CN103064392B - Satellite borne integrated electronic system - Google Patents
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Abstract
本发明公开了一种星载综合电子系统，包括星上计算机，分别与卫星的遥控数传设备、姿控设备和载荷相连，并与地面站建立通讯链路，以接收来自地面站的指令，将数据传输给地面站；遥测下位机，用于采集各星载设备的温度、电压和电流的信息，并在星上计算机的控制下与星上计算机交换数据；上电控制电路和二次电源，二次电源用于控制星上计算机及遥测下位机的电源，且星上计算机通过上电控制电路分别控制遥控数传设备、姿控设备和载荷的电源；且星上计算机、遥测下位机、上电控制电路和二次电源均集成于母板上，能减少卫星中的连接线缆、减轻卫星重量、提高可靠性。
The invention discloses a satellite-borne integrated electronic system, which includes an on-board computer, which is respectively connected with satellite remote control data transmission equipment, attitude control equipment and load, and establishes a communication link with a ground station to receive instructions from the ground station, The data is transmitted to the ground station; the telemetry lower computer is used to collect the temperature, voltage and current information of each spaceborne device, and exchange data with the on-board computer under the control of the on-board computer; the power-on control circuit and the secondary power supply , the secondary power supply is used to control the power supply of the on-board computer and the telemetry lower computer, and the on-board computer controls the power supply of the remote control data transmission equipment, the attitude control equipment and the load through the power-on control circuit; and the on-board computer, the telemetry lower computer, Both the power-on control circuit and the secondary power supply are integrated on the motherboard, which can reduce the connection cables in the satellite, reduce the weight of the satellite, and improve reliability.
Description
技术领域technical field
本发明涉及卫星的星载设备领域，特别地，涉及一种星载综合电子系统。The invention relates to the field of satellite on-board equipment, in particular to an on-board integrated electronic system.
背景技术Background technique
卫星综合电子系统是星上将星载电子设备互连，并实现卫星内部信息共享和综合利用、功能集成、资源重组优化的信息处理和传输系统，它是航天器中与姿轨控、热控、能源、结构与机构系统并列的五大平台系统之一。作为一个能具有一定功能的、由软硬件资源组成的完整系统，是以多种不同的功能模块组成的集成系统，在统一的任务调度和管理下，完成整星的所有管理功能(数据管理、姿轨控管理、星地上下行数据链路管理、热控管理、时间管理及有效载荷管理)，其功能本质是信息产生、变换处理、信息交换和传输分发的信息流。The satellite integrated electronic system is an information processing and transmission system that interconnects on-board electronic equipment and realizes satellite internal information sharing and comprehensive utilization, function integration, and resource reorganization optimization. It is one of the five major platform systems juxtaposed with energy, structure and institutional systems. As a complete system with certain functions and composed of software and hardware resources, it is an integrated system composed of a variety of different functional modules. Under the unified task scheduling and management, it can complete all the management functions of the whole star (data management, Attitude and orbit control management, satellite ground uplink and downlink data link management, thermal control management, time management and payload management), the essence of its function is the information flow of information generation, transformation processing, information exchange and transmission and distribution.
微小卫星平台及其关键部件的微型化、系列化、通用化和标准化是整个卫星技术领域的一个主要发展趋势，是卫星商业化、产业化的必然需求。NASA于1995年提出“新盛世”计划，目标是按照多功能一体化的设计思想，将卫星有效载荷质量比提高到70％，可重复使用的软件通用模块提高到80％～90％，以此研制出满足21世纪需求的微小卫星。The miniaturization, serialization, generalization and standardization of the micro-satellite platform and its key components is a major development trend in the entire satellite technology field, and is an inevitable demand for satellite commercialization and industrialization. NASA put forward the "New Prosperity" plan in 1995. The goal is to increase the mass ratio of satellite payloads to 70% and the reusable software general modules to 80% to 90% in accordance with the design idea of multi-functional integration. Develop microsatellites that meet the needs of the 21st century.
