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  • Geoelektrik
  • Pendel
  • SPACE TRANSPORTATION
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE
  • ddc:300
  • littérature
  • 2015-2019
  • 1980-1984
  • 1975-1979  (537)
  • 1978  (189)
  • 1976  (348)
Collection
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Years
  • 2015-2019
  • 1980-1984
  • 1975-1979  (537)
Year
  • 1
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    Design development of the Apollo command and service module thrust vector attitude control systems (1978)
    In:  CASI
    Details
    Publication Date: 2006-03-02
    Description: Development of the Apollo thrust vector control digital autopilot (TVC DAP) was summarized. This is the control system that provided pitch and yaw attitude control during velocity change maneuvers using the main rocket engine on the Apollo service module. A list of ten primary functional requirements for this control system are presented, each being subordinate to a more general requirement appearing earlier on the list. Development process functions were then identified and the essential information flow paths were explored. This provided some visibility into the particular NASA/contractor interface, as well as relationships between the many individual activities.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 63-82
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  • 2
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    Cryogenic helium 2 systems for space applications (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Two cryogenic systems are described which will provide cooling for experiments to be flown on Spacelab 2 in the early 1980's. The first system cools a scanning infrared telescope by the transfer of cold helium gas from a separate superfluid helium storage dewar. The flexible design permits the helium storage dewar and transfer assembly to be designed independent of the infrared experiment. Where possible, modified commerical apparatus is used. The second cryogenic system utilizes a specially designed superfluid dewar in which a superfluid helium experiment chamber is immersed. Each dewar system employs a porous plug as a phase separator to hold the liquid helium within the dewar and provide cold gas to a vent line. To maintain the low vapor pressure of the superfluid, each system requires nearly continuous prelaunch vacuum pump service, and each will vent to space during the Spacelab 2 flight.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA Spacecraft Thermal and Environ. Control Systems; p 507-515
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  • 3
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    Experimental control requirements for life sciences (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The Life Sciences dedicated Spacelab will enable scientists to test hypotheses in various disciplines. Building upon experience gained in mission simulations, orbital flight test experiments, and the first three Spacelab missions, NASA will be able to progressively develop the engineering and management capabilities necessary for the first Life Sciences Spacelab. Development of experiments for these missions will require implementation of life-support systems not previously flown in space. Plant growth chambers, animal holding facilities, aquatic specimen life-support systems, and centrifuge-mounted specimen holding units are examples of systems currently being designed and fabricated for flight.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA Spacecraft Thermal and Environ. Control Systems; p 467-472
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  • 4
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    Thermal integration of Spacelab experiments (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The method of thermally integrating the experiments for Spacelab is discussed. The scientific payload consists of a combination of European and United States sponsored experiments located in the module as well as on a single Spacelab pallet. The thermal integration must result in accomodating the individual experiment requirements as well as ensuring that the total payload is within the Spacelab Environmental Control System (ECS) resource capability. An integrated thermal/ECS analysis of the module and pallet is performed in concert with the mission timeline to ensure that the agreed upon experiment requirements are accommodated and to ensure the total payload is within the Spacelab ECS resources.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA Spacecraft Thermal and Environ. Control Systems; p 545-559
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  • 5
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    An assessment of thermal design procedures for Shuttle payloads (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: A review of the thermal design options for unmanned Shuttle payloads is presented. Because many future Shuttle payloads will have budgets and less time available for the definition of their thermal subsystems, simplified design procedures will be the most cost-effective. The thermal interface between an individual payload and the Orbiter is discussed. A simplified, modular thermal control system that will reduce the cost of providing thermal protection by minimizing both the initial procurement cost of any specialized hardware and the need for a detailed thermal interface analysis is described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA Spacecraft Thermal and Environ. Control Systems; p 481-486
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  • 6
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    Thermal/environmental control and life support system requirements for future space application (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Thermal/environmental control systems concepts being considered for the power module and manned orbital facilities are described. To assure an economically viable program, the approach being pursued is utilization of existing hardware, where possible, and construction of orbital facilities in modular fashion to meet anticipated growth of space processing, astronomy, life science, solar/terrestrial observation, construction, etc. Configurations include Orbiter tended missions (Orbiter remains attached to orbiting facility) and freeflying manned or unmanned earth-orbiting facilities. Utilization of shuttle hardware, e. g., external tank, or the currently orbiting Skylab vehicle is being considered for orbital facilities. Studies include use of Spacelab hardware with a power module to permit extending on-orbit mission time beyond the capability of the current space transportation system. Power levels of 25 kW are being considered for the power module. Mission duration is not limited due to the modular approach and the concept of utilizing a logistics module to provide consumables' resupply capability to the orbital facility.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA Spacecraft Thermal and Environ. Control Systems; p 575-582
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  • 7
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    Orbiting Astronomical Observatory (OAO-A2) stabilization and control subsystem (1978)
    In:  CASI
    Details
    Publication Date: 2006-03-02
    Description: The OAO was successfully operating for approximately 11 months and has made over 2500 stellar observations. The OAO control system was a complex system which takes the 4500-lb vehicle through initial stabilization to star tracker control where a pointing accuracy of less than 1 arc minute was achieved. To obtain this pointing accuracy, the system used six orthogonally mounted gimbaled star trackers. The trackers were two gimbaled devices, having a 1-deg field of view with a + or - 43 deg gimbal excursion. The tracker could recognize and track 2.0 magnitude stars or brighter. The flight results indicated spacecraft pointing accuracies of less than 1 arc minute after tracker calibration with spacecraft jitter less than 3 arc seconds.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 83-125
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  • 8
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    Shuttle/tethered satellite system (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A tethered satellite system has been conceived as a device to extend the capability of the Space Shuttle to perform scientific/applications investigations and operational activities. The concept envisions a multiple-use tethered system with closed-loop control, capable of supporting a payload or satellite suspended from the Shuttle cargo bay, toward or away from the earth, at distances up to 100 kilometers from the Shuttle. This paper discusses the background and results of early analyses and feasibility studies, and presents a design and operational description of the system. Also presented are a discussion of potential applications of the Tethered Satellite System, and plans for an operational verification flight in 1982.
    Keywords: SPACE TRANSPORTATION
    Type: Journal of the Astronautical Sciences; 26; Jan
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  • 9
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    Space Shuttle (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The function, capabilities, and intended uses of the Space Shuttle are described. Attention is directed to the propulsion system and the construction of some of its components. The assembly and launching of the Shuttle are considered, as is the contribution of the Shuttle to the project which involves flights to the sun.
    Keywords: SPACE TRANSPORTATION
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  • 10
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    Considerations in STS payload environmental verification (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Considerations regarding the Space Transportation System (STS) payload environmental verification are reviewed. It is noted that emphasis is placed on testing at the subassembly level and that the basic objective of structural dynamic payload verification is to ensure reliability in a cost-effective manner. Structural analyses consist of: (1) stress analysis for critical loading conditions, (2) model analysis for launch and orbital configurations, (3) flight loads analysis, (4) test simulation analysis to verify models, (5) kinematic analysis of deployment/retraction sequences, and (6) structural-thermal-optical program analysis. In addition to these approaches, payload verification programs are being developed in the thermal-vacuum area. These include the exposure to extreme temperatures, temperature cycling, thermal-balance testing and thermal-vacuum testing.
    Keywords: SPACE TRANSPORTATION
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  • 11
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    Environmental effects of the Space Shuttle (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Rocket exhaust products, acoustic noise, and a sonic boom are produced during launch of the Space Shuttle. Their environmental effects have been assessed and found to be small and transient, or controllable by the choice of launch azimuth or launch conditions. Reentry of the Orbiter will produce a very low-level sonic boom over populated areas.
    Keywords: SPACE TRANSPORTATION
    Type: Journal of Environmental Sciences; 21; Mar
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  • 12
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    Some results from 1/8-scale Shuttle model vibration studies (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Highlights of experimental and analytical vibration studies of a 1/8-scale structural dynamic model of the Space Shuttle are presented. The Space Shuttle is a launch vehicle with elements assembled in an asymmetric manner. Responses of the assembled vehicle are characterized by directional coupling and high modal density at low frequencies. Effects of distortion of structure near element interfaces are shown to be significant and predictable with highly detailed mathematical models. Acquisition of modal data by single-point random excitation is shown to be viable for these complex structures. Element studies reveal large liquid-structure interactions and a wide range of structural damping.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 13
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    Space Shuttle payloads and data handling accommodations (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The Space Transportation System, which includes the Space Shuttle, will reduce the costs of earth orbital operations while improving operational capabilities and flexibility. The Shuttle can deliver payloads up to 65,000 pounds to a 150-nmi circular orbit at a substantially lower operational cost per flight than the Titan III-C system, which has a payload delivery capability of only 30,000 pounds. In addition, the Space Shuttle can return to earth with up to 32,000 pounds of payload, a capability not provided by expendable launch vehicles. Typical payload missions are considered along with aspects of satellite placement and recovery, typical free-flying payloads, attached scientific payloads, and the typical nature of payload data.
