Issue 10 Volume 41 May 16, 2003

Bipropellant propulsion systems currently represent the largest bus subsystem for many missions. These missions range
from low Earth orbit satellite to geosynchronous communications and planetary exploration. The payoff of high performance
bipropellant systems is illustrated by the fact that Aerojet Redmond has qualified a commercial NTO/MMH engine based on
the high Isp technology recently delivered by this program. They are now qualifying a NTO/hydrazine version of this engine.
The advanced rhenium thrust chambers recently provided by this program have raised the performance of earth storable
propellants from 315 sec to 328 sec of specific impulse. The recently introduced rhenium technology is the first new
technology introduced to satellite propulsion in 30 years. Typically, the lead time required to develop and qualify new chemical
thruster technology is not compatible with program development schedules. These technology development programs must be
supported by a long term, Base R&T Program, if the technology s to be matured. This technology program then addresses the
need for high performance, storable, on-board chemical propulsion for planetary rendezvous and descent/ascent. The primary
NASA customer for this technology is Space Science, which identifies this need for such programs as Mars Surface Return,
Titan Explorer, Neptune Orbiter, and Europa Lander. High performance (390 sec) chemical propulsion is estimated to add
105\% payload to the Mars Sample Return mission or alternatively reduce the launch mass by 33\%. In many cases, the use
of existing (flight heritage) propellant technology is accommodated by reducing mission objectives and/or increasing enroute
travel times sacrificing the science value per unit cost of the program. Therefore, a high performance storable thruster utilizing
fluorinated oxidizers with hydrazine is being developed.
Derived from text
Chemical Propulsion; Liquid Rocket Propellants; Storable Propellants; Technology Utilization; NASA Programs
20030033102 Air Force Research Lab., Edwards AFB, CA, USA
High Performance Hall System Info for AIAA Short Course to be Taught by Roger Myers of Primex
McFall, Keith; July 08, 1998; 3 pp.; In English
Contract(s)/Grant(s): F04611-97-C-0064; AF Proj. 4373
Report No.(s): AD-A410592; AFRL/PRS-AFRL-PR-ED-TP-1998-123; No Copyright; Avail: CASI; A01, Hardcopy
The USA Air Force’s Air Force Research Laboratory is supporting the development and ground demonstration of a 4.5
kW class Hall Effect Thruster propulsion system under the Integrated High Payoff Rocket Propulsion Technology (IHPRPT)
program. Flight derivatives of this system will be applicable to orbit raising, station-keeping, and maneuvering applications.
The High Performance Hall System (HPHS) program, a four-year effort begun in September 1997, is projected to meet the
Phase I IHPRPT spacecraft goal of improving total impulse over wet mass by 20\%. The jointly funded government/industry
effort includes the qualification of a flight-like thruster and power processing unit, and an integrated system demonstration.
The contractor team is lead by Atlantic Research Corporation and includes International Space Technology Incorporated Space
Systems/Loral, and Engineering Design Bureau/Fakel.
DTIC
Rocket Propellants; Propulsion
20030033104 Air Force Research Lab., Edwards AFB, CA, USA
Advanced Expander Combustor (AEC) Hot Firing Test Results
Fentress, Steve; Cooley, Christine; Spero, Eric; January 28, 2002; 5 pp.; In English
Contract(s)/Grant(s): F04611-95-C-0123; AF Proj. 1011
Report No.(s): AD-A410589; AFRL/PRS-AFRL-PR-ED-AB-2002-016; No Copyright; Avail: CASI; A01, Hardcopy
This paper summarizes the test results of a full scale copper tubular combustion chamber for application in a high thrust
Upper Stage Expander Cycle Engine. The chamber was developed by Pratt & Whitney Liquid Space Propulsion under contract
for the USA Air Force Research Laboratory (AFRL). The Advanced Expander Copper Tubular Combustor (AEC) was hot fire
tested on Pratt & Whitney’s E8 component test facility in July 2001 and demonstrated the necessary heat load capacity and
coolant pressure drop characteristics to support future high thrust expander engine applications.
DTIC
Combustion Chambers; Liquid Propellant Rocket Engines; Engine Tests; Test Firing
20030033861 Air Force Research Lab., Edwards AFB, CA, USA
High Performance Hall Thruster Ground Demo
Fife, John M.; Sep. 1999; 16 pp.; In English
Contract(s)/Grant(s): F04611-97-C-0064; AF Proj. 4373
Report No.(s): AD-A410320; AFRL-PR-ED-TP-FY99-0182; No Copyright; Avail: CASI; A03, Hardcopy
No abstract available
Hall Thrusters; Spacecraft Propulsion; Technology Utilization; Electric Rocket Engines; Propulsion System Performance
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