Analysis of separation of a two-stage winged launch vehicle

Naftel, J. C.; Wilhite, Alan W.; Cruz, Christopher I.

doi:10.2514/6.1986-195

Cited by 18 publications

(12 citation statements)

References 1 publication

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“…System analysis studies continued to examine two-stage, fully reusable systems. 12,13 Following the accidental loss of the Shuttle Challenger on ascent in 1986, a focused program employing experimental and system analysis tools was initiated to look at Shuttle Orbiter boost-phase abort scenarios, i.e. separation of the orbiter from the external tank on ascent.…”

Section: Previous Workmentioning

confidence: 99%

Experimental Stage Separation Tool Development in NASA Langley's Aerothermodynamics Laboratory

Murphy

Scallion

2005

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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As part of the research effort at NASA in support of the stage separation and ascent aerothermodynamics research program, proximity testing of a generic bimese wing-body configuration was conducted in NASA Langley's Aerothermodynamics Laboratory in the 20-Inch Mach 6 Air Tunnel. The objective of this work is the development of experimental tools and testing methodologies to apply to hypersonic stage separation problems for future multi-stage launch vehicle systems. Aerodynamic force and moment proximity data were generated at a nominal Mach number of 6 over a small range of angles of attack. The generic bimese configuration was tested in a belly-to-belly and back-to-belly orientation at 86 relative proximity locations. Over 800 aerodynamic proximity data points were taken to serve as a database for code validation. Longitudinal aerodynamic data generated in this test program show very good agreement with viscous computational predictions. Thus a framework has been established to study separation problems in the hypersonic regime using coordinated experimental and computational tools.

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Section: Previous Workmentioning

confidence: 99%

Experimental Stage Separation Tool Development in NASA Langley's Aerothermodynamics Laboratory

Murphy

Scallion

2005

AIAA Atmospheric Flight Mechanics Conference and Exhibit

View full text Add to dashboard Cite

show abstract

“…System analysis studies continued to examine two-stage, fully reusable systems. 9,10 Following the accidental loss of the Shuttle Challenger on ascent in 1986, a focused program employing experimental and system analysis tools was initiated to look at Shuttle Orbiter boost-phase abort scenarios, i.e. separation of the orbiter from the external tank on ascent.…”

Section: Previous Workmentioning

confidence: 99%

Overview of Transonic to Hypersonic Stage Separation Tool Development for Multi-Stage-To-Orbit Concepts

Murphy

Buning

Pamadi

et al. 2004

24th AIAA Aerodynamic Measurement Technology and Ground Testing Conference

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An overview of research efforts at NASA in support of the stage separation and ascent aerothermodynamics research program is presented. The objective of this work is to develop a synergistic suite of experimental, computational, and engineering tools and methods to apply to vehicle separation across the transonic to hypersonic speed regimes. Proximity testing of a generic bimese wing-body configuration is on-going in the transonic (Mach numbers 0.6, 1.05, and 1.1), supersonic (Mach numbers 2.3, 3.0, and 4.5) and hypersonic (Mach numbers 6 and 10) speed regimes in four wind tunnel facilities at the NASA Langley Research Center. An overset grid, Navier-Stokes flow solver has been enhanced and demonstrated on a matrix of proximity cases and on a dynamic separation simulation of the bimese configuration. Steady-state predictions with this solver were in excellent agreement with wind tunnel data at Mach 3 as were predictions via a Cartesian-grid Euler solver. Experimental and computational data have been used to evaluate multi-body enhancements to the widely-used Aerodynamic Preliminary Analysis System, an engineering methodology, and to develop a new software package, "SepSim," for the simulation and visualization of vehicle motions in a stage separation scenario. Web-based software will be used for archiving information generated from this research program into a database accessible to the user community. Thus, a framework has been established to study stage separation problems using coordinated experimental, computational, and engineering tools.

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“…Also, the simulation did not include the attachment between the stages and the release mechanism. Recent NASA studies by Naftel et al [8][9][10] consider Mach 3 staging of two winged vehicles. They modeled the attachment of stages, the release mechanism in their simulations and used active control during separation but their aerodynamic data did not include the mutual interference effects.…”

Section: Introductionmentioning

confidence: 99%

Simulation and Analyses of Stage Separation of Two-Stage Reusable Launch Vehicles

Pamadi

Neirynck

Hotchko

et al. 2007

Journal of Spacecraft and Rockets

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NASA has initiated the development of methodologies, techniques and tools needed for analysis and simulation of stage separation of next generation reusable launch vehicles. As a part of this activity, ConSep simulation tool is being developed which is a MATLAB-based front-and-back-end to the commercially available ADAMS ‚ solver, an industry standard package for solving multi-body dynamic problems. This paper discusses the application of ConSep to the simulation and analysis of staging maneuvers of two-stage-to-orbit (TSTO) Bimese reusable launch vehicles, one staging at Mach 3 and the other at Mach 6. The proximity and isolated aerodynamic database were assembled using the data from wind tunnel tests conducted at NASA Langley Research Center. The effects of parametric variations in mass, inertia, flight path angle, altitude from their nominal values at staging were evaluated. Monte Carlo runs were performed for Mach 3 staging to evaluate the sensitivity to uncertainties in aerodynamic coefficients.

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Analysis of separation of a two-stage winged launch vehicle

Cited by 18 publications

References 1 publication

Experimental Stage Separation Tool Development in NASA Langley's Aerothermodynamics Laboratory

Experimental Stage Separation Tool Development in NASA Langley's Aerothermodynamics Laboratory

Overview of Transonic to Hypersonic Stage Separation Tool Development for Multi-Stage-To-Orbit Concepts

Simulation and Analyses of Stage Separation of Two-Stage Reusable Launch Vehicles

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