Theoretical basis of the jpl orbit determina- tion program
Theoretical basis of orbit determination - mathematical model, computation and correction of observables, and regression coefficients
REGRESSION COEFFICIENT↗
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Results for “ORBIT CALCULATION”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Guidance analysis.
Unmanned spacecraft guidance policy and orbit determination, using linear perturbation theory and minimum variance estimation
SPACECRAFT GUIDANCE↗
Astrodynamical results from the radio tracking of the mariner venus and ranger lunar missions.
Earth based radio tracking and orbit determination accuracies for Ranger and Mariner missions
ORBIT CALCULATION↗
Completely general closed-form solution for coordinates and partial derivatives of the two- body problem.
Two-body problem completely generalized closed- form solution for coordinates and partial derivatives
ORBIT CALCULATION↗
Optical radar using a corner reflector on the moon.
Lunar corner reflector landing proposal for laser beam precision measurements including Moon orbit, size, ephemeris time and libration
OPTICAL RADAR↗
Universal variables.
Universal variable parameters and formulas used for two-body problem, differential correction and various orbits and perturbations
ORBIT CALCULATION↗
The origin of meteorites as small bodies. ii - the model.
Monte Carlo technique to determine final orbital parameters and bombardment age distribution of meteoritic fragments ejected into inner solar system
ASTEROID↗
Results on physical constants and related data from the radio tracking of mariner /venus/ and ranger iii-vii missions.
Earth based radio tracking and orbit determination accuracies for Ranger and Mariner missions
ORBIT CALCULATION↗
Ascent and descent abort flight corridors for orbital transport vehicles
Ascent and descent abort flight corridors for orbital transport vehicles - two dimensional equations of motion for point mass vehicle derived in circular earth coordinate system
MOTION EQUATION↗
Capability guide- tracking accuracy prediction program /TAPP MOD I/
Tracking accuracy prediction program designed for statistical analysis of preflight orbital determination problems
TRACKING↗
Launch windows for two types of orbits synchronous with the lunar period
Saturn/Centaur launch windows for orbits synchronous with lunar period
ORBIT CALCULATION↗
Hexadecimal to decimal conversion tables for hexadecimal values 0-3F,FFFF - Decimal values 0-262,143
Hexadecimal to decimal system conversion tables for advanced orbital programming systems
CONVERSION TABLE↗
Long-term motion of a lunar satellite
Harmonic analysis including Moon oblateness for long term motion of lunar satellite
OBLATENESS↗
EGO orbital parameters and heat inputs
Computation methods and results for orbital data, spacecraft angle, and heat input for OGO AND specifically for EGO
SPACECRAFT↗
SPODP - Single Precision Orbit Determination Program
This Technical Memorandum describes the Single Precision Orbit Determination Program which was developed for operation under the data processing system of the Space Flight Operations Facility. Included are sections containing flow diagrams, load maps, the common storage map, input and output descriptions, subroutine writeups, operating instructions, and check cases. The computational methods employed by the program are described in the subroutine documentation.
COMPUTER PROGRAM↗
Gravity gradient stabilization system for the Applications Technology Satellite Third quarterly progress report, 1 Jan. - 31 Mar. 1965
Flow diagram for computer program for gravity gradient stabilization system for Applications Technology Satellite /ATS/ mathematical model and orbit test plan for ATS-A flight
GRAVITY GRADIENT SATELLITE↗
Use of mean elements to calculate the position of the sun, moon and earth
Tabulated formulae for calculating mean orbital elements of Earth, Moon, and Sun during 12-hour ephemeris time
SUN↗
Special orbits for the exploration of Mars and Venus
Planetary exploration optimization problems using swing-by trajectories and capture orbits
CAPTURE EFFECT↗