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Large eddy simulation of a shear-coaxial LOX-H2 jet at supercritical pressure

Large eddy simulation of a shear-coaxial LOX-H2 jet at super...

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38th aiaa/ASME/SAE/ASEE Joint Propulsion conference and exhibit 2002

作者： Oefelein, Joseph C. Combustion Research Facility Sandia National Laboratories Livermore CA 94551-0969 United States

ISBN: (纸本)9781624101151

This paper highlights results from the first of a series of hierarchical simulations aimed at assessing the modeling requirements for application of the large eddy simulation technique to cryogenic injection and combustion processes in liquid rocket engines. The focus is on liquid-oxygen-hydrogen coaxial injectors at a condition where the liquid-oxygen is injected at a subcritical temperature into a supercritical environment. For this situation a diffusion dominated mode of combustion occurs in the presence of exceedingly large thermophysical property gradients. Though continuous, these gradients approach the behavior of a contact discontinuity. Significant real gas effects and transport anomalies coexist locally in colder regions of the flow, with ideal gas and transport characteristics occurring within the flame zone. The current focal point is on the interfacial region between the liquid-oxygen core and the coaxial hydrogen jet where the flame anchors itself. © 2002 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Large eddy simulation

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A method of efficient inclination changes for low-thrust spacecraft

A method of efficient inclination changes for low-thrust spa...

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aiaa/AAS Astrodynamics Specialist conference and exhibit 2002

作者： Falck, Robert Gefert, Leon AIAA NASA Glenn Research Center Case Western Reserve University Cleveland OH United States NASA Glenn Research Center Cleveland OH United States

ISBN: (纸本)9781624101243

The evolution of low-thrust propulsion technologies has reached a point where such systems have become an economical option for many space missions. The development of efficient, low trip time control laws has received an increasing amount of attention in recent years, though few studies have examined the subject of inclination changing maneuvers in detail. A method for performing economical inclination changes through the use of an efficiency factor is derived from Lagrange's planetary equations. The efficiency factor can be used to regulate propellant expenditure at the expense of trip time. Such a method can be used for discontinuous-thrust transfers that offer reduced propellant masses and trip-times in comparison to continuous thrust transfers, while utilizing thrusters that operate at a lower specific impulse. Performance comparisons of transfers utilizing this approach with continuous-thrust transfers are generated through trajectory simulation and are presented in this paper. © 2002 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Propellants

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modeling oil flows in engine sumps: Drop dynamics and wall impact simulation

Modeling oil flows in engine sumps: Drop dynamics and wall i...

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38th aiaa/ASME/SAE/ASEE Joint Propulsion conference and exhibit 2002

作者： Weinstock, Vladimir D. Heister, Stephen D. Purdue University West Lafayette IN United States

ISBN: (纸本)9781624101151

A computational preliminary design tool has been developed to help simulate the processes that take place in an oil sump of a gas turbine engine on the basis of the best available knowledge in the areas of drop tracking, deformation, breakup, and drop/wall interactions. Drop equations of motion are solved with a 4th order Runge-Kutta scheme. Gas phase uses an exact solution of the Navier-Stokes equations for the special case of a rotating inner cylinder and a stationary outer cylinder, thus allowing to bypass the complexity and run time penalty of a separate flow solver. Detailed results for the baseline case that attempts to replicate the conditions found in a typical oil sump of a turbofan engine are presented. In addition, the results of more general parametric studies utilizing a simplified geometry that investigated the effects of changing various parameters are discussed. © 2002 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Drops

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Propellant densification for launch vehicles: simulation and testing

Propellant densification for launch vehicles: Simulation and...

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38th aiaa/ASME/SAE/ASEE Joint Propulsion conference and exhibit 2002

作者： Nguyen, Ke Knowles, Timothy E. Greene, William D. Tomsik, Thomas M. Lockheed Martin Space Systems Company Michoud Operations New Orleans LA United States NASA Marshall Space Flight Center Huntsville AL United States NASA Glenn Research Center Cleveland OH United States

