Status Report

NASA Space Station On-Orbit Status 26 Feb 2004

By SpaceRef Editor

February 26, 2004

Filed under ISS, ISS On-orbit status, NASA HQ, US

NASA Space Station On-Orbit Status 26 Feb 2004 — 02.26.04.iss.jpg

All ISS systems continue to function nominally, except as noted previously or below.

After last night’s accomplished isolation of the U.S. segment (USOS), CDR Michael Foale spent the night in the second sleep compartment of the Service Module (SM). [“kayuta” size: 2.4 ft x 2.8 ft x 6.2 ft.]

Wake-up was at 5:55am EST, to a long and strenuous 10h15m-day.

Before breakfast, the crew completed the mandatory Russian pre- & post-EVA biomedical assessment MO-9/Urinalysis. [MO-9 uses the sophisticated in-vitro diagnostic apparatus “Urolux” developed for the Mir program. The device is first calibrated with prepared calibration strips (if not used for more than seven days) before receiving the measuring strips with the subject’s urine samples for automatic (photometric) analysis. LEDs indicate immediately if the data are within (green) or outside (red) the physiological norm, and they are also printed on a tape for report to MCC-M/TsUP (actually to IBMP, the Moscow Institute of Biomedical Problems).]

After breakfast, Foale and Kaleri worked through a detailed list of pre-EVA closedown activities in the Russian segment (RS), preparing the ISS for the unmanned period. [In the FGB, the VD ventilation air duct was disassembled and taken down to enable hatch closing. Preparations in the DC-1 docking compartment were mostly to ensure that all necessary equipment is in place (e.g., fire extinguisher, pressure gauge, lighting fixtures, medical kits, etc.). In the SM, Kaleri closed the protective window covers and deactivated the TVIS treadmill, the Rasteniya-2 and Akvarius payloads, the food supply subsystem (SOP), the condensate water processing system (SRV-K2), the thermal control system (SOTR), the toilet system (ASU, the Vozdukh CO2 scrubber and the ventilation system. In the SM, the crew also powered off the manual controls console (InPU) with its laptop, the pressure alarm sensors (DSD), the C&W (caution & warning) panel (PSS), the digital clock, and all laptops in the RS (5 Russian: Wiener, Paket, TR1, TR2 and EGE2; 5 US: SSC1-3, PCS and SSC Router in FGB).]

After removing the ventilation air duct extending from the SM through the DC-1 to the Soyuz TMA-3, including its interior fans, the crew verified the Soyuz’ readiness for its contingency use as a CRV (crew return vehicle). [This would involve using its orbital module (BO) as an airlock, a possible relocation flight from the DC-1 to the FGB to redock at its nadir port, or an emergency return to Earth. The hatch between the DC-1 and the Soyuz BO was closed but left unlatched.]

Later, the crew performed a checkout of the Orlan systems, as well as of the DC-1’s BSS spacesuit interface unit and BK-3 oxygen repressurization tank. Testing of communication links followed, including VHF/voice and biomedical electrode belt and telemetry hookups via the BSS (later by the wireless in-suit Tranzit-B radio telemetry system) for vital signs and equipment monitoring.

DC-1 hatches were closed at ~2:26pm. Inside the DC-1 Foale and Kaleri began suit donning and backpack sealing at ~2:36pm.

Next steps will be final checkout of suits and their controls, followed by successive stages of depressurization while checking for leaks. Pressure inside the Orlans will be reduced to 0.42 at (6.2 psi). After suit purge, a 30-minute oxygen prebreathe period starts at ~3:24pm, as pressures between DC-1 and the SM transfer compartment (PkhO) are equalized and then further reduced. A final leak check will be conducted of the BK-3 O2 tanks. At end of prebreathe, DC-1 pressure will be down to 15 mmHg (torr), holding for 5 min for a final cabin leak check, followed by switch to independent Orlan suit power at ~4:12pm and opening of the EV hatch at 4:14 am.

