6 ---------A~g~e~n~d_a ~~~~~ BEAM Project Overview ~ • BEAM Sensor System Overview • Current State of BEAM Sensor Systems • Future Plans & Summary Q&A & 2 6 --=Eiiiiii!!l!!!!!B_EA_M_P-=r=-o-~e_c_tO ~ve_rv_ie_w _ _ • What is Bigelow Expandable Activity Module (BEAM)? • https://yout .b~/VopaBsuwikk • The Bigelow Expandable Activity Module (BEAM) is an expandable habitat technology demonstration on ISS. - • Increase human-rated inflatable structure Technology Readiness Level (TRL) to level 9. • NASA managed ISS payload project in partnership with Bigelow Aerospace. • Launched to ISS on Space X 8 (April Sth, 2016). • Fully expanded on May 28th, 2016. • Jeff Williams/Exp. 48 Commander first entered_B EAM on June 5th, 2016. - °"'.) • I Timeline pictures of BEAM expansion 3 Artist rendition of BEAM attached to Node 3 Aft BEAM Project Overview 7 hours of deployment in 25 seconds with a sample of audio including RSS popping ... 4 BEAM Project Overview BEAM IMV Duct Soft Goods (SG) Assembly Anomalous Depressurization and Stabilization System (ADSS) struts (x4) Flight Support Equipment (x6) Shear Panel (x8) PCBM to Bulkhead Tunnel Adapter Aft Bulkhead BEAM Hatch __, ____, Air Tanks (x8) 5 B_E_A~Mi!!!!!!!!!P!!!!!!!!!!!!!!!r!!!!!50!!!!!J!!!!.!! !!!!!!m _o_v_er~vie!!!!!w!!!51 e_c_t __ • ___ • First use of inflatable module in ISS or any manned space program. • Inflatable structures provide more useable volume per launch mass vs. traditional rigid modules. • BEAM was compressed 4 times its expansion volume in the Space X Dragon trunk. • NASA desires engineering data on Bigelow module deployment and on orbit operation: • deployment dynamics (NASA Pl - M. Grygier) • thermal performance (NASA Pl - J. lovine/W. Walker) • debris impact monitoring (NASA Pl - Dr. E. Madaras) • radiation monitoring (NASA Pl - DR. D. Fry) • Flight-heritage sensor systems will be adapted to collect this data requires new interfacing hardware (cables, etc.) and longer-life battery power and data acquisition system modifications 6 • A pre-flight MM/OD impact detection system feasibility assessment involved performing a variety of tests to ensure the sensor system could be installed onto the softgoods material and detect an imoact response. •Tests included: •Instrumented tap testing of DTI inflatable for screening sensor attachment method and standalone data acquisition testing •Pull-testing of sensor attachment method to softgoods material •Wiring/DAO hardware attachment mechanism inside of module •Hypervelocity Impact Testing with representative coupon of softgoods material w/MM/OD shielding NASA provided inflatable module for initial sensor sys em •RF communications testing feasibility assessment which was NOT part of the BEAM project. 7 inside of the module 6 Hypervelocity Impact (HVI) Testing Accomplishments • • Demonstrated that the system recorded signal matched accurately with a calibrated data acquisition system at WSTF. • Verified that adhesive attachment method for accelerometers to smooth surfaces (Bladder) survives HVI impacts. • Velocity behavior of the restraint layer was determined (Anisotropic effects and speed of sound measured). • Most of these HVI tests did not reach the restraint layer, and instead were captured by the shielding layers. Since the shielding system was resting on the restraint layer in these tests, the momentum from those impacts did transfer into the restraint layer via the foam coupling. 8 BEAM Sensor System Overview l l I I I I I ! I I I I I I I I 11 • I I I ' .L l?~P oyn;ier~ Da~a: Ret!iev~I: pr~~itju~ ~se I D1stnbuted Impact Detects structural Installed pre-launch RF to SSC ISS Ultrasonic Detection System impacts to BEAM •4 transducers on the (closed hatch) Background Noise (DIDS) bulkheads Test SOTO Installed on orbit: •12 transducers on the soft goods •sensor boxes Deployment Records acceleration 3 DDS units and triax1al USB to SSC Shuttle Wing Dynamics Sensors loads during inflation accelerometers are (BEAM ingress) Leading Edge (DDS) stage installed prelaunch accelerometers and Crew Seat OTO Wireless Temperature Monitors temperature 4 WTS units Installed RFtC"J SSC Shuttle Wireless Senso~ (WTS) of BEAM surface on-orbit (qty 4 RTD (closed hatch) Strain Gauge (IVA) channels each) Instrumentation System Radiation Monitors radiation 2 REM Installed on-orbit USBtoSSC REM SOTO Environment Monitor environment internal (closed hatch) (REM) to the BEAM structure Radiation Area Passive radiation 6 RAMs Installed on- Replaced and Monitor (RAM) monitoring badges orbit returned to ground every Soyuz vehicle cycle 6 • Eiiiiiiiiiiiiiiii!!i!ll!liEiiiiiiiiiiiiiii!!iE!!llB~E_AM_s_e_n-=s-o-r-S-y!5s!!!t!-e_m_o_v_e_rv_ie_w!!§!E1!!!!!!5ii1!!!!5E!!5-- WTS DIDS I'~ 'i \ ,.._ '· .. • ~ 111 REM RAM DDS