ISBN: (纸本)9781624101151

Lockheed Martin Space Systems Company and NASA have been developing the use of densified cryogenic propellants for launch vehicle applications. Propellant densification is the technology of sub-cooling cryogenic propellant below their normal saturation conditions thereby making them more dense. By using densified propellant, more propellant can be loaded on board a launch vehicle, thus increasing the vehicle's performance. Propellant densification is one of the key technologies needed to meet the challenges of future reusable launch vehicles. This paper is the fourth in a series of aiaa papers (98-3688, 98-3689 and 99-2335) detailing our propellant densification activities. This paper discusses the status of the current and continuing efforts of the test program in cooperation with NASA Glenn Research Center. The first phase of testing involved the verification of the densification unit associated with a 20,000-gallon propellant tank. The liquid oxygen densification unit processes a maximum flowrate of 30 lbm/s of liquid oxygen lowering its temperature 40R from normal boiling point conditions. The second phase of testing involved a series of closed-loop recirculation tests within a propellant test tank, which marks the first time such a test has been done. This testing used the densification unit in conjunction with the propellant test tank to simulate the recirculation and densification processes. For the recirculation tests the test tank was outfitted with a siphon outlet at the top of the tank and horizontal splash plates at the two fill points. A liquid level capacitance probe used to control the propellant liquid level and a series of silicon diode temperature sensors used to measure the thermal stratification were also installed in the tank. Discussed within this paper are the parallel efforts of analytical modeling of the in-tank densification process along with performance reconstruction of the densification test. The key to the modeling effort is the unders

关键词： Propellants

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A study on the feasibility of using a genetic algorithm to generate realistic air traffic scenarios based on recorded field data

A study on the feasibility of using a genetic algorithm to g...

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aiaa Guidance, Navigation, and Control conference and exhibit 2002

作者： Oaks, Robert D. FAA William J. Hughes Technical Center Atlantic City International Airport Signal Corporation ACB-330 Simulation and Modeling Group NJ 08405 United States

ISBN: (纸本)9781624101083

Air traffic scenarios based on recorded live data are used for the development and analysis of decision support tools used by air traffic controllers. Frequently these scenarios need to be modified in order to create aircraft-to-aircraft encounters that are not present in the live data. This paper shows that a genetic algorithm can be used to time shift the flights in a scenario in order to create encounters with specific constrained characteristics. For this study these constraints were the distributions of the closest point of approach and the encounter angle of the encounters. The paper first describes how a genetic algorithm was implemented and then presents the results of two series of tests. The first series of tests were designed to determine if the implementation of a genetic algorithm could solve the problem. The second series of tests were designed to assess the time it took the implementation to solve the problem. The results of the study showed that a genetic algorithm could solve the problem in a reasonable time. © 2002 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Genetic algorithms

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modeling and simulation of a Sail

Modeling and simulation of a Sail

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aiaa/AAS Astrodynamics Specialist conference and exhibit 2002

作者： Wilkins, Matthew P. Subbarao, Kamesh Alfriend, Kyle T. Vadali, Srinivas R. Texas A and M University College Station TX 77843 United States The Math Works Inc. 3 Apple Hill Dr. Natick MA 01760 United States Aerospace Engineering Dept. Texas A and M University College Station TX 77843 United States

ISBN: (纸本)9781624101243

The objective of this work is to model and simulate the behavior of a new type of satellite system called the Power Sail. The Power Sail concept includes a large solar array, measuring 400m2, that is flown separately from the host satellite but connected via rigid links. The concept calls for two rigid links, which also act as power conduits, connected by a joint. The joint is modeled as being locked with some desired angle between the links. The attitude of the Power Sail system is controlled via thrusters located on the Power Sail solar panel. The natural motion of this system is found to be unstable in the desired nominal configuration. A control law is developed to maintain a desired reference attitude. To minimize reaction forces on the host satellite, a constant reference attitude with the center of mass located on the host orbit is found to be desirable. © 2002 by the author(s).

关键词： Orbits

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Trailing edge noise prediction based on a new acoustic formulation

Trailing edge noise prediction based on a new acoustic formu...

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8th aiaa/CEAS Aeroacoustics conference and exhibit, 2002

作者： Casper, J. Farassat, F. NASA Langley Research Center Computational Modeling and Simulation Branch Hampton VA 23681 United States NASA Langley Research Center Aeroacoustics Branch Hampton VA 23681 United States

ISBN: (纸本)9781624101199

A new analytic result in acoustics called "Formulation IB", proposed by Farassafc, is used to compute broadband trailing edge noise from an unsteady surface pressure distribution on a thin airfoil in the time domain. This formulation is a new solution of the Ffowcs Williams-Hawkings equation with the loading source term, and has been shown in previous research to provide time domain predictions of broadband noise that are in excellent agreement with experiment. Furthermore, this formulation lends itself readily to rotating reference frames and statistical analysis of broadband trailing edge noise. Formulation IB is used to calculate the far field noise radiated from the trailing edge of a NACA 0012 airfoil in low Mach number flows, using both analytical and experimental data on the airfoil surface. The results are compared to analytical results and experimental measurements that are available in the literature. Good agreement between predictions and measurements is obtained. © 2002 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Airfoils

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A six degree-of-freedom adaptive flight control architecture for trajectory following

A six degree-of-freedom adaptive flight control architecture...

