CN105159158A - Electrical bus applicable to micro satellites - Google Patents
Electrical bus applicable to micro satellites Download PDFInfo
- Publication number
- CN105159158A CN105159158A CN201510465808.1A CN201510465808A CN105159158A CN 105159158 A CN105159158 A CN 105159158A CN 201510465808 A CN201510465808 A CN 201510465808A CN 105159158 A CN105159158 A CN 105159158A
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- China
- Prior art keywords
- bus
- power
- data
- applicable
- microsatellite
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
Abstract
The invention provides an electrical bus applicable to micro satellites, comprising physical topology, working mode and interface definition. According to the physical topology, a power bus and a data bus are connected in parallel and carry out transmission independently. In the aspect of working mode, hot backup is adopted. In the aspect of interface definition, the electrical bus leads out a power signal and a data signal through a three-way electrical connector, and the electrical bus and an on-satellite standalone device are interconnected by the same electrical connector. According to the invention, the power bus and the data bus are integrated on the same electrical connector, the contact is defined as the general cable standard, the design ensures that power signals and data signals are transmitted independently and do not interfere with each other, the complexity of whole-satellite power supply and data transmission is reduced, the degree of product standardization and interface unification is improved, the complexity and weight of a whole-satellite cable are reduced, and the design idea of 'plug and play' for micro satellite electronic products is realized.
Description
Technical field
The present invention relates to a kind of electric bus design method being applicable to microsatellite, this electric bus design method is applicable to microsatellite cable system technical field, can meet the demands such as microsatellite rapid Design, fast manufacture.
Background technology
At present, the transmission of microsatellite power supply signal adopts power bus abroad many moonlets to carry out successful flight and puts into practice, have that quality is light, take up room the feature such as little, be in the starting stage at home, but traditional pure power bus often needs custom-made, great majority adopt bus bars (busbar), increase development cost.On tiny satellite star, information transmission have employed data bus technology, conventional data bus comprises the types such as MIL-STD-1553B, SpaceWire, RS-232, RS-485, I2C, CAN, CAN has strong interference immunity, efficiency is high, real-time is good advantage, as a kind of application of high-speed serial bus, adopt the transmission based on priority and receiving handling method, the requirement that real-time communicates with big data quantity can be met.
For microsatellite, the selection collocation of bus need consider, and selects power bus and CAN to carry out physical integration, can improve reliability, versatility, realizes " integration " design.Compared with traditional means, power bus and the integrated electric bus design method of data bus can be reduced further the complicacy of the whole star cable of microsatellite, alleviate the weight of whole star cable, there is higher applicability.
Current space industry does not find explanation or the report of the similar correlation technique with the present invention, not yet collects similar data both at home and abroad yet.
Summary of the invention
For defect of the prior art, the object of this invention is to provide a kind of electric bus design method being applicable to microsatellite, comprise the definition of physical topological structure, mode of operation and interface.
According to a kind of electric bus being applicable to microsatellite provided by the invention, comprising: power bus and data bus;
Power bus and data bus adopt parallel join, individual transmission mode, physical form are carried out integrated, realize data and the same cable transmission of power supply.
Preferably, the mode of operation being applicable to the electric bus of microsatellite described in is:
Adopt Hot Spare mode, power bus and data bus all have one main one for two-way;
Each road power bus all can carry out control power supply by the switch of Power Management Unit, when meeting whole star power demand, provide full adjustment busbar voltage of regulation pressure value, and the output of each road power bus all can meet whole star power demand;
Data bus meets CAN2.0 communications protocol, and the bus data stream of data bus is dispatched centered by computing machine, when meeting total inorganic nitrogen requirement and system real time requirement, selects master-slave mode working method.
Preferably, the interface being applicable to the electric bus of microsatellite described in is defined as:
The described electric bus being applicable to microsatellite draws power signal and data-signal by tee electric connector; and interconnected by unit on same electric connector and star; each hang over described in the unit be applicable in the electric bus of microsatellite all want allocating power bus interface protection circuit; and carry out the secondary power distribution of unit inside as required; all to configure corresponding data bus controller simultaneously, complete data transmit-receive.
Preferably, described data bus and power bus integrate, and form the universal cordage standard with unified electric connector and contact definition, ensure signal and power supply individual transmission simultaneously, do not interfere with each other.
Compared with prior art, the present invention has following beneficial effect:
1, reduce the complicacy that whole star is powered and data are transmitted, alleviate the weight of whole star cable, the standardization and the interface that improve product unitize, and ensure that the modularization of microsatellite, meet the design concept of " plug and play ".
2, can realize the mass production of whole star electricity bus, goods-shelf type is stocked, and reduces development cost.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is physical topological structure schematic diagram.
Embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some changes and improvements can also be made.These all belong to protection scope of the present invention.
Core concept of the present invention is to provide a kind of electric bus design method being applicable to microsatellite, comprising: physical topological structure, mode of operation and interface define.