传统卫星的结构质量占卫星净质量的25％左右，电缆系统质量(电缆、导线和接插件)一般占卫星总质量的6％～10％，其中30％为焊接和接插等互连件所占的质量比例。由此可见，要实现70％以上的有效载荷重量比，必须采用新的设计方法来降低结构和电缆质量，采用星载电子器件高密度集成设计，开发微小卫星综合电子系统则能够有效解决这一问题。The structural mass of a traditional satellite accounts for about 25% of the net mass of the satellite, and the mass of the cable system (cables, wires, and connectors) generally accounts for 6% to 10% of the total mass of the satellite, of which 30% is due to interconnections such as welding and plugging. percentage of mass. It can be seen that in order to achieve a payload-to-weight ratio of more than 70%, new design methods must be adopted to reduce the quality of structures and cables. The use of high-density integrated design of on-board electronic devices and the development of integrated electronic systems for microsatellites can effectively solve this problem. question.
发明内容Contents of the invention
本发明目的在于提供一种集成度高、线缆少的星载综合电子系统，以解决卫星中连接线缆过多导致卫星过重的技术问题。The purpose of the present invention is to provide a satellite-borne integrated electronic system with high integration and few cables, so as to solve the technical problem that the satellite is too heavy due to too many cables connected in the satellite.
为实现上述目的，本发明提供了一种星载综合电子系统，包括：To achieve the above object, the present invention provides a space-borne integrated electronic system, comprising:
星上计算机，分别与卫星的遥控数传设备、姿控设备和载荷相连，并与地面站建立通讯链路，以接收来自所述地面站的指令，将数据传输给所述地面站；The on-board computer is respectively connected to the remote control data transmission equipment, attitude control equipment and payload of the satellite, and establishes a communication link with the ground station to receive instructions from the ground station and transmit data to the ground station;
遥测下位机，用于采集各星载设备的温度、电压和电流的信息，并在所述星上计算机的控制下与所述星上计算机交换数据；The telemetering lower computer is used to collect the temperature, voltage and current information of each on-board device, and exchange data with the on-board computer under the control of the on-board computer;
上电控制电路和二次电源，所述二次电源用于控制所述星上计算机及所述遥测下位机的电源，且所述星上计算机通过所述上电控制电路分别控制所述遥控数传设备、姿控设备和载荷的电源；A power-on control circuit and a secondary power supply, the secondary power supply is used to control the power supplies of the on-board computer and the remote measurement slave computer, and the on-board computer controls the remote control data through the power-on control circuit Transmission equipment, attitude control equipment and load power supply;
且所述星上计算机、所述遥测下位机、所述上电控制电路和二次电源均集成于母板上。And the on-board computer, the telemetry slave computer, the power-on control circuit and the secondary power supply are all integrated on the motherboard.
作为本发明的进一步改进：As a further improvement of the present invention:
所述星载综合电子系统还包括：The on-board integrated electronic system also includes:
驱动电路，用于为驱动至少部分的所述姿控设备和载荷，接收来自被驱动的所述姿控设备和载荷的信息并传输给所述星上计算机；所述驱动电路的电源由所述二次电源提供；The drive circuit is used to drive at least part of the attitude control equipment and load, receive information from the driven attitude control equipment and load and transmit it to the on-board computer; the power supply of the drive circuit is controlled by the Secondary power supply;
所述驱动电路集成于所述母板上，所述至少部分的所述姿控设备和载荷通过设置于所述母板上的对应的接插件与所述驱动电路电连接。The drive circuit is integrated on the motherboard, and the at least part of the attitude control device and the load are electrically connected to the drive circuit through corresponding connectors provided on the motherboard.
所述卫星的姿控设备至少包括：The attitude control equipment of the satellite includes at least:
磁强计，用于测量所述卫星运行环境的磁场强度信息，并将所述磁场强度信息通过所述驱动电路传输给所述星上计算机；a magnetometer, used to measure the magnetic field strength information of the satellite operating environment, and transmit the magnetic field strength information to the on-board computer through the drive circuit;
磁力矩器线圈，用于接收来自所述星上计算机的控制信号，并通过所述驱动电路产生磁场信息，并根据所述磁场信息与偏置动量轮配合完成卫星的对地三轴稳定控制。The magnetic torquer coil is used to receive control signals from the on-board computer, generate magnetic field information through the drive circuit, and cooperate with the bias momentum wheel according to the magnetic field information to complete the three-axis stability control of the satellite on the ground.
