Search NASA⌕ Search
Home/Archive/NASA NTRS

NASA NTRS · 19670045619

A method for calculating parachute opening forces for general deployment conditions.

Jamison, L. R.
View original source ↗Export metadata ↓

Abstract

Calculating method for parachute opening forces, system velocity, cloth pressure loading and filling time for horizontal and vertical deployment conditions

Explore related subjects

NUMERICAL INTEGRATIONPARACHUTE FABRICDYNAMIC LOADPRESSURE EFFECT

Keep this discovery

Explore connections, maps & timelines

BibTeXRIS

Jamison, L. R.. 1967-04-01. A method for calculating parachute opening forces for general deployment conditions.. https://ntrs.nasa.gov/citations/19670045619

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

KEEP EXPLORING

Related reports

NASA NTRS1966

Numerical integration of periodic orbits in the elliptic restricted three-body problem

The problem of finding periodic orbits in the circular restricted three-body problem has been very extensively studied in celestial mechanics. It is well known that continuous families of periodic orbits exist, for which the period varies in a continuous way. However, all the applications which are found in the solar system correspond to cases with non-zero eccentricities, and the elliptic restricted three-body problem is thus a better approximation than the circular one. For instance, for the motion of a satellite in the Earth-Moon system, as a first approximation, we may assume that the Moon moves around the Earth in circular motion; but as a much better approximation, we can also assume that the Moon moves in an elliptic orbit around the Earth.

NUMERICAL INTEGRATION↗