    Keywords: SPACE TRANSPORTATION
    Type: IEEE Transactions on Communications; COM-26; Nov. 197
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  • 14
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    Space Shuttle Program description and status (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The main reason for the development of the Space Shuttle is related to the aim to achieve a major reduction in the cost of placing a payload into space. Such a reduction is to be obtained by using a reusable in place of an expendable launch vehicle. Developments concerning launch vehicles show a steady reduction in launching expenses. From a cost of about $500,000 a pound in the late 1950's, launching expenses were reduced to $600 a pound for payloads on the Saturn V. With the Space Shuttle the cost will drop to approximately $150 a pound. The Space Shuttle Program is discussed, taking into account a system description, a typical mission profile, aspects of mission design, launch costs, and Space Shuttle characteristics. The Space Shuttle Program status is also examined, giving attention to orbital flight schedules, flight hardware tests, launch area facilities, the mission control center, and details of flight crew training.
    Keywords: SPACE TRANSPORTATION
    Type: IEEE Transactions on Communications; COM-26; Nov. 197
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  • 15
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    Cryogenic cooling for spacecraft sensors, instruments, and experiments (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Several disciplines requiring in-space cryogenic cooling are identified including high-energy, gamma-ray, and IR astronomy, relativity missions, and superconducting devices. Radiant coolers are limited in terms of temperature ranges and cooling loads. Other spacecraft cryogenic systems include stored solid cryogenic coolers using materials such as hydrogen, neon, argon, and methane. Two such cooler designs are described including one for the Nimbus F limb radiance inversion radiometer and one for the Nimbus G limb infrared monitoring of the atmosphere. Suggestions for increasing the performance of solid cryogenic coolers are made, such as a multimission cooler, a mechanical refrigerator, Stirling-cycle refrigerators, and Vuilleumier mechanized coolers. Techniques for obtaining cryogenic cooling in the milli-K range are identified as dilution refrigeration and adiabatic demagnetization.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 16; Nov. 197
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  • 16
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    Insulator edge voltage gradient effects in spacecraft charging phenomena (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Insulating surfaces on geosynchronous satellites have been charged by geomagnetic substorms to a point where discharges occur. The electromagnetic pulses from these discharges couple into satellite electronic systems disrupting operations. Laboratory tests conducted on insulator charging have indicated that discharges appear to be initiated at insulator edges where voltage gradients can exist. An experimental investigation has been conducted to measure edge voltage gradients on silvered Teflon samples as they are charged by monoenergetic electron beams. It has been found that the surface voltage at insulator edges can be approximated by an exponential expression based on an electron current density balance. Using this expression at known breakdown conditions results in a discharge voltage gradient down the insulator edge to ground of about 150,000 V/cm.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 17
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    Practical design of low-cost large space structures (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The practical design of low-cost space structures involves the use of approaches that reduce the cost of the design and development effort itself. Such approaches include: (1) design with criteria arrived at rationally; (2) design for simplicity, repeatability, and modularity; (3) assembly without adjustments; (4) design for testability on the ground; (5) the attainment of structural efficiency by configuration and material choice rather than by squeezing down on the design margins; and (6) prefabrication and preassembly before launch. Attention is given to truss platform designs, and the Seasat Extendible Support Structure is discussed as a particular example.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 16; Oct. 197
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  • 18
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    Space shuttle main engine plume radiation model (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The methods are described which are used in predicting the thermal radiation received by space shuttles, from the plumes of the main engines. Radiation to representative surface locations were predicted using the NASA gaseous plume radiation GASRAD program. The plume model is used with the radiative view factor (RAVFAC) program to predict sea level radiation at specified body points. The GASRAD program is described along with the predictions. The RAVFAC model is also discussed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-161498 , RTR-014-7
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  • 19
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    Infrared Imagery of Shuttle (IRIS). Task 2 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An opto-electronic breadboard of 10 channels of the IR temperature measuring system was produced as well as a scaled up portion of the tracking system reticle in order to verify Task 1 assumptions. The breadboards and the tests performed on them are described and both raw and reduced data are presented. Tests show that the electronics portion of the imaging system will provide a dc to 10,000 Hz bandwidth that is flat and contributes no more than 0.4% of full-scale uncertainty to the measurement. Conventional packaging is adequate for the transresistance amplifier design. Measurement errors expected from all sources tested are discussed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-152123-TASK-2-FINAL , MCR-76-564-TASK-2-FINAL
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  • 20
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    Infrared Imagery of Shuttle (IRIS). Task 2, summary report (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: End-to-end tests of a 16 element indium antimonide sensor array and 10 channels of associated electronic signal processing were completed. Quantitative data were gathered on system responsivity, frequency response, noise, stray capacitance effects, and sensor paralleling. These tests verify that the temperature accuracies, predicted in the Task 1 study, can be obtained with a very carefully designed electro-optical flight system. Pre-flight and inflight calibration of a high quality are mandatory to obtain these accuracies. Also, optical crosstalk in the array-dewar assembly must be carefully eliminated by its design. Tests of the scaled up tracking system reticle also demonstrate that the predicted tracking system accuracies can be met in the flight system. In addition, improvements in the reticle pattern and electronics are possible, which will reduce the complexity of the flight system and increase tracking accuracy.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-152123-TASK-2-SUMM , MCR-76-564-TASK-2-SUMM
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  • 21
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    Three-dimensional radiative exchange factors for nongray, nondiffuse surfaces (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A computer program using a variation of the Monte Carlo method was developed to predict radiative exchange factors in three-dimensional configurations with curved surfaces. The model allows for arbitrary emission, absorption, and reflection characteristics and for radiation exchange between surfaces as well as external irradiation through openings. It was shown that exchange factors can be determined efficiently by using the normal Monte Carlo method for closed configurations and/or high surface emissivities, while energy partitioning is vastly superior in the case of open configurations and/or low surface emissivities. Comparison with some experiments performed on the Space Shuttle heat rejection system demonstrates the model's accuracy as well as its superiority over a simplified diffuse-surface analysis, which requires similar amounts of computer time.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Numerical Heat Transfer; 1; July-Sep
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  • 22
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    The decrease in effective photocurrents due to saddle points in electrostatic potentials near differentially charged spacecraft (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The reported investigation had the objective to illustrate the presence of important multidimensional effects in spacecraft charging. Two-dimensional codes have been under development by Parker (1976). A description is presented of a calculation which was performed using the three-dimensional NASA Charging Analyzer Program (NASCAP). NASCAP was run to calculate the electrostatic potentials on the surface of, and in the space surrounding, a sunlit Teflon-coated sphere. Currents to the sunlit surfaces were determined on the basis of an approximate photosheath model for strong differential charging.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 23
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    STS payload data collection and accommodations analysis study. Volume 3: Accommodations analysis (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Payload requirements were compared to launch site accommodations and flight accommodations for a number of Spacelab payloads. Experiment computer operating system accommodations were also considered. A summary of accommodations in terms of resources available for payload discretionary use and recommendations for Spacelab/STS accommodation improvements are presented.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-150817 , ES78-MSFC-2241-VOL-3
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  • 24
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    An Induced Environment Contamination Monitor for the Space Shuttle (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Induced Environment Contamination Monitor (IECM), a set of ten instruments integrated into a self-contained unit and scheduled to fly on shuttle Orbital Flight Tests 1 through 6 and on Spacelabs 1 and 2, is described. The IECM is designed to measure the actual environment to determine whether the strict controls placed on the shuttle system have solved the contamination problem. Measurements are taken during prelaunch, ascent, on-orbit, descent, and postlanding. The on-orbit measurements are molecular return flux, background spectral intensity, molecular deposition, and optical surface effects. During the other mission phases dew point, humidity, aerosol content, and trace gas are measured as well as optical surface effects and molecular deposition. The IECM systems and thermal design are discussed. Preflight and ground operations are presented together with associated ground support equipment. Flight operations and data reduction plans are given.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-78193
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  • 25
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    Quick look test report: MPT static firing no. 2 test MPT-S2 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The three engine cluster was fired at 70 percent power level for a nominal 15 seconds to evaluate the integrated performance of the main propulsion system. Engine ignition occurred at approximately 1403 with the planned mainstage duration achieved for all three engines. Operation of all systems was as expected with the exception of the recirculation pumps. The pumps were started while the propellant loading was in fast fill, but they cavitated and lost head at the termination of fast fill. The pumps were subsequently restarted after pressurizing the tank and draining back propellant to get good quality. Post test inspection of the engines revealed some discoloration on the inside of the thrust chamber and distorted drain lines for engine #2.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151814 , SD-78-SH-0125
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  • 26
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    Technology requirements for advanced earth orbital transportation system. Volume 1: Executive summary (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Normal technology requirements applicable to Single Stage to Orbit (SSTO) systems were projected to the 1985 time period. These technology projections were then incorporated in a vehicle design analysis of three different operational concepts resulting in four configurations of a Single Stage to Orbit system. The resultant performance, weights and costs of each concept were then compared and a system concept selected. A figure of merit was developed for advanced technology programs based on a cost/performance basis. The selected advanced technology programs were then used to reassess the vehicle to determine the impact on performance, weight and cost. Based on study results, recommendations are provided in technology areas associated with earth orbit transportation systems. The recommendations address advanced space transportation system design considerations, both hardware and software technolgoy program requirements.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-2878 , D180-19168-3-VOL-1
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  • 27
