mech anisms were al so performe d afte r ran dom vib ration testin g and o peration perform ed in a the rmal  vacuum with exposure to p redicted hot a nd col d extre mes.   

System Level  Testing   In orde r to e nsure that th e CBM de sign woul d wo rk co rrectly for all of the different a pplications o n ISS,  including the different p ressure an d thermal enviro nments it wo uld see during berthing operations, thre e  phases of system level testing we re pe rformed. 

Phase ‘A’ testing develo ped the t hermal profile s and se aling capabilities of the CBM in variou s  config uratio ns and conditi ons. A set o f thermal b alance test s were p erformed on full-scal e CBM te st  article s at the  Arnold Engi neerin g Test Center So lar Simulation Te st Chamb er in Tullahom a, Tenne ssee.   Therm al data  obtained allowed valid ation of thermal model s for e stablishing qualificatio n testing the rmal  conditions. Full-Scale Seal  Tests validat ed the se aling ability of th e CBM at various d eflecte d and therm al  conditions. 

Phase  ‘B’ im plemente d six deg ree of freedom  (Six-DOF ) testing  to validate th e captu re dynamic an alysis  and d etermi ne the captu re envelop e. Ini tial con ditions were established which p laced the Pa ssive half in   orientatio ns (lateral offset, roll offs et an d pitch (wob ble) offset ) to the Active half  in orde r to e stablish the   captu re envelope. Capture latch o perat ions were pe rformed to pull the Passive h alf to the Active half into  the po sition  for which bolti ng operation s would begin. Initial testin g was perform ed on the Marshall Space  Flight Ce nter (MSFC) Six-DOF tabl e. A Six-DOF re sistive load sy stem wa s dev elope d and pl aced into the  20-foot va cuum ch amber at the MSFC facility. Follow on ambi ent and va cuum six -DOF  testing was  perfo rmed, e stablishing the initial con dition paramete rs for the follo w on Pha se C testing. 

Phase ‘C ’ te sting  culmin ated in  the CB M  performing complete   berthin g op eration s at  deflecte d condition s of  the Active a nd Pa ssive  halves,  therm ally  conditioned  (hot active /   cold p assive, hot  passive / cold  active), at  sets of initial conditions,   based on Phase  B  testing,  thro ugh  compl ete ca pture  and  prelo ading events an d  perfo rmed a t vacuum.   This test set up was  perfo rmed  in the sa me  6-m (2 0-ft) va cuum  cham ber as the Pha se  B tes ting wit h the SixDOF resistiv e load syste m. The test setup i s shown in Figure 4. The sepa rate pre ssure vessels i n the  vacuum chamber in duced the pre ssure defle ction s to each CBM interface. Pressu re deflection s were  based off of ISS pressuri zed modul e structural testin g and validat ed FE M anal ysis. Lea k rate testing wa s  perfo rmed  to ensure  the sealed  joint was l eak tight. Compl ete de-berthin g operations were p erform ed to  validate all the function al requireme nts.  Active Pressure FixturePassive Pressure FixtureV20 Chambe r in MSFC 4619 Resistive Load System L egs (6) Mass Offload  Rail/Carri age System Figure 4.  CBM As sembl y Level Qualification Te st Fixtur e

Flight Article Acce ptance Testing   With all com ponent s install ed and integ rated in the fli ght config uration on the ISS pressu rized module, a  stand alone acceptan ce test of the  CBM is pe rform ed. Th e standalon e test is performed at ambie nt  conditions to assure the i ntegrate d CBM is satisfa ctorily configu red prior to turno ver for inte grated testin g  305