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Airborne power distribution system for general aviation aircrafts

A technology for power distribution systems, aircraft, used in aerospace

Inactive Publication Date: 2017-05-17
许亚夫
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The biggest shortcoming of this design lies in the technical bottleneck of reliability and intelligence

Method used

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  • Airborne power distribution system for general aviation aircrafts
  • Airborne power distribution system for general aviation aircrafts
  • Airborne power distribution system for general aviation aircrafts

Examples

Experimental program
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Embodiment Construction

[0018] Such as figure 1 Shown is a structural connection block diagram of a general aviation aircraft onboard power distribution system of the present invention. In the figure, it includes avionics equipment, power system, environmental control system, power supply module, and airborne electrical equipment; the key points of its structure are: the avionics equipment, power system, and environmental control system are connected with a communication module through the CAN bus, The communication module is connected to the CPU module, and the CPU module is connected with a data acquisition module, a state monitoring module, an FPGA module, and a drive control module, and the drive control module is connected with a contactor module; the FPGA module is connected with an expansion interface, The expansion interface is connected with an SSPC device, and the SSPC device is connected with the airborne electrical equipment; the power supply module is a communication module, a CPU module...

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Abstract

An airborne power distribution system for general aviation aircrafts of the invention has the characteristics of high reliability, effectiveness and extensibility. The airborne power distribution system comprises avionics equipment, a power system, an environment control system, a power supply module, and airborne electrical equipment. The system is structurally characterized in that the avionics equipment, the power system and the environment control system are connected with a communication module through a CAN bus; the communication module is connected with a CPU module; the CPU module is further connected with a data acquisition module, a state monitoring module, an FPGA module and a driving control module; the driving control module is connected with a contactor module; the FPGA module is connected with an extended interface, the extended interface is connected with an SSPC device, and the SSPC device is connected with the airborne electrical equipment; and the power supply module provides power for the communication module, the CPU module, the data acquisition module, the state monitoring module, the FPGA module, the driving control module, the contactor module, the extended interface and the SSPC device.

Description

technical field [0001] The invention belongs to the technical field of aerospace, and in particular relates to an on-board power distribution system of a general aviation aircraft. Background technique [0002] General aviation refers to civil aviation activities other than public air transportation, including operational flights in industry, agriculture, forestry, fishery and construction, as well as public and commercial flights, medical and health care, emergency rescue and disaster relief, geological and meteorological exploration, ocean monitoring, flight teaching, tourism, etc. Flight activities such as sightseeing. General aviation aircraft include small aircraft, hot air balloons, airships, gliders, helicopters, etc. Among them, small aircraft have the highest share, and their salient features are: the maximum take-off weight is generally within 5t, the flight altitude is below 600m, and the flight speed Within 400km / h. [0003] The design of general aviation aircr...

Claims

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Application Information

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IPC IPC(8): H02J9/08
CPCH02J9/08
Inventor 许亚夫
Owner 许亚夫