ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
Filter
  • SPACE VEHICLES  (142)
  • 2020-2023
  • 2010-2014
  • 1970-1974  (142)
  • 1965-1969
  • 1974  (61)
  • 1973  (81)
  • 11
    facet.materialart.
    Unknown
    Room temperature stretch forming of scale space shuttle external tank dome gores. Volume 1: Technical (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An account of activities and data gathered in the Room Temperature Stretch Forming of One-third Scale External Tank Bulkhead Gores for space shuttle study, and a tooling design and production cost study are reported. The following study phases are described: (1) the stretch forming of three approximately one-third scale external tank dome gores from single sheets of 2219-T37 aluminum alloy; (2) the designing of a full scale production die, including a determination of tooling requirements; and (3) the determination of cost per gore at the required production rates, including manufacturing, packaging, and shipping.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120365 , CASD-NAS-74-029-VOL-1
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 12
    facet.materialart.
    Unknown
    System design of the Pioneer Venus spacecraft. Volume 8: Command/data handling subsystems studies (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Study tasks for the command and data handling subsystems have been directed to: (1) determining ground data systems, (GDS) interfaces and deep space network (DSN) changes, if required, (2) defining subsystem requirements, (3) surveying existing hardware that could be used or modified to meet subsystem requirements, and (4) establishing a baseline design. Study of the existing GDS led to the conclusion that the Viking configuration GDS can be used with only minor changes required for the Pioneer Venus baseline. Those changes required are associated with providing a predetection recording capability used during probe entry and descent. Subsystem requirements were first formulated with sufficient latitude so that surveys of existing hardware could lead to low cost hardware which, in turn, could modify more narrowly defined subsystem requirements.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-137495
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 13
    facet.materialart.
    Unknown
    Stability region maximization by decomposition-aggregation method (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This work is to improve the estimates of the stability regions by formulating and resolving a proper maximization problem. The solution of the problem provides the best estimate of the maximal value of the structural parameter and at the same time yields the optimum comparison system, which can be used to determine the degree of stability of the Skylab. The analysis procedure is completely computerized, resulting in a flexible and powerful tool for stability considerations of large-scale linear as well as nonlinear systems.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-2428
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 14
    facet.materialart.
    Unknown
    Decomposition-aggregation stability analysis (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This report presents the development and description of the decomposition aggregation approach to stability investigations of high dimension mathematical models of dynamic systems. The high dimension vector differential equation describing a large dynamic system is decomposed into a number of lower dimension vector differential equations which represent interconnected subsystems. Then a method is described by which the stability properties of each subsystem are aggregated into a single vector Liapunov function, representing the aggregate system model, consisting of subsystem Liapunov functions as components. A linear vector differential inequality is then formed in terms of the vector Liapunov function. The matrix of the model, which reflects the stability properties of the subsystems and the nature of their interconnections, is analyzed to conclude over-all system stability characteristics. The technique is applied in detail to investigate the stability characteristics of a dynamic model of a hypothetical spinning Skylab.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-2196
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 15
    facet.materialart.
    Unknown
    Computer simulation for time optimal or energy optimal attitude control of spin-stabilized spacecraft. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An original technique for determining the optimal magnetic torque strategy for control of the attitude of spin stabilized spacecraft is presented. By employing Lagrange multipliers and the Calculus of Variations, optimal control equations are derived which define minimum time and minimum energy attitude maneuvers. Computer program algorithms to numerically solve these optimal control equations are also described. The performance of this technique is compared with a commonly employed planning method.
    Keywords: SPACE VEHICLES
    Type: Summer Computer Simulation Conference; Jul 17, 1973 - Jul 19, 1973; Montreal; Canada
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 16
    facet.materialart.
    Unknown
    Some considerations for Space Tug launch site support operations. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The study reported was undertaken to investigate the requirements placed on the Space Tug by the ground operations. On the basis of the results obtained, it will be possible to consider in future Tug systems studies the full spectrum of both ground and flight operations requirements in defining selected Tug configurations. The central core of the study consists of a functional analysis of ground operations during the Tug turnaround. Electronic system studies were initiated concurrently with the functional analysis study phase to evaluate interrelationships between ground and vehicle checkout and fault isolation capability.
    Keywords: SPACE VEHICLES
    Type: AIAA PAPER 73-620 , Joint Space Mission Planning and Execution Meeting; Jul 10, 1973 - Jul 12, 1973; Denver, CO
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 17
    facet.materialart.
    Unknown
    Lightweight evacuated multilayer insulation systems for the space shuttle vehicle (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The elements in the evacuated multilayer insulation system were investigated, and the major weight contributors for optimization selected. Outgassing tests were conducted on candidate vacuum jacket materials and experiments were conducted to determine the vacuum and structural integrity of selected vacuum jacket configurations. A nondestructive proof test method, applicable to externally pressurized shells, was validated on this program.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-121105 , D180-15171
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 18
    facet.materialart.
    Unknown
    Aerodynamic characteristics of a 142-inch diameter solid rocket booster, configuration 139 (SA2FA/SA2FB) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests of a 2.112 percent scale model of the space shuttle solid rocket booster model were conducted in a transonic pressure tunnel. Tests were conducted at Mach numbers ranging from 0.4 to 1.2, angles of attack from minus one degree to plus 181 degrees, and Reynolds numbers from 0.6 million to 6.1 million per foot. The model configurations investigated were as follows: (1) solid rocket booster without external protuberances, (2) solid rocket booster with an electrical tunnel and a solid rocket booster/external tank thrust attachment structure, and (3) solid rocket booster with two body strakes.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-134105 , DMS-DR-2088
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 19
    facet.materialart.
    Unknown
    Prediction of shuttle vehicle damping from component test results (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A dissipative energy approach for predicting the damping of four-component space shuttle model by means of modal parameters obtained from tests of the individual components is presented. A relationship between modal damping energy per cycle and peak strain (or kinetic) energy is first determined empirically from test data for each component. Undamped analytical models of each component are also developed, and combined into a system model from which are obtained modal kinetic (or strain) energies for its respective modes. These data are then used with the empirical damping curves to apportion the proper amount of damping energy to each component in a combined system mode, and thereby allow a prediction of damping ratio. Some discrepancies in results are noted to occur because of incomplete modeling of connecting link mechanisms and anomalies in modal responses.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-124209
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 20
    facet.materialart.
    Unknown
    Satellite attitude control simulations (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Work was conducted to develop an extremely low drift rate gyroscope and a very precise star tracker. A proposed relativity satellite will measure very accurately the theoretically predicted 'relativistic' precession of the gyroscope relative to an inertial reference frame provided by the star tracker. Aspects of precision spinning attitude control are discussed together with questions of gyro operation, and the hopping mode for lunar transportation. For the attitude control system of the lunar hopper, a number of control laws were investigated. The studies indicated that some suboptimal controls should be adequate for the system.
    Keywords: SPACE VEHICLES
    Type: International Seminar on Simulation and Space; Sept. 10-14, 1973; Toulouse; France
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...