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The shock and vibration isolation system for hard mounting of a manifold of a brake control valve includes shock and vibration isolators that can be assembled in the mounting feet of the manifold of the brake control valve. The shock and vibration isolators have a pre-selected, predetermined natural

The shock and vibration isolation system for hard mounting of a manifold of a brake control valve includes shock and vibration isolators that can be assembled in the mounting feet of the manifold of the brake control valve. The shock and vibration isolators have a pre-selected, predetermined natural frequency operative to protect components of the brake control valve from shock and vibration. Each of the shock and vibration isolators includes a radially inner generally spool shaped rigid insert portion and a radially outer generally spool shaped vibration insulating sheath portion.

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1. A shock and vibration isolator for hard mounting an aircraft brake control valve to a structural part of an aircraft, comprising: a radially inner generally spool shaped rigid insert portion defining a central aperture configured to receive a fastener for hard mounting of the brake control valve

1. A shock and vibration isolator for hard mounting an aircraft brake control valve to a structural part of an aircraft, comprising: a radially inner generally spool shaped rigid insert portion defining a central aperture configured to receive a fastener for hard mounting of the brake control valve to the structural part of an aircraft, wherein said radially inner generally spool shaped rigid insert portion includes a first radially inner rigid tubular member and a second radially inner rigid tubular member that overlaps and interfits with the first radially inner rigid tubular member, and said first radially inner rigid tubular member includes an upper radially outwardly flared annular end portion and a lower tubular shaft portion, and said second radially inner rigid tubular member includes a lower radially outwardly flared end portion and an upper flange that overlaps and interfits with the lower tubular shaft portion of the first radially inner rigid tubular member; anda radially outer generally spool shaped vibration insulating sheath portion, wherein said outer generally spool shaped vibration insulating sheath portion comprises a first generally tubular radially outer vibration insulating sheath portion and a second generally tubular radially outer vibration insulating sheath portion that overlaps and interfits with the first generally tubular outer vibration insulating sheath portion;wherein said shock and vibration isolator has a natural frequency selected to protect a component of the aircraft brake control valve from damage from shock and vibration. 2. The shock and vibration isolator of claim 1, wherein the natural frequency of the shock and vibration isolator is predetermined to be below a natural frequency of the component of the brake control valve to protect the component of the brake control valve from shock and vibration. 3. The shock and vibration isolator of claim 2, wherein the component of said brake control valve is a flapper nozzle, and the natural frequency of the shock and vibration isolator is selected to be approximately 75.5 Hz. 4. The shock and vibration isolator of claim 1, wherein said first radially inner rigid tubular member and said second inner rigid tubular member of the generally spool shaped rigid insert portion together define said central aperture therethrough. 5. The shock and vibration isolator of claim 1, wherein said first and second radially inner rigid tubular members are made of metal. 6. The shock and vibration isolator of claim 5, wherein said metal is selected from the group consisting of stainless steel, titanium, aluminum, copper, brass, and combinations thereof. 7. The shock and vibration isolator of claim 1, wherein said second generally tubular radially outer vibration insulating sheath portion includes a radially outer tubular portion and a radially inner annular portion, and said first generally tubular radially outer vibration insulating sheath portion includes a lower radially outwardly flared end portion with a lower lip portion that extends over the lower radially outwardly flared end portion of the second inner rigid tubular member of the radially inner generally spool shaped rigid insert portion, and said first generally tubular radially outer vibration insulating sheath portion includes an upper radially inner flange that is overlapped by and interfits with the radially inner annular portion of the second generally tubular outer vibration insulating sheath portion. 8. The shock and vibration isolator of claim 1, wherein said first generally tubular radially outer vibration insulating sheath portion is secured about the upper flange and lower radially outwardly flared annular end portion of the second radially inner rigid tubular member of the generally spool shaped rigid insert portion, and the second generally tubular radially outer vibration insulating sheath portion is secured about the upper radially outwardly flared annular end portion of the first radially inner rigid tubular member. 