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  • 1
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    A case for inherent geometric and geodetic accuracy in remotely sensed VNIR and SWIR imaging products (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Significant aberrations can occur in acquired images which, unless compensated on board the spacecraft, can seriously impair throughput and timeliness for typical Earth observation missions. Conceptual compensations options are advanced to enable acquisition of images with inherent geometric and geodetic accuracy. Research needs are identified which, when implemented, can provide inherently accurate images. Agressive pursuit of these research needs is recommended.
    Keywords: EARTH RESOURCES AND REMOTE SENSING
    Type: Proc. of the NASA Workshop on Registration and Rectification; p 454-468
    Format: application/pdf
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  • 2
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    Analysis of heliographic missions complementary to ISPM (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Five concepts were formulated, analyzed, and compared for satisfying heliographic science mission objectives both with and without a concurrent International Solar Polar Mission (ISPM) Spacecraft. Key astrodynamic constraints and performance factors are known from literature for the Lagrange point mission and the sun-synchronous earth orbit mission, but are set forth in this paper for the three solar orbiting missions concepts considered. Any of these five missions should be doable at modest cost since no strong cost drivers were encountered in the analyses. The mission to be flown depends on mission capability to meet science measurement needs more than on strong economic factors. Each mission offers special advantages for particular measurement emphasis. Based on selected qualitative mission discriminators, an overall 'best mission' was selected and described in some detail.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: AAS PAPER 83-351
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  • 3
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    Current status of solar electric-propelled asteroid probe studies (1969)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Solar photoelectric power ion propelled probe of asteroid region, describing design and mission planning
    Keywords: SPACE VEHICLES
    Type: AIAA PAPER 69-1105 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, ANNUAL MEETING AND TECHNICAL DISPLAY, 6TH; Oct 20, 1969 - Oct 24, 1969; ANAHEIM, CA
    Format: text
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  • 4
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    Stereosat - A new astrodynamics challenge (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The paper investigates the astrodynamics requirements for a spacecraft which produces stereo images of the land masses of the earth for use in geoscience investigations, cartography and earth resource exploration. It describes a candidate Stereosat imaging product, presents criteria for evaluating potential image quality and usability, and assesses the impact of various spacecraft and astrodynamic factors on image quality. Several challenges are identified and discussed, namely (1) securing adequate image quality for pixel level elevation measurements, (2) determining absolute location of imaged phenomena in remote regions, (3) satisfying the long-term orbit prediction requirements, and (4) transmitting accurate orbit data along with the image data stream. Meeting these challenges will greatly enhance operational facility.
    Keywords: EARTH RESOURCES AND REMOTE SENSING
    Type: AIAA PAPER 80-0237 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
    Format: text
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  • 5
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    Encounter trajectory design for SEP rendezvous with low mass celestial bodies. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper shows the considerations which precede and affect encounter trajectory design and the impact of this design on propulsion system performance requirements and interplanetary trajectory design. Representative missions selected to illustrate the problems and characteristics of encounter trajectory design are a Mercury Orbiter, Eros Rendezvous, Encke Rendezvous, and Ceres Orbiter. The paper shows that for SEP missions, particularly for low mass celestial bodies, the encounter trajectory may be freely specified to a large extent to satisfy mission goals rather than being dictated by a rigid interplanetary trajectory design.
    Keywords: SPACE SCIENCES
    Type: AIAA PAPER 72-424 , American Institute of Aeronautics and Astronautics, Electric Propulsion Conference; Apr 17, 1972 - Apr 19, 1972; Bethesda, MD
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  • 6
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    Earth applications orbit analysis for a shuttle-mounted Multispectral Mapper (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The earth remote sensing problem of orbit design to acquire images with inherent geometric and geodetic accuracy is addressed. The basis for precise orbit modeling is discussed. Various orbit propagation tools are compared. Orbit characteristics for a nominal case at shuttle altitude are displayed. Modeling Parameter sensitivities are evaluated to determine limits on orbit propagation accuracy versus time. It is found that attainable propagation accuracies are sufficient for image quality assessment over the short term at the 15m pixel size desired for a Multispectral Mapper.
