Aircraft brake assembly structures for reducing noise

Abstract

Various embodiments of aircraft brake assembly structures are provided for achieving noise reduction during braking activity. In certain embodiments of the invention, the actual application of force to the pressure plate is regulated such that a different number of actuator pistons are used during low-energy stops than during high-energy stops. In other embodiments of the invention, the pressure plate or endplate is augmented as to surface area in some instances and as to a taper angle in others, again to achieve a desired increase in effective pressure application during low-energy stops. In other embodiments of the invention, the stator and/or rotor disks are characterized by slots to break up the propagation of noise waves.

What is claimed is: 
     
         1 . An aircraft brake assembly configured to minimize noise during braking, comprising:
 a heat stack of alternating interleaved stator disks and rotor disks between a pressure plate and endplate;   a plurality of brake-actuating assemblies connected to said heat stack and in selective operative engagement therewith; and   a controller operatively connected to said plurality of brake-actuating assemblies in a manner to accommodate actuation of selected ones of said brake-actuating assemblies as a function of a desired braking activity.   
     
     
         2 . The aircraft brake system according to  claim 1 , wherein said desired braking activity is taken from the group of aircraft landing operations and aircraft taxiing operations. 
     
     
         3 . The aircraft brake system according to  claim 2 , wherein said plurality of brake-actuating assemblies are divided into groups. 
     
     
         4 . The aircraft brake system according to  claim 3 , wherein said controller actuates said brake-actuating assemblies of said groups independently of the actuation of said brake-actuating assemblies of other groups. 
     
     
         5 . The aircraft brake system according to  claim 4 , wherein said controller actuates said brake-actuating assemblies of selected ones of said groups as a function of said desired braking activities. 
     
     
         6 . The aircraft brake system according to  claim 5 , wherein said desired braking activities are determined by events taken from the group of a ground speed of an associated aircraft, a level of brake pedal travel of said associated aircraft, and pilot control. 
     
     
         7 . The aircraft brake assembly according to  claim 6 , further comprising brake control valves interposed between said controller and said groups of brake-actuating assemblies. 
     
     
         8 . The aircraft brake assembly according to  claim 7 , wherein all of said brake-actuating assemblies of each group are connected to a same control valve. 
     
     
         9 . A brake system of an aircraft for minimizing noise generated during braking operations, comprising:
 a heat stack of alternating interleaved stator disks and rotor disks between a pressure plate;   first and second sets of brake-actuating assemblies connected to said heat stack and in selective operative engagement therewith; and   a controller operatively and independently connected to said first and second sets of brake-actuating assemblies for selectively actuating said sets of brake-actuating assemblies as a function of whether the aircraft is landing or taxiing.   
     
     
         10 . The brake system of an aircraft according to  claim 9 , wherein a determination as to whether the aircraft is landing or taxiing is made as a function of a land speed of the aircraft. 
     
     
         11 . The brake system of an aircraft according to  claim 9 , wherein a determination as to whether the aircraft is landing or taxiing is made as a function of brake pedal depression. 
     
     
         12 . The brake system of an aircraft according to  claim 9 , wherein a determination as to whether the aircraft is landing or taxiing is made by pilot control. 
     
     
         13 . The brake system of an aircraft according to  claim 9 , wherein selective actuation of said brake-actuating assemblies of said first and second sets ensures sufficient force application to said pressure plate during taxiing to minimize generation of brake noise. 
     
     
         14 . The brake system of an aircraft according to  claim 13 , wherein a brake control valve is interposed between said controller and each of said first and second sets of brake-actuating assemblies.