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    Space Shuttle astrodynamical constants (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Basic space shuttle astrodynamic constants are reported for use in mission planning and construction of ground and onboard software input loads. The data included here are provided to facilitate the use of consistent numerical values throughout the project.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-79516 , JSC-14262 , REPT-78-FM-32 , MSC-02446
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  • 28
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    A highly accurate method for the determination of mass and center of mass of a spacecraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An extremely accurate method for the measurement of mass and the lateral center of mass of a spacecraft has been developed. The method was needed for the Voyager spacecraft mission requirement which limited the uncertainty in the knowledge of lateral center of mass of the spacecraft system weighing 750 kg to be less than 1.0 mm (0.04 in.). The method consists of using three load cells symmetrically located at 120 deg apart on a turntable with respect to the vertical axis of the spacecraft and making six measurements for each load cell. These six measurements are taken by cyclic rotations of the load cell turntable and of the spacecraft, about the vertical axis of the measurement fixture. This method eliminates all alignment, leveling, and load cell calibration errors for the lateral center of mass determination, and permits a statistical best fit of the measurement data. An associated data reduction computer program called MASCM has been written to implement this method and has been used for the Voyager spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-156130 , JPL-PUB-78-2
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  • 29
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    Vibration effects of the space shuttle main engine high pressure oxidizer turbopump bellows (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A welded metal bellows was subjected to a series of vibration tests in a 400 psi oxygen environment to evaluate the effects of the bellows convolutes rubbing on the damper ring in the high pressure oxidizer turbopump of the space shuttle main engine. The bellows was subjected to approximately 2 million cycles at 0.007 in. double amplitude displacement during this series of tests, at a frequency of 400 Hz. Intrumentation of the test specimen revealed no significant heat buildup caused by the rubbing of the bellows convolutes on the damper ring. A final destruct test was made to determine if a fire would result if the bellows ruptured in the 400 psi oxygen environment, thus exposing a fresh metal surface. The vibration input was changed to 0.8 in. double amplitude displacement at 20 Hz to intentionally rupture the bellows. Failure occurred after 2.5 sec; no fire or heat buildup was encountered.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-78157
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  • 30
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    Space Shuttle Orbiter Approach and Landing Test: Final Evaluation Report (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Approach and Landing Test Program consisted of a series of steps leading to the demonstration of the capability of the Space Shuttle orbiter to safely approach and land under conditions similar to those planned for the final phases of an orbital flight. The tests were conducted with the orbiter mounted on top of a specially modified carrier aircraft. The first step provided airworthiness and performance verification of the carrier aircraft after modification. The second step consisted of three taxi tests and five flight tests with an inert unmanned orbiter. The third step consisted of three mated tests with an active manned orbiter. The fourth step consisted of five flights in which the orbiter was separated from the carrier aircraft. For the final two flights, the orbiter tail cone was replaced by dummy engines to simulate the actual orbital configuration. Landing gear braking and steering tests were accomplished during rollouts following the free flight landings. Ferry testing was integrated into the Approach and Landing Test Program to the extent possible. In addition, four ferry test flights were conducted with the orbiter mated to the carrier aircraft in the ferry configuration after the free-flight tests were completed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-79404 , JSC-13864
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    Mission feasibility study of a very long baseline interferometer utilizing the space shuttle (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An introductory overview of very long baseline interferometry (VLBI) as it exists and is used today is given and the scientific advances that have been achieved with this technique in the past decade are described. The report briefly reviews developments now in progress that will improve ground station VLBI in the next few years, and the limitations that still will exist. The advantages and the scientific return on investment that may be expected from a VLBI terminal in space are described. Practical problems that have to be faced range from system design through hardware implementation, to data recovery and analysis.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-155938
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  • 32
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    Space power systems technology enablement study (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The power system technologies which enable or enhance future space missions requiring a few kilowatts or less and using the space shuttle were assessed. The advances in space power systems necessary for supporting the capabilities of the space transportation system were systematically determined and benefit/cost/risk analyses were used to identify high payoff technologies and technological priorities. The missions that are enhanced by each development are discussed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-155804 , JPL-PUB-78-7
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  • 33
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    Representative shuttle evaporative heat sink (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design, fabrication, and testing of a representative shuttle evaporative heat sink (RSEHS) system which vaporizes an expendable fluid to provide cooling for the shuttle heat transport fluid loop is reported. The optimized RSEHS minimum weight design meets or exceeds the shuttle flash evaporator system requirements. A cold trap which cryo-pumps flash evaporator exhaust water from the CSD vacuum chamber test facility to prevent water contamination of the chamber pumping equipment is also described.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151599 , T157-77
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  • 34
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    Integrated guidance, navigation and control verification plan primary flight system (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The verification process and requirements for the ascent guidance interfaces and the ascent integrated guidance, navigation and control system for the space shuttle orbiter are defined as well as portions of supporting systems which directly interface with the system. The ascent phase of verification covers the normal and ATO ascent through the final OMS-2 circularization burn (all of OPS-1), the AOA ascent through the OMS-1 burn, and the RTLS ascent through ET separation (all of MM 601). In addition, OPS translation verification is defined. Verification trees and roadmaps are given.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151815 , SD-78-SH-0141
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  • 35
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    Space shuttle orbiter reaction control system interactions with the vehicle flow field (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Test data on the effect of the interaction between the space shuttle orbiter rear-mounted reaction control system jets and the flow over the vehicle in the atmosphere are analyzed with particular attention to yaw angle effects. Masted tank-plus-orbiter jet interactions resulting from combinations of forward and rear-mounted reaction control jets being fired prior to external tank staging are also documented. The primary correlating parameter used for the mated data is a single-jet momentum ratioed to free-stream momentum. An analytic model for computing reaction control system interactions for all control combinations used for mated vehicle coast is included.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151807 , CASD-NAS-78-007
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  • 36
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    Experimental investigation of contamination prevention techniques to cryogenic surfaces on board orbiting spacecraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Within the simulation limitations of on-orbit conditions, it was demonstrated that a helium purge system could be an effective method for reducing the incoming flux of contaminant species. Although a generalized purge system was employed in conjunction with basic telescope components, the simulation provided data that could be used for further modeling and design of a specific helium injection system. Experimental telescope pressures required for 90% attenuation appeared to be slightly higher (factor of 2 to 5). Cooling the helium purge gas and telescope components from 300 to 140 K had no measurable effect on stopping efficiency of a given mass flow of helium from the diffuse injector.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-152171 , MCR-78-578
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  • 37
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    Shuttle environmental and thermal control/life support system computer program (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Users guide describes the computer programs developed to aid in the analysis of RSECS (Representative Shuttle Environmental Control System) related material. These programs were prepared to provide pretest predictions, pst test analysis, and real time problem analysis for RSECS related testing planning and evaluation. The programs was designed for use on a Wang 2200 series computer system.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151661
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  • 38
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    IUS prerelease alignment (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Space shuttle orbiter/IUS alignment transfer was evaluated. Although the orbiter alignment accuracy was originally believed to be the major contributor to the overall alignment transfer error, it was shown that orbiter alignment accuracy is not a factor affecting IUS alignment accuracy, if certain procedures are followed. Results are reported of alignment transfer accuracy analysis.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-79349 , JSC-78-FM-3 , JSC-13838
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  • 39
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    An introduction to shuttle/LDEF retrieval operations: The R-bar approach option (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Simulated orbiter direct approaches during long duration exposure facility (LDEF) retrieval operations reveal that the resultant orbiter jet plume fields can significantly disturb LDEF. An alternate approach technique which utilizes orbital mechanics forces in lieu of jets to brake the final orbiter/LDEF relative motion during the final approach, is described. Topics discussed include: rendezvous operations from the terminal phase initiation burn through braking at some standoff distance from LDEF, pilot and copilot activities, the cockpit instrumentation employed, and a convenient coordinate frame for studying the relative motion between two orbiting bodies. The basic equations of motion for operating on the LDEF radius vector are introduced. Practical considerations of implementing an R-bar approach, namely, orbiter/LDEF relative state uncertainties and orbiter control system limitations are explored. A possible R-bar approach strategy is developed and demonstrated.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-78668
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  • 40
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    Nitric oxide production in the stratosphere within the Space Shuttle's solid rocket motor plumes (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This study focuses on establishing the sensitivity of predictions of NO production to uncertainties in altitude, reaction rate coefficients, turbulent mixing rates, and Mach disk size and location. The results show that relatively large variations in parameters related to these phenomena had surprisingly little effect on predicted NO production.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TP-1305 , L-12182
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  • 41
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    STS payload data collection and accommodations analysis study. Volume 2: Payload data collection (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A format developed for Space Transportation System payload data collection and a process for collecting the data are described along with payload volumes and a data deck to be used as input for the Marshall Interactive Planning System. Summary matrices of the data generated are included.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-150816 , ES78-MSFC-2241-VOL-2
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  • 42