    Keywords: EARTH RESOURCES AND REMOTE SENSING
    Type: AAS PAPER 81-182 , Astrodynamics Specialist Conference; Aug 03, 1981 - Aug 05, 1981; Lake Tahoe, NV; US
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  • 7
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    A flexible approach to an Operational Land Observing System (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper presents a concept for an Operational Land Observing System (OLOS) formulated to satisfy a broad spectrum of perceived user needs for a diverse discipline community. The concept formulated will allow continuous orthographic imaging across multiple spectral bands, near-global stereoscopic imaging, and next-day oblique imaging of any desired spot on earth. Imaging parameters will be adaptable to known phenomena characteristics to facilitate information extraction including optional onboard theme selection. The conceptual system will provide 6- to 12-hour quick-look capability, 48-hour turnaround on all standard imaging products, and a guaranteed data flow schedule reliability for 10 to 20 years. A fleet of successive operational satellites will be used.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: AIAA PAPER 81-0315 , Aerospace Sciences Meeting; Jan 12, 1981 - Jan 15, 1981; St. Louis, MO
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  • 8
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    Mission analysis for design of a SEP multi-mission spacecraft. (1972)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Study of the multimission capability of a solar electric propulsion spacecraft. The study includes such factors as spacecraft constraints, payload variations with launch opportunity, propellant on-loading and off-loading requirements, and limitations in thrusting time, throttling range and steering. The study determined that a single spacecraft design, with P sub zero = 12 kW and I sub s = 3000 sec launched by a Titan IIIC or Titan IIID/Centaur can be used to conduct at least five diverse missions: Eros rendezvous, 1 AU out-of-ecliptic, Mercury orbiter, Jupiter flyby/probe, and Jupiter orbiter. Flight time and injection velocity vary as needed to achieve the desired payload capability. The mission analysis approach and results are presented.
    Keywords: SPACE VEHICLES
    Type: AIAA PAPER 72-51 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 17, 1972 - Jan 19, 1972; San Diego, CA
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  • 9
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    Shuttle/IUS performance for planetary missions (1975)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Potential requirements for planetary missions in the 1980s, capabilities of the Interim Upper Stage (IUS) candidates to perform those missions, and Shuttle/IUS mission profile options for performance enhancement are examined. The most demanding planetary missions are the Pioneer Saturn/Uranus/Titan Probe and the Mariner-class orbiters of Mercury, Jupiter, and Saturn. Options available to designers of these missions will depend on the specific IUS selected for development and the programmatic phasing of the IUS and the NASA Tug. Use of Shuttle elliptic orbits as initial conditions for IUS ignition offers significant performance improvements; specific values are mission dependent.
    Keywords: SPACE TRANSPORTATION
    Type: AAS PAPER 75-273 , Meeting on Space Shuttle Missions of the 80''s; Aug 26, 1975 - Aug 28, 1975; Denver, CO
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  • 10
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    Analysis of an Arctic Polesitter (1979)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The concept and rationale are presented and the fundamental dynamical requirements set forth for a spacecraft that remains stationary in space above the North or South Pole of the earth for an extended period of time. The mathematical basis and acceleration characteristics are shown. Performance capability using present day Ion Drive technology is evaluated in terms of stay time at the pole and imaging resolution as a function of viewing distance. The analysis shows that a Polesitter spacecraft can be maintained without difficulty for one or two years at several lunar distances from the earth, admitting large resolution visual imagery and some less useful measurements in the infra-red regime. Microwave measurements are not practical using today's technology. Sensitivity calculations show that substantial improvement in performance capability must await major advances in available technology.
    Keywords: ASTRODYNAMICS
    Type: AIAA PAPER 79-0127 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA
    Format: text
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