Satellite situation report, volume 5, no. 2
Ephemeris of satellite geodesy - object, code inclination, apogee, perigee, and transmitting frequency
EPHEMERIS↗
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Satellite situation report, volume 6, number 10
Data tables of objects in orbit and decayed objects - code name, catalogue number, source, launch date, period, inclination, apogee, perigee, and transmitting frequency
TABLE↗
Orbital mechanics. I - Analytical treatment. II - Problems.
Orbital mechanics, examining problems relating to patched conics, perigee determination, eccentricity of satellite orbits and drag effect computations
SATELLITE ORBIT↗
The lunar-solar effect on the orbital lifetimes of artificial satellites with highly eccentric orbits.
Lunar-solar perturbation effect on satellites with eccentric orbits, noting lifetimes on perigee heights
ORBITAL MOTION↗
Long-period variations in the eccentricity and argument of perigree of Nimbus 2
Long period variations in eccentricity and perigee for Nimbus 2 explained in terms of earth zonal harmonic coefficents, plus first order earth oblateness perturbations
Felsentreger, T. L.↗
Working with orbits
Orbit calculations for size and shape of orbit, required velocity at perigee and apogee, and gravitational effects on satellite orbit
Gerster, D. E.↗
Application of the matched conic model in the study of circumlunar trajectories. Project Apollo
Matched conic model and integrated circumlunar trajectories compared at injection, pericynthion and perigee
Gibson, T. F., Jr.↗
Relation of measured outgassing pressures to surface adsorption in satellite borne pressure gauges
Outgassing pressure variation with time near perigee in satellite-borne pressure gages, using Langmuir model of surface adsorption
Newton, G. P.↗
Optimum launch trajectories for the ATS-E mission
Optimum launch trajectories for ATS-E mission with noncircular parking orbits, considering apogee motor size, perigee radius and duration constraints
Spurlock, O. F.↗
Tesseral resonance on IMP-4 orbit
Tesseral harmonics of Explorer 34 satellite orbit perturbation in time of perigee passage due to third harmonic of earth gravitational field
Lowrey, B. E.↗
Space tug aerobraking study. Volume 1: Executive summary
The feasibility and practicality of employing an aerobraking trajectory for return of the reusable space tug from geosynchronous orbit was investigated. The aerobraking return trajectory modes employ transfer ellipses from high orbits which have low perigee altitudes wherein the earth's sensible atmosphere provides drag to reduce the tug return delta velocity requirements and thus decrease the required return trip propulsive energy. Aerodynamics, aerothermodynamics, trajectories, guidance and control, configuration concepts, materials, weights and performance were considered. Sensitivities to trajectory uncertainties, atmospheric anomalies and reentry environments were determined. New technology requirements and future studies required to further enhance the aerobraking potential were identified.
Corso, C. J.↗
Moonquakes.
Although the average rate of seismic energy release within the moon appears to be far below that of the earth, over 100 events believed to be moonquakes have been recorded by the two seismic stations installed on the lunar surface during Apollo missions 12 and 14. With few exceptions, the moonquakes occur at monthly intervals near times of perigee and apogee and show correlations with the longer-term (7-month) lunar gravity variations. The repeating moonquakes are believed to occur at not less than 10 different locations. However, a single focal zone accounts for 80 per cent of the total seismic energy detected. This active zone appears to be 600 kilometers south-southwest of the Apollo 12 and 14 sites and deep within the moon. Each focal zone must be small (less than 10 kilometers in linear dimension) and fixed in location over a 14-month period. Cumulative strain at each location is inferred. Thus, the moonquakes appear to be releasing internal strain of unknown origin, the release being triggered by tidal stresses.
Latham, G.↗
Plasma waves in the dayside polar cusp. I - Magnetospheric observations.
