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Jones, L. W.

Publications and source records attributed to Jones, L. W..

9 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1991

Propulsion at the Marshall Space Flight Center - A brief history

The history of propulsion development at the NASA Marshall Space Flight Center is summarized, beginning with the development of the propulsion system for the Redstone missile. This course of propulsion development continues through the Jupiter IRBM, the Saturn family of launch vehicles and the engines that powered them, the Centaur upper stage and RL-10 engine, the Reactor In-Flight Test stage and the NERVA nuclear engine. The Space Shuttle Main Engine and Solid Rocket Boosters are covered, as are spacecraft propulsion systems, including the reaction control systems for the High Energy Astronomy Observatory and the Space Station. The paper includes a description of several technology efforts such as those in high pressure turbomachinery, aerospike engines, and the AS203 cyrogenic fluid management flight experiment. These and other propulsion projects are documented, and the scope of activities in support of these efforts at Marshall delineated.

Jones, L. W.↗
NASA NTRS1986

Oxygen/hydrogen Space Station propulsion system concept definition for IOC

The potential for the reduction in propulsion system life cycle costs through the use of on-board water electrolysis to generate oxygen and hydrogen propellants, as well as the potential advantages of improved system safety and contamination impact, led to a study to evaluate candidate oxygen-/hydrogen-based propulsion systems. In this study a representative set of propulsion system requirements were compiled and candidate oxygen/hydrogen-based propulsion systems synthesized. These candidate concepts were screened and a systems evaluation was performed on the remaining eight candidate concepts. Detailed system schematics were prepared. Operational design conditions were determined and system weight, volume, energy requirements, and costs were calculated. Evaluation results indicated that the oxygen/hydrogen propulsion systems can provide simple, low cost, and viable systems for the IOC Space Station. Based on these data, a relative concept evaluation was conducted using as selection criteria reliability, safety, cost, technical risk, contamination, operational utility, growth potential, and integration potential. Top ranked candidate systems were recommended to NASA/MSFC for consideration for the IOC Space Station.

Shoji, J. M.↗
NASA NTRS1986

High energy interactions of cosmic ray particles

The highlights of seven sessions of the Conference dealing with high energy interactions of cosmic rays are discussed. High energy cross section measurements; particle production-models of experiments; nuclei and nuclear matter; nucleus-nucleus collision; searches for magnetic monopoles; and studies of nucleon decay are covered.

Jones, L. W.↗
NASA NTRS1985

Space station advanced propulsion and fluid management program

In preparation for the development of a manned space station program of advanced technology and development to make new advanced propulsion options available for the initial space station in the 1990's is described. This paper reviews the objectives of the advanced technology and development program in propulsion, describes its origin and how it relates to the forthcoming development program. The advanced propulsion and fluid management systems to be investigated in the program are discussed along with the rationale for their selection. Finally, the systems test program is discussed.

Richmond, R. J.↗
NASA NTRS1983

A NASA high-power space-based laser research and applications program

Applications of high power lasers are discussed which might fulfill the needs of NASA missions, and the technology characteristics of laser research programs are outlined. The status of the NASA programs or lasers, laser receivers, and laser propulsion is discussed, and recommendations are presented for a proposed expanded NASA program in these areas. Program elements that are critical are discussed in detail.

Deyoung, R. J.↗
NASA NTRS1982

NASA's laser-propulsion project

Design concepts, study results, and research directions toward development of CW laser heating of remotely flying spacecraft fuels to provide high impulse thrust are presented. The incident laser radiation would be absorbed by hydrogen through a medium of a laser-supported plasma. The laser energy could be furnished from an orbiting solar-powered laser platform and used to drive the engines of an orbital transfer vehicle (OTV) at costs less than with a chemical propulsion system. The OTV propulsion chamber would be reduced in size comparable to the volume addition of the incident laser energy absorber. The temperatures in the hydrogen-fueled system could reach 5000-15,000 K, and studies have been done to examine the feasibility of ion-electron recombination. Kinetic performance, temperature field, and power necessary to sustain a laser thrust augmented system modeling results are discussed, along with near-term 30 kW CO2 laser system tests.

Jones, L. W.↗
NASA NTRS1980

Laser propulsion - 1980

An overview of the current government sponsored work in laser propulsion is presented and the NASA program is discussed. Attention is given to the overall NASA plan in laser propulsion and the laser rocket engine technology program. Some results of an analytical effort at Physical Sciences Inc. are presented, as well as results of the NASA/Army Missile Command experimental effort. Finally, future plans are briefly summarized.

Jones, L. W.↗
NASA NTRS1977

Standardization - A method of reducing auxiliary propulsion systems costs

This paper deals with the efforts of the National Aeronautics and Space Administration to take advantage of the economies made possible by the Space Shuttle by reducing the costs of acquiring and flying payloads for the Shuttle. Specifically, the paper addresses the route that NASA's Low Cost Systems Office is following in order to reduce the cost of auxiliary propulsion systems. This approach emphasizes the establishment of standard hardware items, which will be used on as many spacecraft as possible. The method by which a standard is selected and how it is maintained as a standard are discussed. The process by which the 5 Newton hydrazine thruster was adopted is described, as a typical example.

Jones, L. W.↗