CN105490339A - Boost power supply controller for carrying spacecraft - Google Patents
Boost power supply controller for carrying spacecraft Download PDFInfo
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- CN105490339A CN105490339A CN201510995429.3A CN201510995429A CN105490339A CN 105490339 A CN105490339 A CN 105490339A CN 201510995429 A CN201510995429 A CN 201510995429A CN 105490339 A CN105490339 A CN 105490339A
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- Prior art keywords
- bus
- electrically connected
- power
- booster circuit
- output
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
Abstract
The invention discloses a boost power supply controller for a carrying spacecraft. The boost power supply controller at least comprises M boost circuits and a bus filter unit, wherein the M boost circuits are used for converting output voltages of N storage batteries into required voltages; M is a natural number greater than 1; an output positive terminal of each storage battery is connected with a battery bus bar through a battery input relay; each battery bus bar is electrically connected with an input positive terminal of at least one boost circuit; a positive power output terminal for of each boost circuit is connected with a same bus bar; negative power input and output terminals of all boost circuits all are electrically connected with a negative bus bar; the bus filter unit is used for filtering a high-frequency signal and a low-frequency signal on a bus; the bus filter unit comprises a hall sensor, a bus high-frequency capacitor and a bus low-frequency capacitor, which are sequentially connected with one another; the hall sensor is used for detecting a current between the bus bar and the positive terminal of the bus high-frequency filter capacitor; and the bus low-frequency capacitor is electrically connected with each load power supply interface through each load output relay.
Description
Technical field
The invention belongs to the physical power source technical field of spacecraft, particularly relate to a kind of mother spacecraft boosting power-supply controller.
Background technology
At home with international space field of power supplies, to the research and development of satellite power system and application along with the fast development of satellite technology reaches its maturity, Comparatively speaking because serving as primary power source of launch vehicle is powered highly reliable and task feature that the is short time, it is first-selected that battery is directly powered to bus always, but along with the appearance of carrier rocket new model, the time that mother spacecraft is executed the task is elongated gradually, and the content of executing the task also is enriched gradually, also starts to propose more demands for a bussed supply.
At present, some aerial mission satellites entered the orbit before the restriction such as flight time length, battery capacity, its cells energy storage is relied on to be not sufficient to the long-time need for electricity before maintaining satellite and the rocket separation, needing by the novel mother spacecraft that such as Upper Stage is such is satellite bussed supply, and the traditional direct battery power mode scope range of the fluctuation of voltage of mother spacecraft is large, the requirement of satellite load to bus quality can not be met.The direct battery power mode schematic block circuit diagram that current mother spacecraft generally adopts as shown in Figure 1.。
Summary of the invention
The technical problem to be solved in the present invention is: provide one to have the input of many storage batterys, and single busbar connection exports the mother spacecraft boosting power-supply controller of high-accuracy voltage; By the parallel combination of multiple booster circuit input and output, storage battery electric energy constant voltage is exported, can be used for floating and two kinds of primary power source subsystem ground connection systems altogether, for mother spacecraft self or satellite provide the reliable primary power supply system of long-time stable to power.
The technical scheme that the present invention takes for the technical problem existed in solution known technology is:
A kind of mother spacecraft boosting power-supply controller, at least comprises:
For the output voltage of N number of storage battery being converted to M booster circuit of required voltage; Wherein M be greater than 1 natural number; The output cathode of each storage battery is connected with a battery busbar by a battery input relay, and each battery busbar is electrically connected with the input plus end of at least one booster circuit; The power stage plus end of booster circuit is all electrically connected with same bus busbar;
The bus filter unit of high-frequency signal and low frequency signal on filtering bus; Described bus filter unit comprises the Hall element, bus high frequency capacitance, the bus low frequency capacitive that are electrically connected successively; Described Hall element is for detecting the electric current between bus busbar to bus high-frequency filter capacitor positive pole; Described bus busbar is electrically connected with bus filter unit positive pole; The positive pole of described bus low frequency capacitive is electrically connected with each road load power supply interface by each road load output relay.
Further: on the lead-out terminal of described bus filter unit, to be electrically connected with error to amplify feedback closed-loop control circuit; The signal input terminal that described error amplifies feedback closed-loop control circuit is electrically connected with bus low frequency capacitive; The signal output terminal that described error amplifies feedback closed-loop control circuit is electrically connected with the control terminal of each booster circuit.
