The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Feb. 01, 2022

Filed:

Jul. 06, 2021
Applicant:

Zhejiang University, Hangzhou, CN;

Inventors:

Yao Zheng, Hangzhou, CN;

Junyin Chen, Hangzhou, CN;

Changping Du, Hangzhou, CN;

Guanghua Song, Hangzhou, CN;

Rui Yang, Hangzhou, CN;

Zhixian Ye, Hangzhou, CN;

Zekun Zhang, Hangzhou, CN;

Assignee:

Zhejiang University, Hangzhou, CN;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
H02P 6/00 (2016.01); B60L 50/52 (2019.01); B60L 50/60 (2019.01); H02P 7/292 (2016.01);
U.S. Cl.
CPC ...
B60L 50/52 (2019.02); B60L 50/60 (2019.02); H02P 7/292 (2013.01); B60L 2200/10 (2013.01); B60L 2210/10 (2013.01); B60L 2240/427 (2013.01);
Abstract

The present disclosure provides an efficient control system and method for a brushless motor with a wide working range, which are applied to an aerospace vehicle energy system. The system of the present disclosure includes a power supplying module, a first DC-DC circuit, a battery pack, a second DC-DC circuit, an anti-reverse-connection circuit, an electronic speed control (ESC), a brushless direct current motor (BLDC), an airborne controller and a communication link. Electric energy from the power supplying module is configured to charge the battery pack via the first DC-DC circuit, and electric energy of the battery pack sequentially flows through the second DC-DC circuit and the anti-reverse-connection circuit to energize the ESC, wherein output voltage of the second DC-DC circuit and throttle signal input of the ESC are controlled in real time by the airborne controller according to a power demand of an aircraft.


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