The X-43A Six Degree of Freedom Monte Carlo Analysis

Baumann, Ethan; Bahm, Catherine; Strovers, Brian K.; Beck, Roger; Richard, Michael

doi:10.2514/6.2008-203

Cited by 38 publications

(22 citation statements)

References 11 publications

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“…With the historic 2004 scramjet-powered Mach 7 and 10 flights of the X-43A [1][2][3][4] , hypersonics research has seen a resurgence. This is attributable to the fact that air-breathing hypersonic propulsion is viewed as the next critical step toward achieving (1) reliable, affordable, routine access to space, as well as (2) global reach vehicles.…”

Section: Motivationmentioning

confidence: 99%

See 1 more Smart Citation

Elevator Sizing, Placement, and Control-Relevant Tradeoffs for Hypersonic Vehicles

Dickeson

Rodriguez

Sridharan

et al. 2010

AIAA Guidance, Navigation, and Control Conference

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Within this paper, control-relevant vehicle design concepts are examined using a widely used 3 DOF (plus flexibility) nonlinear model for the longitudinal dynamics of a generic carrot-shaped scramjet powered hypersonic vehicle. The impact of elevator size and placement on control-relevant static properties (e.g. level-flight trimmable region, trim controls, AOA, thrust margin) and dynamic properties (e.g. instability and right half plane zero associated with flight path angle) are examined. Elevator usage has been examine for a class of typical hypersonic trajectories.

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Section: Motivationmentioning

confidence: 99%

“…This paper focuses on control challenges associated with scramjet-powered hypersonic vehicles. Such vehicles are characterized by significant aerothermo-elastic-propulsion interactions and uncertainty [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17] .…”

Section: Motivationmentioning

confidence: 99%

Elevator Sizing, Placement, and Control-Relevant Tradeoffs for Hypersonic Vehicles

Dickeson

Rodriguez

Sridharan

et al. 2010

AIAA Guidance, Navigation, and Control Conference

View full text Add to dashboard Cite

Within this paper, control-relevant vehicle design concepts are examined using a widely used 3 DOF (plus flexibility) nonlinear model for the longitudinal dynamics of a generic carrot-shaped scramjet powered hypersonic vehicle. The impact of elevator size and placement on control-relevant static properties (e.g. level-flight trimmable region, trim controls, AOA, thrust margin) and dynamic properties (e.g. instability and right half plane zero associated with flight path angle) are examined. Elevator usage has been examine for a class of typical hypersonic trajectories.

show abstract

Section: Motivationmentioning

confidence: 99%

Section: Motivationmentioning

confidence: 99%

Control-Relevant Modeling, Analysis, and Design for Scramjet-Powered Hypersonic Vehicles

Rodriguez

Dickeson

Sridharan

et al. 2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

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Within this paper, control-relevant vehicle design concepts are examined using a widely used 3 DOF (plus flexibility) nonlinear model for the longitudinal dynamics of a generic carrot-shaped scramjet powered hypersonic vehicle. Trade studies associated with vehicle/engine parameters are examined. The impact of parameters on control-relevant static properties (e.g. level-flight trimmable region, trim controls, AOA, thrust margin) and dynamic properties (e.g. instability and right half plane zero associated with flight path angle) are examined. Specific parameters considered include: inlet height, diffuser area ratio, lower forebody compression ramp inclination angle, engine location, center of gravity, and mass. Vehicle optimizations is also examined. Both static and dynamic considerations are addressed. The gap-metric optimized vehicle is obtained to illustrate how this controlcentric concept can be used to "reduce" scheduling requirements for the final control system. A classic inner-outer loop control architecture and methodology is used to shed light on how specific vehicle/engine design parameter selections impact control system design. In short, the work represents an important first step toward revealing fundamental tradeoffs and systematically treating control-relevant vehicle design.

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“…This is because random variations in input uncertainties can interact with each other in unexpected and potentially detrimental manner. Such an analysis was performed for the Hyper-X Program to simulate the dynamics of the X-43A vehicle (Baumann et al, 2007). figure. During the second stage burn, thrust is much greater than drag.…”

Section: Dispersionmentioning

confidence: 99%

Test Program for a Dual-mode Scramjet

Smayda¹

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Since flow at hypersonic Mach numbers (M≥5) behaves very differently from flow at subsonic or supersonic Mach numbers, the testing of hypersonic engines involves challenges not encountered in engine testing for flight in other regimes. For hypersonic Mach numbers, thermal, chemical, radiative, and ablative effects become important.Energy and heat transfer considerations make continuous-run, full scale testing at hypersonic Mach numbers difficult or impossible. While facilities have been devised specifically to study certain aspects of hypersonic flight, no single facility has the ability to simulate all the flow conditions that a hypersonic vehicle or engine may encounter.Flight can be considered the ultimate test of a hypersonic vehicle or engine because no facility effects are present. It is often the case, however, that budgetary, thermal, structural, or other logistical limitations restrict the range of diagnostics available for flight vehicle testing. Flight programs also incur significant risk that is generally not present or is significantly reduced for ground testing programs. If an unguided rocket is used to minimize cost, the likelihood that the payload will achieve the desired test conditions decreases. If a reactive control system is utilized to increase the likelihood that the payload will achieve the desired test conditions, both complexity and cost increase significantly. As such, flight programs are nearly always augmented with significant ground testing to reduce risk and confirm engine operability limits. Often a range of wind tunnels is used in order to resolve the inherent deficiencies of any one type of ground test facility. Two common shortcomings of hypersonic test facilities are the short test time associated with shock-heated facilities and the contaminated or vitiated test gas associated with combustion-heated facilities.

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The X-43A Six Degree of Freedom Monte Carlo Analysis

Cited by 38 publications

References 11 publications

Elevator Sizing, Placement, and Control-Relevant Tradeoffs for Hypersonic Vehicles

Elevator Sizing, Placement, and Control-Relevant Tradeoffs for Hypersonic Vehicles

Control-Relevant Modeling, Analysis, and Design for Scramjet-Powered Hypersonic Vehicles

Test Program for a Dual-mode Scramjet

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