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    Aerodynamic roll characteristics of a 0.00548 scale 146-inch solid rocket booster reentry configuration (MSFC Model Number 486) over a portion of the reentry flight regime in the NASA MSF 14-inch trisonic wind tunnel (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted in the MSFC 14 inch TWT to study the roll characteristics of a 0.00548 scale model of the 146 inch shuttle solid rocket booster to obtain more accurate rolling moment data on the solid rocket booster. A sensitive single component roll balance was utilized. Data were obtained for a single nose mounted sting. The angle of attack range consisted of angles from 150 deg to 190 deg; roll angles consisted of angles from 0 deg to 337 1/2 deg in increments of 22 1/2 deg; and Mach numbers were 1.46, 1.96, 2.74 and 2.48.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-78195
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  • 43
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    Viking dynamics experience with application to future payload design (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analytical and test techniques are discussed. Areas in which hindsight indicated erroneous, redundant, or unnecessarily severe design and test specifications are identified. Recommendations are made for improvements in the dynamic design and criteria philosophy, aimed at reducing costs for payloads.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-3014 , MCR-77-144
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  • 44
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    Space shuttle separation mechanisms (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The development of space shuttle separation devices is reviewed to illustrate the mechanisms involved in separating the Orbiter from the Boeing 747 carrier aircraft and from the externally mounted propellant tank. Other aspects of the separation device development discussed include design evolution, operational experience during the orbiter approach and landing tests, and the work required to produce an operational system.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-58210
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  • 45
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    STS payload data collection and accommodations analysis study. Volume 1: Executive summary (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The requirements of investigations/instruments and integrated missions to be flown on the Space Transportation System (STS) and the accommodations/resources on the STS actually available for use by these investigations and missions are identified. Deficiencies, areas of concern, and needed improvements in the STS are considered in terms of requirements versus accommodations. A data base developed for investigations/instruments considered in mission planning activities for OSTA is described.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-150815 , ES78-MSFC-2241-VOL-1
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  • 46
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    Space shuttle orbiter trimmed center-of-gravity extension study. Volume 6: System design studies (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: System studies were made to determine the required changes in shuttle orbiter mass for various changes in aerodynamic shape. These changes are designed to extend the current shuttle orbiter trimmed c.g. envelope to accommodate a greater range of payloads. One of the apparently most viable changes for the amount of c.g. extension obtained involves the removal of the present wing/body fillet and the replacement of this structural element with a forward located fixed canard.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-72661-VOL-6
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  • 47
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    SRB Materials and Processes Assessment from Laboratory and Ocean Environmental Tests (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Materials and Processes Laboratory evaluation of Solid Rocket Boosters (SRB) and Solid Rocket Motors (SRM) candidate material, both in-house and with ocean exposure tests at Panama City and Kennedy Space Center (KSC), Florida is presented. Early sample tests showed excellent seawater corrosion resistance for inconel 718 and titanium 6A1-4V alloys. Considerable corrosion and biofouling occurred with bare 2219-T87 aluminum. Subsequent tests conclusively demonstrated that epoxy coatings prevented corrosion of 2219-T87 aluminum as long as the coatings stays intact. The results and assessment of the series of ocean environmental tests that were conducted are also presented.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-78187
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  • 48
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    Extravehicular activity translation arm (EVATA) study (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The preliminary design of a deployable Extravehicular Activity Translation Arm (EVATA) assembly which will allow an EVA crewman to perform tasks in the vicinity of the External TNK (ET) umbilical doors and to inspect most of the underside of the shuttle spacecraft is reported. The concept chosen for the boom structure was the Astro Extendable Support Structure (ESS) which formed the main structure for the Synthetic Aperture Radar (SAR) Antenna System on the SEASAT A spacecraft. This structure is a deployable triangular truss. A comparison of the EVATA and the SEASAT A ESS is shown. The development of status of the ESS is shown. The satellite configuration, the stowed truss load path, and the envelope deployment sequence for the ESS are also shown.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-151755 , ARC-TN-1064
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  • 49
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    The 1980-90 shuttle star catalog for onboard and ground programs (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The 1980-90 shuttle star catalog for onboard and ground programs is presented. The data used in this catalog are explained according to derivation, input, format for the catalog, and preparation. The tables include the computer program listing, input star position, and the computed star positions for the years 1980-90.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-79514 , JSC-14292 , REPT-78-FM-38
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  • 50
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    Space shuttle orbiter avionics software: Post review report for the entry FACI (First Article Configuration Inspection) (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Status of the computer programs dealing with space shuttle orbiter avionics is reported. Specific topics covered include: delivery status; SSW software; SM software; DL software; GNC software; level 3/4 testing; level 5 testing; performance analysis, SDL readiness for entry first article configuration inspection; and verification assessment.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151742 , IBM-78SS-3937
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  • 51
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    Technology requirements for advanced earth orbital transportation systems. Volume 3: Summary report - dual mode propulsion (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The impact of dual-mode propulsion on cost-effective technology requirements for advanced earth-orbital transportation systems is considered. Additional objectives were to determine the advantages of the best dual mode concept relative to the LO2/LH2 concept of the basic study. Normal technology requirements applicable to horizontal take-off and landing single-stage-to-orbit systems utilizing dual mode rocket propulsion were projected to the 1985 time period. These technology projections were then incorporated in a vehicle parametric design analysis for two different operational concepts of a dual mode propulsion system. The resultant performance, weights and costs of each concept were compared. The selected propulsion concept was evaluated to confirm the parametric trending/scaling of weights and to optimize the configuration.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-3037 , D180-19168-5
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  • 52
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    Shuttle Ku-band signal design study (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Carrier synchronization and data demodulation of Unbalanced Quadriphase Shift Keyed (UQPSK) Shuttle communications' signals by optimum and suboptimum methods are discussed. The problem of analyzing carrier reconstruction techniques for unbalanced QPSK signal formats is addressed. An evaluation of the demodulation approach of the Ku-Band Shuttle return link for UQPSK when the I-Q channel power ratio is large is carried out. The effects that Shuttle rocket motor plumes have on the RF communications are determined also. The effect of data asymmetry on bit error probability is discussed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151743 , TR-7805-0476
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  • 53
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    A digital computer program for the dynamic interaction simulation of controls and structure (DISCOS), volume 2 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N78-25123.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1219-VOL-2 , G-7702-F26-VOL-2
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  • 54
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    A digital computer program for the dynamic interaction simulation of controls and structure (DISCOS), volume 1 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical development and associated digital computer program system for the dynamic simulation and stability analysis of passive and actively controlled spacecraft are presented. The dynamic system (spacecraft) is modeled as an assembly of rigid and/or flexible bodies not necessarily in a topological tree configuration. The computer program system is used to investigate total system dynamic characteristics, including interaction effects between rigid and/or flexible bodies, control systems, and a wide range of environmental loadings. In addition, the program system is used for designing attitude control systems and for evaluating total dynamic system performance, including time domain response and frequency domain stability analyses.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1219-VOL-1 , G-7702-F26-VOL-1
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  • 55
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    Primary reaction control system/remote manipulator system interaction with loaded arm. Space shuttle engineering and operations support (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study of the interaction between the orbiter primary reaction control system (PRCS) and the remote manipulator system (RMS) with a loaded arm is documented. This analysis was performed with the Payload Deployment and Retrieval Systems Simulation (PDRSS) program with the passive arm bending option. The passive-arm model simulates the arm as massless elastic links with locked joints. The study was divided into two parts. The first part was the evaluation of the response of the arm to step inputs (i.e. constant jet torques) about each of the orbiter body axes. The second part of the study was the evaluation of the response of the arm to minimum impulse primary RCS jet firings with both single pulse and pulse train inputs.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151721 , WORKING-PAPER-1.4-7-229
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  • 56
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    Orbiter/payload proximity operations SES Postsim report. Lateral approach and other techniques (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Various approach and stationkeeping simulations (proximity operations) were conducted in the Shuttle engineering simulator (SES). This simulator is the first to dynamically include the Orbiter reaction control system (RCS) plume effects on a payload being recovered after rendezvous operations. A procedure for braking, using the simultaneous firing of both jets, was evaluated and found very useful for proximity operations. However this procedure is very inefficient in the RCS usage and requires modifications to the digital autopilot (DAP) software. A new final approach, the lateral approach technique (LAT), or the momentum vector proximity approach, was also evaluated in the simulations. The LAT, which included a tailfirst approach for braking, was evaluated successfully with both inertial and gravity stabilized payloads.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-79450 , JSC-13913 , REPT-78-FM-16
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  • 57
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    The dynamics and control of large flexible space structures. Part B: Development of continuum model and computer simulation (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The equations of motion of an arbitrary flexible body in orbit were derived. The model includes the effects of gravity with all its higher harmonics. As a specific example, the motion of a long, slender, uniform beam in circular orbit was modelled. The example considers both the inplane and three dimensional motion of the beam in orbit. In the case of planar motion with only flexible vibrations, the pitch motion is not influenced by the elastic motion of the beam. For large values of the square of the ratio of the structural modal frequency to the orbital angular rate the elastic motion was decoupled from the pitch motion. However, for small values of the ratio and small amplitude pitch motion, the elastic motion was governed by a Hill's 3 term equation. Numerical simulation of the equation indicates the possibilities of instability for very low values of the square of the ratio of the modal frequency to the orbit angular rate. Also numerical simulations of the first order nonlinear equations of motion for a long flexible beam in orbit were performed. The effect of varying the initial conditions and the number of modes was demonstrated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-156976
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  • 58
