Space programs summary no. 37-47, volume 2 for the period July 1 to August 31, 1967. The deep space network
Space navigation, tracking, and telecommunication engineering for deep space instrumentation network
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Unmanned thermal performance evaluation of a Gemini extravehicular space suit. Volume 1 - Test report Gemini Bravo test series space environment simulator test
Thermal and space environment simulation testing of Gemini extravehicular space suit
Copeland, R. J.↗
Evolution of space feeding concepts during the Mercury and Gemini space programs.
Space feeding concepts during Mercury and Gemini space programs noting packaging techniques, food variety and sterilization constraints
Lachance, P. A.↗
Space programs summary no. 37-55, volume 2 for the period 1 November to 31 December 1968. The deep space network
Deep space network system for communication and guidance of planetary and interplanetary space probes
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Manned space missions - Gateway to our future in space.
Manned space stations for future space exploration, discussing earth-like environment, artificial gravity, human factors and time dependence
Gilruth, R. R.↗
The space station - A fundamental element of the integrated space program
Orbital space station program, discussing common module design, support, space shuttles and objectives
Cramblit, D. C.↗
Deep space network support of the Manned space flight network for Apollo, 1962 - 1968, volume 1
Deep Space Network support of Manned Space Flight Network for Apollo project
Flanagan, F. M.↗
Use of space tug to increase payload capability of space shuttle
Use of space tug to increase payload capability of space shuttle, and effect of orbit inclination variation on payload capability
Harrison, E. F.↗
Space radiation protection - Space vehicle design criteria
Criteria and procedures for determining dosage of penetrating space radiation and design of appropriate protection for space vehicles
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Space and planetary environment criteria guidelines for use in space vehicle development, 1971 revision
A consolidation of natural environment data is presented for use as design criteria guidelines in space and planetary exploration vehicle development programs. In addition to information in the disciplinary areas of aeronomy, radiation, geomagnetism, astrodynamic constants, and meteoroids for the earth's environment above 90 kilometers, interplanetary space, and the planetary environments, the upper atmosphere model currently recommended for use at MSFC is discussed in detail.
Smith, R. E.↗
Development of space stable thermal control coatings for use on large space vehicles
The evaluation and environmental testing of zinc orthotitanate pigments for use as space stable thermal control coatings on large space vehicles are discussed. Electron paramagnetic resonance spectra of the pigments and their precursor compounds are examined. A continuing study of the spectral intensity of mercury-argon and mercury-xenon sources in reported. Results of long term environmental testing of commercially available, strippable, protective coatings are discussed.
Gilligan, J. E.↗
Space shuttle: Directional and lateral stability and interference effects of cruise engine location on a 0.015 scale space shuttle
The results are presented that were obtained from a wind tunnel tests to improve space shuttle booster baseline lateral-directional stability, control characteristics, and cruise engine location optimization. Tests were conducted in a 7 x 10-foot transonic wind tunnel. The model employed was a 0.015-scale replica of a space shuttle booster. The three major objectives of this test were to determine the following: (1) force, static stability, and control effectiveness characteristics for varying angles of positive and negative wing dihedral and various combinations of wing tip and centerline dorsal fins; (2) force and static stability characteristics of cruise engines location on the body below the high aerodynamic canard; and (3) control effectiveness for the low-mounted wing configuration. The wing dihedral study was conducted at a cruise Mach number of 0.40 and simulated altitude of 10,000 feet. Portions of the test were conducted to determine the control surfaces stability and control characteristics over the Mach number range of 0.4 to 1.2. The aerodynamic characteristics determined are based on a unit Reynolds number of approximately 2 million per foot. Boundary layer trip strips were employed to induce boundary layer transition.
Buchholz, R. E.↗
Manned space flight nuclear system safety. Volume 1: Executive summary. Part 2: Space shuttle nuclear system safety
The nuclear safety integration and operational aspects of transporting nuclear payloads to and from an earth orbiting space base by space shuttle are discussed. The representative payloads considered were: (1) zirconium hydride-Brayton power module, (2) isotope-Brayton power module, and (3) small isotope power systems or heat sources. Areas of investigation also include nuclear safety related integration and packaging as well as operational requirements for the shuttle and payload systems for all phases of the mission.
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Manned space flight nuclear system safety. Voluem 5: Nuclear system safety guidelines. Part 2: Space shuttle/nuclear payloads safety
The design and operations guidelines and requirements developed in the study of space shuttle nuclear system transportation are presented. Guidelines and requirements are presented for the shuttle, nuclear payloads (reactor, isotope-Brayton and small isotope sources), ground support systems and facilities. Cross indices and references are provided which relate guidelines to each other, and to substantiating data in other volumes. The guidelines are intended for the implementation of nuclear safety related design and operational considerations in future space programs.
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Space shuttle: Aerodynamic characteristics of various MDAC space shuttle ascent configurations with parallel burn pressure-fed and SRM boosters. Volume 1: Tanks T1 and T2 ascent configurations
Various space shuttle ascent configurations were tested in a trisonic wind tunnel to determine the aerodynamic characteristics. The ascent configuration consisted of a NASA/MSC 040 orbiter in combination with various HO centerline tank and booster geometries. The aerodynamic interference between components of the space shuttle and the effect on the orbiter aerodynamics was determined. The various aerodynamic configurations tested were: (1) centerline HO tanks T1 and T2, (2) centerline HO tank T3, and (3) centerline HO tank H4.
Jarrett, T. W.↗
A method for determining the response of space shuttle to atmospheric turbulence. Volume 1: Space shuttle turbulence response
A computer program has been developed and demonstrated that can analyze the response of space shuttle to atmospheric turbulence. The method developed accounts for propellant slosh, gimballed engine, and stability augmentation system (SAS) coupling with the elastic vehicle. Statistical outputs are generated that relate vehicle loads and accelerations to level of random turbulence. For discrete turbulence descriptions, response time-histories are computed. Preliminary turbulence response analyses of space shuttle were conducted for one ascent and one booster flyback subsonic flight condition. The ascent case considered both symmetric and antisymmetric boundary conditions, while only the symmetric analysis was conducted for booster flyback. The three conditions were analyzed with SAS active and inactive, but apparent instabilities with SAS active (arising from improper gains) invalidated the results. Load and acceleration responses in all cases, however, were well within vehicle design limits.
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Optical space astronomy and goals of the large space telescope.
Optical astronomy now means the study of EM radiation in the very near IR and vacuum UV in addition to the visible wavelengths. Practical constraints presently define the IR limit at about 11000 A, where photoemissive cathodes become ineffective, and the UV limit at 912 A, where the hydrogen of the interstellar medium limits the view to very nearby objects. Salient events of the first decade of optical space astronomy are discussed together with the orbiting astronomical observatories. Particular attention is given to the large space telescope (LST) project, taking into account the physical characteristics of the LST and the scientific program.
O'Dell, C. R.↗
Kennedy Space Center Space Shuttle facilities.
Description of tasks and facilities involved in the processing of Space Shuttle missions at the Kennedy Space Center. Responsibilities considered include vehicle integration and launch, recovery and refurbishment of the spent solid rocket motors, and landing and refurbishment of the Orbiter vehicles. Facility options are evaluated for transportation, on-site processing, mating, and recovery of the booster, drop tank, and Orbiter elements. Processing flow patterns are outlined for assembly, maintenance, checking, safing, refurbishment, and launch operations.
Clark, R. L.↗