CN111799729B - High-power multilayer composite bus bar capable of being shaped for space navigation - Google Patents
High-power multilayer composite bus bar capable of being shaped for space navigation Download PDFInfo
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- CN111799729B CN111799729B CN202010441993.1A CN202010441993A CN111799729B CN 111799729 B CN111799729 B CN 111799729B CN 202010441993 A CN202010441993 A CN 202010441993A CN 111799729 B CN111799729 B CN 111799729B
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G5/00—Installations of bus-bars
- H02G5/06—Totally-enclosed installations, e.g. in metal casings
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G5/00—Installations of bus-bars
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Abstract
The invention discloses a high-power shapeable multilayer composite bus bar for aerospace, which comprises a confluence positive bus 1, cavity insulating glue 2, a confluence positive bus binding post 3, a cavity insulating assembly 4, a confluence negative bus binding post 5, a confluence negative bus 6, an external insulating protective cover 7, a confluence negative bus mounting groove 8, an insulating mounting sleeve 9, a bus bar protective insulating plate 10 and a terminal insulating assembly 11. The high-voltage end is connected to the positive generating line 1 that converges, is located the intermediate position, and the negative generating line 6 that converges connects the low-voltage end (direct current zero potential end promptly), is the U-shaped and will converge positive generating line 1 trilateral encirclement for the electric field line that produces after high-voltage end and the low-voltage end circular telegram is confined to inside the U-shaped, guarantees good electromagnetic compatibility effect, adopts the silvered copper wire with equal power cable assembly and compares, under the horizontal cross-sectional area circumstances of same transmission, can save about 20% weight and volume. The radiating area is large, the radiating capacity is strong, the environmental temperature rise is low, and the transmission impedance can be reduced.
Description
Technical Field
The invention relates to a high-power shapeable multilayer composite bus bar for aerospace, belonging to the technical field of aerospace high-power supply and distribution.
Background
With the implementation of space projects such as high-resolution earth observation, deep space exploration and the like, the requirement of effective load is improved, the requirements of the resolution of a spacecraft and the range of a surveying and mapping band on energy supply are increased, and the current carrying capacity of a main power transmission channel is improved to be more than 100A.
The combination of the aerospace cable network and the electronic single machine forms an electric energy transmission path of the whole satellite ship, and energy and various command signals are transmitted among equipment. The domestic spacecraft generally increases the transmission power level and the number of signal paths by means of increasing the number of leads, so that the structure and the general assembly of the satellite-borne cable tend to be complex. Particularly, in the area between a primary power supply and a secondary power supply with power convergence, the power cables are densely laid, and the number of power wires in a unit section is greatly increased. On one hand, the situation causes the cable to generate heat sharply, and the heat is influenced by a large number of insulating layers between the wires and cannot be transmitted out in time through conduction or radiation, so that the electrothermal coupling is aggravated; on the other hand, the distance between the power cable and the surrounding electronic single machine and structural components is obviously reduced, the laying and fixing are difficult, and the problem of abnormal conduction caused by damage to the insulating layer of the conducting wire is easy to occur when the power cable is influenced by strong vibration conditions in the transmitting stage.
At present, the bus function of the spacecraft is mainly realized by a bus device in a power supply case and a short circuit of a contact of a power supply cable grid power connector, stray capacitance is more, a single-point power supply and multipoint equipment are required to be interconnected into a network, and the efficiency of a distributed power supply system is restricted.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the high-power shape-endowable multilayer composite bus bar for aerospace is provided, the distributed power supply system is suitable for parallel power supply, the plug-and-play and high-power transmission functions are achieved, the problems that a traditional aerospace high-power cable is large in heat productivity and slow in heat dissipation are solved, the electrothermal coupling is slowed down, meanwhile, the light weight and the miniaturization of a power supply and distribution unit of a spacecraft are promoted, the laying efficiency of a power cable network is improved, and the carrying reliability is improved.
