Fixing device for satellite-borne cable harness secondary isolation and installation method

Abstract

The invention relates to the technical field of spacecraft spaceborne cable laying, in particular to a fixing device for secondary isolation of spaceborne cable bunches and an installation method.A first cable bunch is bound to a first longitudinal rod and a third longitudinal rod through a binding belt, a second cable bunch is bound to a second longitudinal rod and a fourth longitudinal rod through a binding belt, and the second longitudinal rod and the fourth longitudinal rod are bound through a binding belt; the third cable bundle is bound on the outer side of the first trapezoidal frame through a binding belt, the fourth cable bundle is bound on the outer side of the second trapezoidal frame through a binding belt, and the fifth cable bundle is bound between the first trapezoidal frame and the second trapezoidal frame through a binding belt; the arrangement of a single cable bundle, two cable bundles, three cable bundles, four cable bundles and five cable bundles is further realized, and a user can flexibly arrange and bind the cable bundles according to the number of the cable bundles needing to be arranged, so that the technical scheme of the invention is higher in universality and flexibility.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft onboard cable laying, and in particular to a fixing device and an installation method for secondary isolation of a spacecraft onboard cable bundle. Background Art

[0002] As spacecraft products develop towards the direction of product diversification and product function complexity, higher requirements are put forward for the assembly design of cables inside spacecraft. In order to ensure that the high-frequency cables, low-frequency cables and bus cables on board meet the requirements of electromagnetic compatibility, it is necessary to carry out secondary isolation design for distribution cables, pyrotechnic cables, signal cables, etc.; the interval between two adjacent cables inside the main power cable is at least 10mm according to the different types of subdivisions; therefore, it is necessary to design an independent cable path channel on the satellite.

[0003] Satellite cable harnesses are responsible for the important tasks of signal transmission and power distribution within the satellite system and between satellite and external equipment. Satellite cable harnesses are usually composed of multiple wires or cables with specific functions. Satellite cable harnesses are resistant to high temperatures, corrosion, radiation, lightweight, and have good electrical insulation and signal transmission performance to meet the stable operation requirements of satellites in extreme space environments.

[0004] As the current requirements for satellite-borne design payload power continue to increase, the satellite configuration and the layout of the instruments and equipment in the cabin are becoming more and more compact. It is impossible to implement the independent branching design between the distribution cables and signal cables within the existing space, and it is also impossible to implement the isolation design of the cables inside the main bundle. Therefore, it is particularly important to implement the isolation design of more cable bundles on the public cable channel in the field of satellite assembly design.

[0005] At present, the secondary physical isolation of spacecraft is designed by tying cable bundles together on a bracket fixing point to achieve the mutual physical isolation between cables. At present, the secondary physical isolation of spacecraft is designed by tying cable bundles together on a bracket fixing point to achieve the mutual physical isolation between cables. In actual use, there are the following shortcomings:

[0006] The diameter of the cable that can be tied at a single bracket fixing point is small, and the addition of heat shrink cloth as cable isolation material makes the diameter of the cable that can be tied at a single point even smaller, which cannot meet the needs of isolating multiple types and directions of cables in the main cable channel; the allowable width of the heat shrink cloth is only 25mm-50mm, and the secondary insulation requirements are not met at the parallel connection of the wire harnesses outside the combined binding points.

[0007] To solve this problem, existing spacecraft often use round rod-shaped cable brackets. Please refer to the attached manual. Figure 1 As shown, the cable bundles are fixed on round rods in high and low layers to achieve cable binding and fixation. Although this method can ensure that the spacing between cable bundles meets the requirements of physical isolation, this isolation method still has the following technical pain points:

[0008] The two-layer cable bracket is at least 80mm high, and the three-layer cable bracket is at least 140mm high, which seriously occupies the space inside the spacecraft in the vertical direction and reduces the effective load ratio;

[0009] The cable bundles layered at high altitudes have a high center of mass and a large vibration response. The cables do not have a fixed binding position on the round rod bracket, and may slide along the round rod during vibration. In extreme cases, there is a possibility that the cable bundles will slip off the top of the round rod. The existing brackets cannot solve the need to simultaneously fix complex cables in multiple directions on satellites and rockets.

[0010] Therefore, how to reduce the space occupied by multiple bundles of cables inside the spacecraft and maintain the stability of their installation while achieving the effect of physical isolation has become a technical problem that needs to be urgently solved by technical personnel in this field. The present invention can solve the need to simultaneously bind and fix multiple bundles of cables in multiple directions. Summary of the invention

[0011] The present invention provides a fixing device and an installation method for secondary isolation of satellite-borne cable bundles, which are used to solve the problem of how to reduce the space occupied by multiple bundles of cables laid inside a spacecraft and maintain the stability of their installation while achieving the effect of physical isolation.