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    The dynamics and control of large flexible space structures. Part A: Discrete model and modal control (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Attitude control techniques for the pointing and stabilization of very large, inherently flexible spacecraft systems were investigated. The attitude dynamics and control of a long, homogeneous flexible beam whose center of mass is assumed to follow a circular orbit was analyzed. First order effects of gravity gradient were included. A mathematical model which describes the system rotations and deflections within the orbital plane was developed by treating the beam as a number of discretized mass particles connected by massless, elastic structural elements. The uncontrolled dynamics of the system are simulated and, in addition, the effects of the control devices were considered. The concept of distributed modal control, which provides a means for controlling a system mode independently of all other modes, was examined. The effect of varying the number of modes in the model as well as the number and location of the control devices were also considered.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-156975
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  • 59
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    Space Shuttle Orbiter trimmed center-of-gravity extension study. Volume 4: Effects of configuration modifications on the aerodynamic characteristics of the 139B orbiter at Mach 20.3 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Force tests were conducted at Mach 20.3 to determine the effect of several forebody, wing-fillet, and canard modifications on the hypersonic trim capability of a 139B Space Shuttle Orbiter model. Force and moment data were obtained at angles of attack of 10 deg to 54 deg at zero sideslip angle and at a Reynolds number of 1,900,000 based on body length. The results indicated that wing-fillet and canard modifications would increase the allowable forward trimmed center-of-gravity capability by as much as 3.0 percent of the body length.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-X-72661
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  • 60
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    Preliminary design of an Orbiter/IUS separation sequence (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An orbiter/IUS separation sequence to satisfy the assumed requirements of Shuttle Flight 8 was defined for the purpose of gaining an insight into the flight design software requirements. The key to economical and effective flight design for orbiter/IUS proximity operations is considered to be the capability for rapid and accurate generation of graphical displays that will facilitate not only decision making on the part of the designer, but also lucid documentation of rationale and the resulting design features. The data indicate that (1) an OMS burn is required to attain the necessary velocity without subjecting the IUS and its payload to undue plume impingement, and (2) a departure trajectory that places the orbiter above and behind the IUS at SRM ignition time is preferred over the alternative which would place it below and ahead.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151696 , TRW-28415-H006-RO-00
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  • 61
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    Mission Control Center (MCC) system specification for the shuttle Orbital Flight Test (OFT) timeframe (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Mission Control Center Shuttle (MCC) Shuttle Orbital Flight Test (OFT) Data System (OFTDS) provides facilities for flight control and data systems personnel to monitor and control the Shuttle flights from launch (tower clear) to rollout (wheels stopped on runway). It also supports the preparation for flight (flight planning, flight controller and crew training, and integrated vehicle and network testing activities). The MCC Shuttle OFTDS is described in detail. Three major support systems of the OFTDS and the data types and sources of data entering or exiting the MCC were illustrated. These systems are the communication interface system, the data computation complex, and the display and control system.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151687 , JSC-10013B
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    Static and dynamic stability analysis of the space shuttle vehicle-orbiter (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The longitudinal static and dynamic stability of a Space Shuttle Vehicle-Orbiter (SSV Orbiter) model is analyzed using the FLEXSTAB computer program. Nonlinear effects are accounted for by application of a correction technique in the FLEXSTAB system; the technique incorporates experimental force and pressure data into the linear aerodynamic theory. A flexible Orbiter model is treated in the static stability analysis for the flight conditions of Mach number 0.9 for rectilinear flight (1 g) and for a pull-up maneuver (2.5 g) at an altitude of 15.24 km. Static stability parameters and structural deformations of the Orbiter are calculated at trim conditions for the dynamic stability analysis, and the characteristics of damping in pitch are investigated for a Mach number range of 0.3 to 1.2. The calculated results for both the static and dynamic stabilities are compared with the available experimental data.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TP-1179 , A-7217
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    Manned remote work station development article (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The two prime objectives of the Manned Remote Work Station (MRWS) Development Article Study are to first, evaluate the MRWS flight article roles and associated design concepts for fundamental requirements and embody key technology developments into a simulation program; and to provide detail manufacturing drawings and schedules for a simulator development test article. An approach is outlined which establishes flight article requirements based on past studies of Solar Power Satellite, orbital construction support equipments, construction bases and near term shuttle operations. Simulation objectives are established for those technology issues that can best be addressed on a simulator. Concepts for full-scale and sub-scale simulators are then studied to establish an overall approach to studying MRWS requirements. Emphasis then shifts to design and specification of a full-scale development test article.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151870 , NSS-MR-RP-006
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  • 64
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    Formulation of consumables management models, executive summary (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Future manned space programs that have increased launch frequencies and reusable systems require an implementation of new consumables and systems management techniques that relieve both the operations support personnel and flight crew activities. Analytical models and techniques were developed which consist of a Mission Planning Processor (MPP) with appropriate consumables data base, methods of recognizing potential constraint violations in both the planning and flight operations functions, and flight data files for storage/retrieval of information over extended periods interfacing with flight operations processors for monitoring of the actual flights. Consumables subsystems considered in the MPP were electrical power, environmental control and life support, propulsion, hydraulics and auxiliary power.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-160099 , TRW-26821-H023-RO-00
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  • 65
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    Formulation of consumables management models. Volume 2: Mission planning processor user guide (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A user guide for the MPP (Mission Planning Processor) is presented. The MPP is used in the evaluation of particular missions, with appropriate display and storage of related consumables data. Design goals are accomplished by the use of an on-line/demand mode computer terminal Cathode Ray Tube Display. The process is such that the user merely adds specific mission/flight functions to a skeleton flight and/or alters the skeleton. The skeleton flight includes operational aspects from prelaunch through ground support equipment connect after rollout as required to place the STS (Space Transportation System) in a parking orbit, maintain the spacecraft and crew for the stated on-orbit period and return.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-160097 , TRW-26821-H024-RO-00-VOL-2
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  • 66
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    Shuttle GPS R/PA evaluation analysis and performance tradeoff study (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Primary responsibility was understanding and analyzing the various GPS receiver functions as they relate to the shuttle environment. These receiver functions included acquisition properties of the sequential detector, acquisition and tracking properties of the various receiver phase locked loops, and the techniques of sequential receiver operation. In addition to these areas, support was provided in the areas of oscillator stability requirements, antenna management, and navigation filter requirements, including preposition aiding.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151854 , TR-0978-0278
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  • 67
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    Engineering description of the OMS/RCS/DAP modes used in the HP-9825A High Fidelity Relative Motion Program (HFRMP) (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Simplified mathematical models are reported for the space shuttle's Orbital Maneuvering System (OMS), Reaction Control System (RCS), and on-orbit Digital Autopilot (DAP) that have been incorporated in the High-Fidelity Relative Motion Program (HFRMP) for the HP-9825A desk-top calculator. Comparisons were made between data generated by the HFRMP and by the Space Shuttle Functional Simulator (SSFS), which models the cited shuttle systems in much greater detail. These data include propellant requirements for representative translational maneuvers, rotational maneuvers, and attitude maintenance options. Also included are data relating to on-orbit trajectory deviations induced by RCS translational cross coupling. Potential close-range stationkeeping problems that are suggested by HFRMP simulations of 80 millisecond (as opposed to 40 millisecond) DAP cycle effects are described. The principal function of the HFRMP is to serve as a flight design tool in the area of proximity operations.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151855 , TRW-28415-H009-RO-00
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    Assessment of SEPS solar array technology for orbital service module application (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Work performed in the following assessment areas on the SEPS solar array is reported: (1) requirements definition, (2) electrical design evaluation, (3) mechanical design evaluation, and (4) design modification analysis. General overall assessment conclusions are summarized. There are no known serious design limitations involved in the implementation of the recommended design modifications. A section of orbiter and array engineering drawings is included.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151859 , LMSC-D665410
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  • 69
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    Results of a low speed approach and landing experimental investigation of a 0.050-scale space shuttle orbiter model (39-0) in the NASA/Ames Research Center's 12-foot pressure wind tunnel (OA101), volume 5 (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-151760 , DMS-DR-2405-VOL-5
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  • 70
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    Preliminary analysis of a flexible instrument mount for large instruments on the Space Shuttle (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A flexible instrument mount for large instruments on the space shuttle is analyzed. Concepts for pointing instruments while in orbit, with weights up to 2000 Kg and dimensions of 2 to 3 m were identified and analyzed. A mechanical concept was selected that can accommodate a set class of scientific instruments such as the LAMAR X-ray experiment with 24 LAMAR telescopes.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-166787 , NAS 1.26:166787
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  • 71
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    Space transportation systems, 1980-2000 (1978)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: An overview of projected space transportation systems for the 1980-2000 period is presented. Methods for meeting the requirements in that area are documented through a description of the Space Shuttle and its current upper stages, reusable transfer vehicles, Shuttle uprating, fully reusable and single-stage transports, heavy lift vehicles, and advanced vehicles for orbital transfer and lunar landing. The structure of the liquid oxygen/liquid hydrogen boosters, cryogenic propellants, whose main propulsion system is a derivative of the RL-10 engine used in the Centaur launch, and mixed mode propulsion engine is also described, as is the flyback booster concept and such related issues as propellants and rocket engines, staging velocity, configuration shape, and whether it should be manned or unmanned. Especially noted are proposed propulsion systems going beyond the present Shuttle such as the nuclear and electric propulsion concepts, the resistojet, using liquid hydrogen, ion thruster, using argon, magnetoplasmadynamic thrusters, solar thermal rocket, and solar sail concept where the basic idea is to use a 'sail' of thin reflective material to generate a net force by reflection of solar radiation.
