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Redus, J. R.

Publications and source records attributed to Redus, J. R..

STV engine requirements

The Space Exploration Initiative program and the Space Transfer Vehicle studies provide the opportunity to evaluate the engine requirements for the next generation space engine within the context of a credible but technologically demanding program. Some of these requirements are generic, basically independent of the architecture, and others are mission and configuration dependent. Generic requirements include high reliability, space-basing, man-rataing, long life and reusability, and extended health monitoring, including automatic pre-mission checkout. Mission and configuration dependent requirements include vehicle/engine interfaces, engine throttling, performance specifications, engine system architecture, and operational requirements. It is argued that engine technology requirements must be extended from the usual performance-related issues to encompass reliability, space-basing, life, and extended health monitoring.

Redus, J. R.

Effects of ascent trajectory mode and tank disposal method on shuttle payload accommodation

The effects of external tank disposal by retrorocket versus passive tank drop, and targeting the main engine burn for high apogee versus the baseline parking orbit ascent method on shuttle payload accommodation capability were investigated. Missions launched from Eastern Test Range were investigated over a range of orbit altitudes to determine tank disposal requirements including footprint dispersions and alternate impact locations, performance, and orbital maneuvering system requirements. Passive tank drop also proved to be advantageous from a payload accommodation standpoint. Direct insertion was shown to be a means of accommodating long payloads at higher altitudes than permitted by the baseline ascent method.

Blair, J. C.

Effects of atmospheric models on space shuttle trajectories and aerodynamic heating.

Review of the respective contributions from the atmospheric physicist, trajectory analyst, and aerothermodynamist to the design problem underlying the selection of the space-shuttle booster mode to be developed, i.e., either expendable booster, recoverable booster, or flyback booster, and the configuration and composite configuration. The interrelationships between atmospheric variables, trajectory parameters, and aerodynamic heating loads are discussed.

Smith, O. E.