An integrated energy management system for hybrid electric propulsion aircraft

Abstract

The embodiment of the invention discloses an integrated energy management system for a hybrid electric propulsion aircraft, relates to the technical field of electric propulsion, and can improve the thermal management efficiency and the safety of the power supply system of the hybrid electric propulsion aircraft. The invention includes: the fan is coaxially connected to the driving motor, the driving motor is connected to the lubricating oil / air heat exchanger, the lubricating oil / air heat exchanger is connected to the lubricating oil / fuel heat exchanger through a three-way joint, and then connected to the drive The motor; the combined power unit is coaxially connected to the combined power unit shaft; the turbine and the compressor are respectively connected to the air inlet; the fuel tank is connected to the second fuel / coolant heat exchanger, and connected to the first fuel / coolant heat exchanger through a tee joint and combined power unit combustor; combined power unit motor-generator connected to coolant / oil heat exchanger via pump. The invention is suitable for hybrid electric propulsion aircraft.

Description

Technical field [0001] The present invention relates to the field of electric propulsion technology, in particular to an energy integrated management system for hybrid electric propulsion aircraft. Background [0002] At present, transportation electrification is an important technical direction to achieve the national 2060 carbon neutrality plan. For the aviation field, due to the low power and energy density of traditional batteries, the application of pure electric aircraft has been limited by many restrictions, and it is difficult to solve the problem of small payload and short range of the aircraft caused by excessive battery weight. The hybrid electric propulsion vehicle solution can solve the above problems, but faces more serious and complex thermal and electrical energy management problems. [0003] In terms of electrical energy, the electrical load of the hybrid electric propulsion aircraft includes not only the secondary energy, but also the electric bypass fan with h...

AI Technical Summary

Problems solved by technology

Therefore, the power capacity has been greatly increased, and the requirements for the reliability and power density of the power system are getting higher and higher. The current battery technology is still difficult to meet the requirements of aircraft.

[0004] In terms of heat, the airborne system of the currently designed hybrid electric propulsion aircraft has high power and serious heat generation; and due to the increase in flight speed, the aerodynamic heating effect is significant, and the use of a large number of composite materials makes heat dissipation more difficult

And because the power of the aeroengine is relatively reduced, the environmental control system of the engine bleed air is still used, which has a great impact on the thrust and efficiency of the engine, especially the use of ram air to take away all the heat generated by the system and dissipate the heat outside the aircraft In the air, it will adversely affect the overall system efficiency of the aircraft

[0005] In general, the current hybrid electric propulsion aircraft solution has the problems of low cooling and heat dissipation system efficiency and poor flight safety caused by the overall system architecture

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