Fixed-base simulator investigation of lightweight vehicles for lunar escape to orbit with kinesthetic attitude control and simplified manual guidance

Piloted simulator investigation of lightweight vehicles for emergency lunar escape to orbit with kinesthetic attitude control and simplified manual guidanc

A system for aerodynamic design and analysis of supersonic aircraft. Part 3: Computer program description

The computer program documentation for the design and analysis of supersonic configurations is presented. Schematics and block diagrams of the major program structure, together with subroutine descriptions for each module are included

Aerodynamic design and analysis system for supersonic aircraft. Part 2: User's manual

An integrated system of computer programs for supersonic configurations is described. An explanation of system usage, the input definitions, and example output are included. For Part 1, see N75-18185; for Part 3, see N75-18186

A computational system for aerodynamic design and analysis of supersonic aircraft. Part 2: User's manual

An integrated system of computer programs was developed for the design and analysis of supersonic configurations. The system uses linearized theory methods for the calculation of surface pressures and supersonic area rule concepts in combination with linearized theory for calculation of aerodynamic force coefficients. Interactive graphics are optional at the user's request. This user's manual contains a description of the system, an explanation of its usage, the input definition, and example output

A computational system for aerodynamic design and analysis of supersonic aircraft. Part 3: Computer program description

For abstract, see Vol. 1

Development of a simulator for studying simplified lunar escape systems

Design and development of lunar escape system simulator for investigation of lunar escape problems and simplified manual guidance and control for lunar escape vehicle

Description and flight tests of an oculometer

A remote sensing oculometer was successfully operated during flight tests with a NASA experimental Twin Otter aircraft at the Langley Research Center. Although the oculometer was designed primarily for the laboratory, it was able to track the pilot's eye-point-of-regard (lookpoint) consistently and unobtrusively in the flight environment. The instantaneous position of the lookpoint was determined to within approximately 1 deg. Data were recorded on both analog and video tape. The video data consisted of continuous scenes of the aircraft's instrument display and a superimposed white dot (simulating the lookpoint) dwelling on an instrument or moving from instrument to instrument as the pilot monitored the display information during landing approaches

Preliminary flight tests of an oculometer

A remote sensing oculometer has been successfully operated during flight tests. This device was able to track the pilot's eye-point-of-regard (lookpoint) consistently and unobtrusively in the flight environment. The instantaneous position of the lookpoint was determined to within approximately 1 degree. Data were recorded on both analog and video tape. The video data consisted of continuous scenes of the aircraft's instrument display and a superimposed white dot (simulating the lookpoint) dwelling or moving from instrument to instrument as the pilot monitored the display information during landing approaches

Technique for thermal isolation of antenna-coupled infrared microbolometers

A new method was developed to thermally isolate monolithic antenna-coupled infrared microbolometers from their substrate. Using a SiO2 sacrificial layer to create a 400 mn thick Si3N4 membrane, square spiral antennas coupled to Ni microbolometers were fabricated and tested. The responsivity of the thermally isolated devices is 164 times greater than a similar device that is not fabricated on a membrane. (c) 2006 American Vacuum Society