A high-voltage DC power system for hybrid electric propulsion aircraft

A high-voltage direct current and power system technology, applied in the field of electric propulsion, can solve problems such as the inability of the electric drive system to work and affect flight safety, and achieve the effects of eliminating the turbofan engine accessory case, improving reliability, and improving efficiency

Active Publication Date: 2022-04-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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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. However, it is still difficult for aircraft batteries to meet the requirements. It is urgent to propose a reasonable and feasible power system and power system architecture.
Moreover, the failure of the power supply system will also cause the problem that the electric drive system cannot work, which will affect flight safety.

Method used

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  • A high-voltage DC power system for hybrid electric propulsion aircraft
  • A high-voltage DC power system for hybrid electric propulsion aircraft
  • A high-voltage DC power system for hybrid electric propulsion aircraft

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Embodiment Construction

[0056]In order to enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. Hereinafter, embodiments of the present invention will be described in detail, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary only for explaining the present invention and should not be construed as limiting the present invention. Those skilled in the art will understand that unless otherwise stated, the singular forms "a", "an", "said" and "the" used herein may also include plural forms. It should be further understood that the word "comprising" used in the description of the present invention refer...

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Abstract

Embodiments of the present invention disclose a high-voltage direct current power system for hybrid electric propulsion aircraft, which relates to the technical field of electric propulsion and can improve the safety, efficiency and power density of the power supply system. The invention includes: a first electric ducted fan, a second electric ducted fan, a turbofan engine, a combined power device, a power distribution system, a low-voltage battery, a high-voltage battery, a low-voltage electrical load, and a high-voltage electrical load. The power distribution system includes built-in generator system / drive motor system, built-in starter-generator system, first DC / DC converter, second DC / DC converter, low-voltage DC bus bar, combined power unit motor-generator system , No. 1 main circuit breaker, No. 2 main circuit breaker, No. 3 main circuit breaker. The invention is suitable for hybrid electric propulsion aircraft.

Description

technical field [0001] The present invention relates to the technical field of electric propulsion, and in particular to a high-voltage direct current power system for a hybrid electric propulsion aircraft. Background technique [0002] At present, transportation electrification is an important technical direction to achieve the national 2060 carbon neutrality plan. In the aviation field, due to the low power and energy density of traditional batteries, the application of pure electric aircraft has been subject to many restrictions. It is difficult to solve the problems of small aircraft payload and short range caused by excessive battery weight. The solution of hybrid electric propulsion aircraft can solve the above problems, but it faces more serious and complex power management problems. [0003] The electrical load of the hybrid electric propulsion aircraft includes not only secondary energy, but also a high-power drive motor system for electric ducted fans, while tradi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D27/02B64D27/24H02J1/12H02J7/14
CPCB64D27/02B64D27/24H02J1/12H02J7/1492B64D2027/026Y02T50/60
Inventor 于立朱锡庆张卓然张美琳李进才
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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