TY - GEN
T1 - Design and validation of hydraulic pump system driven by the electromotor under the high-power and long-Time working state in an airborne
AU - Jiang, Huijun
AU - Li, Zhenshui
AU - Liu, Hong
AU - Jiao, Zongxia
AU - Shang, Yaoxing
AU - Liu, Xiaochao
N1 - Publisher Copyright:
© 2016 IEEE.
PY - 2016/11/17
Y1 - 2016/11/17
N2 - This paper introduced a type of aircraft electric hydraulic pump system working principle, the key points of the system are analyzed and described, including calculation of boost pressure, system oil temperature control design, environmental temperature checking, starting logic design, the system validation and verification methods are expounded. This system passed through the ground test and flight time Validation, and worked well and reliably.
AB - This paper introduced a type of aircraft electric hydraulic pump system working principle, the key points of the system are analyzed and described, including calculation of boost pressure, system oil temperature control design, environmental temperature checking, starting logic design, the system validation and verification methods are expounded. This system passed through the ground test and flight time Validation, and worked well and reliably.
UR - https://www.scopus.com/pages/publications/85006804275
U2 - 10.1109/AUS.2016.7748177
DO - 10.1109/AUS.2016.7748177
M3 - 会议稿件
AN - SCOPUS:85006804275
T3 - AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems
SP - 874
EP - 878
BT - AUS 2016 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2016 IEEE/CSAA International Conference on Aircraft Utility Systems, AUS 2016
Y2 - 10 October 2016 through 12 October 2016
ER -