CN111191334A - Rapid positioning method for laying spacecraft cable network - Google Patents
Rapid positioning method for laying spacecraft cable network Download PDFInfo
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- CN111191334A CN111191334A CN202010004520.5A CN202010004520A CN111191334A CN 111191334 A CN111191334 A CN 111191334A CN 202010004520 A CN202010004520 A CN 202010004520A CN 111191334 A CN111191334 A CN 111191334A
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Abstract
The application discloses a rapid positioning method for laying a cable network of a spacecraft, which comprises the steps of designing a three-dimensional layout of cables according to the structure of the spacecraft, and adding marks of characteristic points in the trend of each cable in the three-dimensional layout; converting the three-dimensional layout drawing into a two-dimensional production drawing, and synchronizing the identification of the characteristic points into the two-dimensional production drawing; generating code codes corresponding to the marks one by one according to the marks of the feature points on the three-dimensional layout drawing, and arranging the code codes on the spacecraft; manufacturing the cable network according to the two-dimensional manufacturing drawing, and arranging the code number on the cable; and determining the position of the cable on the spacecraft according to the code number on the cable. The accuracy, efficiency and reliability of cable network laying are improved.
Description
Technical Field
The invention relates to the technical field of spacecraft assembly integration, in particular to a rapid positioning method for laying a spacecraft cable network.
Background
The cable network is one of the important components of the spacecraft, and is a bond and a bridge of each subsystem and each cabin section. The design of the cable network is a complex system engineering, a set of cable networks with higher design level need to be manufactured from the source, the purposes of reliability, safety design and electromagnetic compatibility design are taken as the goals, the optimal design of the branch relation of the cable networks, accurate connection, correct distribution of joint signals, clear trend, reasonable length, reasonable binding design and clear identification are achieved, and the spacecraft can be reliably, safely and stably supported to complete set tasks in orbit. The spacecraft is a complex system engineering, and the cable network has the characteristics of numerous branches, complex trend and the like, so that the laying efficiency of the cable network is low, and the problems of inaccurate positioning, unreasonable trend and the like often occur.
For example, after a cable of a certain type is three-dimensionally designed, 125 branches are provided, the 125 branches are distributed on 15 devices of 2 cabin sections of the whole star, 10 cabin plates need to be penetrated, and 10 branches need to be taken out of the cabin. The information of the electric connectors on the cable network is the only positioning information in the laying process of the cable network. According to the technical process, the cable network is laid before general equipment is installed, so that the electric connector cannot be accurately assembled at a theoretical design position in the cable laying process, and the installation position of the electric connector can only be roughly determined according to the layout direction of the equipment electric connector. Therefore, in the cable laying process, it is necessary to lay the cables in order from a certain electrical connector of the cable. In the starting point area of laying, the accuracy of laying the route, laying the slack is guaranteed relatively easily, but along with the advance of laying the route, in the position of keeping away from laying the starting point, the accumulative error is bigger and bigger, leads to after equipment fixing in place very easily, when electric connector grafting, length can't satisfy the grafting requirement. In this case, the cable and the electrical connector branch that have already been laid must be reworked and adjusted along the entire laying path, which results in low laying efficiency of the cable network, and multiple reworking adjustments also increase the possibility of damage to the cable network, and ultimately affect the assembly reliability of the cable network.
Disclosure of Invention
In view of the above-mentioned deficiencies or inadequacies in the prior art, it would be desirable to provide a fast positioning method for spacecraft cabling.
In order to overcome the defects of the prior art, the technical scheme provided by the invention is as follows:
the invention provides a rapid positioning method for laying a spacecraft cable network, which is characterized by comprising the following steps:
designing a three-dimensional layout of cables according to the structure of a spacecraft, and adding marks of characteristic points in the direction of each cable in the three-dimensional layout;
converting the three-dimensional layout drawing into a two-dimensional production drawing, and synchronizing the identification of the characteristic points into the two-dimensional production drawing;
generating code codes corresponding to the marks one by one according to the marks of the feature points on the three-dimensional layout drawing, and arranging the code codes on the spacecraft;
manufacturing the cable network according to the two-dimensional manufacturing drawing, and arranging the code number on the cable;
and determining the position of the cable on the spacecraft according to the code number on the cable.
In an embodiment, the method further comprises: and laying the cable to a corresponding position, scanning the mark of the characteristic point on the spacecraft again, and confirming the laying position of the cable.
