Skip to content

Home/Archive/NASA NTRS

NASA NTRS · 19660022729

Orbit prediction accuracy theory

H E Montgomery·R C Blanchard·F Whitlock

View original source ↗Export metadata ↓

Abstract

Equations for estimating orbit prediction accuracy theory, with partial derivatives calculated from two-body elliptical orbit theory

Explore related subjects

ORBIT EQUATION PREDICTION THEORY TWO-BODY ORBIT

Keep this discovery

Explore connections, maps & timelines

H E Montgomery, R C Blanchard, F Whitlock. 1963-01-01. Orbit prediction accuracy theory. https://ntrs.nasa.gov/citations/19660022729

Cite the original work for its findings. Save a collection to share your selection of sources.

KEEP EXPLORING

Related reports

NASA NTRS1967

Geometric theory of optimum disorbit problems

General solutions to trajectory and orbit equations

ORBIT EQUATION↗

NASA NTRS1966

Satellite motion for arbitrary eccentricity and inclination around the smaller primary in the restricted three-body problem.

Motion of close satellite of smaller primary in restricted three-body problem referred to conventional rotating frame in which central angle is chosen as independent variable

ORBIT EQUATION↗

NASA NTRS1964

A solution of the euler-lambert equation for flight orbits close to hohmann types < o reshenii uravneniya eylera-lamberta dlya perelet-nykh orbit, blizkikh k khomanovskim<

Rapidly converging expansion of euler-lambert equation for flight orbits

ORBIT EQUATION↗