Activation Testing and Lessons Learned During the Aerodynamic and Propulsion Test Unit Upgrade

Garrard, Doug; Bates, Brent L.; Rigney, Sharon

doi:10.2514/6.2006-2953

Cited by 7 publications

(3 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The pressure and temperature limits provide for a Mach 8 capability. 4 The various primary and secondary subsystems of APTU are shown in Fig. 1.…”

Section: A the Aptu Facilitymentioning

confidence: 99%

“…Secondary systems include the high-pressure water system for cooling hardware and the gaseous hydrogen system for igniting the fuel and air in the combustion air heater. 4 After the combustion air heater, the gases are mixed in a stilling chamber and are typically expanded through a freejet nozzle and into the test cell. However, the MSCC test program will be using three direct-connect nozzles.…”

Section: A the Aptu Facilitymentioning

confidence: 99%

See 1 more Smart Citation

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

2014

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

View full text Add to dashboard Cite

Advanced ground-test facilities such as the Aerodynamic and Propulsion Test Unit (APTU) at the Arnold Engineering Development Complex (AEDC) require advanced, stateof-the-art, high-speed control systems to operate safely and robustly. Given the unique nature in which APTU and other blowdown test facilities operate, a high-fidelity transient facility math model and computer simulation is integrated into the new APTU control system to verify hardware operation and test sequence logic before each run. AEDC invested in a new control system and facility simulation for APTU in 2009. With the upcoming Medium Scale Critical Components (MSCC) direct-connect test program, additional improvements and additions will be required to support the direct-connect testing of the medium scale scramjet propulsion systems. This paper will document the enhancements to various fluid models and routines to calculate selected facility performance parameters. The new requirements imposed on the control system and facility model due to the installation of a new heated fuel system will be described.

show abstract

“…The pressure and temperature limits provide for a Mach 8 capability. 4 The various primary and secondary subsystems of APTU are shown in Fig. 1.…”

Section: A the Aptu Facilitymentioning

confidence: 99%

Section: A the Aptu Facilitymentioning

confidence: 99%

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

2014

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

View full text Add to dashboard Cite

show abstract

“…APTU is a blowdown freejet test facility designed to provide a simulated, true pressure and temperature flight environment for missile scale hardware operating at velocities up to approximately Mach 8 (Ref. 1). Since 2001 the DOD and AEDC have invested in multiple upgrades to APTU specifically to support ground testing of HS/H ABP systems (Ref.…”

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

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.

show abstract

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

Smith

Garrard

Jackson

2006

14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

View full text Add to dashboard Cite

Activation Testing and Lessons Learned During the Aerodynamic and Propulsion Test Unit Upgrade

Cited by 7 publications

References 1 publication

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)

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)

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

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

Contact Info

Product

Resources

About