[0012] In a first aspect, the present invention provides a fixing device for secondary isolation of a satellite-borne cable bundle, comprising a first longitudinal rod 1, a third longitudinal rod 2, a first trapezoidal frame 3, a first transverse support rod 4, a fourth longitudinal rod 5, a second longitudinal rod 6, a second transverse support rod 7, a second trapezoidal frame 8, a bottom plate 9 and a bolt hole 10;

[0013] A first longitudinal rod 1 is installed at one end of the bottom plate 9, a second longitudinal rod 6 is installed at the other end of the bottom plate 9, a first trapezoidal frame 3 and a second trapezoidal frame 8 are relatively installed in the middle of the bottom plate 9, and a third longitudinal rod 2 and a fourth longitudinal rod 5 are connected between the first trapezoidal frame 3 and the second trapezoidal frame 8;

[0014] A second transverse support rod 7 is installed in the middle of the second trapezoidal frame 8, a first transverse support rod 4 is installed in the middle of the first trapezoidal frame 3, a bolt hole 10 is provided at the bottom of the base plate 9, and the third longitudinal rod 2, the fourth longitudinal rod 5, the first transverse support rod 4 and the second transverse support rod 7 are used to carry the satellite cable bundle.

[0015] In some of the embodiments, a fixing device for secondary isolation of a satellite-borne cable bundle according to claim 1;

[0016] A first through hole is provided between the second trapezoidal frame 8 and the bottom plate 9, a second through hole is provided between the first trapezoidal frame 3 and the bottom plate 9, a third through hole is provided between the fourth longitudinal rod 5 and the first trapezoidal frame 3, the second trapezoidal frame 8 and the bottom plate 9, a fourth through hole is provided between the third longitudinal rod 2 and the first trapezoidal frame 3, the second trapezoidal frame 8 and the bottom plate 9, a fifth through hole is provided between the first longitudinal rod 1 and the bottom plate 9, a sixth through hole is provided between the second longitudinal rod 6 and the bottom plate 9, a sixth through hole is provided between the first trapezoidal frame 3, the second trapezoidal frame 8, the third longitudinal rod 2 and the fourth longitudinal rod 5, and the first through hole, the second through hole, the third through hole, the fourth through hole, the fifth through hole and the sixth through hole are used to pass the satellite cable bundle.

[0017] In some of the embodiments, a fixing device for secondary isolation of a satellite-borne cable bundle according to claim 1;

[0018] The first longitudinal rod 1 and the second longitudinal rod 6 are inclined downward from the top, and a first groove is arranged between the first longitudinal rod 1 and the bottom plate 9, the first trapezoidal frame 3 and the second trapezoidal frame 8. A second groove is arranged between the second longitudinal rod 6 and the bottom plate 9, the first trapezoidal frame 3 and the second trapezoidal frame 8. The first groove and the second groove are used to pass the satellite cable bundle, the second transverse support rod 7 is used to divide the first through hole between the second trapezoidal frame 8 and the bottom plate 9 into two through holes, the first transverse support rod 4 is used to divide the second through hole between the first trapezoidal frame 3 and the bottom plate 9 into two through holes, and a third groove is arranged on the top of the third longitudinal rod 2, the first trapezoidal frame 3, the fourth longitudinal rod 5 and the second trapezoidal frame 8.

[0019] In some of the embodiments, a fixing device for secondary isolation of a satellite-borne cable bundle according to claim 1;

[0020] The first groove and the second groove are used to fix two bundles of parallel cables respectively, and the third groove is used to fix a bundle of cables. The bundle of cables fixed on the third groove is in a perpendicular state to the two bundles of cables fixed on the first groove and the second groove.

[0021] In a second aspect, the present invention provides an installation method for secondary isolation of a satellite-borne cable bundle, which is applied to the fixing device for secondary isolation of a satellite-borne cable bundle, and comprises the following steps:

[0022] S1. Bolt the fixed frame to the location where the cable bundle is to be installed;

[0023] S2, tying the first cable bundle to the first longitudinal rod and the third longitudinal rod by passing a cable tie around the first longitudinal rod and the third longitudinal rod;

[0024] S3. Tie the second cable bundle to the second longitudinal rod and the fourth longitudinal rod by passing a cable tie around the second longitudinal rod and the fourth longitudinal rod.