Further: each booster circuit to be electrically connected with current detecting and feedback closed-loop control circuit.
Further: on the power output terminal of each booster circuit, to be parallel with high frequency capacitance.
Further: the control circuit of each booster circuit includes overcurrent protective device.
Further: the control circuit of each booster circuit includes electric voltage over press protective device.
Further: described booster circuit is non-isolation type stepup transformer, the input-output power negative terminal of all booster circuits is all electrically connected with a power negative rail.
The advantage that the present invention has and good effect are:
1. versatility of the present invention is good, the overall structural module boom formula that adopts designs, each construction unit functional independence, ease of assembly and debugging, multiple booster circuit parallel connection uses, be easy to carry out power backup and power expansion according to input battery capacity and load power demand, access owing to being equipped with battery and turn electric output relay, and Combined storage battery use and can form electric power system.
2. boost module of the present invention adopts multimode Hot Spare mode, has input overcurrent and output over-voltage protection function separately, can guarantee to quit work when there is internal fault, reduced by only complete machine peak power output, does not affect completing of power supply task.
3. in-line power loop of the present invention and control circuit electrical isolation, namely can be used as the primary power source of unit on arrow, and compatible arrow floating ground system is powered, and can access again satellite bus, cross-system is that multi-satellite is powered.
4. the present invention compares traditional power-supply system on arrow, there is battery tension input range wide, output voltage precision high (-50 DEG C ~+70 DEG C, within the scope of input battery tension, output no-load is to fully loaded, voltage accuracy can reach output voltage ± 1% within), be applicable to long distance power supply, have on star the advantage (efficiency reaches more than 93%, and ripple peak-to-peak value is less than 0.5V) that high power switching power supply efficiency is high, output ripple is low simultaneously concurrently.
In rated power output situation of the present invention, can work long hours continuously, can adapt to environmental condition on arrow, reliability is high
Compare mother spacecraft traditional storage battery directly to power and the limitation only can powered for self electrical system, the present invention provides high accuracy a bussed supply except can be self electrical system, can also cross-system be that multi-satellite is powered flexibly, and power output is large, voltage accuracy is high, solves cross-system and to power the problem that power supply quality that ground connection system matching problem and long distance power supply far-end ground connection brings reduces.Meet the growth requirement of long-life mother spacecraft Energy control technology, powered by cross-system, expanded the task scope of mother spacecraft, the consumption of satellite battery during decreasing task, is of value to the satellite long-life in orbit.
Accompanying drawing illustrates:
Fig. 1 is the direct battery power mode schematic block circuit diagram that traditional mother spacecraft adopts;
Fig. 2 is the structure chart of the preferred embodiment of the present invention;
Fig. 3 is power main track path profile between construction module in the preferred embodiment of the present invention;
Fig. 4 is voltage in the preferred embodiment of the present invention, double current loop modulation circuit theory diagrams;
Fig. 5 is the supply power mode of system altogether in the preferred embodiment of the present invention;
Fig. 6 is the supply power mode of floating ground system in the preferred embodiment of the present invention;
Fig. 7 is booster circuit output filter circuit in the preferred embodiment of the present invention.
Embodiment
For summary of the invention of the present invention, Characteristic can be understood further, hereby exemplify following examples, and coordinate accompanying drawing to be described in detail as follows:
Refer to Fig. 1 to Fig. 7, a kind of mother spacecraft boosting power-supply controller, comprising:
For the output voltage of N number of storage battery being converted to M non-isolation type booster circuit of required voltage; Wherein M be greater than 1 natural number; The output plus terminal of each storage battery is connected with a battery busbar by a battery input relay, and each battery busbar is electrically connected with the input plus end of at least one booster circuit; The power stage plus end of each booster circuit is all electrically connected with same bus busbar; All booster circuit input-output power negative terminals are all electrically connected with a negative rail.
The bus filter unit of high-frequency signal and low frequency signal on filtering bus; Described bus filter unit comprises the Hall element, bus high frequency capacitance, the bus low frequency capacitive that connect successively; Described Hall element is for detecting the electric current between bus busbar to bus high-frequency filter capacitor anode; Described bus low frequency capacitive is electrically connected with each road load power supply interface by each road load output relay.
