Timed Launch Operations Applied Physics Laboratory-Books Pdf

TIMED Launch Operations Applied Physics Laboratory
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TIMED LAUNCH OPERATIONS, was monitored at 30 min intervals. by APL spacecraft personnel using, portable oxygen monitors to ensure. crew safety During these monitor, ing activities the nitrogen ow. rates and purity of the purge system, were also checked and the data. Upon arrival at VAFB the, TIMED spacecraft and supporting.
hardware were off loaded to at, bed trucks and transported to the. Figure 1 TIMED spacecraft shipment The spacecraft inside the container is secured Payload Processing Facility PPF. for land shipment to Andrews Air Force Base, located several miles from the air. craft runway, The spacecraft itself was protected from the elements PAYLOAD PROCESSING FACILITY. and other hazards by a metallic shipping container This. container was under constant nitrogen purge supplied Site Selection. by boil off of liquid nitrogen from dewars that accom The remotely located PPF originally chosen by. panied the spacecraft at all times It was instrumented NASA Kennedy Space Center KSC for the TIMED. to record shocks and incorporated externally readable mission based on a competitive procurement was. gauges to measure the internal temperature pressure approximately 20 miles from the launch pad Space. and humidity Internal shock isolation mounts provided Launch Complex SLC 2W Selection was based on a. dynamic protection of the payload against jolts encoun requirements document produced by APL early in the. tered during transportation and handling events program and the ndings of several subsequent Ground. All loading and transportation activities were con Operations Working Group meetings involving Boeing. trolled and overseen by a mechanical payload team that NASA Vandenberg Range Safety and APL It soon. also accompanied the payload throughout its journey became apparent that the initially selected NASA. Constant communication links were maintained via facilities at VAFB were inadequate to support a dual. two way radios and cell phones between the payload payload i e Jason and TIMED attach tting mission. team and APL As a result NASA KSC instituted a competitive pro. Upon arrival at Andrews personnel inspected the curement between two available commercial PPFs The. cargo and ensured that the proper clearances and waiv APL requirements document served as a technical basis. ers had been approved and all hazardous materials were for contract bid evaluations and eventual award which. accounted for and labeled properly Equipment and the went to Spaceport Systems International SSI. spacecraft were then packaged onto cargo pallets for. rapid loading onto a C 17 military aircraft Figure 2. depicts the loading of the shipping container as viewed. from inside the C 17, Because of the requirement for continuous nitrogen. purge coupled with aircraft emergency contingency, planning e g unscheduled aircraft diversions due to.
weather or national emergencies aircraft maintenance. or mechanical problems encountered on the ground, it was determined that three dewars of liquid nitrogen. totaling 1080 L be shipped with the TIMED spacecraft. This was calculated to cover at least 9 5 days at full ow. rates The large amount of liquid nitrogen required. that the dewar pressure relief safety burst disk devices. be plumed and vented to one of the overboard ttings. located inside the C 17 aircraft This was done to ensure. crew safety should a rupture of a dewar burst disk occur. in ight Figure 2 Air Force C 17 loading operation Air Force personnel. direct the loading operations of the TIMED spacecraft within the. In addition to the onboard aircraft monitoring sys shipping container for the ight to Vandenberg Air Force Base in. tems the oxygen content of the cargo compartment Lompoc California. JOHNS HOPKINS APL TECHNICAL DIGEST VOLUME 24 NUMBER 2 2003 171. S R VERNON AND S F KOZUCH, The SSI commercial PPF Fig 3 the primary location at VAFB where team then removed the last bag. the eld crew equipment spacecraft and eld of ce were located was and hoisted the spacecraft into. designated as SLC 6W It contained clean rooms cranes a multilayer insu the processing cell mounting it to. lation MLI fabrication area storage for the GSE of ce space a precision a work stand for testing and ight. cleaning station forklifts and a dewar storage re ll station Onsite testing buildup The processing cell doors. laboratories fabrication capabilities and a metrology laboratory for tool and were closed and sealed from the. measurement calibration and certi cation were contracted out to various other facility clean areas to prevent. on base facilities organizations as required cross contamination from opera. The PPF was originally constructed for Space Shuttle payload integration tions of other payloads and tasks in. and subsequent West Coast launch operations Existing Boeing Delta IV preparation for launch vehicle LV. facility and launch pad modi cations were ongoing near the PPF during the mating. entire period in which the TIMED spacecraft was present but these con SLC 6W with its cranes air han. struction operations had no impact on the TIMED eld operations dling and cleaning systems power. systems communications systems, Contamination Control environmental controls and moni. toring systems proved more than suf, Once at the PPF the TIMED spacecraft was moved inside and the. cient for the TIMED mission Facil, shipping container cover and outer contamination bag surrounding it were.
ity personnel responded instantly to, removed The inner bag and shipping container base were cleaned and. any and all requests with creative, the system was rolled into the high bay clean room After the entry doors. and satisfactory solutions Contami, were closed the clean room was allowed time to stabilize to meet program. nation control and cleaning teams, requirements for temperature humidity and cleanliness The mechanical. performed with diligence care and, complete respect for the security of.
the payload Security 24 h monitor, ing separation of Jason and TIMED. personnel and hardware and access, to the TIMED spacecraft and sup. port equipment both during times, of activity and storage were all. under PPF personnel control, The spacecraft underwent nal. mechanical assembly installation of, MLI integration with the LV inter.
face hardware and separation sys, tems and nal software and system. checkout while still at the PPF, After buildup and checkout were. complete the spacecraft system was, readied for shipment to the launch. pad These operations and tests are, detailed in the section below. SPACECRAFT FLIGHT, BUILDUP AND FINAL, The TIMED spacecraft was.
shipped with several non ight, instrument aperture protective. covers in place but minus critical, power system components In addi. tion the ight MLI with the nal, ight coating applied needed to be. installed after most handling and, Figure 3 The PPF where the TIMED spacecraft was processed prior to transportation. to the launch pad top and another view showing its proximity to the Paci c Ocean assembly events were completed. bottom to keep from damaging the fragile, 172 JOHNS HOPKINS APL TECHNICAL DIGEST VOLUME 24 NUMBER 2 2003.
