A bus-type satellite system

Abstract

The present invention provides a bus-type satellite system, characterized in that it includes: a solar cell array, a lithium-ion battery pack, a power controller, a bus controller, measurement and control, a satellite computer and other power loads; wherein, except for the solar cell array and the lithium-ion battery pack, all other electronic devices use bus-type interfaces, and the interfaces only include a power bus and a communication bus. The communication bus of general platform equipment uses a CAN bus, and special equipment and payload equipment are allowed to use other forms of buses, such as RS422 bus, I2C and LVDS. The present invention unifies and bus-types the interfaces of various satellite devices, which is conducive to mass production and rapid assembly of satellites, and at the same time improves the heat dissipation and anti-interference of the cable network, so that the reliability and safety of the satellite are guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite systems, and in particular to a bus-type satellite system. Background Art

[0002] Satellites are generally composed of multiple subsystems, including power subsystem, control subsystem, measurement and control subsystem, satellite service subsystem and payload subsystem. Each subsystem is composed of multiple devices that perform different functions. Power and signal interconnection is achieved between devices through connectors or low-frequency cable networks.

[0003] With the development of micro-satellite technology, the integration is getting higher and higher, which also leads to more and more complex interface relationships. Power, bus, instructions, analog quantities, etc. are all transmitted in a bundle of cables, making the low-frequency cable network of the entire satellite completely become a "net", and the production and processing cycle is lengthened, which is not conducive to the rapid assembly of the low-frequency cable network of the entire satellite and the rapid assembly of the satellite, affecting the process of mass production of micro-satellites. Moreover, the mesh structure of the cable further makes it difficult to dissipate heat from the power cable and interferes with weak signals, which has an adverse impact on the satellite's mission and even affects the safety of the entire satellite. Summary of the invention

[0004] The main purpose of the present invention is to provide a bus-type satellite system, which aims to unify and bus the interfaces of various satellite devices, facilitate mass production and rapid assembly of satellites, improve the heat dissipation and anti-interference capabilities of the cable network, and ensure the reliability and safety of the satellite.

[0005] In order to achieve the above-mentioned object, the present invention proposes a bus-type satellite system, including: measurement and control, onboard computer, several power loads, solar cell array, lithium-ion battery pack, power controller and bus controller; wherein,

[0006] The external connector XS of the solar cell array is connected to the external connector XP1 of the power controller via a cable, and the external connector XB1 of the lithium-ion battery pack is connected to the external connector XP2 of the power controller via a cable;

[0007] The external connector XP3 of the power controller is connected to the external connector XZ1 of the bus controller via a cable, and the external connector XP4 of the power controller is connected to the external connector XZ2 of the bus controller via a cable, so as to realize the CAN bus connection between the power controller and the bus controller;

[0008] The external connector XK of the measurement and control is connected to the external connector XZ5 of the bus controller via a cable, the bus controller provides power to the measurement and control, and the measurement and control provides direct instructions to the bus controller, while realizing CAN bus communication;

[0009] The external connector XO1 of the onboard computer is connected to the external connector XZ3 of the bus controller via a cable, and the external connector XO2 of the onboard computer is connected to the external connector XZ4 of the bus controller via a cable;

[0010] The several power loads include power load 1 to power load n, and the external connectors XF1 to XFn of the power loads 1 to power load n are interconnected one-to-one with the external connectors XZ6 to XZn of the bus controller through cables; and the external connector XFQ of other power loads is interconnected one-to-one with the external connector XZQ of the bus controller through cables.

[0011] A further technical solution of the present invention is that the bus controller includes a primary power bus, a secondary power bus, a CAN bus, a DC / DC converter, a microprocessor unit and peripheral circuits;

[0012] The primary power bus transmits primary power, the secondary power bus transmits secondary power, the CAN bus realizes CAN signal transmission, the DC / DC converter realizes conversion of primary power into secondary power required by electrical equipment and transmits it through the secondary power bus, the microprocessor unit and peripheral circuits realize data instruction decoding, instruction driving, and analog quantity acquisition functions, and at the same time send the analog quantity to the CAN bus, which is received by the onboard computer.

[0013] A further technical solution of the present invention is that the primary power bus and the positive power supply line of the primary power load 1 to the primary power load n are controlled by power distribution switches K1 to K1n to be powered on and off, and have overcurrent protection, current and voltage measurement functions;

[0014] The microprocessor unit and the peripheral circuit receive the data instructions transmitted by the CAN bus, and after decoding, drive the distribution switches K1 to K1n to perform on-off operations. The voltage and current measurement values ​​are collected by the microprocessor unit and the peripheral circuit and transmitted through the CAN bus.

