Topics
optimizationCultivar (cultivated variety)
thermal protection systemOrganisation
Space shuttle trajectory-shaping optimization considering the vehicle's thermal environment and the resulting requirements of the thermal protection system (TPS) are discussed. Optimization studies have been conducted yielding results which are generally applicable to shuttle orbiters and are independent of evolution and redirection of the space shuttle program. Two investigations of optimal trajectory shaping, with different methods of considering the thermal environment are presented
An approach to calculating optimal, gliding flight paths of the type associated with the space shutt...
Two computer programs for shuttle reentry trajectory optimization are listed and described. Both pro...
During its lifetime a space launcher is subjected to extreme heat loads. To protect space vehicles f...
Shielding a spacecraft from the severe thermal environment of an atmospheric entry requires a sophis...
The Space Shuttle orbiter's thermal protection system (TPS), designed mainly on the basis of wind tu...
Aerothermodynamic development flight test data from the first orbital flight test of the Space Trans...
A broad base of thermocouple and phase change paint data was assembled and correlated to the nominal...
The Space Shuttle descent mission planning, mission design, deorbit targeting, and entry guidance ha...
During its lifetime a space launcher is subjected to extreme heat loads. These can dramatically infl...
The performance gains which are possible through the use of optimal trajectories for a particular sp...
Analytical models are presented for optimal trajectories and reentry guidance of the space shuttle o...
A structural performance and resizing finite element thermal analysis computer program was used in t...
Quantitative estimates of the uncertainty in predicting aerodynamic heating rates for a fully reusab...
ABSTRACT: The aim of this paper was to identify, for a specific maneuver, the optimal combination be...
A mission profile for advanced thermal protection system suborbital flight testing is identified. It...
An approach to calculating optimal, gliding flight paths of the type associated with the space shutt...
Two computer programs for shuttle reentry trajectory optimization are listed and described. Both pro...
During its lifetime a space launcher is subjected to extreme heat loads. To protect space vehicles f...
Shielding a spacecraft from the severe thermal environment of an atmospheric entry requires a sophis...
The Space Shuttle orbiter's thermal protection system (TPS), designed mainly on the basis of wind tu...
Aerothermodynamic development flight test data from the first orbital flight test of the Space Trans...
A broad base of thermocouple and phase change paint data was assembled and correlated to the nominal...
The Space Shuttle descent mission planning, mission design, deorbit targeting, and entry guidance ha...
During its lifetime a space launcher is subjected to extreme heat loads. These can dramatically infl...
The performance gains which are possible through the use of optimal trajectories for a particular sp...
Analytical models are presented for optimal trajectories and reentry guidance of the space shuttle o...
A structural performance and resizing finite element thermal analysis computer program was used in t...
Quantitative estimates of the uncertainty in predicting aerodynamic heating rates for a fully reusab...
ABSTRACT: The aim of this paper was to identify, for a specific maneuver, the optimal combination be...
A mission profile for advanced thermal protection system suborbital flight testing is identified. It...
An approach to calculating optimal, gliding flight paths of the type associated with the space shutt...
Two computer programs for shuttle reentry trajectory optimization are listed and described. Both pro...
During its lifetime a space launcher is subjected to extreme heat loads. To protect space vehicles f...
Add to ORKG