    Keywords: SPACE TRANSPORTATION
    Type: AD-A057620
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  • 72
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    Formulation of consumables management models. Volume 1: Mission planning (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Development of an STS (Space Transportation System) interactive computer program MPP (Mission Planning Processor) working model was conducted. A summary of the computer program development and those supporting tasks conducted is presented. Development of the MPP Computer Program is discussed. This development was supported by several parallel tasks. These tasks either directly supported the program development, or provided information for future application and/or modification to the program in relation to the flight planning and flight operations of the STS and advanced spacecraft. The supporting tasks also included development of a Space Station MPP to demonstrate the applicability of the analytical methods developed under this RTOP to more advanced spacecraft than the STS.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-160098 , TRW-26821-H024-RO-00-VOL-1
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  • 73
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    Space Shuttle Plume Simulation Effect on Aerodynamics (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Technology for simulating plumes in wind tunnel tests was not adequate to provide the required confidence in test data where plume induced aerodynamic effects might be significant. A broad research program was undertaken to correct the deficiency. Four tasks within the program are reported. Three of these tasks involve conducting experiments, related to three different aspects of the plume simulation problem: (1) base pressures; (2) lateral jet pressures; and (3) plume parameters. The fourth task involves collecting all of the base pressure test data generated during the program. Base pressures were measured on a classic cone ogive cylinder body as affected by the coaxial, high temperature exhaust plumes of a variety of solid propellant rockets. Valid data were obtained at supersonic freestream conditions but not at transonic. Pressure data related to lateral (separation) jets at M infinity = 4.5, for multiple clustered nozzles canted to the freestream and operating at high dynamic pressure ratios. All program goals were met although the model hardware was found to be large relative to the wind tunnel size so that operation was limited for some nozzle configurations.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-150848 , RTR-016-5
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  • 74
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    Apparatus for assembling space structure (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An apparatus for producing a structure in outer space from rolls of prepunched ribbon or sheet material that are transported from the earth to the apparatus located in outer space is described. The apparatus spins the space structure similar to a spider spinning a web utilizing the prepunched ribbon material. The prepunched ribbon material is fed through the apparatus and is shaped into a predetermined channel-shaped configuration. Trusses are punched out of the ribbon and are bent downwardly and attached to a track which normally is a previously laid sheet of material. The size of the overall space structure may be increased by merely attaching an additional roll of sheet material to the apparatus.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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    Glossary, Acronyms, Abbreviations: Space transportation system and associated payloads (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A glossary of terms (and definitions) in current usage for the space transportation system and associated payloads, as well as acronyms and abbreviations, are presented.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-X-74337 , KSC-GP-1052-REV-8
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  • 76
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    The Approach and Landing Test program of the Space Shuttle Orbiter 101 (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The Approach and Landing Test (ALT) program was conducted in late 1976 through November 1977 to investigate the low speed characteristics of the Orbiter alone. The innovative aspects of the Orbiter are discussed along with the ALT program and the testing methodology used. The Shuttle Transportation System concept is briefly reviewed. The ALT was a first step towards operational missions for the Shuttle. The prime objective of the ALT was to verify the systems design and integrated operation of the Orbiter, and to demonstrate the capability of the Orbiter to safely land at a designated runway. The first free flight of the Orbiter occurred on August 12, 1977. Attention is also given to the results obtained in free-flight two, three, four, and five. Free-flight five was specifically planned to demonstrate a runway landing.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 78-1446 , Aircraft Systems and Technology Conference; Aug 21, 1978 - Aug 23, 1978; Los Angeles, CA
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  • 77
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    Potential SSME modifications to provide extended capabilities for future applications (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Expendable launch vehicles will be phased out during the first years of shuttle operation and the payloads currently carried to orbit by these vehicles will be placed in low earth orbit by the reusable shuttle. In connection with limitations regarding the weight of the payload which can be launched by the Space Shuttle in its present form, approaches have been considered for increasing the payload capability of the Shuttle. Propulsion systems for Shuttle derived vehicles with larger payload capabilities have been studied. Such systems can potentially be obtained from modifications of the Space Shuttle Main Engine (SSME). Concepts based on modifications to the basic engine include an SSME-35 for low altitude operation with liquid rocket boosters and an SSME-150 for operation over the complete altitude range as might be required in a single-stage-to-orbit vehicle application. Another modification would provide operation with a hydrocarbon fuel instead of hydrogen.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-976 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
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  • 78
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    Attitude control of a flexible spacecraft (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An algorithm is presented for designing optimal low order compensators for high order systems and it is applied to the title problem where many vibration modes are excited by the control torque. These low order compensators are compared with the full order optimal compensator and found to be less sensitive to modeling errors and to provide near optimal attitude regulation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-1281 , Guidance and Control Conference; Aug 07, 1978 - Aug 09, 1978; Palo Alto, CA
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  • 79
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    Flying qualities of an aircraft with strong lateral-directional coupling (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Flying qualities of aircraft with strong lateral-directional coupling may be unsatisfactory without command and stability augmentation. Although sensitivity to stability derivative variation may be decreased by such a flight control system (FCS), deficiencies associated with control derivative uncertainty may persist or worsen. This is especially true in systems with necessarily high gains, e.g., the Space Shuttle Entry FCS. Effects of stability/control derivative variations on the flying qualities of the Space Shuttle (with and without FCS) have been investigated, and the unaugmented Space Shuttle has been simulated in flight using Princeton's Variable-Response Research Aircraft (VRA).