所述卫星的载荷至少包括：The payload of the satellite includes at least:
相机，用于拍摄卫星分离时刻以及星下点的图像，并将影像信息通过所述驱动电路发送给所述星上计算机；The camera is used to take images of satellite separation time and sub-satellite points, and send the image information to the on-board computer through the drive circuit;
AIS接收机，用于接收船只的AIS信号并进行解调后，通过所述驱动电路发送给所述星上计算机。The AIS receiver is used for receiving and demodulating the AIS signal of the ship, and sending it to the on-board computer through the driving circuit.
所述相机和所述AIS接收机均通过串口与所述驱动电路连接。Both the camera and the AIS receiver are connected to the driving circuit through a serial port.
所述AIS接收机的天线通过天线展开及检测电路与所述遥测下位机相连，且所述天线展开及检测电路集成于所述母板上，所述天线展开及检测电路通过设置于所述母板上的对应的接插件与所述AIS接收机电连接。The antenna of the AIS receiver is connected to the telemetry slave computer through the antenna deployment and detection circuit, and the antenna deployment and detection circuit is integrated on the motherboard, and the antenna deployment and detection circuit is arranged on the motherboard Corresponding connectors on the board are electrically connected to the AIS receiver.
所述载荷还包括：The load also includes:
原子氧测量仪，所述原子氧测量仪由集成在所述母板上的原子氧测量电路以及设置于所述卫星外表面的银膜电阻，所述原子氧测量电路通过测量所述银膜电阻的阻值，计算卫星所在的轨道空间的原子氧浓度信息，并将所述原子氧浓度信息发送给所述遥测下位机，所述银膜电阻通过设置于所述母板上的对应的接插件与所述原子氧测量电路电连接。An atomic oxygen measuring instrument, the atomic oxygen measuring instrument is composed of an atomic oxygen measuring circuit integrated on the motherboard and a silver film resistance arranged on the outer surface of the satellite, and the atomic oxygen measuring circuit measures the silver film resistance resistance value, calculate the atomic oxygen concentration information of the orbital space where the satellite is located, and send the atomic oxygen concentration information to the telemetry lower computer, and the silver film resistance is set through the corresponding connector on the motherboard It is electrically connected with the atomic oxygen measurement circuit.
所述卫星的姿控设备还包括：The attitude control equipment of the satellite also includes:
GPS接收机，用于接收GPS信号以获取卫星的位置、速度以及时间信息，并将所述位置、速度以及时间信息通过设置于所述母板上的对应的接插件建立电连接后发送给所述星上计算机；The GPS receiver is used to receive GPS signals to obtain the position, speed and time information of the satellite, and to send the position, speed and time information to the said motherboard after establishing an electrical connection with the corresponding connector on the motherboard. on-board computer;
惯组，用于测量卫星的三轴角速度、三轴加速度、和所处位置的三轴磁场强度信息，并发送给所述星上计算机；The inertial group is used to measure the three-axis angular velocity, three-axis acceleration, and three-axis magnetic field strength information of the satellite, and send it to the on-board computer;
偏置动量轮，用于在所述星上计算机的控制下通过恒定转速的转子使卫星进行定轴；an offset momentum wheel for pivoting the satellite with a constant speed rotor under the control of said onboard computer;
模拟太阳敏，用于在所述星上计算机的控制下通过感知太阳光的入射角度，测量卫星本体相对太阳的二位角度信息；Simulate the sun sensor, which is used to measure the two-dimensional angle information of the satellite body relative to the sun by sensing the incident angle of sunlight under the control of the on-board computer;
所述偏置动量轮与所述模拟太阳敏通过设置于所述母板上的对应的接插件与所述星上计算机电连接。The bias momentum wheel and the simulated solar sensor are electrically connected to the on-board computer through corresponding connectors arranged on the motherboard.
所述遥测下位机还与用于测量卫星运行环境的温度、电压及电流的温度、电压及电流传感器相连，所述温度、电压及电流传感器通过设置于所述母板上的对应的接插件与所述遥测下位机电连接。The remote measurement lower computer is also connected with the temperature, voltage and current sensors for measuring the temperature, voltage and current of the satellite operating environment, and the temperature, voltage and current sensors are connected to the corresponding connectors on the motherboard through the corresponding connectors. The telemetry lower electromechanical connection.
