Spacecraft ground power supply safety alarm and processing system based on load characteristics
A ground power supply and processing system technology, applied in the direction of electrical components, circuit devices, AC network circuits, etc., can solve problems such as weak emergency handling capabilities, deterioration of failures, and failure to consider emergency handling of equipment on spacecraft, so as to prevent the expansion of the scope of failures , the effect of improving safety
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[0038] The present invention will be further described below in conjunction with the accompanying drawings. The specific implementation is as follows:
[0039] The invention provides a safety alarm and processing system for ground power supply of spacecraft based on load characteristics, which can adjust the maximum output power of the ground power supply in real time, prevents the insufficient output capacity of the ground power supply from causing undervoltage of the busbar or over-discharge of the battery, and prevents the output of the ground power supply Excessive capacity will cause the power supply to age too quickly and the failure rate to increase; monitor the health of the load power consumption, and can realize timely alarm when the actual power of the load is inconsistent with the expected situation; quickly handle bus short-circuit faults and bus overvoltage faults to prevent the expansion of the fault range , leading to load burnout or overcurrent, greatly improv...
Embodiment 1
[0047] In this example, the load expected power P load =150W, redundant power threshold ΔP min =100W, ΔP error =10W, upper limit ΔI of mild alarm for current jump max1 =15A, current jump severe alarm upper limit ΔI max2 =20A, bus voltage lower limit V min =95V, bus voltage upper limit V max =105V.
[0048] In the first step, the data acquisition module collects the spacecraft bus voltage V bus =100V, spacecraft bus current I bus =20A, ground power output power P max =2200W, the command type flag is 1, and the collected spacecraft bus voltage V bus , Spacecraft bus current I bus , ground power output power P max and the instruction type flag are output to the logic judgment module;
[0049] In the second step, the logic judgment module according to the received spacecraft bus voltage V bus , Spacecraft bus current I bus , ground power output power P max and the instruction type flag to judge the safety status of the current spacecraft ground power supply. Calcula...
Embodiment 2
[0058] In this example, the load expected power P load =150W, redundant power threshold ΔP min =100W, ΔP error =10W, upper limit ΔI of mild alarm for current jump max1 =15A, current jump severe alarm upper limit ΔI max2 =20A, bus voltage lower limit V min =95V, bus voltage upper limit V max =105V.
[0059] In the first step, the data acquisition module collects the spacecraft bus voltage V bus =90V, spacecraft bus current I bus From 20A to 45A, ground power output power P max =2200W, the instruction type flag is 0, and the collected spacecraft bus voltage V bus , Spacecraft bus current I bus , ground power output power P max and the instruction type flag are output to the logic judgment module;
[0060] In the second step, the logic judgment module according to the received spacecraft bus voltage V bus, Spacecraft bus current I bus , ground power output power P max and the instruction type flag to judge the safety status of the current spacecraft ground power sup...
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