CN103064392B - Satellite borne integrated electronic system - Google Patents
Satellite borne integrated electronic system Download PDFInfo
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- CN103064392B CN103064392B CN201210584214.9A CN201210584214A CN103064392B CN 103064392 B CN103064392 B CN 103064392B CN 201210584214 A CN201210584214 A CN 201210584214A CN 103064392 B CN103064392 B CN 103064392B
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Abstract
The invention discloses a satellite borne integrated electronic system which comprises a satellite computer, a telemetering lower computer, an upper electric control circuit and a secondary power supply, wherein the satellite computer is respectively connected with a remote-control data transmission device of a satellite, an attitude control device and a load, and the satellite computer and a ground station build a communication line to receive commands from the ground station and enable data to be transmitted to the ground station. The telemetering lower computer is used for collecting temperature, voltage and current of each satellite device, and the telemetering lower computer swaps data with the satellite computer under the control of the satellite computer. The secondary power supply is used for controlling power supplies of the satellite computer and the telemetering lower computer, and the satellite computer is respectively connected with the remote-control data transmission device, the attitude control device and the load through the upper electric control circuit. The satellite computer, the telemetering lower computer, the upper electric control circuit and the secondary power supply are all integrated on a bus board, connection cables of satellite can be reduced, the weight of the satellite can be lightened, and reliability can be improved.
Description
Technical field
The present invention relates to the satellite borne equipment field of satellite, especially, relate to a kind of spaceborne Integrated Electronic System.
Background technology
Satellite Integrated Electronic System is that electronic equipment on satellite interconnects by star, and realize inside satellite information sharing and comprehensive utilization, information processing that function i ntegration, resource restructuring are optimized and transmission system, it is one of five large platform systems arranged side by side with rail control, thermal control, the energy, structure and machinery system in spacecraft.Holonomic system that can have certain function as one, that be made up of software and hardware resources, with the integrated system of multiple different functional modules composition, under unified task scheduling and management, complete all management functions (data management, rail control management, star down data links management on the ground, thermal control management, time management and useful load management) of whole star, its function quintessence is the information flow that information generation, conversion process, message exchange and transmission are distributed.
The microminiaturization of microsatellite platform and critical component thereof, seriation, universalization and standardization are Main Trends of The Developments in whole satellite technology field, are the necessity of satellite commercial, industrialization.NASA proposes " new flourishing age " plan in nineteen ninety-five, target is the design philosophy according to multifunctional all, Satellite Payloads mass ratio is brought up to 70%, and reusable software generic module brings up to 80% ~ 90%, develops with this microsatellite meeting 21 century demand.
The architecture quality of conventional satellite accounts for about 25% of the clean quality of satellite, and cable system quality (cable, wire and connector) generally accounts for 6% ~ 10% of satellite gross mass, and wherein 30% is welding and the mass ratio that to patch etc. shared by cross tie part.As can be seen here, realize the payload weight ratio of more than 70%, new method for designing must be adopted to reduce structure and cable quality, adopt spaceborne electron device High Density Integration to design, exploitation integrated electronics system of micro-satellite then can effectively address this problem.
Summary of the invention
The object of the invention is to provide the spaceborne Integrated Electronic System that a kind of integrated level is high, cable is few, too much causes to solve connection cable in satellite the technical matters that satellite is overweight.
For achieving the above object, the invention provides a kind of spaceborne Integrated Electronic System, comprising:
On board computer, is connected with load with the remote control data transmission equipment of satellite, appearance control equipment, and sets up communication link with land station respectively, to receive the instruction from described land station, transfer data to described land station;
Remote measurement slave computer, for gathering the temperature of each satellite borne equipment, the information of voltage and current, and exchanges data with described On board computer under the control of described On board computer;
Electrifying control circuit and secondary power supply, described secondary power supply is for controlling the power supply of described On board computer and described remote measurement slave computer, and described On board computer controls the power supply of described remote control data transmission equipment, appearance control equipment and load respectively by described electrifying control circuit;
And described On board computer, described remote measurement slave computer, described electrifying control circuit and secondary power supply are all integrated on motherboard.
As a further improvement on the present invention:
Described spaceborne Integrated Electronic System also comprises:
Driving circuit, for the described appearance control equipment for being urged to small part and load, receiving the information from driven described appearance control equipment and load and being transferred to described On board computer; The power supply of described driving circuit is provided by described secondary power supply;
Described driving circuit is integrated on described motherboard, and described at least part of described appearance control equipment and load are electrically connected with described driving circuit by the connector being arranged at the correspondence on described motherboard.
