Explorer 35 attitude control system
Flight performance of Explorer 35 attitude control system
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Flight performance of Explorer 35 attitude control system
Oscillations in pulse modulated satellite attitude control systems
Control system optimization hybrid computer program
Effect of cabin pressure on environmental control system
Structural flexibility effects on launch vehicle control systems and design criteria
Comparative evaluation of attitude control system
Optimal desaturation of angular momentum exchange controllers in spacecraft attitude control systems, using natural environmental torques
M2-F2 lifting body flight control system
Mathematical model of global spacecraft attitude control system based on three dimensional motion
Adaptive digitalized learning control system for launch vehicles
Neural pulse frequency modulated error sampled control system stability, considering model limitations and modifications
Optimal momentum exchange desaturation in attitude control systems for orbiting spacecraft, concerning gravity gradient and disturbance torques
Saturn launch vehicle navigation, guidance and control system, discussing optimal system design for flight path optimization
The main aspects of the attitude control system used on both the IMP-H and J spacecraft are presented. The mechanical configuration is described. Information on all the specific components comprising the flight system is provided. The acceptance and qualification testing of both individual components and the installed system are summarized. Functional information regarding the operation and performance in relation to the orbiting spacecraft and its mission is included. Related topics which are discussed are: (1) safety requirements, (2) servicing procedures, (3) anomalous behavior, and (4) pyrotechnic devices.
This paper describes the NASA/MSFC thermal control activities performed in support of the European design and development of the Spacelab environmental control system (ECS) and the integration of the ECS with experiments and with the Shuttle Orbiter. Thermal interfaces with the Orbiter are reviewed, including payload bay temperature profiles for the long module and pallet Spacelab configuration for the on-orbit mission phase. Thermal designs and predicted thermal performance are also reviewed for the module air cooling systems and specific experiment interfaces, such as the experiment dedicated heat exchanger and rack cooling.
Materials illustrating a presentation on environment control systems for electric flight systems are presented. Schematics and flow diagrams of fresh air source and air conditioning systems, and vapor cycle and air cycle parts lists are presented.
Materials illustrating a presentation on environmental control systems for electric flight systems are presented. The major technology issues, major development and application steps, the role of NASA, and required flight testing are outlined.
Executive Control Systems (ECSs) are software structures for the unification of various engineering design application programs into comprehensive systems with a central user interface (uniform access) method and a data management facility. Attention is presently given to the most significant determinations of a research program conducted for 24 ECSs, used in government and industry engineering design environments to integrate CAD/CAE applications programs. Characterizations are given for the systems' major architectural components and the alternative design approaches considered in their development. Attention is given to ECS development prospects in the areas of interdisciplinary usage, standardization, knowledge utilization, and computer science technology transfer.