Author: Richard Scott Kirkpatrick
Publisher:
ISBN:
Category :
Languages : en
Pages : 61
Book Description
The testing of solid and liquid rocket propulsion systems in a confined test facility often produces explosive or flammable gases which must be safely handled. Often inert gases such as nitrogen are used to lower the molar fraction of oxygen to low enough levels to minimize the probability of an explosion or deflagration. For this thesis, the chemical composition of these rocket exhaust gases mixed with air were used to determine the flammability limits of the gas mixture. Using the ideal gas law and the conservation of mass, the exhaust gas composition and gas properties such as pressure, temperature, volume and mole fractions inside the test facility were calculated. This exhaust gas composition along with La Chatelier's law was applied to an air-free basis for calculating the flammability limits of the rocket exhaust gas in air. Using Test Driven Development and Object Oriented Programming, a computer program using the Python programming language was created with a Graphical User Interface (GUI) to automate these calculations. This program was validated using existing analytical techniques developed at the Arnold Engineering Development Complex (AEDC). The results from the Python program agree well, a maximum of 1.4% difference, with the validated AEDC techniques.
Analysis of Flammability Limits and Gas Properties of a Solid Rocket Motor Test in a High Altitude Test Facility
Author: Richard Scott Kirkpatrick
Publisher:
ISBN:
Category :
Languages : en
Pages : 61
Book Description
The testing of solid and liquid rocket propulsion systems in a confined test facility often produces explosive or flammable gases which must be safely handled. Often inert gases such as nitrogen are used to lower the molar fraction of oxygen to low enough levels to minimize the probability of an explosion or deflagration. For this thesis, the chemical composition of these rocket exhaust gases mixed with air were used to determine the flammability limits of the gas mixture. Using the ideal gas law and the conservation of mass, the exhaust gas composition and gas properties such as pressure, temperature, volume and mole fractions inside the test facility were calculated. This exhaust gas composition along with La Chatelier's law was applied to an air-free basis for calculating the flammability limits of the rocket exhaust gas in air. Using Test Driven Development and Object Oriented Programming, a computer program using the Python programming language was created with a Graphical User Interface (GUI) to automate these calculations. This program was validated using existing analytical techniques developed at the Arnold Engineering Development Complex (AEDC). The results from the Python program agree well, a maximum of 1.4% difference, with the validated AEDC techniques.
Publisher:
ISBN:
Category :
Languages : en
Pages : 61
Book Description
The testing of solid and liquid rocket propulsion systems in a confined test facility often produces explosive or flammable gases which must be safely handled. Often inert gases such as nitrogen are used to lower the molar fraction of oxygen to low enough levels to minimize the probability of an explosion or deflagration. For this thesis, the chemical composition of these rocket exhaust gases mixed with air were used to determine the flammability limits of the gas mixture. Using the ideal gas law and the conservation of mass, the exhaust gas composition and gas properties such as pressure, temperature, volume and mole fractions inside the test facility were calculated. This exhaust gas composition along with La Chatelier's law was applied to an air-free basis for calculating the flammability limits of the rocket exhaust gas in air. Using Test Driven Development and Object Oriented Programming, a computer program using the Python programming language was created with a Graphical User Interface (GUI) to automate these calculations. This program was validated using existing analytical techniques developed at the Arnold Engineering Development Complex (AEDC). The results from the Python program agree well, a maximum of 1.4% difference, with the validated AEDC techniques.
