CN107994669A - A kind of missile-borne microsatellite energy control system - Google Patents
A kind of missile-borne microsatellite energy control system Download PDFInfo
- Publication number
- CN107994669A CN107994669A CN201711236234.6A CN201711236234A CN107994669A CN 107994669 A CN107994669 A CN 107994669A CN 201711236234 A CN201711236234 A CN 201711236234A CN 107994669 A CN107994669 A CN 107994669A
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- China
- Prior art keywords
- storage battery
- missile
- microsatellite
- borne
- control system
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Classifications
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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
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/425—Power storage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/428—Power distribution and management
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
-
- 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
- H02J7/0013—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries acting upon several batteries simultaneously or sequentially
-
- 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
-
- 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
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention discloses a kind of missile-borne microsatellite energy control system, including solar array, MPPT charhing units, voltage transformation module and electricity accumulating unit；The MPPT charhing units are connected with the solar array, for setting the output voltage of the solar array with Maximum Power Output；The voltage transformation module is connected by dc bus with the MPPT charhing units, the voltage for being transformed into the output voltage of MPPT charhing units needed for load；The electricity accumulating unit includes storage battery group and battery management module, and the power end of the battery management module is connected with the storage battery group by a switch module with the dc bus.The missile-borne microsatellite energy control system of the present invention has simple in structure, high reliability.
Description
Technical field
The invention mainly relates to satellite technology field, refers in particular to a kind of missile-borne microsatellite energy control system.
Background technology
Satellite power supply controller system is one of satellite key subsystem, it is the other subsystems and payload of satellite
Reliable energy is provided.The design of missile-borne microsatellite power control system generally has the characteristics that following at present：(1) use
Firer's cutter is as celestial body and the separator of bullet；(2) using three-junction gallium arsenide solar battery, lithium-ions battery group etc.
Space power sources；(3) Power converter system reliable design, volumetric spaces meet microsatellite feature；(3) Power converter system
Centralized management load power demand and fire attack cutter separator, power supply and distribution are combined；(4) storage battery group band BMS is managed, and is prevented
Only energy-storage battery permanent failure.The function of power control system is permanent with constant current to track the maximum power point of solar array
Die pressing type charges a battery, and whole power-supply system charges storage battery and power to load, in satellite not when satellite is shone
When being shone, electronic equipment is by storage battery power supply on star, when converting posture solar energy energy supply deficiency, by solar battery array and electric power storage
Pond, which is combined, powers load.External charging interface is docked with missile-borne power supply, and before satellier injection, missile-borne power supply provides to be used on star
Electricity, control storage battery access busbar, and it is fully charged to storage battery.Control circuit completes the sampling and pretreatment of telemetered signal, connects
By and perform telecommand and landline instruction.
A kind of miniature satellite power system involved in a kind of existing patent " microsatellite energy resource system ", by maximum power point
Tracking circuit and charge management circuit are combined, and realize that solar battery array maximum power is defeated using relatively simple MPPT modes
Go out, while control lithium-ions battery charging voltage, and output voltage is converted.But filled in this patent without outside
Electrical interface, does not possess the separation function of firer's cutter, and switch is accessed without the storage battery of outside control, and system integrity is low,
Reliability is relatively low.
If the factors such as BMS power supplies directly by bussed supply, are put when BMS was detected, high temperature, low temperature and cut off storage battery
When group departs from dc bus, storage battery group can not be accessed direct current by dc bus power down, BMS again after fault-signal removing
Busbar；If BMS power supplies are directly powered by the both ends of storage battery group, when storage battery group needs to store for a long time, BMS mono-
It is straight in running order, can be by storage battery group electric quantity consumption totally.In addition, firer's cutter corresponds to one group using a pair of of fire point
Storage battery, fire point have a pair to backup each other, but storage battery is powered for single group, and reliability reduces.
The content of the invention
The technical problem to be solved in the present invention is that：For technical problem existing in the prior art, the present invention provides one
The missile-borne microsatellite energy control system that kind is simple in structure, reliability is high.
In order to solve the above technical problems, technical solution proposed by the present invention is：
A kind of missile-borne microsatellite energy control system, including solar array, MPPT charhing units, voltage transformation list
Member and electricity accumulating unit；The MPPT charhing units are connected with the solar array, for setting the solar array
Output voltage with Maximum Power Output；The voltage transformation module is connected by dc bus with the MPPT charhing units,
For the voltage being transformed into the output voltage of MPPT charhing units needed for load；The electricity accumulating unit includes storage battery group and electricity
Pond management module, the power end of the battery management module are female by a switch module and the direct current with the storage battery group
Line is connected.