The technical scheme of the invention is as follows: a high-power shape-able multilayer composite bus bar for aerospace comprises: the device comprises a confluence positive bus (1), cavity insulating glue (2), a confluence positive bus terminal (3), a cavity insulating assembly (4), a confluence negative bus terminal (5), a confluence negative bus (6), an outer insulating protective cover (7), a confluence negative bus mounting groove (8), an insulating mounting sleeve (9), a confluence bar protecting insulating plate (10) and a terminal insulating assembly (11);
the bus positive bus (1) and the bus negative bus (6) are used as a whole conductor medium for electric energy integration and transmission, the bus positive bus (1) is connected with a high-voltage end and is positioned in the middle, the bus negative bus (6) is connected with a low-voltage end and is U-shaped and surrounds three surfaces of the bus positive bus (1);
a plurality of bus positive bus binding posts (3) are connected and led out above the bus positive bus (1) and are used for connecting the power supply positive level or high potential of the aerospace equipment; the side edge of the bus negative bus (6) is connected with and led out of a plurality of bus negative bus binding posts (5) for connecting the power supply negative level or low potential of the aerospace equipment;
the terminal insulation assembly (11) seals the terminal of the confluence negative bus (6) and fixes the terminal of the confluence positive bus (1); by adopting a plurality of U-shaped cavity insulating assemblies (4), the arrangement intervals are equal, the bus-bar positive bus (1) is supported and fixed, and the gap intervals between the bus-bar positive bus (1) and the bus-bar negative bus (6) are ensured to be equidistant in the length direction of the bus bar;
the bus positive bus (1), the bus positive bus binding post (3) and the bus negative bus binding post (5) are subjected to insulation treatment except for the wiring plane and the stud position; the outer surface of the bus negative bus (6) and the outer surfaces of the multiple groups of bus negative bus mounting grooves (8) are selectively subjected to insulation treatment according to the grounding requirement of the spacecraft. The bus negative bus mounting groove (8) is connected with the bus negative bus (6) and is positioned at the bottom of the bus negative bus (6).
Cavity insulating glue (2) is filled in positions without the U-shaped cavity insulating assemblies (4) between the U-shaped cavity insulating assemblies (4) and the terminal insulating assembly (11), between two adjacent U-shaped cavity insulating assemblies (4) and between the bus positive bus (1) and the bus negative bus (6), so that the integration of a bus bar insulating structure is realized, and a modularized bus bar is formed;
an external insulation protecting cover (7) is arranged to isolate the non-insulation positions of the wiring of the bus positive bus terminal (3) and the bus negative bus terminal (5);
an insulating mounting sleeve (9) which runs through from the busbar mounting groove (8) to the protective insulating plate (10)
The busbar protection insulating plate (10) performs insulation protection on the bottom surfaces of the busbar (6) and the busbar mounting groove (8), namely a busbar mounting plane.
Preferably, the bus positive bus bar 1 and the bus negative bus bar 6 are made of aluminum alloy.
Preferably, the negative bus (6) is converged, so that electric field lines generated after the high-voltage end and the low-voltage end are electrified are limited in the U-shaped interior, and a good electromagnetic compatibility effect is ensured.
Preferably, the bus bar terminal (3) is composed of a round-angle cuboid boss and a stud, the stud and the round-angle cuboid boss are integrally formed, and the round-angle cuboid boss is in direct contact with the bus bar 1.
Preferably, the bus negative bus binding post (5) consists of a boss with a trapezoidal cross section and a stud, the boss with the trapezoidal cross section is in direct contact with the bus negative bus (6), and the stud and the boss with the trapezoidal cross section are integrally formed.
Preferably, the bus bar positive bus bar binding post (3) and the bus bar negative bus bar binding post (5) can be designed and determined in advance according to the arrangement condition of electric equipment of a spacecraft cabin plate, the position and the number of bus bars in the length direction can be determined, the wiring direction can be changed, and flexible electric energy shunting is realized.
Preferably, the terminal insulation assembly (11) seals both terminals of the negative bus bar (6) inside the U-shape of the negative bus bar (6).
Preferably, the U-shaped cavity insulating assembly (4) is positioned between the bus positive bus (1) and the bus negative bus (6) and supports and insulates the bus positive bus (1) and the bus negative bus (6).