[0025] In some of the embodiments, the method further includes step S4 of tying the third cable bundle to the outside of the first trapezoidal frame by wrapping a cable tie around the first trapezoidal frame and the first transverse support rod.

[0026] In some of the embodiments, the method further includes step S5 of tying the fourth cable bundle to the outside of the second trapezoidal frame by wrapping a cable tie around the second trapezoidal frame and the second transverse support rod.

[0027] In some of the embodiments, the method further includes step S6 of binding the fifth cable bundle between the first trapezoidal frame and the second trapezoidal frame by wrapping a cable tie around the first trapezoidal frame and the second trapezoidal frame.

[0028] In some embodiments, the first cable bundle and the second cable bundle are located parallel to each other.

[0029] In some embodiments, the third cable bundle, the fourth cable bundle, and the fifth cable bundle are positioned parallel to each other.

[0030] In some embodiments, the first cable bundle and the second cable bundle are located perpendicular to the third cable bundle, the fourth cable bundle, and the fifth cable bundle.

[0031] In some embodiments, the first cable bundle, the second cable bundle, the third cable bundle, the fourth cable bundle, and the fifth cable bundle are all bound with heat shrinkable cloth at their binding locations.

[0032] In some of the embodiments, the distance between two adjacent cable bundles is greater than 10 mm.

[0033] In some embodiments, the first cable bundle, the second cable bundle, the third cable bundle, the fourth cable bundle and the fifth cable bundle are all tied into bundles by cotton thread.

[0034] The beneficial effects of the present invention are as follows: the present invention realizes the secondary isolation of the cables on the cable channel without modifying the fasteners on the cable channel of the satellite-borne spacecraft. On the path of the minimum cable channel, the effect of laying multiple bundles of cables in a limited space is achieved by using a fixed frame, and the prior art needs to determine the height of the bracket according to the specific number of cables, and the laying direction is single, while in the present invention, the laying of a single cable bundle, two cable bundles, three cable bundles, four cable bundles, and five cable bundles can be realized, and the user can flexibly arrange and tie according to the required number of cable bundles. At the same time, in the technical solution of the present invention, in addition to arranging the cable bundle in the horizontal direction, it can also be arranged in the vertical direction, and the two laying methods can be used crosswise, making the technical solution of the present invention more versatile, and the cable bundle binding positions are all tied with heat shrink cloth, which solves the secondary insulation problem when fixing multiple bundles of cables, and now increases the cable passage efficiency. The technical solution of the present invention has the advantages of high flexibility, strong operability and low cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 A schematic diagram of the structure of a round rod-shaped cable support in the prior art;

[0036] Figure 2 It is a structural schematic diagram of a fixed frame in an installation method for secondary isolation of a satellite-borne cable bundle according to the present invention;

[0037] Figure 3 yes Figure 1 A schematic structural diagram of another perspective of a fixed frame in an installation method for secondary isolation of a satellite-borne cable bundle is shown;

[0038] Figure 4 It is a structural schematic diagram of some embodiments of the installation of a single cable bundle in an installation method for secondary isolation of a satellite-borne cable bundle;

[0039] Figure 5 It is a structural schematic diagram of some embodiments of the installation of two cable bundles in the installation method for secondary isolation of a satellite-borne cable bundle;

[0040] Figure 6 It is a structural schematic diagram of some embodiments of the installation of three cable bundles in the installation method for secondary isolation of a satellite-borne cable bundle;

[0041] Figure 7 It is a structural schematic diagram of other embodiments of the installation of three cable bundles in the installation method for secondary isolation of satellite-borne cable bundles;

[0042] Figure 8 The present invention is a structural schematic diagram of some embodiments of the installation of five cable bundles in an installation method for secondary isolation of a satellite-borne cable bundle.

[0043] Fig. 9 The invention is a structural schematic diagram of an embodiment of cable bundle installation in an installation method for secondary isolation of a satellite-borne cable bundle.

[0044] In the attached drawings, 1, first longitudinal rod; 2, third longitudinal rod; 3, first trapezoidal frame; 4, first transverse support rod; 5, fourth longitudinal rod; 6, second longitudinal rod; 7, second transverse support rod; 8, second trapezoidal frame; 9, bottom plate; 10, bolt hole. DETAILED DESCRIPTION

[0045] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0046] As described in the background technology, currently, spacecraft often use round rod-shaped cable brackets, such as Figure 1 As shown, the cable bundles are fixed on round rods in high and low layers to achieve cable binding and fixation. Although this method can ensure that the spacing between cable bundles meets the requirements of physical isolation, this isolation method still has several problems:

[0047] The parallel two-layer cable bracket is at least 80mm high, and the three-layer cable bracket is at least 140mm high, which seriously occupies the space inside the spacecraft in the vertical direction and reduces the effective load ratio;

[0048] The cable bundles layered at high places have a high center of mass and a large vibration response. The cables do not have a fixed binding position on the round rod bracket, and may slide along the round rod during vibration. In extreme cases, there is a possibility that the cable bundles will slip off the top of the round rod.

