Add to ORKGThe Level C requirements for the shuttle orbiter terminal area energy management (TAEM) guidance and flight control functions to be incorporated into the Mission Control Center entry profile planning processor are defined. This processor will be used for preentry evaluation of the entry through landing maneuvers, and will include a simplified three degree-of-freedom model of the body rotational dynamics that is necessary to account for the effects of attitude response on the trajectory dynamics. This simulation terminates at TAEM-autoland interface
A program was developed to calculate trajectories for both military and commercial aircraft for use ...
The navigation and flight director guidance systems implemented in the NASA/FAA helicopter microwave...
The acceptance test procedure is described for the Lockheed Electronics Elevon Servoactuator Simulat...
The definition of standard flight segments of phases, representing flight profile components which c...
The TAEM guidance and body rotational dynamics models required for the MCC simulation of the TAEM mi...
The scheduling algorithm for mission planning and logistics evaluation (SAMPLE) is presented. Two ma...
The study to develop a system model and computer program representative of broadcasting satellite sy...
The development of space shuttle separation devices is reviewed to illustrate the mechanisms involve...
The formulation of Level C requirements for guidance software was reported. Requirements for a PEG s...
Calibration method and ultrahigh vacuum components for ionization gage and mass spectromete
Computer program documentation and user manual for steady state attitude control propulsion system -...
A study was performed to determine the types of manned missions that will likely be performed in the...
Work completed on the design and study of an annular suspension and pointing (ASP) system for the sp...
The experimental program which was conducted in the Calspan 96-inch hypersonic shock tunnel to inves...
Space shuttle guidance, navigation, and control design equations are presented. The space-shuttle mi...
A program was developed to calculate trajectories for both military and commercial aircraft for use ...
The navigation and flight director guidance systems implemented in the NASA/FAA helicopter microwave...
The acceptance test procedure is described for the Lockheed Electronics Elevon Servoactuator Simulat...
The definition of standard flight segments of phases, representing flight profile components which c...
The TAEM guidance and body rotational dynamics models required for the MCC simulation of the TAEM mi...
The scheduling algorithm for mission planning and logistics evaluation (SAMPLE) is presented. Two ma...
The study to develop a system model and computer program representative of broadcasting satellite sy...
The development of space shuttle separation devices is reviewed to illustrate the mechanisms involve...
The formulation of Level C requirements for guidance software was reported. Requirements for a PEG s...
Calibration method and ultrahigh vacuum components for ionization gage and mass spectromete
Computer program documentation and user manual for steady state attitude control propulsion system -...
A study was performed to determine the types of manned missions that will likely be performed in the...
Work completed on the design and study of an annular suspension and pointing (ASP) system for the sp...
The experimental program which was conducted in the Calspan 96-inch hypersonic shock tunnel to inves...
Space shuttle guidance, navigation, and control design equations are presented. The space-shuttle mi...
A program was developed to calculate trajectories for both military and commercial aircraft for use ...
The navigation and flight director guidance systems implemented in the NASA/FAA helicopter microwave...
The acceptance test procedure is described for the Lockheed Electronics Elevon Servoactuator Simulat...