Preferably, the wiring plane is a surface of the boss connected with the stud.
Preferably, a plurality of groups of bus negative bus mounting grooves (8) are arranged symmetrically along the length direction of the bus bars, the positions of the mounting holes can be reserved according to the spacecraft cabin plate, the slotting positions are designed and confirmed in advance, and the modular bus bars are convenient to mount and fix.
Preferably, an external insulation protective cover (7) is arranged to isolate the non-insulation positions of the wiring of the bus positive bus terminal (3) and the bus negative bus terminal (5), so that the influence of high potential and large current of a bus bar on surrounding equipment and environment is avoided, and meanwhile, an electronic breakdown diffusion path during abnormal discharge is blocked.
Preferably, the outer insulating protecting cover (7) is provided with an opening (7-1) and an isolating pile (7-2), and the opening (7-1) is positioned on the side wall of the outer insulating protecting cover (7) and is used as an inlet and outlet channel of a lead; a plurality of isolation piles (7-2) are respectively located between positive and negative bus connection posts of each group of bus bars, the bus bars are installed on the cabin plate, and the external insulation protective covers (7) are also installed on the cabin plate through the isolation piles, so that the bus bars can be isolated in a grouping mode, and can be installed and supported as the external insulation protective covers (7).
Preferably, the projection surface size of the busbar protection insulating plate 10 on the deck is the same as the projection surface size of the combined negative busbar 6 and the plurality of groups of negative busbar mounting grooves 8 on the deck, and the insulating mounting sleeve 9 has a T-shaped cross section and penetrates from the upper surface of the negative busbar mounting groove 8 to the bottom surface of the protection insulating plate 10.
Compared with the prior art, the invention has the advantages that:
(1) compared with the silver-plated copper wire adopted by the same power cable assembly, the invention can save about 20% of weight and volume under the condition of the same transmission horizontal cross section area.
(2) The invention has large heat dissipation area, strong heat dissipation capability and low environmental temperature rise, and can reduce transmission impedance.
(3) The spacecraft cable network system has the advantages of saving complex circuit design and cable wiring, occupying small space, being convenient to install, being capable of forming interface design, being beneficial to integration and realizing modular application, and being capable of reducing the laying time of the spacecraft cable network.
(4) The invention relates to a high-power shapeable multilayer composite bus bar for aerospace, which is suitable for a distributed power system with parallel power supply and has the functions of plug and play and high-power transmission.
(5) The invention increases the distance between the power cable network and the electronic single machine and between the power cable network and the structural member, avoids abnormal conduction and improves the carrying reliability.
Drawings
Fig. 1 is a high-power shape-able multilayer composite bus bar for aerospace.
FIG. 2 is an overall three-dimensional perspective view of a high-power formable multilayer composite bus bar for aerospace with an integral external insulation protective cover.
Fig. 3 is a cross-sectional view of a multi-layer composite bus bar at a mounting threaded hole.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
The invention discloses a high-power shapeable multilayer composite bus bar for aerospace, which comprises a confluence positive bus 1, cavity insulating glue 2, a confluence positive bus binding post 3, a cavity insulating assembly 4, a confluence negative bus binding post 5, a confluence negative bus 6, an external insulating protective cover 7, a confluence negative bus mounting groove 8, an insulating mounting sleeve 9, a bus bar protective insulating plate 10 and a terminal insulating assembly 11. The high-voltage end is connected to the positive generating line 1 that converges, is located the intermediate position, and the negative generating line 6 that converges connects the low-voltage end (direct current zero potential end promptly), is the U-shaped and will converge positive generating line 1 trilateral encirclement for the electric field line that produces after high-voltage end and the low-voltage end circular telegram is confined to inside the U-shaped, guarantees good electromagnetic compatibility effect, adopts the silvered copper wire with equal power cable assembly and compares, under the horizontal cross-sectional area circumstances of same transmission, can save about 20% weight and volume. The radiating area is large, the radiating capacity is strong, the environmental temperature rise is low, and the transmission impedance can be reduced.