[0049] To ensure strength, the round rod bracket can only be processed by turning and milling in one piece, which is difficult to process, has a high scrap rate, a long processing cycle and high cost.

[0050] Therefore, how to reduce the space occupied by multiple cables inside the spacecraft and maintain the stability of their installation while achieving the effect of physical isolation has become a technical problem that needs to be urgently solved by technical personnel in this field.

[0051] To solve the above technical problems, please refer to Figure 2 as well as Figure 3 The present invention provides a fixing device for secondary isolation of a satellite-borne cable bundle, comprising a first longitudinal rod 1, a third longitudinal rod 2, a first trapezoidal frame 3, a first transverse support rod 4, a fourth longitudinal rod 5, a second longitudinal rod 6, a second transverse support rod 7, a second trapezoidal frame 8, a bottom plate 9 and a bolt hole 10;

[0052] A first longitudinal rod 1 is installed at one end of the bottom plate 9, a second longitudinal rod 6 is installed at the other end of the bottom plate 9, a first trapezoidal frame 3 and a second trapezoidal frame 8 are relatively installed in the middle of the bottom plate 9, and a third longitudinal rod 2 and a fourth longitudinal rod 5 are connected between the first trapezoidal frame 3 and the second trapezoidal frame 8;

[0053] A second transverse support rod 7 is installed in the middle of the second trapezoidal frame 8, a first transverse support rod 4 is installed in the middle of the first trapezoidal frame 3, a bolt hole 10 is provided at the bottom of the base plate 9, and the third longitudinal rod 2, the fourth longitudinal rod 5, the first transverse support rod 4 and the second transverse support rod 7 are used to carry the satellite cable bundle.

[0054] In some of the embodiments, a fixing device for secondary isolation of a satellite-borne cable bundle according to claim 1;

[0055] A first through hole is provided between the second trapezoidal frame 8 and the bottom plate 9, a second through hole is provided between the first trapezoidal frame 3 and the bottom plate 9, a third through hole is provided between the fourth longitudinal rod 5 and the first trapezoidal frame 3, the second trapezoidal frame 8 and the bottom plate 9, a fourth through hole is provided between the third longitudinal rod 2 and the first trapezoidal frame 3, the second trapezoidal frame 8 and the bottom plate 9, a fifth through hole is provided between the first longitudinal rod 1 and the bottom plate 9, a sixth through hole is provided between the second longitudinal rod 6 and the bottom plate 9, a sixth through hole is provided between the first trapezoidal frame 3, the second trapezoidal frame 8, the third longitudinal rod 2 and the fourth longitudinal rod 5, and the first through hole, the second through hole, the third through hole, the fourth through hole, the fifth through hole and the sixth through hole are used to pass the satellite cable bundle.

[0056] In some of the embodiments, a fixing device for secondary isolation of a satellite-borne cable bundle according to claim 1;

[0057] The first longitudinal rod 1 and the second longitudinal rod 6 are inclined downward from the top, and a first groove is arranged between the first longitudinal rod 1 and the bottom plate 9, the first trapezoidal frame 3 and the second trapezoidal frame 8. A second groove is arranged between the second longitudinal rod 6 and the bottom plate 9, the first trapezoidal frame 3 and the second trapezoidal frame 8. The first groove and the second groove are used to pass the satellite cable bundle, the second transverse support rod 7 is used to divide the first through hole between the second trapezoidal frame 8 and the bottom plate 9 into two through holes, the first transverse support rod 4 is used to divide the second through hole between the first trapezoidal frame 3 and the bottom plate 9 into two through holes, and a third groove is arranged on the top of the third longitudinal rod 2, the first trapezoidal frame 3, the fourth longitudinal rod 5 and the second trapezoidal frame 8.

[0058] In some of the embodiments, a fixing device for secondary isolation of a satellite-borne cable bundle according to claim 1;

[0059] The first groove and the second groove are used to fix two bundles of parallel cables respectively, and the third groove is used to fix a bundle of cables. The bundle of cables fixed on the third groove is in a perpendicular state to the two bundles of cables fixed on the first groove and the second groove.

