Engineering topics

Brien, E. P.

Publications and source records attributed to Brien, E. P..

5 records

NASA NTRS1984

A shuttle derived utility vehicle for delivery of small payloads to orbit

A small-payload utility-vehicle (UV) configuration for the Space Shuttle is proposed and illustrated with drawings, diagrams, and graphs, and tables. The primary modification to the Shuttle involves removal of the solid-rocket boosters and addition of three Shuttle main engines to the external tank, resulting in an overall weight reduction from about 4.53 to 2.07 Mlbs and a per-flight cost savings of 16 percent. For current Shuttle parameters, such a UV could carry up to 2 klbs of payload in the forebody mid-deck, the entire payload bay being occupied by fuel tanks with capacity 180 klbs; with advanced-technology weight reductions of 15 percent in Orbiter subsystem dry weights (including structures), the UV could carry up to 17 klbs of payload using only 125 klbs of internally loaded propellants, allowing a 15-ft cargo space.

Macconochie, I. O.↗

NASA NTRS1983

Lightweight Thermal-Protection System

Hexagonal honeycomb panels secured by Y-shaped plates form lightweight, easily-maintained thermal-protection system. Honeycomb outer panel and fastener materials are selected to match local heating rates. Typical materials include composites, titanium, superalloys, and refractory metals. Advantages include complete symmetry of components--there are no left- or right-hand parts and no asymmetry in thermal expansion.

Macconochie, I. O.↗

NASA NTRS1979

Two priority cargo earth-to-orbit transports

Two priority cargo earth-to-orbit transports are described. One of the vehicles is powered by all-LOX/hydrogen rocket engines. The vehicle is launched vertically but is equipped with aero-surfaces (delta wings and canards) for horizontal landing. The second vehicle is powered by engines utilizing dual fuels (hydrogen and hydrocarbon), the latter concept giving a more compact vehicle. The vehicle is designed for horizontal takeoff and horizontal landing. Both vehicle concepts are used for identification of possible future technology needs.

Macconochie, I. O.↗

NASA NTRS1979

Preliminary design for a space based orbital transfer vehicle

A space-based orbital transfer vehicle has been sized for a 50-metric-ton payload delivery from low-earth-orbit to a geosynchronous orbit. Space basing effected substantial reductions in cryogenic insulation, tank, and body structure. The tank and body structural masses are shown to be lower for space basing because of the larger difference in acceleration loads between the on-orbit case (0.2 g's) and delivery (3.0 g's), the latter applying to ground-based vehicles which are delivered to orbit fully loaded with propellants. Insulation masses are lower because of the absence of an atmosphere and the attendant heat transfer losses. Insulation systems masses are also reduced because of the elimination of the problem of liquefaction and freezing of moisture on the tanks.

Macconochie, I. O.↗

NASA NTRS1979

Several preliminary designs for heavy-lift earth-to-orbit transport

Several design concepts are identified for earth-to-orbit delivery of payloads in the 200 Mg range. The concept include winged vehicles which take-off vertically and land horizontally and ballistic shapes similar to the Gemini or Mercury vehicles which take-off and land vertically. Major technology issues include stability problems for the winged vehicle with large base mounted engines and heat shield design problems for the ballistic vehicle, the latter requiring doors in the heat shield for the main engines.

Brien, E. P.↗