The invention is preferably used for spacecraft bus units under the heavy current working condition of more than 100A, such as aerospace distributed power supply system buses and high-flux spacecraft primary energy system buses, and compared with the traditional aerospace high-power cable, the invention has the following advantages:
high current density: compared with an aerospace high-power cable, the aerospace high-power cable has a special radiating plane, can be directly connected with a spacecraft thermal control system interface, can bear higher power loss under the condition of the same conductor sectional area, and has higher current density.
And (3) lightweight design: because the invention has higher current-carrying density than the aerospace high-power cable, the volume of the metal conductor which can be used under the same current level is smaller; in addition, the conductor bar with the large cross section is used for replacing a wire core, so that the using amount of external insulating materials can be reduced, and the weight of the bus bar is further reduced; compared with the bus copper bar used in ground equipment, the invention can achieve the technical goal of reducing weight by more than 20% on the premise of not reducing electrical performance by optimizing the selection of materials.
Parasitic parameter optimization: the aerospace high-power cable needs to use thicker wires for power distribution under a high-current working condition, the wires with high rated current are harder, and particularly when a plurality of wires are connected in parallel, the twisted-pair winding of a positive wire and a negative wire is difficult to realize, and a larger parasitic inductance exists in a cable loop. The invention adopts the structural design of tightly coupling the positive line and the negative line, has lower parasitic inductance and can optimize the dynamic characteristic of the direct current bus; in addition, compared with an aerospace high-power cable, the space between the positive line and the negative line has larger overlapping area, a parasitic filter capacitor can be formed between the positive line and the negative line, and the effect of filtering high-frequency peaks is achieved.
And (3) structural multiplexing: the bus bar structure has the characteristics of multi-source and multi-load simultaneous power supply, and different electric energy sources can transmit current to a plurality of loads through the same bus bar; compared with a point-to-point connection mode of an aerospace high-power cable, the bus bar structure can realize local sharing and multiplexing of a power distribution conductor material, not only can reduce the weight of a power distribution system, but also is beneficial to simplifying the integration process of the system.
The invention provides a high-power shapeable multilayer composite bus bar for aerospace, which further adopts the following preferred scheme:
the high-power multilayer composite bus bar capable of being shaped for aerospace comprises: the positive generating line 1 converges, cavity insulating cement 2, the positive generating line terminal 3 converges, cavity insulating assembly 4, the negative generating line terminal 5 that converges, the negative generating line 6 that converges, external insulation protecting cover 7, the negative generating line mounting groove 8 that converges, insulating installation sleeve 9, busbar protection insulation board 10, terminal insulating assembly 11.
The bus positive bus 1 and the bus negative bus 6 are used as a whole conductor medium for electric energy integration and transmission and are made of aluminum alloy materials. The positive bus 1 that converges connects the high-voltage terminal, is located the intermediate position, and the negative bus 6 that converges connects the low-voltage end (direct current zero potential end promptly), is the U-shaped and will converge positive bus 1 trilateral encirclement for the electric field line that the high-voltage terminal produced after the low-voltage end circular telegram is confined to inside the U-shaped, guarantees good electromagnetic compatibility effect.
A plurality of bus-bar binding posts 3 (for connecting the power supply positive level or high potential of aerospace equipment) are connected and led out above the bus-bar 1, and the bus-bar binding posts 3 consist of round-angle cuboid bosses and studs (the studs and the round-angle cuboid bosses are integrally formed and directly contact with the bus-bar 1; the side edge (U-shaped side edge) of the confluence negative bus 6 is connected with and leads out a plurality of confluence negative bus binding posts 5 (used for being grounded together with nearby space equipment and flexibly adjusting the wiring quantity according to the quantity of the equipment), and each confluence negative bus binding post 5 consists of a boss with a trapezoidal cross section (used for forming conductive contact with the power supply negative level or low potential of the space equipment) and a stud (the boss with the trapezoidal cross section is in direct contact with the confluence negative bus 6, and the stud and the boss with the trapezoidal cross section are integrally formed). The bus bar positive bus bar binding post 3 and the bus bar negative bus bar binding post 5 can be designed and determined in advance according to the arrangement condition of electric equipment of a spacecraft cabin plate, the position and the number of bus bars in the length direction can be determined, the wiring direction can be changed, and flexible electric energy shunting is realized.
The terminal insulating assembly 11 seals the U-shaped interior of the terminal of the bus negative bus 6 (for limiting the flow range of the cavity insulating glue 2 and supporting the two ends of the bus positive bus 1), and simultaneously fixes the terminal of the bus positive bus 1; through adopting a plurality of U-shaped cavity body insulation assemblies 4, the interval of arranging equals, supports fixedly to converging positive bus 1, guarantees simultaneously that the gap interval between converging positive bus 1 and the negative bus 6 that converges is equidistant in busbar length direction. (U-shaped cavity insulation component 4 located between the confluence positive bus 1 and the confluence negative bus 6 for supporting and insulating the confluence positive bus 1 and the confluence negative bus 6)
The high-power shapeable multilayer composite bus bar for aerospace is characterized in that a bus positive bus 1, a bus positive bus binding post 3, a bus negative bus binding post 5, a wiring plane (namely a surface connected with a stud on a boss) and the position of the stud are subjected to insulation treatment; and the outer surface of the bus negative bus 6 and the outer surfaces of the multiple groups of bus negative bus mounting grooves 8 are selectively subjected to insulation treatment according to the grounding requirement of the spacecraft. (the confluence negative bus installation groove 8 is connected with the confluence negative bus 6 and is positioned at the bottom of the confluence negative bus 6.)
Between a plurality of U-shaped cavity body insulating assemblies 4 and terminal insulating assembly 11, between two adjacent U-shaped cavity body insulating assemblies 4, converge and do not have the position of U-shaped cavity body insulating assembly 4 between positive generating line 1 and the negative generating line 6 that converges, all fill with cavity body insulating cement 2, realize busbar insulation system integration, form the modularization busbar.
The bus bar installation grooves 8 are symmetrically arranged along the length direction of the bus bar, the positions of installation holes can be reserved according to a spacecraft cabin plate, the slotting positions are designed and confirmed in advance, and the modularized bus bar is convenient to install and fix.
An external insulation protecting cover 7 is arranged to isolate the non-insulation positions of the wiring of the bus positive bus terminal 3 and the bus negative bus terminal 5 (the non-insulation positions refer to the upper surface of a circular-angle cuboid boss and a stud in the bus positive bus terminal 3 and the upper surface of a trapezoidal boss and a stud in the cross section of the bus negative bus terminal 5), thereby avoiding the influence of the high potential and the large current of the bus bar on the peripheral equipment and the environment, and simultaneously blocking the electric breakdown diffusion path during abnormal discharge (when the peripheral electronic equipment discharges abnormally, an insulation barrier is arranged, and even if a potential difference exists between the bus bar and the electronic equipment, the abnormal discharge cannot be transmitted to the bus bar). Wherein 7-1 is the opening position of the external insulation protective cover 7 and is used as an access passage of the lead; 7-2 are the isolation stake (say that the busbar is installed on the cabin board, and outer insulating protecting cover 7 also installs on the cabin board through the isolation stake) between positive and negative generating line terminal of every group busbar, can realize the isolation of grouping wiring to the busbar (explain how to isolate the terminal), can regard as the erection bracing of outer insulating protecting cover 7 again.
The projection surface size of the busbar protection insulation board 10 on the cabin board is the same as the projection surface size of the combined negative busbar 6 and the combined negative busbar installation grooves 8 on the cabin board, the section of the insulation installation sleeve 9 is T-shaped, and the upper surface of the negative busbar installation groove 8 penetrates through to the bottom surface of the protection insulation board 10. (when the bus bar is installed on the spacecraft cabin plate by using the screw, the installation screw is insulated and isolated from the bus bar body by the insulating installation sleeve 9)
The invention discloses a further preferable scheme of a high-power shapeable multilayer composite bus bar for space navigation, which comprises the following steps:
as shown in fig. 1, 2 and 3, the bus positive bus 1 is a rectangular conductor material and is located at the center of the whole bus bar, and the bus negative bus 6 is a U-shaped long-strip conductor material and surrounds the bus positive bus 1 on three sides, so that the structural design of close coupling of the positive line and the negative line is realized, a good electromagnetic compatibility effect is ensured, and the transmission of electric energy is realized. And phosphoric acid anodizing smoothing treatment is carried out on the surface of the bus to avoid electric field distortion caused by the tip of the surface.