Further as above-mentioned technical proposal is improved：
The switch module includes double electric shock magnetic latching relays, and the power end of the battery management module passes through double electric shocks
The one of which normally opened contact of magnetic latching relay is connected with dc bus, and the storage battery group keeps relay by double electric shock magnetic
The another set normally opened contact of device is connected with dc bus.
The switch module includes two double electric shock magnetic latching relays, and two double electric shock magnetic latching relays are superfluous each other
It is remaining.
The twin coil of double electric shock magnetic latching relays is being parallel with diode, wherein the cathode connection circle of diode just
Pole, the anode of anode connection circle.
The storage battery group includes plurality of groups of storage batteries, is serially connected between each group storage battery.
Every group of electric power storage group includes the storage battery of two series connection.
Each firer's cutter is corresponding with two group storage batteries, and each battery respectively corresponds to the two of firer's cutter
Road and bridge silk.
The storage battery is lithium battery.
The group number of the storage battery is four groups, is corresponding with four firer's cutters.
The voltage transformation module is DC/DC translation circuits.
Compared with prior art, the advantage of the invention is that：
The present invention missile-borne microsatellite energy control system, by the power end of battery management module by switch module with
Dc bus is connected, thus it is abnormal in storage battery group and when causing battery management module to turn off, then by switch module by battery
Management module is connected with dc bus and realizes startup, ensures the normal operation of storage battery group.
Brief description of the drawings
Fig. 1 is the frame assumption diagram of the present invention.
Fig. 2 is the connection circuit figure of the switch module of the present invention.
Fig. 3 is the wiring diagram of firer's cutter in the present invention.
Figure label represents：1st, solar array；2nd, MPPT charhing units；3rd, voltage transformation module；4th, electricity accumulating unit；
5th, charging circuit is isolated；6th, firer's cutter；7th, switch module.
Embodiment
Below in conjunction with Figure of description and specific embodiment, the invention will be further described.
As shown in Figure 1 to Figure 3, the missile-borne microsatellite energy control system of the present embodiment, including solar array 1,
MPPT charhing units 2, voltage transformation module 3 (such as DC/DC translation circuits), isolation charging circuit 5 and electricity accumulating unit 4；MPPT fills
Electric unit 2 is connected with solar array 1, for setting the output voltage of solar array 1 with Maximum Power Output；Voltage
Converter unit 3 is connected by dc bus with MPPT charhing units 2, for the output voltage of MPPT charhing units 2 to be transformed into
Voltage needed for load；Electricity accumulating unit 4 includes storage battery group and battery management module (abbreviation BMS)；The electricity of battery management module
Source is connected with storage battery group by a switch module 7 with dc bus.As shown in Figure 1, solar array 1 passes through photoelectricity
Conversion converts the solar into electric energy, is energy resource system energy source；MPPT charhing units 2 make the output of solar array 1
Power maximizes, and realizes the charge function of constant pressure crossing current；Isolation charging circuit 5 in wherein Fig. 1 is separated in celestial body with guided missile
It is preceding to charge for electricity accumulating unit 4 on star, while power in the case that electricity accumulating unit 4 is without access on star to whole system.Wherein
Storage battery group is the storage element of energy, and battery management module major function is the discharge and recharge of management of battery group, there is provided battery
Equalizaing charge function, and protection storage battery group Electrical Safety.Voltage transformation module 3 is then by voltage transformation for needed for load on star
Voltage.The present invention missile-borne microsatellite energy control system, by the power end of battery management module by switch module 7 with
Dc bus is connected, thus it is abnormal in storage battery group and when causing battery management module to turn off, then by switch module 7 by battery
Management module is connected with dc bus and realizes startup, ensures the normal operation of storage battery group.
In the present embodiment, switch module 7 includes two double electric shock magnetic latching relays, two double electric shock magnetic latching relays
It is mutually redundant, to improve reliability.The power end of battery management module is normal by the one of which of double electric shock magnetic latching relays
Open contact with dc bus to be connected, storage battery group is female by the another set normally opened contact and direct current of double electric shock magnetic latching relays
Line is connected.Specifically, as shown in Fig. 2, V28 and PGND are the positive and negative anodes of satellite primary power source busbar respectively, PWR_ON is electric power storage
Pond group accesses the control signal of dc bus by magnetic latching relay, and PWR_OFF is that storage battery group passes through magnetic latching relay
Depart from the control signal of dc bus, Carry_GND is the signal ground of PWR_ON and PWR_OFF.One magnetic latching relay contains
Two groups of contacts, act at the same time, and wherein magnetic latching relay 4,10 feet connect V28 ends, and 3,9 feet connect Bat4 ends, and 6 feet connect PWR_ON letters
Number, 8 feet connect PWR_OFF signals, and 2,5 feet connect Carry_GND signals.D1 is attempted by coil 5,6 ends, 6 end of cathode connection circle cathode,
D2 is attempted by coil 2,8 ends, 8 end of cathode connection circle cathode, and D1, D2 are used for the direction voltage sensed when clamper coil turns off, protect
Protect front-end circuit.3 feet of magnetic latching relay KA1 individually connect Bat4 ends, the supply line gone here and there into BMS, 9 feet of KA2 and KA2's
3 feet and 9 feet simultaneously connect Bat4 ends, as storage battery group access dc bus end.
