Rocket-nozzle Testing and Evaluation PDF Download
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Author: E. W. Ungar
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 22
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Book Description
Author: E. W. Ungar
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 22
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 12
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Book Description
Author: Cedric Bielawski
Publisher:
ISBN:
Category :
Languages : en
Pages : 141
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Book Description
Seven 1.7-inch throat diameter rocket nozzles were test fired in the HIPPO high pressure facilities at Edwards Air Force Base using three different solid propellants. Three 1.0-inch and two 2.0-inch throat diameter rocket nozzles were test fired at Atlantic Research Corporation using three different gel propellants. All of the throat inserts and most of the entrance sections were coated with PG/SiC. The erosion rates of all of the coated inserts tested in this program are plotted in Figures 49 and 50 as functions of pressure with temperature and level of gas oxidizing species indicated. No delaminations occurred. Some cracking of the inserts occurred but this did not interfere with the attainment of erosion data. (Modified author abstract).
Author: John H. Povolny
Publisher:
ISBN:
Category : Stages (Rocketry)
Languages : en
Pages : 28
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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: 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: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723045219
Category :
Languages : en
Pages : 136
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Book Description
The activity performed on the screening and evaluation of various coatings for application on columbium alloy test panels representative of a radiation-cooled nozzle extension for the RL10 rocket engine is summarized. Vendors and processes of candidate coatings were evaluated. Post engine test evaluations of the two selected coatings are discussed. Murphy, Kenneth S. and Castro, Joaquin H. Unspecified Center COATINGS; NIOBIUM ALLOYS; PERFORMANCE TESTS; ROCKET ENGINES; MICROSTRUCTURE; NOZZLE DESIGN; PANELS...
Author: C. E. Franklin
Publisher:
ISBN:
Category : Combustion
Languages : en
Pages : 642
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Book Description
Author: Carl L. Meyer
Publisher:
ISBN:
Category : Ablative materials
Languages : en
Pages : 28
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Book Description
This report evaluates twenty-two ablative-material samples as nozzle sections of a storable-propellant (nitrogen textroxide and a 50-50 percent blend of unsymmetrical dimethylhydrazine with hydrazine) rocket engine to determine general trends among the material variables and to enable comparison of such trends with those observed from similar tests with a hydrogen-oxygen rocket engine reported in NASA TN D-3258.
Author: Kenneth J. Kacynski
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 32
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Book Description