所述遥控数传设备包括：The remote control data transmission equipment includes:
ISM收发信机，用于所述星上计算机的控制下传输载荷任务数据，并作为USB应答机的备份；The ISM transceiver is used to transmit payload task data under the control of the on-board computer, and is used as a backup of the USB transponder;
所述USB应答机，用于在所述星上计算机的控制下完成测控数据的编码、调制解调、变频以及放大；The USB transponder is used to complete the encoding, modulation and demodulation, frequency conversion and amplification of measurement and control data under the control of the on-board computer;
所述ISM收发信机和所述USB应答机通过设置于所述母板上的对应的接插件与星上计算机电连接。The ISM transceiver and the USB answering machine are electrically connected to the on-board computer through corresponding connectors arranged on the motherboard.
本发明具有以下有益效果：The present invention has the following beneficial effects:
本发明星载综合电子系统，各组件之间通过共用母板的方式，能减少连接线缆、减轻卫星重量、提高可靠性。In the satellite-borne integrated electronic system of the present invention, each component can reduce connecting cables, reduce the weight of the satellite, and improve reliability by sharing the mother board.
除了上面所描述的目的、特征和优点之外，本发明还有其它的目的、特征和优点。下面将参照图，对本发明作进一步详细的说明。In addition to the objects, features and advantages described above, the present invention has other objects, features and advantages. Hereinafter, the present invention will be described in further detail with reference to the drawings.
附图说明Description of drawings
构成本申请的一部分的附图用来提供对本发明的进一步理解，本发明的示意性实施例及其说明用于解释本发明，并不构成对本发明的不当限定。在附图中：The accompanying drawings constituting a part of this application are used to provide further understanding of the present invention, and the schematic embodiments and descriptions of the present invention are used to explain the present invention, and do not constitute an improper limitation of the present invention. In the attached picture:
图1是本发明优选实施例的星载综合电子系统的硬件连接示意图。Fig. 1 is a schematic diagram of the hardware connection of the on-board integrated electronic system of the preferred embodiment of the present invention.
具体实施方式Detailed ways
以下结合附图对本发明的实施例进行详细说明，但是本发明可以由权利要求限定和覆盖的多种不同方式实施。The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in many different ways defined and covered by the claims.
参见图1，本发明的一种星载综合电子系统，包括星上计算机、遥测下位机、上电控制电路和二次电源，且星上计算机、遥测下位机以及上电控制电路和二次电源集成于母板上，三者共用母板，减少了三者之间连接的线缆，并可更好地实现资源共享、大大减少了星载综合电子系统的体积和重量，提高了卫星的载荷比。其中：星上计算机分别与卫星的遥控数传设备、姿控设备和载荷相连，并与地面站建立通讯链路，以接收来自地面站的指令，将数据传输给地面站。遥测下位机，用于采集各星载设备的温度、电压和电流的信息，并在星上计算机的控制下与星上计算机交换数据。上电控制电路和二次电源中，二次电源用于控制星上计算机及遥测下位机的电源，且星上计算机通过上电控制电路分别控制遥控数传设备、姿控设备和载荷的电源。Referring to Fig. 1, a kind of on-board integrated electronic system of the present invention comprises on-board computer, telemetry slave computer, power-on control circuit and secondary power supply, and on-star computer, telemetry slave computer, power-on control circuit and secondary power supply Integrated on the motherboard, the three share the motherboard, reducing the cables connected between the three, and better sharing resources, greatly reducing the volume and weight of the satellite-borne integrated electronic system, and increasing the load of the satellite Compare. Among them: the computer on the satellite is connected with the satellite's remote control data transmission equipment, attitude control equipment and payload, and establishes a communication link with the ground station to receive instructions from the ground station and transmit data to the ground station. The telemetry lower computer is used to collect information on the temperature, voltage and current of each space-borne device, and exchange data with the on-board computer under the control of the on-board computer. In the power-on control circuit and the secondary power supply, the secondary power supply is used to control the power supply of the on-board computer and the telemetry slave computer, and the on-board computer controls the power supply of the remote control data transmission equipment, attitude control equipment and load through the power-on control circuit.