TIMED LAUNCH OPERATIONS, thermal properties of the MLI and radiator coatings the hot side of the spacecraft This maneuver is a 180. The completion of all remaining tasks preparations for yaw of the spacecraft along the nadir line The yaw. ight and veri cation of ight subsystems readiness are maneuver is conducted near a beta 0 orbit It also is. referred to as ight buildup and closeout activities conducted in shadow to prevent inadvertent sunlight. Flight buildup started when the mechanical team from shining on the cold side of the spacecraft during. mounted the spacecraft to the work stand in the PPF the maneuver. clean room processing cell 3 as noted earlier The At this point the spacecraft was in a con guration. spacecraft was then connected to the electrical GSE that enabled mission operations personnel to perform a. which had an active electrical interface with the space Mission Operations Readiness Demonstration as well. craft ight hardware as a 96 Hour Readiness Demonstration The former. TIMED was subjected to an electrical functional test consisted of a simulated countdown spacecraft separa. to verify post shipment performance i e to con rm tion de tumble and early orbit station contacts The. subsystem and instrument integrity after handling stor 96 h test which was started using TASTIE and solar. age and transportation or after exposure to environ array simulators simulated a week in the life of TIMED. mental testing This functional test was used to ensure and included spacecraft and instrument commanding. that the spacecraft would operate nominally through all during simulated station contacts The simulation. of its direct and cross strapped electrical interfaces As began when the spacecraft and instruments were. this was a nominal condition test it did not subject the nally put into the on orbit con guration Solid state. spacecraft to a wide range of test conditions for perfor recorder dumps were executed at each contact and all. mance assessment post contact data processing and distribution activities. After the successful completion of the functional were exercised. test a comprehensive performance test was conducted In parallel to the system testing described above. to verify performance speci cation parameters As such preparations for solar array integration were ongoing. it tested the spacecraft to speci cation extremes under Before solar array installation the wings were carefully. a wide range of scenarios designed to simulate on orbit opened and visually inspected to ensure that no solar. conditions and included in its design the following cells were damaged after almost 1 5 years of storage and. most critical criteria the subsequent shipping and handling events Also in. preparation for the spacecraft ight build ight fuses. Veri cation of all command and data paths between, housed in the Power Switching Unit solar array junc. components within the system, tion boxes and G C Attitude Interface Unit were. Veri cation of all subsystem and instrument opera, checked and installed in the Power Distribution Unit. tional modes, In addition ight batteries were removed from tempera.
Evaluation of all ight hardware and ight software, ture controlled storage and installed into the spacecraft. interfaces, in their nal ight con guration, Subsequent to the comprehensive performance Prior to nal installation of the last spacecraft. test an event driven simulation was conducted on the internal access panel quality control mechanical and. spacecraft s primary and redundant components This electrical teams independently veri ed that every con. simulation initially had TIMED in a normal on orbit nector ground strap fastener and tting was properly. con guration An electrical GSE GPS simulator and a secured for ight High resolution photographs were. guidance and control G C simulator TIMED Atti taken to provide the as built documentation re. tude System Test and Integration Equipment TASTIE quired should any questions arise at a later date The. provided inputs to the spacecraft to achieve the required structural y access panel was then installed and the. simulation which consisted of several simulated ground solar arrays were assembled onto the spacecraft The. contacts as well as a yaw maneuver see below The solar array pyrotechnic release devices were installed. intent of this event based simulation was twofold next and nal closeout of the spacecraft power sys. 1 to exercise intra subsystem data transfer and com tem was completed Additional closeout photographs. munications as much as possible and 2 to generate were taken of items that would eventually be hidden. as many of the event driven status ags as possible to by the MLI. exercise the responses from the respective spacecraft While the spacecraft system testing and closeout. subsystems and instruments activities just described were being performed instru. The yaw maneuver is a periodic event that needs ment teams and subsystem lead engineering and sci. to be performed on the spacecraft The spacecraft pre ence staff converged on the PPF and prepared their. cesses its orbit approximately 3 per day with respect instruments and sensors for ight Protective covers and. to the Sun After about 60 days the Sun has traveled high voltage sa ng plugs were removed and pyrotech. a full 180 Eventually the spacecraft must perform a nic deployment mechanisms were installed Flight MLI. maneuver to allow the Sun to continue to travel on installation was carried out as scheduling permitted. JOHNS HOPKINS APL TECHNICAL DIGEST VOLUME 24 NUMBER 2 2003 173. S R VERNON AND S F KOZUCH, After all closeout activities were completed nal. cleaning inspection and certi cation of cleanliness. were performed and the TIMED spacecraft team of, cially noti ed the Boeing launch service provider that. joint APL and Boeing LV integration operations were. ready to commence, LAUNCH VEHICLE INTEGRATION, OPERATIONS.
LV mating operations consisted of the following steps. in order ight payload adapter tting PAF integration. of the spacecraft into the dual payload adapter tting. DPAF Jason spacecraft integration transportation, canning and transport and nally LV integration. These steps are detailed below, PAF Mating and Clamp Band Installation. TIMED Launch Operations Steven R Vernon and Stanley F Kozuch ompletion of all ground based environmental testing of a spacecraft marks the start of the launch campaign Launch operations are the hand off point when the ground teams design development assembly and test relinquish control and responsibility to the launch vehicle provider and Mission Operations Team that will actually

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