Accession Number:

AD0642361

Title:

BUOYANT PLANETARY ENTRY

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1966-03-01

Pagination or Media Count:

125.0

Abstract:

It was assumed that the large buoyant volume is deployed prior to atmospheric entry. The effect of buoyancy on the entry dynamics was investigated, using a first-order entry model. That is, a two-dimensional entry trajectory, a perfectly spherical planet, a constant gravity, and no wind were assumed. It was found that the effect of buoyancy on the velocity, maximum deceleration, and altitude of maximum deceleration of planetary entry vehicles is insignificant. This is true for all entry angles, even if the entry velocity is decreased considerably by rocket braking, and even if the buoyant volume diameter is very large greater than 500 feet. For buoyant planetary entry, the heating problem can be solved by several methods. The first of these methods would entail using expandable heat-resistant materials which could be expanded to protect the buoyant envelope prior to entry. In the second method, a cone or tension shell structure would be constructed around the buoyant volume while in Earth orbit.

Subject Categories:

  • Atmospheric Physics
  • Astronautics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE