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Lunar-landing rocket research hits milestone with “hot-fire” test

Wed, 08/13/2014 - 8:00am
Emil Venere, Purdue Univ.

Purdue students have conducted the first "hot-fire" test of the rocket, which uses liquid oxygen and liquid methane propellants. The students have designed, built and tested a central part of the new engine—called the thrust chamber or combustor—as part of NASA's Project Morpheus. Image: Purdue Univ./Maurice J. Zucrow LaboratoriesA Purdue Univ. student team has designed, built and tested a critical part of a new a rocket engine as part of a NASA project to develop spacecraft technologies needed to land on the moon, Mars and other cosmic venues.

The students are making a central part of the new engine—called the thrust chamber or combustor—as part of NASA's Project Morpheus. The project aims to develop a prototype vehicle capable of vertical takeoff and landing using an autonomous system.

Such a system requires a high-performance, lightweight rocket engine, said Michael Bedard, a Purdue propulsion engineer and doctoral student.

The Purdue team in May conducted its first "hot-fire" test of the rocket, which uses liquid oxygen and liquid methane propellants. The rocket's thrust chamber was designed, built and tested using specialized facilities at Purdue's Maurice J. Zucrow Laboratories.

The work began as a senior design project in 2010, initiated by students in a propulsion course taught by William Anderson, a professor in Purdue's School of Aeronautics and Astronautics.

"The students worked amazingly hard on this and were committed to finishing it," Anderson said. "It was a pretty remarkable feat."

Students not only developed the engine's thrust chamber, but also a system to liquefy methane from methane gas.

"By liquefying our own methane, we reduced the propellant cost and challenges in transporting the propellant," said Bedard, who led efforts to continue the work after completing the senior design project.

The research paper was authored by Bedard, Anderson and graduate students Eric Meier and William Hallum.

The eventual goal of the project is to build a lightweight thrust chamber, which requires a thin-walled combustor. Having a thin wall makes it essential to properly cool all of the chamber surfaces, particularly portions that heat up the most. The recent test focused on measuring the "temperature profile" of the thrust chamber wall.

"Propellants burning in the chamber result in extreme temperatures along the chamber walls," Bedard said. "To cool the chamber effectively we need to know exactly where the cooling must be applied. Temperatures inside the combustor can approach 5,000 F. The engine has to run for about two minutes at a time, so keeping the walls cool is critical. The data we are getting from these tests will help us design an optimized cooling approach.”

Source: Purdue Univ.

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