Evans, Richard K.

Hill, Gerald M.

Kudlac, Maureen T.

Maloney, Christian T.

Weaver, Harold F.

NASA Technical Reports Server

National Aeronautics and Space Administration
www.nasa.gov
NASA Plum Brook Station Spacecraft Propulsion Research Facility (B–2)
The largest hydrogen-compatible thermal vacuum
test facility in the United States.
The world’s largest space simulations facility
capable of full-scale rocket engine and stage testing.
https://ntrs.nasa.gov/search.jsp?R=20110016530 2019-08-30T17:47:28+00:00Z
LG–2011–03–022–GRC
RJC
2005
CD-05-82817
Hydrogen/Oxygen Rocket 
Test Capability With Vacuum Start
•	30K	lbf	thrust	engine	for	400	sec	test	duration
•	100K	lbf	thrust	engine	for	270	sec	test	duration
•	300K	lbf	thrust	engine	for	15	sec	test	duration
Space Simulation
B–2’s	test	chamber	is	capable	of	reproducing	space 
environment	temperatures	and	vacuum.
Vacuum	pressure	 5x10–7	torr
LN2	chamber	temperature	 –320	°F		
Infrared	radiation	intensity	 130	W/ft2 
Control and Data Systems
•	Test	operations	are	controlled	by	a	fully
	 redundant	computerized	control	system	via	a
	 remote	control	room	located	2400	ft	from	the
	 test	site.
•	A	state-of-the-art	data	acquisition	system
	 records	all	parameters	associated	with	the
	 test.		Features	include	600	channels	at	direct
	 current	to	1	kHz	per	channel	and	a	high-speed
	 system	capability	up	to	115	kHz	per	channel.
Spray Chamber
•	67	ft	diameter	by	120	ft	deep	underground
	 chamber	holds	1.7	million	gallons	of	chilled	water.
•	Four	2000-hp	water	pumps	recirculate
	 224,000	gal	of	chilled	water	per	minute	to
	 condense	engine	exhaust.
•	Three	propellant	dump	tanks	are	available	for
	 enhanced	safety.
Electrical Systems
Facility	is	rated	Class	1,	Div.	2,	Group	B	to	enable	
testing	of	hydrogen/oxygen	propellant	systems.
Test Chamber Facts
Test	chamber	 38	ft	diameter	by	65	ft	tall
Test	volume	 33	ft	diameter	by	55	ft	tall
Top	access	opening	 27	ft	diameter
Liquid	nitrogen	(LN2)	is	used	in	the	chamber’s
interior	cold	wall	to	simulate	the	low	temperatures
of	space.	Infrared	lamps	simulate	solar	heating.
 
Exhaust Systems
Two	three-stage	intercondensing	steam	ejector	
trains	remove	rocket	exhaust	during	hot	fire	tests	
and	maintain	the	spray	chamber	vacuum
environment.
B–2 Facility Capability Summary
*	All	values	are	approximate	and	for	reference	only.
PS–00466–0511


NASA Plum Brook Station Spacecraft Propulsion Research Facility (B-2): An Innovative Multi-Purpose Test Facility

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