The Experts below are selected from a list of 6 Experts worldwide ranked by ideXlab platform
Michael J. Wilson - One of the best experts on this subject based on the ideXlab platform.
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Monopropellant Hydrazine Thrusters for Use on the Atlas Centaur Upper Stage During the Lunar Reconnaissance Orbiter (LRO) and Lunar Crater Observation and Sensing Satellite (LCROSS) Missions
2016Co-Authors: Jeffrey P Honse, Carl T Bangasser, Michael J. WilsonAbstract:This paper discusses a Delta-Qualification test of Aerojet’s 6 and 9 lbf monopropellant hydrazine MR-106 thrusters for use on the Atlas Centaur upper stage while operating in an atypical mode and for an extended period of time. This qualification testing was performed in support of the Lunar Reconnaissance Orbiter (LRO) and Lunar Crater Observation and Sensing Satellite (LCROSS) missions. The primary objective of the LCROSS mission is to determine the presence or absence of water ice in a permanently shadowed crater near a lunar polar region. The accomplishment of this objective requires that the Atlas V rocket’s Centaur upper stage perform a LCROSS orbit insertion as well as a fly-by of the moon before the Centaur upper stage crashes into a lunar crater to create a debris plume. The LCROSS Satellite will pass through the debris to collect and relay plume constituent data back to Earth. Prior to the LCROSS separation from the Centaur upper stage, the Centaur pneumatic pressurization system will transition from regulated to blow-down mode, which requires that the thrusters operate at a lower propellant feed pressure than had previously been qualified. Furthermore, the Lunar Reconnaissance Orbiter (LRO) will be launched simultaneously with LCROSS, requiring the Centaur stage to be responsible for additiona
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delta qualification test of aerojet 6 and 9 lbf mr 106 monopropellant hydrazine thrusters for use on the atlas centaur upper stage during the lunar reconnaissance orbiter lro and lunar crater observation and sensing Satellite LCROSS missions
45th AIAA ASME SAE ASEE Joint Propulsion Conference & Exhibit, 2009Co-Authors: Jeffrey P Honse, Carl T Bangasser, Michael J. WilsonAbstract:3Aerojet-General Corporation, Redmond, WA, 98052 This paper discusses a Delta-Qualification test of Aerojet’s 6 and 9 lbf monopropellant hydrazine MR-106 thrusters for use on the Atlas Centaur upper stage while operating in an atypical mode and for an extended period of time. This qualification testing was performed in support of the Lunar Reconnaissance Orbiter (LRO) and Lunar Crater Observation and Sensing Satellite (LCROSS) missions. The primary objective of the LCROSS mission is to determine the presence or absence of water ice in a permanently shadowed crater near a lunar polar region. The accomplishment of this objective requires that the Atlas V rocket’s Centaur upper stage perform a LCROSS orbit insertion as well as a fly-by of the moon before the Centaur upper stage crashes into a lunar crater to create a debris plume. The LCROSS Satellite will pass through the debris to collect and relay plume constituent data back to Earth. Prior to the LCROSS separation from the Centaur upper stage, the Centaur pneumatic pressurization system will transition from regulated to blow-down mode, which requires that the thrusters operate at a lower propellant feed pressure than had previously been qualified. Furthermore, the Lunar Reconnaissance Orbiter (LRO) will be launched simultaneously with LCROSS, requiring the Centaur stage to be responsible for additional maneuvers to position the LRO spacecraft on its correct trajectory. For a more typical mission, the Atlas V Centaur upper stage is not used after spacecraft separation. Since the Centaur upper stage will accompany the LCROSS Satellite to the moon, and because the Aerojet Rocket Engine Modules (REMs) that are installed on the Centaur upper stage will be partially responsible for performing the lunar trajectory maneuvers en route to the moon for both the LRO and LCROSS spacecrafts, additional life and low pressure operation beyond that which was qualified for the REMs was required. In June of 2008, DeltaQualification testing on an Aerojet MRM-106D Centaur REM successfully validated the engines’ capability of achieving these mission needs with margin.