本实施例中，遥控数传设备包括ISM收发信机和USB应答机。其中，ISM(IndustrialScientific Medical,国际共用频段)收发信机用于星上计算机的控制下传输载荷任务数据，并作为USB应答机的备份。USB应答机用于在星上计算机的控制下完成测控数据的编码、调制解调、变频以及放大。ISM收发信机和USB应答机通过设置于母板上的对应的接插件与星上计算机电连接。In this embodiment, the remote control data transmission device includes an ISM transceiver and a USB answering machine. Among them, the ISM (Industrial Scientific Medical, international shared frequency band) transceiver is used to transmit payload mission data under the control of the on-board computer, and is used as a backup of the USB transponder. The USB transponder is used to complete the coding, modulation and demodulation, frequency conversion and amplification of measurement and control data under the control of the on-board computer. The ISM transceiver and the USB answering machine are electrically connected with the on-board computer through corresponding connectors arranged on the motherboard.
本实施例中，星载综合电子系统还包括驱动电路，用于为驱动部分的姿控设备和载荷(详见下文)，接收来自被驱动的姿控设备和载荷的信息并传输给星上计算机。驱动电路集成于母板上，被驱动的姿控设备和载荷通过设置于母板上的对应的接插件与驱动电路电连接。驱动电路的电源由二次电源提供。将外接设备的驱动电路集成于母板上，进一步减少了星载综合电子系统中的连接线缆，减少了卫星的重量。In this embodiment, the spaceborne integrated electronic system also includes a drive circuit, which is used to drive the attitude control equipment and load (see below for details), receive information from the driven attitude control equipment and load and transmit it to the on-board computer . The drive circuit is integrated on the motherboard, and the driven attitude control equipment and load are electrically connected to the drive circuit through corresponding connectors arranged on the motherboard. The power supply of the drive circuit is provided by the secondary power supply. The drive circuit of the external device is integrated on the motherboard, which further reduces the connection cables in the satellite-borne integrated electronic system and reduces the weight of the satellite.
本实施例中，卫星的姿控设备包括以下六种：In this embodiment, the satellite attitude control equipment includes the following six types:
1、磁强计，用于测量卫星运行环境的磁场强度信息，并将磁场强度信息通过驱动电路传输给星上计算机。本实施例中，磁强计与驱动电路通过RS422接口连接。1. The magnetometer is used to measure the magnetic field strength information of the satellite operating environment, and transmit the magnetic field strength information to the on-board computer through the drive circuit. In this embodiment, the magnetometer is connected to the drive circuit through an RS422 interface.
2、磁力矩器线圈，用于接收来自星上计算机的控制信号，并通过驱动电路产生磁场信息，并根据磁场信息与偏置动量轮配合完成卫星的对地三轴稳定控制。2. The magnetic torque device coil is used to receive the control signal from the computer on the satellite, and generate magnetic field information through the drive circuit, and cooperate with the bias momentum wheel according to the magnetic field information to complete the three-axis stability control of the satellite to the ground.
3、GPS接收机，用于接收GPS信号以获取卫星的位置、速度以及时间信息，并将位置、速度以及时间信息通过设置于母板上的对应的接插件建立电连接后发送给星上计算机。3. GPS receiver, used to receive GPS signals to obtain satellite position, speed and time information, and send the position, speed and time information to the on-board computer after establishing an electrical connection through the corresponding connector set on the motherboard .
4、惯组，用于测量卫星的三轴角速度、三轴加速度、和所处位置的三轴磁场强度信息，并发送给星上计算机。本实施例中，惯组通过SPI(Serial Peripheral Interface,串行外设接口)接口与星上计算机电连接。4. The inertial group is used to measure the satellite's three-axis angular velocity, three-axis acceleration, and three-axis magnetic field strength information at its location, and send them to the on-board computer. In this embodiment, the inertial group is electrically connected to the on-board computer through a SPI (Serial Peripheral Interface, Serial Peripheral Interface) interface.
5、偏置动量轮，用于在星上计算机的控制下通过恒定转速的转子使卫星进行定轴。实际应用中，是由星上计算机控制遥测下位机采集转子的转速信息，进而完成卫星定轴。5. The offset momentum wheel is used to fix the axis of the satellite through the rotor of constant speed under the control of the on-board computer. In practical application, the satellite computer controls the remote measurement lower computer to collect the rotor speed information, and then completes the satellite axis positioning.
6、模拟太阳敏，用于在星上计算机的控制下通过感知太阳光的入射角度，测量卫星本体相对太阳的二位角度信息。实际应用中，是由星上计算机控制遥测下位机采集太阳敏依据光的入射位置产生的四路电流信号，进而计算得到卫星本体相对太阳的二位角度信息。6. Simulate the sun sensor, which is used to measure the two-dimensional angle information of the satellite body relative to the sun by sensing the incident angle of sunlight under the control of the on-board computer. In practical application, the on-board computer controls the telemetry lower computer to collect four-way current signals generated by the sun sensor according to the incident position of light, and then calculates the two-dimensional angle information of the satellite body relative to the sun.
