Environment
Equipment to be Protected
Sources of Vibration-Shock- Noise
Other Destructive or Deteriorative Conditions
Applicable Specifications and Typical Vibration, Shock, Noise Input
Desirable Isolator Characteristics
Applicable Barry Isolators or Systems
Fixed Wing Aircraft Fighter Jet

Radar; Radios.
Air data recorder.
Gyroscopes; Instrument panels.
Engine pressure ratio transducers.
Radar antennae; Antenna couplers.
Instruments, indicators, gages, etc.
Electronic countermeasures equipment.
Fire control radar and computers.
Bomb racks and sights.

Propulsion system.
Air turbulence.
Landing impact.
Taxiing.
Amplified vibration caused by
structural resonances.
Gunfire.
Temperature and humidity
extremes.
Altitude.
Chemical action of hydraulic
fluids, fuels, lubricants.
Sunlight and ozone.
Salt spray.
Fungus.
Sand and dust.
MIL-E-5400; MIL-E-5272; MIL-STD-810.
Typical Vibration Input:
5-10 Hz .080” D. A.
10-15 Hz .41 g.
15-75 Hz .036” D. A.
75-1000 Hz 10 g.
Typical Shock Input:
15 g - .011 sec.
30 g - .011 sec. (crash safety).
Note: Vibration & shock input levels vary widely; usually specified by airframe & component manufacturers.
MIL-C-172 (general reference for size & hardware requirements).
Natural frequency 10-25 Hz.
All attitude performance.
Maximum isolation efficiency.
Low amplification at resonance.
Minimum rotational coupling.
Minimum shock output.
Minimum sway space.
Minimum size and weight.
Electrical grounding.
Designed to ensure equipment survival.
Note: Isolator characteristics are a function of mission
of aircraft and performance parameters to which
equipment is subjected.
Example: extreme sustained acceleration.

Rotary Wing Aircraft
Helicopter
Radar; Radios.
Gyroscopes; Instrument panels.
Radar antennae; Antenna couplers.
Instruments, indicators, gages, etc.
Integrated avionics packages.
Fire control equipment
Propulsion system.
Rotor.
Landing impact.
Amplified vibration caused by
structural resonances.
Gunfire.
Temperature and humidity
extremes.
Altitude.
Chemical action of hydraulic
fluids, fuels, lubricants.
Sunlight and ozone.
Salt spray; Sand and dust.
Fungus.
MIL-E-5400; MIL-E-5272; MIL-STD-810.
Airframe and Component Manufacturers’ Specifications.
Typical Vibration Input:
5 - 20 Hz .100” D. A.
20 - 32 Hz 2 g.
32 - 72 Hz .036” D. A.
72 - 500 Hz 10 g.
Typical Shock Input:
15 g - .011 sec.
30 g - .011 sec. (crash safety).
MIL-C-172 (general reference for size &
hardware requirements).
Natural frequency 5-15 Hz.
Maximum isolation efficiency.
Low amplification at resonance.
Minimum rotational coupling.
Minimum shock output.
Minimum sway space.
Minimum size and weight.
Electrical grounding.
Designed to ensure equipment survival.

Space Vehicles 
Space Vehicle

Telemetry; Electronics.
Fuel lines.
Relay boxes, Arming and fusing systems
Electronics.
Antennae; Antenna couplers.
Instruments, indicators, gages, etc.,
Instruments panels.
Structural members.
Photographic and other optical equipment.
Propulsion system.
Separation of booster stages.
Re-entry deceleration.
Amplified vibration caused by
structural resonances
Temperature and humidity
extremes.
Altitude.
Chemical action of hydraulic
fluids, fuels, lubricants.
Sunlight and ozone.
Special handling.
Transport.
Storage and service environmental conditions
Specifications established by Systems Contractor.
Vibration inputs up to .50” D. A.
Sustained acceleration as high as 1000 g.
All attitude performance.
Maximum isolation efficiency.
Low amplification at resonance.
Minimum rotational coupling.
Minimum shock output.
Minimum sway space.
Minimum size and weight.
Electrical grounding.
Designed to ensure equipment survival.



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