Executes functions associated with the management and implementation of integration and test (I&T) activities for space flight projects. Provides remote field support at other NASA centers or contractor facilities for flight project logisitics, payload integration, qualification and performance testing, launch activities, initial engineering and research elements during the fabrication, assembly, integration, inspection, functional checkout, developmental testing, environmental qualification testing, and cleanliness certification testing, complex end-to-end system performance testing, and operations of aerospace flight and ground support systems. Support includes: precision prototype machining, assembly, and integration of aerospace flight systems; preparation of technical specifications, integration and checkout procedures; development of test verification plans and test procedures; performance of environmental testing at LaRC facilities or oversight of such test at remote locations; and, management of overall project I&T activities. Enables world class research and systems development by maintaining and operating ground test and support facilities and equipment such as: electromagnetic compatibility and interference test complex; thermal-vacuum space simulation chambers and thermal cycling equipment; vibration shaker machines, dynamic shock equipment, load test equipment, mass property measurement devices and field modal testing and analysis systems; class 100 clean rooms; high bay assembly area; bonded and controlled stores areas; potentially hazardous materials test facility; fluid system testing equipment; and, electronic systems interface and controls development lab.
The Flight Systems, Systems Integration and Test Laboratories (Building 1250) consist of laboratories and equipment used to qualify components, subsystems, and small payloads for atmospheric and space flight. The facility include several thermal vacuum chambers for temperature/ pressure testing and space simulation, three dynamic shakers, mass properties equipment, and a large structural backstop for vibration and load testing and modal analysis, and class 100 and class 10,000 clean rooms for system preparations. The laboratory is staffed by engineering and technical support personnel and uses other specialized support resources such as a chromatographic analysis lab to perform cleanliness evaluations, electronics support for data acquisition and reduction, fluids lab for heat exchanger development, and mechanical support for test fixture design and fabrication.
The 8-by 15-foot, 6-by 6-foot, and 5-by 5-foot thermal vacuum chambers are capable of simulating altitude and thermal environments to orbital conditions. Vacuum levels of 10-7 torr are attainable with large capacity cryogenic pumps. Thermal shrouds and quartz heater arrays are computer controlled to maintain precise control of complex thermal profiles about user selectable locations from -300 to 1000 degrees Fahrenheit. These facilities meet stringent cleanliness criteria for space flight hardware as documented by Temperature-controlled Quartz Crystal Microbalance (TQCM) readings of less than 1 Hz/hour over a 12-hour period. They are also equipped with Residual Gas Analyzers (RGA) and cryogenic scavenger plates to monitor and identify contamination spectra and quality. A number of electrical and fluid penetrations are available to accommodate testing needs. Class 100 portable downflows provide clean areas for final hardware preparation prior to payload insertion into test chamber. Three thermal vacuum bell jars are able to accommodate components up to approximately 1 cubic foot. Each has a cryogenic pumping system, conductive and radiative heat sources and cold plates, and computerized control and data acquisition systems.
The vibration test lab is equipped to perform vibration testing, modal testing, modal analysis, and center of gravity and moment of inertia characterization of aerospace components, subsystems, small payloads, and facilities. Vibration capability consists of three dynamic shakers (3000, 17000, and 34000 force-pound), sharing a common control and data acquisition system. The dynamic shakers are used to qualify payload performance by simulating expected mission acceleration forces. Control software enables the application of complex frequency/amplitude spectra such as sine, random, shock, and various combinations of these spectra as required. Rotatable armatures, fixture cubes, head expanders, and slippery tables permit adaptation to a variety of payload shapes and sizes and enables testing in three axes. Equipment (structural backstops and 256 channel portable system) and trained personnel are available to conduct comprehensive modal analysis to identify resonant characteristics of complex systems and structures. Instruments relating to the identification of mass properties are available to accurately determine center of gravity and moment of inertia of structures weighing up to 1320 pounds. Forced-limited test capability available beginning in Fall 2001.
Clean rooms
available for space flight projects include: a conventional class 10,000
(conditionally operated as a class 100) vertical turbulent flow clean room,
37 by 40 by 26 hook height; a class 100 horizontal laminar flow clean
room, 14 by 33; and, a class 100 vertical laminar flow clean room, 15
by 24. All clean rooms are certified in accordance with U.S. Federal Standard
209E and are equipped with particle counters for constant monitoring of
air cleanliness.
Cleanliness
Measurement Lab
performs spectroscopic,
microscopic and gravimetric measurements and analyses of spaceflight hardware,
vacuum facilities and cleanrooms. Radiated thermal response measurements
for test and flight hardware. Chemical analyses of organic films, contamination
and particles are also characterized per MIL STD 1246D.
The Semi-Anechoic Electromagnetic Compatibility Test Complex (Building 1220) provides environment for pre-qualification electromagnetic compatibility (EMC) testing for spaceflight and aeronautics flight hardware. Provides for radiated emissions, radiated susceptibility, conducted emissions, and conducted susceptibility testing as per MIL STD-461 for spaceflight hardware and RTCA-DO-160 for aeronautics hardware. Semi-anechoic, fully welded, shielded test chamber (performance of 120 dB up to 40 GHz) meets FCC 3-meter chamber requirements. 9m x 6m x 5.5m test chamber with 2-meter turntable and filtered power (DC, 60 Hz, 400 HZ), and two shielded control rooms.