Evaluation program for secondary spacecraft cells - General performance test of General Electric 20 ampere-hour nickel-cadmium secondary spacecraft cells
Evaluation of nickel cadmium cells for spacecraft power use
Christy, D. E.↗
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Prediction of the dynamic environment of spacecraft components. Part 2 - Acoustic and structural path transmission through two models of a shroud-enclosed spacecraft Final report
Acoustic and structural path transmission through shroud enclosed spacecraft
Greenspon, J. E.↗
A two spacecraft test of a single spacecraft method of estimating shock normals
Calculating improved shock normals using least squares technique on combined magnetic field and plasma data from single spacecraft
Lepping, R. P.↗
Thermionic spacecraft design study, 120 kw nuclear electric propulsion system. Volume 2: External fuel reactor spacecraft design
Design and development of electrically propelled spacecraft based on external-fuel reactor concepts for thermionic reactors - Vol. 2
Source record↗
Evaluation program for secondary spacecraft cells: initial evaluation tests of 20.0 ampere-hour nickel-cadmium spacecraft cells manufactured by Gulton Industries, Incorporated
The report describes testing and performance of 20.0 ampere-hour Ni-Col spacecraft batteries.
Harkness, J. D.↗
System design of the Pioneer Venus spacecraft. Volume 4: Probe bus and orbiter spacecraft vehicle studies
The requirements, trades, and design descriptions for the probe bus and orbiter spacecraft configurations, structure, thermal control, and harness are defined. Designs are developed for Thor/Delta and Atlas/Centaur launch vehicles with the latter selected as the final baseline. The major issues examined in achieving the baseline design are tabulated. The importance of spin axis orientation because of the effect on science experiments and earth communications is stressed.
Bozajian, J. M.↗
Evaluation program for secondary spacecraft cells: Initial evaluation tests of General Electric Company 6.0 ampere-hour nickel-cadmium spacecraft cells for the Improved Tiros Operational Satellite (ITOS)
Quality control measures for Ni-Cd spacecraft cells were analyzed. Cells were examined for electrolyte leakage, internal shorts, low capacity, or inability of any cell to recover its open circuit voltage above 1.50 volts during the internal short test. Test results are given in tabular form.
Harkness, J. D.↗
The dynamics and optimal control of spinning spacecraft and movable telescoping appendages, part B: Effect of gravity-gradient torques on the dynamics of a spinning spacecraft with telescoping appendages
The effects of gravity gradient torques during boom deployment maneuvers of a spinning spacecraft are examined. Configurations where the booms extended only along the hub principal axes and where one or two booms are offset from the principal axes were considered. For the special case of symmetric deployment (principal axes booms) the stability boundaries are determined, and a stability chart is used to study the system behavior. Possible cases of instability during this type of maneuver are identified. In the second configuration an expression for gravity torque about the hub center of mass was developed. The nonlinear equations of motion are solved numerically, and the substantial influence of the gravity torque during asymmetric deployment maneuvers is indicated.
Bainum, P. M.↗
Relative toxicity testing of spacecraft materials. 1: Spacecraft materials
In chamber thermodegradation procedures were used to access the lethality to rats of the pyrolysis/combustion products of three foams, an adhesive backed metallic tape and RTV silicone rubber adhesive sealant used in spacecraft construction. The role of carbon monoxide in the overall pyrolysate toxicity was also investigated. Post exposure observation of the rats, histological evaluation of selected organs, carbon monoxide concentration in the chamber atmosphere during exposure and the percent carboxyhemoglobin in the animals expiring in the chamber are discussed. Thermogravimetric analysis and dosage response results are given. The lethal effect of the RTV silicon appears to be due to physical obstruction of the respiratory system by particulate matter from pyrolysis.
Lawrence, W. H.↗
Enhancement of the flexible spacecraft dynamics program for open spacecraft
The modifications and additions made to the Flexible Spacecraft Dynamics (FSD) Program are described. The principal addition to the program was the capability to simulate a single axis gimble platform nadir pointing despin control system. The formulation for the single axis gimble equations of motion is a modification of the formulation. The details of the modifications made to the FSD Program are presented. Modifications to existing subroutines are briefly described and a detailed description of new subroutines is given. In addition, e program variables in new labelled COMMON blocks are described in detail. A description of new input symbols for the FSD Program is given.
