Search NASA⌕ Search

Engineering topics

Brinton, B. C.

Publications and source records attributed to Brinton, B. C..

4 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1980

Space Shuttle solid rocket motor /SRM/ development and qualification

The configuration of the reusable Space Shuttle solid rocket motors is described. In addition, their design evolution is reviewed, noting that the requirement that certain components be recovered, refurbished, and used on as many as 20 flights dictated a conservative design approach, the validity of which has been proven by successful testing of all development and qualification motors. Aspects discussed include ballistics, the motor case, nozzle, nozzle materials, and the ignition system. Finally, summary results of the first two of three qualification motor firings designated QM-1 and QM-2 are presented.

Lund, R. K.↗
NASA NTRS1979

Space Shuttle SRM development

The successful static test of the fourth Development Space Shuttle Solid Rocket Motor (SRM) in February 1979 concluded the development testing phase of the SRM Project. Qualification and flight motors are currently being fabricated, with the first qualification motor to be static tested. Delivered thrust-time traces on all development motors were very close to predicted values, and both specific and total impulse exceeded specification requirements. 'All-up' static tests conducted with a solid rocket booster equipment on development motors achieved all test objectives. Transportation and support equipment concepts have been proven, baselining is complete, and component reusability has been demonstrated. Evolution of the SRM transportation support equipment, and special test equipment designs are reviewed, and development activities discussed. Handling and processing aspects of large, heavy components are described.

Brinton, B. C.↗
NASA NTRS1975

Thrust vector control for the Space Shuttle Solid Rocket Motor

Thrust vector control (TVC) for the Space Shuttle Solid Rocket Motor (SRM) is obtained by omniaxis vectoring of the nozzle. The development and integration of the system are under the cognizance of Marshall Space Flight Center (MSFC). The nozzle and flexible bearing have been designed and will be built by Thiokol Corporation/Wasatch Division. The vector requirements of the system, the impact of multiple reuse on the components, and the unique problems associated with a large flexible bearing are discussed. The design details of each of the major TVC subcomponents are delineated. The subscale bearing development program and the overall development schedule also are presented.

Counter, D. N.↗