SPACE LINKAGE SYSTEM. ANALYTICAL STUDY AND PRELIMINARY DESIGN. VOLUME I.
Abstract
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. This configuration utilizes either a Ryan type deployable boom or a folding type of linkage. 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. It is concluded that a linkage providing four degrees of freedom at appropriate locations will meet the mission requirements of this study. One of these degrees of freedom must be placed on the mission vehicle, providing 90 degrees of rotation to allow system operation at any orbital inclination angle. 10-KW power transfer and signal transfer is accomplished by using slip rings and flexible cables at appropriate degrees of freedom joints. A balance analysis was performed on the two connected space bodies and revealed that the system must be perfectly balanced for minimum attitude control torques. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1967
- Accession Number
- AD0816039
Entities
People
- A. F. Woldow
- A. J. Daughton
- E. F. Weiten
- J. R. Heim
- R. D. Dotson
Organizations
- Lockheed Martin Missiles and Space