Visualization of Jettison Motor Plumes from an Orion Launch Abort Vehicle Wind Tunnel Model Using Background-Oriented Schlieren

Reinholtz, Carrie; Heltsley, F L; Scott, Kenneth E.; Afb, Arnold; Rhode, Matthew N.

doi:10.2514/6.2010-1736

Cited by 9 publications

(6 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Unlike the traditional schlieren method however, the BOS technique does not require any optical devices on the transmitting side. 17 A diagram of the BOS technique is shown in Fig. 1.…”

Section: A Background Oriented Schlierenmentioning

confidence: 99%

“…[8][9][10] The BOS method has been used to visualize large field-of-view flows in applications ranging from on-site industrial HVAC systems to short-duration shock tunnel facilities. [11][12][13][14] Reinholtz et al utilized a pseudo-random pattern of manually stamped 3/16" black dots on retro-reflective paint in the AEDC's 16-ft transonic tunnel. 11 The constant diameter dot sizing corresponded to 3-5 pixel diameter dots when imaged allowing for sub pixel accuracy, while variable density gradient magnitudes in separate regions of the flow required a variation in interrogation window sizing.…”

Section: Technical Backgroundmentioning

confidence: 99%

“…[11][12][13][14] Reinholtz et al utilized a pseudo-random pattern of manually stamped 3/16" black dots on retro-reflective paint in the AEDC's 16-ft transonic tunnel. 11 The constant diameter dot sizing corresponded to 3-5 pixel diameter dots when imaged allowing for sub pixel accuracy, while variable density gradient magnitudes in separate regions of the flow required a variation in interrogation window sizing. BOS has furthermore found an application in the visualization of short-duration, hypersonic flow-fields through the work of Kirmse et al 12 A laser speckle pattern generated by the background illumination of ground glass was used as a background pattern to visualize the shock layer of a 160mm diameter sphere in flows of M = 8.1 with total enthalpies ranging from 12MJ/kg to 22MJ/kg.…”

Section: Technical Backgroundmentioning

confidence: 99%

See 2 more Smart Citations

Visualization of Shock Train-Boundary Layer Interaction in Mach 2.5 Isolator Flow

Geerts

2013

43rd Fluid Dynamics Conference

View full text Add to dashboard Cite

Interaction between turbulent boundary layer and slowly moving oblique shock train was investigated in a long constant-area duct, simulating Mach 2.5 isolator flow experimentally. Two different types of schlieren techniques were employed to visualize the unsteady interaction while measuring the corresponding wall pressure on the top and bottom. For visualizing the entire length of the isolator, a background oriented schlieren (BOS) technique was customized and implemented in the present study. The flow-field images were then compared with those obtained from a conventional schlieren technique. The correlated results elucidated the relationship between shock train movement and evolving pressure gradient, which caused boundary layer separation immediately downstream of the shock train. The paper contains not only the time-resolved schlieren images corresponding to various pressure data but it also describes the optimization of the background pattern and the implementation of the BOS for the current experiment.

show abstract

“…Unlike the traditional schlieren method however, the BOS technique does not require any optical devices on the transmitting side. 17 A diagram of the BOS technique is shown in Fig. 1.…”

Section: A Background Oriented Schlierenmentioning

confidence: 99%

Section: Technical Backgroundmentioning

confidence: 99%

Section: Technical Backgroundmentioning

confidence: 99%

See 1 more Smart Citation

Visualization of Shock Train-Boundary Layer Interaction in Mach 2.5 Isolator Flow

Geerts

2013

43rd Fluid Dynamics Conference

View full text Add to dashboard Cite

show abstract

“…Schröder (2009, 2010) investigated a propeller slipstream wake geometry and Bencs et al (2011) the wake of a heated cylinder. Reinholtz et al (2010) investigated jettison motor plumes from an Orion launch abort vehicle model and Wolf et al (2012) rocket model near-wakes. As optical flow diagnostics are frequently used for research on turbines for aero-engines and power generation, BOS is also useful in this field.…”

Section: Bos Applications In Complex Facilitiesmentioning

confidence: 99%

Background-oriented schlieren (BOS) techniques

2015

View full text Add to dashboard Cite

“…An example image from Test 24-AA is shown in Figure 21. 12 A standard schlieren system was used for Test 25-AA, with images acquired using a high-resolution digital video camera for both single image "stills" and video clips. An example image from Test 25-AA is given in Figure 22.…”

Section: Testing and Data Reductionmentioning

confidence: 99%

Aerodynamic Testing of the Orion Launch Abort Tower Separation with Jettison Motor Jet Interactions (Invited)

Rhode

Chan

Niskey³

et al. 2011

29th AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

The aerodynamic database for the Orion Launch Abort System (LAS) was developed largely from wind tunnel tests involving powered jet simulations of the rocket exhaust plumes, supported by computational fluid dynamics (CFD) simulations. The LAS contains three solid rocket motors used in various phases of an abort to provide propulsion, steering, and Launch Abort Tower (LAT) jettison from the Crew Module (CM). This paper describes a pair of wind tunnel experiments performed at transonic and supersonic speeds to determine the aerodynamic effects due to proximity and jet interactions during LAT jettison from the CM at the end of an abort. The tests were run using two different scale models at angles of attack from 150° to 200°, sideslip angles from -10° to +10°, and a range of powered thrust levels from the jettison motors to match various jet simulation parameters with flight values. Separation movements between the CM and LAT included axial and vertical translations as well as relative pitch angle between the two bodies. The paper details aspects of the model design, nozzle scaling methodology, instrumentation, testing procedures, and data reduction. Sample data are shown to highlight trends seen in the results.

show abstract

Visualization of Jettison Motor Plumes from an Orion Launch Abort Vehicle Wind Tunnel Model Using Background-Oriented Schlieren

Cited by 9 publications

References 1 publication

Visualization of Shock Train-Boundary Layer Interaction in Mach 2.5 Isolator Flow

Visualization of Shock Train-Boundary Layer Interaction in Mach 2.5 Isolator Flow

Background-oriented schlieren (BOS) techniques

Aerodynamic Testing of the Orion Launch Abort Tower Separation with Jettison Motor Jet Interactions (Invited)

Contact Info

Product

Resources

About