[0015] A further technical solution of the present invention is that the secondary power bus and the positive power supply line of the secondary power load 1 to the secondary power load n are controlled by power distribution switches K2 to K2n to be powered on and off, and have overcurrent protection, current and voltage measurement functions;

[0016] The microprocessor unit and the peripheral circuit receive the data instructions transmitted by the CAN bus, and drive the distribution switches K2 to K2n to perform on-off operations after decoding. The voltage and current measurement values ​​are collected by the microprocessor unit and the peripheral circuit and transmitted through the CAN bus.

[0017] The beneficial effects of the bus-type satellite system of the present invention are:

[0018] The present invention unifies and busses the interfaces of various satellite devices, which is beneficial to the mass production and rapid assembly of satellites, while improving the heat dissipation and anti-interference performance of the cable network, thereby ensuring the reliability and safety of the satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the composition of the bus-type satellite system of the present invention;

[0020] Figure 2 It is the functional block diagram of the bus controller.

[0021] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. DETAILED DESCRIPTION

[0022] It should be understood that the specific embodiments described herein are only used to explain the present invention, and are not used to limit the present invention.

[0023] In order to solve the technical problems existing in the prior art, the present invention proposes a bus-type satellite system. Except for the solar cell array and the lithium-ion battery pack, all other electronic devices adopt bus-type interfaces, and the interface only includes power and communication buses. The communication bus of general platform equipment adopts CAN bus, and special equipment and payload equipment are allowed to adopt other forms of buses, such as RS422 bus, I2C and LVDS.

[0024] For details, please refer to Figure 1 The preferred embodiment of the bus-type satellite system of the present invention includes: measurement and control, a satellite-borne computer, a plurality of power loads, a solar cell array, a lithium-ion battery pack, a power controller and a bus controller.

[0025] The external connector XS of the solar cell array is connected to the external connector XP1 of the power controller via a cable.

[0026] The external connector XB1 of the lithium-ion battery pack is connected to the external connector XP2 of the power controller via a cable. The lithium-ion battery pack transmits power to the power controller, and the power controller collects the voltage and temperature of the lithium-ion battery pack and provides heating control.

[0027] The external connector XP3 of the power controller is connected to the external connector XZ1 of the bus controller through a cable, and the power controller outputs the adjusted stable primary power bus to the bus controller. The external connector XP4 of the power controller is connected to the external connector XZ2 of the bus controller through a cable, so as to realize the CAN bus connection between the power controller and the bus controller.

[0028] The external connector XK of the measurement and control is connected to the external connector XZ5 of the bus controller via a cable, the bus controller provides power to the measurement and control, and the measurement and control provides direct instructions to the bus controller, while realizing CAN bus communication;

[0029] The external connector XO1 of the onboard computer is connected to the external connector XZ3 of the bus controller through a cable, and the bus controller provides power to the onboard computer. The external connector XO2 of the onboard computer is connected to the external connector XZ4 of the bus controller through a cable, thereby realizing a communication bus connection between the power controller and the bus controller, which may include a CAN bus and other types of communication buses.

[0030] The several power loads include power load 1 to power load n, and the external connectors XF1~XFn of the power loads 1 to power load n are interconnected one-to-one with the external connectors XZ6~XZn of the bus controller through cables to transmit power and CAN bus; the external connector XF of other power loads is connected to the external connector XZ of the bus controller through cables to transmit power and other types of communication buses.

[0031] In this embodiment, there are only power supply interfaces and communication interfaces between satellite devices. The communication interfaces of platform devices uniformly use CAN bus, while taking into account other forms of bus, such as RS422 bus and LVDS. The unification and busization of interfaces between devices are conducive to mass production and rapid assembly of satellites.

[0032] In this embodiment, the bus controller is the control core and the dispatching hub for the energy and communication of the entire satellite. It can realize the bus-based distribution and control functions of satellite energy and communication, and has the functions of secondary power conversion, power distribution, analog quantity acquisition, CAN bus communication, power transmission, bus signal transmission, DC / DC conversion and power distribution control, while taking into account other types of communication buses of individual equipment.

[0033] Specifically, Figure 2 As shown, the bus controller includes a primary power bus, a secondary power bus, a CAN bus, a DC / DC converter, a microprocessor unit, peripheral circuits and other buses.

[0034] The primary power bus transmits primary power, the secondary power bus transmits secondary power, the CAN bus realizes CAN signal transmission, the DC / DC converter realizes conversion of primary power into secondary power required by electrical equipment and transmits it through the secondary power bus, the microprocessor unit and peripheral circuits realize data instruction decoding, instruction driving, and analog quantity acquisition functions, and at the same time send the analog quantity to the CAN bus, which is received by the onboard computer.

[0035] The primary power bus and the positive power supply line of the primary power load 1 to the primary power load n are controlled by power distribution switches K1 to K1n, and have overcurrent protection, current and voltage measurement functions.

[0036] The microprocessor unit and the peripheral circuit receive the data instructions transmitted by the CAN bus, and after decoding, drive the distribution switches K1 to K1n to perform on-off operations. The voltage and current measurement values ​​are collected by the microprocessor unit and the peripheral circuit and transmitted through the CAN bus.