The appearance control equipment of described satellite at least comprises:
Magnetometer, for measuring the magnetic field intensity information of described satellite transit environment, and is transferred to described On board computer by described magnetic field intensity information by described driving circuit;
Magnetic torquer coil, for receiving the control signal from described On board computer, and produces Magnetic Field by described driving circuit, and takes turns according to described Magnetic Field and bias momentum and coordinated the three-axis stabilization over the ground of satellite to control.
The load of described satellite at least comprises:
Camera, is separated the image of moment and substar, and image information is sent to described On board computer by described driving circuit for taking satellite;
AIS receiver, for receiving the ais signal of ship and after carrying out demodulation, sending to described On board computer by described driving circuit.
Described camera is all connected with described driving circuit by serial ports with described AIS receiver.
The antenna of described AIS receiver is launched by antenna and testing circuit is connected with described remote measurement slave computer, and described antenna launches and testing circuit is integrated on described motherboard, described antenna launches and testing circuit is electrically connected with described AIS receiver by the connector being arranged at the correspondence on described motherboard.
Described load also comprises:
Elemental oxygen measuring instrument, described elemental oxygen measuring instrument is by the elemental oxygen metering circuit be integrated on described motherboard and the silverskin resistance being arranged at described satellite external surface, described elemental oxygen metering circuit is by measuring the resistance of described silverskin resistance, calculate the Atomic oxygen density information of the orbit space at satellite place, and described Atomic oxygen density information is sent to described remote measurement slave computer, described silverskin resistance is electrically connected with described elemental oxygen metering circuit by the connector being arranged at the correspondence on described motherboard.
The appearance control equipment of described satellite also comprises:
GPS, for receiving gps signal to obtain the position of satellite, speed and temporal information, and sends to described On board computer after described position, speed and temporal information are set up electrical connection by the connector being arranged at the correspondence on described motherboard;
Used group, for the three-axle magnetic field strength information of three axis angular rates of instrumented satellite, 3-axis acceleration and present position, and sends to described On board computer;
Bias momentum is taken turns, and makes satellite carry out dead axle for the rotor by constant rotational speed under the control of described On board computer;
Simulated solar is quick, for the incident angle by perception sunshine under the control of described On board computer, and two angle informations of the relative sun of instrumented satellite body;
Described bias momentum wheel is electrically connected with described On board computer by the corresponding connector be arranged on described motherboard with described simulated solar is quick.
Described remote measurement slave computer also with for the temperature of the temperature of instrumented satellite running environment, voltage and electric current, voltage and current sensor is connected, and described temperature, voltage and current sensor are electrically connected with described remote measurement slave computer by the connector being arranged at the correspondence on described motherboard.
Described remote control data transmission equipment comprises:
ISM transceiver, for transmission payload task data under the control of described On board computer, and as the backup of USB answering machine;
Described USB answering machine, for completing the coding of measuring and control data, modulation /demodulation, frequency conversion and amplification under the control of described On board computer;
Described ISM transceiver and described USB answering machine are electrically connected with On board computer by the connector being arranged at the correspondence on described motherboard.
The present invention has following beneficial effect:
The spaceborne Integrated Electronic System of the present invention, by sharing the mode of motherboard between each assembly, can reduce connection cable, alleviating satellite weight, improve reliability.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
Accompanying drawing explanation
The accompanying drawing forming a application's part is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the signal wiring schematic diagram of the spaceborne Integrated Electronic System of the preferred embodiment of the present invention.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
See Fig. 1, the spaceborne Integrated Electronic System of one of the present invention, comprise On board computer, remote measurement slave computer, electrifying control circuit and secondary power supply, and On board computer, remote measurement slave computer and electrifying control circuit and secondary power supply are integrated on motherboard, three shares motherboard, decrease the cable connected between three, and resource sharing can be realized better, greatly reduce the volume and weight of spaceborne Integrated Electronic System, improve the load ratio of satellite.Wherein: On board computer is connected with load with the remote control data transmission equipment of satellite, appearance control equipment, and sets up communication link with land station respectively, to receive the instruction from land station, transfers data to land station.Remote measurement slave computer, for gathering the temperature of each satellite borne equipment, the information of voltage and current, and exchanges data with On board computer under the control of On board computer.In electrifying control circuit and secondary power supply, secondary power supply is for controlling the power supply of On board computer and remote measurement slave computer, and On board computer controls the power supply of remote control data transmission equipment, appearance control equipment and load respectively by electrifying control circuit.
