Study shows that for reasonable values of initial-condition errors and equipment biases, resultant position indication errors will not become excessive unless re-entry maneuver time is greater than 45 to 60 min; position indication error caused by accelerometer uncertainties can be reduced by leaving accelerometers off until their output becomes significantly greater than their uncertainty.
Investigation of errors of inertial guidance system during satellite re-entry
NASA -- Tech Note
1960
42 pages
Article (Journal)
English
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