NASA's Second Generation Reusable Launch Vehicle Program advances propulsion technology with successful engine test series
NASA's Second Generation Reusable Launch Vehicle Program - also known as the Space Launch Initiative - is making advances in propulsion technology with this third and final successful engine hot-fire designed to test electro-mechanical actuators.
Information learned from this hot-fire test series about new electro-mechanical actuator technology - which controls the flow of propellants in rocket engines - could provide key advancements for the propulsion systems of future spacecraft.
The test of twin Linear Aerospike XRS-2200 engines, originally built for the X-33 program, was performed Monday, Aug. 6, at NASA's Stennis Space Center, Miss. The engines were fired for the planned 90-seconds and reached a planned maximum power of 85 percent.
The test was originally slated to attain full-power during 100-seconds of testing. Prior to the test, engineers determined the necessary results could be achieved at reduced duration and power. Based on this determination, both planned duration and planned power were reduced.
Two shorter hot-fires of the aerospike engines were performed last month in preparation for the final test firing on Aug. 6.
The Second Generation Reusable Launch Vehicle Program, led by NASA's Marshall Space Flight Center in Huntsville, Ala., is a technology development program designed to increase safety and reliability while reducing costs for space travel.
"Because every engine proposed by industry for a second generation vehicle has electro-mechanical actuators, we took advantage of these aerospike engines already on the test stand to explore this relatively new technology now -- saving us valuable time later," said Garry Lyles, Propulsion Projects Office manager of the Second Generation Reusable Launch Vehicle Program at the Marshall Center. "This data is critical toward developing the confidence required to support the use of these actuators on future launch vehicles."
Electro-mechanical actuators electronically regulate the amount of propellant (fuel and oxidizer) flow in the engine. The new technology is a potential alternative and improvement to the older pneumatic and hydraulic-fluid systems currently used by the aerospace industry to drive and control critical rocket engine valves.
NASA's Second Generation Reusable Launch Vehicle Program - also known as the Space Launch Initiative - is making advances in propulsion technology with this third and final successful engine hot-fire designed to test electro-mechanical actuators.
Information learned from this hot-fire test series about new electro-mechanical actuator technology - which controls the flow of propellants in rocket engines - could provide key advancements for the propulsion systems of future spacecraft.
The test of twin Linear Aerospike XRS-2200 engines, originally built for the X-33 program, was performed Monday, Aug. 6, at NASA's Stennis Space Center, Miss. The engines were fired for the planned 90-seconds and reached a planned maximum power of 85 percent.
The test was originally slated to attain full-power during 100-seconds of testing. Prior to the test, engineers determined the necessary results could be achieved at reduced duration and power. Based on this determination, both planned duration and planned power were reduced.
Two shorter hot-fires of the aerospike engines were performed last month in preparation for the final test firing on Aug. 6.
The Second Generation Reusable Launch Vehicle Program, led by NASA's Marshall Space Flight Center in Huntsville, Ala., is a technology development program designed to increase safety and reliability while reducing costs for space travel.
"Because every engine proposed by industry for a second generation vehicle has electro-mechanical actuators, we took advantage of these aerospike engines already on the test stand to explore this relatively new technology now -- saving us valuable time later," said Garry Lyles, Propulsion Projects Office manager of the Second Generation Reusable Launch Vehicle Program at the Marshall Center. "This data is critical toward developing the confidence required to support the use of these actuators on future launch vehicles."
Electro-mechanical actuators electronically regulate the amount of propellant (fuel and oxidizer) flow in the engine. The new technology is a potential alternative and improvement to the older pneumatic and hydraulic-fluid systems currently used by the aerospace industry to drive and control critical rocket engine valves.