The bus positive bus terminal 3 is an extension part of the bus positive bus 1, and the bus negative bus terminal 5 and the bus negative bus mounting groove 8 are extension parts of the bus negative bus 6 and are made of aluminum alloy materials. The upper surface of the lug boss of the binding post is plated with gold to reduce contact resistance, and the lug boss is used for interconnecting the bus bar and the aerospace power supply equipment. The mounting groove is a hollow cube slice and is used as a fixing through hole of the bus bar and the spacecraft cabin plate.
The cavity insulating glue 2 is made of a high-molecular insulating material with low outgassing and good fluidity, the breakdown strength is larger than the maximum breakdown strength between the positive bus and the negative bus after the breakdown strength is used in a derating manner, and the long-term reliable operation of the bus bar is realized.
The cavity insulating assembly 4, the terminal insulating assembly 11 and the insulating mounting sleeve 9 are made of solid insulating materials with corona resistance and good thermal stability. The cavity insulating assembly 4 is U-shaped, the terminal insulating assembly 11 is dustpan-shaped, the combination of the two defines the position of the bus positive bus 1 relative to the bus negative bus 6, the size consistency of the gap in the length direction is ensured, and the dislocation of the bus positive bus 1 in the length direction and the sinking in the vertical direction are avoided. The insulating mounting sleeve 9 is T-shaped and insulates the mounting screw from the busbar body.
The external insulation protecting cover 7 and the bus bar protection insulating plate 10 are made of solid insulating materials with light weight, high thermal conductivity and good mechanical property, and respectively insulate and isolate the exposed surface and the bottom surface of the bus bar from the surrounding environment.
The invention further discloses a scheme for realizing the light weight of the bus bar, which comprises the following steps: the load current of the bus bar is I, the resistance of the bus bar is R1, the thermal resistance of the heat dissipation interface of the thermal control system is R2, and 0 is preferably satisfied<R2*I2*R1<2, satisfying the preferable constraint condition, a further reduction in the weight of the bus bar can be achieved.
The invention realizes the further proposal of improving the reliability of the bus bar: by selecting an insulating encapsulating material with a specific dielectric constant and combining the performance parameters of the distributed power supply, the design, control and utilization of the bus bar capacitor can be realized, and high-frequency spike interference signals can be effectively filtered.
The invention relates to a high-power shapeable multilayer composite bus bar for space navigation, which further adopts the following optimal scheme:
including the positive generating line 1 that converges, cavity insulating cement 2, the positive generating line terminal 3 that converges, cavity insulating assembly 4, the negative generating line terminal 5 that converges, the negative generating line 6 that converges, external insulation protecting cover 7, the negative generating line mounting groove 8 that converges, insulating installation sleeve 9, busbar protection insulation board 10, terminal insulating assembly 11.
The specific implementation mode is as follows:
the bus positive bus 1 and the bus positive bus terminal 3 are combined or integrally molded for use, and the bus negative bus 6, the bus negative bus terminal 5 and the bus negative bus mounting groove 8 are integrally molded for use. The components are made of aluminum alloy materials, and are anodized through phosphoric acid, and the upper surfaces of bosses of the bus bar positive wiring terminal 3 and the bus bar negative wiring terminal 5 are plated with gold for reducing contact resistance during wiring.
The surfaces of the bus positive bus 1, the bus positive bus binding post 3, the bus negative bus 6, the bus negative bus binding post 5 and the bus negative bus mounting groove 8 except for the boss gold-plated surface are treated by polyurethane varnish to play the role of insulation protection. The surfaces of the bus bar 1 and the bus bar binding post 3 except the lug boss gold-plated surface are wound with polyimide adhesive tapes according to the overlapping degree of more than 50%, and the polyimide adhesive tapes are repeatedly adhered to irregular areas according to the shapes, so that the secondary insulation protection effect is achieved.
