transmission shaft and a cross beam bracket; the first motor is fixed on the upper chassis, the first gear is fixed on the first motor, the second gear is meshed with the first gear, one end of the first transmission shaft is connected with the second gear, the other end of the first transmission shaft is connected with the beam support, and the beam support is connected with the clamping system through the second transmission shaft; the second steering assembly comprises a third gear, a fourth gear, a second transmission shaft and a second motor, the second motor is fixed on the beam support, the third gear is connected with the second motor, the fourth gear is meshed with the third gear, and the second transmission shaft penetrates through the beam support and is fixedly connected with the clamping support.

Further, the flatness detection system includes a sensor and a sensor base; the sensor base is fixed on the lower base through the supporting block, a first sliding groove is formed in the sensor base, and the sensor is fixed in the first sliding groove through the connecting plate.

Furthermore, the mechanical interface detection system is fixed on the upper base and comprises a third motor, a fourth motor, a first lead screw, a second lead screw, a sliding column, a spline connecting rod, a fixed platform and a first camera; the third motor is fixed on the upper base plate, the first lead screw is connected with the third motor, the first lead screw is connected with a moving platform, the moving platform is provided with a spline sleeve, the sliding column penetrates through the moving platform and is fixed on a tray, the tray is fixed on the box body, the moving platform is connected with a fourth motor, the fourth motor is connected with the second lead screw, one end of the second lead screw is connected with a first bearing seat, and the other end of the second lead screw is connected with a spline connecting rod; a first bearing is arranged in the first bearing seat, the inner diameter of the first bearing is connected with the second lead screw, and the outer diameter of the first bearing is connected with the first bearing seat; the spline connecting rod passes through the spline housing and is connected with fixed platform, and first camera is fixed on fixed platform.

Furthermore, the electric interface contact pin detection system is fixed on one side of the clamping system and comprises a gantry support, a fifth motor, a sixth motor, a rack, a fifth gear, a third lead screw, a second camera and a connecting block; the fifth motor is fixed on the gantry support, the third lead screw is connected with the fifth motor, a synchronizing assembly is arranged on the third lead screw, the second camera is fixed on the synchronizing assembly through a connecting block, the sixth motor is fixed at the bottom of the gantry support and connected with the fifth gear through a third transmission shaft, and the rack is meshed with the fifth gear and fixed on the lower chassis.

Furthermore, the synchronizing assembly comprises a seventh motor, a synchronizing belt wheel and a synchronizing belt, the synchronizing assembly is fixed on the third screw rod through a sliding support, a linkage shaft is arranged in the middle of the synchronizing belt wheel and connected with the seventh motor, and a second bearing is arranged at the joint of the linkage shaft and the fixing seat.

Furthermore, a through hole is formed in the connecting block, and the synchronous belt penetrates through the through hole and is fixed on the synchronous belt pulley.

Furthermore, sliding assemblies are arranged on two sides of the gantry support and comprise sliding rails and sliding blocks, the sliding block on one side is located at the bottom of the gantry support through a supporting table, the sliding block on the other side is connected with a sixth motor through the supporting table, the sliding rails are fixed on the lower chassis, and the sliding blocks are fixed on the sliding rails.

Furthermore, a second sliding groove is formed in the fixed platform, and the first camera is fixed in the second sliding groove.

Compared with the prior art, the utility model, following advantage and beneficial effect have:

the utility model discloses can replace the process that artifical detected completely to detect the redundancy and detect the process of several differences with the geometric dimensions and combine together and accomplish on same platform, can realize the accuracy, the rapid detection out the redundancy in the not unidimensional satellite-borne electronic equipment, and can detect the size of satellite-borne electronic equipment mounting surface's plane degree and mechanical interface bore. The clamping system can clamp satellite-borne electronic equipment with different sizes, can perfectly avoid abnormal conditions such as mechanical interface caliber size, contact pin shrinkage, askew pin and the like, and effectively improves the detection efficiency and precision when the sanitation leaves the factory.

Drawings

Fig. 1 is a schematic diagram of a multi-modal detection platform for redundancy and geometry of a satellite-borne electronic device.

Fig. 2 is a schematic view of the connection of the clamping system and the steering system.

FIG. 3 is a schematic view of a flatness detection system.

FIG. 4 is a schematic diagram of a mechanical interface detection system.

FIG. 5 is a side view of a mechanical interface detection system.

Fig. 6 is a schematic diagram of an electrical interface pin detection system.

FIG. 7 is a diagram of a synchronization module.