9. The shock and vibration isolator of claim 1, wherein said first generally tubular radially outer vibration insulating sheath portion and the second generally tubular radially outer vibration insulating sheath portion of the radially outer generally spool shaped vibration insulating sheath portion comprise an elastomer. 10. The shock and vibration isolator of claim 9, wherein said elastomer is selected from the group consisting of fluorosilicone elastomer, silicone rubber, nitrile rubber, butyl rubber, and combinations thereof. 11. The shock and vibration isolator of claim 1, wherein said shock and vibration isolator has a radially outer diameter that is dimensioned such that the fastener placed through the central aperture of the rigid tubular insert portion will be spaced apart from a mounting foot in which the shock and vibration isolator is placed by the vibration insulating sheath portion, wherein vibrations transmitted through the fastener from the aircraft structural part will be substantially isolated from the mounting feet of the manifold of the brake control valve. 12. A shock and vibration isolation mounting system for hard mounting an aircraft brake control valve to a structural part of an aircraft, the aircraft brake control valve including a component having at least one frequency of vibration, the shock and vibration isolation mounting system comprising: an aircraft brake control valve manifold, said manifold including a plurality of mounting feet configured to be hard mounted to a structural part of an aircraft, each of said plurality of mounting feet having a central mounting aperture configured to receive and retain a shock and vibration isolator;a shock and vibration isolator disposed in each said central aperture of each of said plurality of mounting feet, each said shock and vibration isolator including a radially inner generally spool shaped rigid insert portion and a radially outer generally spool shaped vibration insulating sheath portion; andwherein each said shock and vibration isolator has a natural frequency predetermined to be below a natural frequency of the component of the brake control valve to protect the component of the brake control valve from random vibration and to avoid gun fire sinusoidal frequencies. 13. The shock and vibration isolation mounting system of claim 12, wherein said inner generally spool shaped rigid insert portion comprises a first radially inner rigid tubular member and a second inner rigid tubular member that overlaps and interfits with the first radially inner rigid tubular member. 14. The shock and vibration isolation mounting system of claim 13, wherein said first radially inner rigid tubular member and said second inner rigid tubular member of the generally spool shaped rigid insert portion together define a central aperture therethrough for receiving a fastener for hard mounting of the mounting feet of the brake control valve manifold to a structural part of the aircraft. 15. The shock and vibration isolation mounting system of claim 13, wherein said first and second inner rigid tubular members are made of stainless steel. 16. The shock and vibration isolation mounting system of claim 15, wherein said first and second radially inner rigid tubular members are made of a metal selected from the group consisting of stainless steel, titanium, aluminum, copper, brass, and combinations thereof. 17. The shock and vibration isolation mounting system of claim 12, wherein said outer generally spool shaped vibration insulating sheath portion comprises a first generally tubular radially outer vibration insulating sheath portion and a second generally tubular radially outer vibration insulating sheath portion that overlaps and interfits with the first generally tubular outer vibration insulating sheath portion. 18. The shock and vibration isolation mounting system of claim 17, wherein said first generally tubular radially outer vibration insulating sheath portion and said second generally tubular radially outer vibration insulating sheath portion of the radially outer generally spool shaped vibration insulating sheath portion comprise an elastomer. 19. The shock and vibration isolation mounting system of claim 18, wherein said elastomer is selected from the group consisting of fluorosilicone elastomer, silicone rubber, nitrile rubber, butyl rubber, and combinations thereof. 20. The shock and vibration isolation mounting system of claim 12, wherein said shock and vibration isolator has a radially outer diameter that is dimensioned such that a fastener placed through the central aperture of the rigid tubular insert portion will be spaced apart from the mounting foot in which the shock and vibration isolator is placed by the vibration insulating sheath portion, wherein vibrations transmitted through the fastener from the aircraft structural part will be substantially isolated from the mounting feet of the manifold of the brake control valve. 21. The shock and vibration isolation mounting system of claim 12, wherein the component of the brake control valve is a flapper nozzle, and the natural frequency of the shock and vibration isolators is selected to be approximately 75.5 Hz.