Comments on the operation of the JPL 25-ft space simulator.
JPL 25-ft space simulator tests Ranger, Mariner and Surveyor spacecraft under conditions of extreme cold, high vacuum and intense solar radiation
SPACE SIMULATOR↗
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Comments on preflight training for Gemini V.
Preflight planning and training stages for Gemini V, considering spacecraft test, mission simulators, planetarium, survival and parachute training, etc
MISSION PLANNING↗
Mechanical properties of wire insulation automatically determined
Three separate mechanisms test the insulation on electrical wire specimens for mechanical resistance to flexure, abrasion or wear, and vibration. The test mechanisms perform the evaluation tests on insulated wire specimens in a chamber which can be controlled to simulate space or spacecraft cabin environments.
Dawn, F. S.↗
Radiometry Research
Vortex arc studies, solar flux and spectral measurements, spacecraft coatings, solar simulation studies, and solar cell radiation effects testing
TEMPERATURE CONTROL↗
Apollo ECS man-rated simulation systems.
Design, tests, operation and limitations of Apollo man-rated environmental control system simulation chamber
SYSTEMS DESIGN↗
Molecular sink.
Molecular sink for simulated testing of spacecraft components noting vessel construction, vacuum pump system, molecular trap array, etc
MOLECULAR PUMP↗
Four-bar linkage for thermal compensation in test mounts for structures
Supporting system compensates automatically for the dimensional changes produced by contraction and expansion of structures undergoing thermal proofing on mounts. Structurally destructive forces would be exerted on a spacecraft in a simulator if this four bar linkage test mount was not used.
Norman, R. M.↗
Space simulator Patent
Space environment simulator for testing spacecraft components under aerospace conditions
Stephens, J. B.↗
Pilot compartment airbag restraint program Final report
Computerized and manned spacecraft and aircraft simulator impact testing of air cushion elastic restraint systems
Blechschmidt, C.↗
Primary and secondary particle contributions to the depth dose distribution in a phantom shielded from solar flare and Van Allen protons
Calculations have been made using the nucleon-meson transport code NMTC to estimate the absorbed dose and dose equivalent distributions in astronauts inside space vehicles bombarded by solar flare and Van Allen protons. A spherical shell shield of specific radius and thickness with a 30-cm-diam. tissue ball at the geometric center was used to simulate the spacecraft-astronaut configuration. The absorbed dose and the dose equivalent from primary protons, secondary protons, heavy nuclei, charged pions, muons, photons, and positrons and electrons are given as a function of depth in the tissue phantom. Results are given for solar flare protons with a characteristic rigidity of 100 MV and for Van Allen protons in a 240-nautical-mile circular orbit at 30 degree inclination angle incident on both 20-g/sq cm-thick aluminum and polyethylene spherical shell shields.
Santoro, R. T.↗
Lunar soil properties and soil mechanics
The long-range objectives were to develop methods of experimentation and analysis for the determination of the physical properties and engineering behavior of lunar surface materials under in situ environmental conditions. Data for this purpose were obtained from on-site manned investigations, orbiting and softlanded spacecraft, and terrestrial simulation studies. Knowledge of lunar surface material properties are reported for the development of models for several types of lunar studies and for the investigation of lunar processes. The results have direct engineering application for manned missions to the moon.
Mitchell, J. K.↗
Geometric stiffness characteristics of a rotating elastic appendage
Previous work by Likins (1972 and 1973) on finite element appendage equations for hybrid coordinate dynamic analysis and on the dynamic analysis of a system of hinge-connected rigid bodies with nonrigid appendages is extended to the establishment of a basis for a generic digital computer program to be developed for the simulation of nonrigid spacecraft. A subtle but significant generalization of that previous work as well as a correction and elaboration accomplish this purpose.
Likins, P. W.↗
Postflight Evaluation of Atlas-Centaur AC-5 (Launched 2 March 1965)
The Atlas-Centaur AC-5 vehicle was launched from ETR Complex 36A on March 2., 1965 at 8:25.04 a.m. EST. Within about 1 second after launch the thrust of the Atlas booster engine decayed rapidly; the vehicle settled back on the launch pad and was quickly destroyed by fire and explosion. Considerable damage was sustained by the launch complex and its associated equipment. Loss of booster engine thrust was due to fuel depletion at the turbopump inlets, which is attributed to closure of the fuel prevalve or the staging valve. To preclude the recurrence of either of these fuel valving malfunctions, the following corrective action has been taken: The remote control actuator has been replaced by manual operation of the Atlas fuel prevalve; the internal passage dimensions in the staging valve have been increased to lessen the hydraulic load on the valve poppet. In addition to the Atlas fuel system malfunction, a failure in the power control circuitry of the Centaur guidance computer resulted in partial removal of power at umbilical ejection. To prevent such a guidance system failure on future flights some redundant circuitry has been eliminated and more rigorous checkout procedures have been adopted. No further anomalies were discovered in the telemetered data prior to the Atlas booster thrust decay. A prime objective of the AC-5 flight was to place a dynamic model of the Surveyor spacecraft in a simulated lunar transfer trajectory. An important facet of this problem is the demonstration of a launch-on-time capability in accordance with the proper Earth-moon relation. The window opening time was established at 8:25 a.m. EST; thus the actual launch occurred within 4 seconds of the planned time.
