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Aircraft Hydraulic Systems

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Aircraft Hydraulic
Systems
AIAA Design Group II
Basic Hydraulic System
•A valve is
opened, the
hydraulic flows
into the actuator
and presses
against the piston,
causing it to move
and in turn move
the attached
control surface
Reference:
http://www.allstar.fiu.edu/AERO/Hydr02.htm
General Uses
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Used for flight control, actuation of
flaps, slats, weapons bays, landing
gear, breaks
Provides the extra force required to
move large control surfaces in heavy
aerodynamic loads.
General Specifications
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Several different Fluids
• MIL-H-5606, MIL-H-83282, and MIL-H81019
• General Temperature Ranges : -65°F to 295°F
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Pressures:
• Airbus A380 has 5000psi hydraulic system
• Typical commercial airline pressure is 3000 psi
•http://aerospace.eaton.com/news.asp?articledate=06/01/03
&NewsCommand=ViewMonth
•http://www.tpub.com/content/aviation/14018/css/14018_17
8.htm
Problems with Hydraulics
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Heavy
High maintenance
• Adds cost and creates a logistics
problem
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Requires space (pumps, hydraulic
lines, etc.)
Possible Improvements
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Electric Actuators
• Consists of a small electric motor, pump
and actuator ram requiring about 1 pint
of hydraulic fluid
• Flight tested by NASA’s Dryden Flight
Research Center on a modified F-18.
• Provides significant weight savings by
eliminating pumps and hydraulic lines
• Also could decrease required
maintenance
Reference: NASA Dryden Flight Research Center. News
Release 98-84
Electro – Mechanical Actuator
Reference: Air Force Research Laboratory
http://www.afrlhorizons.com/Briefs/0006/VA9902.html
Impact on Design
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Need to allow sufficient space for
required hydraulic systems
Weight of the system must be
accounted for
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