Flexural vibration of gravity-stabilized, structurally damped, large flexible satellites SHRIVASTAVA, S. K.; MAHARANA, P. K. (Indian Institute of Science, Bangalore, India) Journal of Guidance, Control, and Dynamics (ISSN 0731-5090), vol. 8, Mar.-Apr. 1985, p. 214-222. 14 Refs. Language: English Country of Origin: India. Country of Publication: United States Document Type: JOURNAL ARTICLE Most documents available from AI A A Technical Library Journal Announcement: IAA8511 The stability and response of the in-plane flexural motion of gravity-stabilized, structurally damped, large flexible satellites in circular and eccentric orbits are analyzed. Employing the method of strained parameters, the stability analysis shows that the critical damping is sensitive to the satellite inertia ratio. It is noted that the orbital eccentricity excites satellite inertia ratio. It is noted that the orbital eccentricity excites motion in several high and low frequencies and generally decreases the stability of the system. An analytical expression for flexural response is obtained using the multiple-scales techniques. Finally, stability charts and response are presented for a range of the system parameters. (Author) Source of Abstract (Subfile): AIAA/TIS Descriptors: ‘ELASTIC DAMPING; ‘FLEXIBLE SPACECRAFT; ‘LARGE SPACE STRUCTURES; ‘SPACECRAFT STABILITY; ‘STRUCTURAL VIBRATION; CIRCULAR ORBITS; ECCENTRIC ORBITS; ELASTIC BODIES; EQUATIONS OF MOTION; SATELLITE ORBITS Subject Classification: 7518 Spacecraft Design, Testing & Performance (1975- ) Space Station attitude control—An overview of requirements and solutions BUCHANAN, H. J. (NASA, Marshall Space Flight Center, Dynamics and Trajectory Analysis Branch, Huntsville, AL) National Aeronautics and Space Administration. Marshall Space Flight Center, Huntsville, Ala. Corp. Source Code: ND736801 American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 23rd Reno, NV, Jan. 14-17, 1985. 7 p. Report No.: AIAA PAPER 85-0027 Language: English Country of Origin: United States. Country of Publication: United States Document Type: PREPRINT Most documents available from AIAA Technical Library Journal Announcement: IAA8510 Attitude control and various structural aspects of NASA's permanent manned Space Station are discussed in the framework of design flexibility, obsolescence as a deterrent to a long operational life, modularity, and autonomy. Among the variable factors of specific importance, consideration is given to internal factors, such as inertial variations (up to 400 percent), center of mass movements (up to 28m), and shifts in modal characteristics, as well as to external torque shifts associated with aerodynamic moments and gravity gradients. The compatibility among multiple-user requirements is also considered. As the Station is a low-orbit spacecraft, its attitude will be greatly affected by the inhomogeneity of the atmosphere, placing a priority on the attitude
RkJQdWJsaXNoZXIy MTU5NjU0Mg==