During DC-1 depress, station control will be moded to Attitude Hold, with SM thrusters enabled (to counteract any reactionary forces). After depress, they will again be inhibited for the spacewalk, to prevent pluming the crew and minimizing contamination potential, and attitude control is returned to the U.S. CMGs.

At 12:45pm, the U.S. solar array BGAs (beta gimbal assemblies) were set to Autotrack, which provides the best contingency-response capability during the EVA. SM solar arrays will be feathered at 3:50pm, and the 400 MHz transmitter of the ESA-sponsored GTS (global timing system) will be deactivated for safety.

At 1:20pm, both PCUs (plasma contactor units) on the Z1 truss were turned on to Discharge Mode. [The PCU is the best currently available means to prevent charge buildup (“static electricity”) on spacecraft structures which accumulates on them when high-voltage photovoltaic arrays (or ion thrusters, electrodynamic tethers, etc.) are operating in space. The station’s two PCUs emit a stream of charged xenon atoms (ions) into space, representing a “ground” to the environment, which prevents large charges from building up on the structure. They are activated for EVAs to prevent potential hazard of arcing damage or electrical shocks, although past measurements have indicated that EVA workers are in no danger of electrical shocks and discharges. The measurements have shown that the PCUs reduce the already low voltage by 3-5 volts. ]

At 1:30pm, the Lab RWS (robotic workstation) of the MSS (mobile service system) was powered up by the ground, along with the redundant string of the SSRMS (Space Station Remote Manipulator System). [The robotarm had been “walked off” to the Lab PDGF (power & data grapple fixture) on 2/10 to cover the EVA with its video cameras.]

EVA-9 will begin with egress from the DC-1 EV hatch at (nominal) 4:20pm EST, and is estimated to last ~5h 35min. Mike Foale will be EV1 (suit marked blue), Sasha Kaleri EV2 (suit marked red). While outside the station, they will rest during three eclipses (periods in Earth’s shadow) of 36 min. length each. [Objectives of the spacewalk are (1) installation of the Matryoshka radiation measuring equipment, (2) photography of two Japanese contamination monitors (MPAC, SEED), removal and swapout of foldable sampling panels (SKKs, removable cassette containers), (3) replacement of the Russian Kromka contamination monitoring SKK, (4) ATV (automated transfer vehicle) support engineering for EVA (removal/relocation of LSV laser retroreflectors), and (5) removal of a foreign object (Velcro strap) from the WA-2 ham radio antenna. A detailed list of additional photo imagery targets during the EVA was also uplinked this morning, specifying areas with damaged coating, potential contamination spots, close-ups of MLI (multi-layer insulation) condition and the region on the SM’s exterior where the still-unexplained “metallic” noise appeared to have originated on 11/26/03.]

After completing the EVA (at ~9:49pm EST), the crew will spend several hours reconfiguring the Soyuz TMA-3, the DC-1 and the RS to their initial conditions, essentially reversing the sequence of shutdowns executed this morning. [The retrieved Kromka-2 SKK container will be packed up and stowed, the also-retrieved Japanese MPAC & SEED panels temporarily stowed in the DC-1, comm systems returned to their nominal configuration, and Orlan suits & gear prepared for dry-out and stowing tomorrow.]

Sleep time begins at 4:10am tomorrow morning. Reopening of the USOS is scheduled for tomorrow (2/27), but Mike Foale may exercise his option to ingress his “home” already before sleep.

Today’s CEO targets (excluding Asia due to the current sleep cycle and North American and European targets due to winter weather conditions as well as all targets during and post EVA) were Niger River delta (Dynamic event. Few clouds predicted for this major but seldom seen delta. Good pass with the whole delta in view just right of track, close to the glint point), and Bahamas (coral reefs near the east end of Cuba should be unaffected by the cloud band draped across the Florida peninsula. Detailed images were requested).

CEO images can be viewed at the websites.