Please refer to Fig. 1, physical topological structure of the present invention comprises power bus 101, data bus 102, three-way connector 103 and unit terminal adapter 104.Power bus 101 and data bus 102 walk abreast individual transmission, and power bus 101 comprises voltage A, voltage B two-way, and the rated current that the number of cables on every road can bear according to load power and cable decides; Data bus 102 comprises CANA, CANB two-way, and every road CAN includes CANH, CANL two cables or two point two-wire four cables; Power signal and data-signal are all integrated in unified electric connector and transmit by three-way connector 103 and unit terminal adapter 104, and its quantity is determined according to the quantity of institute's sheet machine in electric bus, and are not limited to 6 unit interfaces painting in figure.
Please refer to Fig. 1, mode of operation of the present invention adopts Hot Spare mode, and data bus and power bus all have a master one standby.Each road power bus 101 all carries out control power supply by the switch of Power Management Unit, when meeting whole star power demand, there is provided full adjustment busbar voltage of regulation pressure value, and the output of each road power bus 101 all can meet whole star power demand; Data bus 102 meets CAN2.0 communications protocol, and bus data stream is dispatched centered by computing machine, when meeting total inorganic nitrogen requirement and system real time requirement, selects master-slave mode working method.
Please refer to Fig. 1, interface definition of the present invention adopts integrated design, electricity bus draws data-signal and power signal by tee electric connector 103, and comprise integrated electronics by same unit end electric connector 104 with unit on star, power management, appearance control unit, advance unit, load unit and other units interconnect, the node definition of all unit end electric connectors 104 is identical, allocating power bus interface protection circuit all wanted by each unit hung in electric bus, and carry out the secondary power distribution of unit inside as required, all to configure corresponding data bus controller simultaneously, complete data transmit-receive.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make a variety of changes within the scope of the claims or revise, and this does not affect flesh and blood of the present invention.
Claims (4)
1. be applicable to an electric bus for microsatellite, it is characterized in that, comprising: power bus and data bus;
Power bus and data bus adopt parallel join, individual transmission mode, physical form are carried out integrated, realize data and the same cable transmission of power supply.
2. the electric bus being applicable to microsatellite according to claim 1, is characterized in that, described in be applicable to the electric bus of microsatellite mode of operation be:
Adopt Hot Spare mode, power bus and data bus all have one main one for two-way;
Each road power bus all can carry out control power supply by the switch of Power Management Unit, when meeting whole star power demand, provide full adjustment busbar voltage of regulation pressure value, and the output of each road power bus all can meet whole star power demand;
Data bus meets CAN2.0 communications protocol, and the bus data stream of data bus is dispatched centered by computing machine, when meeting total inorganic nitrogen requirement and system real time requirement, selects master-slave mode working method.
3. the electric bus being applicable to microsatellite according to claim 1, is characterized in that, described in be applicable to the electric bus of microsatellite interface be defined as:
The described electric bus being applicable to microsatellite draws power signal and data-signal by tee electric connector; and interconnected by unit on same electric connector and star; each hang over described in the unit be applicable in the electric bus of microsatellite all want allocating power bus interface protection circuit; and carry out the secondary power distribution of unit inside as required; all to configure corresponding data bus controller simultaneously, complete data transmit-receive.
4. the electric bus being applicable to microsatellite according to claim 1, it is characterized in that, described data bus and power bus integrate, and form the universal cordage standard with unified electric connector and contact definition, ensure signal and power supply individual transmission simultaneously, do not interfere with each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510465808.1A CN105159158A (en) | 2015-07-31 | 2015-07-31 | Electrical bus applicable to micro satellites |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510465808.1A CN105159158A (en) | 2015-07-31 | 2015-07-31 | Electrical bus applicable to micro satellites |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105159158A true CN105159158A (en) | 2015-12-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510465808.1A Pending CN105159158A (en) | 2015-07-31 | 2015-07-31 | Electrical bus applicable to micro satellites |
Country Status (1)
| Country | Link |
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| CN (1) | CN105159158A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111891398A (en) * | 2020-08-13 | 2020-11-06 | 中国人民解放军国防科技大学 | Elastic universal intelligent satellite hardware system architecture |
| CN113900460A (en) * | 2021-10-25 | 2022-01-07 | 哈尔滨工大卫星技术有限公司 | Temperature control method, system and medium for satellite platform |
| CN114759637A (en) * | 2022-04-28 | 2022-07-15 | 长光卫星技术股份有限公司 | Bus type power distribution framework suitable for extensible micro-nano satellite platform |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111891398A (en) * | 2020-08-13 | 2020-11-06 | 中国人民解放军国防科技大学 | Elastic universal intelligent satellite hardware system architecture |
| CN111891398B (en) * | 2020-08-13 | 2022-03-11 | 中国人民解放军国防科技大学 | Elastic universal intelligent satellite hardware system architecture |
| CN113900460A (en) * | 2021-10-25 | 2022-01-07 | 哈尔滨工大卫星技术有限公司 | Temperature control method, system and medium for satellite platform |
| CN114759637A (en) * | 2022-04-28 | 2022-07-15 | 长光卫星技术股份有限公司 | Bus type power distribution framework suitable for extensible micro-nano satellite platform |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20151216 |
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| RJ01 | Rejection of invention patent application after publication |