[0060] The main feature of the present invention is that it can realize the binding and fixing of different cables in the same direction and vertical direction of multiple cable bundles:

[0061] The main feature of the present invention is that it can provide a second, third, fourth, fifth, sixth, seventh, eighth and ninth cable binding fulcrums, which are a total of eight cable binding fulcrums. According to the binding requirements of the cables on the cable path, by selecting different cable binding fulcrums, the cable binding and fixing requirements are met;

[0062] The present invention can realize the binding and fixing of a bundle of cables above the bracket through the third cable binding fulcrum and the eighth cable binding fulcrum;

[0063] The present invention can achieve the binding and fixing of two bundles of cables arranged side by side by binding one bundle of cables at the seventh and eighth cable fulcrums and binding one bundle of cables at the third and fourth cable fulcrums;

[0064] The present invention can achieve the tying and fixing of two bundles of cables side by side by tying a bundle of cables at the first and second cable fulcrums and tying a bundle of cables at the fifth and sixth cable fulcrums:

[0065] The present invention can bind a cable in a vertical direction through the first and second cable fulcrums, bind a bundle of cables in a vertical direction through the fifth and sixth cable fulcrums, and bind a bundle of cables in a vertical direction through the third and eighth cable fulcrums, thereby realizing the binding and fixing of three bundles of cables in a vertical and cross direction;

[0066] The present invention can achieve the binding and fixing of three bundles of cables in parallel by binding a bundle of cables at the third and eighth cable fulcrums, binding a bundle of cables at the third and fourth cable fulcrums, and binding a bundle of cables at the seventh and eighth cable fulcrums;

[0067] The present invention can bind a bundle of cables in the vertical direction through the third and eighth cable fulcrums, bind a bundle of cables in the vertical direction through the third and fourth cable fulcrums, bind a bundle of cables in the vertical direction through the seventh and eighth cable fulcrums, bind a bundle of cables in the vertical direction through the first and second cable fulcrums, and bind a bundle of cables in the vertical direction through the fifth and sixth cable fulcrums, thereby realizing the binding and fixing of a total of five bundles of cables, namely three bundles in the vertical direction and two bundles in the vertical direction;

[0068] The present invention provides a mounting surface through the bottom plate 9, and the cable and bracket assembly can be installed and fixed through the bolt holes 10 on the mounting surface; the bolt holes 10 of the present invention are mounting holes with a diameter of 4.2, which are suitable for mounting surfaces with a thickness of 4mm.

[0069] Secondly, in order to solve the above problems, refer to Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 and Figure 8 The present invention provides an installation method for secondary isolation of a satellite-borne cable bundle, which is applied to the fixing device for secondary isolation of a satellite-borne cable bundle, and comprises the following steps:

[0070] S1. Bolt the fixed frame to the location where the cable bundle is to be installed;

[0071] S2, tying the first cable bundle to the first longitudinal rod 1 and the third longitudinal rod 2 by wrapping a cable tie around the first longitudinal rod 1 and the third longitudinal rod 2;

[0072] S3, tying the second cable bundle to the second longitudinal rod 6 and the fourth longitudinal rod 5 by passing a cable tie around the second longitudinal rod 6 and the fourth longitudinal rod 5;

[0073] Specifically, the fixed frame includes: a first longitudinal rod 1, a third longitudinal rod 2, a first trapezoidal frame 3, a first transverse support rod 4, a fourth longitudinal rod 5, a second longitudinal rod 6, a second transverse support rod 7, a second trapezoidal frame 8 and a bottom plate 9; wherein the first longitudinal rod 1 and the second longitudinal rod 6 are respectively installed at the left and right ends of the bottom plate 9, and rectangular openings for tying with straps are provided between the first longitudinal rod 1 and the bottom plate 9 and between the second longitudinal rod 6 and the bottom plate 9, the first trapezoidal frame 3 and the second trapezoidal frame 8 are respectively installed at the front and rear ends of the bottom plate 9, and the first transverse support rod 6 is installed at the second transverse support rod 7, the second trapezoidal frame 8 and the bottom plate 9. The support rod 4 is horizontally installed inside the first trapezoidal frame 3, the second transverse support rod 7 is horizontally installed inside the second trapezoidal frame 8, the third longitudinal rod 2 and the fourth longitudinal rod 5 are both arranged between the first trapezoidal frame 3 and the second trapezoidal frame 8, and one end is connected to the first trapezoidal frame 3, and the other end is connected to the second trapezoidal frame 8. A bolt hole 10 is opened at the geometric center of the bottom plate 9 for fixing the fixed frame on the structural mounting surface. The bolt hole 10 is a mounting hole with a diameter of 4.2 mm. The thickness of the bottom plate 9 is 4 mm, and the national standard M3 and M4 fasteners can be used;

