Simulation of Flight Conditions During Lift off for Rocket Engine Testing

2004 ◽  
Author(s):  
Klaus Schäfer ◽  
Herbert Zimmermann
Keyword(s):  
Rocket Engine ◽  
Lift Off ◽  
Engine Testing

Transient Lift-Off Test Results for an Experimental Hybrid Bearing in Air, Simulating a Liquid Hydrogen Turbopump Start Transient

2016 ◽  
Author(s):  
Dara W. Childs ◽  
David Klooster ◽  
Henry Borchard ◽  
Dustin Pavelek ◽  
Stephen Phillips
Keyword(s):  
Rocket Engine ◽  
Transient Behavior ◽  
Simulation Software ◽  
Test Results ◽  
Unit Load ◽  
Ramp Rate ◽  
Fluid Medium ◽  
Supply Pressure ◽  
Lift Off ◽  
Point Of Departure

Start-transient testing of a hybrid (combined hydrostatic and hydrodynamic action) bearing supplied with air was completed, providing an indication of its performance while operating in a compressible fluid medium. The test start transients were modeled after Rocket Engine Transient Simulation Software (ROCETS) predictions for start-transient behavior of running speed ω(t) and bearing supply pressure Ps(t). The top test speed was 15 krpm. The ramp rate, supply pressure Ps values at 15 krpm, constant bearing unit load magnitude w0, and load orientation (load-on-recess LOR or load-on-land LOL) were varied. Five different load-case combinations were carried out (separately) for LOR and LOL load configurations with ramp rates varying from 2206 rpm/s to 8824 rpm/s. The target pressures at 15 krpm varied from 5.32 bars to 18.25 bars. The tested bearing dimensions were: L = D = 38.1 mm, and Cr =.0635 mm. Lift-off occurs due to the increase in Ps (ω dependent) and was defined as the point of departure towards the center of the bearing with increasing ω while the rotor remained 0.00254 mm (0.1 mils) above the bearing surface. This method is limited by the inability to accurately measure an established operating bearing clearance. Evaluation of the lift-off Ps versus applied unit load w0 supports the following conclusions: (1) Lift-off Ps is approximately a linear function of w0, (2) Changing the ramp rate while keeping constant the specified Ps at 15 krpm has no significant impact, (3) Lowering the limit Ps at 15 krpm may reduce the lift-off Ps value, and (4) The LOR start-transient cases required a higher lift-off speed and lift-off Ps values than the corresponding LOL start-transient cases.

Categorization of Human Errors in Rocket Engine Testing

1961 ◽  
Author(s):  
Lane B. Blank ◽  
Gustavus S. Miller
Keyword(s):  
Rocket Engine ◽  
Human Errors ◽  
Engine Testing

Engine Testing of Advanced Materials for Hypersonic Applications

2005 ◽  
Author(s):  
Michael J. Bur
Keyword(s):  
Rocket Engine ◽  
Ceramic Composites ◽  
Gaseous Hydrogen ◽  
Metal Alloys ◽  
Advanced Materials ◽  
Metallic Foams ◽  
Combustion Chambers ◽  
Hypersonic Propulsion ◽  
Engine Testing ◽  
Engine Components

This paper describes the use of a ground based gaseous hydrogen/oxygen rocket engine to test advanced materials for rocket engine and hypersonic propulsion applications. The types of materials that have been tested include ceramic composites, metallic alloys and ceramic and metallic foams. There are various configurations in which these materials can be tested. A “square” engine is used for testing flat rectangular panels by placing the panel downstream of the rocket nozzle in the exhaust path. A more traditional “round” rocket engine is used to test axisymmetric engine components such as nozzle inserts and combustion chambers that are fabricated from either ceramic composites or metal alloys. Besides hydrogen, other engine fuels such as methane are being evaluated in order to expose test materials to a hydrocarbon environment. Various organizations from industry, academia and other government agencies have used this test cell to facilitate the development of advanced materials for use in both rocket engine and hypersonic propulsion applications.

Noise Prediction of Liquid Rocket Engine by the Software AutoSEA2

2012 ◽  
Vol 466-467 ◽  
pp. 794-798
Author(s):  
Xiao Long Duan ◽  
Xiao Yong Liu
Keyword(s):  
Rocket Engine ◽  
Sound Field ◽  
Noise Spectrum ◽  
Test System ◽  
Acoustic Energy ◽  
Liquid Rocket Engine ◽  
Analysis Model ◽  
Lift Off ◽  
Liquid Rocket ◽  
High Level

Because of the high-cost of the spaceflight launching, the reliability of the payload must be ensured in the high level acoustic energy produced by the first stage rocket engine. It’s the base for ensuring the normal work of the instruments during the lift-off. In this paper, the exhaust noise and the specific sound field produced by the liquid rocket engine on the ground-test system were measured, and the statistical energy analysis model was built to predict the noise environment of the rocket engine. In order to obtain the noise spectrum loaded on the fairing and the instrument cabin during the lift-off, two measurements were made and some measuring locations were set for each test. During the testing, the sound pressure level around the engine spout and the corresponding heights of the payload cabin were measured. By comparing the data derived from different measuring locations for the same measurement and the different measurements for the same location, the characteristics of the noise field was obtained. Results showed that the measured data agreed well with the predicted data used AutoSEA2 software.

scholarly journals Development of treatment media for advanced stormwater treatment at an industrial site

2018 ◽  
Vol 14 (1) ◽  
pp. 81-87
Author(s):  
R. E. Pitt ◽  
S. E. Clark ◽  
B. Steets
Keyword(s):  
Los Angeles ◽  
Rocket Engine ◽  
Stormwater Treatment ◽  
Water Quality Control ◽  
Natural Treatment Systems ◽  
Natural Treatment ◽  
Wide Range ◽  
The Media ◽  
Engine Testing ◽  
Regional Water

Abstract The Santa Susana Field Laboratory (SSFL) occupies about 2,850 acres and is located in Ventura County, California. The site is jointly owned by the Boeing Company and the federal government (the National Aeronautics and Space Administration administers the federal portion of the property). Much of the site was historically used as a rocket engine testing and energy research facility from 1949 to 1998. The site stormwater discharges are permitted by the Los Angeles Regional Water Quality Control Board through an individual industrial NPDES permit that includes numeric effluent limits for a wide range of constituents, including dioxins and metals. A large portion of the site uses distributed source stormwater controls with natural treatment systems utilizing chemically active media. As part of this approach, extensive research was conducted to develop a robust media for use in these controls to meet the discharge objectives. This paper describes the development of the media and its characteristics.

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