The cavity insulating assembly 4 and the terminal insulating assembly 11 are sequentially placed in the bus negative bus 6, and as shown in fig. 1, an adhesive is coated on the bottom surface and the upper surface of the terminal insulating assembly 11 on the cavity insulating assembly 4 and is fixed between the bus positive bus 1 and the bus negative bus 6. The terminal insulating assemblies 11 are located at two end ports of the bus negative bus 6, the cavity insulating assemblies 4 are uniformly distributed in the length direction of the bus negative bus 6, and the optimal distribution distance is not more than 150 mm.
And filling and curing the cavity insulating glue 2, and then pasting a polyimide adhesive tape on the surfaces of the confluence negative bus 6, the confluence negative bus binding post 5 and the confluence negative bus mounting groove 8 except for a boss gold-plated surface for secondary insulation treatment.
The bus bar protection insulating plate 10 is attached to and placed under the bus bar negative bus 6, an insulating mounting sleeve 9 is arranged in each bus bar negative bus mounting groove 8, and the bus bar protection insulating plate 10 is in compression fit with the bus bar protection insulating plate for use, as shown in fig. 3.
And penetrating screws into each insulating mounting sleeve 9 one by one, screwing the screws into the reserved threaded holes of the spacecraft cabin plate, and mounting the bus bar to the spacecraft cabin plate.
The distributed power supply and the electronic equipment to be converged are led out of a positive potential end and a negative potential end through lead terminals, penetrate into a converging positive bus terminal 3 and a converging negative bus terminal 5 respectively, are screwed and fixed by nuts, are provided with an external insulating protective cover 7 to isolate a bus bar circuit, and lead wires are routed from a design access 7-1 as shown in figure 2.
The two power supply modules are connected in parallel on the bus bar for power supply, the test shows that the two power supply modules can meet the requirement of current sharing control when being connected in parallel, and the system service is continuous and reliable in the hot plugging process of a single power supply module. When the bus bar carries current 200A at the ambient temperature of 25 ℃, the working temperature rise is less than 30 ℃ within 8 minutes.
The embodiment has the characteristics of quick equipment, flexible design, small volume, light weight, quick heat dissipation and high-capacity transmission, and can improve the current carrying capacity of the main power transmission channel to be more than 100A. The bus can be applied to a bus of an aerospace distributed power supply system and a bus of a primary energy system of a high-flux spacecraft, has low transmission impedance, and is convenient to install, lay and maintain in orbit.
Claims (10)
1. A high-power multilayer composite bus bar capable of being shaped for aerospace is characterized by comprising: the device comprises a bus positive bus (1), a cavity insulating glue (2), a bus positive bus binding post (3), a U-shaped cavity insulating assembly (4), a bus negative bus binding post (5), a bus negative bus (6), an external insulating protective cover (7), a bus negative bus mounting groove (8), an insulating mounting sleeve (9), a bus bar protective insulating plate (10) and a terminal insulating assembly (11);
the bus positive bus (1) and the bus negative bus (6) are used as a whole conductor medium for electric energy integration and transmission, the bus positive bus (1) is connected with a high-voltage end and is positioned in the middle, the bus negative bus (6) is connected with a low-voltage end and is U-shaped and surrounds three surfaces of the bus positive bus (1);
a plurality of bus positive bus binding posts (3) are connected and led out above the bus positive bus (1) and are used for connecting the power supply positive electrode or high potential of aerospace equipment; the side edge of the bus negative bus (6) is connected with and led out of a plurality of bus negative bus binding posts (5) for connecting a power supply negative electrode or a low potential of aerospace equipment;
the terminal insulation assembly (11) seals the terminal of the confluence negative bus (6) and fixes the terminal of the confluence positive bus (1); by adopting a plurality of U-shaped cavity insulating assemblies (4), the arrangement intervals are equal, the bus-bar positive bus (1) is supported and fixed, and the gap intervals between the bus-bar positive bus (1) and the bus-bar negative bus (6) are ensured to be equidistant in the length direction of the bus bar;
