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Low-cost inertial navigation for moderate-g missionsA low cost inertial navigation system (INS) concept is described for flight missions characterized by moderate accelerations and limited attitude variations. These missions involve general aviation aircraft, helicopters, or remotely piloted vehicles. The significance of the moderate acceleration and limited attitude is reviewed with respect to platform mechanization and instrumentation. A hybrid mechanization, partially gimballed and partially strapdown, is presented. The INS is implemented by an unbalanced two axis gimbal system and controlled by a two degree of freedom gyro. The INS provides locally level two axis acceleration information along with pitch and roll measurements. Heading information is provided by a second gyro mounted in the inner gimbal. The system error model is equivalent to that of a conventional platform with a tilt error determined by the integral of the gyro drift rate and an equivalent accelerometer type errors are also cancelled. Rapid gyro-compassing, implemented with opened gimbal control loops, and a strapdown procedure provides calibration of gyro drift rate biases.
Document ID
19790024034
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Merhav, S. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 3, 2013
Publication Date
September 1, 1979
Subject Category
Aircraft Instrumentation
Report/Patent Number
A-7920
NASA-TM-78611
Accession Number
79N32205
Funding Number(s)
PROJECT: RTOP 505-07-10-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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