Aerodynamic separation and glideback of a Mach 3 staged booster

Naftel, J. C.; Powell, Richard W.

doi:10.2514/6.1990-223

Cited by 15 publications

(13 citation statements)

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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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“…More recently, Naftel et al considered staging of two wing-body vehicles. [8][9][10] NASA's interest in stage separation research was renewed in early 2000 when it was realized that the technologies needed for the development of a next generation, reusable single-stage-to-orbit vehicle were not yet available and focus shifted to multi-stage launch vehicles. Subsequently, NASA's Next Generation Launch Technology (NGLT) Program identified stage separation as one of the critical technologies needed for successful development and operation of next generation multi-stage reusable launch vehicles.…”

Section: Introductionmentioning

confidence: 99%

Constraint Force Equation Methodology for Modeling Multi-Body Stage Separation Dynamics

Toniolo

Tartabini

Pamadi

et al. 2008

46th AIAA Aerospace Sciences Meeting and Exhibit

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This paper discuses a generalized approach to the multi-body separation problems in a launch vehicle staging environment based on constraint force methodology and its implementation into the Program to Optimize Simulated Trajectories II (POST2), a widely used trajectory design and optimization tool. This development facilitates the inclusion of stage separation analysis into POST2 for seamless end-to-end simulations of launch vehicle trajectories, thus simplifying the overall implementation and providing a range of modeling and optimization capabilities that are standard features in POST2. Analysis and results are presented for two test cases that validate the constraint force equation methodology in a stand-alone mode and its implementation in POST2.

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Aerodynamic separation and glideback of a Mach 3 staged booster

Cited by 15 publications

References 0 publications

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

Constraint Force Equation Methodology for Modeling Multi-Body Stage Separation Dynamics

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