Executive Summary of Propulsion on the Orion Abort Flight-Test Vehicles

Jones, Daniel S.; Koelfgen, Syri; Barnes, Marvin W.; McCauley, Rachel; Wall, Terry; Reed, Brian D.; Duncan, C. Miguel

doi:10.2514/6.2012-3891

Cited by 2 publications

(2 citation statements)

References 3 publications

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“…The AM provided a maximum thrust of approximately 5 x 10 5 lbf. 5 The JM was a solid rocket motor with four scarfed nozzles canted at 35° from the motor centerline. The JM was intended to pull the LAS away from the CM.…”

Section: A Pa-1 Vehicle Descriptionmentioning

confidence: 99%

“…The JM was capable of producing a maximum thrust of approximately 4.0 x 10 4 lbf. 5 The ACM was a solid rocket motor with eight radially spaced, throttled nozzles placed at 45° increments symmetrically about the LAS centerline. The ACM provided directional control for the LAS and provided approximately 6.5 x 10 3 lbf of commanded omnidirectional thrust during the first 7 s of flight, followed by 2.5 x 10 3 lbf of commanded omnidirectional thrust during the next 20 s of flight.…”

Section: A Pa-1 Vehicle Descriptionmentioning

confidence: 99%

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Analysis and Results from a Flush Airdata Sensing System in Close Proximity to Firing Rocket Nozzles

Ali

Borrer

2013

AIAA Atmospheric Flight Mechanics (AFM) Conference

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This paper presents information regarding the nosecap Flush Airdata Sensing (FADS) system on Orion's Pad Abort 1 (PA-1) vehicle. The purpose of the nosecap FADS system was to test whether or not useful data could be obtained from a FADS system if it was placed in close proximity to firing rocket nozzles like the Attitude Control Motor (ACM) nozzles on the PA-1 Launch Abort System. The nosecap FADS system used pressure measurements from a series of pressure ports which were arranged in a cruciform pattern and flush with the surface of the vehicle to estimate values of angle of attack, angle of sideslip, Mach number, impact pressure, and freestream static pressure. This paper will present the algorithms employed by the FADS system along with the development of the calibration datasets and a comparison of the final results to the Best Estimated Trajectory (BET) data for PA-1. Also presented in this paper is a Computational Fluid Dynamics (CFD) study to explore the impact of the ACM on the nosecap FADS system. The comparison of the nosecap FADS system results to the BET and the CFD study showed that more investigation is needed to quantify the impact of the firing rocket motors on the FADS system.

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Section: A Pa-1 Vehicle Descriptionmentioning

confidence: 99%

Section: A Pa-1 Vehicle Descriptionmentioning

confidence: 99%

Analysis and Results from a Flush Airdata Sensing System in Close Proximity to Firing Rocket Nozzles

Ali

Borrer

2013

AIAA Atmospheric Flight Mechanics (AFM) Conference

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Conceptual Design for a Dual-Bell Rocket Nozzle System Using a NASA F-15 Airplane as the Flight Testbed

Jones¹,

Ruf²,

Bui³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The dual-bell rocket nozzle was first proposed in 1949, offering a potential improvement in rocket nozzle performance over the conventional-bell nozzle. Despite the performance advantages that have been predicted, both analytically and through static test data, the dual-bell nozzle has still not been adequately tested in a relevant flight environment. In 2013 a proposal was constructed that offered a National Aeronautics and Space Administration (NASA) F-15 airplane as the flight testbed, with the plan to operate a dual-bell rocket nozzle during captive-carried flight. If implemented, this capability will permit nozzle operation into an external flow field similar to that of a launch vehicle, and facilitate an improved understanding of dual-bell nozzle plume sensitivity to external flow-field effects. More importantly, this flight testbed can be utilized to help quantify the performance benefit with the dual-bell nozzle, as well as to advance its technology readiness level. Toward this ultimate goal, this paper provides plans for future flights to quantify the external flow field of the airplane near the nozzle experiment, as well as details on the conceptual design for the dual-bell nozzle cold-flow propellant feed system integration within the NASA F-15 Propulsion Flight Test Fixture. The current study shows that this concept of flight research is feasible, and could result in valuable flight data for the dual-bell nozzle. NomenclatureACN = altitude-compensating nozzle AFRC = Armstrong Flight Research Center (Edwards, California) AoA = angle of attack CB = conventional-bell CCIE = Channeled Centerbody Inlet Experiment CDE = Cone Drag Experiment CFD = computational fluid dynamics COPV = composite overwrapped pressure vessel DOF = degrees-of-freedom GN 2 = gaseous nitrogen I sp = specific impulse LEO = low-Earth orbit LMI = Local Mach Investigation MEOP = maximum expected operating pressure MSFC = Marshall Space Flight Center (Huntsville, Alabama) 2 NASA = National Aeronautics and Space Administration NNPR = normalized nozzle pressure ratio NPR = nozzle pressure ratio (P c /P amb ) NTF = Nozzle Test Facility OML = outer mold line P amb = ambient pressure P c = nozzle chamber pressure PFTF = Propulsion Flight Test Fixture PRA = pressure reducing assembly RAGE = Rake Airflow Gage Experiment RFS = rocket forebody simulator SSME = Space Shuttle Main Engine STS = Space Transportation System TRL = technology readiness level

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Executive Summary of Propulsion on the Orion Abort Flight-Test Vehicles

Abstract: The NASA Orion Flight Test Office was tasked with conducting a series of flight tests in several launch abort scenarios to certify that the Orion Launch Abort System is capable of delivering astronauts aboard the Orion Crew Module to a safe environment, away from a failed booster.

Cited by 2 publications

References 3 publications

Analysis and Results from a Flush Airdata Sensing System in Close Proximity to Firing Rocket Nozzles

Analysis and Results from a Flush Airdata Sensing System in Close Proximity to Firing Rocket Nozzles

Conceptual Design for a Dual-Bell Rocket Nozzle System Using a NASA F-15 Airplane as the Flight Testbed

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