Mission analysis.
Spacecraft mission analysis illustrating requirements for Earth orbital mission, launch window choice for rendezvous and lunar landing mission
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Biosatellite 2 operations
Launch window, flight performance, and recovery procedures for biosatellite
Dyer, J. W.↗
Apollo 10 /AS-505/ Apollo Saturn 5 space vehicle Technical information summary
Launch window for Apollo 10 Apollo Saturn 5 space vehicle
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Reference system characteristics for manned stopover missions to Mars and Venus
Launch window characteristics for manned interplanetary stopover flights to Mars and Venus
Deerwester, J. M.↗
Mariner Mars 1971 - Press kit
Mariner Mars mission planning including launch windows and scientific objectives in 1971
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Alternate multiple-outer-planet missions using a Saturn-Jupiter flyby sequence
A study has been made of a method for providing more frequent launch opportunities for multiple-planet Grand Tour type missions to the outer solar system. A Saturn-Jupiter flyby sequence was used in the analysis to initiate the mission instead of the normal Jupiter-Saturn sequence. The Saturn-first approach is shown to yield several new launch opportunities following the 1980 cutoff date for Jupiter-first missions. Results are given for various two-planet, three-planet, and four-planet Jupiter-first and Saturn-first missions. A unique five-planet Saturn-first mission and a Saturn-Jupiter flyby which returns to earth are also discussed. Mission performance is evaluated for each flyby technique by comparing Saturn-first and Jupiter-first missions with respect to launch energy requirements, available launch windows, planetary encounter conditions, and total mission times.
Young, J. W.↗
ATS-F launch planning document
Launch operations of the ATS 6 satellite and the Titan 3 C launch vehicle are analyzed. The subjects discussed are: (1) launch vehicle trajectory, (2) launch vehicle mark events, (3) standard orbital parameter messages, (4) STADAN ground station visibility, (5) launch window, (6) separation attitude, and (7) separation events. The VHF Omni earth coverage antenna is described. Graphs of visibility from various ground stations are developed.
Walsh, R.↗
Mission analysis for the interplanetary monitoring platforms IMP-H and -J
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.
Muhonen, D. P.↗
Apollo 14 (mission H-3) Baseline Mission Profile
Preliminary Apollo 14 (Mission H-3) trajectory data for the July 1970 launch window are presented in this document. A general mission profile is presented, and approximate variations of selected mission parameters are indicated. Note that the information in this document is preliminary and will be updated in the Apollo 14 (Mission H-3) operational trajectory documents.
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INTELSAT 4
A news release on the launching of Intelsat 4 commercial communication satellite is presented. This satellite will be positioned on the equator over the Pacific Ocean. The Atlas-Centaur launch vehicle is considered, along with the launch windows.
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Viking Mars launch set for August 11
The 1975-1976 Viking Mars Mission is described in detail, from launch phase through landing and communications relay phase. The mission's scientific goals are outlined and the various Martian investigations are discussed. These investigations include: geological photomapping and seismology; high-resolution, stereoscopic horizon scanning; water vapor and thermal mapping; entry science; meteorology; atmospheric composition and atmospheric density; and, search for biological products. The configurations of the Titan 3/Centaur combined launch vehicles, the Viking orbiters, and the Viking landers are described; their subsystems and performance characteristics are discussed. Preflight operations, launch window, mission control, and the deep space tracking network are also presented.
Panagakos, N.↗
Mission design implications of an inclined elliptical geosynchronous orbit /International Ultraviolet Explorer/
In order to maximize the weight capability, an inclined elliptical geosynchronous orbit rather than the initially conceived circular one was selected for the International Ultraviolet Explorer (IUE), a joint NASA/ESA effort to study the ultraviolet spectra of stars, galaxies and nebulae. The design of intermediate and mission orbits satisfying the numerous mission requirements and constraints is discussed. The other areas of mission analysis included in the paper are launch window analysis, and orbit evolution and stationkeeping analysis. A significant result of the study is the manner in which statistical data, generated by a Monte Carlo simulation, were incorporated into the pre-flight mission analysis.
Dial, O. L.↗
Venus Orbital Imaging Radar mission analysis
Mission objectives for the Venus Orbital Imaging Radar (VOIR) project are outlined with attention to its scientific instrumentation. Design parameters of the SAR (Synthetic Aperture Radar) are described, including a high resolution capability of 200 m from a circular orbit of 375 km, which will be able to map the entire surface of the planet. Nineteen atmospheric experiments are foreseen, among them: CO2 stability assays, measurements of vertical mass transfer rates, observations of cloud circulation and composition, and an evaluation of solar wind effects on atmospheric dynamics. Navigation and orbital injection plans are reviewed, noting that the 1983 launch window (using STS) is optimum.
Nock, K. T.↗
Single-axis attitude determination accuracy
This paper extends the analysis of attitude determination accuracy introduced at the 1975 American Astronautical Society/American Institute of Aeronautics and Astronautics (AAS/AIAA) Astrodynamics Conference. It contains more generalized expressions, new geometrical relations, and additional applications. A complete set of attitude accuracy equations for both arc-length (portion of a great circle) and rotation-angle (dihedral angle) measurements are presented. These expressions can then be applied to determine the geometrical conditions under which a specified accuracy can be achieved by using either the attitude or a selected reference-vector direction as the independent variable. Representative applications to attitude determination accuracy studies and launch window analyses are discussed. The clear physical interpretation and straightforward graphical procedures greatly simplify mission analysis, maneuver planning, hardware configuration studies, and interpretation of results.
Chen, L. C.↗
STS utilization planning
The paper shows how NASA plans to utilize the Shuttle to carry a wide variety of payloads. Topics covered include: Shuttle Transportation System (STS) description and capabilities, payload integration and manifesting payload business today, and NASA-JSC user services. Consideration is given to the flight assignment process and flight manifest which is a listing of flights with their attendant launch dates, payload names, days on-orbit, altitude, inclination, and crew required. Additional data such as weight, center of gravity, payload-on-orbit capability, and launch windows are checked to see if the manifest is still valid. The STS traffic model is described along with the small self-contained payloads.
Bauch, G. T.↗
Orbit decay analysis of STS upper stage boosters
An orbit decay analysis of the space transportation system upper stage boosters is presented. An overview of the computer trajectory programs, DSTROB, algorithm is presented. Atmospheric drag and perturbation models are described. The development of launch windows, such that the transfer orbit will decay within two years, is discussed. A study of the lifetimes of geosynchronous transfer orbits is presented.
Graf, O. F., Jr.↗
IUS guidance algorithm gamma guide assessment
The Gamma Guidance Algorithm which controls the inertial upper stage is described. The results of an independent assessment of the algorithm's performance in satisfying the NASA missions' targeting objectives are presented. The results of a launch window analysis for a Galileo mission, and suggested improvements are included.
Bray, R. E.↗
Potential problems relative to TDRS/IUS tilt table elevation with failed VRCS
Operational concerns and preliminary solution alternatives related to elevating the inertial upper stage/tracking and data relay satellite (IUS/TDRS) with a failed orbiter vernier reaction control system (VRCS) are presented. Problems arise from the combination of TDRS thermal constraints and tilt table constraints (the primary reaction control system (PRCS) cannot be used to hold attitude while the tilt table is being elevated), and the problems are compounded by the minimum PRCS attitude deadband. The potential solution options are affected by the launch window, flight profile, crew procedures, vehicle capability and constraints, and flight rules.
Bell, J.↗