Engineering topics

Riccio, Joseph R.

Publications and source records attributed to Riccio, Joseph R..

4 records

NASA NTRS2010

Boundary Layer Transition Protuberance Tests at NASA JSC Arc-Jet Facility

A series of tests conducted recently at the NASA JSC arc -jet test facility demonstrated that a protruding tile material can survive the exposure to the high enthalpy flows characteristic of the Space Shuttle Orbiter re-entry environments. The tests provided temperature data for the protuberance and the surrounding smooth tile surfaces, as well as the tile bond line. The level of heating needed to slump the protuberance material was achieved. Protuberance failure mode was demonstrated.

Larin, Max E.↗

NASA NTRS1993

Common Lunar Lander vehicle propulsion system conceptual design

The Common Lunar Lander (CLL) is a concept for a small, unpiloted vehicle which would provide a low-cost capability to land any of a variety of payloads in the 200 kg class at any point on the surface of the moon. Initiated as a precursor mission for the First Lunar Outpost, it also has considerable potential for use by the scientific community at large. A series of studies has been conducted at the NASA Johnson Space Center to define initial requirements and to initiate the design process. This paper describes the propulsion subsystem design as it existed at the CLL System Design Review. The propulsion subsystem design is described in detail along with the planned operations concept, including the unique concept of using pulsing of main engines for thrust modulation. Design options and trades considered and the verification process philosophy which was being planned for the program are discussed.

Hyatt, C. D.↗

NASA NTRS1992

Space Shuttle Orbiter Fleet Leader Orbital Maneuvering Engine SN 002A injector replacement

During testing of the Fleet Leader Orbital Maneuvering Engine (OME) Serial Number (SN) 002A at the White Sands Test Facility (WSTF) in 1983 the injector was inadvertently damaged. After testing was completed in 1985, there was a concern that the performance of the engine and its response to specific test conditions might not be sufficiently representative of flight engines to provide valid test results. To correct this damage, the engine was returned to the manufacturer to replace the injector. The task assigned was to evaluate the damage and generate a unique process to repair the Fleet Leader OME while providing minimum impact to the overall life condition of the engine. In addition to successfully performing the repair operation, the as received condition of the engine and its components were documented for Fleet Leader reference. The engine is currently at WSTF where it has accumulated 11,341 seconds of firing time to date, 2615 seconds of which have occurred since the engine repair.

Riccio, Joseph R.↗

NASA NTRS1991

Requirements for maintaining cryogenic propellants during planetary surface stays

Potential impacts on the planetary surface system infrastructure resulting from the use of liquid hydrogen and oxygen propellants for a stage and half lander are discussed. Particular attention is given to techniques which can be incorporated into the surface infrastructure and/or the vehicle to minimize the impact resulting from the use of these cryogens. Methods offered for reducing cryogenic propellant boiloff include modification of the lander to accommodate boiloff, incorporation of passive thermal control devices to the lander, addition of active propellant management, and use of alternative propellants.

Riccio, Joseph R.↗