Single gimbal/strapdown inertial navigation system for use on spin stabilized flight test vehicles

Conference · Mon Dec 31 23:00:00 EST 1979

OSTI ID:6811191

Watts, A C; Andreas, R D

A hybrid strapdown inertial navigation system intended for use on spin stabilized flight test vehicles is described. The configuration of the navigator which is briefly described consists of three floated rate integrating gyros, one of which is used in conjunction with the gimbal with the remaining two operated in a rate gyro mode. Outputs from the two strapdown gyros and three accelerometers are digitized and processed by a high performance computer. The navigation algorithms utilize a direction cosine matrix formulation for the attitude computation implemented in the digital computer. The implementation of this algorithm for the single gimbal configuration is described. An accuracy model and results for a reentry vehicle flight test trajectory are presented. The flight test performance from launch to reentry is presented.

• Research Organization: Sandia National Labs., Albuquerque, NM (USA)
• DOE Contract Number: AC04-76DP00789
• OSTI ID: 6811191
• Report Number(s): SAND-80-2479C; CONF-801211-1
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
420200* -- Engineering-- Facilities
Equipment
& Techniques
COMPUTERS
DATA
DESIGN
INERTIAL GUIDANCE
INFORMATION
NAVIGATIONAL INSTRUMENTS
NUMERICAL DATA
PERFORMANCE
SPACE FLIGHT
SPACE VEHICLES
STABILITY
THEORETICAL DATA
VEHICLES