Evaluation of Rocket Nozzle Passive Temperature Indicators (Test Nozzle No. 2). PDF Download
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Author: John R. Ellison
Publisher:
ISBN:
Category :
Languages : en
Pages : 60
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Book Description
The objective of this test was to demonstrate a technique for measuring subsurface nozzle material temperatures beyond the range of conventional thermocouples. The objective was achieved by designing and fabricating a 2.3-inch-throat-diameter solid rocket nozzle and instrumenting it with high-temperature indicators, the evaluation and selection of propellant ballistic properties to obtain 6500 degrees F flame temperature, 810-psig maximum chamber pressure, 21.9-sec effective firing duration, and posttest evaluation of the rocket nozzle including X-ray analysis and sectioning. (Author).
Author: John R. Ellison
Publisher:
ISBN:
Category :
Languages : en
Pages : 60
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Book Description
The objective of this test was to demonstrate a technique for measuring subsurface nozzle material temperatures beyond the range of conventional thermocouples. The objective was achieved by designing and fabricating a 2.3-inch-throat-diameter solid rocket nozzle and instrumenting it with high-temperature indicators, the evaluation and selection of propellant ballistic properties to obtain 6500 degrees F flame temperature, 810-psig maximum chamber pressure, 21.9-sec effective firing duration, and posttest evaluation of the rocket nozzle including X-ray analysis and sectioning. (Author).
Author: E. W. Ungar
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 22
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Book Description
Author:
Publisher:
ISBN:
Category : Weights and measures
Languages : en
Pages : 590
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Book Description
Author: United States. National Bureau of Standards
Publisher:
ISBN:
Category : Temperature measurements
Languages : en
Pages : 144
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 12
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Book Description
Author: Paul D. Freeze
Publisher:
ISBN:
Category : Temperature
Languages : en
Pages : 144
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Book Description
Author: Kenneth J. Kacynski
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 32
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Book Description
Author: THIOKOL CHEMICAL CORP HUNTSVILLE ALA.
Publisher:
ISBN:
Category :
Languages : en
Pages : 88
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Book Description
This quarterly report describes progress made during the period 22 June through 21 September 1963 on the program to evaluate experimental rocket motor nozzles produced under the Army Materials Research Agency Program. During this period, the Army Missile Command 29amicom0 delivered to Thiokol Chemical Corporation one Atlantic Research 2-in. pyrolytic graphite coated nozzle insert and two titanium boronitride Calorobic 1-in. nozzle inserts, numbered HTB-3 B 109 and HTD-3 A 7, respectively. AMICOM has approved the use of the TX-24 motor to test the 1-in. nozzles at chamber pressures of 700 psi or lower. The TX-338 test motor will be used for testing 1- or 2-inch nozzle inserts at chamber pressures exceeding 700 psi. Two test plans, A and B, were submitted by Thiokol to AMICOM for AMRA's consideration. Test Plan A was a comprehensive plan which included pretest and posttest evaluations of the nozzle insert. Test Plan B was submitted basically as a go-no-go tye test in which the insert would be shipped to Watertown Arsenal for evaluation after the test. (Author).
Author:
Publisher:
ISBN:
Category : Nuclear energy
Languages : en
Pages : 964
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Book Description
Author: J. J. Warga
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
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Book Description
This report is the first of a series describing the results of static test firings conducted to verify the performance of ablative nozzle components fabricated from low-cost materials and/or low-cost manufacturing processes. The nozzle test configuration and the temperature measurement system is described and a comparison is drawn between predicted and actual performance of the ablative plastics utilized in each nozzle component.