In one embodiment, the marks of the characteristic points are classified according to parts of the spacecraft and comprise binding point marks, deck-penetrating point marks and cross-cabin section point marks, wherein the binding points are points of the cables on the cable support or the nylon base; the cabin penetrating plate point is a point at which the cable penetrates from one side of the cabin plate to the other side of the cabin plate; the bay section crossing point is the point where the cable passes from one bay section to another.
In one embodiment, adding the identification of the feature point to each cable run in the three-dimensional layout comprises: adding a deck-passing point mark to each cable passing through the deck; adding a cabin penetrating section point identifier to each cable penetrating through the cabin section; and adding a binding point mark to the cable passing through the cable bracket or the nylon base.
Preferably, the binding point of the cable on the cable support or the nylon base is selected to be close to the electric connector.
In one embodiment, when the binding point marks are added to the cables passing through the cable bracket or the nylon base, the number of the branch cables is 5 or less, and the number of the binding point marks cannot be less than 1; for cable branch numbers of 10 and below, the number of tie point identifications cannot be less than 2.
In one embodiment, when the binding point marks are added to the cables passing through the cable bracket or the nylon base, the number of the binding point marks cannot be less than 3 for the number of the cable branches of 20 or less; for cable branch numbers of 30 and below, the number of tie point identifications cannot be less than 4.
In one embodiment, when the binding point marks are added to the cables passing through the cable bracket or the nylon base, the number of the binding point marks cannot be less than 5 for the number of the cable branches of 50 or less; the number of cable branches is more than 50, and the number of the banding point marks cannot be less than 6.
In one embodiment, the code is synchronously completed during the processing of the cable or is adhered to the cable after the processing of the cable is completed.
In one embodiment, the two-dimensional production drawing is a pegboard drawing.
Compared with the prior art, the invention has the beneficial effects that:
according to the scheme, a three-dimensional layout of cables is designed according to the structure of a spacecraft, and the mark of a characteristic point is added to the direction of each cable in the three-dimensional layout; converting the three-dimensional layout drawing into a two-dimensional production drawing, and synchronizing the identification of the characteristic points into the two-dimensional production drawing; generating code codes corresponding to the marks one by one according to the marks of the feature points on the three-dimensional layout drawing, and arranging the code codes on the spacecraft; manufacturing the cable network according to the two-dimensional manufacturing drawing, and arranging the code number on the cable; and determining the position of the cable on the spacecraft according to the code number on the cable. The accuracy, efficiency and reliability of cable network laying are improved.
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 flowchart of a fast positioning method for laying a spacecraft cable network according to an embodiment of the present invention;
fig. 2 is a further flowchart of a fast positioning method for cable net laying of a spacecraft according to an embodiment of the present invention;
fig. 3 is a three-dimensional structure model diagram of a spacecraft, provided by an embodiment of the invention;
FIG. 4 is a schematic view of a cable routing and electrical connector arrangement according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of the positions of feature points in a three-dimensional layout diagram according to an embodiment of the present invention;
fig. 6 is a diagram of an effect of adding feature points in a two-dimensional production diagram according to an embodiment of the present invention.
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.
As mentioned in the background, during the cable laying process, it is necessary to lay the cables in sequence starting from a certain electrical connector of the cable. In the starting point area of laying, the accuracy of laying the route, laying the slack is guaranteed relatively easily, but along with the advance of laying the route, in the position of keeping away from laying the starting point, the accumulative error is bigger and bigger, leads to after equipment fixing in place very easily, when electric connector grafting, length can't satisfy the grafting requirement. In this case, the cable and the electrical connector branch that have already been laid must be reworked and adjusted along the entire laying path, which results in low laying efficiency of the cable network, and multiple reworking adjustments also increase the possibility of damage to the cable network, and ultimately affect the assembly reliability of the cable network.
The invention relates to a method for positioning a cable laying path, which aims to reduce or eliminate errors of the cable laying path and improve the accuracy and efficiency of cable laying, and the method is an improvement direction of the method. Thus, a fast positioning method for the cabling of spacecraft cable networks is provided.
Referring to fig. 1, a method of the present invention for rapid positioning for spacecraft cable net deployment is shown.
In step 110, a three-dimensional layout of cables is designed according to the structure of the spacecraft, and the mark of a feature point is added to the direction of each cable in the three-dimensional layout.
In step 120, the three-dimensional layout map is converted into a two-dimensional production map, and the identification of the feature points is synchronized into the two-dimensional production map.
In step 130, code numbers corresponding to the identifiers one to one are generated according to the identifiers of the feature points on the three-dimensional layout, and the code numbers are arranged on the spacecraft.
In step 140, the cable network is manufactured according to the two-dimensional manufacturing drawing, and the code is arranged on the cable.
