Configuration Design, Hot-firing Test and Performance Evaluation of 200 N-Class GCH4/LOx Small Rocket Engine (Part II: Steady State-mode Ground Hot-firing Test)

The paper deals with modeling and performance evaluation of a series-parallel system using Markov Birth-Death process and probabilistic approach. The system consists of four subsystems arranged in series-parallel with three possible states, working with full capacity, reduced capacity and failed. Through the transition diagrams, systems of differential equations are developed and solved recursively via probabilistic approach. Explicit expressions for steady-state availability are de-rived. Availability matrices for each subsystem have been developed to provide various performance values for different combinations of failure and repair rates of all subsystems. The results from this paper will enhance the system performance and useful for timely execution of proper maintenance improvement, decision, planning and optimization.

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Digital Design and Performance Evaluation of the Rocket Engine

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.236-237.1339 ◽

2012 ◽

Vol 236-237 ◽

pp. 1339-1343

Author(s):

Bo Wen Hu ◽

Bing Wang

Keyword(s):

Performance Evaluation ◽

Rocket Engine ◽

Digital Design ◽

Performance Parameters ◽

Solid Rocket Motors ◽

Rocket Motors ◽

Input Parameters ◽

And Performance ◽

Solid Rocket

In order to achieve the digital design of solid rocket motors, the MFC module of Visual Studio2010 is used for interface software programming in this paper. Beginning with the initial performance parameters, the software receives the input parameters and gives the results of grain design and its interior ballistic calculation. Given all the results, we can evaluate the performance of grain. The design cases show that the design results of the software are correct and reliable.

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Hydrostatic Bearings for Cryogenic Rocket Engine Turbopumps

Journal of Lubrication Technology ◽

10.1115/1.3554989 ◽

1969 ◽

Vol 91 (3) ◽

pp. 557-575 ◽

Cited By ~ 47

Author(s):

J. M. Reddecliff ◽

J. H. Vohr

Keyword(s):

Steady State ◽

Rocket Engine ◽

Liquid Oxygen ◽

Support Provision ◽

Hydrostatic Bearing ◽

Stability Performance ◽

Performance Requirements ◽

Hydrostatic Bearings ◽

Rotor Support ◽

And Performance

This paper summarizes an analytic and experimental investigation of hydrostatic bearings for use in high-pressure cryogenic rocket engine turbopumps. A hydrostatic bearing analysis was developed to predict bearing steady-state and time-dependent (stability) performance. The analysis accounts for the effects of turbulence, inertia, and compressibility in the fluid film. Bearing design charts were generated from the analysis to permit rapid prediction of bearing performance and to aid in the selection of optimum bearing configuration. Liquid hydrogen and liquid oxygen turbopump conceptual designs were prepared and the designs were used to establish hydrostatic bearing size and performance requirements. The turbopump designs included provision for operation when bearing supply pressure is insufficient to support the rotor. Two bearing designs, one LH2 and one LO2, were fabricated and tested in a test rig. Test bearing designs met turbopump requirements and included the turbopump start-stop rotor support provision. Experimental data for both test programs agreed well with steady-state predictions and the bearings were stable under all conditions. Both test bearing designs were in excellent mechanical condition after testing, which included 10 simulated turbopump start-stop cycles.

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