本实施例中，偏置动量轮与模拟太阳敏通过设置于母板上的对应的接插件与星上计算机电连接。In this embodiment, the bias momentum wheel and the simulated solar sensor are electrically connected to the on-board computer through corresponding connectors arranged on the motherboard.
本实施例中，卫星的载荷包括以下三种：In this embodiment, the satellite loads include the following three types:
1、相机，用于拍摄卫星分离时刻以及星下点的图像，并将影像信息通过驱动电路发送给星上计算机；1. The camera is used to take images of satellite separation time and sub-satellite points, and send the image information to the on-board computer through the drive circuit;
2、AIS(Automatic Identification System，船舶自动身份识别系统)接收机，用于接收船只的AIS信号并进行解调后，通过驱动电路发送给星上计算机。AIS接收机的天线通过天线展开及检测电路与遥测下位机相连，且天线展开及检测电路集成于母板上，天线展开及检测电路通过设置于母板上的对应的接插件与AIS接收机电连接。2. AIS (Automatic Identification System) receiver, used to receive and demodulate the AIS signal of the ship, and then send it to the on-board computer through the drive circuit. The antenna of the AIS receiver is connected to the telemetry lower computer through the antenna deployment and detection circuit, and the antenna deployment and detection circuit is integrated on the motherboard, and the antenna deployment and detection circuit is electrically connected to the AIS receiver through the corresponding connector set on the motherboard .
本实施例中，相机和AIS接收机均通过串口与驱动电路连接。In this embodiment, both the camera and the AIS receiver are connected to the driving circuit through a serial port.
3、原子氧测量仪，原子氧测量仪由集成在母板上的原子氧测量电路以及设置于卫星外表面的银膜电阻，原子氧测量电路通过测量银膜电阻的阻值，计算卫星所在的轨道空间的原子氧浓度信息，并将原子氧浓度信息发送给星上计算机，银膜电阻通过设置于母板上的对应的接插件与原子氧测量电路电连接。3. Atomic oxygen measuring instrument. The atomic oxygen measuring instrument is composed of the atomic oxygen measuring circuit integrated on the mother board and the silver film resistance set on the outer surface of the satellite. The atomic oxygen measuring circuit calculates the position of the satellite by measuring the resistance value of the silver film resistance. Atomic oxygen concentration information in the orbital space, and send the atomic oxygen concentration information to the on-board computer, and the silver film resistor is electrically connected to the atomic oxygen measurement circuit through the corresponding connector set on the motherboard.
本实施例中，如图1所示，星上计算机还通过I2C总线与电源控制器相连，电源控制器用于在光照期完成太阳能帆板输入电压到母线电压的转换，给星上设备供电，同时给蓄电池充电；在阴影期通过蓄电池放电，给星上设备供电。遥测下位机还与用于测量卫星运行环境的温度、电压及电流的温度、电压及电流传感器相连，温度、电压及电流传感器通过设置于母板上的对应的接插件与遥测下位机电连接。In this embodiment, as shown in Figure 1, the computer on the star is also connected to the power controller through the I2C bus. Charge the battery; discharge through the battery during the shadow period to supply power to the equipment on the star. The telemetry lower computer is also connected with the temperature, voltage and current sensors used to measure the temperature, voltage and current of the satellite operating environment, and the temperature, voltage and current sensors are connected with the telemetry lower electromechanically through the corresponding connectors arranged on the motherboard.
综上所述，本发明星载综合电子系统，各组件之间通过共用母板的方式，且母板与外接设备之间采用直接的接插件方式，减少了线缆、减轻了卫星的重量、提高了卫星的可靠性。To sum up, in the satellite-borne integrated electronic system of the present invention, each component shares a motherboard, and a direct connector is used between the motherboard and external devices, which reduces the number of cables and the weight of the satellite. Improved satellite reliability.
以上所述仅为本发明的优选实施例而已，并不用于限制本发明，对于本领域的技术人员来说，本发明可以有各种更改和变化。凡在本发明的精神和原则之内，所作的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.
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