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Title:
PIEZOELECTRIC RING BENDER SERVO VALVE ASSEMBLY FOR AIRCRAFT FLIGHT CONTROL ACTUATION AND FUEL CONTROL SYSTEMS
Document Type and Number:
WIPO Patent Application WO/2021/002907
Kind Code:
A3
Abstract:
A piezoelectric ring bender servo valve assembly reduces mechanical wear by removing mechanical components used in prior art servo valves. The assembly does not use torque motor, flapper, and feedback spring. In this manner, no moving parts are required, which reduces maintenance and costs. A pair of piezoelectric ring benders mount adjacently to a pair of nozzles. The piezoelectric ring benders independently regulate the flow of fluid through the nozzles by moving between an open position to enable flowage, and a closed position to restrict flowage. A linear position sensing device measures and provides feedback about the spool position to a valve controller. The valve controller allows the spool valve to move until valve position achieves command position and the force on the spool valve is in equilibrium with pressure difference across spool valve. An H-bridge operable to switch the polarity of a differential pressure applied across to a load.

Inventors:
YUAN, Michael (Irvine, California, US)
Application Number:
US2020/026461
Publication Date:
April 08, 2021
Filing Date:
April 02, 2020
Export Citation:
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Assignee:
YUAN, Michael (Irvine, California, US)
International Classes:
F16K31/00; B64C23/00; F16K11/07; B64C13/40; F02C9/26; F16K31/42; F15B11/10; F02M2200/24
Attorney, Agent or Firm:
YANG, Elizabeth (Suite 201Monterey Park, California, US)
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