SPACE LINKAGE SYSTEM. ANALYTICAL STUDY AND PRELIMINARY DESIGN. VOLUME II. APPENDIXES.
Abstract
Electrical power may be generated in space by heliotropically oriented static or dynamic energy conversion devices. Such devices, however, must be capable of being attached to an earth-oriented mission vehicle. To provide maximum utility, the resulting two-body system must be capable of operation at any orbital inclination angle. The physical connection of two bodies in space, which precludes shadowing or collision of the two bodies, imposes a widely spaced, linked-together, two-body space system. The severe control dynamics problem associated with such a system must be investigated and solved. The objective of this study was to analytically determine the problems associated with a space linkage used to tether a sun-oriented space power system to an earth-oriented mission vehicle and to provide a preliminary design of a feasible space linkage system consistent with the established analytical results and criteria. A computer program was developed in which the appropriate parameter variations of control system design of the two vehicles were analyzed. Families of possible space linkages were established from which the final space linkage configuration evolved. Assuming a five-minute extension time for the space linkage, a loads and dynamics response analysis was accomplished which established the loads for the space linkage preliminary design.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1967
- Accession Number
- AD0816040
Entities
People
- A. F. Woldow
- A. J. Daughton
- E. F. Weiten
- J. R. Heim
- R. D. Dotson
Organizations
- Lockheed Martin Missiles and Space