Upgrades to the Aerodynamic and Propulsion Test Unit Facility Control System and Simulator in Support of the Medium Scale Critical Components Direct Connect Test Program (Invited)

Boylston, Brett

doi:10.2514/6.2014-2766

Cited by 8 publications

(4 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…A comparable model was introduced by Köcke et al [18] and Bolk et al [19], which allows for research on test specimen-ATF interactions and the resulting effects on the engine performance [10]. Moreover, this foundation is utilized to develop and test the sequence logic of modern ATF control concepts [20][21][22]. However, the one-dimensional and quasi-steady-state nature of the simulation with simplifications like constant parameters and assumptions for loss coefficients and efficiencies is accompanied by shortcomings in accurately representing the facility response, as highlighted by Sheeley et al [17].…”

Section: Introductionmentioning

confidence: 99%

Asymmetric Flow Phenomena Affecting the Characterization of the Control Plant of an Altitude Test Facility for Aircraft Engines

Roth,

Hartmann,

Schiewe

et al. 2023

Symmetry

View full text Add to dashboard Cite

As an indispensable part of the engine manufacturer supply chain, the eco-efficiency of altitude test facility (ATF) operations must improve. Automation is a key enabler in this context since it not only increases precision and reproducibility but also allows for reducing the test time and energy consumption. A suitable controller and reliable validation are crucial to ensure the stability and appropriate response of the control system. Both aspects necessitate a thorough understanding of the control plant, expressed in a numerical model. These models have to be suitable for control system design and validation while covering asymmetric flow phenomena that occur in the pipe system and detailing the nonlinear system dynamics to a high degree of accuracy. One-dimensional network models, state-space models, highly resolving numerical models, and data-driven models are relevant applications for this task. We compare the results of state-of-the-art one-dimensional network models which mainly imply symmetric flow conditions with those of three-dimensional Reynolds-averaged-Navier–Stokes (RANS) simulations which cover asymmetric flow phenomena. The findings show that the assumptions of idealized, axis-symmetric flow in the one-dimensional flow elements do not hold true for the complex flows in an altitude test facility. In a second step, we have compared the results of one-dimensional simulations with in-service measurements taken during ATF test campaigns. Deviations were observed, which become explainable based on the insights gained from the comparison with the RANS simulation. The findings reveal that the one-dimensional simulation-based approach is insufficient to adequately reflect the plant and subsequently for validation due to the observed asymmetric flow phenomena. To overcome this limitation, the application of an empirical first-order transfer function using system identification methods is proposed. Its applicability is successfully demonstrated for the exhaust gas section of the ATF. Subsequently, essential criteria for the design of a suitable control concept for the outlet condition are derived.

show abstract

Section: Introductionmentioning

confidence: 99%

Asymmetric Flow Phenomena Affecting the Characterization of the Control Plant of an Altitude Test Facility for Aircraft Engines

Roth,

Hartmann,

Schiewe

et al. 2023

Symmetry

View full text Add to dashboard Cite

show abstract

“…[4][5][6][7] This paper addresses a new heated fuel system designed to supply superheated hydrocarbon fuel to a medium scale scramjet engine at APTU. This system is meant to simulate the heating of fuel through cooling passages along the interior and exterior surfaces of a scramjet-powered flight vehicle.…”

Section: Introductionmentioning

confidence: 99%

Activation and Calibration Plans for the Aerodynamic and Propulsion Test Unit Heated Fuel System (Invited)

Holst

2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

View full text Add to dashboard Cite

As part of the upgrades required to support the Medium Scale Critical Components (MSCC) program testing, an existing high-temperature and high-pressure heated fuel system (HFS) at the Aerodynamic and Propulsion Test Unit (APTU) is being modified and upgraded to provide endothermic heated fuel to scramjet propulsion test systems. This paper will briefly address the overall requirements for the new HFS and the overall design of the system. The paper will then discuss the activation and calibration plans for the HFS. Operational processes will be generally described. Various system shutdown parameters will be identified, and the resulting processes used to protect the system hardware will be documented. Particular attention will be given to the calibration of the mass-flow rate measurement instrumentation used to provide a high-fidelity calculation of the fuel mass flow entering the test engine. NomenclatureAEDC = Arnold Engineering Development Complex APTU = Aerodynamic and Propulsion Test Unit C f = venturi flow coefficient C v = valve flow coefficient DARPA = Defense Advanced Research Projects Agency FCV = flow control valve FDS = fuel distribution system GN2 = gaseous nitrogen HFS = heated fuel system MSCC = Medium Scale Critical Components NIST = National Institute of Standards and Technology PCV = pressure control valve

show abstract

“…[4][5][6][7] This paper focuses on the HFS upgrade project that was set up and funded jointly by AFRL and AEDC to increase the HFS's capability. The project was scoped to meet the needs of the MSCC test program as follows:…”

Section: Introductionmentioning

confidence: 99%

Upgrades to the Aerodynamic and Propulsion Test Unit Heated Fuel System (Invited)

Butler

2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

View full text Add to dashboard Cite

As part of the upgrades required to support the Medium Scale Critical Components (MSCC) program testing, an existing high-temperature and high-pressure heated fuel system at the Aerodynamic and Propulsion Test Unit (APTU) is being modified and upgraded to provide endothermic heated fuel to scramjet propulsion test systems. This paper will address the overall requirements for the new fuel heater system and then discuss the multiple upgrades. The mechanical design will be discussed with comparisons to the previous system. The new control system will be discussed along with the installed instrumentation. Finally, upgrades to the electrical power supply system at APTU will be discussed. NomenclatureAEDC = Arnold Engineering Development Complex AFRL = Air Force Research Laboratory AN = Army/Navy fitting (37° flare fitting standard) APTU = Aerodynamic Propulsion Test Unit ASME = American Society of Mechanical Engineers CAH = combustion air heater DARPA = Defense Advanced Research Projects Agency DOD = Department of Defense DPU = digital processing unit dP = delta pressure FaCET = Falcon Combined Cycle Engine Test FCS = Facility Control System FCV = flow control valve FDS = Fuel Delivery System FRS = Fuel Recovery System ft = feet ft 3 = cubic feet GN2 = gaseous nitrogen HFS = Heated Fuel System HMI = human machine interface HS/H = high-speed/hypersonic kV = kilovolt lbm = pounds mass MPa = megapascal MSCC = Medium-Scale Critical Components MW = megawatt NFPA = National Fire Protection Association PCV = pressure control valve PID = proportional-integral-derivative PLC = programmable logic controller psia = pounds per square inch absolute 2 Approved for public release; distribution unlimited. psig = pounds per square inch gage psid = pounds per square inch differential s = second T&E = Test and Evaluation

show abstract

Upgrades to the Aerodynamic and Propulsion Test Unit Facility Control System and Simulator in Support of the Medium Scale Critical Components Direct Connect Test Program (Invited)

Cited by 8 publications

References 8 publications

Asymmetric Flow Phenomena Affecting the Characterization of the Control Plant of an Altitude Test Facility for Aircraft Engines

Asymmetric Flow Phenomena Affecting the Characterization of the Control Plant of an Altitude Test Facility for Aircraft Engines

Activation and Calibration Plans for the Aerodynamic and Propulsion Test Unit Heated Fuel System (Invited)

Upgrades to the Aerodynamic and Propulsion Test Unit Heated Fuel System (Invited)

Contact Info

Product

Resources

About