Fixed slip hydraulic anti-lock braking system

Claim 2

In an airplane landing gear of the type having a first, braked wheel, and a second, less than fully braked wheel, an anti-lock braking system comprising in combination; a first positive displacement hydraulic pump driven by said first wheel, a hydraulically actuated brake means for braking said first wheel, a second positive displacement hydraulic pump driven by said second wheel, the output of said second pump being less than the output of said first pump when said wheels are rotating at equal peripheral speeds, and conduit means connecting an output port of said first pump with the input port of said second pump and with said brake means, wherein said first whEel''s braking is regulated by said system so as to cause said first pump''s output to substantially equal to said second pump''s input.

Claim 3

A system as in claim 1 wherein manual pressure relief means are added and connected with said conduit means for manually reducing and limiting the pressure prevailing in said conduit means and thereby over-ruling said system.

Claim 4

A system as in claim 1 wherein a bleeding means is added and connected to said conduit means for metering out of said conduit substituting the second pump in the initial stage of the airplane''s landing during which the first wheel is in contact with a runway and said second wheel is not, and valving means adapted to shut said bleeding means after said second wheel has established contact with the runway.

Claim 5

In an airplane''s landing gear having a braking wheel, an anti-lock braking system comprising in combination; a positive displacement hydraulic pump driven by said wheel, a hydraulically actuated brake means for braking said wheel, a metering means adapted to permit flow through itself at a rate which is proportional to airplane''s ground speed and which is smaller than the output of said pump when the peripheral speed of said wheel equal''s the airplane''s ground speed, manual pressure relief means for manually over-ruling said system, and conduit means connecting an output port of said pump to an input port of said metering means with said brake means and with said manual pressure relief means, wherein said wheel''s braking is regulated by said system so as to cause said pump''s output to substantially equal the flow permitted by said metering means through itself and wherein said manual pressure relief means are adapted to manually reduce and limit the pressure prevailing in said conduit means thereby over-rule said system.

Claim 6

In an airplane''s landing gear having a braking wheel, an anti-lock braking system comprising in combination; a positive displacement hydraulic pump driven by said wheel, a hydraulically actuated brake means for braking said wheel, a metering means adapted to permit flow through itself at a rate which is proportional to airplane''s ground speed and which is smaller than the output of said pump when the peripheral speed of said wheel equal''s the airplane''s ground speed, manual pressure relief means for manually over-ruling said system, and conduit means connecting an output port of said pump to an input port of said metering means with said brake means and with said manual pressure relief means, wherein said wheel''s braking is regulated by said system so as to cause said pump''s output to substantially equal the flow permitted by said metering means through itself and wherein said manual pressure relief means are adapted to manually reduce and limit the pressure prevailing in said conduit means thereby over-rule said system.

Claim 7

In an airplane landing gear of the type having a first, braked wheel, and a second, less than fully braked wheel, an anti-lock braking system comprising in combination; a first positive displacement hydraulic pump driven by said first wheel, a hydraulically actuated brake means for braking said first wheel, a second positive displacement hydraulic pump driven by said second wheel, the output of said second pump being less than the output of said first pump when said wheels are rotating at equal peripheral speeds, a pressure source equipped with relief means by which its pressure output can be made to follow a signal pressure, conduit means for connecting an output port of said first pump with an input port of said second pump and with said relief means for directing said signal pressure to said relief means, and fluid transmitting means for connecting said pressure source with an input port of said first pump, with an output port of said second pump and with said brake means, wherein said first wheel''s braking is regulated by said system so as to cause said first pump''s output to substantially equal said second pump''s input.

Claim 8

In an airplane landing gear of the type having a first, braked wheel, and a second, less than fully braked wheel, an anti-lock braking system comprising in combination; a first positive displacement hydraulic pump driven by said first wheel, a hydraulically actuated brake means for braking said first wheel, a second positive displacement hydraulic pump driven by said second wheel, the output of said second pump being less than the output of said first pump when said wheels are rotating at equal peripheral speeds, a pressure source equipped with relief means by which its pressure output can be made to follow a signal pressure, conduit means for connecting an output port of said first pump with an input port of said second pump and with said relief means for directing said signal pressure to said relief means, and fluid transmitting means for connecting said pressure source with an input port of said first pump, with an output port of said second pump and with said brake means, wherein said first wheel''s braking is regulated by said system so as to cause said first pump''s output to substantially equal said second pump''s input.

Claim 9

A system as in claim 5 wherein a manual pressure relief means is added and connected to said fluid transmitting means for manually reducing and limiting the pressure prevailing in said fluid transmitting means and thereby over-ruling said system.

Claim 10

A system as in claim 5 wherein a bleeding means is added and connected to said conduit means for metering out of said conduit means flow and thereby substituting said second pump in the initial stage of the airplane''s landing during which the first wheel is in contact with a runway and said second wheel is not, and valving means adapted to shut said bleeding means after said second wheel has established contact with the runway.