[0074] Furthermore, the distance between the center of mass of the bottom cable bundle and the height of the cabin board is no more than 30 mm, the distance between the center of mass of the top cable bundle and the height of the cabin board is no more than 50 mm, and the center of mass of the entire cable assembly is no higher than 37 mm. The low center of mass of the cable means that the overall mechanical response of the cable assembly is small;

[0075] Furthermore, the fixed frame adopts the flight-proven nylon material, namely modified nylon. The modified nylon has good insulation properties and can easily promote the occurrence of a short circuit to the ground after a cable failure. The fixed frame of the present invention does not need to perform post-embedded fastener treatment on the cabin panel on the original cable bundle path, reducing the need for fastening points by 50%, improving versatility and flexibility, and when installing the fixed frame, there is no need to clean the adhesive installation surface of the thermal control coating on the cabin panel. It can be fixed and installed by using any fastener installation point installed on the cabin panel, with strong flexibility and operability.

[0076] Preferably, the method further includes step S4, tying the third cable bundle to the outer side of the first trapezoidal frame 3 by wrapping a cable tie around the first trapezoidal frame 3 and the first transverse support rod 4.

[0077] Preferably, the method further includes step S5 of tying the fourth cable bundle to the outside of the second trapezoidal frame 8 by wrapping a cable tie around the second trapezoidal frame 8 and the second transverse support rod 7 .

[0078] Preferably, the method further includes step S6, tying the fifth cable bundle between the first trapezoidal frame 3 and the second trapezoidal frame 8 by wrapping a cable tie around the first trapezoidal frame 3 and the second trapezoidal frame 8;

[0079] Specifically, the technical solution of the present invention proposes an installation method for bundling five cable bundles. In specific applications, the number of cable bundles to be bundled and the bundling positions can be selected according to specific circumstances. That is, the technical solution of the present invention has five cable bundle bundling positions, and users can flexibly select the cable bundle bundling positions according to the number of cable bundles to be laid and the laying direction.

[0080] Preferably, the first cable bundle and the second cable bundle are positioned parallel to each other.

[0081] Preferably, the third cable bundle, the fourth cable bundle and the fifth cable bundle are positioned parallel to each other;

[0082] Specifically, the installation method disclosed in the present invention can be used to bundle cables in two directions, including two cable bundles in one direction and three cable bundles in the other direction. Users can combine and arrange the cable bundles according to actual needs.

[0083] Furthermore, the present invention can limit and fix the cable bundle, and the cable bundle tie can only be slightly adjusted within a limited range, thereby reducing stress concentration on the cable bundle path and eliminating the risk of the cable falling off or slipping during the mechanical process.

[0084] Preferably, the first cable bundle and the second cable bundle are perpendicular to the third cable bundle, the fourth cable bundle and the fifth cable bundle;

[0085] Specifically, compared with the prior art which can only tie the cable bundle in the horizontal direction, the present invention can not only tie the cable bundle in the horizontal direction but also tie it in the vertical direction;

[0086] Furthermore, by installing the fixed frame obliquely, the oblique bundling of the cable bundle can be achieved, and the specific rotation angle can be flexibly set according to the actual application situation.

[0087] Preferably, the binding places of the first cable bundle, the second cable bundle, the third cable bundle, the fourth cable bundle and the fifth cable bundle are all bound with heat shrinkable cloth;

[0088] Specifically, the heat shrinkable cloth is used to bind the surface of the cable bundle 5-10 times to enhance its physical isolation effect. The outer layer of this material also has the characteristics of insulation, corrosion resistance, and wear resistance, which can further improve the stability of installation and use and further reduce costs.

[0089] Preferably, the distance between two adjacent cable bundles is greater than 10 mm;

[0090] Specifically, the straight-line distance between two adjacent cable bundle binding locations shall not be less than 12 mm.

[0091] Preferably, the first cable bundle, the second cable bundle, the third cable bundle, the fourth cable bundle and the fifth cable bundle are all tied into bundles by cotton thread.

[0092] With the diversification of spacecraft product forms and the complexity of functions, the layout of onboard cable bundles faces increasingly higher requirements. The traditional cable bundle layout method has problems such as large space occupation, poor installation stability, and poor physical isolation. Especially when high-power and multi-type cable bundles need to be laid at the same time, it is necessary to effectively reduce space occupation, improve installation stability, and achieve good physical isolation.

