Engineering topics
Publications and source records attributed to Gilruth, R. R..
Research is described which was conducted at the Wallops Island Missile Range (operated by the old National Advisory Committee for Aeronautics). These early beginnings are shown to be the base from which the Mercury Project evolved.
A very broad mission objective was established; i.e., manned circumlunar flight and return to earth. It is implicit that the Saturn will be the primary propulsion system for this mission. The following attempts to: (1) define the objective so as to achieve as much capability in the vehicle as possible; (2) draw on Mercury experience to provide broad guidelines for vehicle performance and safety; (3) provide flexibility in the vehicle capability in the event that the manned lunar mission is proved to be subject to unacceptable risk in the target time period; and (4) indicate problem areas where work appears to be particularly needed.
Manned flight from Montgolfier Balloon to Apollo 13, discussing future space programs including lunar base and space shuttle
Earth-orbiting manned space station as single facility base for power, volume, logistics, experimental equipment and data communications
Manned space stations for future space exploration, discussing earth-like environment, artificial gravity, human factors and time dependence
Manned space stations size, crew, orbit, lifetime, resupply requirements, etc
Space station design requirements, Apollo applications program and various experimental programs
Manned space station advantages, experimental programs, and design possibilities, with Apollo Applications Program plans
Manned space flight - scientific, technological and sociological background
Reliability and quality control in manned spacecraft
Apollo project is discussed, considering manned lunar mission and lunar orbital rendezvous requirements, utilizing project mercury experience
Reliability and quality control requirements for manned space flight - designs, procedures, and schedules
Explore the source record for details and available documents.
Results are presented of brief flight tests of the aileron characteristics of the XP-60 airplane with internally balanced, sealed ailerons, which were developed by the NACA for use, particularly, on low-drag-type wings. The results show that light and effective aileron control was obtained without evidence of overbalance or undesirable shaking of the control system at any part of the deflection range within the level-flight speed range.
Flight tests were made with a Kellett YG-1 autogiro to determine the relationship between the ground reaction and the vertical velocity at contact for landings of the flared and gliding three-point types. The data obtained are presented in the form of time histories of linear accelerations at the center of gravity resulting from the initial landing impact. In addition, the attitude angle and velocity of the autogiro at contact were measured. The landings were all mild as compared to those representative of airplanes tested in this manner, the maximum vertical velocity being 4.4 feet per second with a corresponding normal acceleration of 2.35 g.