[0037] The secondary power bus and the positive power supply lines of the secondary power load 1 to the secondary power load n are controlled to be powered on and off through the distribution switches K2 to K2n, and have overcurrent protection, current and voltage measurement functions.

[0038] The microprocessor unit and the peripheral circuit receive the data instructions transmitted by the CAN bus, and after decoding, drive the power distribution switches K2 to K2n to perform on-off operations. The voltage and current measurement values ​​are collected by the microprocessor unit and the peripheral circuit, and transmitted through the CAN bus.

[0039] The power supply and bus connection methods for other bus loads are the same.

[0040] The bus controller receives direct instructions sent by the measurement and control, and can control the key circuits to be turned on and off when necessary.

[0041] The key points and protection points of the bus-type satellite system of the present invention are:

[0042] 1. There are only power supply interfaces and communication interfaces between satellite devices. The communication interfaces of platform devices uniformly use CAN bus, while taking into account other forms of buses, such as RS422 bus and LVDS;

[0043] 2. The bus controller has the ability to allocate power to all electrical equipment and the ability to transfer communications;

[0044] 3. The unification and busing of interfaces between devices are conducive to mass production and rapid assembly of satellites;

[0045] 4. The heat dissipation, anti-interference, safety and reliability of the low-frequency cable network are guaranteed.

[0046] The beneficial effects of the bus-type satellite system of the present invention are:

[0047] The present invention unifies and busses the interfaces of various satellite devices, which is beneficial to the mass production and rapid assembly of satellites, while improving the heat dissipation and anti-interference performance of the cable network, thereby ensuring the reliability and safety of the satellite.

[0048] The above description is only a preferred embodiment of the present invention, and does not limit the patent scope of the present invention. Any equivalent structure or process transformation made by using the contents of the present invention specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. A bus-type satellite system, characterized in that: include: Solar cell array, lithium-ion battery pack, power controller, bus controller, measurement and control, onboard computer and other power loads; among which, The external connector XS of the solar cell array is connected to the external connector XP1 of the power controller via a cable, and the external connector XB1 of the lithium-ion battery pack is connected to the external connector XP2 of the power controller via a cable; The external connector XP3 of the power controller is connected to the external connector XZ1 of the bus controller via a cable, and the external connector XP4 of the power controller is connected to the external connector XZ2 of the bus controller via a cable, so as to realize the CAN bus connection between the power controller and the bus controller; The external connector XK of the measurement and control is connected to the external connector XZ5 of the bus controller via a cable, the bus controller provides power to the measurement and control, and the measurement and control provides direct instructions to the bus controller, while realizing CAN bus communication; The external connector X01 of the onboard computer is connected to the external connector XZ3 of the bus controller via a cable, and the external connector X02 of the onboard computer is connected to the external connector XZ4 of the bus controller via a cable; The plurality of power loads include power load 1 to power load n, and the external connectors XF1 to XFn of the power loads 1 to power load n are interconnected one-to-one with the external connectors XZ6 to XZn of the bus controller through cables; the external connectors XFQ of other power loads are interconnected one-to-one with the external connector XZQ of the bus controller through cables; The bus controller includes a primary power bus, a secondary power bus, a CAN bus, a DC / DC converter, a microprocessor unit and peripheral circuits; The primary power bus transmits primary power, the secondary power bus transmits secondary power, the CAN bus realizes CAN signal transmission, the DC / DC converter realizes conversion of primary power into secondary power required by electrical equipment and transmits it through the secondary power bus, the microprocessor unit and peripheral circuits realize data instruction decoding, instruction driving, and analog quantity acquisition functions, and at the same time send the analog quantity to the CAN bus, which is received by the onboard computer.

2. The bus-type satellite system according to claim 1, characterized in that: The primary power bus and the positive power supply line of the primary power load 1 to the primary power load n are controlled by power distribution switches K1 to K1 n, and have overcurrent protection, current and voltage measurement functions; The microprocessor unit and the peripheral circuit receive the data instructions transmitted by the CAN bus, and drive the power distribution switches K1 to K1 n to perform on-off operations after decoding. The voltage and current measurement values ​​are collected by the microprocessor unit and the peripheral circuit and transmitted through the CAN bus.

3. The bus-type satellite system according to claim 2, characterized in that: The secondary power bus and the positive power supply line of the secondary power load 1 to the secondary power load n are controlled by power distribution switches K2 to K2n, and have overcurrent protection, current and voltage measurement functions; The microprocessor unit and the peripheral circuit receive the data instructions transmitted by the CAN bus, and drive the distribution switches K2 to K2n to perform on-off operations after decoding. The voltage and current measurement values ​​are collected by the microprocessor unit and the peripheral circuit and transmitted through the CAN bus.

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