Last edited by Aranris
Monday, July 13, 2020 | History

4 edition of Research pressure instrumentation for NASA space shuttle main engine found in the catalog.

Research pressure instrumentation for NASA space shuttle main engine

P. J Anderson

Research pressure instrumentation for NASA space shuttle main engine

by P. J Anderson

  • 148 Want to read
  • 28 Currently reading

Published by Honeywell Inc., Solid State Electronics Division in Plymouth, MN .
Written in English

    Subjects:
  • Space shuttles

  • Edition Notes

    Statementprepared by P.J. Anderson, P. Nussbaum, G. Gustafson
    SeriesNASA-CR -- 173932
    ContributionsNussbaum, P, Gustafson, G, Honeywell, inc. Solid State Electronics Division, George C. Marshall Space Flight Center
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14928992M

    "Wings in Orbit" is an authoritative documentation of the many accomplishments of the NASA Space Shuttle Program. Starting with a foreword written by astronauts John Young and Robert Crippen, this compelling book provides accurate, authentic and easily understood accounts from NASA's best subject matter experts and external resources. The book captures the passion of those who devoted their 4/5(1). A Space Shuttle Main Engine (SSME) hoist prepares to lift the first Block I engine to be installed in an orbiter into the number one position on Discovery while the spaceplane is being prepared for the STS mission in the high bay of Orbiter Processing Facility bay 2.

    The cabin was filled with a pure oxygen atmosphere and pressurized greater than ambient pressure ( psi). Over the course of several hours, the oxygen permeated all materials in the cabin, which had been tested to the normal flight pressure of pure oxygen (5 psi). When the fire began it spread rapidly.   This fact, in combination with its high, throttleable thrust, led NASA to the decision to use the remaining engines from the space shuttle program for their new space launch system, with the first launch being scheduled for Metals and highly optimised superalloys enabled modern space exploration. Yet, the possibilities to develop novel.

    STS On Ma the third launch attempt of STS was aborted at T-3 seconds when the Space Shuttle Main Engine (SSME) 3 oxidizer preburner purge pressure exceeded the maximum pressure. The monitor detected that the combustion product pressure exceeded the 50 psi redline due to one of the five check valves in the purge system leaking. The Space Shuttle Program has also served as an inspiration for young people to study science, technology, engineering, and math, which is so important to the future of our nation. The Space Shuttle is an engineering marvel perhaps only exceeded by the station itself. The shuttle was based on the technology of the s and early Size: 3MB.


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Research pressure instrumentation for NASA space shuttle main engine by P. J Anderson Download PDF EPUB FB2

Research pressure instrumentation for NASA space shuttle main engine Author: P J Anderson ; P Nussbaum ; G Gustafson ; Honeywell Inc. Solid State Electronics Division. The advantages of silicon piezoresistive strain sensing technology are being used to achieve the objectives of state of the art pressure sensors for SSME applications.

The integration of multiple functions on a single chip is the key attribute being exploited. Progress is reported in transducer packaging and materials; silicon resistor characterization at cryogenic temperatures; chip mounting Author: P.

Anderson, P. Nussbaum, G. Gustafson. Abstract. Research concerning the development of pressure instrumentation for the space shuttle main engine is reported.

The following specific topics were addressed: (1) transducer design and materials, (2) silicon piezoresistor characterization at cryogenic temperatures, (3) chip mounting characterization, and (4) frequency response optimizationAuthor: P.

Anderson, P. Nussbaum and G. Gustafson. Research pressure instrumentation for NASA space shuttle main engine. By P. Nussbaum, G. Gustafson and P. Anderson.

Abstract. The breadboard feasibility model of a silicon piezoresistive pressure transducer suitable for space shuttle main engine (SSME) applications was demonstrated. The development of pressure instrumentation for the SSME Author: P. Nussbaum, G. Gustafson and P.

Anderson. Research pressure instrumentation for NASA Space Shuttle main engine, modification no. (Task C) of this research study effort to develop pressure instrumentation for the SSME. The objective of this contract (Task C) is to direct Honeywell's Solid State Electronics Division's (SSED) extensive experience and expertise in solid state Author: P.

Nussbaum, P. Anderson and G. Gustafson. The objective of this contract (Task C) is to direct Honeywell's Solid State Electronics Division's (SSED) extensive experience and expertise in solid state sensor technology to develop prototype pressure transducers which are targeted to meet the SSME performance design goals and to fabricate, test and deliver a total of 10 prototype units.

