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  • 1
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    The effect of satellite spin on two-way Doppler range-rate measurements (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Error introduced into coherent two-way Doppler tracking measurements on spinning satellite, using turnstile antenna
    Keywords: COMMUNICATIONS
    Type: ; TROPHYSICAL JOURNAL
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Correction of satellite tracking data for an arbitrary tropospheric profile. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A procedure is given for deriving elevation-error and range-error correction equations in a form suitable for use in the rapid processing of satellite tracking data. The refractivity of the troposphere is assumed to have spherical symmetry, but may have any given profile that does not depart greatly from standard. When the procedure was tested for numerical accuracy by application to an exponential profile, the corrections calculated agreed with those obtained by ray tracing to 0.3% or better over a range of surface refractivity from 200 to 450 and a range of radiowave arrival angles from horizontal to vertical.
    Keywords: COMMUNICATIONS
    Type: Radio Science; 7; Feb. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Error analysis for relay type satellite-aided search and rescue systems (1979)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: An analysis is made of the errors in the determination of the position of an emergency transmitter in a satellite-aided search and rescue system. The satellite is assumed to be at a height of 820 km in a near-circular near polar orbit. Short data spans of four minutes or less are used. The error sources considered are measurement noise, transmitter frequency drift, ionospheric effects, and error in the assumed height of the transmitter. The errors are calculated for several different transmitter positions, data rates, and data spans. The only transmitter frequency used was 406 MHz, but the result can be scaled to different frequencies.
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-15; Sept
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Ambiguity resolution for satellite Doppler positioning systems (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A test for ambiguity resolution was derived which was the most powerful in the sense that it maximized the probability of a correct decision. When systematic error sources were properly included in the least squares reduction process to yield an optimal solution, the test reduced to choosing the solution which provided the smaller valuation of the least squares loss function. When systematic error sources were ignored in the least squares reduction, the most powerful test was a quadratic form comparison with the weighting matrix of the quadratic form obtained by computing the pseudo-inverse of a reduced rank square matrix. A formula is presented for computing the power of the most powerful test. A numerical example is included in which the power of the test is computed for a situation which may occur during an actual satellite aided search and rescue mission.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-TM-78049
    Format: application/pdf
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  • 5
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    Error analysis for relay type satellite-aided search and rescue systems (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis was made of the errors in the determination of the position of an emergency transmitter in a satellite aided search and rescue system. The satellite was assumed to be at a height of 820 km in a near circular near polar orbit. Short data spans of four minutes or less were used. The error sources considered were measurement noise, transmitter frequency drift, ionospheric effects and error in the assumed height of the transmitter. The errors were calculated for several different transmitter positions, data rates and data spans. The only transmitter frequency used was 406 MHz, but the results can be scaled to different frequencies. In a typical case, in which four Doppler measurements were taken over a span of two minutes, the position error was about 1.2 km.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA-TM-78050
    Format: application/pdf
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  • 6
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    Tropospheric range-rate tracking data correction (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A formula for correcting the tropospheric error in range-rate satellite tracking data is given. The formula is based on the method which was used to obtain corrections for elevation-angle and range data. In addition, an improved method is given for calculating some of the parameters required in the correction formulas.
    Keywords: SPACE SCIENCES
    Type: NASA-TM-X-66017 , X-551-72-277
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    A test of the effect of satellite spin on two-way Doppler range-rate measurements. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: NAVIGATION
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-8; May 1972
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    On the decrease of the radar cross section of the Apollo Command Module due to reentry plasma effects (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Radar cross section decrease of Apollo command module due to reentry plasma sheath effects
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-55824 , X-507-67-283
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    GEOS-C altimeter attitude bias error correction (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A pulse-limited split-gate-tracking radar altimeter was flown on Skylab and will be used aboard GEOS-C. If such an altimeter were to employ a hypothetical isotropic antenna, the altimeter output would be independent of spacecraft orientation. To reduce power requirements the gain of the altimeter antenna proposed is increased to the point where its beamwidth is only a few degrees. The gain of the antenna consequently varies somewhat over the pulse-limited illuminated region of the ocean below the altimeter, and the altimeter output varies with antenna orientation. The error introduced into the altimeter data is modeled empirically, but close agreements with the expected errors was not realized. The attitude error effects expected with the GEOS-C altimeter are modelled using a form suggested by an analytical derivation. The treatment is restricted to the case of a relatively smooth sea, where the height of the ocean waves are small relative to the spatial length (pulse duration times speed of light) of the transmitted pulse.
    Keywords: SPACECRAFT INSTRUMENTATION
    Type: NASA-TM-X-70858 , X-932-74-367
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Closed form satellite tracking data corrections for an arbitrary tropospheric profile (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Method for deriving atmospheric elevation error and range error correction formulas for effects of tropospheric refraction on satellite tracking data
    Keywords: SPACE SCIENCES
    Type: NASA-TM-X-65533 , X-551-71-122
    Format: application/pdf
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