Flight Test Experiments to Evaluate Aided-Inertial System Performance for Terminal Guidance

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Abstract
Flight test experiments were carried out, in an H-19 helicopter, to establish the level of performance improvement which could be realized by updating an on-board inertial navigation system. Testing was accomplished in two parts. The first was pure inertial to establish the guidance system performance in the aircraft environment, and the second part established system performance in a position/velocity up-date mode. Simulations were carried out to include position/velocity/attitude up-date mode. Typically, tests were performed to examine total system position error as a function of flight profile, flight time, time of last up-date and frequency of up-date. The equipment used for the experiments (approximately sixty flights) included an inertial navigation system, a data transmission system, a digital command system and a radar system as the external navigation aid. Data will be presented in graphical form.

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