In step 150, the position of the cable on the spacecraft is determined based on the code number on the cable.
When the cable network is manufactured according to the two-dimensional manufacturing drawing, the two-dimensional manufacturing drawing adopts a pegboard drawing. The code codes are synchronously finished in the processing process of the cable, or are adhered to the cable after the cable is processed. After the processing is finished, the code is attached to the cable, the position of the code can be changed according to different conditions, and the processing method is flexible. Because the cable can be considered to be disposable, the code can be directly processed on the cable in the manufacturing process of the cable.
As shown in fig. 2, in some preferred embodiments, the method further comprises the step 160: and laying the cable to a corresponding position, scanning the mark of the characteristic point on the spacecraft again, and confirming the laying position of the cable.
In this embodiment, the marks of the feature points are classified by the parts of the spacecraft, and include a binding point mark, a deck penetrating point mark, and a bay crossing point mark, where the binding point is a point of the cable on the cable support or the nylon base, the deck penetrating point is a point where the cable penetrates from one side of the deck to the other side of the deck, and the bay crossing point is a point where the cable penetrates from one bay to the other bay. Preferably, the binding point of the cable on the cable support or the nylon base is selected to be close to the electric connector.
The identification selection principle of the characteristic points is different, and the identification of the characteristic points added to the cable trend in the three-dimensional layout diagram comprises the following steps:
adding a deck-passing point mark to each cable passing through the deck;
adding a cabin penetrating section point identifier to each cable penetrating through the cabin section;
and adding a binding point mark to the cable passing through the cable bracket or the nylon base.
Similarly, the number of selected identifiers of each feature point is also different, taking the binding points as an example:
when binding point marks are added to cables passing through a cable support or a nylon base, the number of the cable branches is 5 or less, and the number of the binding point marks cannot be less than 1; for cable branch numbers of 10 and below, the number of tie point identifications cannot be less than 2.
When binding point marks are added to cables passing through a cable support or a nylon base, the number of the cable branches is 20 or less, and the number of the binding point marks cannot be less than 3; for cable branch numbers of 30 and below, the number of tie point identifications cannot be less than 4.
When binding point marks are added to cables passing through a cable support or a nylon base, the number of the cable branches is 50 or less, and the number of the binding point marks cannot be less than 5; the number of cable branches is more than 50, and the number of the banding point marks cannot be less than 6.
The generation process of the code number codes of the binding points, the code number codes of the cabin penetrating plate points and the code number codes of the cross cabin section points is as follows:
binding points: binding points of the cable, a cable support and a nylon base are generally selected, wherein the code of the binding points is BZ _ cabin board code _ N, and the binding points are close to the electric connector;
and (3) plate penetrating points: the cable penetrates from one side of the cabin plate to the other side of the cabin plate, and the code is CCB _ cabin plate code _ N;
a cross-cabin section point: the cable passes through from one cabin section to another cabin section, and the code is CCD _ cabin section 1 code _ cabin section 2 code _ N;
and N is a positive integer and provides a unique number for each characteristic point.
As shown in FIG. 3, the code number 11-0 is used as the code number of the first deck board 1, the code number 21-0 is used as the code number of the second deck board 2, the code number 22-0 is used as the code number of the third deck board 3, the code number 23-0 is used as the code number of the fourth deck board 4, and the code number 31-0 is used as the code number of the fifth deck board 5. The code XX01 is encoded as the code of the first device 6, the code XX02 is encoded as the code of the second device 7, and the code XX03 is encoded as the code of the third device 8. The first cabin plate 1, the first equipment 6 and the cable support 9 which are arranged on the first cabin plate form a first cabin section, the code number 1-0 is used as the code number of the first cabin section, the second cabin plate 2, the third cabin plate 3, the fourth cabin plate 4, the cable support 9 and the nylon base 10 form a second cabin section, the code number 2-0 is used as the code number of the second cabin section, the fifth cabin plate 5, the second equipment 7, the third equipment 8 and the cable support 9 which are arranged on the fifth cabin plate 5 form a third cabin section, and the code number 3-0 is used as the code number of the third cabin section.
As shown in fig. 4, XX01-X01 is used as the code number of the first electrical connector 12 of the first device 6, XX01-X02 is used as the code number of the second first electrical connector 13 of the first device 6, XX02-X01 is used as the code number of the first second electrical connector 14 of the second device 7, and XX03-X01 is used as the code number of the first third electrical connector 15 of the third device 8. As shown in FIG. 5, a code BZ _11-0_1 is used as a code of a first binding point 16 of a first cabin plate, a code CCB _22-0_1 is used as a code of a first cabin penetrating plate point 17 of a third cabin plate, a code CCD _2-0_3-0_1 is used as a code of a first cabin penetrating point 18 of a third cabin, and a code CCD2-0_3-0_2 is used as a code of a second cabin penetrating point 19 of the third cabin.
