Independent monitoring system, aerospace craft electrical system and monitoring method
A technology for aerospace vehicles and electrical systems, which is applied in the field of monitoring of aerospace vehicle electrical systems, and can solve problems such as impact monitoring
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Embodiment 1
[0035] figure 1 It is a schematic diagram of an independent monitoring system of an aerospace vehicle electrical system according to an embodiment of the present application; figure 2 for figure 1 A schematic diagram of the stand-alone monitoring system shown for monitoring the electrical systems of a spacecraft.
[0036] Such as figure 1 and figure 2 As shown, the independent monitoring system 100 of the aerospace vehicle electrical system of the embodiment of the present application includes:
[0037] Master monitoring unit 111 and slave monitoring unit 112;
[0038] Monitoring dedicated communication bus 120, connected between the main monitoring unit 111 and the slave monitoring unit 112; the slave monitoring unit 112 is used to monitor the functional modules 210 of the aerospace vehicle electrical system, the master monitor The unit 112 is used to monitor the functional modules 210 of the aerospace vehicle electrical system and obtain the monitoring data from the m...
Embodiment 2
[0076] An electrical system for an aerospace vehicle according to an embodiment of the present application, comprising:
[0077] Electrical system body;
[0078] The independent monitoring system described in Embodiment 1.
Embodiment 3
[0080] Figure 5 for figure 1 Flowchart of the monitoring method for the stand-alone monitoring system shown. The monitoring method of the aerospace vehicle electrical system of the embodiment of the present application is the monitoring method of the aerospace vehicle electrical system of the second embodiment, such as Figure 5 shown, including the following steps:
[0081] During the test or launch process, after all the systems of the aerospace vehicle are ready, the power distribution of the test, launch and control system of the aerospace vehicle;
[0082] Checking the status of ground equipment associated with said spacecraft and distributing power to an independent monitoring system;
[0083] After the independent monitoring system enters the real-time monitoring working state, the power distribution of the electrical system of the aerospace vehicle is turned on, and the electrical system of the aerospace vehicle enters a normal working process.
[0084] In impleme...
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