General survey of the Ogo 5 plasma-wave measurements for the dayside polar-cusp encounters of Nov. 1, 1968, and detailed analysis of the observations at the low-altitude (r approximately 3 to 5 earth radii) cusp boundaries. The survey section contains an overall discussion of the ULF magnetic-field wave levels and the VLF electric-field amplitude ranges measured from perigee out to 9 earth radii on Nov. 1, 1968. These cusp-associated observations are compared with those made on Oct. 27 and Nov. 6, 1968, when Ogo 5 traversed the dayside magnetosphere without encountering the cusp. It is shown that at the November 1 low-altitude cusp boundaries intense wave levels were detected over a broad spectral region at the steep gradients in cusp plasma density and thermal energy. The results are interpreted in terms of drift instabilities for low-beta plasmas with hot ions, and associated wave-particle and wave-wave interactions are briefly discussed.
Scarf, F. L.↗
The earth's atmosphere.
Topics discussed include the effects of solar radiation on the heat balance of the earth and its atmosphere, the physicomathematical models of the atmosphere and the computational schemes used in numerical investigations of the general circulation of the atmosphere, the effects of atmospheric turbulence on aeronautical systems, te chemistry of different regions of the atmosphere, the use of hot-filament and cold-cathode vacuum gauges to measure upper-atmosphere densities, methods of determining the air density at heights near a satellite's perigee by analyzing changes in its orbit, and an evaluation of various atmospheric models in the 100- to 1000-km altitude range.
Vaughan, W. W.↗
Ephemeris of a highly eccentric orbit - Explorer 28.
An ephemeris has been obtained for Explorer 28 (IMP 3) which agrees well with 2 years of radio observations and with SAO observations a year later. This ephemeris is generated over the 3 year lifetime by a numerical integration method utilizing a set of initial conditions at launch and without requiring further differential correction. Because highly eccentric orbits are difficult to compute with acceptable accuracy and because a long continuous arc has been obtained which compares with actual data to a known precision, this ephemeris may be used as a standard for computing highly eccentric orbits in the earth-moon system. Orbit improvement was used to obtain the initial conditions which generated the ephemeris. This improvement was based on correcting the energy by adjusting the semimajor axis to match computed times of perigee passage with the observed. This procedure may generate errors in semimajor axis to compensate for model errors in the energy; however, this compensation error is also implicit in orbit determination itself.
Lowrey, B. E.↗
An extreme ultraviolet photometer for solar observations from the Atmosphere Explorer satellites
A broadband photometer experiment is being fabricated for the Atmosphere Explorer C, D and E missions to record the solar irradiance in the 40 to 1250 A region with seven distinct passbands. The experiment consists principally of four spinal electron multipliers located behind a moving eight position filter wheel. Six metallic filters are used to spectrally isolate the solar irradiance. In addition three Al2O3 diodes, two with filters, are being used to record the solar irradiance over the range of orbital altitudes from perigee through apogee. A principal goal of the experiment will be to measure time dependence of the solar irradiance with respect to a storage ring synchrotron light source which has been calibrated in terms of the best currently available standards of irradiance.
Heath, D. F.↗
Smoothing of functions of range and range rate measurements from earth orbiting satellites
It is shown that for satellites in circular Earth orbits with altitudes of 500 kilometers to 1500 kilometers, and for satellites in elliptical orbits with an approximate 4000 kilometer height of perigee, a high degree least squares polynomial (e.g., a 9th or 10th degree in some cases) is required to smooth both range and range rate data for purposes of input to orbit determination programs. In order to circumvent this problem, functions of range and range rate are smoothed with lower degree least squares polynomials (e.g., 3rd and 4th degree) and it is shown that under the above geometric constraints the standard deviation of fit can be reduced to levels commensurate with typical S-band tracking system resolution which is 1 to 2 meters in range and 0.005 meters/second in range rate for a 1 per second data rate. Also shown are the effects of Gaussian random noise, biases, and periodic noise. This analysis includes numerous examples applied to the 44 point data smoothing interval currently used in much of the operational preprocessing at the Goddard Space Flight Center.
Grenchik, T. J.↗
Quiet-time magnetospheric field depression at 2.3 to 3.6 R sub E
Fluxgate magnetometer data obtained by OGO-5 near perigee were used to establish the existence of large field depressions in the magnetosphere under conditions of varying degree of disturbance at distances ranging from 2.3 to 3.6 R sub E at all local times. The results also provide the average delta B at these distances when Dst, as being derived at present, is zero.
Sugiura, M.↗