In the present embodiment, remote control data transmission equipment comprises ISM transceiver and USB answering machine.Wherein, ISM (IndustrialScientific Medical, international share frequency range) transceiver is used for transmission payload task data under the control of On board computer, and as the backup of USB answering machine.USB answering machine is used under the control of On board computer, complete the coding of measuring and control data, modulation /demodulation, frequency conversion and amplification.ISM transceiver and USB answering machine are electrically connected with On board computer by the connector being arranged at the correspondence on motherboard.
In the present embodiment, spaceborne Integrated Electronic System also comprises driving circuit, for being the appearance control equipment of drive part and load (referring to hereafter), receiving the information from driven appearance control equipment and load and being transferred to On board computer.Driving circuit is integrated on motherboard, and driven appearance control equipment and load are electrically connected with driving circuit by the connector being arranged at the correspondence on motherboard.The power supply of driving circuit is provided by secondary power supply.The driving circuit of external equipment is integrated on motherboard, further reduces the connection cable in spaceborne Integrated Electronic System, decrease the weight of satellite.
In the present embodiment, the appearance control equipment of satellite comprises following six kinds:
1, magnetometer, for the magnetic field intensity information of instrumented satellite running environment, and is transferred to On board computer by magnetic field intensity information by driving circuit.In the present embodiment, magnetometer is connected by RS422 interface with driving circuit.
2, magnetic torquer coil, for receiving the control signal from On board computer, and produces Magnetic Field by driving circuit, and takes turns according to Magnetic Field and bias momentum and coordinated the three-axis stabilization over the ground of satellite to control.
3, GPS, for receiving gps signal to obtain the position of satellite, speed and temporal information, and sends to On board computer after position, speed and temporal information are set up electrical connection by the connector being arranged at the correspondence on motherboard.
4, used group, for the three-axle magnetic field strength information of three axis angular rates of instrumented satellite, 3-axis acceleration and present position, and sends to On board computer.In the present embodiment, used group is electrically connected with On board computer by SPI (Serial Peripheral Interface, Serial Peripheral Interface (SPI)) interface.
5, bias momentum wheel, makes satellite carry out dead axle for the rotor by constant rotational speed under the control of On board computer.In practical application, be control by On board computer the rotary speed information that remote measurement slave computer gathers rotor, and then complete satellite dead axle.
6, simulated solar is quick, for the incident angle by perception sunshine under the control of On board computer, and two angle informations of the relative sun of instrumented satellite body.In practical application, be the four road current signals produced by the quick incoming position according to light of the On board computer control remote measurement slave computer collection sun, and then calculate two angle informations of the relative sun of satellite body.
In the present embodiment, bias momentum wheel is electrically connected with On board computer by the corresponding connector be arranged on motherboard with simulated solar is quick.
In the present embodiment, the load of satellite comprises following three kinds:
1, camera, is separated the image of moment and substar, and image information is sent to On board computer by driving circuit for taking satellite;
2, AIS (Automatic Identification System, the automatic identification system of boats and ships) receiver, for receiving the ais signal of ship and after carrying out demodulation, sending to On board computer by driving circuit.The antenna of AIS receiver is launched by antenna and testing circuit is connected with remote measurement slave computer, and antenna launches and testing circuit is integrated on motherboard, and antenna launches and testing circuit is electrically connected with AIS receiver by the connector being arranged at the correspondence on motherboard.
In the present embodiment, camera is all connected with driving circuit by serial ports with AIS receiver.
3, elemental oxygen measuring instrument, elemental oxygen measuring instrument is by the elemental oxygen metering circuit be integrated on motherboard and the silverskin resistance being arranged at satellite external surface, elemental oxygen metering circuit is by measuring the resistance of silverskin resistance, calculate the Atomic oxygen density information of the orbit space at satellite place, and Atomic oxygen density information is sent to On board computer, silverskin resistance is electrically connected with elemental oxygen metering circuit by the connector being arranged at the correspondence on motherboard.