Jeffrey P Honse - One of the best experts on this subject based on the ideXlab platform.
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Monopropellant Hydrazine Thrusters for Use on the Atlas Centaur Upper Stage During the Lunar Reconnaissance Orbiter (LRO) and Lunar Crater Observation and Sensing Satellite (LCROSS) Missions
2016Co-Authors: Jeffrey P Honse, Carl T Bangasser, Michael J. WilsonAbstract:This paper discusses a Delta-Qualification test of Aerojet’s 6 and 9 lbf monopropellant hydrazine MR-106 thrusters for use on the Atlas Centaur upper stage while operating in an atypical mode and for an extended period of time. This qualification testing was performed in support of the Lunar Reconnaissance Orbiter (LRO) and Lunar Crater Observation and Sensing Satellite (LCROSS) missions. The primary objective of the LCROSS mission is to determine the presence or absence of water ice in a permanently shadowed crater near a lunar polar region. The accomplishment of this objective requires that the Atlas V rocket’s Centaur upper stage perform a LCROSS orbit insertion as well as a fly-by of the moon before the Centaur upper stage crashes into a lunar crater to create a debris plume. The LCROSS Satellite will pass through the debris to collect and relay plume constituent data back to Earth. Prior to the LCROSS separation from the Centaur upper stage, the Centaur pneumatic pressurization system will transition from regulated to blow-down mode, which requires that the thrusters operate at a lower propellant feed pressure than had previously been qualified. Furthermore, the Lunar Reconnaissance Orbiter (LRO) will be launched simultaneously with LCROSS, requiring the Centaur stage to be responsible for additiona
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delta qualification test of aerojet 6 and 9 lbf mr 106 monopropellant hydrazine thrusters for use on the atlas centaur upper stage during the lunar reconnaissance orbiter lro and lunar crater observation and sensing Satellite LCROSS missions
45th AIAA ASME SAE ASEE Joint Propulsion Conference & Exhibit, 2009Co-Authors: Jeffrey P Honse, Carl T Bangasser, Michael J. WilsonAbstract:3Aerojet-General Corporation, Redmond, WA, 98052 This paper discusses a Delta-Qualification test of Aerojet’s 6 and 9 lbf monopropellant hydrazine MR-106 thrusters for use on the Atlas Centaur upper stage while operating in an atypical mode and for an extended period of time. This qualification testing was performed in support of the Lunar Reconnaissance Orbiter (LRO) and Lunar Crater Observation and Sensing Satellite (LCROSS) missions. The primary objective of the LCROSS mission is to determine the presence or absence of water ice in a permanently shadowed crater near a lunar polar region. The accomplishment of this objective requires that the Atlas V rocket’s Centaur upper stage perform a LCROSS orbit insertion as well as a fly-by of the moon before the Centaur upper stage crashes into a lunar crater to create a debris plume. The LCROSS Satellite will pass through the debris to collect and relay plume constituent data back to Earth. Prior to the LCROSS separation from the Centaur upper stage, the Centaur pneumatic pressurization system will transition from regulated to blow-down mode, which requires that the thrusters operate at a lower propellant feed pressure than had previously been qualified. Furthermore, the Lunar Reconnaissance Orbiter (LRO) will be launched simultaneously with LCROSS, requiring the Centaur stage to be responsible for additional maneuvers to position the LRO spacecraft on its correct trajectory. For a more typical mission, the Atlas V Centaur upper stage is not used after spacecraft separation. Since the Centaur upper stage will accompany the LCROSS Satellite to the moon, and because the Aerojet Rocket Engine Modules (REMs) that are installed on the Centaur upper stage will be partially responsible for performing the lunar trajectory maneuvers en route to the moon for both the LRO and LCROSS spacecrafts, additional life and low pressure operation beyond that which was qualified for the REMs was required. In June of 2008, DeltaQualification testing on an Aerojet MRM-106D Centaur REM successfully validated the engines’ capability of achieving these mission needs with margin.