Detailed Description

With reference to fig. 1 to 7, a multi-modal detection platform for excess and geometric dimension of satellite-borne electronic devices includes a box 1 and satellite-borne electronic devices 2, wherein upper and lower chassis of the box 1 are connected through a strut 3; the device also comprises a clamping system 4, a steering system 5, a flatness detection system 6, a mechanical interface detection system 7 and an electrical interface pin detection system 8; the satellite-borne electronic equipment 2 is fixed on the clamping system 3, and the clamping system 4 is fixed on the box body 1 through the steering system 5. The tested satellite-borne electronic equipment 2 is fixed on the clamping system 4, the steering system 5 can enable the satellite-borne electronic equipment 2 to move and rotate, and the planeness detection system 6, the mechanical interface detection system 7 and the electrical interface pin detection system 8 can detect the satellite-borne electronic equipment 2 more comprehensively.

The clamping system 4 is composed of two clamping assemblies 40, the clamping system 4 is located in the middle of the box body 1, the clamping assemblies 40 are located on two sides of the satellite-borne electronic device 2, each clamping assembly 40 comprises a clamping support 41, a clamping screw 42 and a locking nut 43, the clamping screw 42 penetrates through the clamping support 41 and is connected to the satellite-borne electronic device 2, and the clamping screw 42 is connected with the locking nut 43. The clamping support 41 is of a symmetrical structure, the clamping screw 42 penetrates through the clamping support 41 to fix the satellite-borne electronic equipment 2, a nut 44 is arranged at the joint of the clamping support 41 and the inner side of the clamping screw 42, a locking nut 43 is arranged on the outermost side of the clamping screw 42, fixing of different satellite-borne electronic equipment can be achieved through the nut 44, and the clamping support 41 is of an up-and-down symmetrical structure and can be used for fixing two satellite-borne electronic equipment 2 at the same time.

The steering system 5 includes a first steering assembly including a first motor 50, a first gear 51, a second gear 52, a first transmission shaft 53, and a cross member bracket 54; the first motor 50 is fixed on the upper chassis 11, the first gear 51 is fixed on the first motor 50, the second gear 52 is meshed with the first gear 51, one end of the first transmission shaft 53 is connected with the second gear 52, the other end of the first transmission shaft is connected with the cross beam bracket 54, and the cross beam bracket 54 is connected with the clamping system 4 through the second transmission shaft 55; the first steering assembly can enable the clamping system 4 to drive the satellite-borne electronic equipment 2 to rotate in the left-right direction, and therefore the satellite-borne electronic equipment 2 can be detected more comprehensively.

The second steering assembly comprises a third gear 56, a fourth gear 57, a second transmission shaft 55 and a second motor 59, the second motor 59 is fixed on the cross beam bracket 54, the third gear 56 is connected with the second motor 59, the fourth gear 57 is meshed with the third gear 56, and the second transmission shaft 55 penetrates through the cross beam bracket 54 and is fixedly connected with the clamping bracket 41. The second motor 59 can enable the satellite-borne electronic equipment 2 to rotate in the up-down direction, and therefore the satellite-borne electronic equipment 2 can be detected more comprehensively. The second motor 59 can also swing back and forth, and can control the clamping system 4 to vibrate the satellite-borne electronic device 2, so as to achieve the purpose of cleaning the redundant objects in the satellite-borne electronic device 2.

The flatness detection system 6 includes a sensor 61 and a sensor base 62; the sensor base 62 is fixed on the lower base 12 through a supporting block 63, a first sliding groove 64 is formed in the sensor base 62, and the sensor 61 is fixed in the first sliding groove 64 through a connecting plate 65. The sensor base 62 can slide in the first sliding groove 64, and since the satellite electronic device 2 has different sizes, when the plane detection system 6 detects the satellite electronic device, sliding focusing is required. Because the plane detection system 6 can only detect half of the satellite-borne electronic equipment 2, the rotation system 5 is required to be matched, so that the satellite-borne electronic equipment 2 can be comprehensively detected, the detection is more accurate, and the efficiency is higher.

