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
  • 1
    facet.materialart.
    Unknown
    International Solar Terrestrial Physics (ISTP) program (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The International Solar Terrestrial Physics (ISTP) Program is a large, multi-national program involving three space agencies and up to eight spacecraft. NASA, together with the Institute of Space and Astronomical Science (ISAS) and the European Space Agency (ESA), has agreed in principle to coordinate their efforts in investigating the Sun and the Earth. Each agency is planning to construct and operate different spacecraft as part of this cooperative venture: Geotail provided by ISAS, the Solar Heliospheric Observatory (SOHO) and Cluster (four spacecraft) contributed by ESA, and Wind and Polar by NASA. A general description of the program is presented.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: JPL, California Inst. of Tech., Deep Space Network: Mission Support Requirements; 2 p
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    Doubly-periodic orbits in the Sun-Earth-Moon system (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A series of periodic orbits in the Earth-Moon circular restricted problem of three bodies was found which is ideally suited for exploring the Earth's geomagnetic tail. The mean apsidal motion of the basic highly elliptical Earth orbit was maintained at about one degree per day by a sequence of lunar swingbys, keeping the apogees in the anti-Sun direction. The orbits were periodic in reference frames rotating at both lunar and solar rates. Apogee distances were alternately raised and lowered by the lunar swingby maneuvers. Several categories of these Sun-synchronous double lunar swingby orbits were identified. The strength and flexibility of this trajectory concept was demonstrated with real world simulations.
    Keywords: ASTRODYNAMICS
    Type: Fifth Ann. Flight Mech.(Estimation Theory Symp.; 19 p
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    Unknown
    Transfer trajectory design for the SOHO libration-point mission (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: It is shown that transfer trajectories to the halo orbit exist throughout the year, with a one week closure of the launch window each month because of unfavorable lunar perturbations that cannot be corrected in the case of transfer trajectory insertion errors. The launch window for transfers to large-amplitude Lissajous orbits is virtually the same as that for transfers to the baseline halo orbit. Details of these trajectories are described and questions about groundstation coverage are discussed.
    Keywords: ASTRODYNAMICS
    Type: IAF PAPER 92-0066
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 4
    facet.materialart.
    Unknown
    Instructions for the use of the marquardt ibm 7040 computer program. controlled tethering in space (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Computer program for orbiting three body system simulation in Fortran
    Keywords: COMPUTERS
    Type: NASA-CR-63851
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 5
    facet.materialart.
    Unknown
    TBERR - Two-body error analysis program (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two-body error analysis computer program to evaluate resulting state vector and covariance matrix for orbiter after one coast and one burn maneuver
    Keywords: SPACE SCIENCES
    Type: NASA-TM-X-65620 , X-551-71-238
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 6
    facet.materialart.
    Unknown
    An experimental comparison of several approaches to the linear least squares problem (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Algorithms and original data matrix approaches compared for linear least squares problem
    Keywords: MATHEMATICS
    Type: NASA-TM-X-63722 , X-551-69-422
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 7
    facet.materialart.
    Unknown
    Mission design for a halo orbiter of the earth (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The International Sun-Earth Explorer (ISEE) scientific satellite to be stationed in 1978 in the vicinity of the sun-earth interior libration point to continuously monitor the space between the sun and the earth, including the distant geomagnetic tail is described. Orbit selection considerations for the ISEE-C are discussed along with stationkeeping requirements and fuel-optimal trajectories. Due to the alignment of the interior libration point with the sun as viewed from the earth, it will be necessary to place the satellite into a 'halo orbit' around the libration point, in order to eliminate solar interference with down-link telemetry. Parametric data for transfer trajectories between an earth parking orbit (altitude about 185 km) and a libration-point orbit are presented. It is shown that the insertion magnitude required for placing a satellite into an acceptable halo orbit is rather modest.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: AIAA PAPER 76-810 , Astrodynamics Conference; Aug 18, 1976 - Aug 20, 1976; San Diego, CA
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 8
    facet.materialart.
    Unknown
    Mission analysis for the interplanetary monitoring platforms IMP-H and -J (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: IMP-H and -J were launched in September 1972 and October 1973, respectively, and placed into orbits of low eccentricity halfway distant to the moon. IMP-H was required to remain between 30 and 40 earth radii for three years, and IMP-J was to maintain a similar orbit while staying on the opposite side of the earth. In both cases no orbit-adjust capability was provided after firing of a solid-propellant apogee kick motor; so strategy during mission operations depended on advance studies of orbit evolution and sensitivity to pertinent error sources. This is presented in detail along with the launch window study, and comparisons are made between the target and achieved orbits.
    Keywords: SPACE SCIENCES
    Type: AIAA PAPER 74-784 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 9
    facet.materialart.
    Unknown
    Mission design for a ballistic slow flyby Comet Encke 1980 (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Preliminary mission analyses for a proposed 1980 slow flyby (7-9 km/s) of comet Encke are presented. Among the topics covered are science objectives, Encke's physical activity and ephemeris accuracy, trajectory and launch-window analysis, terminal guidance, and spacecraft concepts. The nominal mission plan calls for a near-perihelion intercept with two spacecraft launched on a single launch vehicle. Both spacecraft will arrive at the same time, one passing within 500 km from Encke's nucleus on its sunward side, the other cutting through the tail region. By applying a small propulsive correction about three weeks after the encounter, it is possible to retarget both spacecraft for a second Encke intercept in 1984. The potential science return from the ballistic slow flyby is compared with other proposed mission modes for the 1980 Encke flyby mission, including the widely advocated slow flyby using solar-electric propulsion. It is shown that the ballistic slow flyby is superior in every respect.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-TN-D-7726 , G-7508 , AIAA Aerospace Sci. Meeting; Jan 31, 1974; Washington, D. C.; United States
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 10
    facet.materialart.
    Unknown
    IMP-1 launch window analysis (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: IMP-1 launch window and secondary injection into eccentric orbit
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-65450 , X-551-71-5
    Format: application/pdf
    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...