[0093] The present invention aims to provide a fixing device and an installation method for secondary isolation of satellite-borne cable bundles. By introducing two installation methods, the overpass type and the pyramid type, not only the problems existing in the traditional laying method are solved, but also the flexibility of cable bundle laying and the space utilization efficiency are further improved.

[0094] The fixing device provided by the present invention includes a first longitudinal rod, a third longitudinal rod, a first trapezoidal frame, a first transverse support rod, a fourth longitudinal rod, a second longitudinal rod, a second transverse support rod, a second trapezoidal frame, a base plate and bolt holes, etc., forming a stable frame for carrying and fixing the satellite-borne cable bundle.

[0095] Flyover type installation method: In the flyover type installation method, the present invention uses components such as a first longitudinal rod, a third longitudinal rod, a first trapezoidal frame, and a second trapezoidal frame to construct a structure similar to an overpass. The specific steps are as follows: Bolt the fixed frame to the position where the cable bundle is to be installed through the bolt holes. Use cable ties to bypass the first longitudinal rod and the third longitudinal rod, and tie the cable bundles that need to be laid longitudinally to the two rods. Use the outer space of the first trapezoidal frame and the second trapezoidal frame to tie the cable bundles that need to be laid horizontally to the outside of the two trapezoidal frames respectively through cable ties. For cable bundles that need to be laid crosswise, the space between the first trapezoidal frame and the second trapezoidal frame can be bypassed by cable ties and tied between the two. In this way, the cable bundles can be flexibly arranged in the longitudinal, transverse and cross directions, effectively improving the efficiency of space utilization.

[0096] Pyramid installation method: In the pyramid installation method, the present invention uses components such as a first longitudinal rod, a second longitudinal rod, a first trapezoidal frame, a second trapezoidal frame, and a transverse support rod to construct a pyramid-like structure. The specific steps are as follows: The bottom plate of the fixed frame is fixed to the position where the cable bundle is to be installed through the bolt hole. The cable bundle that needs to be laid at the bottom is tied to the two rods by using the grooves between the first longitudinal rod and the second longitudinal rod and the bottom plate. The cable bundle that needs to be laid on the side is tied to the two sides of the trapezoidal frame respectively through the side space of the first trapezoidal frame and the second trapezoidal frame, and the through holes between them and the bottom plate. The cable bundle that needs to be laid on the top is tied in the groove by using the third groove at the top of the trapezoidal frame. At the same time, the structure of the trapezoidal frame can be reinforced by the transverse support rod to improve the overall stability. In this way, the cable bundle can be laid simultaneously in the three directions of the bottom, the side and the top, which further improves the space utilization efficiency and the installation stability.

[0097] The invention provides two installation methods, overpass type and pyramid type, which can be flexibly selected according to actual needs to meet the cable bundle layout requirements in different scenarios. Through ingenious structural design, the multi-dimensional layout of cable bundles in a limited space is realized, effectively improving the efficiency of space utilization. The fixing device adopts a stable frame structure and a reasonable binding method, which improves the stability of the cable bundle during installation and reduces the risk of vibration and falling off. Through the heat shrink cloth binding at the binding point and the reasonable cable bundle spacing setting, a good physical isolation effect is achieved, meeting the requirements of electromagnetic compatibility.

[0098] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0099] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0100] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0101] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples" or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, unless they are contradictory.

[0102] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A fixing device for secondary isolation of a satellite-borne cable bundle, characterized in that: It comprises a first longitudinal rod (1), a third longitudinal rod (2), a first trapezoidal frame (3), a first transverse support rod (4), a fourth longitudinal rod (5), a second longitudinal rod (6), a second transverse support rod (7), a second trapezoidal frame (8), a bottom plate (9) and bolt holes (10); A first longitudinal rod (1) is installed at one end of the bottom plate (9), a second longitudinal rod (6) is installed at the other end of the bottom plate (9), a first trapezoidal frame (3) and a second trapezoidal frame (8) are relatively installed in the middle of the bottom plate (9), and a third longitudinal rod (2) and a fourth longitudinal rod (5) are connected between the first trapezoidal frame (3) and the second trapezoidal frame (8); A second transverse support rod (7) is installed in the middle of the second trapezoidal frame (8), a first transverse support rod (4) is installed in the middle of the first trapezoidal frame (3), a bolt hole (10) is arranged at the bottom of the base plate (9), and the third longitudinal rod (2), the fourth longitudinal rod (5), the first transverse support rod (4) and the second transverse support rod (7) are used to carry the satellite cable bundle.