Further: on the lead-out terminal of described bus filter unit, to be electrically connected with error to amplify feedback closed-loop control circuit; The signal input terminal that described error amplifies feedback closed-loop control circuit is electrically connected with bus low frequency capacitive; The signal output terminal that described error amplifies feedback closed-loop control circuit is electrically connected with the control terminal of each booster circuit.
Further: each booster circuit to be electrically connected with current detecting and feedback closed-loop control circuit.
Further: on the power output terminal of each booster circuit, be parallel with high frequency capacitance.
Further: the control circuit of each booster circuit includes overcurrent protective device.
Further: the control circuit of each booster circuit includes electric voltage over press protective device.
After above-mentioned mother spacecraft boosting power-supply controller links electric power system, when battery input relay receive external control signal closed after, booster circuit starts simultaneously starts working, and now load does not turn electricity, and booster circuit does not export, and general power supply current is 0.When load needs power supply, close load output relay by control signal and realize turning electricity output, as shown in Figure 2.
Power-supply controller boosting regulates the realization of constant voltage output function
Mother spacecraft boosting power-supply controller comprises three kinds of construction modules, battery can be divided into access boost module, can expand boost module and bus filtration module by function.Can expand boost module boost module can increase and decrease flexibly according to load power demand and backup requirements, and battery access boost module also can configure respective numbers according to storage battery quantity, as accompanying drawing 3.Output voltage signal on bus filtration module amplifies closed loop feedback through error and controls multiple booster circuit, to ensure power-supply controller high accuracy constant voltage power output, meanwhile, each boost module controls by self output current feedback closed loop, balanced output current, as accompanying drawing 4.
Under improving floating ground system, Electromagnetic Compatibility designs
Storage battery power, from battery input relay access battery busbar, extremely exports bus busbar through multiple booster circuit Parallel opertation again, finally by filter circuit and the output relay output of bus filtration module.Which ensure that power flows through each module successively, decrease intermodule cabling, shorten boost pressure controller power output path, thus to reduce on outlet line distributed inductance to the amplification of due to voltage spikes, in addition, each booster circuit exports near-end parallel connection high frequency capacitance, coordinates combinationally using of the row of the high and low frequency electric capacity in bus filtration module, reaches respectively and absorb switching noise and bus low-frequency fluctuation two kinds effect.Finally improve booster circuit power supply quality, as accompanying drawing 7.
Be applicable to the design of different ground connection system
The invention belongs to mother spacecraft series products, design is required according to mother spacecraft floating ground system, internal electric part and casing (structurally) insulate, control signal and power electrical part are isolated, when uploading charged source as mother spacecraft, due to load itself with isolate structurally, power-supply controller floating ground mode is powered.And when carrying class spacecraft cross-system power supply as satellite etc., then by service cable far-end ground connection, form long distance power supply under mode altogether.The present invention has and exports power supply quality preferably, can meet the requirement of power supply target under these two kinds of supply power modes, as shown in accompanying drawing 5, accompanying drawing 6.
The present invention adopts high-power step-up switching power supply to realize the last bussed supply of mother spacecraft and controls, namely mother spacecraft floating ground system is suitable for, power with casing electric insulation mode constant voltage and export, compatible satellite system altogether again can cross-system be satellite bussed supply by satellite far-end ground connection (casing).Meanwhile, present invention optimizes circuit layout, decrease intermodule power cabling, add multiple-stage filtering electric capacity, ensure that and export busbar voltage quality.Therefore, the present invention has novelty on mother spacecraft bus is powered flexibly, is easy to that power is expanded, constant voltage output accuracy high enhances its versatility, has widened high power switch type power supply in space power system range of application.
Above embodiments of the invention have been described in detail, but described content being only preferred embodiment of the present invention, can not being considered to for limiting practical range of the present invention.All equalizations done according to the present patent application scope change and improve, and all should still belong within patent covering scope of the present invention.