Research pressure instrumentation for NASA Space Shuttle main engine, modification no. The objective of the research project described is to define and demonstrate methods to advance the state of the art of pressure sensors for the space shuttle main engine (SSME).

Silicon piezoresistive technology was utilized in completing tasks Author: P. Nussbaum, G. Gustafson and P. Anderson. Research pressure instrumentation for NASA Space Shuttle main engine, modification no. of silicon piezoresistive strain sensing technology are being used to achieve the objectives of state of the art pressure sensors for SSME applications.

The integration of multiple functions on a single chip is the key attribute being exploited Author: G. Gustafson, P. Nussbaum and P.

Anderson. RESEARCH PRESSURE INSTRUMENTATION FOR NASA SPACE SHUTTLE MAIN ENGINE HONEYWELL, INC. Introduction and Objective The first phase of this contract (Tasks A and B) resulted in a highly successful demonstration in April at the MSFC of Honeywell's bread-board feasibility model of a silicon Piezoresistive Pressure Transducer.

Photo credit: NASA. After the solid rockets are jettisoned, the main engines provide thrust which accelerates the Shuttle from 4, kilometers per hour (3, mph) to o kilometers per hour (17, mph) in just six minutes to reach orbit. They create a combined maximum thrust of more than million pounds.

Research concerning the utilization of silicon piezoresistive strain sensing technology for space shuttle main engine applications is reported.

The following specific topics were addressed: (1) transducer design and materials, (2) silicon piezoresistor characterization at cryogenic temperatures, (3) chip mounting characterization, and (4) frequency response : P.

Anderson, R. Johnson. The External Tank: The External Tank, or ET, is the "gas tank" for the Orbiter; it contains the propellants used by the Space Shuttle Main Engines. Image left: An External Tank falls back to Earth after being jettisoned from the Shuttle. Click image to play video of External Tank separation (no audio) Photo credit: NASA.

Research pressure instrumentation for NASA space shuttle main engine: monthly report Author: P J Anderson ; P Nussbaum ; G Gustafson ; Honeywell Inc. Solid State Electronics Division. This paper describes instrumentation that is under development for an in-flight demonstration of a plume spectroscopy system on the space shuttle main engine.

The instrumentation consists of a. Research pressure instrumentation for NASA space shuttle main engine. 1 microfiche. (OCoLC) Paper version: Anderson, P.J. Research pressure instrumentation for NASA space shuttle main engine. 1 v. (various pagings)). (OCoLC) Material Type: Document, Government publication, National government publication, Internet resource: Document Type.

Get this from a library. Research pressure instrumentation for NASA space shuttle main engine: monthly report. [P J Anderson; P Nussbaum; G Gustafson; Honeywell Inc. Solid State Electronics Division.; George C. Marshall Space Flight Center.]. To obtain a more vibration resistant pressure sensor for use on the Space Shuttle Main Engine, a proximity probe based, diaphragm type pressure sensor breadboard was developed.

A fiber optic proximity probe was selected as the sensor. In combination with existing electronics, a thermal stability evaluation of the entire probe system was : L.

Hoogenboom, G. Hull-Allen. Therefore, for each Space Shuttle flight, the SRB contributes over channels of telemetered data. Each Space Shuttle Main Engine (SSME) contributes 66 more channels of telemetered data, making a total of channels of telemetered data for the reusable propulsion system components of the Space Shuttle.

PROGRAM SUMMARY United Technologies Research Center (UTRC) has developed a framework to integrate state-of-the-art rocket engine technology with fault detection algorithms for a Health Management System (HMS) for the space shuttle main engine (SSME).

ATTACHMENT 'A' RESEARCH PRESSURE INSTRUMENTATION FOR NASA SPACE SHUTTEL MAIN ENGINE HONEYWELL, INC. Introduction and Objective F The first phase of this contract (Tasks A and B) resulted in a highly suc- cessful demonstration in.

RESEARCH PRESSURE INSTRUMENTATION f OR NASA SPACE SHUTTLE MAIN ENGINE HONEYWELL, INC. Introduction and Objective The first phase of this contract (Tasks A and ii) resulted in a highly suc-cessful demonstration in April at the MSFC of Honeywell's breadboard feasibility model of a silicon Piezoresistive Pressure Transducer suitable.John C.

Stennis Space Center was established to test the engines used to propel the Apollo spacecraft to the moon.The Space Shuttle’s Main Engine (SSME) was a highly innovative, high performance, liquid propelled rocket engine with a variable thrust and mixture ratio. It was controlled electronically by an automatic system that could perform checkout, start, mainstage and shutdown functions/5(13).