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aiaa Guidance, Navigation, and Control conference and exhibit 2002

作者： Johnson, Eric N. Calise, Anthony J. School of Aerospace Engineering Georgia Institute of Technology Atlanta GA 30332 United States Guided Systems Technologies Inc McDonough GA 30253-1453 United States

ISBN: (纸本)9781624101083

For reusable launch vehicles, it is common to separate the guidance and flight control problem into an outer loop and an inner loop. The inner loop uses aerodynamic and propulsive controls to achieve a commanded attitude. The attitude commands are generated by an outer loop. This outer loop uses inner loop commands and control variables to achieve desired positions/velocities. This paper describes improvements and evaluation results for combined inner-outer loop adaptive flight control architecture for reusable launch vehicles. This architecture includes the online training of a neural network to correct for force and moment model errors. The result is a system that can respond to large model errors (significant failure scenarios) in both inner loop attitude control as well as in trajectory tracking. The resulting system can be used to improve performance and/or to increase guidance, navigation, and control system tolerance to model error, failures, and the environment. simulation results are presented for failure scenarios. © 2002 by the author(s).

关键词： Attitude control

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Performance of SCPS in complex networks

Performance of SCPS in complex networks

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20th aiaa International Communication Satellite Systems conference and exhibit, ICSSC 2002

作者： Edwards, E. Younghusband, C. Fodil-Lemelin, K. Bélisle, C. Peng, J. Phisel, M. Hartman, L. Xiphos Technologies Inc. Suite 800 3981 boul. St-Laurent Montreal QC H2W 1Y5 Canada Communications Research Centre 3701 Carling Ave. P.O. Box 11490 Station H Ottawa ON K2H 8S2 Canada Canadian Space Agency 6767 route de l'Aéroport Saint-Hubert QC J3Y 8Y9 Canada

ISBN: (纸本)9781624101113

In this paper, a new, high fidelity, independent implementation of the Transport Protocol of the Space Communication Protocol Specification (SCPS-TP) is presented and the measured performance over a satellite link is compared with emulated and simulated results. The simulation model is then employed to extrapolate a complex, multi-user, hybrid network scenario and estimate the performance potential. These results are discussed and the behaviour is compared against contemporary, state-of-the-art terrestrial TCP stacks. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Satellite links

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Slat cove noise modeling: A posteriori analysis of unsteady RANS simulations

Slat cove noise modeling: A posteriori analysis of unsteady ...

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8th aiaa/CEAS Aeroacoustics conference and exhibit, 2002

作者： Choudhari, Meelan Khorrami, Mehdi R. Lockard, David P. Atkins, Harold L. Lilley, Geoffrey M. Computational Modeling and Simulation Branch M.S. 128 NASA Langley Research Center Hampton VA 23681 United States Pennsylvania State University University Park PA 16802 United States

ISBN: (纸本)9781624101199

A companion paper by Khorrami et al[1] demonstrates the feasibility of simulating the (nominally) self-sustained, large-scale unsteadiness within the leading-edge slatcove region of multi-element airfoils using unsteady Reynolds-Averaged Navier-Stokes (URANS) equations, provided that the turbulence production term in the underlying two-equation turbulence model is switched off within the cove region. In conjunction with a FfowcsWilliams-Hawkings solver, the URANS computations in ref. [1] were shown to capture the dominant portion of the acoustic spectrum attributed to slat noise, as well as reproducing the increased intensity of slat cove motions (and, correspondingly, far-field noise as well) at the lower angles of attack. This paper examines that simulation database, augmented by additional simulations, with the objective of transitioning this apparent success to aeroacoustic predictions in an engineering context. As a first step towards this goal, the simulated flow and acoustic fields are compared with experiments[2-5] and simplified analytical models[6,7]. Rather intense near-field fluctuations in the simulated flow are found to be associated with unsteady separation along the slat bottom surface, relatively close to the slat cusp. Accuracy of the laminar-cove simulations in this near-wall region is raised to be an open issue. The adjoint Green's function approach is also explored in an attempt to identify the most efficient noise source locations. © 2002 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Acoustic fields

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