In the present embodiment, as shown in Figure 1, On board computer is also connected with power-supply controller of electric by I2C bus, and power-supply controller of electric is used for completing the conversion of solar energy sailboard input voltage to busbar voltage in illumination period, powers, charge a battery simultaneously to on-board equipment; In the shade phase by battery discharging, power to on-board equipment.Remote measurement slave computer also with for the temperature of the temperature of instrumented satellite running environment, voltage and electric current, voltage and current sensor is connected, and temperature, voltage and current sensor are electrically connected with remote measurement slave computer by the connector being arranged at the correspondence on motherboard.
In sum, the spaceborne Integrated Electronic System of the present invention, by sharing the mode of motherboard between each assembly, and adopts direct connector mode, the reliability decreasing cable, alleviate the weight of satellite, improve satellite between motherboard and external equipment.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (9)
1. a spaceborne Integrated Electronic System, is characterized in that, comprising:
On board computer, is connected with load with the remote control data transmission equipment of satellite, appearance control equipment, and sets up communication link with land station respectively, to receive the instruction from described land station, transfer data to described land station;
Remote measurement slave computer, for gathering the temperature of each satellite borne equipment, the information of voltage and current, and exchanges data with described On board computer under the control of described On board computer;
Electrifying control circuit and secondary power supply, described secondary power supply is for controlling the power supply of described On board computer and described remote measurement slave computer, and described On board computer controls the power supply of described remote control data transmission equipment, appearance control equipment and load respectively by described electrifying control circuit;
And described On board computer, described remote measurement slave computer, described electrifying control circuit and secondary power supply are all integrated on motherboard;
Described spaceborne Integrated Electronic System also comprises driving circuit, for the described appearance control equipment for being urged to small part and load, receiving the information from driven described appearance control equipment and load and being transferred to described On board computer; The power supply of described driving circuit is provided by described secondary power supply;
Described driving circuit is integrated on described motherboard, and described at least part of described appearance control equipment and load are electrically connected with described driving circuit by the connector being arranged at the correspondence on described motherboard.
2. spaceborne Integrated Electronic System according to claim 1, is characterized in that, the appearance control equipment of described satellite at least comprises:
Magnetometer, for measuring the magnetic field intensity information of described satellite transit environment, and is transferred to described On board computer by described magnetic field intensity information by described driving circuit;
Magnetic torquer coil, for receiving the control signal from described On board computer, and produces Magnetic Field by described driving circuit, and takes turns according to described Magnetic Field and bias momentum and coordinated the three-axis stabilization over the ground of satellite to control.
3. spaceborne Integrated Electronic System according to claim 1, is characterized in that, the load of described satellite at least comprises:
Camera, is separated the image of moment and substar, and image information is sent to described On board computer by described driving circuit for taking satellite;
AIS receiver, for receiving the ais signal of ship and after carrying out demodulation, sending to described On board computer by described driving circuit.
4. spaceborne Integrated Electronic System according to claim 3, is characterized in that,
Described camera is all connected with described driving circuit by serial ports with described AIS receiver.
5. the spaceborne Integrated Electronic System according to claim 3 or 4, it is characterized in that, the antenna of described AIS receiver is launched by antenna and testing circuit is connected with described remote measurement slave computer, and described antenna launches and testing circuit is integrated on described motherboard, described antenna launches and testing circuit is electrically connected with described AIS receiver by the connector being arranged at the correspondence on described motherboard.
6. the spaceborne Integrated Electronic System according to claim 3 or 4, is characterized in that, described load also comprises:
Elemental oxygen measuring instrument, described elemental oxygen measuring instrument is by the elemental oxygen metering circuit be integrated on described motherboard and the silverskin resistance being arranged at described satellite external surface, described elemental oxygen metering circuit is by measuring the resistance of described silverskin resistance, calculate the Atomic oxygen density information of the orbit space at satellite place, and described Atomic oxygen density information is sent to described remote measurement slave computer, described silverskin resistance is electrically connected with described elemental oxygen metering circuit by the connector being arranged at the correspondence on described motherboard.
7. the spaceborne Integrated Electronic System according to claim 2 or 3, is characterized in that, the appearance control equipment of described satellite also comprises:
GPS, for receiving gps signal to obtain the position of satellite, speed and temporal information, and sends to described On board computer after described position, speed and temporal information are set up electrical connection by the connector being arranged at the correspondence on described motherboard;
Used group, for the three-axle magnetic field strength information of three axis angular rates of instrumented satellite, 3-axis acceleration and present position, and sends to described On board computer;
Bias momentum is taken turns, and makes satellite carry out dead axle for the rotor by constant rotational speed under the control of described On board computer;
Simulated solar is quick, for the incident angle by perception sunshine under the control of described On board computer, and two angle informations of the relative sun of instrumented satellite body;
Described bias momentum wheel is electrically connected with described On board computer by the corresponding connector be arranged on described motherboard with described simulated solar is quick.