2. A fixing device for secondary isolation of a satellite-borne cable bundle according to claim 1, characterized in that: A first through hole is provided between the second trapezoidal frame (8) and the bottom plate (9), a second through hole is provided between the first trapezoidal frame (3) and the bottom plate (9), a third through hole is provided between the fourth longitudinal rod (5) and the first trapezoidal frame (3), the second trapezoidal frame (8) and the bottom plate (9), a fourth through hole is provided between the third longitudinal rod (2) and the first trapezoidal frame (3), the second trapezoidal frame (8) and the bottom plate (9), a fifth through hole is provided between the first longitudinal rod (1) and the bottom plate (9), a sixth through hole is provided between the second longitudinal rod (6) and the bottom plate (9), a sixth through hole is provided between the first trapezoidal frame (3), the second trapezoidal frame (8), the third longitudinal rod (2) and the fourth longitudinal rod (5), and the first through hole, the second through hole, the third through hole, the fourth through hole, the fifth through hole and the sixth through hole are used to pass a satellite cable bundle.

3. A fixing device for secondary isolation of a satellite-borne cable bundle according to claim 1, characterized in that: The first longitudinal rod (1) and the second longitudinal rod (6) are inclined downward from the top; a first groove is arranged between the first longitudinal rod (1) and the bottom plate (9), the first trapezoidal frame (3) and the second trapezoidal frame (8); a second groove is arranged between the second longitudinal rod (6) and the bottom plate (9), the first trapezoidal frame (3) and the second trapezoidal frame (8); the first groove and the second groove are used to pass the satellite cable bundle; the second transverse support rod (7) is used to separate the first through hole between the second trapezoidal frame (8) and the bottom plate (9) into two through holes; the first transverse support rod (4) is used to separate the second through hole between the first trapezoidal frame (3) and the bottom plate (9) into two through holes; and a third groove is arranged on the top of the third longitudinal rod (2), the first trapezoidal frame (3), the fourth longitudinal rod (5) and the second trapezoidal frame (8).

4. A fixing device for secondary isolation of a satellite-borne cable bundle according to claim 1, characterized in that: The first groove and the second groove are used to fix two bundles of parallel cables respectively, and the third groove is used to fix a bundle of cables. The bundle of cables fixed on the third groove is in a perpendicular state to the two bundles of cables fixed on the first groove and the second groove.

5. A method for installing secondary isolation of a satellite-borne cable bundle, applied to the fixing device for secondary isolation of a satellite-borne cable bundle as claimed in any one of claims 1 to 4, characterized in that: The following steps are involved: Step S1, bolting the fixing frame to the position where the cable bundle is to be installed; Step S2, tying the first cable bundle to the first longitudinal rod (1) and the third longitudinal rod (2) by wrapping a cable tie around the first longitudinal rod (1) and the third longitudinal rod (2); Step S3, tying the second cable bundle to the second longitudinal rod (6) and the fourth longitudinal rod (5) by wrapping the cable tie around the second longitudinal rod (6) and the fourth longitudinal rod (5); Step S4, using a cable tie to wrap around the first trapezoidal frame (3) and the first transverse support rod (4) to tie the third cable bundle to the outside of the first trapezoidal frame (3); Step S5, using a cable tie to wrap around the second trapezoidal frame (8) and the second transverse support rod (7) to tie the fourth cable bundle to the outside of the second trapezoidal frame (8); Step S6: Using a cable tie to bypass the first trapezoidal frame (3) and the second trapezoidal frame (8), the fifth cable bundle is tied between the first trapezoidal frame (3) and the second trapezoidal frame (8).

6. The installation method for secondary isolation of a satellite-borne cable bundle according to claim 5, characterized in that: The first cable bundle and the second cable bundle are positioned parallel to each other, and the third cable bundle, the fourth cable bundle and the fifth cable bundle are positioned parallel to each other.

7. The installation method for secondary isolation of a satellite-borne cable bundle according to claim 5, characterized in that: The first cable bundle and the second cable bundle are perpendicular to the third cable bundle, the fourth cable bundle and the fifth cable bundle. The first cable bundle, the second cable bundle, the third cable bundle, the fourth cable bundle and the fifth cable bundle are all bound with heat shrink cloth at their binding locations.

8. The installation method for secondary isolation of a satellite-borne cable bundle according to claim 5, characterized in that: The distance between two adjacent cable bundles is greater than 10 mm, and the first cable bundle, the second cable bundle, the third cable bundle, the fourth cable bundle and the fifth cable bundle are all tied into bundles by cotton thread.

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