Experimental Investigation in an Altitude Test Facility of Burning of Excess Combustibles in a Rocket Engine Exhaust
Author: Harry E. Bloomer
Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages : 36
Book Description
National Altitude Rocket Test Facilities
Author: J. A. Suddreth
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
Technical Abstract Bulletin
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 780
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 780
Book Description
Solid Rocket Motor Witness Test
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781729268568
Category : Science
Languages : en
Pages : 48
Book Description
The Solid Rocket Motor Witness Test was undertaken to examine the potential for using thermal infrared imagery as a tool for monitoring static tests of solid rocket motors. The project consisted of several parts: data acquisition, data analysis, and interpretation. For data acquisition, thermal infrared data were obtained of the DM-9 test of the Space Shuttle Solid Rocket Motor on December 23, 1987, at Thiokol, Inc. test facility near Brigham City, Utah. The data analysis portion consisted of processing the video tapes of the test to produce values of temperature at representative test points on the rocket motor surface as the motor cooled down following the test. Interpretation included formulation of a numerical model and evaluation of some of the conditions of the motor which could be extracted from the data. These parameters included estimates of the insulation remaining following the tests and the thickness of the charred layer of insulation at the end of the test. Also visible was a temperature signature of the star grain pattern in the forward motor segment. Welch, Christopher S. Unspecified Center NAS1-18347; RTOP 505-63-01-17
Publisher: Independently Published
ISBN: 9781729268568
Category : Science
Languages : en
Pages : 48
Book Description
The Solid Rocket Motor Witness Test was undertaken to examine the potential for using thermal infrared imagery as a tool for monitoring static tests of solid rocket motors. The project consisted of several parts: data acquisition, data analysis, and interpretation. For data acquisition, thermal infrared data were obtained of the DM-9 test of the Space Shuttle Solid Rocket Motor on December 23, 1987, at Thiokol, Inc. test facility near Brigham City, Utah. The data analysis portion consisted of processing the video tapes of the test to produce values of temperature at representative test points on the rocket motor surface as the motor cooled down following the test. Interpretation included formulation of a numerical model and evaluation of some of the conditions of the motor which could be extracted from the data. These parameters included estimates of the insulation remaining following the tests and the thickness of the charred layer of insulation at the end of the test. Also visible was a temperature signature of the star grain pattern in the forward motor segment. Welch, Christopher S. Unspecified Center NAS1-18347; RTOP 505-63-01-17
Captive-fired Testing of Solid Rocket Motors
Author: James W. Kordig
Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages : 112
Book Description
Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages : 112
Book Description
Solid Rocket Motor Performance Analysis and Prediction
Author: William H. Miller
Publisher:
ISBN:
Category : Solid propellant rockets
Languages : en
Pages : 124
Book Description
Publisher:
ISBN:
Category : Solid propellant rockets
Languages : en
Pages : 124
Book Description
Some Experimental Tests to Change the Total Volume And/or Molecular Weight of Rocket Engine Exhaust Gas in an Altitude Test Facility
Author: A. J. Zazzi
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
The investigation was conducted mainly to determine the possibility of burning fuel-rich combustible exhaust gas mixtures by the injection of either gaseous oxygen or gaseous carbon dioxide into the exhaust stream. The burning of the combustibles, especially hydrogen, results in a large volume decrease when the hot gas in cooled. The reaction of the oxygen or carbon dioxide with combustible products (hydrogen rich in this test) was possible, as evidenced by the results of the chemical analysis of the exhaust products. The possibility of generating an electrostatic field along the viscous mixing boundary between two gases was studied using argon, helium, and stream jets at different energy levels. An electrostatic field along the viscous mixing boundary between two gases (one being steam) was produced in an ungrounded installation; even with only a steam jet in an ungrounded installation, an electrostatic field was generated. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
The investigation was conducted mainly to determine the possibility of burning fuel-rich combustible exhaust gas mixtures by the injection of either gaseous oxygen or gaseous carbon dioxide into the exhaust stream. The burning of the combustibles, especially hydrogen, results in a large volume decrease when the hot gas in cooled. The reaction of the oxygen or carbon dioxide with combustible products (hydrogen rich in this test) was possible, as evidenced by the results of the chemical analysis of the exhaust products. The possibility of generating an electrostatic field along the viscous mixing boundary between two gases was studied using argon, helium, and stream jets at different energy levels. An electrostatic field along the viscous mixing boundary between two gases (one being steam) was produced in an ungrounded installation; even with only a steam jet in an ungrounded installation, an electrostatic field was generated. (Author).
Rocket Testing and Evaluation in Ground Facilities
Author: John H. Povolny
Publisher:
ISBN:
Category : Stages (Rocketry)
Languages : en
Pages : 28
Book Description
Publisher:
ISBN:
Category : Stages (Rocketry)
Languages : en
Pages : 28
Book Description
Rocket-nozzle Testing and Evaluation
Author: E. W. Ungar
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 22
Book Description
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 22
Book Description