Carl T Bangasser - One of the best experts on this subject based on the ideXlab platform.
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Monopropellant Hydrazine Thrusters for Use on the Atlas Centaur Upper Stage During the Lunar Reconnaissance Orbiter (LRO) and Lunar Crater Observation and Sensing Satellite (LCROSS) Missions
2016Co-Authors: Jeffrey P Honse, Carl T Bangasser, Michael J. WilsonAbstract:This paper discusses a Delta-Qualification test of Aerojet’s 6 and 9 lbf monopropellant hydrazine MR-106 thrusters for use on the Atlas Centaur upper stage while operating in an atypical mode and for an extended period of time. This qualification testing was performed in support of the Lunar Reconnaissance Orbiter (LRO) and Lunar Crater Observation and Sensing Satellite (LCROSS) missions. The primary objective of the LCROSS mission is to determine the presence or absence of water ice in a permanently shadowed crater near a lunar polar region. The accomplishment of this objective requires that the Atlas V rocket’s Centaur upper stage perform a LCROSS orbit insertion as well as a fly-by of the moon before the Centaur upper stage crashes into a lunar crater to create a debris plume. The LCROSS Satellite will pass through the debris to collect and relay plume constituent data back to Earth. Prior to the LCROSS separation from the Centaur upper stage, the Centaur pneumatic pressurization system will transition from regulated to blow-down mode, which requires that the thrusters operate at a lower propellant feed pressure than had previously been qualified. Furthermore, the Lunar Reconnaissance Orbiter (LRO) will be launched simultaneously with LCROSS, requiring the Centaur stage to be responsible for additiona
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delta qualification test of aerojet 6 and 9 lbf mr 106 monopropellant hydrazine thrusters for use on the atlas centaur upper stage during the lunar reconnaissance orbiter lro and lunar crater observation and sensing Satellite LCROSS missions
45th AIAA ASME SAE ASEE Joint Propulsion Conference & Exhibit, 2009Co-Authors: Jeffrey P Honse, Carl T Bangasser, Michael J. WilsonAbstract:3Aerojet-General Corporation, Redmond, WA, 98052 This paper discusses a Delta-Qualification test of Aerojet’s 6 and 9 lbf monopropellant hydrazine MR-106 thrusters for use on the Atlas Centaur upper stage while operating in an atypical mode and for an extended period of time. This qualification testing was performed in support of the Lunar Reconnaissance Orbiter (LRO) and Lunar Crater Observation and Sensing Satellite (LCROSS) missions. The primary objective of the LCROSS mission is to determine the presence or absence of water ice in a permanently shadowed crater near a lunar polar region. The accomplishment of this objective requires that the Atlas V rocket’s Centaur upper stage perform a LCROSS orbit insertion as well as a fly-by of the moon before the Centaur upper stage crashes into a lunar crater to create a debris plume. The LCROSS Satellite will pass through the debris to collect and relay plume constituent data back to Earth. Prior to the LCROSS separation from the Centaur upper stage, the Centaur pneumatic pressurization system will transition from regulated to blow-down mode, which requires that the thrusters operate at a lower propellant feed pressure than had previously been qualified. Furthermore, the Lunar Reconnaissance Orbiter (LRO) will be launched simultaneously with LCROSS, requiring the Centaur stage to be responsible for additional maneuvers to position the LRO spacecraft on its correct trajectory. For a more typical mission, the Atlas V Centaur upper stage is not used after spacecraft separation. Since the Centaur upper stage will accompany the LCROSS Satellite to the moon, and because the Aerojet Rocket Engine Modules (REMs) that are installed on the Centaur upper stage will be partially responsible for performing the lunar trajectory maneuvers en route to the moon for both the LRO and LCROSS spacecrafts, additional life and low pressure operation beyond that which was qualified for the REMs was required. In June of 2008, DeltaQualification testing on an Aerojet MRM-106D Centaur REM successfully validated the engines’ capability of achieving these mission needs with margin.