The mechanical interface detection system 7 is fixed on the upper base plate 11 and comprises a third motor 70, a fourth motor 71, a first lead screw 72, a second lead screw 73, a sliding column 74, a spline connecting rod 75, a fixed platform 76 and a first camera 77; the third motor 70 is fixed on the upper base plate 11, the first lead screw 72 is connected with the third motor 70, the first lead screw 72 is connected with the moving platform 78, the moving platform 78 is provided with a spline sleeve 79, the sliding column 74 penetrates through the moving platform 78 and is fixed on the tray 704, the tray 704 is fixed on the box body 1, the moving platform 78 is connected with the fourth motor 71, the fourth motor 71 is connected with the second lead screw 73, one end of the second lead screw 73 is connected with the first bearing seat 701, and the other end of the second lead screw 73 is connected with the spline connecting rod 75; a first bearing 702 is arranged in the first bearing seat 701, the inner diameter of the first bearing 702 is connected with the second lead screw 73, and the outer diameter of the first bearing 702 is connected with the first bearing seat 701; the spline link 75 is connected to the fixed platform 76 through the spline housing 79, and the first camera 77 is fixed to the fixed platform 76. The fixed platform 76 is provided with a second sliding groove 703, and the first camera 77 is fixed in the second sliding groove 703. The third motor 70 enables the first camera 77 to move in the vertical direction, the fourth motor 71 enables the first camera 77 to move in the front-rear direction, the first camera 77 can slide in the second sliding groove 703 to move in the left-right direction, and therefore the first camera 77 can move in three directions, and the first camera 77 has three degrees of freedom, so that the mechanical interface can be detected more conveniently and efficiently. The mechanical interface detection system 7 can detect the upper satellite-borne electronic equipment 2, and after the detection is finished, the steering system 5 can enable the upper satellite-borne electronic equipment and the lower satellite-borne electronic equipment to be transposed, so that the satellite-borne electronic equipment 2 can be comprehensively detected.

The electrical interface pin detection system 8 is fixed on one side of the clamping system 4 and comprises a gantry bracket 80, a fifth motor 81, a sixth motor 82, a rack 83, a fifth gear 84, a third lead screw 85, a second camera 87 and a connecting block 86; the fifth motor 81 is fixed on the gantry support 80, the third lead screw 85 is connected with the fifth motor 81, a synchronizing assembly is arranged on the third lead screw 85, the second camera 87 is fixed on the synchronizing assembly through a connecting block 86, the sixth motor 82 is fixed at the bottom of the gantry support 80, the sixth motor 82 is connected with the fifth gear 84 through a third transmission shaft 89, the rack 83 is meshed with the fifth gear 84, and the rack 83 is fixed on the lower chassis 12. The gantry support 80 is bilaterally symmetrical, the fifth motor 81 is located at the upper left of the gantry support 80, and when the fifth motor 81 moves, the third lead screw 85 rotates to drive the synchronization assembly to move up and down, so that the second camera 87 moves up and down.

The synchronous assembly comprises a seventh motor, a synchronous belt wheel 803 and a synchronous belt 801, the synchronous assembly is fixed on the third screw rod 85 through a sliding support 802, a linkage shaft 88 is arranged in the middle of the synchronous belt wheel 803, and the linkage shaft 88 is connected with the seventh motor. A through hole is arranged on the connecting block 86, and the synchronous belt 801 passes through the through hole and is fixed on the synchronous belt wheel 803. When the seventh motor is moved, the timing pulley 803 is rotated, and the timing belt 801 engaged with the timing pulley 803 is also moved, thereby driving the second camera 87 fixed to the timing belt 801 to move in the left-right direction.

Two sides of the gantry support 80 are provided with sliding components, each sliding component comprises a sliding rail 91 and a sliding block 92, the sliding block 92 on one side is fixed at the bottom of the gantry support 80 through a support table 93, the sliding block 92 on the other side is connected with the sixth motor 82 through the support table 93, the sliding rails 91 are fixed on the lower chassis 12, and the sliding blocks 92 are fixed on the sliding rails 91. The right side of the gantry bracket 80 is connected with a sixth motor 82, the sixth motor 82 is connected with a fifth gear 84 through a third transmission shaft 89, and when the sixth motor 82 moves, the fifth gear 84 is driven to move on the rack 83 to drive the second camera 87 to move in the front-back direction. The sixth motor 82 is fixed on the sliding rail 91 through a sliding block 92, and the sliding assembly can help the fifth gear 84 and the rack 83 increase the bearing capacity, so that the movement is smoother.

Of course, the above description is not intended to limit the present invention, and the present invention is not limited to the above examples, and the changes, modifications, additions or substitutions made by those skilled in the art within the scope of the present invention should also belong to the protection scope of the present invention.

Claims

1. A multi-mode detection platform for surplus objects and geometric dimensions of satellite-borne electronic equipment comprises a box body and the satellite-borne electronic equipment, wherein an upper chassis and a lower chassis of the box body are connected through struts; the device is characterized by also comprising a clamping system, a steering system, a flatness detection system, a mechanical interface detection system and an electrical interface contact pin detection system; the satellite-borne electronic equipment is fixed on a clamping system, and the clamping system is fixed on the box body through a steering system.