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 78-1361 , Atmospheric Flight Mechanics Conference; Aug 07, 1978 - Aug 09, 1978; Palo Alto, CA
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  • 80
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    Pointed science scan platforms (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Two examples of science scan platform mechanization concepts are presented to familiarize the reader with today's planetary scan platform technology. The first example is the Voyager scan platform, which will demonstrate the traditional approach to scan pointing from planetary vehicles. Although this conventional approach may be familiar to many, the control law implemented in the scan positioning loop is a new and interesting one. It is called 'Zero Crosser + Terminal Control'. The other example marks the beginning of a new generation of planetary scan pointing systems. It is the Galileo scan platform which will be inertially stabilized and decoupled from spacecraft motion.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS PAPER 78-113 , Annual Rocky Mountain Guidance and Control Conference; Mar 10, 1978 - Mar 13, 1978; Keystone, CO
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  • 81
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    Analysis and design of the Multimission Modular Spacecraft hydrazine propulsion module (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The translational velocity increment, stabilization and control requirements, vehicle weight, and geometric considerations of the Multimission Modular Spacecraft (MMS) provided the basic data on which to initiate the analysis and design of the hydrazine propulsion modules. The Landsat D was used as the mission model. Tradeoff studies were conducted on thrust level, thruster location, and clustering arrangement together with tankage volume and location. The impact of the use of single and dual seat thruster valves on plumbing configuration, reliability, and overall system cost was studied in detail. Conceptual designs of a recommended propulsion module configuration for both the Delta 3910 and Shuttle were prepared.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-1094 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
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  • 82
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    Modeling of thruster and solar array characteristics in the JPL low-thrust trajectory analysis (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Recent advances in thruster and solar array technology have resulted in the possibility of performing many high energy space missions previously considered infeasible. This capability was demonstrated by an extensive study last year of a comet Halley rendezvous mission. In order to perform this extremely high energy mission, several advanced concepts in electric propulsion technology were investigated; notably the use of very high power, lightweight solar arrays which directly powered the beam supply of the electric propulsion thrusters, and the use of solar concentrators on the arrays together with conventional thrusters and power processors. These technology advances have directly impacted the modeling of the solar arrays and thrusters in the programs used in generating low-thrust trajectories. The intent of this paper is to discuss the modeling of the solar arrays and thrusters as employed in the trajectory programs presently being used in low-thrust mission studies at JPL.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-645 , International Electric Propulsion Conference; Apr 25, 1978 - Apr 27, 1978; San Diego, CA; US
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  • 83
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    Ion Propulsion Module design and mission performance (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper describes the design options, processes and tradeoffs that occur during the establishment of viable Ion Drive vehicle and mission designs. The options identify those internal vehicle design alternatives which are being considered for future Ion Drive missions, such as sunlight concentrating arrays and direct drive thrust subsystems, and their effect on mission performance. Also, the highly interactive nature of the Ion Drive design process, which occurs between the spacecraft and mission designers, is described. The results of design tradeoffs, performed for three Ion Drive comet rendezvous missions, are presented. These results include the following: (1) the power profile is determined primarily by the trajectory while second order effects include the solar cell characteristics and array concentration factor and degradation; and (2) the dominant parameter in mission performance determination, Ion Propulsion Module (IPM) mass, and IPM design, is the total cell power evaluated without concentration, at the beginning of life and at 1 AU.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-644 , International Electric Propulsion Conference; Apr 25, 1978 - Apr 27, 1978; San Diego, CA; US
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  • 84
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    Thermal design and development of a planetary probe - Pioneer Venus large probe (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The thermal control system developed for the Large Atmospheric Probe of the Pioneer Venus Multiprobe Mission is described. The scope of the thermal control task requires maintaining the probe internal equipment shelf temperatures within a nonoperating range of -40 to 122 F and an operating range of -4 to 122 F during three different mission phases: (1) preseparation, the transit phase of the mission when the probe is attached to the Multiprobe Spacecraft Bus, (2) postseparation, the free-flight cruise phase of the mission following release from the Bus, and (3) descent, the phase of the mission from preentry equipment turn-on to impact on the Venus surface. Thermal control for these phases is achieved by a combination of passive thermal finishes on the probe exterior surfaces and heaters mounted on the equipment shelves. Verification of the adequacy of the total thermal design to meet all mission requirements has been completed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-916 , Thermophysics and Heat Transfer Conference; May 24, 1978 - May 26, 1978; Palo Alto, CA
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  • 85
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    Interaction of large, high power systems with operational orbit charged particle environments (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Concepts are presently being advanced for space systems to be used for such activities as manufacturing, earth observations, scientific exploration, power generation and human habitation, in locations ranging from low earth orbit (300-500 km) to geosynchronous orbit and beyond. Many of these systems concepts envision large structures and high power levels, and consequently higher operating voltages than have been used in space to date. The potential impact of interactions of space systems with their operational orbit charged particle environments on the systems' performance must be accounted for in the design process. A potentially hazardous spacecraft-environment interaction is discussed, namely the interaction of large high voltage systems with low energy (less than 50 eV) plasmas which can result in loss of power, and/or arcing. The impact of this class of interactions on system operation is most severe at low orbits where the ambient plasmas are densest. Results of experimental work and predictions of simple analytical models are presented and their implications for design of space systems are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS 77-243 , Annual Meeting; Oct 18, 1977 - Oct 20, 1977; San Francisco, CA
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  • 86
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    Thermal analysis of a high energy propulsion system /hydrazine and liquid fluorine/ for a rover class Mars Orbiter (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Maintaining cryogenic fluorine at a -189 C during the interplanetary cruise period to Mars is a major thermal problem. At this low temperature the heat rejection by radiation is severely limited and the allowable thermal load to the fluorine tank is less than approximately 8 watts. Previous studies generally constrain the spacecraft to an inline tank configuration which tends to maximize the fluorine tank's view and heat rejection to space. With the Inertial Upper Stage, sufficient stack height may not be available on the Shuttle for an inline tank configuration. Therefore, this study addresses the more thermally constraining side by side tank configuration.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-888 , Thermophysics and Heat Transfer Conference; May 24, 1978 - May 26, 1978; Palo Alto, CA
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  • 87
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    An ultralightweight, evacuated, load-bearing, high-performance insulation system (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A new hollow-glass microsphere insulation and a flexible stainless-steel vacuum jacket were demonstrated on a flight-weight cryogenic test tank, 1.17 m in diameter. The weight of the system is three times lighter than the most advanced vacuum-jacketed design demonstrated to date, a free-standing honeycomb hard shell with a multilayer insulation system (for a Space Tug application). Design characteristics of the flexible vacuum jacket are presented along with a model describing the insulation thermal performance as a function of boundary temperatures and emittance, compressive load on the insulation and insulation gas pressure. Test data are compared with model predictions and with prior flat-plate calorimeter test results. Potential applications for this insulation system or a derivative of this system include the cryogenic Space Tug, the Single-Stage-to-Orbit Space Shuttle, LH2 fueled subsonic and hypersonic aircraft, and LNG applications.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-878 , Thermophysics and Heat Transfer Conference; May 24, 1978 - May 26, 1978; Palo Alto, CA
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  • 88
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    Comparison of reusable insulation systems for cryogenically-tanked earth-based space vehicles (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Three reusable insulation systems concepts have been developed for use with cryogenic tanks of earth-based space vehicles. Two concepts utilized double-goldized Kapton (DGK) or double-aluminized Mylar (DAM) multilayer insulation (MLI), while the third utilized a hollow-glass-microsphere, load-bearing insulation (LBI). All three insulation systems have recently undergone experimental testing and evaluation under NASA-sponsored programs. Thermal performance measurements were made under space-hold (vacuum) conditions for insulation warm boundary temperatures of approximately 291 K. The resulting effective thermal conductivity was approximately .00008 W/m-K for the MLI systems (liquid hydrogen test results) and .00054 W/m-K for the LBI system (liquid nitrogen test results corrected to liquid hydrogen temperature). The DGK MLI system experienced a maximum thermal degradation of 38 percent, the DAM MLI system 14 percent, and the LBI system 6.7 percent due to repeated thermal cycling representing typical space flight conditions. Repeated exposure of the DAM MLI system to a high humidity environment for periods as long as 8 weeks provided a maximum degradation of only 24 percent.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-877 , Thermophysics and Heat Transfer Conference; May 24, 1978 - May 26, 1978; Palo Alto, CA
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    HEPP - A low temperature Heat Pipe Experiment Package developed for flight on-board the Long Duration Exposure Facility /LDEF/ (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Heat Pipe Experiment Package (HEPP) is designed to provide a flight evaluation system for low temperature heat pipes. The HEPP will be flown aboard the Long Duration Exposure Facility which will be launched and retrieved as part of the Space Shuttle program. The experiment contains two heat pipes: an axially grooved fixed conductance heat pipe and a liquid blockage thermal diode. A phase change material canister is also integrated with a radiant cooler system. Additional hardware consists of supporting electrical equipment, including electronics for signal conditioning and command functions, a data recorder, and a hermetically sealed battery which powers the experiment. A thermal model was developed to simulate the behavior of the HEPP and a ground test program was conducted to verify the predicted performance of the equipment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-459 , International Heat Pipe Conference; May 22, 1978 - May 24, 1978; Palo Alto, CA
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  • 90