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Spacecraft flight simulation: A human factors investigation into the man-machine interface between an astronaut and a spacecraft performing docking maneuvers and other proximity operations
The anticipated increase in rendezvous and docking activities in the various space programs in the Space Station era necessitates a renewed interest in manual docking procedures. Ten test subjects participated in computer simulated docking missions in which the influence of initial velocity was examined. All missions started from a resting position of 304.8 meters (1000 feet) along the space station's +V-bar axis. Test subjects controlled their vehicle with a translational hand controller and digital auto pilot which are both virtually identical to their space shuttle counterparts. While the 0.1 percent rule (range rate is equal to 0.1 percent of the range) used by space shuttle pilots is comfortably safe, it is revealed to be extremely inefficient in terms of time and not justifiable in terms of marginal safety. Time is worth money, not only because of training and launch costs, but because the sooner a pilot and spacecraft return from a mission, the sooner they can begin the next one. Inexperienced test subjects reduced the costs of simulated docking by close to a factor of 2 and achieved safe dockings in less than 4 percent of the time the baseline approach would entail. This reduction in time can be used to save lives in the event of an accident on orbit, and can tremendously reduce docking costs if fuel is produced from waste water on orbit.
Brody, Adam R.↗
A mathematical problem and a Spacecraft Control Laboratory Experiment (SCOLE) used to evaluate control laws for flexible spacecraft. NASA/IEEE design challenge
Discussed here is a NASA program which was initiated to make direct comparisons of control laws for a mathematical problem. An experimental test item is being assembled under the cognizance of the Spacecraft Control Branch at Langley Research Center. The physical apparatus will consist of a softly supported dynamic model of an antenna attached to the Space Shuttle by a flexible beam. The control objective will include the task of directing the line of sight of the Shuttle/antenna configuration toward a fixed target, under conditions of noisy data, limited control authority, and random disturbances.
Taylor, Lawrence W., Jr.↗
The effects of 1 kW class arcjet thruster plumes on spacecraft charging and spacecraft thermal control materials
Arcjet thrusters are soon to be used for north/south stationkeeping on commercial communications satellites. A series of tests was performed to evaluate the possible effects of these thrusters on spacecraft charging and the degradation of thermal control material. During the tests the interaction between arcjet plumes and both charged and uncharged surfaces did not cause any significant material degradation. In addition, firing an arcjet thruster benignly reduced the potential of charged surfaces to near zero.
Bogorad, A.↗
Instrument interface description for NOAA 2000 instruments with European morning spacecraft and/or NOAA-OPQ spacecraft
The purpose is to describe at a high level the common interface provisions and constraints placed on the NOAA-2000 instruments and the interfacing spacecraft elements in the following areas: electrical interface, mechanical interface, thermal interface, magnetic interface, electromagnetic compatibility, structural/mechanical environmental interface, contamination control, and the ionizing radiation environment. The requirements reflect the fact that these instruments must be compatible with a number of different polar orbiting satellite vehicles including the NOAA-OPQ satellites and the EUMETSAT METOP satellites.
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Empirical models for spacecraft damage from orbital debris penetration and effects on spacecraft survivability
Semi-empirical models of hole diameter and tip-to-tip crack length for different multi-wall shielding systems currently under development for the International Space Station are presented. These equations were developed using light gas gun test data at impact velocities of 6.5 km/s and inhibited shaped charge test data for an impact velocity of 11.3 km/s. These models are incorporated into a survivability analysis using the manned spacecraft crew survivability computer code to determine whether or not module unzipping or crew incapacitation would occur under a specific set of impact conditions.
Williamsen, Joel↗
Navigating Mars Observer: Launch Through Encounter and Response to the Spacecraft's Pre-Encounter and Response to the Spacecraft's Pre-Encounter Anomaly
This paper provides an in-depth review of the Mars Observer Navigation Team's activities throughout interplanetary cruise to Mars and our response to the spacecraft's anomaly which occurred approximately 68 hours before encounter.
Navigating Mars Observe↗
EMI from Spacecraft Docking Systems Spacecraft Charging - Plasma Contact Potentials
The plasma contact potential of a visiting vehicle (VV), such as the Orion Service Module (SM), is determined while docking at the Orion Crew Exploration Vehicle (CEV). Due to spacecraft charging effects on-orbit, the potential difference between the CEV and the VV can be large at docking, and an electrostatic discharge (ESD) could occur at capture, which could degrade, disrupt, damage, or destroy sensitive electronic equipment on the CEV and/or VV. Analytical and numerical models of the CEV are simulated to predict the worst-case potential difference between the CEV and the VV when the CEV is unbiased (solar panels unlit: eclipsed in the dark and inactive) or biased (solar panels sunlit: in the light and active).
Norgard, John D.↗
Real-Time Testbed Spacecraft Simulation for the Deep Space One Spacecraft
This paper states the requirements for, describes the overall architecture of, and identifies the future work involved in developing the DS1 Testbed spacecraft simulation.
Deep↗