A New Baseline for the Inertial Navigation Strapdown Simulator Program. Volume 2. Analytical Development
Abstract
The user may simulate not only the gross dynamics of the flight profile (from an external or internal profile generation) but also the angular and linear random vibrations resulting from gusts and turbulence acting on the airframe. The total environment is applied to the models of the inertial components (laser or SDR gyros and pendulous accelerometers). The resulting outputs of simulated IMU are summed in an interface module and compensated and scaled in the simulated navigation computer. The latter also contains the velocity/attitude algorithm, which computes the body-to-inertial transformation, using either the direction cosine matrix or quaternion, and the navigation algorithm which numerically integrates the specific forces after transformation to the local vertical, wander azimuth computational frame. The outputs of the simulated navigation computer are the computed position, velocity, and attitude of the vehicle with respect to a local vertical, north pointing frame. The flight profile and the differences between it and the simulated navigation computer outputs are tabulated in an evaluation module for printing, plotting, or post processing. A ground alignment Kalman filter for the INSS, also developed under this task, is not documented in this report, but may be available from AFAL/RWA-2 or -3. The program is written in Fortran IV for use on a CD6600/CYBER74.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1978
- Accession Number
- ADA062808
Entities
People
- Darold Riegsecker
- John Prohaska
- Roy Nurse
Organizations
- Charles Stark Draper Laboratory