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    A thermal canister experiment for the Space Shuttle (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An experiment will be described which, if successful, will demonstrate the feasibility of using a heat pipe thermal canister to control the temperature of a wide variety of instruments operating in the bay of the NASA Space Shuttle. The experiment will be launched in December 1979 as part of the fourth orbital flight test of the Shuttle. Predictions indicate that the canister can provide an environment controlled to + or - 1 C over the range of 0 C to 30 C for conductively and radiatively coupled instruments with internal power dissipations of approximately 100 to 400 watts. This is the most ambitious thermal control program yet attempted which uses heat pipes as the primary control element. The outcome of this experiment will have far reaching implications for instruments which are operated in the Shuttle bay.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 78-456 , International Heat Pipe Conference; May 22, 1978 - May 24, 1978; Palo Alto, CA
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  • 91
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    Design and evaluation of a rotating variable conductance heat pipe system (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Analysis of the Dynamics Explorer high orbiter spacecraft showed that the proposed louver system, along with existing radiator heat rejection areas on the S/C surface were insufficient to safely control the S/C's thermal excursions caused by highly varying internal power levels and solar input angles. A variable conductance heat pipe system in conjunction with a conventional radial heat pipe system was designed, built, tested, and shown to resolve this problem. The conventional pipes, radial, spinning at 10 rpm were required to carry 35 watts each after experiencing despin from 80 rpm. The VCHPs attached to the radial pipes at the S/C perimeter distributed the excess energy via a finned radiator attached around the S/C's center.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-422 , International Heat Pipe Conference; May 22, 1978 - May 24, 1978; Palo Alto, CA
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  • 92
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    Evaluation of commercially-available spacecraft-type heat pipes (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: As part of an effort to develop reliable, cost effective spacecraft thermal control heat pipes, Lewis Research Center of NASA is conducting life tests on 30 commercially-available heat pipes in 10 groups of different design and material combinations. Materials are aluminum and stainless steel, and working fluids are methanol and ammonia. The formation of noncondensible gas is observed for times exceeding 11,000 hours. The heat transport capacities of the pipes are also determined. Considerable gas is found in two groups of methanol pipes; one group shows no gas. One group of ammonia pipes has no observable gas. Another group has much gas. Manufacturers' processing schedules are examined for differences explaining the presence of gas. Heat transport capacity is found to be severely reduced in some pipes containing gas.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-397 , International Heat Pipe Conference; May 22, 1978 - May 24, 1978; Palo Alto, CA
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    NASA Charging Analyzer Program - A computer tool that can evaluate electrostatic contamination (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The data from the ATS-5 and -6 Auroral Particles Experiments have shown that the environment at geosynchronous orbit can charge spacecraft surfaces to appreciable negative values. Such surface charges could have undesirable effects on satellite equipment and the data obtained in satellite experiments. A computer program, the NASA Charging Analyzer Program (NASCAP), has, in this connection, been developed to determine the surface charging of spacecraft when encountering geomagnetic substorm conditions. Once a model of a spacecraft has been developed in the NASCAP code, the surface charging can be computed for any environmental input flux. On the basis of the obtained information regarding the surface charging, charged particle trajectories can be computed to determine if it is possible for a particle to return to a satellite surface. It is pointed out that the computer runs conducted with the NASCAP code represent the first attempts to use a self-consistent program to study the behavior of spacecraft surfaces experiencing a geomagnetic substorm condition.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: International Spacecraft Contamination Conference; Mar 07, 1978 - Mar 09, 1978; Colorado Springs, CO
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    NASA TECHNICAL REPORTS
  • 94
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    System design of an ion drive spacecraft (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: As electric propulsion technology has improved and mission requirements have changed, a series of Ion Propulsion Module (IPM) design concepts have evolved. The most recent iteration occurred in the NASA-sponsored Halley Comet Rendezvous Mission (HCRM) study of ion drive. Spacecraft system design considerations introduced by the integration of such an IPM as the primary propulsion source are described with reference to the synthesis of the HCRM spacecraft and spacecraft design considerations for other interplanetary applications. IPM interactions with the system (especially telecommunications and science) are found to be manageable. The spacecraft design developed for the HCRM indicates the interface simplicity between the IPM and the spacecraft. Methods are shown for readily applying this IPM to a variety of planetary missions. Methods are also described for the IPM to provide up to 5 kW to the spacecraft for increasing the mission science return
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-642 , International Electric Propulsion Conference; Apr 25, 1978 - Apr 27, 1978; San Diego, CA; US
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  • 95
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    The Space Shuttle Orbiter approach and landing tests - A correlation of flight and predicted performance data (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper represents the results of a program in which a flight test vehicle was flown for a limited number of flights. The vehicle was the Space Shuttle Orbiter. The total free flight time for the entire flight test program was less than half an hour. The flight regime tested represented only the approach and landing phase of the vehicle's planned flight capability. The program relied heavily on an extensive wind tunnel test program to predict the aerodynamic performance data over the complete flight range, as well as to predict data tolerances. During the flight test program, short maneuvers performed were to provide flight motion data. A data extraction program was developed to produce flight derived aerodynamic performance data in coefficient form from the motion data. The resultant flight test data was correlated with the predicted data and fell within the predicted data tolerances for all phases of the subsonic flight test regime, including ground effects.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 78-793 , Aerodynamic Testing Conference; Apr 19, 1978 - Apr 21, 1978; San Diego, CA
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  • 96
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    The Space Shuttle Orbiter and aerodynamic testing (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The concept of utilizing the Space Shuttle Orbiter as an aerodynamic flight research vehicle is discussed. The orbiter's planned flight frequency and its complex flight control system provide an unprecedented flight research potential. This paper defines the orbiter's flight environment and applicable baseline systems, their capabilities and limitations, as well as those instrument systems required to augment the baseline capability. These required systems, which are being developed under NASA's Orbiter Experiments Program (OEX) are the Aerodynamic Coefficient Identification Package (ACIP), Shuttle Entry Air Data System (SEADS), and the Shuttle Upper Atmosphere Mass Spectrometer (SUMS). Finally, the need for and capability of launching payloads from the orbiter to extend the research potential beyond the orbiter configuration and/or environment is defined.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 78-790 , Aerodynamic Testing Conference; Apr 19, 1978 - Apr 21, 1978; San Diego, CA
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  • 97
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    Estimation of payload loads using rigid body interface accelerations (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: In the design/analysis process of a payload structural system, the accelerations at the payload/launch vehicle interface obtained from a system analysis using a rigid payload are often used as the input forcing function to the elastic payload to obtain structural design loads. Such an analysis is at best an approximation since the elastic coupling effects are neglected. This paper develops a method wherein the launch vehicle/rigid payload interface accelerations are modified to account for the payload elasticity. The advantage of the proposed method, which is exact to the extent that the physical system can be described by a truncated set of generalized coordinates, is that the complete design/analysis process can be performed within the organization responsible for the payload design. The method requires the updating of the system normal modes to account for payload changes, but does not require a complete transient solution using the composite system model. An application to a real complex structure, the Viking Spacecraft System, is given.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-519 , Structures, Structural Dynamics and Materials Conference; Apr 03, 1978 - Apr 05, 1978; Bethesda, MD
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  • 98
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    Dynamics of spinning spacecraft during the deployment of flexible boom (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The effect of flexibility on the dynamics of a spinning symmetrical spacecraft during the extension (or retraction) of boom-type appendages is treated by modeling the appendages as compound spherical pendula with varying lengths. Both boom stiffness and structural damping are included. For constant boom length the resulting linearized equations of motion contain periodic coefficients involving the spin frequency. A bounded transformation converts this system into a kinematically equivalent one (with only constant coefficients), whose stability is analyzed using the Kelvin-Tait-Chetaev theorem. The dynamics during extension is predicted by numerical simulation of the nonlinear equations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-489 , Structures, Structural Dynamics and Materials Conference; Apr 03, 1978 - Apr 05, 1978; Bethesda, MD
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  • 99
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    Water sprays in space retrieval operations (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The water spray technique (WST) for nullifying the angular momentum of a disabled spacecraft is examined. Such a despinning operation is necessary before a disabled spacecraft can be retrieved by the Space Shuttle. The WST involving the use of liquid sprays appears to be less complex and costly than other techniques proposed to despin a disabled vehicle. A series of experiments have been conducted to determine physical properties of water sprays exhausting into a vacuum. A computer model is built which together with the experimental results yields satellite despin performance parameters. The selection and retrieval of an actual disabled spacecraft is considered to demonstrate an application of the WST.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-329 , Annual Meeting and Technical Display; Feb 07, 1978 - Feb 09, 1978; Washington, DC
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  • 100
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    Heat pipes in space and on earth (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The heat pipe is a closed tube whose inner surfaces are lined with a porous capillary wick. The wick is saturated with the liquid phase of a working fluid. The heat supplied at one end of the tube, the evaporator, causes evaporation of the working fluid. The vapor will pass to the other end of the tube, the condenser, where it will condense and release the latent heat of vaporization to a heat sink in that section of the pipe. Problems concerning a design of heat pipes for space applications are related to certain difficulties regarding the prediction of device performance under zero-g conditions. Heat pipes are usually tested on the ground under the influence of gravity, and then their performance is extrapolated to space. A description is presented of the approaches used to insure good heat pipe performance in space. Attention is given to an international heat pipe experiment conducted to accumulate zero-g performance data for several new and unique heat pipe designs, heat pipes for ATS-6, cryogenic heat pipes, and future activities.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-295 , Annual Meeting and Technical Display; Feb 07, 1978 - Feb 09, 1978; Washington, DC
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