the bus positive bus (1), the bus positive bus binding post (3) and the bus negative bus binding post (5) are subjected to insulation treatment except for the wiring plane and the stud position; the outer surfaces of the bus negative buses (6) and the outer surfaces of the multiple groups of bus negative bus mounting grooves (8) are selectively subjected to insulation treatment according to the grounding requirement of the spacecraft; the confluence negative bus mounting groove (8) is connected with the confluence negative bus (6) and is positioned at the bottom of the confluence negative bus (6);
cavity insulating glue (2) is filled at the positions where no U-shaped cavity insulating assembly (4) exists between the U-shaped cavity insulating assemblies (4) and the terminal insulating assembly (11), between two adjacent U-shaped cavity insulating assemblies (4) and between the bus positive bus (1) and the bus negative bus (6), so that the integration of a bus bar insulating structure is realized, and a modularized bus bar is formed;
an external insulation protecting cover (7) is arranged to isolate the non-insulation positions of the wiring of the bus positive bus terminal (3) and the bus negative bus terminal (5);
an insulating mounting sleeve (9) penetrating from the bus bar negative bus bar mounting groove (8) to the bus bar protective insulating plate (10),
the busbar protection insulating plate (10) performs insulation protection on the bottom surfaces of the busbar (6) and the busbar mounting groove (8), namely a busbar mounting plane.
2. The high-power formable multilayer composite bus bar for aerospace of claim 1, wherein: the confluence positive bus (1) and the confluence negative bus (6) are made of aluminum alloy.
3. The high-power formable multilayer composite bus bar for aerospace of claim 1, wherein: the bus negative bus (6) is U-shaped and surrounds the bus positive bus (1) on three sides, so that electric field lines generated after the high-voltage end and the low-voltage end are electrified are limited in the U-shaped interior, and a good electromagnetic compatibility effect is guaranteed.
4. The high-power formable multilayer composite bus bar for aerospace of claim 1, wherein: the bus-bar binding post (3) comprises a round-angle cuboid boss and a stud, the stud and the round-angle cuboid boss are integrally formed, and the round-angle cuboid boss is in direct contact with the bus-bar (1).
5. The high-power formable multilayer composite bus bar for aerospace of claim 1, wherein: the bus negative bus binding post (5) is composed of a boss with a trapezoidal cross section and a stud, the boss with the trapezoidal cross section is in direct contact with the bus negative bus (6), and the stud and the boss with the trapezoidal cross section are integrally formed.
6. The high-power formable multilayer composite bus bar for aerospace of claim 1, wherein: the bus-bar positive bus-bar terminal (3) and the bus-bar negative bus-bar terminal (5) can be designed and determined in advance according to the arrangement condition of electric equipment of a spacecraft cabin plate, the positions and the number of the bus-bar terminals in the length direction are well designed, the wiring direction can be changed, and flexible electric energy shunting is realized.
7. The high-power formable multilayer composite bus bar for aerospace of claim 1, wherein: the terminal insulation assembly (11) seals two terminals of the negative bus bar (6) in the U-shaped interior of the negative bus bar (6).
8. The high-power formable multilayer composite bus bar for aerospace of claim 1, wherein: the U-shaped cavity insulating assembly (4) is positioned between the bus positive bus (1) and the bus negative bus (6) and used for supporting and insulating the bus positive bus (1) and the bus negative bus (6).
9. The high-power energizable multilayer composite bus bar for aerospace according to claim 4 or 5, wherein: the wiring plane is a plane connected with the stud on the boss.
10. The high-power formable multilayer composite bus bar for aerospace of claim 1, wherein: the bus bar installation grooves (8) are symmetrically arranged along the length direction of the bus bar, the positions of installation holes can be reserved according to a spacecraft cabin plate, the slotting positions are designed and confirmed in advance, and the modularized bus bar is convenient to install and fix.
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| CN113488820B (en) * | 2021-08-06 | 2023-05-09 | 中国电子科技集团公司第三十八研究所 | High-integration-level high-power active phased array radar array surface bus bar device |
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| CN111799729A (en) | 2020-10-20 |
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