The Future and Way Forward for the Aerodynamic and Propulsion Test Unit

Smith, Chris; Garrard, Doug; Jackson, Frank

doi:10.2514/6.2006-8049

Cited by 16 publications

(2 citation statements)

References 4 publications

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“…Since 2001 the DOD and AEDC have invested in multiple upgrades to APTU specifically to support ground testing of HS/H ABP systems (Ref. 2). Two upgrades have been previously completed.…”

Section: Introductionmentioning

confidence: 99%

Checkout Testing of the New Basic Process Control System at the Aerodynamic and Propulsion Test Unit

Garrard¹,

Vaughn²,

Milhoan³

et al. 2012

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference

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This paper describes the test campaign conducted to support the final development and activation of the new Aerodynamic and Propulsion Test Unit (APTU) Basic Process ControlSystem (BPCS). The testing was conducted in two phases. Cold flow tests were conducted to define the installed effective area of the individual flow control valves as a function of the valve's percentage open. Cold flow tests were also used to demonstrate the safe, reliable, and effective operation of the BPCS and facility before initiating hot flow tests. Hot flow tests were then used to demonstrate full operation of the APTU with the new BPCS. Three supersonic and hypersonic Mach number freejet nozzles were used during the checkout tests. Cold and hot runs were intermixed between the different nozzles due to operational constraints on various hardware components. The new BPCS has been shown to provide significantly improved control over the previous control system by maintaining flow rates to within .5% of steady-state set point value and within 2% of set point values during flight representative facility transients. The new control system is now operational and is being used to support test customers.

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“…Since 2001 the DOD and AEDC have invested in multiple upgrades to APTU specifically to support ground testing of HS/H ABP systems (Ref. 2). Two upgrades have been previously completed.…”

Section: Introductionmentioning

confidence: 99%

Checkout Testing of the New Basic Process Control System at the Aerodynamic and Propulsion Test Unit

Garrard¹,

Vaughn²,

Milhoan³

et al. 2012

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference

Self Cite

View full text Add to dashboard Cite

show abstract

“…There is also a design for a hypersonic propulsion test capability (HPTC) that would utilize a "fly the mission" flexible-walled freejet nozzle to simulate transient flight from Mach 2.8 to above Mach 5 during a single run. 1 The HPTC project is currently on hold while APTU supports the current work load and until funding can be allocated. The CAH uses combustion to generate the total temperature (T t ) and total pressure (P t ) required to accurately simulate high-speed and hypersonic flight in the atmosphere.…”

Section: Introductionmentioning

confidence: 99%

Hypersonic Ground Testing Combustion Air Heater Ignition Optimization via Design of Experiments

Vaughn

Garrard

Landman

2012

28th Aerodynamic Measurement Technology, Ground Testing, and Flight Testing Conference

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This paper describes the ignition optimization of the Aerodynamic and Propulsion TestUnit's (APTU) combustion air heater (CAH) with a fixed-area ratio (AR) nozzle installed. During a recent facility upgrade to a new Basic Process Control System (BPCS), the facility incorporated an improved capability to set parameters for ignition at various levels. However, CAH ignition reliability with a fixed-AR nozzle used during checkout was significantly lower than that demonstrated with the previous control system. A project was established to study, improve, and demonstrate reliability with the new control system. As a part of the study, key factors were identified for the ignition process. The CAH owner's manual described high and low settings for two parameters, delta pressure (DP) across the fuel injectors and CAH chamber pressure (psia). With the new BPCS the facility could easily and repeatably set these parameters at various levels within the high and low ranges for ignition. The historical data from the previous control system ignition process were reviewed, analyses were completed for the process with the new control system, and control measures for noise that may affect ignition were identified and implemented. From the results of the study, a design of experiment (DOE) checkout matrix was created and executed. During execution the results were analyzed and the matrix was modified to narrow in on the high probability for ignition region. Post-DOE testing, the results were analyzed and optimized, and parameter settings were selected. Ignition reliability of the CAH with the fixed-AR nozzle was verified to be greater than 90% with 80% confidence through the execution of consecutive successful ignition sequences at those settings. NomenclatureAEDC = Arnold Engineering Development Center APTU = Aerodynamic Propulsion Test Unit BPCS = Basic Process Control System BUT = Isobutane CAH = Combustion Air Heater CCD = Central Composite Design DOE = Design of Experiments DP = Delta Pressure FAN = Fixed-Area Ratio Nozzle FCV = Flow Control Valve FCD = Face-Centered Design FINJ = Fuel Injectors GH2 = Gaseous Hydrogen

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A reduced theoretical model for estimating condensation effects in combustion-heated hypersonic tunnel

et al. 2017

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The Future and Way Forward for the Aerodynamic and Propulsion Test Unit

Cited by 16 publications

References 4 publications

Checkout Testing of the New Basic Process Control System at the Aerodynamic and Propulsion Test Unit

Checkout Testing of the New Basic Process Control System at the Aerodynamic and Propulsion Test Unit

Hypersonic Ground Testing Combustion Air Heater Ignition Optimization via Design of Experiments

A reduced theoretical model for estimating condensation effects in combustion-heated hypersonic tunnel

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