Source record↗
Thermal performance of gaseous-helium-purged tank-mounted multilayer insulation system during ground-hold and space-hold thermal cycling and exposure to water vapor
An experimental investigation was conducted to determine (1) the ground-hold and space-hold thermal performance of a multilayer insulation (MLI) system mounted on a spherical, liquid-hydrogen propellant tank and (2) the degradation to the space-hold thermal performance of the insulation system that resulted from both thermal cycling and exposure to moisture. The propellant tank had a diameter of 1.39 meters (4.57ft). The MLI consisted of two blankets of insulation; each blanket contained 15 double-aluminized Mylar radiation shields separated by double silk net spacers. Nineteen tests simulating basic cryogenic spacecraft thermal (environmental) conditions were conducted. These tests typically included initial helium purge, liquid-hydrogen fill and ground-hold, ascent, space-hold, and repressurization. No significant degradation of the space-hold thermal performance due to thermal cycling was noted.
Sumner, I. E.↗
EPS analysis of nominal STS-1 flight
The results of electrical power system (EPS) analysis of the planned Shuttle Transportation System Flight 1 mission are presented. The capability of the orbiter EPS to support the planned flight and to provide program tape information and supplementary data specifically requested by the flight operations directorate was assessed. The analysis was accomplished using the orbiter version of the spacecraft electrical power simulator program, operating from a modified version of orbiter electrical equipment utilization baseline revision four. The results indicate that the nominal flight, as analyzed, is within the capabilities of the orbiter power generation system, but that a brief, and minimal, current overload may exist between main distributor 1 and mid power controlled 1, and that inverter 9 may the overloaded for extended periods of time. A comparison of results with launch commit criteria also indicated that some of the presently existing launch redlines may be violated during the terminal countdown.
Wolfgram, D. F.↗
Environmental control and life support system: Analysis of STS-1
The capability of the orbiter environmental control and life support system (ECLSS) to support vehicle cooling requirements in the event of cabin pressure reduction to 9 psia was evaluated, using the Orbiter versions of the shuttle environmental consumbles usage requirement evaluation (SECURE) program, and using heat load input data developed by the spacecraft electrical power simulator (SEPS) program. The SECURE model used in the analysis, the timeline and ECLSS configuration used in formulating the analysis, and the results of the analysis are presented. The conclusion which may be drawn drom these results. is summarized. There are no significant thermal problems with the proposed mission. There are, however, several procedures which could be optimized for better performance: setting the cabin HX air bypass and the interchanger water bypass to the zero flow position is of questionable efficacy; the cabin air pressure monitoring procedure should be re-evaluated; and the degree of equipment power down specified for this analysis and no problems were noted.
Steines, G.↗
Monte Carlo Investigation of Trajectories
Monte Carlo Investigation of Trajectory Operations and Requirements (MONITOR) program performs spacecraft mission maneuver simulations for craft mission maneuver simulations for geosynchronous single-maneuver, and cometencounter trajectories. Used primarily to study geosynchronous missions and model trajectories of satellites deployed by Space Shuttle. Program written in FORTRAN IV.
Glass, A. B.↗
Effects of weightlessness on body composition in the rat
The effects of weightlessness on the body composition of rats were investigated using 5 male rats exposed to 18.5 days of weightlessness on the COSMOS 1129 biosatellite and killed after reentry. The animals were immediately dissected and the three major body divisions (musculoskeletal system, skin, and pooled viscera) were analyzed for fat, water, solids, and six elements. These results were determined as percentages of the fat-free body or its components and then compared with two groups of terrestrial controls, one of which was subjected to a flight simulation in a spacecraft mock-up while the other was under standard vivarium conditions. Compared with the control groups, the flight group was found to exhibit a reduced fraction of total body water, a net shift of body water from skin to viscera, a marked diminution in the fraction of extracellular water in the fat-free body, a marked reduction in the fraction of bone mineral, no change in the quantity of stored fat or adrenal masses, and a net increase in total muscle mass as indicated by total body creatine, protein, and body cell mass.
Pitts, G. C.↗