A dynamically equivalent four body approximation of the NASTRAN finite element model supplied for hybrid deployable truss to support the digital computer simulation of the ten body model of the flexible space platform that incorporates the four body truss model were investigated. Coefficients for sensitivity of state variables of the linearized model of the three axes rotational dynamics of the prototype flexible spacecraft were generated with respect to the model's parameters. Software changes required to accomodate addition of another rigid body to the five body model of the rotational dynamics of the prototype flexible spacecraft were evaluated.
Exhibit D Modular Design Attitude Control System Study
1984
69 pages
Report
Keine Angabe
Englisch
Exhibit D modular design attitude control system study
NTRS | 1984
|Modular design attitude control system
NTRS | 1982
|Modular Design Attitude Control System
NTIS | 1982
|Modular Design Attitude Control System
NTIS | 1983
|Modular design attitude control system
NTRS | 1983
|