Claims (7)
1. a mother spacecraft boosting power-supply controller, is characterized in that: at least comprise:
For the output voltage of N number of storage battery being converted to M booster circuit of required voltage; Wherein M be greater than 1 natural number; The output cathode of each storage battery is connected with a battery busbar by a battery input relay, and each battery busbar is electrically connected with the input plus end of at least one booster circuit; The power stage plus end of booster circuit is all electrically connected with same bus busbar;
The bus filter unit of high-frequency signal and low frequency signal on filtering bus; Described bus filter unit comprises the Hall element, bus high frequency capacitance, the bus low frequency capacitive that are electrically connected successively; Described Hall element is for detecting the electric current between bus busbar to bus high-frequency filter capacitor positive pole; Described bus busbar is electrically connected with bus filter unit positive pole; The positive pole of described bus low frequency capacitive is electrically connected with each road load power supply interface by each road load output relay.
2. according to claim 1 mother spacecraft boosting power-supply controller, it is characterized in that: be electrically connected with on the lead-out terminal of described bus filter unit error amplify feedback closed-loop control circuit; The signal input terminal that described error amplifies feedback closed-loop control circuit is electrically connected with bus low frequency capacitive; The signal output terminal that described error amplifies feedback closed-loop control circuit is electrically connected with the control terminal of each booster circuit.
3. mother spacecraft boosting power-supply controller according to claim 1 or 2, is characterized in that: each booster circuit is electrically connected with current detecting and feedback closed-loop control circuit.
4. according to claim 3 mother spacecraft boosting power-supply controller, it is characterized in that: on the power output terminal of each booster circuit, be parallel with high frequency capacitance.
5. according to claim 4 mother spacecraft boosting power-supply controller, it is characterized in that: the control circuit of each booster circuit includes overcurrent protective device.
6. according to claim 5 mother spacecraft boosting power-supply controller, it is characterized in that: the control circuit of each booster circuit includes electric voltage over press protective device.
7. according to claim 6 mother spacecraft boosting power-supply controller, it is characterized in that: described booster circuit is non-isolation type stepup transformer, the input-output power negative terminal of all booster circuits is all electrically connected with a power negative rail.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510995429.3A CN105490339B (en) | 2015-12-24 | 2015-12-24 | A kind of mother spacecraft boosting power-supply controller |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510995429.3A CN105490339B (en) | 2015-12-24 | 2015-12-24 | A kind of mother spacecraft boosting power-supply controller |
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| CN105490339A true CN105490339A (en) | 2016-04-13 |
| CN105490339B CN105490339B (en) | 2018-04-17 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428637A (en) * | 2016-10-14 | 2017-02-22 | 深圳航天科技创新研究院 | Integrated electric propulsion power system |
| CN112462273A (en) * | 2020-10-23 | 2021-03-09 | 北京空间飞行器总体设计部 | Flight event driven upper-level satellite assembly power supply capability verification system and method |
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| CN203632333U (en) * | 2013-12-19 | 2014-06-04 | 江苏金帆电源科技有限公司 | Energy-saving storage battery forming charging and discharging power supply |
| US20150048785A1 (en) * | 2010-09-20 | 2015-02-19 | Batteroo, Inc. | Methods of extending the life of battery |
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| US20150048785A1 (en) * | 2010-09-20 | 2015-02-19 | Batteroo, Inc. | Methods of extending the life of battery |
| CN203632333U (en) * | 2013-12-19 | 2014-06-04 | 江苏金帆电源科技有限公司 | Energy-saving storage battery forming charging and discharging power supply |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428637A (en) * | 2016-10-14 | 2017-02-22 | 深圳航天科技创新研究院 | Integrated electric propulsion power system |
| CN106428637B (en) * | 2016-10-14 | 2019-03-26 | 深圳航天科技创新研究院 | A kind of full electric propulsion power system |
| CN112462273A (en) * | 2020-10-23 | 2021-03-09 | 北京空间飞行器总体设计部 | Flight event driven upper-level satellite assembly power supply capability verification system and method |
| CN112462273B (en) * | 2020-10-23 | 2023-03-28 | 北京空间飞行器总体设计部 | Flight event driven upper-level satellite assembly power supply capability verification system and method |
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| CN105490339B (en) | 2018-04-17 |
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Effective date of registration: 20211119 Address after: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Patentee after: CETC Energy Co.,Ltd. Address before: 300384 No. 6, Hua Ke seven road, hathai Industrial Park, Xiqing District, Tianjin Patentee before: The 18th Research Institute of China Electronics Technology Group Corporation |
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Address after: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Patentee after: CETC Blue Sky Technology Co.,Ltd. Address before: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Patentee before: CETC Energy Co.,Ltd. |
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