Wherein be in series with the current supply circuit of BMS double electric shock magnetic latching relay KA1 3 foot contacts (when there is PWR_ON,
Access V28).Wherein BMS power supplying control signals are all that storage battery group accesses busbar bullet control signal PWR_ON, detailed process
For：
1) before storage battery group does not access dc bus, magnetic latching relay is held off (3, the 9 equal skies of foot connect), and BMS must not
Electricity is without working；
2) when storage battery group internal temperature probe detects that storage battery group temperature is in operating temperature range, bullet control
Signal PWR_ON is opened, and magnetic latching relay is attracted, and 3,9 feet and 4,10 feet are connected at this time, and V28 is connected with storage battery group cathode,
BMS is directly powered by storage battery group, and BMS is opened, and controls storage battery group to access dc bus by BMS internal switches；
3) when putting occurred in storage battery group, high temperature, low temperature when factor when, BMS protection storage battery groups, cut off and are opened inside BMS
Close, storage battery group departs from dc bus at this time；
4) kept after being closed due to magnetic latching relay, BMS is directly powered by storage battery both ends at this time, when BMS is detected
After Failure elimination, BMS internal switches, storage battery group access busbar are controlled.
In the present embodiment, when storage battery group stores electric energy, since switch module 7 is off position, BMS breaks at this time
Electricity, avoids BMS from working long hours storage battery group electric quantity consumption totally；And in storage battery group after abnormal shutdown, pass through switch
BMS is accessed dc bus and restarted by component 7.
As shown in figure 3, in the present embodiment, storage battery group includes plurality of groups of storage batteries, is serially connected between each group storage battery.Tool
Body, every group of electric power storage group includes the storage battery (lithium battery) of two series connection.Storage battery group is connected into by 8 section lithium batteries, and every two
It is one group that string, which draws tap, is powered to firer's cutter 6, totally 5 limits, be respectively Bat0, Bat1, Bat2, Bat3,
Bat4, wherein Bat4 are the cathodes of whole storage battery group, and Bat0 is the anode of whole storage battery group.Each firer's cutter 6 is equal
Two group storage batteries are corresponding with, and each battery respectively corresponds to the two-way igniter wire of firer's cutter 6.Cutter operating voltage is
6~8.4V, every two strings storage battery supply cutter as one group.6 igniter wire initial firing current of firer's cutter uses cross-over control pattern,
Each battery is not corresponded with each pair cutter.As shown in figure 3, wherein battery pack one is supplied respectively to cutter 1# and cutting
Igniter wire all the way in device 2#, battery pack two are supplied respectively to the other igniter wire all the way in cutter 1# and cutter 2#, battery pack three
The igniter wire all the way being supplied respectively in cutter 3# and cutter 4#, battery pack four are supplied respectively in cutter 3# and cutter 4#
In addition igniter wire all the way.The Interleaved control pattern of firer's cutter 6 has increased exponentially the reliability of cutter action.
In the present embodiment, 8 tunnels of the control of firer's cutter 6 using 8 groups of electronic switches in parallel to 4 firer's cutters 6
Igniter wire is carried out at the same time control, and control signal comes from house keeping computer.To ensure the action message of firer's cutter 6, firer's cutting
6 initiation control of device is related to three-level protective, is respectively：
Direct instruction 2：160ms pulse commands A；
Attitude control computer fuze：160ms pulse commands B；
House keeping computer fuze：160ms pulse commands C；
The detonation logic of cutter is：CTL=B ∩ C ∪ A
Meet condition A or meet condition B and C at the same time, firer's cutter 6 detonates, and improves the security reliability of work.
The above is only the preferred embodiment of the present invention, protection scope of the present invention is not limited merely to above-described embodiment,
All technical solutions belonged under thinking of the present invention belong to protection scope of the present invention.It should be pointed out that for the art
For those of ordinary skill, some improvements and modifications without departing from the principles of the present invention, should be regarded as the protection of the present invention
Scope.