As shown in fig. 6, the positions of a first bulkhead binding point 16, a first bulkhead passing point 17, a first bulkhead passing point 18 and a second bulkhead passing point 19 on the third bulkhead, respectively, can be determined on the cable 11 by the above-described quick positioning method. And converting the three-dimensional trend information of the cable into two-dimensional branch length map information, wherein the two-dimensional branch length map information is the basis for processing and producing the cable network under the spacecraft. It is further determined that the first 12 and second 13 first electrical connectors on the first device 6 are at a distance of 400cm and 300cm from the first bay plate first lashing point 16, respectively, the first and second electrical connectors 14 of the second device 7 are at a distance of 400cm from the first bay section point 18 on the third bay section, and the first and third electrical connectors 15 of the third device 8 are at a distance of 400cm from the second bay section point 19 on the third bay section. And after the cable network is processed, the cable network is laid on the spacecraft according to the design trend of the cable network.
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 (10)
1. A method for fast positioning for cable net laying of a spacecraft, characterized in that it comprises:
designing a three-dimensional layout of cables according to the structure of a spacecraft, and adding marks of characteristic points in the direction of each cable in the three-dimensional layout;
converting the three-dimensional layout drawing into a two-dimensional production drawing, and synchronizing the identification of the characteristic points into the two-dimensional production drawing;
generating code codes corresponding to the marks one by one according to the marks of the feature points on the three-dimensional layout drawing, and arranging the code codes on the spacecraft;
manufacturing the cable network according to the two-dimensional manufacturing drawing, and arranging the code number on the cable;
and determining the position of the cable on the spacecraft according to the code number on the cable.
2. A method for the rapid positioning of a spacecraft cabling network according to claim 1, further comprising: and laying the cable to a corresponding position, scanning the mark of the characteristic point on the spacecraft again, and confirming the laying position of the cable.
3. The method of claim 1, wherein the identification of the characteristic points is classified by the parts of the spacecraft, and comprises a binding point identification, a deck plate passing point identification and a bay section crossing point identification, wherein the binding point is a point of the cable on the cable support or the nylon base, the deck plate passing point is a point of the cable passing from one side of a deck plate to the other side of the deck plate, and the bay section crossing point is a point of the cable passing from one bay section to the other bay section.
4. A method for rapid positioning for cable network laying of spacecraft according to claim 3, wherein adding an identification of a feature point on each of said cable runs in said three-dimensional layout comprises:
adding a deck-passing point mark to each cable passing through the deck;
adding a cabin penetrating section point identifier to each cable penetrating through the cabin section;
and adding a binding point mark to the cable passing through the cable bracket or the nylon base.
5. The fast positioning method for spacecraft cable net deployment according to claim 4, wherein when the number of cable branches is 5 or less, the number of binding point markers cannot be less than 1 when adding the binding point markers to cables passing through a cable support or a nylon base; for cable branch numbers of 10 and below, the number of tie point identifications cannot be less than 2.
6. The fast positioning method for spacecraft cable net deployment according to claim 4, characterized in that when the number of cable branches is 20 or less, the number of tie point markers cannot be less than 3 when tie point markers are added to cables passing through a cable support or a nylon base; for cable branch numbers of 30 and below, the number of tie point identifications cannot be less than 4.
7. The fast positioning method for spacecraft cable net deployment according to claim 4, characterized in that when the number of cable branches is 50 or less, the number of tie point markers cannot be less than 5 when the tie point markers are added to the cables passing through the cable support or nylon base; the number of cable branches is more than 50, and the number of the banding point marks cannot be less than 6.
8. A method for the rapid positioning of the laying of a spacecraft cable net according to claim 4, characterized in that the lashing points of the cables on the cable support or the nylon base are chosen close to the electrical connectors.
9. The method of claim 1, wherein the code number is either synchronously completed during the processing of the cable or affixed to the cable after the processing of the cable.
10. The method for the rapid positioning of the laying of a spacecraft cable network according to claim 1, characterized in that the two-dimensional production drawing uses a pegboard drawing.
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| CN202010004520.5A CN111191334A (en) | 2020-01-03 | 2020-01-03 | Rapid positioning method for laying spacecraft cable network |
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| CN202010004520.5A CN111191334A (en) | 2020-01-03 | 2020-01-03 | Rapid positioning method for laying spacecraft cable network |
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