2. The multi-modal detection platform for surplus objects and geometric dimensions of satellite-borne electronic equipment according to claim 1, wherein the clamping system is composed of two clamping assemblies, the clamping system is located in the middle of the box body, the clamping assemblies are located on two sides of the satellite-borne electronic equipment, each clamping assembly comprises a clamping bracket, a clamping screw and a locking nut, the clamping screw penetrates through the clamping bracket and is connected to the satellite-borne electronic equipment, and the locking nut is arranged on the clamping bracket.

3. The multi-modal space borne electronic device redundancy and geometry detection platform of claim 1, wherein the steering system comprises a first steering assembly and a second steering assembly, the first steering assembly comprising a first motor, a first gear, a second gear, a first transmission shaft, and a cross beam bracket; the first motor is fixed on the upper chassis, the first gear is fixed on the first motor, the second gear is meshed with the first gear, one end of the first transmission shaft is connected with the second gear, the other end of the first transmission shaft is connected with the beam support, and the beam support is connected with the clamping system through the second transmission shaft; the second steering assembly comprises a third gear, a fourth gear, a second transmission shaft and a second motor, the second motor is fixed on the beam support, the third gear is connected with the second motor, the fourth gear is meshed with the third gear, and the second transmission shaft penetrates through the beam support and is fixedly connected with the clamping support.

4. The multi-modal spaceborne electronic device redundancy and geometry detection platform as recited in claim 1, wherein the flatness detection system comprises a sensor and a sensor base; the sensor base is fixed on the lower base through the supporting block, a first sliding groove is formed in the sensor base, and the sensor is fixed in the first sliding groove through the connecting plate.

5. The multi-modal detection platform of the redundancy and the geometric dimension of the satellite-borne electronic device according to claim 1, wherein the mechanical interface detection system is fixed to the upper base and comprises a third motor, a fourth motor, a first lead screw, a second lead screw, a sliding column, a spline connecting rod, a fixed platform and a first camera; the third motor is fixed on the upper base plate, the first lead screw is connected with the third motor, the first lead screw is connected with a moving platform, the moving platform is provided with a spline sleeve, the sliding column penetrates through the moving platform and is fixed on a tray, the tray is fixed on the box body, the moving platform is connected with a fourth motor, the fourth motor is connected with the second lead screw, one end of the second lead screw is connected with a first bearing seat, and the other end of the second lead screw is connected with a spline connecting rod; a first bearing is arranged in the first bearing seat, the inner diameter of the first bearing is connected with the second lead screw, and the outer diameter of the first bearing is connected with the first bearing seat; the spline connecting rod penetrates through the spline sleeve to be connected with the fixed platform, and the first camera is fixed on the fixed platform.

6. The multi-modal detection platform for the redundancy and the geometric dimension of the satellite-borne electronic equipment according to claim 1, wherein the electrical interface pin detection system is fixed on one side of the clamping system and comprises a gantry support, a fifth motor, a sixth motor, a rack, a fifth gear, a third lead screw, a second camera and a connecting block; the fifth motor is fixed on the gantry support, the third lead screw is connected with the fifth motor, a synchronizing assembly is arranged on the third lead screw, the second camera is fixed on the synchronizing assembly through a connecting block, the sixth motor is fixed at the bottom of the gantry support and connected with the fifth gear through a third transmission shaft, and the rack is meshed with the fifth gear and fixed on the lower chassis.

7. The multi-modal detection platform for surplus objects and geometric dimensions of satellite-borne electronic equipment according to claim 6, wherein the synchronization assembly comprises a seventh motor, a synchronization pulley and a synchronization belt, the synchronization assembly is fixed on a third lead screw through a sliding support, a linkage shaft is arranged in the middle of the synchronization pulley, the linkage shaft is connected with the seventh motor, and a second bearing is arranged at the joint of the linkage shaft and the fixed seat.

8. The multi-modal detection platform for surplus objects and geometric dimensions of satellite-borne electronic equipment according to claim 6, wherein through holes are formed in the connecting blocks, and the synchronous belt passes through the through holes and is fixed on the synchronous belt pulley.

9. The multi-modal detection platform for surplus objects and geometric dimensions of satellite-borne electronic equipment according to claim 6, wherein sliding assemblies are arranged on two sides of the gantry support and comprise sliding rails and sliding blocks, the sliding block on one side is located at the bottom of the gantry support through a support table, the sliding block on the other side is connected with a sixth motor through a support table, the sliding rails are fixed on the lower chassis, and the sliding blocks are fixed on the sliding rails.

10. The multi-modal detection platform of surplus and geometric dimensions of satellite-borne electronic devices according to claim 5, wherein a second sliding groove is formed in the fixed platform, and the first camera is fixed in the second sliding groove.