See also the website “Space Station Challenge” at

http://voyager.cet.edu/iss/

U.S. and Russian Segment Status (as of today, 1:00pm EST).

Environmental Control and Life Support (ECLSS) and Thermal Control (TCS):

Elektron O2 generator is Off. Vozdukh CO2 scrubber is Off. U.S. CDRA CO2 scrubber is on Standby (ready in dual-bed mode). TCCS (trace contaminant control subsystem) is operating. SM Gas Analyzer has been calibrated and is used for ppO2 and ppCO2 monitoring. MCA (major constituents analyzer) is in Life Extending Mode (LEM). BMP Harmful Impurities unit: absorbent bed #1 in Purify mode, bed #2 in Purify mode. RS air conditioner SKV-1 is Off, SKV-2 is Off (repair now completed; to be tested ASAP).

SM Working Compartment: Pressure (mmHg) — 742; temperature (deg C) — 23.4; ppO2 (mmHg) — 148.7; ppCO2 (mmHg) — 4.5;
SM Transfer Compartment: Pressure (mmHg) — 761; temperature (deg C) — 20.0.
FGB Cabin: Pressure (mmHg) — 756; temperature (deg C) — 23.7.
Node: Pressure (mmHg) — 755.34; temperature (deg C) — 22.3 (shell); ppO2 (mmHg) — n/a; ppCO2 (mmHg) — n/a.
U.S. Lab: Pressure (mmHg) — 757.64; temperature (deg C) — 25.0; ppO2 (mmHg) — n/a; ppCO2 (mmHg) — n/a.
Joint Airlock (Equip. Lock): Pressure (mmHg) — 757.34; temperature (deg C) — 25.7; shell heater temp (deg C) — 24.2, ppO2 (mmHg) — n/a; ppCO2 (mmHg) — n/a.
PMA-1: Shell heater temp (deg C) — 22.1
PMA-2: Shell heater temp (deg C) — 19.2

(n/a = data not available)

Electrical Power Systems (EPS):

Both P6 channels fully operational. BGA (beta gimbal assembly) 2B and 4B both in Autotrack.
SM batteries: All batteries (8) are in “Partial Charge” mode.
FGB batteries: Battery #3 is off (capacity restoration mode, ROM); all other batteries (5) are in “Partial Charge” mode.
Plasma Contactor Unit PCU-1 in Discharge mode; PCU-2 in Discharge mode.

Command & Data Handling Systems:

C&C-1 MDM is prime, C&C-2 is back-up, and C&C-3 is in standby.
GNC-1 MDM is prime; GNC-2 is Backup.
INT-2 is operating; INT-1 is Off.
EXT-2 is On (primary), EXT-1 is Off (both now upgraded to R3).
LA-1, LA-2 and LA-3 MDMs are all operating.
PL-1 MDM is Off; PL-2 MDM is Operational.
APS-1 (automated payload switch #1) and APS-2 are both On.
SM Terminal Computer (TVM): 2 redundant lanes (of 3) operational (string 1 dropped out 11/22).
SM Central Computer (TsVM): 2 redundant lanes (of 3) operational (string #3 dropped out 10/22).

Propulsion System:

Total propellant load available: 4070 kg (8972 lb) as of 2/12/04 [SM(755) + FGB(2656) + Progress M(0) + Progress M-1(659)]. (Capability: SM — 860 kg; FGB — 6120 kg).

Attitude Control Systems:

3 CMGs on-line (CMG-1 failed).
State vector source — U.S. SIGI-1 (GPS)
Attitude source — U.S. SIGI-1 (GPS)
Angular rate source — RGA-1

Flight Attitude:

LVLH XVV (local vertical/local horizontal = “earth-fixed”: z-axis in local vertical, x-axis in velocity vector [yaw: -90 deg, pitch: -9 deg, roll: 1.7 deg]), with CMG/TA (thruster assist) Momentum Management.

Communications & Tracking Systems: