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Reverse thrust system hydraulic flow diagram (Deployed position). Return lines carry a pressure of 50 PSI (344.7Pa). Both systems are powered by engine driven pumps; one mounted on each engine accessory gear box. System B operating at 3000 PSI (20.684MPa). Each engine drives a variable displacement (wobble plate) hydraulic pump providing continuous system pressure of approximately 3000 PSI (20.684MPa). Each pump can deliver from 0 to 15.5 gallons per minute (0.0011m 3 /s) of fluid flow, depending upon system demand [76].

Reverse thrust system hydraulic flow diagram (Deployed position). Return lines carry a pressure of 50 PSI (344.7Pa). Both systems are powered by engine driven pumps; one mounted on each engine accessory gear box. System B operating at 3000 PSI (20.684MPa). Each engine drives a variable displacement (wobble plate) hydraulic pump providing continuous system pressure of approximately 3000 PSI (20.684MPa). Each pump can deliver from 0 to 15.5 gallons per minute (0.0011m 3 /s) of fluid flow, depending upon system demand [76].

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Figure 1 Airplane spins during thrust reverser activation during flight.
Figure 3 Real hydraulic circuit block diagram.
Figure 5 Symbol circuit of a position servo.
Figure 6 Block Diagram of Typical Positioned Controlled Hydraulic...
+41 Figure 7 A hydraulic actuator systems with 4-way valve configuration.
Servovalve design and simulation加伯瑞姆
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  • Jul 2015
The common problem that encountered in reverse thrust system of an aircraft is the tendency to open on air and this is the main causes of accidents. It has fully automated central controller but in some cases it can’t guarantee the smooth operation of reverse thrust and most of the pilots are advised or ordered to de-activate the system. The main p...
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