Aircraft power system and aircraft
By employing multiple power compartments connected to a DC bus in the aircraft power system as switching modules, combined with reconfigurable batteries and piezoelectric power modules, fault isolation and reconfiguration are achieved, solving the reliability problem of the missile power system and improving fault tolerance and rapid response capability.
CN122092178APending Publication Date: 2026-05-26INST OF ELECTRICAL ENG CHINESE ACAD OF SCI
View PDF 0 Cites 0 Cited by
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- INST OF ELECTRICAL ENG CHINESE ACAD OF SCI
- Filing Date
- 2024-11-18
- Publication Date
- 2026-05-26
AI Technical Summary
Technical Problem
Existing aircraft power systems are insufficient to meet the high reliability requirements of missiles, lacking fault tolerance and rapid response capabilities.
Method used
Multiple power compartments are connected to DC bus via switch modules, which are combined with reconfigurable battery modules and piezoelectric power modules to supply power to the power distribution and load modules. The power supply relationship is adjusted through a switch matrix to achieve fault isolation and reconfiguration.
Benefits of technology
It improves the reliability and fault tolerance of the power system, enables rapid response to faults, achieves flexible power supply methods, and significantly enhances the reliability of the missile power system.
✦ Generated by Eureka AI based on patent content.
Smart Images
Figure CN122092178A_ABST
Abstract
This application relates to the field of aircraft technology, specifically providing an aircraft power system and an aircraft, aiming to solve the problem that current aircraft power systems cannot meet the high reliability requirements of missiles. To this end, the aircraft power system provided in this application includes: a DC bus, N power compartments, and N switch modules, wherein the nth power compartment is connected to the DC bus via the nth switch module. Each switch module includes two first switches and a cable. One of the two first switches connects one end of the cable to the DC bus, and the other of the two first switches connects the other end of the cable to the corresponding power compartment, where 1 ≤ n ≤ N. This application achieves the goals of improving the reliability and fault tolerance of the aircraft power system, enabling rapid response to power system failures, and flexibly adjusting the power supply mode, thus solving the problem that aircraft power systems cannot meet the high reliability requirements of missiles.
Need to check novelty before this filing date? Find Prior Art