8. spaceborne Integrated Electronic System according to claim 5, it is characterized in that, described remote measurement slave computer also with for the temperature of the temperature of instrumented satellite running environment, voltage and electric current, voltage and current sensor is connected, and described temperature, voltage and current sensor are electrically connected with described remote measurement slave computer by the connector being arranged at the correspondence on described motherboard.
9. the spaceborne Integrated Electronic System according to any one of claim 2 to 4, is characterized in that, described remote control data transmission equipment comprises:
ISM transceiver, for transmission payload task data under the control of described On board computer, and as the backup of USB answering machine;
Described USB answering machine, for completing the coding of measuring and control data, modulation /demodulation, frequency conversion and amplification under the control of described On board computer;
Described ISM transceiver and described USB answering machine are electrically connected with On board computer by the connector being arranged at the correspondence on described motherboard.
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| CN201210584214.9A CN103064392B (en) | 2012-12-28 | 2012-12-28 | Satellite borne integrated electronic system |
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| CN201210584214.9A CN103064392B (en) | 2012-12-28 | 2012-12-28 | Satellite borne integrated electronic system |
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| CN103064392B true CN103064392B (en) | 2015-05-27 |
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| CN103699069A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Advanced electronic integrated system for microsatellite |
| CN103701542B (en) * | 2013-12-25 | 2015-09-30 | 武汉理工大学 | A kind of ais signal field strength measurement device |
| CN104252137B (en) * | 2014-09-01 | 2018-05-08 | 深圳航天东方红海特卫星有限公司 | A kind of general in-orbit upper note minimum system of microsatellite |
| CN105530040A (en) * | 2014-09-30 | 2016-04-27 | 周飞 | Near-earth orbit celestial burial service system |
| CN105373136A (en) * | 2014-10-22 | 2016-03-02 | 航天恒星科技有限公司 | Integrated electronic system based on VPX architecture |
| CN104460427B (en) * | 2014-10-31 | 2017-01-25 | 上海卫星工程研究所 | Integrated electronic system for modular microsatellite platform |
| CN105514979B (en) * | 2015-11-30 | 2019-05-17 | 上海卫星工程研究所 | The satellite distribution system of high electrical-magnetic compatibility energy |
| CN106557632B (en) * | 2016-11-22 | 2019-12-17 | 上海航天控制技术研究所 | Rapid universal design method for cable network of satellite GNC semi-physical simulation system |
| CN108183741B (en) * | 2017-11-29 | 2021-07-13 | 山东航天电子技术研究所 | Micro-nano satellite universal on-satellite electronic system |
| CN108153183B (en) * | 2017-12-05 | 2019-09-27 | 山东航天电子技术研究所 | Integrated Electronic System on a kind of high functional density star of microminiature |
| CN108106670B (en) * | 2017-12-15 | 2021-01-01 | 北京卫星环境工程研究所 | Low earth orbit space environment and effect integrated detection system |
| CN108594267A (en) * | 2018-04-28 | 2018-09-28 | 中国科学院长春光学精密机械与物理研究所 | The design method of highly integrated integration microsatellite attitude control signal processing unit |
| CN109542063B (en) * | 2018-11-21 | 2020-10-16 | 上海航天计算机技术研究所 | Integrated interface control equipment and satellite-borne integrated electronic system |
| CN109885087B (en) * | 2019-03-12 | 2019-10-29 | 中国人民解放军军事科学院国防科技创新研究院 | The double star short distance formation method of micro-nano satellite |
| CN110647157B (en) * | 2019-09-18 | 2021-07-30 | 中国科学院国家空间科学中心 | Satellite-borne multipath payload manager |
| CN110667896A (en) * | 2019-10-14 | 2020-01-10 | 深圳航天东方红海特卫星有限公司 | Micro-nano satellite integrated electronic system |
| CN113126639A (en) * | 2019-12-30 | 2021-07-16 | 北京九天微星科技发展有限公司 | Satellite whole-satellite system |
| CN111268174A (en) * | 2020-02-27 | 2020-06-12 | 上海利正卫星应用技术有限公司 | Integrated micro-nano satellite electronic system |
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