Claims (10)
1. a kind of missile-borne microsatellite energy control system, it is characterised in that single including solar array (1), MPPT chargings
First (2), voltage transformation module (3) and electricity accumulating unit (4)；The MPPT charhing units (2) and the solar array (1) phase
Even, for setting the output voltage of the solar array (1) with Maximum Power Output；The voltage transformation module (3) is logical
Dc bus is crossed with the MPPT charhing units (2) to be connected, for the output voltage of MPPT charhing units (2) to be transformed into load
Required voltage；The electricity accumulating unit (4) includes storage battery group and battery management module, the power end of the battery management module
It is connected with the storage battery group by a switch module (7) with the dc bus.
2. missile-borne microsatellite energy control system according to claim 1, it is characterised in that the switch module (7)
Including double electric shock magnetic latching relays, the power end of the battery management module passes through wherein the one of double electric shock magnetic latching relays
Group normally opened contact is connected with dc bus, the another set normally opened contact that the storage battery group passes through double electric shock magnetic latching relays
It is connected with dc bus.
3. missile-borne microsatellite energy control system according to claim 2, it is characterised in that the switch module (7)
Including two double electric shock magnetic latching relays, two double electric shock magnetic latching relays are mutually redundant.
4. the missile-borne microsatellite energy control system according to claim 1 or 2 or 3, it is characterised in that double electric shocks
The twin coil of magnetic latching relay is parallel with the cathode connection circle cathode of diode, wherein diode, and anode connection circle is born
Pole.
5. the missile-borne microsatellite energy control system according to claim 1 or 2 or 3, it is characterised in that the storage battery
Group includes plurality of groups of storage batteries, is serially connected between each group storage battery.
6. missile-borne microsatellite energy control system according to claim 5, it is characterised in that every group of electric power storage group includes
The storage battery of two series connection.
7. missile-borne microsatellite energy control system according to claim 5, it is characterised in that each firer's cutter
(6) two group storage batteries are corresponding with, and each battery respectively corresponds to the two-way igniter wire of firer's cutter (6).
8. missile-borne microsatellite energy control system according to claim 6, it is characterised in that the storage battery is lithium electricity
Pond.
9. missile-borne microsatellite energy control system according to claim 7, it is characterised in that the group number of the storage battery
For four groups, four firer's cutters (6) are corresponding with.
10. the missile-borne microsatellite energy control system according to claim 1 or 2 or 3, it is characterised in that the voltage
Converter unit (3) is DC/DC translation circuits.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711236234.6A CN107994669A (en) | 2017-11-30 | 2017-11-30 | A kind of missile-borne microsatellite energy control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711236234.6A CN107994669A (en) | 2017-11-30 | 2017-11-30 | A kind of missile-borne microsatellite energy control system |
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| Publication Number | Publication Date |
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| CN107994669A true CN107994669A (en) | 2018-05-04 |
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ID=62034663
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| CN201711236234.6A Pending CN107994669A (en) | 2017-11-30 | 2017-11-30 | A kind of missile-borne microsatellite energy control system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110148995A (en) * | 2019-04-17 | 2019-08-20 | 上海空间电源研究所 | A kind of spacecraft reconstruction power-supply system framework |
| CN110615123A (en) * | 2019-10-08 | 2019-12-27 | 深圳航天东方红海特卫星有限公司 | Pulse type over-discharge protection and recovery control circuit of satellite-borne storage battery |
| CN111361765A (en) * | 2020-03-19 | 2020-07-03 | 上海卫星工程研究所 | Spacecraft power supply double-bus system |
| CN111422381A (en) * | 2020-05-15 | 2020-07-17 | 中国科学院微小卫星创新研究院 | Satellite seat charging system |
| CN112636446A (en) * | 2020-12-29 | 2021-04-09 | 中国人民解放军国防科技大学 | Power supply system of quick response small satellite |
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| CN110148995A (en) * | 2019-04-17 | 2019-08-20 | 上海空间电源研究所 | A kind of spacecraft reconstruction power-supply system framework |
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| CN111361765A (en) * | 2020-03-19 | 2020-07-03 | 上海卫星工程研究所 | Spacecraft power supply double-bus system |
| CN111422381A (en) * | 2020-05-15 | 2020-07-17 | 中国科学院微小卫星创新研究院 | Satellite seat charging system |
| CN112636446A (en) * | 2020-12-29 | 2021-04-09 | 中国人民解放军国防科技大学 | Power supply system of quick response small satellite |
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Application publication date: 20180504 |